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DOCUMENT HISTORY OF DISCOVERER

IISTIRY IFFICE

CHIEF IF STAFF

SPACE AU MISSILE SYSTEMS MANIZATI1N

AIR FIICE SYSTEMS CINMANI
•

of the

Title 18, U. .

revelation of its co

is prohibited by law.

ument contains information affecting the

es within the meaning of

Lions 793 an •

ease •

ge Laws,

s transmission or the

r to an unauthorized person

•

THIS DOCUME

OR AGENC

WITHO PRIOR APPROVAL OF THE OGIG

OR A HIGHER AUTHORITY IN THE DIRECT L

i

O ANY INDIVIDUAL

AIR FORCE

RGANI-

•

DOCUMENT HISTORY OF. DISCOVERER

Prepaied under the provisions of Air Force Regulatioh . 210-3 and

Air Force Systems Command Supplement No. 1 thereto as part of

the United States Air Force Historical Pro ram.
Pi-epared by

S. A. Grassly

•

DOCILNIENT HISTORY OF DISCOVERER

VOLUME 1

is 

•

NoveMber 1971

IF MICROFILM COPTIS ART:: vaiur, OF

TIME. DOCUME1411S, PLEASE MD

Doctteurs TO AFSC CO:NAED HISTOP.T1

History Office

CHIEF OF STAFF

SPACE ANDI NISSILS SYSTEMS ORGANIZATION
viDDAFZIWSSD/SAMS0

DOCUMENT HISTORY OF DISCOVERER

VOLUME 1

Prepared under the provisions of Air Force Regulation 210-3 and

Air Force Systems Command Supplement No. 1 thereto as part of the

United States Air Force Historical Program.

hi: . •t contains information affecting the national e

United Sta .

in the meaning of the Espionage e 18, U. S. C.

Sections . 793 an • is transmission or ation of its contents

in any manner to an un ' ed pe prohibited by law.

THIS DOCUMENT ME TO ANY INDIVIDUAL OR

AGENCY OUT THE DEPARTMEN )4 b'- TM EN - AIR FORCE WITHOUT T • • APPROVAL OF THE ORIG/NA ' k. Z ATION

O -1GHER AUTHORITY IN THE DIRECT LINE OF CO '• • -

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A

LIST OF SUPPORTING DOCUMENTS

HISTORY OF DISCOVER

1. ARDC Weekly Activity Report, 4 Feb 1957 (Integration of Qualitative

Personnel Requirements Activities at Western Development Division).

2: . AFDC Form 111 (C/0p3), Title: ' Advanced Reconnaissance System, 31 Jan

3. R4 Document am67.3-19, subj: Proposed Use of IRBM as Booster for

Multi-Stage Vehicles, 1 Apr 1957.

•

57•

DD Form 613 (C/Gp3), Project Number: 176k, 2 Apr 57.

DD Form 613 (C/Gp3), Project ',Umber: 8727, 2 Apr 57•

6. Ltr, The Ramo-Wooldridge Corporation to Col E. N. Hall, from R. F.

Mettler, subj: Transmitting copy of om67.3-49, 3)May 57, w/o

2iclosure. /Pee inclosure under date of 1 Apr 52/.

Memorandum for Colonel Terhune, subj: AFPTRC Support of WDD System

Development, 23 Jul 57.

Memorandum for WET and WDO, subj: Joint WDTN andWDODA Staff Visit

Report to Hq ARDC on Elimination of AFPTRC as a Separate. Center of

ARDC, 19 Nov 57.

Memorandum for the Record, subj: Telephone Call from Colonel Nunziato to

General Bitland, 31 Dec 57.

Msg, from Comdr AFBMD to. Comdr Eq ARDC, WDG-1-2, 3 Jan 58.

Ltr (C/Gp3), Lockheed Aircraft Corporation to MejGen Bernard A.

Schriever, subj: Contract AF 04(647)-97, Proposal for Acceleration

of WS 117L Program, 6 Jan 58.

Development Plan (C/Gp3), cover and introduction only for WS 117L,

6 Jan 58.

Conference meg regarding ABDC Five Year Projected Astronautics Program,

6 Jan 58.

14. Ltr (C/Gp3), WDP to Chief of Staff USAF, BUN: Thor Program Acceleration,

6 Jan 58, 144 inclosures: 1. Program Summary; 2. Fund' Summary; 3. Augmented

Schedules; 4. Fund Summary (R8a-Augmentation).
15. Ltr, AMC (OEN) to Comdr AFEMD, subj: Elimination of AFPPBC and

Assignment of Specific Human Factors Functions to AFBMD, 13 . Jan 58.

Memorandum for the Record, WDTD, subj: Long-Distance Call from

Colonel Attvood - ARDC - re "Recoverable Package," 13 Jan 58.

4

Memorandum Tor the Record, MCPTA, subj: Plan for Acceleration of

the WS 117L Program, 21 Jan 58.

5.

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4

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ixs

Meg, from Hq USAF to Comdr AFBMD, Cite MGM 55420, 211805Z Jan 58.

Msg, from Hq USAF to Comdr AFBMD, ' cite AFCGM 39578, 222106Z Jan 58.

Msg, Mg USAF to COmdr ARDC, info Comdr AMMO, Cite AFDDC-SP 55521,

2222142 Jan 58.

Weekly Diary - 16 thru 23 Jan 58 from =PTA to MaIeffitme/ms7,

23 Jan 58.

Memorandum for Record, WDTIM, subj: Lockheed/Douglas WS-117L Co-ordination Meeting, 27 Jan 58, 28 Jan 58.

Meg, Hq USAF to Comdr AFBMD, info Comdr AFB?i/AMC, Cite AFCGM 56224,

0615432 Feb 58.

*24. 'Mem to File, subj:Mmu.-II7L "integration, "12 "Ifcb 58.

Memorandum for the Secretary of Defense (c/cp3), subj: Thor and

WS-117L Program,•14 Feb 58.

Meg, Attn: Colonel F. C. E. Oder murilt, from F. W. O'Green, Lockheed

Missile Systems Div Alto Calif, subj: WS 117L - Reconnaissance

Capsule, 18 Feb 58.

Memoranda& for the Director of Guided Missiles, OSD, sgd Malcolm A.

MAcIntyre, Under Secretary, 21 Feb 58.

GO No. 11, ARDC, 27 Feb 58.

OSD Memorandum (C/Gp3), for Secretary of the Air Force, subj: Reconnaissance Satellites and Manned Space Exploration, 28 Feb 58.

Meg (C/Gp3) from Camdr AFBMD to Lockheed Aircraft Corporation, 12 Mar 58.

Memorandum for the Record, WDGE, subj: Call from Colonel Oder in

Washington to Colonel Hamilton, 13 Mar 58.

WMTSR Memorandum for Major General Funk (C/Gp3), subj: Reorientation

vs 1].7L Program IIA, lk Mar 58.

33. Nemorandum for the Director, ABIV.1 OSD, subj: Air Force Man-in-Space

Program, 19 Mar 58.
1

s!- 34. Memorandum forVice Chief of Start, sgd MajGen J. S. Mills, subj:

Man in Space Program, IN) Mar 58.

s

35• =SR Memorandum Colonel Terhune, alibi: Reply to Inquiry, 24'14=56.

il 36. Msg from Comdr ARDC to Comdr APBMD, Cite TWS 03-24-06, 242015Z Mar 58.

37.' WS 117L Project Office New Phone Extensions, 17 Air 58.

38. Memorandum for Colonel. Evans, sgd Col C. R. Terhune, Jr. subj: Man

in.Space Responsibilities, 28 Apr 58.

3' .

(.T 39. . WDQQ . Memorandumt for Col Terhune, sgd Erigdeil 0. J. 'inland, subj:

k 40-Medical, 2hor BoostedWS 131L Program, 5 May 58. '6

40. Ltr from Lockheed Aircraft Corp to Comdr AMID, subj: Contract No.

AP 04(647)-181 Biosatellite Flight Plan, 6 May 58.

t; 41. Ltr. (S/Gp3), ARDO. (RDZOW) to Comdr' APBMD, subj: Support of Bioastro-

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nantids Program, 22 May 58. '

1..;. 42. GO No. 18, ARDC, 22 Nay 58.

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'' (I .43.. .Futratiorml,Statemeut-Zuman Factors •Division, 12 .Jun . 58.

('' 44. Memorandum for the Director, ARM (C/gp3), sid Malcolm A. MacIntyre,

Under Secretary, 12 Jun 58.

45. Department of the AF Memoranduni for the CofS, USAF, (C/Op3), 24 Jun 58.

A 46. Msg from OSD to Candy BMD, Da 9449114, 1717592 Jul 58.

i. WDT Memorandum for Colonel.Riepe, sgd Col Charles H. Terhune, Jr.,

subj: Schedule Slippagi 117L Program Ilk 28 Jul 58, w/1 Incl,

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Memo for Gen Schriever, subj as above, no date.

DH from WCPTA to )CPT, subj: Authorization for Type of COntract,

'A. . 30 Jul 58, w/o atch.

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* 49. Msg from Ccmdr, AFBilD to Comdr ARDC, 1. Aug 58.

Nag (C/Gp3) from Hi USAF to Comdr AFBM, into Comdr ARM, AFCGM 54161,

061938Z Aug 58.

Ltr, ARDC (RBIS) to Comdr Air University, subj: Responsibilities of

School of Aviation-Medicine in the ARDC Biosatellite Program, Sub- :.

System L WS-117L, 12 Aug 58.
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Ltr, AFBMD (VMMSR) to Lockheed Aircraft Corp., subj: Contract 04(647)-

181, Internal Air Force Responsibilities Concerning Biosatellite

Programs, 4 Sep 58.

ARPA Order No. 17-59, 4 Sep 58.

54. Hag from Comdr AFBMD to Comdr PMR, info AF Liaison Office, PMR,

mmil-9-14-31 14 Sep 58.

55.. ARPA Order No. 17-59, Amendment No 1, 29 Sep 58.

ARPA Order No. 17-59, Amendment No. 2, 17 Oct 58.

ARPA ltr(C/Op3), to Comdr ARDC, no subj, 25 Nov 58 - •

_ .58. ARPA Order No. 17-59, Amendment No. 3, 26 BOIT 58, v/2 Atch: 1. Preparation of Monthly Progress Report; 2. Vehicle Requirements List.

Nag from Comdr ARDC to Comdr AFBMD, RD W-11-39-E,262100Z Nov 58.

ARPA Memorandum for the Secretary of the AF, (C/Op3), subj: WS-117L

Program, 4 Dec 58.

ARPA Memorandum for the Under Secretary of the Air Force (C/O 3),

subj: Discoverer-Thor Project and Sentry Programs, 5 Dec 58.

Meg from Hq USAF to Comdr ADM, info Comdr ARDC, 37375, 052240Z,

Dec 58.

z.lsg (C/cp3), from CSD, ARPA, to Ccadr ARDC, info Comdr MUD,

D2 F 951903, 0522223Z

ARPA-Order No. 48-59 (C/Op3), 16 Dec 58, x/1 atch: Preparation of

3 . RepOrts.

'WM Memorandum for Gen Schriever, subj: Discoverer Launchings,

30 Dec 58.

Hag (C/gp3) from Eq USAF to Comdr AFBMD, info Omar ARDC, AFDAT 54519,

3015207 Dec 58.

Contractor NC/power Status Iockheed-AP (01(647)-97- 181, 31 Dec 58.

Meg from Comdr AFBUD to Comdr Lst Missile Div, info AFBMD Field Office,

WI-1-38.E, 3 Feb 59.

P

67.' Chart, Financial Management Status, Lockheed AF 04(647)-97, 181,

A 31 Dec 58.
asg from Comdr Missile Div to Comdr A?BZID, info AYJ3M]X Field Office,

Vandenberg AFB, 0523582 Feb 59.

k

Ltr (C/Gp3), wraw to Comdr ARDC, subj: WS 117L Program, 11 Feb 59-

ARPA Order No. 48-59, Amendment Mo. 1, 16 Feb 59.

Hag from Comdr AFBICD to CofS, USAF, info Comdr ARDC, WDPP-3-1,

7 Mar 59.

Nag from Comdr AFBMD to Dir ARPA, Info CofS USAF, Comdr ARDC,

Lockheed Missiles and Space Div, Ch, AFBMD Field Office, Palo Alto,

WDZW 3-15-E, 17 Mar 59.

Esg from Ng USAF to AFB, Info ARDC, AYAPF 57888, 1814472 Mar 59.

Ltr, AFBED (WDTI) to Mr. Donald W. DoviUs, Jr., President, Douglas

Aircraft Company, Inc., no subj: 18 Mar 1959.

ARPA Order No. 48-59, Amendment Ho. 2, 24 Mar 59.

ARPA Order No. 48-59, Amendment No. 3, 1 Apr 59.

AEPA Order No. 17-59, Amendment No. 4, 10 Apr 59.

ARPA Order No. 17-59, Amendment No. 5, 13 Apr 59.

Ltr, MED (WD) to Mr. L. Eugene Root, no alibi', 20 Apr 59.

Hag (c/Gp3) from Hq Usaf to Comdr AFBMD, £?.WIT 59353, 272359Z Apr 59.

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WDD Routing Slip, 29 Apr 59.

Nag from AFBMD-ABLOANC-BEC to Lockheed Aircraft Corporation, L3JP-4-15-E

29 Apr59.

Ltr AFBMD (tWDZW) to The Honorable Malcolm A. MacIntyre, no BUN,

1 May 59.

Discoverer Monthly Program Progress Report, 8 May 59.

ARPA Order Ho. 17-59, Amendment No. 6, 18 May 59.

AFBMD (wig) Memorandum for AFBMD Directors, subj: ARPA Order 17-59

(as amended), 18 May 59.

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80.

I s 81.

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84.

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II 85.

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Ltr (C/Gp3), AFBMD (WDTR) to Director of Laboratories, WALL, subj:

Short Title:. ICSMCOD, 3 Jun 59.

Para 41 Weekly Diary - 11 thru 18 Jun 59 from BMC (LBO 18 Jun 59.

ARPA Order No. 17-60, Amendment No. 8, 1 Jul 59.

ARPA Order No. 48-59, Amendment No. 4, 20 May 59.

93.. Discoverer Progress Report, 31 Kay 1959, dated 8 Jun 59.

ARPA Order No. 48-59, Amendment No. 5, 23 Jun 59.

ARPA Order No. 48-0, Amendment No. 6, 20 Jul 59.

Discoverei. Program Progress Report, 31 Jul 59, dated 7 Aug 59.

AFSMD Ltr (WDZPB, to MajGen Otis O. Benson Jr., Commandant USAF

.School of Aviation Medicine, no subj, 18 Aug 59.

Discoverer Program Progress Report, 31 Aug 59•

ARPA Order No. 48-60, Amendment No. 7, 8 Oct 59.

100. AFBMD Ltr, (WDG), subj: Investigating Committee, 29 Oct 59.

. .101. Discoverer Program Progress Report, 9 Nov 59.

Management Report, Advanced Reconnaissance System, 13 Nov 59.

Secretary of Defense Memorandum for the Secretary of the AF subj:

Transfer of the Discoverer Development Program to the Department

of the Air Force, 17 Nov 59.

SO Number 20, AFBMD, 27. Nov 59.

ARPA Order No. 48-60, Amendment No. 8, 3 Dec 59.

106. SOD Memorandum for the Asst Secy of Defense (Comptroller) (C/Gp3),

7 Dec 59.

107. mgg, 8/43) from Bq USAF to AFRO and ARDC, AFABF and =DP 73993,

271712Z Feb 6o.

Ltr (C/Op4) from AFBMD (UDOYD, subj: Procurement of Four Follow-on Agena

Vehicles for Discoverer Program, 14 Mar 6o.

Ltr (C/Gp4) from AMC/BIC (LBZJR, subj: Discoverer Schedule Revision,

4 Oct 60.
Ltr (S/Gp3), Dept AF (APTSD-AT) to ARDC,sNbj: Erploitation of Initial

SA10S Data, 1 Jun 60. .

Ltr (C/Gp4), k4C/BMC CIABZJR to LMJP, subj: DISCOVERER Schedule Revision,

A 4 oat 60.

• 112. .Msgs from HA ARDC, RDGP-12-10-2 and RDOP-121,10-1, 12 .Oct 6o.-• .

113.. Meg fram AM MD to Miseiles and Space Div Lockheed Aircraft Corp,

WDE 24-10-179, 24 Oct 60.

Meg from 14. USAF to ARDC, info AFBMD, AF Air Museum, SAPOI 90547,

282054Z Oct 6o.

Ltr Hq AMC to LtGen B. A. Schriever, 2 Dec 60.

Ltr ARDC (RDE), subj; Anniversary Flight. Ceremonies, 7 Dec 60.

hag from ARDC to AFEMD, RDEP 7-12-16, 0719241 Dec 60.

Nsg from fq ARDC to AFBMD, RDEI 8-12-19, 082043Z Dec 60.

Msg from AFBMD (WD EC) to WDG, subj: Presentation of Discoverer XIV

Capsule, 9 Dec 60.

220.'..--ggested Pemsrk for NajGen O. J. Bitland CommanA v*, AFBYT, at tau

Wright Day Luncheon, 16 Dec 60

121. News Release 61-30, subj: Mackey Trophy for 1960.

1

L, 122 SAFOI-3B Biomedical Release, 12 Jan 61.

I 123. Discoverer Program Chronology, 1 Jul - 31 Dec 60, (C/Gp4), 24 Jan 61.

is

4• 124. 552 Airborne Early Warning and Control Wing (ADC) News Release: 1-4,

17 Feb 61.

Ltr, AFBMD (WDEJS-1, subj: Request for PR Initiation, 13 Mar 61.

AMC (LBZJP) ltr, subj: Authorization for Type of Contract, 28 Mar 61.

Ltr (S/GP3), from Comdr, PNR to Comdr AFBMD, subj: Bioastronautics

Orbiting Space System (BOSS) Development Plan; comments on, 28 Mar 61.

Nag (S/300 from ft AFSC to SSD LosA, SCG 10-5-27, 102210Zlimar 61.

Ltr (S/Op3) from AFSC (SORBS) sgd LtGen 3. A. Schriever, to Rq USAF

(AFDDC), subj: Bioastronautics Development Plan, 16 May 61.

Ltr (C/Gp4) from SSD (SSF) to LtGen B. A. Schriever, subj: De;e10-lxueat

Plans in Support of Five-Year Space Plan, 31 May 61.

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Ltr (S/Gp3) from Eq USAF (APART) to ATC and AFSC, subj: Radiation

Shielding, 8 Jun 61.

Ltr (S/Qp3) franift USAF (AFFDDO) to AFSC, subj: Bioastronautics

Orbital Space Program (BOSP), 12 Jun 61.

133. Ltr (WOO) from HQ, AFSC (SCABS) to SSD (AFSC) and ATC, subj:

Bioastronautics Orbital Space Program (BOSP), 22 Jun 61.

134.. Discoverer Milestones, 12 Jul 61.

MFR (C/Gp4), SSRBT-2,subjki,PrelisineWilata on Disc 27 Flight

Failure, 24 Jun 61.

Memorandum for MajGen Ritlend, subj: Routine and Special Investifations and• Analysis of Discoverer Operations, Aug 61.

Meg (C/Gpl) from l G. A. Levine, Sunnyvale, Calif, to SSDISSZD, subj:

ROM Quotation for Additional Discoverer Vehicles Nos 1129, 1130 and

1131 to Discoverer Contract AF 04(647)-673, 1121358 Aug 61.

UPI press release, 28 Aug 61.

DOD Instructions, subj: Policy on Experimental Animals in Department

of Defense Research (No. 3216.1) 1 Sep 61.

Ltr, Department of State, Washlngton, to Mr. • Huntoon, 15 Sep 61.

Msg (S/( 3) from OSAF to AFSC, DCAS, LosA, SAPS 83174, 0422062

Dec 61.

UPI and AP News Released, 12 Dec 61.

Ltr (C/Gp4) from Hq PMR to Comdr SSD, AFSC, subj: Space Program

698AA (BOSS) Development Plan; comments on, 11 Jan 62.

ADO No. 35 (C/Gp3), subj: Advanced Development Objective for a

Bioastrtnautical Space Test Program, 18 Feb 62. .

.

Ltr from SSD (SSZDB) to SSVX, subj: Discoverer Performance Improvement,

27 Feb 62. •

Ltr from SSD (SUB) to SSVXX, sUbj: Thorad Jr DSV-2C Study for

pis Discoverer, 2 Mar 1962.

Ltr (uncl w/o atch) from SSZLT to SSEH, subj: 622A. Program Summary --

Historical Report, 23 Jul :2, v/1 etch: 622A Historical Report.

Memorandum for the Under Secretary of the Air Force, subj: Joint

Air Force/NASA Bioastronautics Program (698 AA), 23 Jul 62.
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(:149. 1 Msg (C/Op4) from Hq USAF to SSD LosA andIeSA, AFRAE-S-4, 122147Z

Sep 62.

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150. Msg (C/Gp4) from Bq USAF to AFSC, OAR, info SSD, LosA and AFCRL,

AFRST.82769, 142119Z Sep 62.

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151. Msg e0p4) from. Hq USAF to AMC and SSD LosAl AFRAE-S-4, 0141435Z

$: Dec .

152... History Program 162 CY 1962, (C/Qp4). ;.-e

153.:_Relocation List, 31 Jan 63.

Background of Biomedical Capsule Development, Jun 63.

History or Program 162, 1 Jan 63 to 30 Jun 63 (S/Gp4).

Ltr from SSD (SSZ) to AFSC (NSF), subj:-AF Support of Bioastronautics

Program 698AA, 2 Aug 63.

Ltr sigd gajGen Ben I Funk to AFSC (MRF), subj: Air Force Support

of Bioastronautics Program 698AA, 26 Nov 63.

Ltr from AFSC (SCG) to SSD (SSG), subj: Program 698AA, 9 Dec 63.

Ltr (C/Gp4) from AFSC (SCG) to SSD (SSG, Gen Funk), subj: Manned

Space Program, 16 Dec 63.

History of Program 162, 1 Jul-31 Dec 63, 8 Jan 614 (C/Gp4).

Nsg. (C/Gp4) from AFSC to SSD LosAl - YAF' 373-2, 0322292 iimr_64.

Nag (C/0p4) from SSD LosA to Mar, SSGO -3-7, 6 Mar 64.

S0 Ps-17, SSD, 1 Apr 64.

SO PB-22, SSD, 22 Apr 64.

History of Program 162, 1 Jan 64 to 30 Apr 64, 21 Aug 64.

News Release 65-149, 31 Aug 65.

Appendix to History of Discoverer, List of Launches, 21 Jan 59 to 27 Apr 64.
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(unlAssxma)) nrremknoil o warrATIvE PrZSONNEL nixlmsfrars

ACTIVITIES AT WESTMli DEVELOPHaT DIVISION:

• (UNCLASSIFIED) In My. 1956, ATP= established a liaison office

at WDD for the purpose of coordinating Qualitative Personnel Requirements activities. Since that date, personnel and training require-

.

nents studies have been initiated on all weapon systems being developed

by WDD. Two formal reports have been issued on System 107A-1, and an

initial report published on System 315A. An initial report on System

107A-2 is . seheduIed for April 1957. The impact of these studies on

development activities is much greaterldlexARIC has been assigned

responsibility for the Initial. Operational Capability since AR DC

becomes the implmenting agency in theft cases. The QPRI reports

have been used to prepare manning documents, determine over-all training requirements, plan trcininz courses, and to provide a source of

data for technical manuals. In vier of the above, it is apparent

that a satisfactory and useful QPRI program has been established at

WDD. (RDTDJT, Capt. Nichols, ext 32).

copied from ARDC Weekly Activity Report dated 4 February 1957 ne1T-57-468.

C7-40605, pages 6 and 7. •

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BAR 6 1957

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(3) Reviews reports of precreaa finliuse receive. tratt

contractor or other agencies pert rchrtne to Paraobnol reVirel=tss

trairdng earl personnel evaluation. lititna rocannizna•Itions to acceptance

of. these reports sal for invleaentIng RS13 oaboones in system opei•atione•

14) Determine° requirements for technical assistance, infornation

and services of various Arnie sae-mists, or other Air Force a:sencies, ar4

previews teebnicts/ atallirbence as requIreret b' WDO, lakes apriroriztate recteznt,

for seeletenoe in the planning anti. conduct of 'lark for which IMO is

*Me. •nn

Coonlinstce peroonuel oat training R c4tivities N:ith other

offices of WDO, end with other Air POrCO tiattnieft p3rticirAtinG in the

lemma factors pogrom.

Estaliebse pros cures for the mutual er.chege inferesatten

betseen ITDD ale AFFISIC. •
t •

DRAFT

ApprRdiniEcrlys

SUBJECT: APPTRC Participation in WS•107A and WS•415A

Purpose. The purpose of this document is to define the participation

of AFPTRC in WS-107A end VS..315 and to.indicateu, manner of ' integrating this

effort with the other portions of the human factors program.

Imam. This document reflects the methodology and procedures to be

- employed in 00 human factors program as vistalised at this time.

3. Responsibilities:- APPTRC is deiigneted the responsible agency . for the

completion of the .tasks defined in AIDC Rag 2214. The tasks which are of

greatest interest to this project are; •••

Qualitative Personnel Requirements Information (QP?../)

Proficiency Standards and Evaluation - both individual and team.

Command Communications OperatilitY.

Control of.liercle Factors.

e. Social and Community Relation. Studies.

..,

:I 4. ..plarizaion. -The accomplishment of some of . the tasks listed above will c.n

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be aided by the use of a dynamic system mockup, a simulation device or array of

devices that will react to oontrols and display information in the sea mhaer

as the operational system. This dynamic mockup will also. be uses for other Illv.v..s.

..

factors work such as human enginering, andalsy also be used in the training or

r. cadre personnel. To obtain optimum results, the dynamic mockup willbe built vudc:

h

the sponsorship of WDD and will be controlled by a staff reprasentins all Luterei

agencies. The location of the mockup and the exact composition of the oparatil.

effectiveness staff have not been decided at this time; the planning in przzre..:A:

now is aimed at providing the most complete and efficient program.

5. Immediate Procedorea. Vatil such timt as the eatire fectors

Firctroz t'.-is been aplircved and implemented, thc follwina bc

by APPTY.C:
. _

u. Ceneratiee of QUI from the data provided them by the esseciat,i

eft:tractors. The TechniCal Directive establishing the procedures for the

Contractors to provide this information has bean issued to those major Coatrector4

associated with WS•107A.. •

b. The establishment of a Speciallroject Officer in residence at

WDD, to be empowered. to represent APPTRC on all matters within the ecopo of

approved WDD human facture program. The representative will be attached to WDO.•

a

Administrative suppo

•

 rt for the office *will be provided by % however, the

nature of program development ai

▪

 d the faection•involved require that this

officert e services be avallehle to all staff agencies of vto. His duties will

4

be as followc:

(1) Provides infersetion to MO staff agencies on status, plane

and progress of all activities of personnel andtreinins

R&D activities related to wespoin . system development far whie4

MUD. is mellow:lb/a. Specifically, these activitlas

Qualitative personnel requirements information.

Participative in operations and personnel anel7eLe

program.

(a) Individual. and teem training studien.

(d) Relevant portions of the APPTRC technical program.

• Pbrmulates and recommends requirements to WDO porta:inter,

to R&D activities in the personnel and trebling erea.

Revises reports of progress and findings received CI=

Contractor or other agencies pertaining to persounnl

requirements, training and persounel.evaluation. /1,1%.ts

recemmeudarieee acc'eteeac of the rsports

1:mplcmZetipa LW. cutcomen it; cyst 'm opnretizus.

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(4) Determines rdquiremente for technical apsietance, informrtion

and'servicee of various AVM agencies, provides personnel

technical assistance as reqUired by iiMe. and/or cakes.

appropriate reqUests • er Such assistance in the planning and

conduct of work for which ADO is responsible.

..

(5) Coordinates An= person*. and . training R&D activities

• •

•

participating in the human lettere pregram.

(6) : Establishes procedures for the mutual exchange of inform-Um

between WA!) and AMU.

. .

. . -

with other offices of VDO, and with other Air Force sigecriae

-3-
.

0 ACTION ammo

.

SYSTEAL

.411144444,,g • ' 16SISPORTO CONTROL triNICI.. 0 ,... CHANGE a OGNIFICANT non 0 Blum

•

• MANAGEMENT IMPORT AGATE 

i or PAO

jiD2 .i......;2....................A.......LaUwuy...1252. ltO CT ,J1 TASK 0 amosonutan SOWN*

$. .

. 1 . a

S. Nu man

Icansklkr:intgtt---

• HQ ARDC - VIDD

4. MIX .

(U) Advanced Reconnaissance System

. •

. . • • . ,

• %Kw OMNI

.

WDD-WDTR

Is PARTICIPATING COMM .

. •

. AFCRC, WADC, RADC, AIPTRC

Oa PROGRAM STRUCTURIL

100

IS* PANTICIPATIRWGIVIMIDINATIONANTIONNT.

. .

USAF/AMC-P, APGC-P, ATC-P, SAC-C, ADC-C

USN/CND-1, USA/C/S-I, Other /.CIA-I . .

I It TINNINICAL 41110410,

. .

. •

02

lie AVOLICASLIS ARRAS . - .

As 0 TILCOUNC AL /

So 0 TINT . II. OPIUM. O. 014ATORIZI. a. 0 544ms Tsa:

'.0 ININPOIVRII •

Re ,C3 PRI1140104111. N. 0 TRAININ6 I. (t) ceoessialys J. D AIRCRAFT

Ilk NARRATIVIC

a. ,Authorization to obligate an additional $2,0004000 beyond the

viously authorized for System 117L was, received 7 December 1956,

AFDDP-11 33590.

• • b. Letter Contract A1134(647)-103 was lot with the Massachusetts

nology on 25 Jan 1957. Work to be performed is in the Guidance

area. Funds allocated against this contract total $500,000.

Authority to obligate up to a total of $10,0001000 for FY 57

program in TWX, HQ ARDC RDSCBC-1-16-E, dated 15 Jan 1957, was received.

Subsystem Project Plans are in the process of being written

and task number assignments have been established. Upon completion

of the Project Plans, a revision will be made to the System Development

Target date for completion of these actions is the anniversary

Development Plan, 2 April 1957.

Inclosed is a list of project number and task number assignments

the process of writing Project Development Plans.

(1) PR #57-WDD-196-I dated 22 Jan 1957 was initiated to add

Lockheed Aircraft Corporation Contract A? 04(647)-97.

.(2) OA #57-17 dated 25 Jan 1957 was initiated to transfer

continued effort in the Data Processing and Dissemination. area

(3) OK #5745 dated 25 Jan 1957• was initiated to transfer

continued effort in research on conversion equipment for nuclear

units and for continued research on solar auxiliary power units

. ...

(4) '''OA #57-16 dated 25 Jan 57 was initiated for transfer of

for continued research in the Geophysical 'Environment Area for

" )

1111111111.111

$3,000,000 prein TWX, HQ USAF, V/

. '

.

Institute of Techand Control problem

on the WS 117L

and Project number

of the writing

Plan.

date of the WS 117L

made duriu3

$5,563 000 to the

$320,000 to RADC for ,

for WS 117L.

$195,000 to WADC for

auxiliary power

for WS 117L.

$422,000 to AFCRC

WS 11Th. .

• 1101.111011.LN..........

- . ..''it:;:;

WD-57-00437

ARDC I P,,:i:agg PREVIOUS EDITIONS OP THIS PORI. ARE OSSOLETE.

mesot000 • wanotot. it

ANL.. VA. ION IC
i.

p.

c .

4

4 

Advanced Reconnaissance System

S.

31 January 1957

•

g. The aummary of FT 57 funds initiated on WS 117L id: . •

•••nn

Lockheed Aircraft Corporation AP 04(647)-97 $8,563,000

Massachusetts Institute of • AF 04(647)-103 500,000

Technology .

.

WiDC • GA #57-15 - 195,000

UDC OA #574/177 320,000

AFCRC #57-16 422000

OTAL $10,000,000

,- h. Reproduction and distribution of this report is forbidden except . on express

approval of the WS 117L Project Office.

C.

•

1 Incl

Project Number Assignment

1 page (SECRET)

CHARLES R. =HUNK, Jr., Colonel, U

Deputy Commander, Technical Operations

•

ARDC Form 111 (Cont) WD-57-00437
4. •

PROJECT -NUMBER ASSIGNMENT

e •

Project Task Pi'

Aiitrame 39750 - 39767

Propulsion y 39768 - 39782

•

Auxiliary Power Unit 39783 - 39790

Guidance and Control 39800 -'39811

Visual Reconnaissance 39812 - 39821

Ferret RecOnnaissance - 39822 - 39831 •

Infra-Red Reconnaissance 39832 - 39839

Ground Space Comminacat ion 39840 - 39854

Data Processing 39855 - 39862

Geophysics 39791 - 39799

Unassigned

Unassigned

Unassigned

Unassigned

Unassigned

QPRI 39863 - 39864

VD-57-00437

•

Y

k

_- .Esoiect #

P 1755

P 1756

P 1757

• P 1758

P 1759

•

P 1760

P 1761

P 1762

P 1763

!.' P 1764

P 1765

' P 1766

P 1767

P 1768

P 1769

P 8728

i '

is

c

I.

.
%4 GM67. 3-4911

Copy 1 of • •

M. R. Lawrence A. F. Donovan 1 April 1957

P. Dergarabedian

Proposed Use of IRBM as Booster For J. B, Kendrick

Multi-Stage Vehicles

The accompanying data sheets cover the work done to date on three new

designs using the IRBM as booster for the following multi-stage vehicles:

jest Vehicles 

1. Two-Stage Re-entry Test Vehicle M .2 -23 Payload 500 pounds.

;

2. Two-Stage Test Vehicle M-a 25 Payload 0 pounds.

3. Four-Stage Test Vehicle M n 29 Payload 90 pounds.

Satellites 

Two-Stage Vehicle. Payload 50 pounds. Orbit at 190 mi. altitude.

Three-Stage Vehicle. Payload 200 pounds. Orbit at 300 mi. altitude.

These combinations of vehicles are attained by uniting the Thor and the

RTV in various stages. A brief study of the interstage connection between

Thor and RTV reveals no major modifications needed to make the connection.

The spin-rocket system of the RTV is also utillised in those designs (with

streamlined fairings). The Thor guidance system is replaced by a simpler,

lighter system for these designs. In view of the simplicity of these modifications, it is expected that the development costs involved in the above

proposals will ve very nominal.

The performance and payload capabilities of these arrangements seem to

justify further consideration of their potential uses. Please let us know if

we can be of fticther assistance in the development of the idea.

JBK:gg

J. B. Kendrick ,
GM67.3-49

Page I

SUMMARY

The present proposal is to assemble multi-stage rocket vehicle

using the IRBM "Thor" as first stage or booster, and the T-65 as second

stage. The plan appears to be feasible without extensive changes to the

booster or to the T-65 (see Figs. 1 and 2). The nose cone of the Thor may

be removed and the interstage adaptor attached at Sta. 50: The standard

T-65 motor and spin rocket installation as used on the RTV are assumed

for the second stage. Some weight saving modifications to the guidance and

control equipment aid power supply are assumed, and specified.

The payload-velocity-ranee characteristics of the resulting twostage vehicle are as follows:

Payload, lbs. Max. Velocity, ft/sec. Max. Range, n mi.

0 25,400 -

500 23,300 5,300

1,000 21,500 4,150

2,500 18,700 2,800

The bending moment imposed on the interstage connection by the

sudden application of 3 0 motor tip at burnout of Stage 1 is about 500,000 in.lt

applied load. This imposes a stress on the booster at Sta. 141 of 2500 psi and

on the T-65 motor of 6000 psi. These moderate stresses are higher than any

gust load condition would impose, but seem to indicate that the structural

problems involved in the proposal would not be critical.

Given the IRBM booster and the T-65 motor with spin-up rocket installation as used on the RTV, the cost of assembling the two-stage vehicle is

seen to be very nominal. In fact, this is the lowest cost rocket vehicle Navin

a range of about 5000 miles which has come to the authorls attention.

In addition to its suggested use as a Re-entry Test Vehicle for tests

on a half-size nose cone of the ICBM, many other applications may be devised,

such as a weapon, decoy or reconn. vehicle. By virtue of the ease of adaptability from available parts, the latter possibilities should be given further

consideration. Some interesting possibilities can also be obtained by use of

three-and-four-stage combinations of available parts.

A two-stage satellite vehicle capable of orbiting a payload of 50 lbs.

can be obtained, by modifications to the Thor guidance, autopilot and power

supply, and be use of an 18:1 expansion ratio nozzle on the T-65. With

similar modifications, a thzee-stage satellite capable of carrying a payload

of 200 lbs, can be obtained.

7. If a four-stage vehicle is assembled with the IRBM booster and all

three stages of the RTV, a Mach number of M • 29 can be attained with a

payload of 90 obs. Using the low-thrust attitude-control system after Stage 1

burnout, it is possible to provide re-entry angles of 20 degrees or less with

range • values of about 2000 miles.
(

a467.3 19

Page 2

r 4

n

2110203110 .1119-1370416 MEM INEONEZ

usinc mum Boos= '

WITS T-65 MOO STAGE

•

,

- . -.I.e .. •

.. : • .:.':,.

Payload .•' ;:--.;-..;,... , 500 lbs

, ..

,

...

. ..t• 

'I.:- . -, '''L' ...; 31117411111146 ...

• .7 . 5,300 n siA'''.; : .

,•. . . 

• • :,1Ataginetgoic4ltitude•

I, ....,!. %-v.-1.E.,.. • • .. :

stele Vauti4t-Vpaly

Stage 2 BurnoPt Altitude 400,000 ft

Stage 2 Burnout Velocity 23,300 ft/sec

Apogee 4x106 gt.

Re-entry Angle 20./ degrees from horizontal

Plan of Operation 

Fire Stage 14 Climb vertically for 10 seconds, then

programmed turn to angle of 20 degrees using programmer and autopilot mounted in Stage 1. Conventional

Stage 1 controls with vernier & anti-roll to stage burnout

and for 6 seconds thereafter.

Separate and fire spin-up rockets to get 4 revs/sec.

Fire Stage 2, after separation and spin-up initiated by

progremeer.- : Spin *elecityyill meintain:constant

attitute)*.abeut4 degree, •

 by

•

Seperate amose...00mn . . pyiotechnic-or mechanical expulsion

iniiiited 10' time fuse,. after bUrnout of Stage 2.

'.. •

104111 cone.bas no attitude control; hence will re- enter at

any aggle,eed will tunCtolecillate.

immaPeriatureis i - preasures and radiation

effects can be measured under conditions comparable to

ICBM re-entry.

Data can be telemetered to ground stations.

A10,000 ft -.

12,600. ftJt.c.

...

FIGURE 1
V

•

GM67.3-49

Page 3

T'010-STAGE TEST VEHICLE PROPOSAL

The present proposal is to assemble a two-stage rocket vehicle using an

IRBM as booster, with a standard T-65 motor as the second stage. This two

stage vehicle might be used as a Re-entry Test Vehicle, capable of carrying

an ICBM nose cone (one-half size) weighing 500 lbs.,' with a re-entry Mach

-number of about M - 23.

The basic Thor vehicle is not changed except to remove the nose cone and

replace it with an adaptor which supports the second stage (see Fig. 2). The

gross weight of the two-stage vehicle is about 5000 lbs. greater than the orignal

Thor, but the burnout velocity of Stage 1 is still about 12,600 ft/sec. with the

two-stage missile carrying 500 lbs. payload. The original guidance and autopilot

system is assumed to be repalaced by a lighter system for such tests.

The flight plan (see Fig. 1) is to use the conventional IRBM controls and

anti -rolltio verniers through the boost period and for 6 seconds thereafter, then

to separate and fire the second Stage immediately. The RTV spin rocket system

gives 4 revs/sec., which provides stability and attitude control during the

second stage burning period. After burnout the nose cone separates and continues on trajectory without: attitude control. Its shape is believed to prmidt

sufficient stability to cause it to align itself with the flight directiononre-er

Temperature effect and stability characteriestics may be measured and telemetered to the ground.

The ICBM nose cone weighing 3500 lbs. consists of approxiMately fifty

(50) percent warhead and an equal amount • of shell and structure. The same

deceleration would be obtained on a model in which the drag/weight ratio was

held constant. For s half size model, the drag is reduced by a factor of four

due to the reduction in size, and the weight should also be reduced by a factor

of four, to give the same deceleration. Hence, the weight of the half size model

would be 875 lbs., or of a one-third size model 390 lbs. The weight of a scale

modelvaiies as the cube of the scale; hence the half size model would weigh

1/8 of 1750 lbs. or 220 lbs., while the 1/3 size model would weigh only 65-lbs.

Ample weight is then available , for extra skin gage and for telemetering equipment

The re-entry angle can be varied from values of the order of 20 degrees

corresponding to the ICBM to much higher angles, by adjusting the autopilot

programmer during the launch Obese. The similitude conditions to be expected

for the proposed Re-entry Test Vehicle are as followsr

': • . -

;..'. ...,.LCa- 7....i.'.::.%fl.

...... ... ....

Re-entry Test Vehicle.

Similitude Condition ICBM 1/2 Size 113 Size

Re-entry Velocity, ft/sec 23,000 23,300 23,300

Re-entry Angle,. degrees 18 18 - 90 18 - 90

Reynolds Number Ro 1/2 Ro 1/3 Po

Max. Deceleration. "g's" 60 60 60

Heating Period, sec. to to to
.Azr ifi BUILD-UP OF TWO-STAGE VEHICLE

am67.3749

GM 67.3 iat! 4

Changes To

STANDARD THOR*

Remove 3500 lb.

Nose Cone

Replace 1961 lb. Guidance

and power supply with system

veightug . 465 lbs.

HALF SIBS ICBM NOSE CONE

Z

. Weight 500 lbs. or more

T..0 MOTOR

Weight 8160 lbs.

SPIN ROOM

Similar to RIT

Weight 150 lbs. .

.

drops off after .5 sec.

he

sposee

?durf,

.ADAPTOR

Interstage Connector (200 lb)

S andard 6.13:1 Exp. Nozzle

op z 208 sec. (High Alt.)

Vex Igo . 6700 ft/sec.

11:1 Expansion Nozzle

p a 218 sec.

Vex•$ 7000 ft/sec.

p

18:1 Extvaion Nozzle

Top . 225 sec

Vex a 7250 ft/sec.

Extra weight 100 lbs.

*The Standard Thor

the following cha

Empty Weight

is essumedio have

ractsristicat

11,635 lbs Dry

13,532 lbs Wet

Gross Weight 111,438 lbs.

Bbrnout velocity 14,700 ft/sec

at 400,000 ft..

Vernier control 6 sec. after burnout
am67.3-49

' Page 5

TRAJECTORIES AND GROUND STATIONS 

Long Range Trajectories. The two-stage test vehicle can be launched

a long range trajectory of about 5300 n. mi. by tipping over to an angle of

about 20 degrees near the end of Stage 1 burning period and holding that angle

constant during Stage 2 burning period, which is to commence about

0; after St i n,. IP, -

' around stati 34,00Att agg,#i°' •

J '.:. jartecks0.4.The

Imiled-o;,i: 40aing

etatV ed

of the

.to apogee

. OtAgsx d.

stage tint eAlOWnwird leg, at :whatever re-entry ,anglie l is desired,:addrArsetth

altitude that burnout will occur above an altitude of 400,000 ft. This procedure

will reduce the range to about 2000 miles for 20 degree re-entry angles.

Lofted Trajectories. By firing the first stage nearly vertical, and delaying Stage 2 firing until the downward leg, the range may be reduced to any

small value desired. This technique is feasible by use of low-thrust attitudecontrol nozzles, utilizing the remaining LOX tank gas pressure. Such lofted

trajectories will give rather steep re-entry angles, of course, but such may

be desired for some tests. The attitude control may vork in twnways:

Maintain the misfile nose up until ready to fire Stage 2. Then

separate, spin-up and fire Stage 2, which pointi downward.

Tip the missile over to nose down attitude. Then separate, spio-up

and fire Stage 2. (The latter technique requires gyros capable of

operation through a range of about 180 degrees change in attitude.)

AK" OP

DMA

A

WE SEP

..,. : -, . • . ..,,. . ,.. ,... .

- '..=.:;•411rfrivat comm.

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1.0FTF.D iltAJB‘10110t

stem' RAMS1.
L

am67.3-49

Page 6

WEIGHT MARY AND PERPORACE ESTIMATE

.TWORSTACE RE-ENTRY TEST VEHICLE WITH SPIN-UP

(0 lb. Pay'

Add T-65 and 500 lb. Payload 8,810 8.310

Model payload and fitting 500

T-65 with standard nozzle 8160

(including 6978 lbs. propellant)

Spin-up rocket installation 150 (dro p off after .5 sec)

115,252 lbs.

97,906

17,346 lbs. 16,846

Launch weight of Stage 1

Less usable propellant

•

Empty weight of Stage 1

Present weight empty of IRBIL (Dry) 11,635 lbs.

Residual Propellant 1,897

Present weight empty of DON (Wet) 13,532 lbs.

Usable Propellant 97,906

Gross weight,:of present TRIM - 111,438 lbs.

Items to.be removed -5,461

Nose cone 3,500

Structure forward Sta. 151

AC guidance unit 991

Autopilot units, supports, batteries 227„

Reduce size of vernier tanks 200

Items to be added .465

AutopilOt and programmer 150

Power supply 115

Adaptor for T-65 2Q0

Net weight of Stage 1 106,442 lbs

Estimated Burnout Velocity - Stage 1 ** 270,000 ft 12,600 ft/sec 12,800

Velocity increment - Stage 2 at 6700*116# -285 is .19.6700 12,600

Estimated Burnout Velocity Stage 3 23,300 ft/sec 25,400

(Ms 23.9) (Ms 26.,

*

op m 1' 6978

322 10 x e 

` z 208;is Isp x g • 6700 ft/sec.

(Standard 6.13:1 expansion nozzle)

**dv/dw = -.44 ft/sec/lb. See Fig. 4
GM67.3-49

'Page 7

(--

WEIGHT SUMMARY AND PERFORMANCE EST;MATE

TWO-STAGE SATELLITE VEHICLE

Present weight empty of IRBM (Dry)

Residual Propellant

Present weight empty of IREM (Vet)

Usable Propellant

11,635 lbs.

1,897

13,532 lbs.

97, 906

Cross weight of present IRBIL 111,438 lbs.

Items to be removed -5,461

Nose cone 3,500

Structure forward Sta. 151 382

AC guidance unit 991

Autopilot units, supports, cables 161

Power converter, supports, batteries 227 .

Reduce size of vernier tanks 200

Items to be added i485

Autopilot and programmer -150

Power supply 115

Adaptor for T-65 200

Control of attitude - system*. 20 

New weight of booster stage 106,462 lbs.

Add T-65 and Orbiter installation 8,460

Orbiter payload and fittings 50

T-63 with 18:1 nozzle** , 8260

(including 6978 lbs propellant)

Apia-up rocket installation 150 

Launch weight of Stage 1 114,922 lbs.

Less usable propellant 97.9.96 

Empty weight of Stage 1 17,016 lbs.

Estimated Burnout Velocity Stage 1 12,750 ft/sec@ 275,000 ft 10,750@l06ft.

Velocity Increment - Stage 2 • 7250**1144- a 13,250

Earth's Rotational Velocity

Estimated Burnout Velocity Stage 2 25,500 ft/sec

Required Orbit Velocity at 106ft. (190 mi) 25,400 ft/sec

*Standard vernier system (6 sec. after burnbut)000ktinnes until altitude is

about 350,000 ft. Long duration jetsypteuLuay utilize LOR teak gas to turn

body to horizontal and hold it for about five (5) minutes, while coasting to

apogee.

*else 1.309 x 106 x _1 722 • 225; Is x g * 7250 ft/sec.

(18:1 expansion nozzle)

•
am67.3-49

Page 8

STRUCTURAL CONSIDERATIONS 

(See Figure 3)

Case 1. COnsider bending.moient on interstage connection due to sharp. edge

side gust of 60 ft/sec., applied. at maximum dynamic pressure con-

'dition of Immo' 800 lbs/sq ft., Altitude it 35000 ft.,

Velocity is 1500.ft/sec.

Change in angle of attack • 60/1500 • .04 rad.

Side force an nose n CL q8 • 2.0 x 800 x 4.9 x .04

315 lbs.

Bending moment at rear of Sgt. • 315 x 300

n 100,000 inch lbs. (applied)

Case 2.. Consider bending moment at interstagi - coniection due to suddern

application of control on the main motor. One degree tip of main

nozzle gives a moment of

mcs 122.900 x 45 • 120,000 ft lbs/0

57.3

Angular acceleration about the center of gravity will be

Cs if

0.4 red/sec t/0 (near burnout)

Moment at interstaga connection Will be

2

Mio n I . 2,spie 202 0.4 n 14,400 ft lb/o

s 172,000 in.lbio

*Present T-65 is designed for hoisting. moment. of 505,000 in lb.

and hence could take at least 3 degrees of motor tip.

M enn nn I,

Bending stress on • Sta. 151; f • 1 x x37 x 405

2500 lbs/sq in

This corresponds to an increase in tank pressure of about 7.5 psi.

Bending stress on rear of T-65 n PP'994 13.5 

1 15:5. x .125

6000 lbs/sq. in.

Reaction to resist Bending Moment R n Mid

Where d s 36 in. R • 22g#22 2 14,000 lbs.

It is simple to carry this load on two rings of adaptor.

*For further analysis of T-65 load conditions, refer to Thiokol Report SP - 59

"Preliminary Model Spec, Rocket Motor, Solid Prop. T-65, 24-8S•50,000.

SP-59". 5 July 55. (Conf.)
LIVIV j••• -rg

Page 9

fib 3 pirellsrma comiscrrom • 1-4•S Ivs PIM 49

snowy,' #51 awn)

is

.*WT 74 "Di 1". 

NifPaiei MA WIVE Wtsa 3 pirate:info& dettWacrele.

(tioffur Ar srofvvoiv 5%) i ►Am. sir .smtimn)

SifYMATliw air ivArIrs : telutobssosio Ms IA/ APArs. rdfAlic

mill DE ovolAsp Aim) dritimadria 8W0a) 7:45"
w.

•

f

PROPOSED.THREE-STAIX SATELLITE VEHICLE

.481110.11111400STICR

WITH TWiO STAGES OF RTV.

.. •

am67-3.49

Page 10

• ..

. • "

•••••• *."

ari •paylOad

-f oer iurnout

t*

ra. 14 41 11"A. :

s•"' -1.5.70(t - .

••••at —•

44, "• :•••• 444 :1 " IPIOditY •

Plan of Operation

Fire Stage 1. The vehicle then executes a programmes'

turn to horizontal at apogee, using autopilot. Conventional controls to burnout, vlth 1ov-thrust vern:•er to

apogee for attitude control.

Separation, Spin-up and Stage 2 Ignition. The second

stage is ejected using pyrotechnic or mechanical

ejector unit, initiated by programmer on Stage 1.

Motion of separation causes spin-up rocket ignition.

Stage 2 motor • gnition, and initiation of time fuze for

Stage 3 ignition.

Stage 3 Ignition. After time fuze ignites Stage 3 it is

launched through guide rails attached to empty Stage 2,

thus minimizing its dispersion.

Payload :Sepsrations. *pending on .:the porposo of the

flight; psylpad .usp or nit not. teterroated

,

, .

54: • ' • • •%••n •

.

.

.

; s4. 7-•

V. •

' • ..

• "4.* •

•

. .

. r. • ••'.' , s • •

, •

. .

. •
067.3-49

Page 11

WEIGHT MARY AND MORA= unman 

THRER-Slha SNTELLITE VEHICLE WITH SPIN-UP

Present weight empty of TUN (Dry) - 11,635 lbs.

Residual Propellant .1,897

Present weight empty of ISM (Net) 13,532 lbs.

Viable Propellant 97,906

Gross weight of present TREK 111,438 lbs.

Items to be removed - Same as p. 7 -5,461

Items to be added - Same as p. 7 -485

Net weight of Stage 1 106,462

weight of Stage 2 9,980

Satellite Payload 200

Three Recruit Cluster 1,270• 1470 Gross Wt. Stage 3

(including 3 x 263 lbs. propellant)

T-6$ motor with 18:1 nozzle 8,260

(including 6978 lbs. propellant)

Spin-up rocket installation 150

Launcher for Stage 3 100 

Launch weight of Stage 1 116,442 lbs.

Less usable propellant 97.90G 

Shiptyveight'of.Stage L 18,536 lbs.

Estimated Burnout Velocity - Stage 1 12,050 ft/sec@255,000ft 7,730 @ 300 mi

Velocity increment Stage 2 n 7250 1111§- 9,000

Velocity increment Stage 3 s 7400 ig laza 5,700

Earth's rotational velocity . laza

Estimated Burnout Velocity Stage 3 . 23,930 ft/se6

Velocity required to orbit at 300 milelattitude 23,900 ft/sec.
.0152 rad. • 0.87° s 1,11

t'i

OM67.3-49

page 12

DISPERSION OF STAGE 2

Deviation from direction of launch • 0 M sin a we - a sin we 

1;7 1 - a

where X a•unbalanced moment - ft. lbs. (various cameo)

A polar moment of inertia about longitudinal axis - slug ft 2

B moment of inertia about lateral axis thru es.

A a a Tr

s spin frequency in rad/sec.

Cause 1 • Malalignment of thrust axis 1/4 degree a .0044 rad.

So M.e.50,000 x .0044 x 12' a 2640 ft. lbs.

A al 2. x 10.000 x 620 slug ft 2 to 120 slug ft (at burnout) 2

32.2

. 11030 x 252 n 195,000 slug ft2

 to 39000 slug ft2

a s

s 2 x 4- 25 rad/sec usingapin-up rockets.

Then 0 2040 .0068 rad. $ .39°

g2OM.25

.034 rad,

.0032 .0032

Dispersion angle a .034

Cause 2 - Unbalanced mass distribution; i.e. dynamic unblance.

The empty motor can be balanced• to the order of 10-brad.

The loaded motor can also be balance to the order of 106 rad.

Thi4 cause of dispersion is thus seen to be several orders of

magnitude less that Cause 1 above.

Cause 3 - Tip-off from booster. The attitude of the booster is assumed to be

held accurately to .001 tad. * Ejection of Stage 2 and spin-up in 0.5 sec.

are expected to increase this value to .002 radian; i.e. 45% of Cause 1.

Conclusions g:

z

yi2 f Ye + 733 7i2 is believed to be of th,

order of 1 degree for Stage.2.

*Such guidance accuracy may require heavier equipment than assumed in.the

weight summary.
GM67.3-49

page 13

DISPERSION OF STAGE 3 

•

Cause 1 - Difference in igiition timing for three (3) rockets. It may be

assumed that all 3 rockets. ignite, but one of them ignites .005 sec.

before the others, thus giving an increment of. thrust- (say 1/3 of

37,000 lbs) for .004 sec. at moment arm of 3 inches.

it g MO1 n a zit 30. ft. lb .

•

A • 2 !21170 x 42. 17.5 slug ft2 to 8.0 slug t2

a Fix 8

2 • 3500 slug ft2 to 1700

a • .005 .005

'ha •224•7 • .0048 rad.

ttrx 25

.0048 $1

t`sTs .0011 rad.

Cause 2 - 2% difference in thrust of one of three motors

M s .02 x 37,000 x $ 185 ft. lb .

Y2 • .

0011 x Ma • .0068 rad.

Cause 3 - Malalignment of thrust line of one motor 114° • .0044 rad.

M • 37,000 x .0044 x 6 s 980 ft. lb .

13 • .0011 x 2.1gs 0.035 rad. • 2° (Probably less)

Conclusion: jE Yi = ItATi2)i + (Y12)2 + (y12)3 is believed to be

eof the order of 2 to 2 degrees,' according to the above analysis.

This vary as 1/04 hence a slight increase in spin rate

mould be desirable.
Present weight empty of IRBK (Dry)

Residual Propellant

Present weight empty of TREK (Wet)

Usable.Propellant

.

-

Gross weight of present IABW

Items to be removed • Same as p. 7

Items to be added - Same as p. 7 -.

Net weight of Stage 1

Weight of Stage 2

RTV lst Stage 10,500 lbs (less fins)

including 6978 lbs propellant

plus spin-up rockets 150 lbs.

which drOp off after .5 sec.

ATV 2d Stage 1770 lbs.

including 3 x 263 lbs propellant

Launch Weight of Stage 1

Less usable propellant in Stage 1

Empty weight of Stage 1

e-0:49

Page .14

111,438 lbs.

-5,461

-485 

106,462 lbs.

10,500

116,962 lbs.

97,906 

19,056 lbs.

MUGU SIDWARY AND PERFORMANCE VTINATZ

FOUR•STAalt VEHICLE WITH MK AHD RTV

11,635 lbs.

1,897 •

13,532

97.906 

Estimated Burnout Velocity of Stage 1 11,800 ft/sec

Velocity increment Stage 2 • 7250 log o - 285 • 7,800

Velocity increment Stage 3 n 7400 log _Nig a 4,400

. Velocity increment Stew,. 8 7400 los—Ng ,500

Estimated BurnOut Velocity .- Stage 4 29000 ft/sec

C.
0M67,3.49

Page 15

The performance of Stage 1 was computed on the 1103 Computer in

the same detailed manner as for the IRBM. Pour values of burnout

weight were used; he nominal weight of the standard missile and

three higher values.

i.e.,

'turnout velocity and altitude is plotted in Fig. 4

as if function of burnout weight for the case of 97,906 pounds of usable'

propellant.

Pm later stages, the velocity increment is shown in Fig. 5 as a

function of mass ratio for various vitas of effective exhaust velocity.

The effect of gravity add drag for Stage 2 operation in a long range

trajectory was computed on the 1103 Computer, and found to be

285 ft/sec. The velocity increments determined from the chart should

therefore be decreased slightly for gravity and drag.

Range as a function of burnout . velocity is shown in Fig. 6 for the

IRBM family ofimisilles. The four points computed on the 1103 Computer

are distinguished by asterisks.
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Reproduction of this doonient in wh.

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RDB PRCUECT CARD I TYPE or REPORT

1 New Project

REPORTS CONTROL SYMBOL

WAWA )4 0

. PROJECT HUE (UNCLASSIFIED TITLET

Geophysical Environment Data • or ARS, WS117L

Short Title: ARS Enviroement

'. -

.

..

s. SICURITY

SECRETS. PROJECT NINASIN

1764

4. IMOIX IIIIMSIR

2-117L

s. woo BATE

2 April 1957 n

R. BASIC MU) OR mama . 1r.

Strategic Air Warfare System Iktmospheric

117L

sums at swum amour

Physics - 7B

Physics

•

M. TECH. ofL

SA-9A, 9B,

10 10-9

S. COONUANTAONNW

ARDC

12. CONTRACTOR AND/011 LABORATORY

•

Geophysics Research •

ate

COWIRACTAV.O. NO.

-

1P. NAMING'AGENCY

CRD, AFCRC . :

0

1

1,

- I;

r ii) .r.?:-PI 

17...11ST.•:0401.. DATES.

OffICE SMOOT

CRZA

 "". NO.2

.f 2-7730 X-9

10. PAISINISTINO Mina 1 '

HQ, USAF

'

1S.

WS (11) ..P) ,

us. L95,

mmity INV. 195- mmumecommA lt-nml :u2.4.4mmomme USAF USN

AMC-P ATIC-I CNO-I

SAC-I RIA .

ADC-I C/S-I

APGC-I Other .

TEST 1959

OP. EVAL. I

14. DATE APPROVED mammiamma-11

.

Y58 I 1000M

IL/WORM ,.,

lA

M.

ATC-I CIA-I ' A(Missiles) FY60 I 425M

This is the initial report on this project

REQUIREMENT AND/OR JUSTINCATION .

System Requirement No. 5 dated 17 October 1955 and subsequent letter

directive from WDD dated 23 December • 1955 assigned to AFCRC the responsibility for providing environmental data which affect the design and testing of

' ARS vehicles. Based on independent studies by the Geophysic Research Directorate the three design study contractors and conferences with personnel of the

WSPO, it was concluded that in four areas of geophysical environment insuffiCient diti were available for successful design and test of the Advanced

Recannaissance System Vehicles. The four so considered are . (a) Meteor Physics

(b) . Density at Orbital Altitudes, (c) Solar Radiation in the U.V. and X-ray

Region and (d) Thermal Radiation. Specific discussions of requirements for

additional design data in each of these areas are included under each task.

21 a. Brief and Military Characteristics

The objective of this project is to provide environmental data considered essential to insure and simplify the design of a successful Advanced

Reconnaissance System.

22. RM.1 IC & P • 71. I.

•

PAN OF Moss

"1.-Fr 7 e //.414

0
'

.,. -01... ' : t

' • .

.,

(UNCLASSIFIED TITLE) Geophysical Environment... Data for ARS, WS 117L 2 April 19!

1 Short Title: ARS Environment , Proj 1764

Approach,

See individual Tasks. (21c)

Bake

1. (a) T-39791 - Solar Radiation Program in Ultraviolet and X-ray

'anion for ARS 

(b) This task will be accomplished through a combination of "in-house"

and contractual effort. Currently the contractual effort is by Comstock and

Weatcott, Inc., under Contract AF 19(604)-1889. Other contractors contemplated

at the moment are: University of Chicago, Chicago, Ill. and Radio Corporation

of American New York, N. Y.

-

(c) Task objective is to determine the intensity of Solar U.V. and

Soft X-ray radiation as it would strike the satellite and the extent of damage

dun to collisions of molecules.,; atoms and ions with the satellite surface.

Requirement and/or Justification

Vehicle design will be affected by radiation in the solar ultraviolet

(,. 1

and X-ray region. It has been shown by GRD that the quantum yield of photoelectric effect on metals exposed to short wavelength ultraviolet is about 250

times as great as that of the conventional photoelectric effect in the visible an

near UV. Thus, since a vehicle traveling at 500 km is essentially receiving

unfiltered solar radiation of low wavelength, one must consider a possible

"charginglup" of the metal due to the loss of photoeleCtrons from.the surface.

This charge can theoretically rise to a high voltage, depending on the wavelength and intensity distribution of the incident radiation. Such a charging-up

could influence the telemetering or other electronic functions of the equipment in the vehicle. Also, it is known that short wavelength ultraviolet causes

deterioration of a plastic surface. This could fog plexiglass and damage rubber-like materials. Present data are inadequate to evaluate this effect simply

because we do not know within.. several factors of ten the solar intensity above

' the atmosphere at wavelengths below 1500 Angstrom Units and we believe that

design purposes can therefore not be satisfied.

The effect of atmospheric composition at 500 km is difficult to assess.

There might be heating of the vehicle to contend with; due to recombination of

atoms on the surface as•aell as impacts with other atoms and molecules.

Such a heating effect would be super-imposed on that due to solar radiation

and would act even at night when the vehicle is shielded from the sun by the

earth. Since solar ultraviolet endi-rayradiation is part of the total picture

of the integrated interaction of the sun and the earth's atmosphere and data of

this kind are extremely scarce the measurements of these variables at vehicle

altitude would be unique. These measurements would give us information as

to the physical mechanisms operating in the ionosphere and delimit in an

essential fashion theotonospheric functioning by giving us a better understanding of the nature of atmospheric ionization. This would assist in the 'forecasting of ionospheric propagation and could contribute toward the solution of the

satellite communications problou . - •

,

. .

•
(UNCLASSIFIED TITLE) Geophysical Environment Data for ARS, WS117L 2 April 1957

Short Title: ARS Environment 

411111111111111111P

Proj 1764

(d) Approach 

At the present time, there are two main areas of research;

A laboratory investigation of the effect of collisions of

particles, atoms, molecules and ions on solid surfaces (sputtering) conjoined wit

the effect of recombination of atomic species on solid surfaces.

This laboratory study will be carried on mainly in-house,

but with modest contract let for auxiliary studies.

Primary in this research will be the problem of developing

ultra high vacuum mass spectrometer tubes for study of the effect of ion

bombardment of surfaces. Such a tube would require suitable component parts,

valve sealants, tubing and pumps to obtain this vacuum. This is necessary to

duplicate in the laboratory pressures at satellite altitudes. The feasibility

of this development has already been established by in-house work. About half

of this is finished, leaving principally design engineering.

Different techniques, among them molecular beams, will be

used for the acceleration of the non-charged particles on receiving test

plates the nature of which will be determined by vehicle design. In particular,

the effect on metals will be examined. The plates will be tested by a variety

techniques, microscopes, etc., for possible damage due to momentum transport (sputtering).

Solar ultraviolet and X-ray study -- The goal set in this

research is the measuresent of absolute intensities of the solar spectrum

from 1500 Angstroms down to a few Angstroms. This program is divided into

three phases, laboratory investigations, measurements of solar intensities

in rockets and finally, construction of the satellite instrumentation by miniaturization of rocket instrumentation.

This region of the spectrum is relatively unexplored; hence,

a whole new system of monochromators, source's and detectors must be constructed. First, there must be the calibration against a primary detector,

thermocouple not calorimetriC. These secondary detectors must be reliable

and reproducible. In type, • they may be dependent upon-the interaction of

radiation with a filling gas or on the• effect of radiation upon a cathode.

Therefore, laboratory work will be needed to select adequate detectors.

The monochromators to be constructed are unique in. design

and rather elaborate in the equipment necessary to perform the desired calibration. They have already been designed and are presently under construction.

To put them into actual operation will take an extensive period of working7out

of the manifold details and problems involved.

The construction of detect s will. be to a large extent

under contract.
(UNCLASSIFIED TITLE) Geophysical for ARS, WS117L .2 April 1957

Short Title: ARS Environment Proj 1764

Because the interaction of matter with radiation in this

region is as yet little understood, the objectives can only be reached by

an extensive deepening of our insights into the nature of these processes..

For example, a predicted phenomena is that of photoconductivity effect. This,

when more fully investigated, may yield a possible secondary type of detector.

The process of building suitable detectors can only. go on

sieulateneously with this type of exploratory research.. After the laboratory

phase, the instruments will be flown in Aerobee-Hi rockets to measure the

radiation intensity above the earth's atmosphere. The number of flights

necessary will be at least six, possibly increasing to eight or nine depending

on-results.

2. (a) T-39792 Interplanetary Matter and Meteor Physics in

Relation to ARS

(b) This task will be accomplished through a combination of "inhouse" and contractual effort. Currently the following contracts are in

effect:

(1) - AF 19(664)-1894 - Temple University

• (2) - AF 19(604)-1908 - Oklahoma A and M

- AF 19(604)-1901 - Smithsonian Observatory

- AP 19(604)-1892 - Stanford Research Inst.

No other contracts are contemplated at the moment.

t

from meteoric bombardments io a vehicle above the earth's atmosphere and

(c) The objective of this task is to determine the possible hazard

( . to provide data as to the spatial distribution,'size, composition, and velocity

1- of micrometeoric matter.

Reouirement and/or Justification 

kr/

The hazard from meteoric collision with a body essentially in interplanetary space, unprotected by the earth's atmosphere is not very well

known. The probability of collisions intense enough . to destroy the vehicle

I. or affect its operation is very impOitant in the design of a protective "meteor

bumper" to insure proper operation of the vehicle. These meteoric collisions •

may result in dangerous surface erosions affecting heat exchange properties

and optical windows. Stability, temperatUro control, reliability may all be

influenced by meteoric bombardment.

Information regarding the ipflux of meteoric material into the earth's

atmosphere has been collected by the following methods: visual observations,

photography, radio reflections from meteor trails, and telescopic observations. Fromi such studies and measurements, the diurnal and seasonal variations

in the influx of sporadic meteors, velocities and radiants of shower meteors,

velocity distribution of sporadic meteors, mass distribution of meteors, and

spatial density of meteors have been determined. These measurements give

a value for the rate of influx of interplanetary material.into the. earth's

OMR 3

;
4

/.

. .

. .

.

(UNCLASSIFIED TITLE) Geophysical Environment Data

..

 or ARS, WS117L 2 April 1957

Short Title: ARE Environment Proj 1764

atmosphere of 5 x 10 6 gm per. day. However, these ground-based methods are

limited and a grave anomaly, of importance to the ARE, exists. Since the

visual and photographic methods are only sensitive to meteors of visual

magnitude +5 (10-2 grams mass, 10 11 ergs energy) and the radio and telescope

methods to visual magnitude of the order of.0.8 Ness x 10-4 gm, energy

6 x 10/ ergs), informatton derived from these methods regarding meteoric particles

with mass less than 10-* gm is seriously lacking. These smaller particles are

far more numerous and therefore have a high probability of encountering a vehicle

above the earth's atmosphere.

The anomaly on the influx of interplanetary matter arises from various indirect measurements of the fine interplanetary matter. These measurements include determination of the density of matter in the zodiacal cloud, or

the interplanetary dust cloud, by S. C. Van de Hulst and C. W. Allen; measurements of the nickel content in deep sea ocean sediments by H. Pettersson and

H. Rotsch; and initial rocket soundings from V-2 and Aarobee rockets. These

measurements indicate a rate of accretion'of interplanetary matter by the'

earth as high as 5 x 10 10 gm per day, up to a factor of 10 4 times higher than

predicted from regular methods of observation. It seems, also, that this

high rate of influx may be necessary to explain the presence of the E region

ionization during the night. This higher rate leads to a'probably encounter

for visual magnitude 15 (energy '1010 Bay) of one hit per square meter per

second. Such impact rates are significant for a vehicle with a required lifetime of about a year. These impact rates may possibly be further increased

by a factor as gzeat as 10 4 to 106 if geomagnetic focusing of cosmic dust

particles, suggested also by S. F. Singer, was detected experimentally.

From the . standpoint of ARS, the hazard to space.vehicles in an interplanetary environment seems closely dependent upon the effects of interplanetary matter, as well as such other factors as cosmic radiation, atmospheric drag, and energetic solar radiation. On the one hand, relatively large

impacts may result in penetration of the vehicle surface and subsequent destruction of important equipment, affecting the usefulness of the vehicle,

while smaller impacts would result in an abrasion affecting the usefulness of

lenses and photosensitive surface areas, etc.

It is therefore necessary to determine the probability of collisions

with interplanetary particles as a function to time, and the effect of the individual collisions on the vehicle in order to determine design criteria for ARS.'

These requirements may be fulfilled by a measurement program involving

high altitude rockets and satellite type vehicles, and direct laboratory studies

of high speed impact interactions. Related studies that would support direct

probing methods are also of interest in order to afford a higher degree of

validity to the experimental results.. .

(d) AREroach

The areas of investigation in this task may be broadly divided

into rocket and satellite experiments and laboratory studies.
(it

th

(UNCLASSIFIED TITLE) Geophysical Environment . Data for ARS, WS117L 2 April 1957

Short Title: ARS Environment Proj 1764

•

(1)' Determination of the influx of meteoric material by .

yockel experiments L 

•

This includes the design and construction of equipment and

launching of rockets containing this equipment for the detection of meteoric

material. The equipment for detecting meteoric material will operate on the

Principle of detecting the vibrational energy generated upon impact. This

apparatus includes piezoelectric accelerometer, an amplifier, and a telemeteringsysten with its associated ground-based receiver-recorder. Aero

bee and/or Nike-Cajun rockets will be used to carry out the program. It is

important that a statistically valid sample of meteoric material be obtained

for final design of the ARS.

.•

The program of research for direct,roCket probing of interplanetary matter involves first the design and development of a basic

piezoelectric accelerometer capable of measuring the spatial distributionand mass of interplanetary particles. Such equipment has been used by

Prof. Bohn in 1949 and was used again during 1955. Hence, only minor developement and calibration . methods are required prior to construction of the

basic unit. Such equipment is sensitive enough to detect particles of visual.

magnitude 25. Approximately ten'to twenty detection units will be built on a

semi-mass production basis. Approximately five to ten successful experimental firings from Hallman Air Force Base using Aerobee rockets are

required prior to establishing a weighted statistical figure for the intensity

and probability of a particle impact with a vehicle. About five successful

firings at a high latitude would be required. to establish the extent of a latitude

dependence particularly by small meteoric particles.

(2) Design and development of equipment for detection of

meteoric material for inclusion in the ARS.

It is expected that development work in the rocket phase of

detection of meteoric material will aid greatly in the development of equipment

of a similar nature to be included in the early oribiting and non-orbiting

ARS test vehicles. It is important that the apparatus be designed with a high

degree of reliability, yet be lightweight, and have a low power requirement.

(3) Theoretical and laboratory studies and high speed

impact phenomena 

Essential to the measurement of interplanetary matter is a

knowledge of the relation of the intensity and frequency distribution of the accoustical energy generated by high speed meteoric impacts to the mass, the

mass density, and the velocity of collision with the meteoric particle. Thereby, the surface erosion and the distribution function of meteoric material in

space may be determined from the ARS measurements. Polished plate experiments on rockets that =7 . 13e recovered will yield some information, but high

speed impact measurements in the laboratory for the study of collisions of

solids with gases and surfaces are required to support this subtask. In addition, optical and radio measurements of meteor influx and atmospheric interactions will also assist in the direct experimental studies.
(UNCLASSIFIED TITLE) Geophysical Environment Data for ABS., WS1I7L 2 April 195:

Short Title: ARS Environment Prof 1764

High speed impact studies of particles with surfaces are possible at this time only by a method using shaped charges, since only by this

means have particle velocities comparable with meteor velocities been generated in a laboratory basis. The physics of high speed interactions is not well

understood, and experimental measurements at velocities up to 50 kMisec are

highly desirable. Even then, it is difficult to predict the degree of success

of this technique, but this approach is presently available at relatively low

Cost. Because the energy density of the impacting reactions may be as much

as a hundred times greater than previously observed, considerably different

effects than theoretically. predicted are to , be expected.

(4) Theoretical studies 

This .subtask is concerned with the correlation and application

of various data applicable.to the Problem of determining the hazard from

interplanetary matter upon ARS. Where possible, information from shock tube

studies, radio and optical meteoric studies, investigations of meteoric craters,

deep see ocean sediments, microchemical analysis of rare gas constituents,

etc., that contribute to the overall proble6 of the determination of the hazard

from interplanetary matter will be considered. In this manner, the reliability

of the information. derived from the direct experimental program may be .

further evaluated.

The primary emphasis of the approach of the 4 subtasks, therefore, is the determination of the spatial distribution of interplanetary matter,

the size distribution, and the mass density of this material, and thus with

suitable laboratory studies to be able to predict the probability that meteoric

material may penitrate a given thickness of satellite skin per unit time, and •

the rate of erosion per unit area for a surface exposed above the earth's atmosphere. An improved understanding of the physics of hypersonic interactions in

the velocity range equivalent to an energy of 50 to 1000 electron volts is also'

of importance.

The rocket program for detection of meteoric particles would

require approximately ten successful rocket . flights up to altitudes as high as

150 km before sufficient data to make a satisfactory estimate of the rate'of

influx of interplanetary matter. It should be stressed that ten successful

flights corresponds to a total measuring time of. about a quarter of an hour

above altitudes of 50 km. (Measurements below this altitude would be contaminated by terrestrial material). From considerations of the normal difficulties

experienced in past experimental programs using high altitude rockets,'probably instrumentation for fifteen rockets will be necessary. The estimated

cost of development and construction,of . this instrument is 60M to 100M based

on cost of SM per instrumentation. The cost of rockets for this work based on

30M for a single Aerobee rocket would be 450K for 15 Aerobees. However,

since the meteoric detection equipment may be used on a Nike-Cajun rocket

system, also, the overall rocket cost is expected to be much lower than the
1

F

•

(UNCLASSIFIED TITLE) Geophysical Environment Data for ABS; WS117L 2 April 1957

Short Title: ABS Environment Prot 1764

estimate using Aerobee because the Nike-Cajun system when it becomes available would cost less than half as much as an Aerobe*. The fund requirements

however, are based upon rocket requirements using Aerobes..

Upon availability of an ARS vehicle as a platform for the measurement of meteoric particles, a relatively large sampling. time for making measurements of interplanetary matter

•

will be available. It is therefore of importance

that meteoric detection equipment be mounted on such an early test vehicle. Such

equipment must be very reliable and capable of operation over a long period of

time, while its weight should be kept to a minimum. The development of equipment

for the ARS is estimated to cost SOK over a two-year period, while'aight

and rocket testing would involve* an additional 40K.

The program on research on highspeed impala phenomena will

be based on studied using shaped charges, and also investigations of dynamic

interactions of meteoroids in the atmosphere. The estimated cost of the

initial phase of • this work is 80K over a two-year period.

3. (a) T-39793 - Atmospheric Density Determination at Altitudes

of Artifical Earth Satellites) 

(b) This task will be accomplished through a combination of "inhouse" and contractual effort. Current contracts in effect are as follows:

AF 19(604)-1871 - University of Michigan

AF 19(604)-1890 - University of Michigan

(c) The objective of this task is to obtain reliable values of atmo

pheric density, pressure and kinetic temperature between the altitudes of 200

to 400 miles.

4 Requirement and/or Justification 

The primary objective of this task is to obtain reliable values of atmos

pheric density, pressure and kinetic temperature in the vicinity of 200 to 400

miles altitude, the altitude of a proposed satellite system. These•data are

needed in solving.various problems on the design of the ARS vehicle. Some of

these problems are:

What altitude must be maintained by a satellite vehicle of specified

P

size and shape in order.that the atmospheric drag be sufficiently small to permit a minimum specified life time of the satellite.

How does temperature ride on the skin of the satellite vehicle due

to aerodynamic heating (friction between itself and the molecules of the atmosphere) vary with altitude below 400 miles altitude.

3. What is the minimum value of . mass to cross-section area ratio; of a 0 satellite which will permit the required lifetime to be achieved at specific ti

. • '

,....1 1111111111111r.. 13 47.1A a- - 4f.//4/
•

(UNCLASSIFIED TITLE) Gsophysical Environment Data for ARS, WS117L 2 April 19:

Short Title: ARS Environment Froj 1764

orbiting altitudes. The present estimates of the magnitudes of these properties

are quite. uncertain. Pressure and desnity may be in error by factor.of 100 or1000 at 350 miles altitude because they are based on extrapolation of values at

100 miles and on unconfirmed theories. Extension of measurements to 200

miles or 250 miles altitude wOuld greatly improve the reliability of extrapolation to 300 miles, while measurements at 300 miles would be even better.

•

•

The tase.involves the study and implementation of two basically different methods for obtaining the necessary data. The first method involves

tha'direct measurement of the drag force on a sphere falling from great altitudes after its ejection from a rocket. This method is of special interest

since it is the drag force on the satellite which ultimately determines its life

'Results of this measurement are free from effects of contamination from the

rocket. The limitation of this method lies in the fact that the sphere must

fall from an altitude of 10 to 20 percent higher than that for which the drag

data are desired.

The second method for obtaining these. data involves a selective

ionization gauge for measuring number density of particular constituents as

well. as total number density.' This method in principle may be used to the

peak of rocket trajectory but is adversely affected by contamination from the

mother rocket. Various outgassing and ejection techniques under study will

minimize this liMiation.

A secondary objective of this task is to develop the necessary techniques and devices for measuring pressure, temperature and density from

ARS test vehicles. This phase depends in part upon the success of the primary objectives, although the conditions for outgaesing are sufficiently different to materially simplify the accomplishment of this objective.

(d) Approach 

At this writing, the task appears to involve eight steps.

(1) Feasibility study of two proposed methods for measuring

the required parameters:

The feasibility of two methods for the measurement of atmospheric density, pressure and.temperature are being explored. These methods

are (1) an extension of the falling sphere experiment and (2) the ionization

gauge experiment currently being employed up to altitudes of 75 to 100 miles.

The present falling sphere experiment involves the ejection

of a sphere from a rocket at high altitudes, and the measurement of the drag

force of the atmosphere on the sphere as it moves though space. (It may be

ejected anytime after the end of rocket powered flight and hence will rise to

a peak slightly lower than that of the rocket.

0
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i.

(UNCLASSIFIED TITLE) Geophysical* Environment Data for ARS, WS117L 2 April 19!

Short Title: ARS Environment Proj 1764-

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The spheric contains an accelerometer which measures

drag acceleration as a function of time to 1% accuracy, independent of orientation. The sphere also contains a radio transmitter which relays the accel-

-*roaster signal to a ground recorder. The double integration of the total

acceleratiOn yields sphere altitude as a function of time to a reasonable accuracy for high angle flights. An independent complicated analytical reiteration method yields sphere velocity and altitude versus time independently.

The determination of atmospheric density depends upon a knowledge of drag

coefficient at the mach numbers and Reynold's numbers experienced by the

sphere. These values of drag coefficient have been measured in ballistic

ranges and hypersonic wind tunnels.

The present ionization gauge experiment invo/ves the measurement of ion cqrrent from ionized air molecules on one or more chambers

on the surface of a rocket. The knowledge of- air pressures around conical

surfaces with known orisntation to the air stream leads to a value of ambient

pressure and to temperature if the relative velocity of cone to air is known. .

This sytem requires soma kind of tracking for high accuracy although integration of pressure and temperature values results in approximate altitudes.

•

Extending the sphere experiment to higher altitudes involves

increasing the area to mass ratio: of the sphere, shifting the range of the accelerometer to very low values . (this essentially eliminates its use at higher

accelerations, corresponding to lower altitudes). The system does not work

at or near zenith since the velocity is too low (approaching zero for a verital

flight) for drag to be measurable.

The extension of ths . ionization gauge method involves

three main steps: (a) Adapting to rocket use existing ionization gauges

designed for ver low pressures (Alpert type); (b) eliminating the effect of

contamination of the measurement from rocket outgassing by housing the

gauges in a separate thoroughly outgassed body which will be spring ejected

from an evacuated cavity at high altitude; (c) Eliminating the uncertainty of

molecular dissociation by making the gauge sensitive to only one or two

specific molecular species through simple mass specirometer techniques.

The feasibility study of the use of these methods at high

altitudes is currently under vay and involves a study of (a) the theoretical .

limitation (b) inherent sources and estimates of errors (c) engineering difficulties (d) apace and weight requirements (e) estimated cost per flight. An

analysis of these studies will determine which method has the better chance

of success, but at present it appears that both should be tried. Perhaps both

may be flown simultaneously in each,rocket vehicle.

(2) Design and construction of preliminary models of

equipment for one or both methods. . 

This step of the task involves the design and construction'of

the equipment which is'expected to be flown in the initial series of rocket

ir • diei
•

•

r.

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•

(UNCLASSIFIED TITLE) Geophysical Environment: Data for ARS, WS117L 2 April 1957

Short Title: ARS Environment Proj 1764

•

flights. This step may include wind tunnel tests or rocket flight tests of ipeci

is portions of the total instrumentation for the'method, as well as the final

packaging of at least two sets.of the equipment for the rocket flights of each

of ths two methods.

Initial rocket flights of the equipment for one or both methods

This step includes the field operation involved in preparing

the equipment for actual rocket flight together with the necessary operation of

the rocket flights for each method. The preparation for two flights is insurance against rocket or other failure during the first flight.

Evaluation of flight performince and necessary redesign

of equipment 

This step involves the detailed study of the telemeter. record

of the flight to determine the performance of the various parts of the measuring equipment, as velI as the transcription of recorded data to usable form for

computation of the required atmospheric parameters. Deficiencies in the performance of the equipment detected by the record are than to be removed by

suitable redesign. Because of • the urgency of the program, major portions of

the equipment should already have been constructed at this point for the series

of data-gathering flights and it will be necessary to take the chance of having

to modify some.of the components at this stage of the task.

(5) Maior series of data gathering rocket flights 

This step of the task involves the flying of three to ten sets

of instrumentation for density and or pressure measurements in special 300

mile altitude rockets presently being designed for AFCRC or in non-orbiting

ARS Weapons System test vehicles or both. Contact will be made with the

ARS Weapon System office to obtain space in these test vehicles. If the first

three flights indicate sufficient self-consistency the balance of the data.

gathering flights can be cancelled.

The special 300 mile altitude rocket is a multi-stage system

made up of existing rocket components, i.e., Cajun rockets and Nike bcostets.

An engineering study presently contracted for will result in engineering draw-,

ings for the necessary fins and coupling devices and nose cone necessary to

combine the propulsion system into an atmospheric data gathering rocket system

capable of carrying 40 lbs. of instrumentation to 200 - 300 miles. Upon

completion of this engineering study, engineering drawings will be available

from which the necessary parts and pFopulsion units may be built and purchased

at an estimated cost of $20,000 per rocket system.

(6) Analysis of data and preparation of revised atmospheric

model

t .This step.of the task involves the reading of telemeter

records, the computation of the values of the atmospheric parameters,. and
(UNCLASSIFIED TITLE) Geophysical Environment Data for ARS, WS 117L 2 April 19t:

Short Title: ARS Environment Proj 1764

the compilation of these data into consistent atmospheric models. This step

is not necessarily limited to follow step (5) chronologically, but will

follow each rocket flight from which usable data results.

(7) Repackaging of eouipmentlfor test satellite vehicles 

This step involve

▪

 s the electrical mechanical redesign of the

equipment used 'in the rocket firings of step (5) or-planned in steps (1) and (2)

to make that equipment suitable for gathering desired atmospheric data from

,ARS test vehicle.

(8) Installation and flight of density and pressure measuring

-equipment in satellite vehicle

This phase involves the field operation of a program for

measuring atmospheric density and pressure at orbital altitudes of satellite

i test vehicles, and would be followed by a reapplication of step (6).

4. .(a) T-39794 - Thermal Radiation Program for ARS

•

This task will be accomplished through a combination of "inhouse" and contractual effort. Present contractor-is the University of

Colorado unde • Contract Alf 19(604)-1899. Additional contracts are contemplated.

The objective of this task is to measure the intensity of

ti irradiant heat sources above the atmosphere.

1

. The radiation environment is one of the external conditions

... which may grievously affect the period during which information. can be'Obi4

•

tained from an oribiting satellite.

I) To be operational,' the design of the•satellite must be engineered

so as to maintain within pre7determined limits the temperatures of vital comt

. ' munication components, such as electronic units, batteries, etc. If and when

t

nuclear sources are used for power, then the excess energy must be radiated

) away from an external heat exchanger; Its design requires a knowledge of the

radiation exchange environment. . .

t

IL

The temperature of a satellite in orbit at given times and places

can be calculated. Required for these calculations are a knowledgeof the in-.

terstellar. heat sink into which it is radiating energy -- thus cooling it and

a knowledge of the intensities of the thermal fluxes which tend to warm it.

Estimates of the equilibrium temperatUre of the satellite can be verified only

by measurements within the orbiting satellite. Under the worst condition the

TT (.19 17 *-7P6 -.6- 7 O /NO
I-

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(UNCLASSIFIED TITLE) Geophysical EnvirneVent . Data for ARS, WS117 L 2 April 195

Short Title: ARS Environment Proj 1764

.

temperature within the communication equipment may cause it to fail before

any information is received. A. slightly more favorable but undesirable condition would be a premature failure of communcation, (Thus, should the abaorptivity--equal to emissivity--of the akin of the satellite change while in

orbit, the equilibrium temperature of the satellite might differ drastically

from that calculated on the basis of design specifications.)

The objective of this task is, then, the development and testing

1 of devices adequate for the measurement of the three irradiant sources--

' direct solar energy, solar energy reflected jointly from earth and atmosphere

(I.E., albedo) and earth emissivity (in the infrared)--and the flux from a

satellite into interstellar space.

It is proposed that flux measuring devices should be installed on

the earliest test vehicles so that flux measurements can be obtained so long as

communication with the satellite is continued. Should communications then

cease, and should the thermal, flux measurements seriously disagree with the

values in the design calculations, at least one source of possible trouble should

be identified.

During the development and testing of the devices for measuring

the three sorts of radiation, balloon and rockets equipped with these devices

will be flown. As scientific by-products of the tasting program, some confirmation of current estimates of the intensities of the three sources will be

obtained. Our present information on the radiation environment is next

summarized.

Reliability of Present Estimates of the Solar Constant and

the Albedo and Infrared Emission of Earth Plus Atmosphere 

The solar constant is believed to lie between 1.946 and 2.05

gram calories centimeter - 2 minute -1 , a deviation of 3% from the mean of

' 2.0 gm cal ce2 mie1 (1,396 watts meter -A).

For this discussion, the term albedo applies to the solar

radiation reflected directly from the earth's surface and scattered and reflected from the atmosphere with its content of clouds. From point to .point in the

orbit of a satellite with orbital distances as now stated the albedo will be •

highly variable. Deviations may be expected of at least plus or minus 20 - 30

per cent from the mean value of the albedo 'which may be taken as lying between

36-56 per cent (I.E. approximately 36-56 per cent of the solar constant is

diffusely reflected or scattered back from the earth).

c) The infrared emission of the earth may be estimated by

theory. Current estimates for the various zones of latitude obtained by

deduction may well be in error by 20 to 50 per cent; on the average energy

to about 32 per cent of the solar constant is diffusely emitted as infrared,

radiation from the unit consisting of earth and atmosphere.
••:;:" ••••••,4

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4111111111111111111

UNCLASSIFIED TITLE) Geophysical Environment Data for ARS, WS1I7L 2 April 1957

Short Title: ARS Environment Proj 1764

(d) Approach 

I. Introduction

The following subtasks are foreseen:

(1) The design, development, testing and calibration of

devices for the measurement of radiation of the following kinds.

Total radiation from 0.27 to 2.7 microns (By "total"

is a single detector which integrates the energy in the specific spectral

region non-selectively -- i.e., recording to heating value, not by number

of photons.)

Total. radiation from 4 to 20 microns.

(2) The design, development, testing and calibration of

temperature sensors.

. Considered, but at present neither planned, funded nor

contracted, would be the study of the temperature of a yodel of the satellite

in a simulated radiation environment in a teat chamber in the laboratory, or

balloon-borne to an altitude where the air pressure approximates ten millibars

(about 100,000 feet).

A subtask within scope of this task, but deserving

separate discustion will result in new techniques, design experience, and data

important to ARS as vehicles for reconnaissance. This subtask is amplified

specifically in Section II, Activities in "(4) Activities -Infrared Background

Studies".

II. Activities 

(1) . Activities - General 

The statement of the task may be amplified by noting

that the satellite in its orbit will be warmed by energy from sun and from

earth and cooled by radiating energy outward. Its native temperature will

vary between upper and lower,limits determined by intrinsic qualities (skin

absorptivity and emissivity for various parts of the.spectrum from ultraviolet

through far. ultraviolet and the heat capacity), and the trajectory (portion of

period of orbit when irradiated by sun plus earth, or in the eclipse shadow

of earth wher. irradiated by earth emission only; and the distances from

earth at apogee and perigee, and whether these occur in sunlight or in shadow.

•

DD Form 613 cont.) ....11-49-%.47- //441
(UNCLASSIFIED TITLE) Geophysical Environment Data for ARS WS117L . 2 April 1957

Short Title: ARS Environment. Proj 1764

Further4 ,it is probably that various.othtr sources of heat

may be added as the development of the satellite proceeds from the preliminary

phases of design, construction, and test to the more . sophisticated, complex

designs. For example, possibly a fission reactor may serve as source of

power for attitude control and for electronic equipment. Tbe introduction of

such a heat source vill complicate the engineering considerations because the

efficiency of the removal of the excess heat will depend on the thermal environment of the heat exchangers.

' (2) Activities --- Model Study 

A possible activity which, as noted above, has not passed

beyond the discussion stage, is that of the Model Study for obtaining approximate values of the equilibrium temperatures under working conditions a

simulated satellite might be studied. By appropriate choice of the model,

which would incorporate such devices as quartz windows inserted into the

sphere, probably supplemented by isolated heat - detecting receivers, it is

probably that significant information could be obtained. Such a model could be

tested in a "Stratospheric Chamber" equipped with appropriate radiant heat

sources. Or, the model satellite could be carried by balloon to high altitudes

---about 100,000 feet where pressures approximating 8 nom Eg.•would

minimize convective cooling.

• In such studies numerous experimental details would

(). have to be carefully watched. For the receivers consideration would have to

be given to the absorption of radiation by the receiving surfaces ("blackness"

to different spectral regions to the "color temperature" of the radiant flux),

also to the conditions for the conductive rental/al of heat, and to the necessary

precautions against convective cooling, since in the satellite at orbital ilt altittudes there would be no convective, cooling.

Departures from anticipated•temperature by the satellite in its early history would be reason to look for unique influence -- heating

IV by collision with meteoric matter, shortwave radiation.vith more than the expetted intensity of gamma radiation.

Such a model might lend itself to experimental work in

the design of a satellite to be. powered by a fission device.

(3) Activities -- Design and development of the temperature

and radiation sensing equipment

It is recognized that measuring the temperature of the

skin and of the important points within the satellite in order to confirm the

adequacy of the design is primarily the concern of the contractors. However,

the themal flux sensors and the temperature sensors both will most likely

be built around thermistors, hence, for reasons of design efficiency they

would be parts of a common system. All thermal flux devices have high

temperature coefficients, and the design will require a reference standard

( ? for absolute temperature determination.

nn v..... 411 Inn.... 4111011111111111 afrA5S7— el/Vo
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(UNCLASSIFIED TITLE) Geophysical iv ronmen Data or ARS, WS117L 2 April 1957 .

i Short Title: ARS Environment Proj 1764

It has been noted the type of thermal flux detector used

should be "total" and "non-selective." As distinguished from, photo-conductive

detectors, the preferred type would . be the "temperature" detector, i.e., the

absorbed energy is measured by temperature change using a thermocouple or

a thermister or equivalent.

Hence, the development and testing (including calibration)

of the radiation sensors involves the use of the same accessory electronic

equipment for imparting information to the telematering system as would

be used when thermistors are employed for obtaining temperature data within

the satellite. A minor activity from the Viewpoint of both man-hours and

dollar costs, is therefore involved adding the responsibility for development,

testing and calibration of the temperature sensing devices to the identical

responsibilities for the devices for measuring. thermal flux.

Timely and detailed reports of progress on this task will be

provided so that designs.of the temperature sensors and accessory electronic .

equipment will be available to the prima contractor for his use in instrumenting early test vehicles.

Approximately six months have passed since Contract

Al 19(604)-1899 for $40,000 was awarded to the University of Colorado for

work on this task. Relatively good progress has been made in the design of

compact lightweight transistorized thermal flux detectors available soon for

testing in high altitude balloon flights. However, for quantitative thermal

flux measurements one acceptedtechnique is alternately to expose the radiation sensor to the thermal flux to be measured and then to view a reference

standard or flux (a black-body) determined by its absolute temperature. It is

the development and testing of these assemblies of components which will

demand the major effort.

(4) Activities -- Infrared Background Studies 

In reconnaissance "vision" is involved. With the eye as the

detector, the significant bandwidths used in vision -are 0.4 to 0.7 microns.

"Vision" in the ultraviolet involves a detector'in the range 0.2 - 0.4 microns.

In the infrared, "vision" comprises wavelengths from 0.7 to 25 microns. It is

obvious that "vision" is the discrimination of an object viewed with a given .

bandwidth against a "bacitruniur i also "seen" by the detector. Further, radiation scattered toward the detector by material between the object and the

detector obscures vision (cf. visibility through fog).

Reconnaissance by use of far infrared introduces another

factor not unlike the scattering effect in .visibility through fog. That is, the

radiation from the object and its background will be veiled by the energy emitte

by the strata 'of atmosphere between object and detector. In the region from

•
I

,4

(UNCLASSIFIEDITTLE) Geophysical Environment Data for ARS, ES1171. 2 April 1957

Short Title: ARS Environment Proj 1764

4. to 24 microns knowledge of temperatures, spectral emissivities (equal

absorptions) of the specific gases of the atmosphere are required. Much is

known about the pressure dependence of the absorption but. easy calculation is

not yet possible.

Both experiiental and • theoretical Osseo under this infrared

background study are planned:

Experimental:

The design and construction of a far-infrared spectrometer to be borne aloft by balloon capable of measuring the terrestrial thermal

flux, spectrally resolved from 4 to 24 microns, etc. The work to be

contracted.

Design and construction of balloon borne equipment to

measure attenuation of the infrared solar flux in the region of 0.8 to 9 microns

at various altitudes from 4,000 to 100,000 feet, with sun at low altitudes to

increase the path length through the atmosphere. The work to be contracted.

Theoretical:

(3) The thermal emission from model atmosphere corresponding as closely as possible to the terrestrial atmosphere will be calculated

using the latest available and suitable modified laboratory transmission

functans. The emission will be computed for various heights to be later

specified in the atmosphere. The work to be contracted.

Possible contractors, and the possible Principal

Investigators are:

Johns Napkins University, Prof. John F. Strong

University Of Utah, Prof. J. V. Males (with Prof.

W. Elsasser, Consultant, Scripps Institute of

Oceanography)

Aerotronics,.Glandale, Calif., Dr. Gilbert N. Plass

University of Colorado, Prof. W. S. Renee

University. of Denver, Mr. David Murcray

• Ball.Bros. Research Institute, Dr. David Stacey

(5) Activities - By-Products Directly Applicable to ARS 

The main groups of by-products of the program of work on

the Thermal Radiation program may be anticipated for ARS. One group is the

reduction in the uncertainty in the three sorts of radiation intensities

DD Form 613 (cont.)

- s.s. •

11111k...

o//4ea
1

•

(UNCLASSIFIED TITLE) Geophysical Environment Data for ARS, WS117L

.Short Title: ARS EnvironMent

2 April 1

Proj 1764

noted as inportant -- the solar constant, the albedo associated with various

physiographic features of the earth (both the earth surfaces itself and cloud

cover meteorologically and physiographically determined), and the infrared

emission. During the testing of the thermal radiation sensors during ballon

and rocket flights data will necessarily accumulate which may reduce the

error in present estimates of the intensity of these radiations.

The studies undertaken during the assessment of the radiation environment of the satellite will produce new knowledge about the enersettee of the planet earth and its atmosphere. The new knowledge, as well as

the sensors and accessory equipment from the task on thermal environment,

will be of advantage to the contemplated Weather Reconnaissance Project in

the event that is . undertaken. Hard and fast lines cannot be drawn separating

the work on thermal flux sensors five the work on the sensors which could be

used on the Weather Reconnaissance Project. .To the extent that work on this

task (T-39794) advances the work on the Weather Reconnaissance Project,

this later progress may be considered a by-product. However, under the

Weather Reconnaissance Prolject would be required the production of sensors

specifiCally adapted for installation in aircraft, and following the flights,

reduction and study of the data. Such work is not contemplated in the budget

proposed for this task.

5. (a) Task 39795 - Rocket and Instrumentation Support 

(b) This task.will.be accomplished through a combination of "inhouse and contractual effort.. The type of effort required by this task is

being.carried on by AFCRC under GRD P-7659. In P-7659 several contractors

have been used and have attained a competence in their respective areas

(See Approach) In view of this, competence, many of the same contractors will •

be used to accomplish the objectives of this task. Contemplated contractors

include:

Aerojet - General Corporation

Wentworth Institute

3.) Oklahoma A and M

4.)•New Mexico A and ti

The task objective is to instrument and launch research rockets

in support of the objectives of the other tasks in•this project.

Requirement and/or Justification

The requirement for this-taak is delineated in the approach of each of

the other tasks of the project..

Approach

•

v.'
(UNCLASSIFIED TITLE) Geophysical Envirooppq Data for ARS, WS117L 2 April 195'

Short Title: ARS Environment Proj 1764 n

The instrumentation and launching of research rockets require

•

The provision• of vehicles and launch facilities suitable

to each experiment. •

The instrumentation of the nose cone. This effort may

vary from simple attachment to the rocket to adaption 'of the experimental

equipment to the vehicle and its support instrumentation.

t

%;.•

(3) Collateral instrumentation for tracking, telemetering,

range safety, data recording, parachute recovery, special sequencing and

command of experiments, orientation of sensing devices (biaxial pointing con-

.. trol) and others.

(4) The provision of suitable ground data recording equipTechniques and procedures have been established under GRD

P-7659 to accomplish the desired results in the above areas of effort. In

order to meet theequirements of the other tasks of this project, the same

techniques and procedures. will be followed under this task. In particular,

the same contractors and facilities will be used, where applicable, and coordir.

X- 4a tion with necessary test facilities will be•carried out in the same manner as

under P-7659.

In order to efficiently and effectively.make use of system test

vehicles close coordination will be established with the prime contractor.

Such liaison is necessary to adapt the experiment to system test vehicles

Other Information

from the. standpoint of size, weight, available telemeter, power, etc.

ti ∎41

Not applicable

Background History

SysteM Requirement No. 5 dated 17 October 1955 subsequent letter

directive from WDD placed on AFCRC the responsibility of providing environmental data effecting the design and test of ASS vehicles. Studies by the

Geophysics Research Directorate, AFCRC, the design study contractors and

the ARS Weapons System office determined that in certain areas the state of

the art was such that additional data would be required to satisfy the design

requirements of ARS. In DeceMber.)955 and January 1956 Tasks 76971, 76972,

76973 and 76974 under Project 1115 were prepared by Geophysics Research

Directorate, Air Force Cambridge Research Center. These tasks were,

with certain exception approved by WDD 3 July 1956. This project constitutes

a rewrite of these tasks under Project 1764 in support of WS 117-L.

giant.

•
F RIC ODER

. Colonel, USAF

. 4,Assistant for WS117L

•=i41

(UNCLASSIFIED TITLE) Geophysical Environment Data for ARS, WS117L 2 April 19

Short Title: ARS Environment

Future Plans

This project is.for the specific purpose of providing environmental

design data for the Advanced Reconnaissance System, therefore, the various

task'and subtasks will be terminated, with concurrence from the WS 117L

WSPO, When it is apparent that'sufficient'data has been obtained in a particular field to satisfy design requirements or to determine a no hazard condition

to the ARS vehicle and operational subsystems.

Conversely close coordination will be maintained with the WSPO and

prime contractor so that new tasks can be timely instituted to meet requireMents generated by the introduction of new design conception.

References

ARDC System Requirement No. 5 dated 17 October 1955

Secret Letter WDD to AFCRC sub: Support of Advanced Reconnaissance System (U) dated 23 'December 1955. •

WS 1I7L Advanced Reconnaissance System Development Plan

dated 2 April 1956.

ARDC System Development Directive Advanced Reconnaissance

System dated 17 August 1956.

SIGNED

MURRAY ZELIKOFF

. Project Scientist

Photochemistry Laboratory

SIGNED •

MILTON GREENBERG

Director

Geophysics Research Directorate

SIGNED •

GEORGE P. JANES, J14

Lt. Colonel USAF

Ballistic Missile Liaison Officer

Air Force Cambridge Research Center
1. Special Annex for Mission

Support Funds

•

4. TITLE 5. Initial

Reports Control Symbol

Page of page

DATE: 2 April 1957

6. NUMBER - 1764

(UNCLASSIFIED TITLE) Oeophysical.Envitanmsnt for ARS WS 117L

SHORT TITLE: ARS Environment

la. $4255. of P-690-02 funds will be required in the performance of cask

39721 in FY 57.

6 trips to Los Angeles and Palo-Alto, Calif. at $400. $2400.

3 trips to Chicago, Ill. at $125. 375.

12 trips to New York, H.Y. at $40. 480.

Miscellaneous travel 1000.

$4255.

This travel will be essentially to monitor contracts and coordinate with

other Centers. The requirements for FY 57 will continua through FY 58 and

FY 59.

In FY 58 six (6) additional trips to HADC at $400. each will be required

to arrange rocket tests.

d. In FY 59 twelve (12) additional trips to HADC or Patrick AFB at $400.

4

each will be required for rocket tests on apparatus.

... T-39792 during FY 57. Specifically it is contemplated.

)

12 trips to Holloman Air Dmielopment Center, N.M.

at $450. each $5400.

I':...

4 trips to San' Francisco, Los Angeles area, Calif.

!, at $400. each 1600.

.

3 trips to Philadelphia, Pa. at $50. each 150.

Miscellaneous travel; $850 • 850.

TOTAL $8000.

e. Therefore, for FY 58 P-690-02

(

$6655.

FY 59 $9055.

2a. $8000. of P-690-02 funds will be required in the performance of
• ;

• C

Special Annex for:Mission Support Funds (cont. 2 April 1957

Project 1764

C

Travel to Holloman Air Development Center will be performed in carrying

out high altitude rocket experiments. Each rocket experiments. Each rocket

firing requires at least two (2) personnel for a period of a week to ten

(10) days.

It is contemplated that some of the shaped-charge experiments may be

performed by the Poulter Laboratories in the San Francisco area. Research

on High Speed Impact Phenomena will be coordinated with Rand Corporation

in Santa Monica. Temple University in Philadelphia has developed acoustical

apparatus for the detection of meteoric impacts.

d. The travel requirements for•this task thru FY 59 will probably remain

at about $8000. per year.

3a. $5970. of P490-02 funds will be requites in the performance of

Task T-39793 in FY 57.

2 trips to Los Angeles, Calif. at $400. each $800.

4 trips to Ann Arbor, Mich. at $125. each 500.

8 trips to HADC,'N.M. at $400. each 3200.

2 trips to Chicago, Ill. at $125. each 250.•

8 trips to New York area at $40. each 320.

Miscellaneous travel 1000.

Total fibbroo

This travel will be essentially to monitor contracts and coordinate

with other Centers. The requirement for FY 57 will continue through FY 58

and FY 59.

In FY 58, 7 additional trips to HADC at $400. and 2 additional trips to

Los Angeles at $400. will be required to participate in rocket data gathering

flights and monitoring contracts.

d. In FY 59, 4 additional trips to HADC at $400. will be required to

participate in rocket data gathering launchings.

3. In lry• 60 travel will be required as follows:

2 trips to Los Angeles at $400. each $800.

2 trips to Chicago at $125. each 250.

3 trips to New York at $40. each 120.

Miscellaneous travel 300. 

Total $1470.

Therefore, P690-02 '

FY 58 9570

FY 59 7570

FY 60 1470

C,-

"Mb nnnn "WO n 1 ?_ emir)
0

Special Annex for Mission. Support Punch; (cont.) 2 April 1957

it

Project 1764

1

4. $3,225.00 of P-690-02 funds will be required in the performance

task T-39794 during FY 57. Specifically we contemplate:

3 trips to Los Angeles, ' California at $400. each

4 trips to Saltimove, Maryland at $60. each

3 trips to Chicago, Illinois at $125. each '

2 trips to Bollomen ADC, N.M. at $400. each

2 trips to WADC, Dayton, Ohio at $100. each

2 trips to RADC, Rome, M.Y. at $55. each

(7) Miscellaneous travel: $300.

of

$1200.

240.

375.

800.

200.

110.

300.

$3225.

a and b Travel to.the Los Angeles area and to-the Baltimore area is predicted on the assumption that the contractors, at least for the vehicles for

scientific measurements, will be in either or both areas. Also, at least

one visit to WDD is contemplated.

►

Travel to the Chicago area is included on the assumption that contractor

for the temperature and radiative transfer sensors might quite probably be

in Chicago or equally distant from Boston, Mass.

Travel to Holleman ADC looks forward to preliminary testing of instrumentation in the upper atmosphere by balloons or rockets, or both.

Travel to WADC and to RADC will be required to coordinate the various

Center efforts.' It is possible that the number listed is a minimum and that

more will be required.

f. Miscellaneous travel to discuss specific problems with experts at various

Universities will be required.

gt After FY 57 we anticipate that because of the increased activity the

travel requirement will be increased to an average $4,500. per year.

h. An annual average of $1000. of P-690-03 funds will be required totransportation of instrumentation units during FT 58 and FY 59.

5a. $14,000 of P690-02 funds mill be required in the performance of task

V49795 during FY 58.

12 trips to HOC at $500. each $6000.

4 trips to Los Angeles, Calif. at $400. 1600.

8 trips to Palo Alto, Calif. at $450. each 3600.

144 trips to Patrick AM Fla. at $200. each 800.

(5) Miscellaneous .2000.

Total $14,000.

149-J7.- 0//41°

. .

DD Form 613 (cont.)
Special Annex for Mission Support Funds (cont.) 2 April 1957

Project 1764

Travel to BAN mill be performed to participate in launching of high

altitude rockets. •

Travel to Los Angeles will be performed for coordination of program

with WSPO.

Travel to Palo Alto will be performed for liaison in obtaining technical

information on use of system test vehicles.

Trivet to Patrick AFB mill be performed for coordination and participation

in launching • of system test vehicles.

f. The travel requirements in this task are expected to remain essentially

the same for FY 39 and FY 60.

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.Ass 24 PAGES

R & D MANPOWER ANNEX

0 SYSTEM PROJECT Q TASK Q OTHER IL DATE

2 April 1957

L. UNCLASSIFIED TITLE

Geophysical Environment Data for MS, WS 117L

Short Title: ARS Environment

G. NUNISER

1764

SAITIAL

CHANGE

s. ORG

COMP .

CODE •'

S.

ORGANIZATION TITLE • TYPE

ORO

ACTUAL

.1.101•QTRS

LAST QTR

PROJECTED DIRECT MAN-YEARS

FY w57 PT sass PT IS SQ PT IS okp

MIAS. • MORD ANAL. ROAD • MIRO NERO

GRD Geophysics Research Directors DB

AFCRC . • 4.5 5.0 !4240 q520 29.0 32.0 26.0

TOTAL 4.5 5.0 24.5 5,0 29.0--..32.0. 26.0

Total Manpower Dollars 7,938 178,360 36,400 211,120 232,960 189,280

•••

Manpower Justification Attact ads

•

•

•

•

TO COUPL

ROAD

•

••••• :!....7.•ft • --.7%-z-vnArr.,.;••=-"Tp•-v.-..p:--s

s.a•

• •

•••

•

•

•

••n•••
a..

TYPE

ORG

TO COMPL

BOND REND

lien o

both G

rough t

Waite

-13, an

durat

VETO ta'ay

•

. R & D MANPOWER ANNEX

0 SYSTEM CR PROJECT 0 TASK 0 OTHER

4. UNCLASSIFIED TITLE

Geophysical Environment Data for ARS, WS 117L

Short Title: ARS Environment

ASS OF 

S. DATE

2 April 1957.

PAS ES

5. INITIAL S. MUDDED

C NA INIII

PROJECTED DIRECT MAN-YEARS

2. The manpower requirements m Task 3

the basis that three physiciots and

nitial phasp of the program duling the

additional mathematician (DS-11) will

e reduced to three (3) through the camp

is group will be responsible for the o

atellite program. The applica.ion of

ignificant experimental labora:ory data,

p by this group also. The preparation

oring of contractual research and devel

andled by this teem. It is be'ieved th

ollision theory, meteor physics and tithe

f at least five (5) people. At this t

irat phase of the research has been comp

116

ACTUAL

MAR.GTRS

LAST QTR

of a tot

r.. Two

inning i

92 for

electro

under

requir

Lion of

tall pl

nificant

and the

d prosec.

nt, th

the sco

basic s

, the ma:

eted.

ORG

COMP

CODE

1. Task 39791 will require the service

fications equaling those of GS-L2 or big

dditional physicistswill be rewired, b

roject.

s.

ORGANIZATION TITLE FT If FY III

NON 0 AVM. NORD NORD

he pros am and

tal lab•ratory d

nt of heoreti

eneral cientifi

ion of summary a

problem involvi

ld be ndled b

this p•gram ma

infl

er (G$-

As tes

analysi

t physi

re now

and ex

ists (c

vallabl

ending

of in rplane

1 to . GS 3) will

firing crease

of this data.

super

ta, and

1 desist

plans,

techn

acoust

a team

not be

Ty matt is est mated

be requ ed duri g the

in FY 5 and FY 59

his rese ch to will

ntal r • Oket an• • •

the esta lishmen oe, •

criteri will b naafi

coordina ion, not

al repo is will be

cs, elec ronics

with a ninon use

terrain d until the

) of qu litherefo e six

of th

•
c.

ip

i.

•

(UNCLASSIFIED TITLE) Geophysical Environment Data for ARS,WS117L 2 April 1957

Short Title: ARS Environment Proj 1764

R&D. Manpower Annex (Cont.)

3. Manpower to perform research on Task 39793 will be divided into the

following listed three (3) experimental teams:

Falling-Sphere Density Experiment Team

This team will consist of'one task scientist (0S-12),

(GS-11), and one engineer (05-9) •

Pressure Gauge Density Experiment Team

one physicist

This team will consist of one deputy task scientist (GS-12), one

physicist (GS-11), and one engineer (GS-9).

c. Data Reduction Team

(GS-9).

This team will consist of one secretary (GS-3), and one computer

. .

•

4. Responsibility of the 3•experimental teams will be as follows:

•

a. Falling-Sphere Deniity Team

The responsibility of the Falling-Sphere Density Team will be

to modify the existing Falling-Sphere Density Measuring Technique and scien- .

tifically develop, test and launch a modified instrumentation for density

measurement at altitudes up to 500 Km.

The responsibility of the task scientist is to plan and direct

the over-all task program. In addition, he will directly administer the program of the Falling-Sphere team. He will consult with and advise the physicist

and angineer l in the theoretical study, design, development, laboratory testing,

and contractual procurement of the flight model instrumentation; and will

serve as Field Director at experimental test grounds:

The physicist will be responsible for carrying out the team

program of theoretical work on the applied and background research pertaining

to the Falling-Sphere Density Experiment. He will be concerned with the evaluation of the theoretical aspects of the experiment, and all experimental

progress in related fields of research. He will consult with, advise and

assist the engineer in the laboratory experimental phases of the team program, and the electronic and mechanical design of instrumentation. He will

be responsible for the'preparation of scientific reports and papers as required

in the experimental program.

The engineer will be responsible for the team laboratory experimental program, the electronic and mechanical design and construction of instrumentation. He will initiate procurement of instrumentation. He will

..2009 57-o//yd
•

4 • •

41911111111111111

(UNCLASSIFIED TITLE) Geophysical Environment Data for ARS,WS117L 2 April 19!

Short Title: ARS Environment Proj 1764

R&D Manpower Annex (cont.)

initiate procurement of and will monitor a contractor construction vontraCt

to build the final instrumentation for rocket installation. He will serve

as•field engineer during proving ground experimental tests.

•

5. Pressure Gauge Density Experiment Team

•

The responsibility of the Pressure Gauge Density Team will, in

consideration of present methods limited to altitudes of about 130 km, scientifically plan, develop, test, and launch a rocket borne pressure gauge instrumentation for density measurement at altitudes up to 500 km.

The responsibility of the deputy task scientist will be to plan,

direct and administer the program of the team. He will consult with and

advise the physicist and engineer in theoretical study, design, development,

laboratorytestke, contractual procurement of the flight model instrumentation

and will serve as Field Director at experimental test grounds.

The Physicist will be responsible for carrying out the team program of theoretical work on applied and background research pertaining to the

Pressure Gauge Density Experiment. He will be concerned with the evaluation

of the theoretical aspects of the experiment, and all experimental progress

in related fields of research. He will consult.; with advise and assist the

engineer in the laboratory experimental phases of the team program and

in the electronic and mechanical design of the instrumentation. He will

be responsible for the preparation of scientific reports and papers, as

required in the experimental program.

The Engineer will be responsible for the ream laboratory experimental program, the electronic and mechanical design and construction of

instrumentation. He will initiate procurement of and will monitor a contractor construction contract to build the final instrumentation for rocket

installation. He will serve as field engineer during proving ground experimental tests.

6. Data Reduction Team - The responsibility of the Data Reduction Team

will be to reduce telemetered, photographic, and other transmitted data

that may be supplied from airborne *unity instrumentation; and to present

this data in useful form for geophysical interpretation.

•

7. The Task 39794 Planning and Supervision will be under the direction

of a Task Scientist. Throughout the period of the task, he will be responsible for the preparation and prosecution of the general scientific plans and

for the coordination of work of the contributing agencies of the entire program. He will be responsible for all the phases of the program, including

selection of contractor, approval of proposals, supervision of both contractual
i .

(UNCLASSIFIED TITLE) Geophysical Environment Data For ARS, WS117L 2 April 1957

, Short Title: ARS Environment Prof 1764

R&D Manpower Annex (cont.)

•

and in-house efforts contributing to design, fabrication, test, calibration

and data reduction and interpretation -- in short, the integration of the

results of the contract prograa and the in-house programa. The Task

Scientist is currently available.

•

8. a. The manpower requirements for T-39795 for Rocket and Instrumentation

Support are estimated on the basis that four Research Engineers, (GS-11 to

GS-13) will be required during FY 57 to accomplish instrumentation for the

required program. During FY 58 an additional two Research Engineers will

be required to absorb the load of frequent field trips to . rocket launch

sites and to maintain the heavy schedule of rocket preparation and firings.

In FY 59 two additional Research Engineers will be required to conduct liaison

on instrumentation of orbiting and non-orbiting test vehicles. .

b. This group will be responsible for the instrumentation of all

rocket experiments in the program for coordination with launch sites, for

collection and recording of data from rocket flighs . and. for . liaison and

planning with prime contractor in use of system test . Wehicles. • .

1

1

4

MOM

.2r6-6 7- 0/a/4/
. • •• • ••••• • ••••••-• Avioi...0.•^V.••••:•7.••n••‘'.1•1•n••••••••••••,rae"rl

e erg`

I. y 

•

.R & 0 CONTRACT FUNDS ANNEX .

.

•

0 SYSTEM . }PROJECT 0 TASK 0 OTHER

a• REPORTS CONTROL bY1IBOL

PAOR •i OF, PAIRS

s. DATE

2 April 1957

4. TITLE

(UNCLASSIFIED TITLE) Geophysical Environment Data for ARS, WS 117E

(Short Title) . ARS Environment

ararewt. • MC .

• CRAPPIE

S. NUMBER

1764 • .

7• ITEM S'PROJ on

TASK NE

"'En° - me

CAT

'8bwritAcT

NUMBER

''' ens gamey YRS ". FY 57 14. ry 58 '

I" ry 59 14. FY 60 "to COMM

GOO _ OTHER OTHER 4•411 OTHER OTHER SOO OTHER BOO • OTHER

ABS Environment.

•

.

-

.

. -

-

•

1764

P•100

P-200

•

.

.

Sub-%otals:

R&E

Fund,:

Fund

..,

•

Various

st

P-600

P-100

P-200

. ..

2-117

.

'

•

160M

.

•

-

160M

6M

.

6M

427/4

-

.

422/4

.

..

•

•

1000H

•

•

•

100011

95011

.

•

.

95011

1410P.4

1410N

-470t4

•

470M

5011

•

.

50M

•

425M

425M

.

' .

•

.

..

'

•

•

•

.

.

TOTAL •

- --

.160M 6M 422E 014 100014 9501.1 141 52011 425N

•

•

01/. ••••••••."*Se rn,T emu• nw Ts4tS FORM ARE 0 ev.efik,
1t

••••• • ;v., *I.. • ••n • ••n••••• .• • NA. rp

. .

,...,

R & D cos' ESTIMATE

0 SYSTEM [1] PROJECT

.

RECAPITULATION

.

REPORTS CONTROL. I... AM

PAIIIE ,g,t, OR ,,„3,, PAWLS

As TASK HI OTHER a. DATE

2 Apri1.1957

. uNa.mossrlso TITLE

It:011111 . . 8174iogentftDat!tfor ARS, WS 117E

11. 1:141TAIALip S. NUMBER

1764

ITEM

A. PREVIOUS YEARS MEAL YEAR57 C. FISCAL YEAR58 FUGAL YEAR 59 U• TO COMPLETE

SiC OTHER ON OTHER AN OTHER IHO OTHER SI ND OTHER 

..---.....

A. TOTAL.

16014 614 42214 100014 950M *. 1410K 52014 425/1 0

CONTRACT S. AVAILAOLE 16014

• 614 .4224

e. HIM REQ 1000M 950M 1410M 52014 42514 0

MATERIEL

•

A. TOTAL •

.

•

S. AVAILABLE

.

•

- . • •

.

C. HIEWRILIS .

11. .

.

FACILITIES •

Io.

MANPOWER

7.9M — •

.

36.414 178.4M / 36.4M

•

422.214

TEAMING

II.

N/A.

.

Ia.

TEST STEMS N/1 •

•

Ii.

TEST SUPPORT AIRICRAIlleT NI A

M.

suarorAL 160M 6M 422K 1000M 950M. 1410M 520M 425M 0

1

if.

TOTAL

173.9M 456.4M 21;8.4M 196i.4M 847.2M

Arf.14C . F.?!.11L 116 PAP-VlotIS ' EDITIONS OF THIS FORK ARE OBSOLETE. "--31(t .2449 — go'/ to
1/41

1 Rewritten Project

WIROSMTUTLE (UNCLASSIFIED Title) A. 'PER3CMEL

OPERATIONS SUBSYSTEM FOR THE ADVANCED RECONNAISSANCE

HMIs (BYs= 117L) b. (SYSTEM 117L POS8)

I IMPORT 0:):::Itrg. synn.

I DD-R&D/P../iI9

. SECURITY Or PROJZCI J. 730.;,....1 he.

SECRET

4. INDEX InsiARER

R&D PROJECT CARD

87t28

L 'Woo- 0..TE

2-117

7. SUS YIELD OR SIMI= SYS OSOUP

Personnel Utilization, 65

II. COSTRACTOS AND/011 LABORATORY

v. •

Lockheed Aircraft Corp

Office for -QPRI

Maintenance Laboratory

Operator Laboratory

Personnel Laboratory

IS. DILATED

WS-117L

.' 2 April12.V 7A. TEM DLL

CONTRACT I W. O. No.

A104(647).-97

.

17. UT. COMPLETION DATES

M. Dec 1960

T ST

OP. SvAL.

.13. PT_. _FISCAL TSTINATts

56 M

22L8M

156.011

164 OM

124:0M

467 OM

zoissecnanosmnaar .

Strategic Air Warfare Systemi.

•

. (117L) .

E. COGNIZANT Mg*" Air Research and

Devitoement Commend Western Dev.

II. PARTICIPATION AND/OR COORDINATION

.AMC (I) ACIC-I

APO (I) USN/CND-I

ATC (I) USA/C

SAC (7,, Other

ADC.(1)

CIA (I) n F MiNIMIN11111

on this

S. INNICTINS MERCY

AFFIRC

-irialluTimi AGENCY

_...231 USAF

IS. REPLACED PROJECT C

This rewritten re

project dated 28

DANDPROAMTSTATCS

t supersedes New

946

sw ISIIIIIMUNINT AND/OR ASTWICAT1011 Requirement orthrillrormeit-maa estaiaished . by ARDC-STsten

Requirement No. 5, dated 17 'October 1955, which directed this Center to7iapfert the

preparation of a System Development Plan. Responsibility for technical support in

the execution of the-WS 117L Development' Plan was assigned under the provisions of

ARDC 'Witten Development Directive No. 117L, dated 17 August 1956. Specific approve

for inclusion of project for development of Qualitative-Personnel Requirements information (QPRI) was contained in Amanda:mt . /1o. 2 to SDD No. 117L, dated 1 October

1956. ARDC Project Development Directive No. • 1728, 'October 1956, directed tatpdementation of this Center's plan for development of QPRI (Project Development P1;

o. 8728, dated 28 February 1950 for VS 117L. 'Requirement for re-writing the

riginal plan for development or Q111 for ITS 117L was established as a result of

wo separate actions First: the -Weapon System Project Xdfice - (VDD) directed eaC

.11 ter concerned with the development of Min. to rewrite project development

lens to align objectives in consonance with the Statement of Work which was

7

repared recently for contractual negotiations, reference 21i(7). Second: the

k

pplication of existing research techniques in the areas of job analylia and

. escripiion, training programming, training equipment requirements and evaluation

ill provide valuable support to the development of the personnel sub-system of

117L.: . This project is designed to . yield • optimum information needed by planning

`

t

species concerned with the personnel and

#

 training aspects of weapon system 1*7L.

. .

.

V

i si. ORM CR15) ION. j CR. .je. >. L.

tst 10 r fiasil

DD 174.613 C

"

RIPLACES DO FORM 11111.

Al lank kte

I JAN ea. %mei. MAY OE USED.

SRO AM!'

I L

IL

PAU 1 OF

c.

7 pi
• •

)

(UNCLUSIFIED Titlo) a. mitsalm OPERATIONO,SUDSYSTEM-EORANDMINAAMO7

RECONNAIEJANCS SYSTAMUSYSIUM.11YL).:, b. (SYSTEM 117L P038)

Brief of Project and Objective: 

The development of this project will utilise the technical and operatiOnal

capabilities of the Air Force Personnel and Training Research Center in the

production of systematic information relevant to the personnel and training

requirements of the total weapon system 117L development plan.

Approach:

•

This project will require both contract and inservice efforts to

facilitate correlation between personnel subsystem development and equipment

development. Initially, great reliance will be placed upon the prime

contractor to develop and systematically integrate information derived from

conceived equipment design. Information will be prepared by the contractor

with consultative and technical monitoring effort on the part of the AFPTRC

project officer. Contract work in support of task efforts and in-service effort

are indicated below. •

21c. Tasks of the Project!

(1) Task 87151-IMPLICATIONS OF DESIGN.

(a) Contractor: Work under this. task will be accomplished .,, primarily by the prime contractor, with consultative and technical guidance

n

t

furnished. by Project Officer, this Headquarters.

s • .

• (b) Objective: To. provide the preliminiry ditto needed to prepare

an early report; or reports, which will forecast the general personnel

subsystem requirementi and the personnel and training problems that

;\ adoption of the system may generate.

(c) Approach: Since this weapon system does not readily lend

1

itself to the concept, of control by a major air command or primary interest

4 P. by a single agency of the Air Force, consideration will be given to the

thorough exploration of the personnel implications under various operating-

. controlling conditions. Basically, the report(s) will attempt to define

problems which will be generated by both operational plans and equipment

design In so doing, consideration will begiven:to the relationship of

u WS-117L to WS-:1071k-1 and possibly 1W107A-2 and the findings of previous

research in support of these latter systems.

.

• .

i

MIKge 2 of 7 pages
R THE ADVANCED

RECONNAISSANCE SYSTEM (SYSTEM 1171) b. (SYSTEM 117L P088)

(2) Task 87300-QUALITATIVE PERSONNEL REQUIREMENTS.TINFORMATION.

' (a) Contractor: Data will be collected and assembled by the

prime contractor for the production of reports which will be phased with,

equipment design and development.

(b) Objective: To provide manning document information, position

descriptions},--end personnel selection information 'regarding the total personnel

subsysten . of W8117L.

(c) Approach: Effort in this area will be directed toward the

development of information which can be used to describe technical jobs

associated with the operation and maintenance of the-system. From these

descriptions, forecasts of required skills and knowledges will be made.

Early identification of skills and knowledges and subsequent classification,

it possible, within the Air Force personnel system will permit forecast

of training requirements. Information derived in the development of the

foregoing area will be used for manning information when operational and

maintenance concepts are stabilized

The QPRI report will comprise four sections: General Information, Manntng

Document'Information, Training Equipment Requirements Information, and

01EToraation on Special Problem Areas. The format of the report will be

patterned after AFPTRC QPRI reports which have been published for ballistic

missile systems.

Section one, °moral Information, will describe the general purpose and

function of the system, as well as stated or assumed concepts of op•ation

and maintenance.

Section two, Manning Document Information, will: identify all equipment

associated operator and maintenance positions; indicate tasks performed within

each job-pesition; indicate skill levels required for those positioncrequiring

new personnel skills; and reference Air Force specialties which most nearly

identify the job-positions.

Section three, Training Equipment Requirements Information, will identify

in general_terms the special training devices which will be needed to

impart new skills required for the operation and maintenance of the weapon

system. Further action in this area is defined in a subsequent task.

Section four, Special problem Areas, will include an expansion of the

problem areas (identified in the "Implications of Design" report) which can

be isolated under a specific set of conditions. This portion of the report will

identify personnel problems of an organizational and/or command nature.

Page 3 of 7 Pages
C.

(UNCLASSIFIED Title) a. PERSONNEL OPERATIONS SUBSYSTEM FOR THE ADVANCED

RECONNAISSANCE SYSTEM (SYSTEM 117L) b. (SYSTEM 117L•POSS)

(3) Task 87152-TRAINING PROGRAMS AND PROCEDURES.

Contractor: None.

Objective: To make recommendations for the training program

and training procedures to be used to Obtain skills required by operator

and maintenance persodhel of the system.

(c) Approach: Recommendations for specific training procedures

will be made in consonance investigative findings from prior tasks.

Elphasis will be given to those areas in which the training of skills may proye

particularly significant and difficult.

(4) Task 871531TRAINING EQUIPMENT CHARACTERISTICS.

Contractor: Preparation of a report on the training

characteristics-of • required trainers will be an in-serviceMfort.

Previous contractual efforts will be need, i -applicable.

Objective: To identify the special training devices required

for the WS-**,L-training program and define the characteristics of the

individual trainers.

(c) Approach: Consideration will be given to the adaptation and/or

modification of research instruments into prototype training devices. Also,

attention will be given to the possible use and/or adapting of special

training devices,' developed for the ballistic missile training program, which

possess characteristics identified by this task effort, e.g., Radar

Tracking and Guidance Computer Trainer.

O

VA" ..IF`

Page 4 of 7 pages

I
Vj

t

. 41111111111ft .•

(UNCLASSIFIED Title) a. PERSONNEL OPERATIONS SUBSYSTEM FOR THE ADVANCED

RECONNAISSANCE SYSTEM (SYSTEM 117L) b: (SYSTEM 117L P088)

(5) Tank 87154-PROFICIENCY TEST DEVELOPMENT.

Contractor: To be determined. Partial in-service effort

by Personnel and Maintenance Laboratories monitored by this Headquarters.

Objective: To provide valid tests of the job knowledge,

skill, and aehlevement verity for meimnring the progress and/or proficiency

of operating and maintenance personnel.

(c) Approach: This activity will consist essentially of

establishing, monitoring and evaluating the test materials to be produced on

a contract basis.

(6) Task 87155-HANDBOOKS AND JOB AIDS

Further detail on this task will be provided•as the system progresses.

(7) Task 87156-TRAINING EQUIPMENTIESTING

Further detail on this task will be provided on this task as

system development progresses.

21d. Other Information.

(1) General. The information basic to •the preparation of reports

required by Task 87151 and Task 87300 efforts will be obtained through-...

contractual effort. Publication of these reports on a contractual basis

may be accomplished with this Headquarters acting in a consultative and-. .t rt

monitoring acapacity It is anticipated that contract funds in the amount

indicated in ARDC Form 110 will be programmed through funding action to

be taken by the Weapon System Project Office for WS 117L.

Tasks 87152, 87153, 87154, 87155, Ina' 87158.1ave.baen:.included_under

the assumption that Tasks 87151'and 87300 will'predece in/formation which

indicates further effort should be expended. to meet an Air Force requirement

for informatibn in the areas covered by these tasks. However, further

development effort will, not be expended in those task areal in which the

associated final activities are purchased by the Air Force as a contract -

service, e g. Task for development . of handbooks and job aids will not

be undertaken if it is determined manning on a contractual basis is

required or desired.

.

(2) Survey of Existing Standardize Equipment or Techniques.

Node except as discussed in Task 87152 and Task 87153.

ae"

v•••

•

Page b of 7 pages
UNCLASSIFIED

(UNCLASSIFIED Title) a. .PERSONNEL OPERATIONS SUBSYSTEM FOR THE ADVANCED

RECONNAISSANCE SYSTEM (SYSTEM 117L) b. (SYSTEM 117L POSE)

Survey of Similar Equipment in Progress of R&D. •

Survey 41/11 be made to determine possible adaptation of research

instruments into special training devices. ltimilmr-expioratien will be

made. in the area of trainers being developed for ballistic missile systems.

Replacement Recommendations. None.

(5) Statement of Effects.

This project will yield information useful to the agenciesrespoisible

for programming the.personnel and training programs required to properly man

W8 117A.

1

Background History and/or.Progress.

Since the writing of the initial project card, several visitis have

been made to WSPO to determine tunding status and to obtain general information

on status of system development. As previously mentioned, representatives

from this Center participated in preparation of statement of work for

contractual negotiations. WSPO clearance was obtained to make initial

contacts at contractor facility to discuss development plan relevant to the

personnel subsystem. System contractor personnel were familiarized with the

URI program and the nature of tasks involved in the development plan for

personnel and training problems. Visit to contractor revealed that

eoppettnt staffing has been accomplished to perform the caliber of

work-Hentred. • Arrangements -have. been-made to furnish contractor with

format guides for reports to be published under this development project.

Future Plans. Tentative arrangements were discussed with prime contractor

for publication of Task 87151 report during June 1957. Also discussed were

plans for publication of initial QPRI report (Task 87300) during December 1957

or early January 1858.

The project officer will maintain close contact with WSPO to establish

proper phase relattousktps-oi-pniject-mtfort-witirequipmen development

status which is, in turn, largely dictated by funding actinn.

References.

ARDC System Requirement No. 5, dated 17 October 1955.

Project Development Plan No. 8728 (DD Form 613), 28 February 1956.

(3) WS 117L Development Plan (WDD), 2 April 1956.

page 6 of 7 pages
-wraiRereievt-tedo,

7,100 STANLEY ArALCIK

•

Major USAF

QPRI Project Officer

THOMAS WILDES

Col USAF

DCS/Operati6ns

C

Li s. . • b.

•

(UNCLASSIFIED Title) a. • PERSONNEL OPERATIONS SUBSYSIEU. MAX ZEJ.,711.11C411),.

RECONNAISSANCE SYSTEM (SYSTEM 117L) b. (SYSTEM 117L POSS)

ARDC System Development Directive No. 117L, 17.Adgust 1958.

Amendment No. 2 to ARDC SLNo. 117L, 1 October 1958.

(8) Project Development Directive No. 8728, October 1958.

(7) Letter WDTR, Bt ARDC, 18 December 1958, subject, "Meeting

of Technical Advisors to WS 117L".

21h. Coordinationtand Signature Block.

Responsible Center, AFPTRC.

•

•

1.116);OL

FREDERIC C.4 ODER

Colonel, USAF

Assistant for 113 117L

Technical Operations OW

. 4 Page 7 of 7 pages
WM/5bl moon

4w4mymnuo1 proTtropay-z

PRFANITTalteW

WWI zIrrigg% =pICZZUTUTVAL

111•11111•1111111111•1=11111111111111111111111 ;0Jd

ger t 1310qPUUR

111111111111•11111•ILIEll

TULL9 00Jd 91 s711s . ff -nluTs41

n11111111• n 00ne nab

Tama ;a suopeundat

ilifFnat saul4

66

1.1110Z 01 LQ 111

s 1 1 ' ieeeeee re vvvvvv *

.

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SI 

, A4 111 59 a

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YM 1111111

NO 123(0114

winaams

INLES.

eiV541111

net z.

111110 

70914! 7Gi1iatOD SLAINISS 

iniL TO "4"3 (s = mutt '4 MU A mun aims s) surwaroomon mouvAav

0 'mum. am memos sumo= IUMMINd 'II (*UTZ amassinom) 21111 •

*mu° 0 xsvi. 0 logroad al wsuAs 0

MINOS 0 It V •

idon; . •

!---":1 • •
1. S. lutPoirrs corrntoz. srmeoz.

ASt 1 OP 1 RASES

R & D MANPOWER ANNEX

0 SYSTEM gg3 PROJECT q TASK 0 OTHER S. DATE

2 April 1957

PNCLASSIPIXO TITLE a. PERSONNEL OPERATIONS SUBSISTR4 FOR THE

ADV RECONNAISSANCE SISTA( (STSVM 1170 b. (SYSTEM 117L . . FOSS

III.

s• INITIAL

.0 HAWS #2

S. NUAISEN

8728

7. ORO

COMP •

CODE

S.

ORGANIZATION TITLE

a.

TYPE

ONO

ACTUAL

MAN-QTRS

LAST QTR

PROJECTED DIRECT MAN-YEARS

19 57 58 FY IR 59 FY IS TO CONPL

AV AL wgwo ATAL ESSPIO ROAD NORD ono

PTQ Office for QPRI R .3 .9 2.2 .2 .4 3.5

PT? Operator Laboratory R i .2 .3 .2 .4 1.6

PTR Maintenance Laboratory R i 1.5 1.5 3.8 3.8 4.8 •

PTS Office fon Social Science R # .5

Programs

Total Manpower .3 2.6 4.0 4.2 5.1 9.9

Total Estimated Manpwr Dollars 361,1 43M 84M

••• ••n ••••7"-••n••••001,0{•:••••••••••;•••n•91.4".rft.•••••••:•••%••,.. ••• .••••••-•"'-...t•n••••••••n••• • •••-• • .• •••

ra%

•
•'71'.‘",••••••••• ....,••••••••-• • ••••••!..- • • t • • • • ••• ••n •••• • = • ••• .1.4 •

rib)

173!

•

.

.

..... •

' canner FUNDS ANNEX

0 SYSTEM 0 pawns. 0 TUit 0 OTNEE

•

1. warn corrnew., •IMMOL

r"

P&SE 1 Or i

& eaTt

•

.

:2 ken .57

4. n".8 (UNCLASSWIRO rita.) a, PENSONNEL OPERATIONS

SOSSIST11 FOR TEE ADVANCED RECONNAISSANCE UST= •

(272TEN ult.) .b. (SYSTEM 117L Ma) 

•

s. unty.m. n & miatocit

87211 GlIamila it.

7.

AINIVraTiO

•

U.

.... AerT T........ NINE=

t. IS.

POOR TSARS

Oa Illsessalkl

II. •

ev 97 OA OsasseaS

U.

re SS OM Ossessaf

IL

ryS9 Oa O pssamed

IS.•

.... 60 *Ow Oreserso)

IS.

egiseavyingi

•

Syeten 117L QPRt

.

.

*.

.

. .

.

. •

•

. .

•

,

.

.

.

.

•

.

. •

.

.

-

.

...

. .

. .

•

.

•

.. .

•

•

12.8K

'

.

•

•

•• •

. .

. .

. .

.

.

.

356.0K

- •

.

•

'

144.0K

.

•

-

•

.

•

•

81.011

.

.

•

•

.

•

IA

TOTAL . 12.8N 156.011 144.0N 81.0m
---••••••

.

.••••••n••

0

ti:•• •• .

I.

R & D COST ESTIMATE RECAPITULATION

0 SYSTEM g3 PROJECT q TASK 0 OTHER

P.. MOM, CONTROL STORM

',Asa 3. of 1 ►A1SKS

a. DATE

.12 Apri.1.1927

4. UNCLWI►IES2 "T " a. PERSOMUIL OPERATIONS

RECONNAISSANCE SESTA (MEM 117L)

SINISTSTIM

b.. (SIREN

FOR THE ADVANCED

217L. WE

TOARST--77

ITEM .

 . _ . . ...

POMO

"4"2."...0

--- ---

8. NumsaiR

8728

A. - Paavioo %%ANS a. . PIS AL FISCAL YEAR 14 FISCAL, yEAR 59 11- TO COMPLETE

MN OTHER SOO ' OTHER MN OTHER GNI on

•

•

.

A. TOTAL 12.811 156.014

.

144.CM 81.0N

CONTRACT •

•

S. PMAI .

-.

C. NEW PIRO

.

12.8N

.

156.0N

.

_

144.114 SI.Cff

MATERIEL

A. TOTAL

a.

S. APPILAWLf

C. New RIM •

.

•

. _

S. ••

• .

FACILITIES .. •

1o.

MANPOWER UN 111I •

.

•

20K 2311 4114 44•

TRAINING -

•

.

. -

It.

TEST ITEMS

Is.

TEST SUPPORT AIRCRAFT

.

- .

SVOTOTAL

IS.

12.8M . 156.0I4 114.014 _ ,__61.0/4

----• I , eis 11 v 1711n1 9nm 16414 23M 1 1244 LAM
(Ititince. It! IV I:J.0.1 • m'y

. • .1*:4 teth

Tsat ttte •

111.1. 1 LIIIIJU IIUVLLJ iUUI3L UUIll Linn luau AU/ . VI- IV je

Los ANGELES 4: 5, CALIrCIRN/A re: GM67. 3-49 CO

INTEROFFICE Co 4RESPONOENCE • .

TO: Col. E. N. Hall

or-- •

1‘. 1*

cc: H. R. Lawrence DATE: 3 May 1957

•

SUBJECT: Transmitting Copy- of GM67.3-49 FROM: R.. F. Mettler

Attached to this transmittal memo is a copy of R-W Document

GM67. 3-49 entitled "Proposed Use of IRBM as Booster for

Multi-Stage Vehicles" which you requested.

•

Please note that this is a preliminary dosurnent, the technical

content of which has not been checked or reviewed by Dr. Dunn's

office. I would suggest that questions on the technical content

of this memo be referred to Mr. H. R. Lawr ce.

. - Ct- l ei 5-1 Enclosure:

GM67. 3-49, Secretary Copy #1 Lb. VositilL,A

R. F. Mettler

t-

•

P0144 Nu. 140.1:

(
t

U. L. ca..4

Colonel, USAF

Director, WS 117L

2,21113.A.MUM FOR COLON TEF.HUIE AIL 2i

•

SUBJECT:. AFFTRC Support of MD Systems Development

In response to your comments and suggestions, further

investigaticn reveals the Missile Research Unit,. Maintenance labora--

tory Field Extension Nunber 3, under Lt Colonel Beers is premmmUy , in

being at AFBED. QPRIFrOject Officers for the various missile systems

will begin reporting for duty 29 July 1957. Tentative scheduling calls

for the WS 117L Project Offioer to report. during Amguit 1957.

The establishment of the ' Field Extension Unit and the scheduled manning of that office is in response to paragraph 2 of General

Schriever's letter of 10 April 1957. A Copy is inclosed for your-reference.

, 3. RespOnsibility for AMR° conduct of the 4S 117L.QPRI was made

by SR #5, dated 17 October 1955. Hsjor Stanley l'alcik of AFPTRC has been

active as the WS 117L QPRI Project Officer for the past year. Some of the

Current difficulties in other missile programs, in the QPRI area, maybe

directly traced to a lack of appreciation of the importance of early

attention to QPRI problems. Assessments of the anticipated work load in

this area as meriting a resident Officer, and the timing of such an -

assignment was left to the discretion of the, Comander, AFFTRO.

We have not concurred in any proposed action which has not already

:been inplemonted in AFEED, nor which is contrary to pres:Ipt r0.:innire

within the Field-Extensien Unit.

If manning the QPRI Project were to be made with AFBND personnel,

I personally would place higher, immediate priority on manning other

projects within WS 11714 In view of the fact that mannings to be done

by AFPTRC from AFFTRC personnel resources, I request your signature to

the letter.

1 Incl .

Cy letter to AFPTRC

subject as above

with inclpsures

fLe...61).c. 1.1441

sedt,(49s
t

.

I

).•

L

. •-fe.

•••*°

macs RALLIS:MC i.IS'AT'ul DIVISION

, ..1j " ,f •%.4,./. HitADQUARIERS

. # ATE EMMA KM DEVZIARt&T CO1-Z:AND

I

liDOTA 19 November 1957 .

•

14EADRANDUM V= AND EDO

.

..

SUBJECT: . (U) Joint WM' and . WDOTA Staff Visit Report

to Hq ARDC on 3:palmation of AFPTRC as a

Seilaratit.Center of ARDC

General: Col H. L. Evans: MTN, and..Capt A. A. CialleS

visited Hq-ATrTn 14;4.5 November 1957 .for the purpose of attending a

conference on the elimination of the. MIRO, and dist.ribUtion of the

AFFIRC functions and . manpower spaces within. the AMC structure.

Persons Contacted.: Brig Oen Fliddnger: Col 14c1Cerley,

Lt Col RitWk: ELS' Wilcox:14a3 StObie: Kaj Hertz, Dr. Gayne and

Mr. Christensen.

3. Discussion and Cement; Lt Col Ritter: Hq ARDC: presented

the proposed elimination of MARC as a separate Center of AMC, end.

the ARDC actions necessary to integrate the AFT= functions and non.

power spaces within the .k.'1DC organization structure. The significant

items covered by Lb do]. P.itter and. a stateuent of required AliitSM actions

are presented below:.

. a. Hq USA? has' directed that the AFPTRC be elimineted as a

separate ARDO Center.

b. ARDC will retain responsibility for the functions presently •

assifpled. to KFITECI 

'follows:

certain reduCtions in the present prcfraros and

r spaces as follows:

(1) Hq Akrele. is to be eliminated, and. the office for VPRI

be added to the Imm—fal.ltors program at liAtia.

- • (2) The Personnel Laboratory Vitt remain at Laakland • Force Base as a dat."-%ecuoe..A.U. future 7Xar.WIZEt programs and

projects for the Laboratory will be validated and approved by the DCS/P:

and DCS/D., Hq USAF.

The programs and projects of the Operator Laboratory

.vill. be integrated with the work of other ARDC eentefiimsdiree-EU---

concerned. trA0 labaqatca7 will vacate the space now occupied at • • Randolph Air .Force Base.

The programa and projects of the Maintenance LeaorAtpry

vill. be integrated with the Pcrsolrael Liberntor ►

seppint turnichod the .6.740 •

1:1a nov

Lowry rcrce

(..;) 4q. USAF hart Tr,opc.sed a reduction or 275 nanin_rs,--:a.

!spaces fr.c-z. the 704 spaces pras ..tnt34- suracrized . vi.11

C
t.

t

result in a net m:atpower anthorization of 158 spaces for the

Personnel Laboratory and 271 spaces for the efforts in support of

NIS development. Tnese new manpower levels are to be effective

January 1955.

The recommended distribution o± the 271 spaces

within the existing ARDC structure ire-as:1=mM:

Mammal Space Vehicles 30

£?PC1. WS Support ' 12

AiTpco . Ws Support 20

AWV.04 WiS Support . - • .. Ir. ... - - 46

AMC, W/S Support. 7

AFSWC, Ws Support 10

MD0, MiVS Stpport 7

RADC, W/8 Support . 26

WAD C, EFIaboratory - - )- 133

WiS Support - -)

assigned to

Total Spaces 271

The ARDC pwieosed bree out of the 46 spaces

AMID are indicated as:

BALLISTIC swam SUPPORT

Group at AMC:

Job Design Engineer:kng 

Design Specifications - -2-

Design Analysis 3

Bards:are Development

Monitoring - - 5

personnel Evaluation

- 2

5. Safety end Protection - - 2

ManningInformation

Operational MI

Job Aids 

Training Equipment Requirements

TOtal 30.

PgD-HE'lleLi Extension at Cooke AM

•

EValustion -. n

▪

n n 41.1. n -

14

10
'We Site DeSign 

Functional checks (t4an-igeehine)

Reliability and System Tests -

3

•

•• 1. Personnel Bub-system ". 8 2. • Safety and Protection so 2

Total

3.6

t8) The fallowing items are noted regarding the 46

total spaces listed. above:

. • (a) The reccumended AIME spaces include:

26 - officers

18 . civilians

2 ir airmene (b) ARDC -indicated that:the spaces are separate

from the e• ergeny augmentation and FY 58 ianpower requirmaents

heretaforestatedbyAFSMD.

•

.AREC indLeated that the spaces W.": to. provide

far normal huniazi factors support required rim. the Veer:milt .koz1.113 missier

and no figolitiotial. miesions in tae Area of. human factors technical programs viii be imposed on AFB10.

Two medical officers - One Occupati•health,

=done Industrial fygiene Engineer are included in the °facer spccee.

(a) The total civilian spaces include support -

typee, clerics etc..

(f) A total of 70 Masan. factors officer spaces

exist in ARDC of which 26 or 37* have been allotted to MAD. AraL7

requested that MUD consider . replacing some of our. officer spazes

witeprofessional citilians, if possible, in order t.orelieve the

shortage of human factors officers in the other ABDC centers.

(9) It was agreed that AF24Dirould provide Haq AMC.

with the following information by' 25: Movember 1957:

Organization structure or distribution of

the 46 humen factor spaces into the emitting AFBN0 organization.

Manning Inrormation:

area •cl.enc.,isirytti.Ons

Rank c3.v114 fat Erkee svread

Jcia titlea

Jpb dca,irintien

. •

-a
•

i •

1. 

•

4. ired. Actions: .

VDTH and SWOT vai develop the information indicated

in paragraph 9 above for delivery to K ARM: on 25 November 1957.

r ecam-psismop "la WDTN and WDOT will.pzop , see appropriate internal

_AFRO policy on the integration of the human factors support

function within

•

EVAUS

Colonel, USA!:

WDTN

••n•

I 7, -•-••• 4' • •

ArnitiaA. GOMES

Captain, USA?

.WDOTA • •

•

.
4300

lar.luvaii.AtaDtat FOR pit Rirk.011,1 31 Dessoriber 195?

51.111Iktett.. Telephone Cpaill Trees Coleael liavu;iste to Gaserel kitiand

. sa A. a.. Cetaial thoelate aetrlsr

that yertertay• A Hot Laiv es the astreassettes progress

14 94.Sc74 aromas. was "duo disappointed 4- la dkti approach eat every- I

thing tIse4 As a teas% Catena Nwhatate slantoot ithet seterhiaatity w

'kw.* s aileek proses,. ate to cease up teak seaothtes by bteesley

Oars rat Pont *a a aegpbararistist yeehar to the FT Si sad S9 pe ►sswele.

ATIDG peas waft net gessideted eiteisate bessael it *W*'$ carer.:

1114 apeeseary it didn't eferttr;:e: *ma• we are at page** sat

it ass at psojected eat. Sawa. Sew golds Ms. svf31ire gives ARK,

asuer• •

Gelesud iirni&Kte eatit Oray were faced Iola swats* vp Isiah ow-40o!

eiT4 =1444 errabld be a cctsgt &or teriesplo, the woad pros:ige

*ad cog ekiitemo rxtia es Ike Wks* past sit'at eite far e.re 1GP3t 7.1:sy

wzot in talk clo.$0.:4 the 11.74 aod peidelps Mira eta "Vdate to* tos44

VeAt Wqh VAS fs) cis la* It te..4 . Law sack/ a. ARDC "al wee

Itsg. c-ks• Ce44.‘ .dowststscrient ant revs/trek and OW) 14157"1 Its • .

alAnciat semn,:fia -- cOmf..ott irc1041,3 wars**. witepttis eftt`At 2:-16

at4 toksaiseen Cease wW bo inalena' :1 is the 4mvalopakest *at sweearab

pacEN&,o.

Alta &wee few ss is 344114 kie R&D nod Psi'"? 39, $71t14

RAD. Ms* wgact Ictams lerwouateb we mod flew end above eict >x e"

wick'. c.o.* be deco with WI attrtiostri& 11-4/74** towasd tIse bagLet:: a,Zer;.ty

'6'02=4 Mk** tadatticat ifit*egunee4 remaerch evivea. rift 1:041 . •

thou t-14 11. Zs ilrassi 1a TIC eM irtrga CI* b' ItS latdiss Ix FT Wit

what :arm be the Wisest pa..1wetty 10.11.4* we would tef. ,

Gemerai Pelt see& the above latesesettea by 1a jr 1st the

laboacs bissatsgs ano the ArciaC ilatartak to eat setae% new weat

te ksterw what we watdt, do alth the 644.11enal sweep mad some a tea

ekairseasiWits • • Wicket entrtfia, what ("mkt be aetekrisoltetsig #4th

as fik, Naos► pert at the. trOciat pretist he an 410914; the tep,u2411

preStet edithigestese Mad* et haste. ease. *Pah. aceelarin*R tZ.* elosterri.,.!e

1)&1'4 at 1 a* “fagracesso of eke saes eteikene, cart perespa s

0.Z1.41-1 potelatc3. X is sok Erscasoary ts..44 1hr abbwo bi ats Eirrat

Ltsv-lat:;!A as N44. 0.:14 ease arc a Jot 4+ s'Asr vocs wevAt ".iv if, Ile,

k44.1sgs rimtvve:.)4. prxejc.s.gct nt,...1S.tegrol 1.Lr tht

trxmfai.1.4.;ai w41 'mat V> tirs.:1 vi;t3.*:k.

*Zoom Lbiorattzercmst • nivavc; moiar-4.
ACTION PRIORITY

INFO

"" At.:"

•

,At`

-

!: L1/4'

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.•

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SECURITY CLA S.

JOINT MESSAGEFORM

Fr

; C /4"

I'.• :•••

SPACE BELOW ItIIIBE.PED FOR OOMMONJOATZON CESTEU •••

41

"A--PARRPHRASY. NOT P.:t4..jr.in •Y.t7U

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L u 3 j

1 PROP. ,,b.j0-,CATZOORT B .1•-•".. 7:;;;;;!..ty a. 4. (Neil /J N1 :.'.j t Ri1.1: ::ENCES BY .:,11:1114T GROUP PRIOR TO DECLASSIF;CATION."

PRECEDENCE TYPE FIFA (0M16)

11100K I MULTI I SIMILE

ACCOUNTING

SYMBOL

ORIG. OR REFERS TO CLAM FICA': I: OR REFCceetiC.1

FROM: COMMANDER AIR FORCE BALLISTIC MISSILE DIVISION SPECIAL I NSTRUCT It

INGLEWOOD, CALIFORNIA

TO:

COMMANDER HQ ARDG

BALTIMORE, MARYLAND

•

(SECRET) FROM WD0-1-2

ON 31 DEC 57, -6ebetW.ItL--fttt;It====0, 1-::0 USAF, P.EQUES'..ED

AFBMD RECOMMENDATIONS FOR AN EARLY ASTRONAUTICS

CAPABILITY, INCLUDING COS IS AND SCHEDULES.. TEIS I14.-ORMATION IS TO E USED FAY GENERAL. PUTT ON S SANITARY IN

CONNECTION WITH THE J01.- SON HEARINGS. IN ORDER TO

ACIUEVE SIGNIFICANT PERFORMANCE RESULTS DURING CALE1 DAR

YEARS 1958 AND • 1959, ALREADY_ DEVELOPED BOOSTERS AND

GUIDANCE COMPONENTS WILL BE REQUIRED. T} OR PLUS THE

VANGUARD SECOND STAGE IS PROPOSED AS TM BASIC BOOSTER

UNIT. WITH THIS VEHICLE, TM FOLLOWING TYPE MISSIONS

DATE

COULD BE PERFORMED: A. PHOTO RECONNAISSANCE SATELLLTE 3 

MONTH Yr .

/11117.4. A RECOVERAW...E DATA CAPSULE. WE BELIEVE THAT ...TAN ..,

SYMBOL

-...

.... a .:......c."1-.'1" - '

... • - '. ' 7'......:, 7:.'::•.41-i.'";c1. it

•n•.`".;"Pc:44••••:.. ..

W TYPI 0 NAME AND TITLE (E4.11 413,r4h '4ee?..:4II....!‘.iI:`•• Fs

R • ,

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• JA"

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TYPE MSG (014c)

MULTI I SOKOL!

ACCOUNTING

WINAROL

ORIG. OR FeClvaRS TO .CLASTIFICAVIe

OF REFERCNC..i

INFO

PRIICIEDIENCC

ACTION PRIORITY

Plt°141 COMMANDER AIR FORCE BALLISTIC MISSILE DIVISION

INGLEWOOD, CALIFORNIA

sPacim. INSTRUCI

(SECRET) FROM WDG4-2*(CONTD)

AN ORBITING TEST COULD BE ACHIEVED BY AUGUST 1958 WITH

TELEMETRY EQUIPMENT BUT NO CAMERA. THE FIRST RECOVEP.A:OLE

PHOTO DATA FLIGHT COULD BE ACHIEVED BY•SEP 1958 FOLLOWED

.BY FOUR ADDITIONAL FLamas THE REMAINDER OF FY 59, A T TAL

OF SIX VEHICLES. THESE EARLY FLIGHTS ARE TEC1-LNICA.LLY

FEASfl LE UTILIZING THE BOOSTERS AND RECOVERABLE DATA

CAPSULE TECHNIQUES THAT ARE ALREADY DEVELOPED. AN

IMMEDIATE. GO-AHEAD IS NECESSARY HOWEVER. B. P-ECOVE 1.1LE

ANIMAL SATELLITE USING RHESUS MONKEYS. THE FIRST FLIG IT

WITH ANIMAL RECOVERY COULD BE ACCOMPLISHED BY JANUAJ

1.959 FOLLOWED BY THREE ADDITIONAL FLIGHTS DURING THE

REMAINDER OF FY 59. LUNAR MISSIONS COULD ALSO BE

ACCOMPLISHED WITH A HIGH PROBABILITY OF SUCCESS BY

A TVIIIINTC1 T1-1E VANGUARD TIMID STAGE0 1 DIM VEHICLE. TWO

E • L

DATE

3

1 WV:

MONTH

SYMBOL

TYCED NAME AND TITLE /A t-ma&T;:-414*-K•ZAN13%,-.

1471,z . I VASIL •, •

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Curry cLi.selIPICAVZ..- • -

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GMUPITY CLAUS,

JOINT MESSAGEFORM

8P406 111:LOW kraquo r n 003(M•I►ICATION COTrAit

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PRECEDENCE I TYPE MED (Meek) ACCOUNTING

ISYNROL

•

ORIG. OR Reruns TO CLASS !FICA.;

or PDT ESTN

ACTION PRIORITY MULTI *INGLE

INFO

FROM: COMMANDER AIR FORGE BALLISTIC MISSILE DIVISION

INGLEWOOD, CALIFORNIA.

SPECIAL INSTRIJO'

THREE

TO: •

(SECRET) FROM WDG-1-2 (CONTD)

TYPES OF MISSIONS COULD BE ACCOMPLISHED.

IMPACT ON THE MOON WITH :AEAC.ON OR

ACCOMPLISHMENT OF MISS;ON. FM It VEHICLES

PROGRAMMED FOR TIUS MISSION. nit FIRST

BE ACCOMPLISHED THE LAST QUARTER

BY THREE AT TWO MONTI; INTERVALS.

FLIGHT Warn MEANS OF PROVING ACCOMPLISHMENT.

VEHICLES SHOULD BE PROGRAMMED )'OR

FIRST FLIGET COULD OCCUR Fl Y JANUARY

DURING THE REMAINDER OF 109. THE ESTIMATED

THIS PROGRAM ARE AS FOLLOWS: MISSION

FY 58 $6.9 MILLION FY 59 $7.8 MILLION.

FY 58 $3.0 MILLION, FY 59 $7.6 MILLION.

FY 58 $6. 4 MILLION, WY 59 $3. 7 MILLION.

C.

OTHT:IL DEVICE

FL.T.CIIT

CY

OF/195E: rOLLOWBD

D. Ciit.C:Utv1.LUNAL

THIS MISSION.

MISSION

MISSION

MISSION

SHOULD

1959 FOLLOWED

A - 6 VEHICLES

HARD

TO PROVE

BE

COULD

POUR

THE

11Y

COSTS 01?

B - 4 VE1-CL

C - 4 VE.}:aC

D - 4

MON1 It I •

JAW I

SYMBOL

TYPED NAME AND TITLE toltiP."71.-7.rr . •

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ACTION

SECURITY CLASS :ATION. ,

10114T MIISSAGIEFORM

irrt77"-

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'1111403 SIZOIr Af,r4APVBX179it..00101VIIICAtION

JAN 4 G2 II "

ORIG. OR RIVERS TO

PRIORITY

ACCOUNTING

SY14•01. .

0.i.er tr,

Or REV Et Ft

it

•

SPECIAL INsTn Ir

TO

(SECRET) FROM WDG-1-2 (-CONTD)

VEHICLES FY 58 $2.5 MILLION, FY 59 $11.3 MILLION. AN

ADDITIONAL LAUNCH COMPLEX CONSISTING OF TWO STANDS A• D

A BLOCKHOUSE WOULD BE REQUIRED AT A COST OF APPROXIMATELY

$8 MILLION WHICH WOULD BE REQUIRED IN FY 58. THE TOTAL

FOR ALL FOUR PROGRAMS IN FY 58 $26.8 MILLION, FY 59 $30.4

MILLION. TEESE COSTS INCLUDE THE COSTS OF THOR AND

VANGUARD BOOSTERS AS WELL. AS THE DEVELOPMENT, PROCU

VENT AND TEST OF PAYLOAD AND ASSOCIATED GROUND EQUIP. vi.EN T..

TrOR PRODUCTION WOULD HAVE TO BE INCREASED TO EIZI-2IT PER

MONTH IMMEDIATELY IN ORDElt. TO PROVIDE. THE ADDITIONAL

THOR BOOSTERS REQUIRED. THE FIRST FLIGHT DATES ARE

oviiajLKeMI FC;e4C• Pea eirtr ea .4.

LEDICATEDAONA INILY• ONE PROJECT OF TIM FOUR BEING IMPLEMENTED. SIMULTANEOUS IMPLEMENTATION OF MORE THAN DATE

3

ONE PROJECT WOULD RESULT IN SLIPPAGE OF TEESE DA 7.1.§.. mOt1T+S

•••1

SYMBOL •

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r Rtm.s.ctie CU 1,01-.*, OCT At. WHIC.V! WILL I::: 1.111X• Ur, tL rxtte.t..%

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ORIG. OR RUINS TO CLMSIFICA,

OF REFEREt:

wer4ow PRIORITY

SPECIAL INSTRUC'

(SECRET) FROM WDG-1-2

ALL COST FIGURES ARE PRE ARY AND SUBJECT TO REFINEMENT.

syNror..

W TYPE!• KAM& AND TITLE tritOo.tbrt. O reogrol)

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wrg .ty► atep-4/.14AME AND T17 LE

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D. 7 .. r i. til. di r r General, -Z7S. t..1.'

Vice Commander

SECURITY CLASS Amu

JOINT MESSAGEFORM

PRECEDIVICK

soot I owl macs

TYPIr MSG f0A.41 AccoutenNo

sveRSOL
CLACEI ► ICATIOt

OF struiptcr

FROM: C C Ai; .1) zit .n.s. reortCz nALLISTIC 821/SELLE DIVISION

I.NOLC WOOD, CALIFORNIA.

SPECIAL sorrouvrie

COlvilfANDEak ARM.

B.ALT1111.011Z, tIAILYLAND

(SVC:11Z 7') rziam Z

Clki 31 Dr.c. 51, eetorz.=-1.0 tranrrtrittit To, IIQ USAV ILEOUr.S71:4)

:1-4.:674-34.ENDAWLOVIS IrO.F4 AN Flatli.LY AS• ILON.AU TICS

INCLPLI.L.k1O at.vaitairagr.s. inds

1.1.1.21.(11 IL 7.0 UCLD D a GI:14411AL PUTT ON 8 MAU

'WITH TI1 . .10101SON 1.1EARDiaS. Oks).F.M TO •

is^=t1Z .V r..ICiNIFICAN T PEltrOk..MANCE RCa2JLTZ Du.r.ING.pit.LE1,1

Y2-4.1-1;8 1958 141D 1 959, 4L'AZA.01( D:.VT1LOP3 /..) DOOSTER`.4 AND

CCAIPON.VITS WILL. EZ THOZ:. 1.1112 .

VANCIVA.1.0.) SZCO.ND STAGE. IS PROPOdED .A.S THE; BASIC BOOST.Z..;

Val% . PITH Ti.I.S vERIGLE. FOLLOW/NG TYPLI.ILSSIONS •

DATE

COULD sr, PZIA.FORIWZD: A. PHOTO R.F.C.OZZIAL5.9.ANCE a/max " - • MONTH

TIXIC

YEAR

• 1

ISTMEEK, ..C1:47• .

Tvpiro NAMC 4110 TITLE (Riaaahlre.fregyirat)

•

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IPHOPh.

rii-tc—uArre tot.

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F4R1, 141:e 173 IMPLAT.E.• OD PORN t OCT AO. %%MU %Mi. sr FArAUF1!:0

•
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CIAPPIF

OF PIEFERr t4:.E

cbt.c/i1:14DER M iPSCt EuklaUsinc *MILE CeVISfON

MaLEWOCali CALFORNIA

Pitoms *maw. starrn uct o

•

(41fIC RE T) MOM "ilia's-1.4 (CONTD)

fal.BIZING TT c.:Ori.u) BE ACII,TEITIM BY 4UGUST

T1.1.1.r.443:- TAT 1UU'M 7t4D BUT MO cmattax. fls 17.1:112 E.ECOVMABLE

/litcs.wx. COULD, B.T. ACHIEVEil BY SIW 1s8 voi4.) Tarl.)

111.1:11i7S TUB 54.154;AIS...9illt (F FY 5`14,

ri..tr t.ia. 11:..1-iesLAS. 11114SE w.i1a.711.141 . • 1t; Ma; VatZ, .ELNICALLV

.1•7:4115113.1.417. UTILIZ.DtG fl nOontaust AND ta.COV)CA AB= DATA

1;;L:GLII.,ar:,111.4: MAT Liti. ALREADY DEV.CL.W;T....U. AN

tLATi. .AHEAD )fOVIZVElt. B. XOVt.,ISLT

:z...!1/41:4AL• uaNz4 ma.r.stri; lelCogigSTS. FieltIOT

Tri7 alrCorraY COULD BB AC GOientrilitl:1Y ..TALCUA.t

159' FOLLOW114.1 BY THD.EC ADDITIONAL FLIGHTS D131141+10 Tkre

P..c.itr/ABilnai. O. FT $ti. LUNAR 1413s10116 COULD ALSO ez •

ACCOMPLISTMO WITH A Mal PROBABILITY Or LIPCC6 BY •

• 171r. VANGUABDTHILWSTA.= TerbrarrlilrICLE:.

DAVE TYNE

YFAM

If ?VMS:0E4E1 AND TITLE (84/00turs1 E Ir‘ralem1)

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nr . ?NOM I smelt

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SICCUF:ITY CLASSIFICATION ...

TYPED fir ttsmotE) NAME AND Tina

t

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1 ° ." 73 kCPIACIlf DO 'aka $73. OCT 40. WHICH W Ett OSLO UNTIL. Ms:stirs'? 43.) • ••••.

I-4, 144't b.:

•
ia.mno!P H.- near.

8PAO1 MOW ltrANITID FYr3 OAV MUTT

•

b rata ON harm. TO

PRIORITY

ril°141 COMMANDER AIR. FORCE DALusinc MISSILE maxim

INGLEWOOD. CALIN'ORNLA. •

SPECIAI. /NSTNLICTIO:

TO:

(aCCRET) FRO) W)304.44CONTD)

TYPTab .0F' MISSION& COMID ACP0101.PLISSED.. C. HAP.1)

1:aIPACT ON TrtE M0014 1 WITH Brdi.CON QL OTiER DEVICE TO PR:AM

ACCO30414:51111i2IT OF ACESSIOIC*. rPOUR VEHICLES SHOULD DE

PiiDGRAMMI:Lt FOR TIM MISSION. TUE mum PLIGHT COULP

• • ,eY

DE ACCO.ki.PLISHED TiE LAST QUARTER. OF/19511 FOLLOWZD

BY MUM AT TWO ISCANT.14 INTERVALS. CIRCUMLUNAR

WITS. MEA,NS PROVING ACCOMPLISHMENT. FOUR

YEitticucs would> Dr. PTtOGRAMMED EVR THIS laSSION. TNT:

F1k$T PLK:HT COULD occur BY IANUARX 1959 FOLLOWED BY max

DUR,114 XEMAIN D.67.14 Or 1959. THE EthiMATED CO:ITS OP

THIS PROCIRA.M.•ARE AS FOLLOWS: MISSION A 6 VEICCLES

FY 58 $6. 9 MILLION rr tr. 8 litILL10/4. MISSION. IS — 4 VE/UCLZS: 

DATI • YINI n

zrY 58 83.4 . 1411.1,XIN, FY 59 $7.6 MILLION. 1415dON C 4 Vi:F1C

'TEM.

- 4

TYPED fir StiOrNet) NAME AND TITLII

PsT 11441k5:

SECURITY CLADSICIDATIOIr. •

Le .....r% F01114. t •n•••:,

MAY OS L

te,

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• .. • ••• g e• .` georaibasmo.

ROP.Motra.S. DD .F01:14 t724 . 1 04T AA. WASCH WILL DC GEV? UMW:. El•'IAU.E!ll
46.1.•.40.4 .pgCDRITY MASSIF' !".

4.1 •41:1r". C.V.? t

JOINT ICI 1,..•N:44: • • •

14'

R.C4; •

41WS BELOW APAIlltreVi at.

MAIM OICA1 OF RIEFERENCC

OOMP.Sai.:›ER AIR. FORCE 11.61.7.471.0 SIMILE DIVISION

INGLEWOOD. CALIFORNIA

PROMS 14CIAI. DAttrtuvric

(SECRET) FROM VIDO4.2jC074TD)

vralcaxs FT C $'5 144.4,zort, $11. 3 MILI01014.

Amanot..41, LJUNCU COMPLEX CONT OZ. TWO ST4Iii:O5i AVD

A DLOCKH.OUST %minx ItEOVILED AT A COST OF APP4Olikka.A.TELY.

$1.0.11.Z.LICA-4 VII:4011 VOULLI DE REQUIRED IN irSZ. TM' /0 TAL

PILL rovae. za Pir.63324. a MLLICni, WY S') $313.4

COST W.C1.17.0E GOla&Or ITIOR .M•ZO

=Lilt I-T.ODUCT:i014 \WOULD NAVE 1(3, DE INCIOLASBD TO ralirt

1501421:11:VMEZI1ATELY Irg ORDER, TO PROVIDE

BP0ST117.6;13 REODIREP. THE nItST. FLIGHT VANES Aar

4t.A4r.:4260.0. 4.44 Az/

PREDICATED OAI.L1 ONE PROTECT 0 THE F6OR B13NJ Da'

MENTCD,, SII.COLTANEOU3 DAPLEMENTATION at MORE TnA.N

•

irruziaXIX:1 1-3132.0 ictULT %••••--1-taGerE-0 " "

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TYPEU KAME AND TITLE (FICAlturf., el re4litrati

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Itii,D4.•AtTY ct.AstirtcATICK

TYPED fw dahood) NAME AND TITLE

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F4: rim •7 "PT nem..,kar? r.0cw*(iiiutet• I e4Y / I •• • •

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VANCill.A.R13 BOOSTERS .Afa, WEL.L. AZ TITS DEVELOPMENT, 15.13.9C, Er.

MZIZT AND TEST Or PAYLOAD AND ASSO?;;IATLID GKOLTV.1.1
• MI:COMITY CIAM1M is t

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ORIG. OR REFERS TO CLAsauFscAl

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INFO'

FROM: -.

OMMAX.C7i4. AIR. FOIICE BALLISTIC 

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MISSILE rarnsgaq

1.140t21K-4.;3), CALIPORNIA .

sPECIAL tpasTmUcl

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