.

,

5 .ato tom i SUP ND= CO...Mt APPANIL414 INSAPPINVALACalantsta ea SWAM ACTSONS

1 NANCOR mu RIMS COMM

ONSANIZATION MO oat 00011ININTION

. .

ma

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ACTION

NOR me

ORM

4 . -NN Mt

INONATIINE

libr your information and for meMbers of your

staff per direction of General Greer.

Since this report vas made in connection with

a DOD directed. stuOy relating to incentive contracts

based on reliability, it may help by pointing out

present pitfalls which lead. to a pratfall as far as

legal liability on the pert of Contractors go.

.

FROM a —

JOU R. l c .1 1 - 1 MAJOR. DEIAF

0A111

7 Feb 62

OwAINATION Ate LOCATION

- 88J -• Staff J ,ige Advocate •

DLo FEB so 94, lona D. DN.,/ 41, wma ray Ema.

MP Reptass DA A1710 roma% I dye 111004 Anal as—n—law-i we:
DRAFT

/

Capt Diener/jm

DISCOVERER XXVII (322/1110) Incident 

1. Following is a chronological sequence of events concerning the CEA, leading

up th the subject incident

13. Apr 61 Missile. 322 arrived at VAFB.

17 Apr 61 CEA removed to DAC LAB for c/o.

I May 61 C/o on CEA in .LAB in progress.

10 May 61 Pitch network removed for rework.

29-30 May 61 Phi 17 on P601 found broken. Therefore, an advanced BO

was written changing.the pitch rate functkat to the ME to

Pin 38 on P601 and its receptacle j601 Hole 38 (HO 2796676 AC) .

This plug connects the programmer board to the rest of

the CEA chassis.

30 May 61 LAB checkout of CEA complete (per DAC Procedure 779'7779).

2 jun 61 CEA removed from can in RDA for control checks.

7 km 61 CEA re-installed in missile and sealed.

1. 5 Jul 61 CEA removed from missile on pad ens sent to LAB for

flight trajectory installation and spin motor monitor mods.

10-11 Jul 61

13 jul 61

1. 14 jul 61

Programmer board SN F60030 was replaced by SN F60012

due to an intermittent relay, a loose roll control pot, and some

chafed wires. Complete checkout of the CEA was completed

per 7797779.

CEA. reinstalled. in Missile. 322 on pad.

Rate gyro sensing tests with main engine.disconnected and

A/S check completed.

m. 20 Jul 61 R-1, all systems. check completed. Rate gyro sensing.check

was included with the missile disconnected.

2. The-CEA (Flight Controller) has contained within it the timer (tape) and programmer board. The attitude gyros are also contained within the CEA plug the rest

of the circuitry. External to the CEA are the rate gyres. The plug'and receptacle

DRAFT
DRAFT

601 are located within the-CEA. The Budd condenser which is also suspected is

internal to the CEA, but extended to the programmer board. It is connected

across the Plug 601.

The. checkout of the•CEA following. the programmer change on 10 Jul was covered.by

DAC inspection and the technician performing the.checkout. Both indicated that the . pitch

circuit to the ME was satisfactory. During this check, an external simulated rate

voltage is placed.on the rate circuitry. The output from the-CEA is connected to

meters on. the checkout console. This voltage is steady and continues.to be registered

on the meters until removed.

There is no paper which would indicate. that the P60 plug.on the new programmer

was changed to be compatible with the 3601 and in theCEA chassis nor vice-versa.

Since the programmer board was a standard item it would appear that Pin 17 on P601

went into an empty receptacle on 3601 since this wire had been removed to hold 38 on

J601 previously.

Conclusion: It is impossible to state whether the.configuration was on Plug 601 at

liftoff, since tests state.that it was and paperwork indicates that it was not.

It is believed by the writer that a technician probably made a modification. to Plug

601 during 'checkout and was not covered by paperwork. Since it would have.been an

unauthorized modification, there is very little chance that it will ever be admitted.

WILLIAM B. D1BNER

Captain, USAF

2 DRAFT
OICLASSFIED

MISSILE MISHAP ta.

erer

SUSSIE

ERIFICII
ei •tuvr . ; or. ,rti ovt ..r-J111111111.Se Aline '

6 10 PO

Snpervisors. Vehicle Systems Section

Lockheed Mottle Space Division

Member

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Recorder

DOWNGRADED AT 3 YEAR MIRKAti

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ICA33.10 EARS

Hq AFTLIO Fid Oto, VAIDs Calif

Chairman

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-

HEADQUARTERS

AIR FORCE BALLISTIC MSS= DIVISION

FIELD OFFICE

Post Office Box 1567

Vandenberg Air Force Basso Calif

REPORT OF MISSILE MISHAP 

ZR I

BY

MISSILE MISHAP INVESTIGATING CONCETTR

V....FEBRUARY la

The follcming signatures indicate concurrence with the contents contained

herein.

1r14, FORA 127
111111111111.

HEADQUARTERS MIND 111W OPFIOZ

Vandenberg Air Force Base, Oalifbrala

29 February 3960

assna XLSHAP INTISTIGATION GOEUTTEE BERET

Discoverer X

AUTS2R321:

In accordance with the intent of APB) DU 31-7, dated 16 Dauswbar 1958,

Investigating committee was appointed by the Chief, ATM Field Office, Vandenberg Air Force Base (Vin), California, to investigate the missile mishap

which occurred co 3$ February 3.960 and resulted in the destrnotion of Discoverer I (Vehicle Numbers 10511/223). (Bee Attachment A).

SCOPEs

This investigation was conducted within the limitations of the information,

capabilities, and facilities directly available to this comeittee at Vandenberg

Air Force Base.

FLIGHT HLSTOW.Cs

Disooverer X was lanndied from Launch Anplacement 75-3.5 at VAFB at

approximately 1215 P.M., 19 February 1960. Immediately after lift-off

oscillations developed in the pitch plane. The oscillations beams more pronounced and the missile began to exceed the prescribed range safety limits.

The Missile Flight Safety Officer commanded missile destruction which resulted

in missile destruct at approximately 21,000 feet altitude * 56.Bsoondis after

lift off. (See Attacheorb B). Major pieces were tracked by radar and cameras

and impacted in the immediate area of the launch operation and up to 11 miles

south. A. detailed description and plotting of pieces is provided in Attach.

leant C.

beNtrAge 

444 taitiAtt

o:timswIED AFTER 12 WES

DOD °MOM 5200.10
INVESTIGATION AND ANALYSIS:

Examination of the post-Ian:16h films revealed clearly that the

observed Oscillations were about the pitch axis. Telemetry records indicated

pitch program . 00mmemiswe*tmdng generated properly. The pitch rate of the

Arabia. was determined from telemetry records of both the Thor booster and the

Agena second-stage. Thor records &owed definite evidence of low► gain in the

pitch rate circuitry. The values recorded on telemetry weave approximatmly

one-tenth of the value which was calculated for the pitch rate from Independent

data sources in either stage of the vehicle. The low gain in the pitch rate

circuitry reduced the damping in this axis to a level which resulted in iDP•

stability after introduction of the normal disturbances associated with

launching. As a result of the above evidences the lowestigmtionwas narrowed

to the Control Electronics Assembly of the Thor booster and to any elapenta

external to it that may have caused this assembly to perform abnormally.

A review of the pitch rate circuitry (See Attaehment D) and the

telemetry pick-off point resulted in isolation of the abnormality to one or

more of the following:

The pitch rate gyro and associated circuitry.

The pitch rate AC amplifier-demodulator.

The shaping network (or summing network).

A condition introduced into the control circuits by telemetry.

3. Theabove components of the pitch rate circuit were recovered from

the wreckage and examined within the capabilities at this station. The pitch

rate gyro was checked for continuitythenit appeared to have no flourelthe

leaks. However the rotor would not spin upon application cd'rwer; the gyro

1W 10111 Z"
was then released to Douglas Aircraft for further examination at other locations.

The AC amplifier demodulator had impact dosage to several circuit elements and

was also released for farther exandnation after physical inspection. (See

Attachment I). The shaping network components and the resistors between the

gyro and the amplifier-demodnlator were checked and found to be within tolerance.

The recovered telemetry package was checked as functional by the 704th Instrumentation Squadron. This committee then shipped it to the Test and Activation

Office, Headquartera AFRO, for test and evaluation.

b. The possibility of the malfunction having been caused by conditions

or events prior to launch, nonadherence to published procedures and dooftents,

or personnel error were thoroughly investigated by the committee. No evidence

of any of. these factors affecting the cause of the incident was found.

a. The following Douglas Aircraft Company records were checked and

cross-checked.

Removal cards on Missile 223 and C.I.A. 521l and all

engineering orders associated with either.

RIM AnilAiog and launch emplacement checkout procedures

(DAC Drawings 7733825, F Change, dated 13 August 1959 and 7733816, 1 Change,

dated 8 February 1960) and Preparation of Missile 223, DAC Drawing 7796330,

D Change, dated 26 February 1960. (See Attachment F).

(3) Inspection records of tests required and accomplished by

the above procedures and the qualifications of the personnel accomplishing.

same.

b. Examination of the above records indicates that Missile 223

experienced an unusually long time period at VAFB prior to lanochs

(1) Arrival at IINFB - 30 July 1959.

3
Missile checkout began 26 August 1959.

Final CEA gain cheek - 2 October 1959.

REM checkout complete - 14 October 3959.

Missile on Stand - 30 Novosber1959•

MOS of Agana 1054 - 9 February 1960.

Limn& - 19 February 1960.

The records thaw a CEA operating time of approximately 29 hours.

However, with additional running time in the electrical laboratory it is

'estimated that the unit had approximately 140 hours of operating time at this

location. The CEA had been removed and reinstalled four tunas for incorporation of changes and checks.

There was no evidence of any unusual performance of Oronnd

Support Equipment which could have caused this malfunction.

A review of all failure reports at VAIJ3 concerning the suspect

elements in the. pitch rate circuitry was conducted using Douglas records for

Discoverer and Air Force Records for the 16115A. In addition AWiTSO obtained

pure statistical information from MAMA on WEL15Afailures in the United

Kingdom. Verbal information indicates a total of 16 failures associated with

the rate gyros and the rate gyro' assembly in the United Kingdom. Only two

failures of rate gyros have been recorded at TAM In addition, the OBAs in

Discoverer IX and X have been forerunners in a program which requires more

modifications to be made at the vendor (RCA) rather than on site by Douglas

personnel. No significant trends in changes or failures were established.

Since the only electrical interference between the two vehicles is

through the command destruct system, photography was the primary means of

determining whether any interference tram the upper stage could have

influenced the course of events.

W POW 1117
a. Attachment G lists the significant events noted on the Nem launch

film. Sequentially these were.as follows

CO Immediately after lift-off, at orbital stage umbilical

ejection, a small amount of acid fumes was noted issuing from the ground half,'

of the acid fill point. This was a normal occurrence. --

Although not noted on Attachment G, a smoky projectile was

next noted in the vicinity of the missile. The exact source of this projectile

is unlmcamq however, it is believed to be a ricocheting vernier engine ignitor.

There is no known reason to believe that this item contributed to the failure.

The next item observed, again not noted on Attachment 11,

was what appeared to be the gaseous nitrogen flex line to the payload falling

to the ground. This is a normal disengagement of this item.

At about 9.7 seconds after lift off a small object appeared

to fall from the missile as it rose. However, no specific pert can be

identified. Since this event occurred after the oscillations began it was

concluded that it did not contribute to the incident.

At about 9.7 seconds after lift-off a series of vapor clouds

appeared to emit from the orbital stage. This may be exambomlbythe fact

that due to the unusual pitching of the vehicle, the fluid.level in the UMW

(Unsymmetrical Dimethyl Hydrazine) tank covered the vent valve connector in the

tank allowing fuel to enter the feed line and vent valve. Liquid in the

pilot caution of the vent valve was thus ejected overboard causing the large

volumes of vapor noted.

(6) Although not noted on Attachment Or, at appromimately 36

seconds after lift off it appears that a door from the booster guidance

5

1C401 127
section was ripped off. This could be due to a combination of the excessive

oscillations of the missile and aerodynamic forces. This again was

determined to have no bearing on the cause of the incident.

b. The possibility of an orbiting stage ullags rocket igniting at

lift off and damaging the CEA. and associated wiring was investigated. Final

inspection of the wreckage in the , area around the ullage rocket exhaust nossle

eliminated this possibility.

o. The Lockheed records concerning Agana Vehicle No. 1054 were also

thoroughly checked. No open paperwork wee found. Spot checks of eignificant

items removed or installed during the period immediately preceding launch

were made; no discrepancies were found.

7. Because of the mid-air destruction of these vehicles several items

involving safety were investigated by this committee.

a. All traces of Unsymmetrical Dimethel Hydresine ODIC and

Inhibited Red Pulsing Nitric Acid (IRFNA) found during the recovery and

selvage operation were negligible and presented no safety hazard. Laboratory

tests revealed that in 10 minutes time all trace of DUE was dissipated frog

mild exposure metal surfaces and that row hours was the maximum for traces

of IRFNA. Six personnel at Pont Arguello, who picked up pieces, were treated

with a neutralizing agent as a precautionary measure.

b, During recovery, pieces of magnesium-thorium alloy stooped

"radioactive" were picked up for disposal. These allays are used in the

Agate vehicle and the IRO adapter section. Magnesium-thorium alloy has

radioamtive thorium in its content. This alloy does not pose an external

radiation hazard; however, it is an alpha radiation emitting element and thus

6

VC fOral 127
is potentially hazardous. Recovery and salvage of fragments of Discoverer X

did riot take into account this alpha radiation until a stamped piece was

discovered. Subsequent collectinft and disposal of these pieces were handled

by the Lockheed organisation in accordance with industrial practice.

c. The area immediately adjacent to the Contra Center 75-3, on

which the four diesel generators and the diesel fuel storage tank are located

drains toward the .main access door of the control center. Should the 6,000

gallon diesel storage tank be ruptured, a quantity of the diesel fuel could

contaminate the interior of the control canter.

FINDINGS:

The malfunction which caused Discoverer X to exceed missile safety

limits and to be destroyed by commend destruct was isolated to the pitch

rate circuitry of the Control Electronic Assenbly of the Thor booster.

This committee found no evidence that the malfanction was 'tensed by personnel

error, non-adherence to procedures, improper procedures, design deficiency,

nor au inadequate inspection system. Checks and investigations of various

conponents at this location have failed to reveal a specific cause for the

malfunction.

The time between final CEA gain checks and launch of the missile

amounted to 140 days. The missile on stand time amounted to 81 dep. There

are no formal requirements for calendar time nor operating time periodic

inspections on the Thor booster in this program.

3. There is no evidence that the second stage Agens vehicle contributed

in anyway to this incident.

14 . Doubt has been raised as to the effectiveness with which pertinent

failure histories from the? have been made known to

7
Readquarters AMID for application to Thor boosters.

Routine and special procednreaCconfteted.mIth an investigation of,

an Incident of this type had not been established.,

The fuels and oxidizers presented no safety hazard during this

• operation. .

There was an original general unawareness of magnesium-thorium

alloy in Discoverer X and at Irreaent there is a lack of specific hazard

,potential, if any, associatad with th.1.4

A potential hazard exieto it Control Center 75-3 131 event of the

rupture of its diesel fuel storage teak.

ittiCCOIENDATIONS:

That the investigations not 'underway at various looetiona continue

.on au expedited basis to diaterurIne whether component failure existed

in the pitch :-..ate gyro or its aasooiated amplifier demodulator. These

ieveetigations.should be conducted under the supervision provided by the

sett/I:addled y.•oject chatnels,

'That the Discoverer program be reviewed to determine what checks are

required, at what frequwcy, :La the event extensive delays are encountered -

in the receipt-of-missile to leunch'sequence.

That Eeedesarters MAD insure that a positive system is in

*eeation whereby failure repoAs from the WS:115A program are reviewed for

epplicability to the Thor bocei:er.

That general standard Ixocedures be established, for the conduct of

proceedings of incidentiaccidart hoards to include membership, conduct of .

investigatim, recovery and perts dispoeition, security control, and

doeUmelltatio4:- Tbe“eprocednree involve actions by the AFBMD1 Field

8

•
OffIce* let Missile Division, and contmustors.

That physical handling of salvaged and recovered ports be denied for

a period of four hours (except specified recovery items handled by tees

ambers) to insure gnarl no eafety hasard exists. This does not include

identification and location of parts.

That the APSMD Yield Office establish the hazards associated with

aagneelne-thorinnal7ao1 and that procedures be established through the

project office for the safe handLing and disposition of this alloy.

7. That a dike be constructed around the diesel fuel storage tank to

iso► .ate ap:Lllage of diesel fuel at Control Cetiter 75.3.

7 itches

Itch As Ltr Order, Subjs XissU.e

Mishap Investiption 

(11

Cc

)

essittee w/

Attend, dtd 1 Mar 60 

Itch Bs 70022 1$ ODASIC-60456)

(74-60-555) (3)

3. Atch Cs DAC lir, aubjs Dispersal. &

Impact Areas

C7-3

of 

- 60

Mal

-60

22

1)

3/1054, 1314-260•

DMIB.4.061 

h. Itch Ds Discoverer IX 200 & Subs;

Pitch & Tear Attitude & Rate (Duw) .

(v-3-63-6o0) (C)

Itch Es AC Amplifier Photo DO

itch Fs DAC Drawing 7796330 On

7. itch Os Data logr Report on Mal 223,

pp; 11 & 12, DAC (v-3i-60499) (3)

9

NW FORM 177
HEADQUARMS

AIR MX BALLISTIC MI33II8 =NOM

map MICE •

Post Office Box 1567

Vandenberg Air Force Ban, California

ReP17 to

Attn ofs Mialgr

SWIM Missile Mishap Investigating Committee

23 February 3.960

TO: See distribution • •

3.. This letter ocofinas verbal orders of 19 February 1960 appointing

ommaittee to investigate the adarile mishap which occurred an that date with

Discoverer vehicle 1054/223. The committee will investigate the cease of

the test mishap and render a report of findings and reoci•endatdons to the

Chief, AVM Yield Office.

2. The committee shall oanaist of the following personnel:

Major Earl M. Thcopecn, 16860A, APB111/10, Changan

Major Pickard R. Moore, 19795A, AVM, Member

4e4ajor Fallon Watson, AO 743877, let MD, DS, Member

Captain Milian Z. Diener, 41:522A, AFISID/F0, Reoorder

Captain Roy D. Lasted, 10734 Avomp/ro, Member

**Mr. W. X. Carrier, Mgr VATS Engr, lockheed, Member

**Mr. R. W. Purdy, Project Bear Thor Systems, Douglas, Amber

*Indicates with concurrence of ocarmander canserced.

**Indicates with concurrence of contractor concerned.

Ka TES COMMANDAR:

-,"-)111P

Colonel,

Chief, AVBMD Field Office

DISTRI3UTDX:

1 • ea Individual

1 - Comdr /B ID, AF Unit PO, los Angeles 145, Calif

1 - Coldr, let Missile Division, TAPS, Calif • 1 • Lockheed Missiles and Space Div, PO Box 1506, VMS, Calif

1 - Douglas Aircraft, PO Box 3596, TAPS, Calif
•

/1114114111MW

lint MOO BILLIIM0 ICBM =SW

• num WS*

1st Ott's. Soar 1,9f

Vasiseborg Air Farm Bus, OallIbeata

RIM TO

MIN OR WOW 1 lbw* 1960

OU10101; 1Sosotiosting Oanittse

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aletbsonss is awls to Utter, faisjsat as shows, ilatoil 23 Pstmera 1960

socolatIos Oandttos to invostioto sisboO. Posopoik It of

odbjoot lotbos is monestt to buds& Os sir of ler J. V. IttIlloo,

l'oldo3o Oistms Ssotlas Ovosovlsor, looklisod, Wass vial WV. 11.

Osollse, Mgr VIM /oar, lootheed, lesibes.

VOIR UN COMOMMIns

1/11/2112‘13012

1 • so ladtsIdosi

1 • Oasts an" t PO, Los Aoggss 49, Wit

1 • ail, lot ltiuUs Insislase Galt

1 • loolhood lL3ssi3as aNd aim Dist, 10 au nay vas, WU

3. • Davolos Alressit, PO In 1596, YAM Cala
, . : 704TH INSTRUNMITAT/ON-SQUADRON

UM/T&D 3TATE1 AIR FORM

Vandenberg Air Force Rase, California

itant, to

Am -yF: 704ISC

SWIM Transmittal of. $7$U Report, Discoverer Vehicle "OlikilY DAY" .

1 Missile Div (DS) , 1 Missile Div (DO, Atte: Nmj Skaggs)

Arsmo Timid Office (Attu; Lt Conlon's)

5 FEB r61

Attached Is the MPSO Report on.piscnverer Vehicle "Dun oat".

• • •: • • • This letter is unclassified when the attachment is withdrawn .

1.1100 , A; PERRY JR.

C01,101 .. , USAF

CoMmandar •

1 Atth

ea stated

DASMC-40-

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rit
MEMORANDUM

TO: Chairman, Missile 223 Incident Review Board

FROM: R. W. Purdy-, A31-260

SUBJECT: DISPERSAL & IMPACT AREA OF MISSILE 223/1054

COPIES TO:

Missile 223/1054 was launched from 75-3-5 on 19 February 1960 at

approximately 12:15 PM. A command destruct signal was transmitted

after approximately 56 seconds of flight. Missile 223/1054 had

attained approximately 21,000 feet in altitude and was proceeding

in a northerly direction.

At time of liftoff, surface winds were 32 to 19 knots from 330°.

Wind at 20,000 feet was 46 knots from 340° and at 30,000 feet was

from 330° at 62 knots.

Attached chart indicates areas of search and recovery also distance

from 75-3-5. Attached detailed lists indicate, in Area "A", major

items found and respective weights, in areas "B" thru "F" smaller

items and weights. At completion of search, 4657 pounds of Missile

223/1054 had been recovered, which is approximately 67% of total

weight.

R. W. Purdy,

Project Engineer

TR Systems

BWPicv

Attachments - 4

THIS DOCUMENT CONTAINS INF

OF THE UNITED THE NATIONAL DEFENSE UION AFFECTING HNITED STATES WITHIN THE MEANING OF THE ESPIONAGE LAWS, TITLE 18, U.S.C., SECTIONS 793 AND 794. ITS MISSION OR THE R TRANS- EVELATIGN OF ITS commas ANY MANNER TO AN UNAUT IN

PROHIBITED BY LAW, HORIZED PERSON IS

00047i4IS
1

PART =BIGHT I.D. NUUBERS 

AREA "A" Actual item (On Area "A" Only)

Main &mine 1402.0 19

1.02 Line 6.7 24

CEA 102.0 1

Guid Section 988.0 21

Nitrogen Line 8.3 25

Right Hand Vernier Engine 95.5 ► 26

Access Door .5 27

I= Not available 28

Turbo Pun & G.G. 505.0 2

High Press Bottle (1) 45.0 . 3

High Press Bottle (1) 46.o 5

Fuel Duct Pipe 36.2 4

Fuel Duct Pipe 180.6 (filled with sand) 7

LOg Start Tank 38.4 22

Fuel Screen 32.6 23

Fuel Start Tank 27.6 6

LOg Vent Valve 20.1 29

Hydraulic Pogo Assem 20.6 30

Missile Center Section 545.0 20

AREA "B"

4 pcs Log Tank Skin 22.0

7 pcs Fuel Tank Skin 7.0

2 pcs Engine Section- 5.0
PART MUGU I.D. NUMBERS 

AREA "C" Actual Avertat (On Area "A" Only)

3 pcs USD Prop Tank 3.5

13 pcs L02 & Fuel Tank Skin 1.0

1 pc LBW Retro Fairing 0.9

1 pc Engine Access Door 5.1

2 pcs L02 Tank Skins 24.0

8 pcs LO2 & Fuel Tank Skins

1 pc Fiber Glass Tunnel Cover 0.7.

5.7

1 pc L02 Tank Skin 19.7

1 pc LMED Skin 0.3

1 pc LQ2 Tank Skin 6.8

1 pc 1.42 Tank Skin 14.6

1 pc Fuel Tank Skin 18.2

AREA "D"

7 pas Engine Section 1.9

14 pcs LOt & Fuel Tank Skin 9.3

1 pc LMSD Skin 0.3

AREA "E"

1 pc LMBD Adapter 10.7

1 pa LMBD Retro Cover 1.6

1 pc Drip Shield 0.1

1 pc Tank Skin 4.3

1 pc Tank Skin 17 .7
PART

AREA "F" 

1 pc LO2 Tank Skin

1 pc Fuel Tank Skin

1 pc L02 Tank Skin

1 pc Engine Section Skin

1 pc Engine Section Skin

1 pc Engine Section Skin

WEIGHT I.D. IUMMERS

Actual Aver W (On Area "A" Only)

13.8

30.4

14.0

0.3

1.7

0.5
4000

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PRICIPILRIED BY• DOUGLAS AIRCRAFT COMPANY, INC.

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1-9-9 2795437 A OUTD Dc J-BGE R Al

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3-11-9 2195392 New HMO 1W!. =TIMM MCI AR • • 23-'

3-12-9 27951137 New GUID DC J-BOX RWE . AZ

3-18-9 2795192 B WHO NOL . CONTINUITY COCK AZ • •23 .

3-2k-9 2733619 M =no ign. PEE? AT R1MHPRIOR To cjo AZ • '

4-1-9 275549 N IMO NEL Mr AT. RIK PRIOR TO C/O AZ -21-.

4-2-9 ' 2796147 New GUM 6 CONT. LOCK WIRING MK FOR 117L MI AZ : 19-•

4-29-9 2796342 New DISABLE TIML TOOT BLAME =ATM AZ • 14

5-5-9 279543T- Memo auxo DC .T,•BOX ANC AR 4 *

5-6-9 2755619 P am mea.121, AT BIN PRIOR TO 00 • .AZ -22* .

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6-4-9.• 2795196 Memo REX INTER PLUG P1 AZ 20- .

6-4-9 2795734 Nemo WIRING REX MO cam= AZ

6-4-9 2796k73 New 117L GUID SECT MOD AZ • '

6-154 2796516 New WIRING mat ENG CIRCUIT Az - : .. •

6-16-9 7795955 C 117L mama c/a moo AZ 9

6-26-9 2733993 * AO CM Alt.:,( ''• •

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7-30-9 279025 C BM GYRO RELOCATION Lin A2 • 18-,

7-30-9 2796626 A BM GYRO WIRING REX 117E AZ • 11-*

8-7-9 7795164 A CENT PROC, MON= BATT AZ '12.3;• #

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8-13-9 2796473 Memo 117L GUM MT EV AZ 19 •

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8-17-9 7733825 1 00 raoc FOR =MISS. . AZ 10-

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8-28-9 2796473 Mew 117L GM SECT NOD . AZ *-11-•

8-31-9 2795041 New CUT FROG TAPE FOR 117L NEL • AZ • 22-•

9-3-9 2795437 B • GUID DC &BOX ME AZ : 9

9.8.9 2796676 c an 5793467 rum COST • AZ : te •

9-10-9 2796676 D WIC 5793467 FLIGHT COW AZ : 22 •

9-14-9 2796676 F REX 5793467 FLIGHT CCHT AZ :.22. •

9-14-9 7796701 I New PITCH FROG RESISTOR ADJ AZ :-22 •

. 9-15-9 2796725 Nev)fill[ 100% FLOAT SIIITCH .AZ :-29 •

9-15-9 7706708 X8 MET TEST PROC FOR 5793467 MGR COttT AZ : •22 •

9-15-9 7733816 G cjo PROC DK 1812.3 L/E AZ ' 11 •

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9-29-9 2795041 X41 MY FROG TAPE FOR 117L ESL AZ • • .4. •

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1-1-9 2733631 Aj 11(932 8-

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3-5-9 2733631 AL 118Th 8. .5

3-8-9 2733631 AM DM 8.26.5

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10-26-5 2733631 AB INS 0 118E 118Th 10+339

11.7.9. 27968141 B 118Th 11.10,1

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DRAWING.. NO 7796330

PAGE. N0,- 5.0 

OIANGE: LETTER C 

. DATE DRAWING *OR

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2•431•9 . ri95628 New Pon U+ 'lit Pim stints AN . PP • 9-11.0

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4-8.9 .. 27961E1. A mat tar 002 imam PUSS no PP 9.26..

4.84 .2796197 New NIX TWM, • 10:11AUST.ZIT XVI - PP 9-15-

4.48.9 2706235 New man NZ EM MP BIM DOLTS - PP 9-4-9

4.20.9 2796268 Naar ailenta cart NEL BOTTLES PP . 8.17.

4.24• 2796268 A 1/010VAL ma VOL. BOTTUM . . PP 8..16-

5-8-9 7795712 1 C/0 ?ROC WM Tilt.FLANT103.3 BIZ 1 ENG PP 10• #

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6-22-9 7795712 maw c/o 'ROC VOL MR .?LAST 103-3 RIZ I no. PP 143. #

6.2‘.9 2796580 Ilav INS' OM= START TANI VINT YALVI PP

6.26.9 779588k • Mao 117L I= 10/0 MC ma! AT PAD PP 12.- " 9

6.304 7795362 Nemo 117L MT FRCP nal MOO PP 2.1

741049 2796532. A XX. LON on •TA1K VENT LINZ PP' 8-17

7-244 . 2796610 Rev PURL START TA* PRESS WITCH DAN • . PP 8-

7-25-9 7795362 c 117L TINT .PRCe ILCW ?ROC PP 2-1

7-214.. 7795 62 D 117L TOT PROP maw PROC PP 2-

8-5-9. . Mom NM gits CAP ASSY PP •

8-5-9 2796121 Kam MX 002 11WLIORT PRESS SYS PP 8-25-

8-5-9 . 2796645 . Nero PIM. 851.12 TAW -FUSS SNIT= IMP PP .9-23-•

8-5-9 7795362 ow um . TEST PROP PLO/ PROC • . PP 2P13bt #

3-5-9 . 2795675 New RECINCIRCZEG RING DRAIN MIX PL PP 9-11-9

84-9 2796560 Mao UNIP OLDIE= STAN2 TAU VENT VALVE PP 8-12-

6.4,9 2796532 Mao AWE WE OIL TAM( VEIT LINE PP 8-2.7-

8-8.9 2796197 Maw BM MOM =MST UT MET PP 9.15.,

8-10-9 7795362 New 1177. TNT nor nor PROC PP am*" i

8.10.9 2795888 • maw , pm mums Puss mica AN PP 9-11 • 8-104 2796268 Memo REMOVAL ON2 VSLBOTTLZ PP 8-17 . 3.12.9 2796121 Rwk 181G00 MIXT ?MS SYS PP 8-16- •

8-124 2796235 • Memo SAPETINMAING MP PET BOLTS lop 9-4-9

8-20-9 7795712 7 0/0 PROC WM PIA PLAIT 148..3 Eft I BIB PP 10- 9 # 8-24-9 7795362 3 117L MST PROP FIX PROC PP 2-1.3- #

8-264 2733996 CS AO CANC .. PP

9-15-9 2795888 A FUEL mama, PR838 8WIT311 AN PP 9.023-

9-24-9 2796610 Memo PILL START TANG PRESS swat mop pp 9-23, 10.6-9 27966115 ark P. STAN TAU PRESS SEITCR 18 IT 10-7-

10.9-9 2733996 Mew AO CANC . PP • 10• •

10-124 2733996 Cs AO CANC PP • *

10•19-9 2796802 Nev OMANI= INN PP 10.

10.30-9 2795464 A IA= W GD1BAL BEARINGS - PP 11-

).1•709 2796854. New MOD; 11.11A2, 1101MOID VALVE • PP 11• •

11-10-9 7795362 7 U.71. TEST PROP. PIM PROC PP 2. . #

11-24•9 779588 ► . D 117L.BIE I 0/0 2210 ESL AT PAD PP 121. 22 •

11-27.9 2796602 A CIZARINICI . INSP . PP 12- * 9

12-1-9 7795362 yari 1177. TEST PROP PLOW PROC PP 2-13- I #

12r1-9 7795884 Z 1177. III I 0/0 MC • ME. AT PAD PP 12-22 9 #

12-11-9 2796700 • C 00 LIQ OXY IBM =TYING PP 12-11 9

12-12-9 2796943 New REPL MA= Pb 4 VAT 801.12101D VALVE . PP 12- • 9

12-15-9 2796854 A ADD, ii WAY SOLIXOID VALVE PP 12-16 9

1-7-0 7795362 Vert 11Th TEST PROP 110•1 PROC - PP 2-13•• • #

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DRAWING NO 7796110

PAGE NO. 5 . 1 .

CHANGE LETTER C •

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PAGE NO 8,0 

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6-25-9 7795858 A .ALIGN CBEGX USD ADAPTER . SOWN • f -- .

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DOUGLAS AIRCRAFT CO., INC. MISSILE&

CNGINEERING ORDER • SANTA MONICA DIVISION

FORM R6.3 S CI SRI

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DESCRIBE IN DETAIL AND GIVE REASON:. DATE OF

ISSUE' usarne CHANGE LETTER

ISSUED FOR USE AT VA 72 CNLY

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TITLE: PREP OF MISSILE 723

DISPOSITION

DESIGN GROUP

PRE

ENGINEERING SECT.

1.0 PREPARED IT

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DWG. MADE OR CHANGED SY

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MODEL REL. S.O. 

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RELEASE THE FOLLOWING FOR EFFECTIVITY LISTED *ROVE

REGUIREMENTS FORMER REG.

PER ARTICLE PER ARTICLE

WING CHECKED BY t

••••'' •

DRAWING NUMBER NEXT ASSEMBLY

•••••••.

SAENGTI4 Z, 1. S • 6

PATTERN MATERIAL 3 -

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MOLD, RELEASE 3

AFFECTED

EXPERIMENTAL

TOOLS Cssi 

EXTRA PRINTS OF DWG TO EXTRA PRINTS OF F n TO

LI

PRODUCTION Ni1/4
Page Mo. 3.1

T114E8 OF VARIOUS EVENTS

Missile Mo. 223 

Item No. 11.15 

* . Corrections have been made for a 14 frame lag on

of strobe (0.

time du0 to position

• ••

COPY NO.

Prepared By D..Peraev

Date 2-2340 

(Data taken from35non filmyhotscrighed at 2550 ft. 110Aagreets, and 48 Cps) 

Event

'Time of • LiO +

Day

Lift-off 1215:14.238

Vernier engine starts roll (to left) 3.215:16.26 2.02

Vernier (max deflection) 1215:16.30 2.06

Vernier (centers) 1215:16.51 2.27

Mein engine gimbal-starts 20.83 6.59

Main engine bard over (left) 21.20 6.96

Main engine center 21.75 7.51

Main engine hard over (right) 22.58 8.34

*Main engine center 23.00 8.76

Main engine hard over (left) 23.32 9.08

Main engine center 2430 10.06

Main engine bard over (right) Rot reedahle(eng10)

Vernier engine hard over (right) 24.68 10.44

Roll program start 23.85 9.61

Roll approximately, 15° to right 25 . 35 11.11

Main engine center 25.86 11.62

Main engine hard over (left) 26.45 12.21

.11hin engine neuter 27.24 13.00

Rolls to left 27.24 13.00

Main engine hard over (right) 27.62 13.38

Vernier center (following main engine) 28.65 14.41

Main engine and Vernier engine hard left 29.23 14.99

Main engine and Vernier engine center 30.16 15.92

Gimbaling continued through entire flight
Prepared by R. Rice& R. Pe agile Ao. 43 

Date 2-23.60tsan No. 11.16

Page No. 12

TIMES 01 VARIOUS EVERTS

(Rata taken, from 70mm file photographed at 2/550 ft., 110 degrees, and 10 fila•t

event .* Time

1.10 +

Vapor appears approximately 2' above first stage T + 0.4

Vapor disappeare(remsins relative to shroud) T + 2.9

Object (one foot diameter or smaller) is approximately 3 feet from

missile and 18 feet below top of first stage)

* *

+ 9.7

Vaporappears (initially) from 2nd stage (LMSD Vehicle) T + 9.7

Vapor intensity increases (approximately 1 foot above first stage) T + 9.8

Vapor intensity increases (approximatell 1 foot above first stage) T + 9.9

Vapor intensity increases (approximatel y 1 foot above first stage) T + 10.0

Vapor intensity increases (approximately 1 foot above first stage) T + 10.1

Vapor intensity iacresses (app proximate1y 1 foot above first stage) T + 10.2

Vapor trail disappears from view (hidden by missile pitch) T + 11.2

Vapor trail appears again (missile pitches back) ' T + 12.5

Vapor trail increases in intensity T + 13.0

Vapor trail extends well beyond missile (down stream) T + 13.1

Vapor trail disappears (missile pitch) T + 13.7

White streak on second stage appears (Approximately 2' in

length). Appears,to be liquid.

bite streak extends down complete length of firstistage T + 13.9

White streak disappears (after intensifying and reseeding) T + 14.8

Vapor appears (as at T + 9.7) T + 15.3

White streak (liquid) appears on second stage T + 16.3

White streak extends along first stage T + 16.4

White streak extends to seam above LOX tank area and reappears

out of LOX tank section-boattail section Beam.

T + 17.0

End of film T + 18.2

Times were obtained by counting frames and are approximate.

Color of vapor cannot be determined. maim 11111111111111 vA.

-

001/61/A

: •
7

INFO: DAC FIELD OFFICE, V p LMSD FIELD OFFICE, UFB, 1ST MD, VAFB

!4:1 PROM WDGEV NEFP10 . SUSI I FLASH REPT OF FIRST

JOINT MESSAGWORkt...............

Tyra moo (Cheth) ACIONARTINO °RIO. OR RIMERS TO CATKIN

ACTION

INFO

PRIORITI imam RON=

xx NA NA

FROM. AIR FORCE BALMS= }IISSILE DIVISION YIELD OFFICE

VANDENBERG AFB, CALIFORNIA

COMMANDER, AIR FORCE BALLISTIC MISSILE DIVISION, INGLEWOOD,

CALIFORNIA .

ICJ

DISCOVERER SATELLITE LAUNCH FROM VANDDDERG AFB.

1. VEHICLE CONFIGURATION

3.1 DISCOVERER SATELLITE VEHICLE, IA MODEL 3205 SERIAL1021,

1.2 BOOSTER, MODIFIED IOC THOR SERIAL 163

DATE AND TIME OF LAUNCH: FEB 20, 1959, 13:49416 PST.

TEST OBJECTIVES

3.1 PRIMARY OBJECTIVES

3.1.1 DEMONSTRATE THE LORBITAL CAPABILITY' OF THE THOR

BOOSTED DISCOVERER CONFIGURATION.

3.1.2 ACHIEVE REQUIRED THOR SYSTEM PER TO LAUNCH,

CONTROL, SEPARATE AND PLACE DISCOVERER AT THE SEPARATION POINT

WITHIN + 4 DEGREES OF DESIRED FLIGHT PATH ANGLE.

3.1.3 MEND SUPPORT WU NONTN

TOIL

1830 

YEAR

597.

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TIMID (ow AMMO NAME AND TITLIN, ,,see

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4 69 gab anomie OAR MAN 17$. t OMAR. WHIM WILL. RE IMO UNTIL ERNAtity•r"
3.1..b.2 , `PROP L I' ON SZS I. , ''.DSTRL'^+'. I .

PRRFoRMANCD OF ULIIAGE.',itOCK$TS, `:LR-81_.3 4QINE . AND S[aL4NT`UTTIZLTION TO ACE BZ3OVERFR'VE1ICL1E IN ORBIT.

3.1.1 3 AUIfIA`. XS(. DEI+K $TRAIN UTXLITY

OF . BATTEIES. AND TV FIRB AND..PUNCTONAL AD$JYACY OF TBEHKAI,... DESICIi .

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CWID.. .53m UXPITS MTPf VIDE i OR"tRE^1ND RECORDS' OF':PRIMARY

VH ICLE INSTRD)FNTAT^SN.:PARAX1!72SRS, ALL-(]R JND-$PACE CCIOWWS, . AND

THE TATWG :AND PROCESS . INI OF DA1L. NECESSARY FOR D 1TB)iIN&TION"OF

EPSEMERIS, ACQUISITION INFORMATION, AND VEHICLE TIMID RESET ' INFOBMATION.

3,2 S'SCONflARY TEE? . OBIJBCTXVES

3.2.1 SALE AND EV ATE ;TH$ THJMAL 1VIRONHT. ,
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