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... CENTRAL ,;:~:~=~CE' AGENCY ~~ ~. -"'"""n'-~ • .. • : 

'· I WASHINGTON as. D. c. . ·· ... . / fr". .· • 

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. ,_,:, ; : · : - MEMORANDUM 1FOR : Director, _National Reconnaissance Office -:_1 ••• ' 

"' 

ISINGLASS Research and Development Program.· ·y l ' ·' :,. . '' 

''" .. 

, 1. Pursuant to your verbal request, I have attached to . . . . · > this memorandum a recommended research and development program ' ·· .,, , for ISINGLASS covering a period of about nine months. This · ·· ·! ; pregram has been ~designed specifically with two goals in mind: I , ... • ... 

~ ' ~ " .~. . .. ~ .. , .. , ,,,-.. 

-, ., ' ' . 

· :· · ,,,:_ .. \ ,.. ' 1a. to. determine capability to satisfy our objectives;· .. · · . :.. ' · in particular, to establish system capabilities with regard :.-( .' · , · . .- to resolutiop, survivability, range, reaotion time, tac-.·~· .. / ~:· .. · .. tical flexibility, and target co~erage; ~nd ' " · 

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b. ta establish reliable program cpst estimates 

based on detailed point design, subsystem~analysis, and 9 

insofar as,,possible, actual manufacturing·experience. 

In order t.CFaccomplish the above, a substantial amount 

of testing, engineering and analysis wil\ be necessary wh~ch will ~urther confirm the technical feasibility of 

the concept. 

·- ,f' 

·,_, '. 2. The estimated cost of the McDonnell portion of the ... . . prpgram is $5, 350,000. In addition, we are recommending camera >· ~ ( 

·· environment studies totalling $150,000, giving a nine month 

.. \ . 

··. ~ " 

~ . ~: . ·>::.program total of $5,500,000. · 

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BYEMAN 

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The basic study areas at McDonnell are: . \1 ' ·,.·· 

'.::·· . . 

a. S tern Effectiveness: This will include 

development o a miss on per ormance computer program : .. and analysis of targe~ing, reaction time, basing recovery, 

and support operations. In addition, necessary contractor 

support to ·government studies on survivability and cost 

effectiveness will be provided. 

b. 

tunnel test 

Using extensive wind 

performance of the 

. •, 

.... '- . ,1. 

aircraft and carrier 

design ·:.sens.itivities 

1 be established and . .· . In addition, extensiV,\\t ...... ..; ~ ... ' . ' ' ::"', ~· ... , .,.~ ..... " ..... .: ... ~.~-'·~· ··,..~ ··- ~; .. ,1:-•• ·~~l.:~ ._\ ~ . .:.. .. ~.;.;.;. .... ~->·• .... 

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·. HANDLE VIA BYEMA.N . 1CONTROL SYSTEM BYE-2100-66 

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testing will be done to 'establish the photographic per- " " · 

1 

fgrmanee~ te 0em~nst~a€e @he wtndew' eavtt eon~ept• and · ~a apt:imiESe. d43aigll, @t:N~rt;:uf~l ~i@m~flt;ij U. be det;43m!ned• .. their performance substantiated and ~efurbishment require-.~;· -.:: 

ments established. ·: 

c. nstrntion: From wind tunnel . : i · tests, therms. es1gn er ll be established and " 

: , . .,: structural elements, including the insulation and water-· ;; '.J .. '. 

· wick, will be' subjected to thermal tests. A full scale . fμselage section will be desigtl.ed and the performance of" . the cryogenic systems will be demonstrated. 

antiation: 'The results · use t a high confi .... :. 

schedule performance. · .. ,._ 

4. In aq~ition to the work at McDonnell. Aircraft Corp.:·· :( .~ .. '. .. we are rec~ · ing certain studies to establish camera ·' .:: · environment. '. . se studies will investigat~ the internal · . · ·. ::.'.!., 

turbulence of the camera bay, window temperature gradients,· 

and boundary i~yer effects. Details are set.forth in the 

attachment. Tqtal cost, over a period of 9·~onths,would be 

• "_''t '•·. 

.,': . 

$150,000. '' . Ill .... , 

5·. If, on conclusion of the fqregoing program, it appears ... : .. desirable to CQntinue work on this project, .,we would pr se a , . second phase. tin particula we feel that a' full scale selage 

: · section and window cavity s ld be constructed. This will . permit us to verify weight factors, harden cost data, and· '·. . "determine capability to achieve resolution requirements. We · :-· .' \·.> · are in the process of preparing this second phase program. to: 

last about nine :.mont.hs and cost about 5 million dollars. ·<< ·\ 

;· · .. ', 

" 

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INDEX TO ATTACHMENT TO BYE-2100-66 

McDonnell Aircraft Corporation 

l.' 

2. 

3. 

4. 

s. 

6. 

System Effectiveness 

Configuration Definition 

Technology Demonstration 

Cost and Schedule Substantiation. 

Reviews and Documentation 

.Program Schedule . • 

with accompanying key' j~i,:~~fjS ' 3 . ~ 

· .• Camera Studies '.i' 

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Approved for Release: 2017 /01 /2~ C0.509621~1 . 
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Approved for Release: 2017 /01 /25 C05096211 •;' . " ... . . ivr ~~~A61 · 

ISINGLASS 

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.HANDLE VIA BYEMAN .. CONTROL SYSTEM Attachment to .... BYE-2100-66 ~.. · .. ~ ' .. 

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ISINGI.AS S . .RE.SEAR.CH...4..DEVELOfMENT. dP&OGRAM · . :· . .' ~, ,/ .. ~.· . ·:. \' .-.. ;,• .. •.. ;t,; 

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... ~ ~ \, • f' ·.\~ · . '.~::.·:A·. McDonnell Aircraft Corp. . '' :• ' .' .~ ~ .. ·. ~- .. l 

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~ ' . '·. ' . . ""; . I ~ < • • • 1. System Effectiveness $440,000 .. .' . ,,J • ~ . 

The global operat concept, logistics p , ... : 

support requirementsi a mission effectiveness or ·: 1 ·:':''. : • 

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·; .. ·.,: ; ' .:'. 

. ·'1 

. ' ·-·. 

i ~ \ 

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(. the McDonnell· Model 92 (ISINGLASS) will be developed. ;,. ·, :, . . .. In ad~ it\pn, necessary contractor support to government. ",1". 

·>.'. 1 . . ,; , stft~ivability and cost effectiveness studies will be · "·· ·~r: ,,. . .. '. 

·,.,. . ' . ~, : 

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.. ; . . , provided. '., 

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a. Mission Effectiveness . · .. ', 

·~ ~ ... ~ ·:, 

. ,_· 1'".'.,;''' 

,/ . •. 

" ~ .. ~ ... ·,' ',' i. Operational Plan the global operating 

concept will be developed and system deployment '~:· ·., :,: . requirements such as basing, recovery, logistic ....._.._ .............. """'··;, . 

, /:. ·." ,• · .• 

support, etc., will be defined. The influence of ; .... ·>: ·c'. 

operational variables, such as response time, data . ~.processing, range, etc., on the operating plans 

will be determined. ·. . . 

• 

'>. ,· • 

... ·.· ,: ' 

·' . ii. Targeting Analysis .. Targeting and mission .. , . ·· -~ .;, effec~:iveness analyses will be performed for the · · · · ·· · Model' 192 • 

... '' .. ,' ..... 

. ·/~,?':•':i! ''~:· ~f .;.,, ,, iii. Target;ing Computer Program - A mission 

.. ','·' :~ . ! ·' · performance c ter .program will be developed. · .. 

~.. . . 

. ' ; . . ... '); This, pro Jn 1 produce the "miss ionized" ground .' .. · · ·: :~:.;~1 "· track of the Model 192. Basic vehicle characteristics · · 

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: •• ·~_.:1_',._" .:-:',\: · and mtissiiton variables,bsiulciht as lautnhchi-rdethcovery dbase. · · .· \" 

-- ~ ::.\\~. . ~l~:t~~e~r!:ig:a~:~!:tionsy~n~w~lig~t di~e~~~~; .. :·.>·" ·:;'_.;. 

', 

will be included. . · · , .... 

1.•:.· ::. 

·.b. Survivability: .' .. 

.. ,. ·;: . '"' 

<,; .. 

.... ~~ . ".• ~. ~. 

Support will be provided to u. s. Government 

vulnerability studies. These will include a first- : · .\:·" 

order evaluation of gross characteristics and a 

technical evaluation in depth. 

c • System Evaluation 

: Support will be provided to u. s. GoveDflnle~nt ..... ' .. ~. :.:_~~ .. :. >·~· ., 

cost effectiveness studies. Necessary data inputs . · · 

·"· ISINGLASS ..... HANDLE VIA BYEMAN .. ~ . . ,. . TOP SEGRBT ·." , CONTROL ·SYSTEM -- . · .. , ~., ---... 

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Approved for Release: 2017 f.01 /25 C~~621 ~--'----·---·-· _ ... " 
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HANDLE VIA BYEMAN . CONTROL SYSTEM 

Approved for Release: 2017 /01 /25 C05096211 

TOP SECRET 

ISINGLASS ';. 

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Attachment to • . • 

BYE-2100-66 ":./ ~: . 

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.· ... 

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. •. i ~ . 

in the areas of operational effectiveness and cost, :· ,

1

1

· .· 

manufacturing cost, refurbishmenti attrition,. etc., . wi11 be analyzed and prepared, A te'r'Mto bocuat... ·. · .· .... glide systems based on point designs will be inves- " {·. :' · tigated. · · ~·' .. ~· , . 

' .. '• /.: :· 2. Configuration Definition· $3,250,000 r· 

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Key parameters of the confi ration will be iden- .. :· . · tified and trade-off studies c ucted .to achieve best ·· , .. · design aJ;td performance. The objective will be to define :i'/· .. ·~: 

. a configuration that assures high confidence, substan- .. · · . tiated analytically and experimentally. Design aids, .. such as· scaled models, will be utilized where appropriate •. ;<., · j 

-:. (. " 

·· a. .Performanc'e ···.>' 

i. Performance characteristics will be 

established and will include operational effects . such as tolerances on launch conditions, guidance, .. · 'control, navigation accuracy, atmospheric variations,. 

energy management techniques, engine performance, etc.·~ 

, i1. Developmental wind tunnel· testing will be ( ; · 

conducted to provide data for design optimization :· 

stud;les. Effects of varying configuration propor- ·: 

'. ·· tions and component size will be investigated through•. '. 

' · out tpe flight envelope. The McDonnell Polysonic ·' · and ijypersonic Impulse Tunnels, and the Cornell .. ~ 

Aeronautical Laboratory Hypersonic Shock Tunnel.will 

be uttllized. Developmental wind tunnel testing., wil~ ~.· · · · utilize four wind tunnel models for support of the .. :~:; .· ... design optimization and sensitivity study for · < .'::" · verification of. the performance characteristics. '· · i :: 

" The results of these model tests will be used to '· 

: finalize and validate key items making possible f .:.: , , 

· design convergence of the aircraft configuration. . , , .. " 

. I. A 2-~ percent model will be tested thru 

the Mach 0.6 to 6.0 range in the M.A.C. polysonic 

wind tunnel. Primary .purpose is for configuration .. ~: • .. ·..; .... .•,\o·,• •development and tradeoff study support. A total .... ,.; ,· 

' .. ~ .. . .. . , ·, '. .. ·of three series are planned totaling approximately · •· 350 hours. '-· '-'· .. ·,.'• .. 

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CONTROL SYSTEM Attachment to·.,.· I.·. BYE-2100-66 , .. :·. ., . ~ 

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IJ;. A.~ per9ent. scale m.odel will be tested ·~fmfl Ma@fi tt €@ ~g ill:Y§ l:fl €11@ M1A1 ~ f§@fil:@ ·, «·, •. 

impul'se tunnel. Primary purpose is ~o rformanee. F :._· . . ' . ~ ' ' .. ~.: :~ · •.. ·· ·~:· ~ ~" \.~ development and verification. A total of two aerie's'.'"- . > · 

are planned totaling approximately 150 hours. · .· · · 

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i .,I :, ~ III. A 2 percent scale model will be tested 

. . ' ' ,. ·l" 

from Mach 10 to 20 ·plus in the Cornell hypersonic:: 

wind tunne 1. The primary purpose of these tea.ts · ·.· will be to obtain stability and control and aero• · · ' 

dynamic performance data. A total of two series · · are planned totaling approximately 200 hours. · .,:t'.; 

'• 

b. Design Sensitivity ·.. •' •"it'•' I 

' I·;. ,/ 

·. , . 

',', . 

Design sensitivities will be defined to effect .. . ···1' ! 

. . the bei-st compromises considering all pertinent "·;:: ··~. 

factors. The effect of design variables and/or . ;·"..t· 

. o1:.·· 

constraints such as volumetric efficiency, aircraft ·: ·;.~~\. 

length, glide weight, launch weight, specific impulse, ,;, : 

and glide insertion conditions, will be determined .· ·. "'-<~:/. 

so that the full impact of different requirements . can b@ accurately assessed. The type of research :'} '.)· · and qivelopment program proposed provides those -·~ · ": 

c· .,. design sensitivity factors, including much hard 

core test data, that are vital to establishing the 

best size and configuration for ISINGLASS. These 

desigx} sensitivities will include all factors 

necessary for a practical, high assurance evaluation . :!· 

of prime design variables, including_ such items as ·: ·: .',: 

range, altitude, manned versus unmanned optimization9 · '.;,. 

manned with unmanned option; payload, wing sweep, 

shape, weight and maneuverability; · 

c. Landing Characteristics . '' . :'. '..:. -,.,.::·,. ,. ' .. 

., . , i. Landing capability and characteristics will 

. •·.· .. ' 

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... •; . be defined. The development of the best piloting 

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1 techniques will be a primary o ective of this 

activity. Key parameters will varied to dev~lop 

design an~ performance sensitivity relationships. 

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Attachment to ... ·,·f •. 

BYE-2100-66 •.,i' 

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ii. Landing sgnfi1uration aerod mio oharacteriseies will §e ebtaine~ ifl the Me 6flfle11 ic:llW• 

speed wind tunnel. Configuration variables, such \ · ~. 

,, as base geometry, landing gear, canopy, speed brakes, " · and controls, ·will be evaluated. Primary resources ··· to be · loyed in this activity are wind tunnel models ' . and simu tors for pilot evaluation. The initial · · ' 

corporate-sponsored activity using a 7-~ percent 

scale model of ISINGLASS would be continued. The . ; i.' · 

M.A.C. low speed tunnel will again be used for 

,develo nt and verification tests for 19nding ·· .... capabi ity. Two series of tests totaling approx- .. '.;·' 

imately 350 hours are planned. In conjunction with . · ~· 

this work, an analog flight simulator program will . ''.·' '· ._ .. be conducted t'o evaluate all dynamic aspects of the , :.: .. ·:·· 

landing characteristics and performance. if:··;··:',,:·' 

d. Jiarrier Aircraft 

Carrier aircraft selection will be validated 

by d~tailed analysis of availability, extent of · .'. ·: 

req14red. modifications (wing beef-up, additions of .. ' .,, "· 

cryQgenic fuel storage, etc.) operational charac- . ·. :· ·j teri$tics and performance. . , : " 

'. ;. • I ~ 

i. Carrier aircraft-Model 192 performance 

". inclμdin flow field effects during cruise and . '/, 1: · 

·launch 11 be determinE;:!d. Appropriate analyses .. 1 

for a variety of speed and attitude conditions will· ·,·~r:·_, ... be performed to obtain the complete performance ..... 1: 

envelope. A~ key resource for the development and > ...... , ... verification of the performance of the carrier/ . · ISINGLASS combination will be a 4 percent scale .::·~ ', -":· 

', model to be tested throughout the subsonic speed . :· .. . :; • ·1 range. These tests will include the combined con- .·. ·~ ;; ~. 

. ·· .. figuration for performance and stability and control. , ·. ver.ification and will include proximity tests to , 1. ~. 

establish the launch characteristics. External , · tanks or other appendages will be included on the 

carrier if required for proper simulation. A total 

of two series totaling approximately 250 hours 

are planned. This continues the ISINGLASS/B-52 

testing that has been accomplished in the M.A.C. low 

speed tunnel utilizing the 7-\ percent scale 

·~ . . .... 

'.';. 

model. is existing model will be used as ap o- . priate f·or further test development and verif tl:ot:r:.~ .. · ·'. 

·· ' ,. ·' ~,. .. ~. HANDLE VIA BYEMAN. 

'·; :· IS INGIASS CONTROL SYSTEM · 'f 6P SEORJR .·' 4 ' .. " 

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of the carrier/ISINGLASS performance and launch ohA~Aet•~i~t1c1-

ii. Launch techniques will be develo~d 

substantiated. Various launch conditions (s 

altitude, load factor, fuel loading, etc.) 

investigated. 

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11 ' · Technical suitability of all aspects of the 

sensor installation will be substantiated. This 

will include analytical and. test effort as well as • 1

" • supporting effort by appropriate consultants. . I 

deveiop the window cavity concept and optimize the 

•. . . .~ .. cav,~t:Y design. Geometric details will be varied,_!:o · .-..·. 

•., .. 

i. Wind tunnel testing will be conducted to · 1' 

. optimize cavity and window environment·. Testing wi~ 

.. : y·, determine the effects of Mach number, Reynolds number 9 · 

) .· 

' 

, .,. . . ~ ·, " . , angle of attack, bounda layer transition, cavity · ~, 

·, ~ · .... ·;. • ·1: ... , len~h-to-depth. ratio, a forward .and aft ramp shapes •. ·· 

/·, 1 ·.· · ,' .. ·l:·.-~~.:".·;~· Test facilities will include the Cornell Aeronautical I"'.. 

" : , : . ·- . Labqfatory. , } . '· ;,~~ . 

... · )' • .. ": '/ ·'· . >A. 10 percent scale model of the ISINGI.ASS ·.,, .,, .,.;:. ,· . .~~' .~,·~;•' ,. 1 ··forward fuselage will be used for wind tunnel · ·. <;; , . ·., ·'·.' .:-~'": )-~-· · '

1

' development. ;resting will be conducted from Mach . , , :) . · "\ 10 to 20 plus. · TemPJ:!rature distributions and levels ·:.~ 

, . , : , . wil~ .be established and\ configuration variations will- , . · ,. · · ·. ,. be utilized to optimize the. environment and desi • 

" In addition to the wind tunnel testing, therma , .: ,, .. .'.;:•,.! testing of components in the M.A.C. laboratory will · ·"· · ·" :.! : be conducted. ,, ' !'t ! ." . ' \.", . . ' .~:' • ·. ~· 

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ii. Backup development testing of an active 

window cooling system will be experimentally 

conducted. Wall cooling, edge cooling, and cavity 

boundary layer cooling by coolant gas injection are 

available techniques for the control and minimization 

of thermal gradients. Provisions will be included · in the 10 percent scale model, used for the activity '· 

descr·ibed in the paragraph above, for an active 

cooling system. If early testing and/or analytical . effort 'indicate that the active system would b~. . . . .:. , \ required,, appropriate model test.ing will':.bel-... coiidw:tea ... · 

'.~ ' ~ . . . ' ~-. _, '\ .. '•: . ... ,·: .: HANDLE VIA BYEMAN 

ISINGLASS ·· · · CONTROL SYSTEM 

··':"'.-::·,~--- \•. 

.. ' 

·., ' TOP SBGRE'l' ,,, 

s ,, ·\ , . 

.. ,·• 
••• 

' ' ' 

' ' Approved for Release: 2017 /01 /25 C05096211 

TOP SECRET ·· ISINGLASS 

Ii • i ' ··I .~ ' 

' ,;,.! 

,•.,,. 

'-. , 

HANDLE VJ.A BYEMAN 

CONTROL SYSTEM 

... '• ,'···· '• 

Attachment to .. \. 

BYE-2100.:.66 :,", i1: 

'·;·: 

,. ' ' 

'" :.· 

I" I , 

.~ '. ' .. ' , •. 1'. 

~' . iii. Boundary layer effects on photographic aeuity will ha determined by wind tunnet ta1t1 

utilizing an appropriate scale model. Test details 

and,· instrumentation requirements and design. will 

be finalized by collaboration with a qualified sensor 

supplier. The Mach test ra and similitude required 

' .. I;• 

'' ',. '~ 

'• 

indicates that several facil ties may be employed ;; . , · ·including Cornell and AEDC. ' .. , · :-;.: , 

··"-'· 

. ·~: .. · ~ .'· 

:• .. 

' ·, . ; ~ 

. . ' 

... ,. ... •:' . . . ~. ··.: ... . ;,,, __ ;.' 

-~ ;. < . 

~ . " .. 

' 1 . ' 

'• .. 

f. Structural Elements -; ,: " 

i. Mechanical properties of the roll diffusion .. ;,' ... bonded type primary structure· will be demonstrated , .... :.~·· · by numerous specimen tests at room and elevated · · · temperatures. ' Variables will include basic core . : > · ·· . . . shapes, various types of pane 1 joints, attachments, '" · ·./. · · · ·· and repairs, ·and an appropriate variety of fabri"'.' ·;, 

~· , 

''-; 

1 cation techniques. Many test specimens will be .. · : .. :' ; ~ 

utilized in thts program. Small samples (dimensions·:·;·:.: 

of s~veral inches) will be used for bending, shear, · · compression and tension strength capability tests, · Larger panels (dimensions up to several feet) will: 

be ed for substantiation of design strength . .' l.,' 

all bles. ·• ' ••• : • ~· 1· 

· A 180 gallon tank constructed of roll bond 

titanium will also be used for structural tests. 

·.•.;.·· 

_, ·~. ' 

This tank has been constructed by M.A.C. as a part ".·~ . of the ISINGLASS corporate sponsored activity to .'.i ... · 

date. The tank dimensions are approximately 4 feet.' 

by 3 feet by 3 feet. This tank is of double bubble ... ·' ·. configuration and includes a 1 itudinal shear : . ; . web divider and end bulkheads. ccess is provided ., ,. .... for installing various cryogenic insulations, · ·· inspection, and for repair. In addition to eval-· .'.: \, .· .. · uation of structural ca ility, *cryogenic system .. · . tests including evaluat on of dynamic effects will · · · be performed. The M.A.C. altitude chamber facilities will be used for part of these tests. .' I 

. ' ' 

. :'!.'.~Mil.I'~' ,,,, .. ,,.ii. External shingle design, producibility, · · · and. performance will be substantiated. Testing in 

. , I the design environment (elevated temperatures, etc.), 

will be performed. Shingle· development will utilize .. both· small specimens (about 6 inches square) al)R .... .;. .... ·• ' 

··; - " 

. ·· . : ... HANDLE vu''·sYtMAN""'··•'r>··~:· .' 

· . , : CONTROL SYSTEM . ·.ISINGLASS ..... ·. . 'fOP SECll!t' .·. : ' : ···'.,; 1 ,; : . ' •. ;- . ; ~- • . . . r . 'tr. ' > , 

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\. . . Approved for Release: 2017 /01 /25 C05096211 

. ·tt· ' . " . 'f6f' 1SECRET 

ISINGLASS ' . ·.', . 

',.' 

HANDLE VIA BYEMAN . . CONTROL SYSTEM 

. '' ,,, J 

' ~, • I 

Attachment to ~ · · . BYE-2100-66 .; ,· . ! • ., 

'·1.1. 

, ·. full_ scale shingles (about 24 inches square). Many· · : ·. - . · 1 • ··.. · €1@V@1 Ht spie~~mens Ys:l: Ta D. niekel1 Rene• 41: 9 . ,. · :'.·, •• ~-. • ... ·'.. • ; 1 and ti anium will be eva ted. Variables ta be , .. " 

·'. . ·· · assessed will include: type of core, face plate · .'.,:· · · <· · · 

. , . , ·-; < '>'.'-~ ': : bonding, attachment inserts, sealing, oxidation . . '· · " ·. ·· • . :·> resistant coa~ing, attachment, and high emissivity·:'.~ , . 

" • • • ', 't: ._.-

coa.tings., · ··: ·'·· . \ . .. , .. :,, .' l- ' ... ' 

' " '" .. : ... ·· '· ;·,. Approximately ten full scale shingles fabri- .>· · · '· ·:.:,.' ~.,:•;". · ... :<;::.· ,: ~.- cated in accordance with the selected design and · >.'.;· .".:· :., . . .... : _. . mate-i;ial will be tested to verify and demonstrate :·:.:/~~ty,·, 

..• _,., .·: .·"" · 1 ;;· ·, the design. Variation in design and testing will...'.:.: ·(:· , • " ·'.:, :, f ., ;<'.,''., verify attachment designs, curved as well as flat .. . '.. : . "· . . . shingles~ strength characteristics, reusability, . ··: · .'· ·' :_·, ~ 

.. <•:: life capability and emissivity. Test facilities r. · · · · 

· ··' · will include the M.A.C. thermal and altitude 

: ' .. · · "-', .· '\• ."··laboratories. 

,.·, 

: : 

,, 

) .. :. __ '.' :'_· __ :·.{·-.··.: . "". · Approximately ten full scale columbium ;-.•:. · . _ '":·::;, · .. : ., .... , leaqing edge specimens will be provided duplicating . ., ::- .::~-'/: ·:; , · ; the radius and support method to be used. Testing .·; • • -· ,.; : 1 under load at room and elevated t~rpperatures will ·:t-: 

.. ;,. .. _ 

''.,_: 

"•' ' .. 

... · .. ' 

'~ ' . . · .. ·::.: .: verify strength properties, installation technique . .:':.:·. · and 'iife characteristics. Reusability and operational:. ;' 

lif~f:ime test will include cyclic thermal loading. • · .; 

The tf.A. C. plasma jet facility will be used during 1. 

.. 'l .... "!:.:·' .: 

thi~'. test program. This pro m will also include ' · · . .. ~,. 

(;·._·: .. _( :: : . ; . ~. . . '. 

.. I , : ~ ' ' 

.. ., 

. ,,~ .. , . several columbium panel spec mens configured for "· · · <: nose transition and control surfaces to substantiate 

· .•. !'"• :' their suitability in the structural and thermal 'I', 

: .. design environment. 

:::'~: '.:' ~· An appropriate number of tests specimens for .~ 

.. ··< .. ~ . development and life demonstration of the main landing : . . , ". -~ _gear skid will be constructed. ': . ';"•'' i•: . ". ..... ~ . ~ 

., ' 

.. 

The nose cap will be.developed utilizing previous 

ASSET laboratory and flight results. Element tests 

to demonstrate capability and acceptability to thermal 

shock and oxidation resistance will determine optimum ... choice of material and design. Two full scale nose 

caps will be utilized in the M.A.C. plasma jet . .~.. ; ....... ~ 

·I :: .. , .. "' 0 ,. facility to- demonstrate design acceptability and 

..... 

. 

• < 

reusa,b..ility. · -~. · · 

., .-. , .... ·, 

')• :'.' . .. / ··; .;, ... ,

. . . . • .... ~· 

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ISINGLASS 

TOP SECltft ··· · 

' 7 

',.... ..r. ~ •• ·.•"""' .... , .. 

HANDLE vtf.,.sYm.lAf(~ ·-~·-~. •: . ! : 

· · . ' CON-tROL. SYSTEM · .. 

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__ ,.t\QE>r()yedf()rRelE?c:tse:2Q1_?LQ1/_25_C_0_50_96_2~11 ___________ _.__ __ 11 
' . 

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HANDLE VIA BYEMAN 

·CONTROL SYSTEM 

\" '~. 

Approved for Release: 2017 /01 /25 C05096211 

TOP SEGlt!T 

ISINGLASS 

g. Refurbishment 

' 

"'·· ·,, ,f 

Attachment to .. 

BYE-2100-66 .:< . . ' ,,.,,. "·' 

.. : . ~-: I . . "., 

~- . . :.· . . · ·Y .·: /_; .. '-~ .. •;,. "·t ' 

Analyeisal and t@et ~Ybd~anttaetm1 of tefY~· . bishment requirements will be performed. Significant .. fall out from this will include maintenance require- : .. · ments, turn-around time, and operational cost factors· •. _·,'. . • .. 

-; , ·.: The technology demonstration program will consist 

·. : :. 

. \ '. 

; ,' ;' ,._\., 3. Technology Demonstration $1,660,000 . ' . ' 

: ·.,::;::,_y:'. 

.. ·' 

. . . ' primarily of component construction and testing of 

,::: . , certain key elements of the Model 192 concept to sub- ... · · -~ -~ .. - ·· .. stant,iate and demonstrate a high confidence technology ,:~-;; ·: · · base. . . 

·' ~ ".·. '. .. 

'·._ .• -.' ... : .: "": t-

· .. ;• '· 

' •' ,. "·: .. ' 

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. . · ·t·. :·:, 

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.. ~" .... a• Structure 1 

' I : A full scale section, approximately 13 feet in .... l~ngt;h, including an 8 foot long section of the LOX . . tank· and the LOX/LH2 tank bulkhead, will be designed_.., . · ; . .. · Carrter pylon attach points for concentrated load · · '.. , . inpiits will be included. The dimensions at the aft · ::t' : end gf the specimen will be approximately 15 feet 

wide""and 11 feet high and will taper to dimensions .··,. 

' I ' 

· of ap,proximately 10 feet wide and 8 feet high at the . forward end of the specimen. Subsequent manufacture .. i '' i ' 

·.- ,_: ··' I ,- and utilization of this full-scale article in a . l 

.. v., : f ollo-w on program will provide demonstrated assurance . .. . I 

of all significant structural characteristics including .· \ .. ., ,.,.;', · ,, . "',, .. . fabricability. This assurance is provided for the · ·. ;: ' I, 

" ..... · .:., ' · · · · design of each element as well as for the assembled ··· · I .. ;. .· , .. ·. · > . , aircraft. This will permit evaluation and verification · , f 

· . · >,>... . . of the strength properties of the basic structure, "1.,.:, " 1 

• ·· ,.··.. •. ·"propellant storage, precise weights, weight factors., .. : ..... .. ', ._,. manufacturing techniques, and quality and costs of . '· . . ·~: 

"· · · "' . tooling, fabrication and assembly,. This will also.. . .--~ ... : .. ·.. ' verify and demonstrate successful transition from . _·,· . element construction to full scale ISINGLASS hardware.'" · 

. ~ . 

·. ~·':". 

,.··· 

. I 

.... . ·;· .. .: ,. --.· 

.. : ''" 

: . ·- . ·~ 

'. "/ "t' I' . ,. 1•; l > 

b. HE. it Protection - . 

i. Thermal design cr4teria will be further · analyzed by conducting wind tunnel tests to establish ... . Ua.ntitative heating rates and temperature levels • 

Pr·imary ~resources provided here are two wind tunnel 

models. ·· One is a 3 percent scale model to be uti- . , ·.·. '. ,' . . .... fl ............ ,,.,., ".'. 

·. •. . .•. . / / · · HANDLE VIA-'°~-.... h ••• ._.. ·: . ,\ .. 

,'" ~ < • j ' ' • ' ' CONTROL SYSTEM ,! 

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l : . ISINGLASS 

. 'fOP SECRET ,. <\ 

·.• ... 

8 -----.' 

', 

Approved for Release: 2017 /01 (25 ~05096211 
Approved for Release: 2017 /01 /25 C05096211 

'f'OP SECRE'f . .ISINGLASS 

.. ·~ ~ 

. ·, 

~' ; . : 

HANDLE VIA BYEMAN 

CONTROL SYSTEM Attachment to ... ·, 

BYE-2100-66 ·· 

r'· 

lized in establi~hing the thermal suitability of the eenfi~~~tt9n. Thie ln~luee~ ~he ~Yalita~ive heat · patterns on the vehicle plus quantitative evaluations 

· ..... 

: ·. ~·,> '< . of t,he configuration including hot spots or other ' " '' ·.::· · ~'·\;:'' '11P 1'1'. "tinique areas. The second is a 5 percent scale model .... · , · for the determination of actual temperature levels . . . " ·,· · · . . throughout the speed range for verifications of design • .• 1 1 . .: environment. This is necessary because of the signif- -" " 11 .2 ~ . . icant impact of design environment on weight, performance, >~·, .. · ..:.·. · .. _, _ .. ,t · and. cost·. It~ is planned to use at least the M.A.C. \ 

'· · <:-' ··.: '·· · ·.' · hypersonic tunnel for heating pattern tests and the 

" · · ,. " }i' · Cornell tunnel for the quantitative test program. A 

' : ~ :'" .-. . total of three series totaling approximately 200 nours- . '' are planned. · 

ii. The performance characteristics and effi- ,. 

" 

}: '. ~ ,. . 

' • l > • • i.·:: ~ . . \• J 

.. ·· ciency of the insulation, water-wick, structural . .arrangement including the effect of heat shorts, will 

,be dewonstrated by testing a sample c osite structural . ' 

.···' '·. 

.. · .. ,. 

, ". ~ ; . 

.. ·• 

:•. ,·'.-,. ; 

' , ' 

.. , ... 

papel~ These tests will also confirm t e performance ,.:.,,,, ~~~''' ··-· . ,

1 of the wicking material and coolant distribution and .·3~ 1 -' · • <:' ', servicing systGS!m• ., ', •.·• 

• .. - Approximately six full scale composite structural· · " · pane'ls will be utilized. They will provide a representative section of the aircraft several feet square 

with the propellant tank liner, basic structure, . water wick, passive. insulation, and the outer radiative - . shingle incorporated. Loading tests in compression, .. · ... shear, torsion, and bending will be applied. Thermal 

test to verify stability, shock capability, cycli6 

life J-!__mits and mission spectrum loadings, for life ,. '·: · , verif-. cation will be conducted. Attachment integrit; 

·· ·will be demonstrated using flight environments. The 

thermal isolation characteristics will be verified by . · · tests including repeated exposure to design environment •. 

' . . ·' .. . ~ 

Water wicking development will include a large ... .) 

structural panel with the water distribution system ,; 

incorporated to verify the performance of the water · i 

blanket system. Dynamic properties of the system t 

· (vibration and accelerated loads) will be established,. · · f 

'These tests will include testing in the M.A.C. lab- f 

oratory. Further demonstration of the performance f 

of .this system will be furnished by test results from i 

the full scale fuselage test. section. ·: ... ,·-~ .::.: : ... ~. ~::.) .. · .·~. I 

• ..~ • ! " ,: ' '... I ~ . 

. ISINGLASS · · . . !OP SEeftET . 

9. 

1' 

.,...,.., .... ~"··~·,-'". HANDLE VIA BYEMAN ··· · CONTROL SYSTEM 

'',' 

. ' .·' ....... .......... ~--- ... ·> 

· Approved for Release: 2017 /01 /25 C05096211 

.. ' 
· .. 

. ' ' 

• ' tlill 

·,' 

HANDLE VIA BYEMAN 

CONTROL SYSTEM 

' I' ' ,. 

,·' 

~· : ., " . > 

Approved for Release: 2017 /01 /25 C05096211 

1U.I:" i)f;c;;itttff 

ISINGLASS 

·:·. 

Attachment to ... BYE-2100.-66 

.. ' 

, ll. I··• 

.; . i-

:,, ' . iJ,i, · PhY~i.c;iQt pt'c.l}:llln;•ei@llg an~ 'Chettt1al l)cn;iformano@ ·. :. 1•• 

" : ·. · · · · · of internal i.nsulation will be established by testing:, .· .· . 

: . :·.· ·'. _;, . ·· • promising materials as insulators for the high temper-· ! • 

.. · : .. : · .·· · attire structure and cryogenic tanks. This work ..... >:!1 ::: :·~, .:1 '· ·· rel?resents the selection and experimental evaluation. : ·, · · ;,. .. · , , .. '. ~.: ::- ..... of 1candidate materials for passive insulation appli..; 1 .·~ 

'· ... ~.·,~I::/_,:.,;·· cation. Samples will be tested to establish thermal.··. · . 1. 

performance, compatibility, ease of handling, dura- ·,".~- .' .. bility, producibility and life characteristics. The .. ~ , bes't materials derived from the element tests will be.: ... ' 

,, . 

:,;. 

',,;; I' ' c. 

utilized in the larger composite test articles. , .. ; · '. · · 

Manufacturing . . . . . '01,,. t• : •• 

I ·, · .. : 

. ,· · .',··.·· Evalμation of promising structural fabrication 

···' .:· '° · · · concepts will be contim~ed to develop the best manufac-

.I,·. · • 

'I•• 

. "· ·· · ~uring methods for the selected materials. This will· ·. · · : ;· · . include fabrication. of nels with various geometric . ·'.· :· ' .... : ... < confi ra\tion and attac nt details. Welding and stress · · · . ;-: .,. ·· re lie g methods will be evaluated. Non-destructive .. . , : ., , .. ; . , .inspection and quality control techni s will be developed.· .. · ·· . · These activities and data will establi 1i a solid basis · ,· .. .. . ; . · .. · ...... · for optiWizing manufacturing time and coat parameters •. · .. ·t : ·. _.' , .. .!; 

• . .,. '• : .'I,' 

· ... · ·:: . : d. Cryogerics ' ~ • ";' ~ :t ~· • '~~· I 

.. '•, 

"•t . 

":. ' .} ) . '· 

.• • . • , · ~ .: 1 The perfoi::mance of the cryogenic sys terns will be . · · .-'. · " :: ·>' 1 demonstrated. This 'will include testing to confirm .. . ·, :~· .- ... , '., boil-off rates, stratification, transfer-rates, and , ullage. Propellant dynamics will be determined by .. ,. 

I .. · 

.... 

',· 

'· · . appropriate scale model tests. Results will define those~ · _key characteristics necessary for best tankage design. '; .. '·,, 1,i · •.. 

. . 

.• 1;. 

:. ·, 

\,,,; 

. ·.·. 

• While available analytical techniques are quite · .;: <': ., advanced and in some respects well substantiated, a . '. .. · · ' · significant amount of experimenta 1 cryogenic work is · ... · . ., · . ,._ planned to identify items and considerations pertinent · '' · · to ISINGLASS, including verification of materials selected . : ·, . and fabrication techniques. .The 180 gallon, double bubble·, · .· 

· .. . . diffusion. bonded test tank will be utilized for numerous ., .. ·. · · "' prw:>pe'llant transfer and storage tests with a wide spectrum .. , . . ·.:. ' : of environmental design conditions imposed. Many typical 

:, ·lines. and 'components will be ev~luated. ,. ' 

,• ' ~ . 

.. , . . . · 

.'· 1 ; 

•.• 

··' f . 

:,\ . 

.. 

.. 

ISINGLASS ··~-· 

"TOP S!eRB'l' · •· .· 

10 .. :· 

Approved for Release: 2017/01!2:.co50~?211 

' . 

...... ,._.,,,,..\~·~" HANDLE VIA"'*·B¥'.EMMl• ..... ,.. . . 

CONTROL SYSTEM 

,. ·' 

, -:--~..__..2 __ .. : 
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· Approved for Release: 2017/01 /25 C05096211 

. xur,~ECKET . 

· .. 

ISINGLASS ' r • "'•' ' ~ 

HANDLE.VIA BYEMAN 

CONTROL SYSTEM ,. 

' 

Attachment to'"';:·._ .. 

BYE-2100-66 <: \, ,. . . ·'' 

• •1, '.. " .. 1·; 

. i 

"''I'./· 

. ~ ': )~ . 

' '! .. : ~..- . 

· .. 

... · .• '' 

·". :. 

! ·' • 

A small scale tankage model dupti~atin the. J,nternal · ;. ie@ffi~~¥V and v@tYme ~l§trl~~~l@tt @f igi e w11t b@ @e 

fo conduct verification tests of propellant volumes 

:. ; attitude sensitivity plus quantitative testing for estab- .. . .. '..·. · liishing dynamic load effects with various propellant levels. : · .. Cost B""'d Schedule Substantiation* .. " 

' . . ~ ~ .. (<. 

=' : • • 1f A primary objective will be to develop a high ,-, . · .. : ~ \~. ~.:, :· .· ~ ·: confidence base for cost and schedule performance. These : ,/ .. '., ... ; · · · analyses will utilize the results of the element inves- « :.,: · . 

. ·· ·, ·, .. : ·. t iga t ions 1 conducted in the previously delineated tasks ~ 1:. • · 

, ·_'..'.: ',: ·;, ·• .: · and will use prior McDonnell experience in the design, ,,,. ·· · •· .' .: .. ; : ·-. • 1 development and production of advanced aircraft and . . . _ ./ , ., · > . , spacecraft systems, ramjet and boost-glide vehicles. · .. , ·:.·.~ . . ;· .:. ._:'.- Particular attention will be appl~ed to systems involving . · . :· . . ' ~ cl -<: ' :',_first generation concepts. . ' ~. '" . ; " .. ·'. ..:, ' 

. . . ·· ...... ·: 

. --··. ,, - . ; . ' 

' 

" i ~' ' 

·: .· .. ' .' 

',°."' _;; :':. a. Engineering Cost Factors ',•. 

··, .. · ' 

. , Technical and cost data generated during this ;'I,: · · 'program will provide a base for evaluating engineering·! · : . : ., u .. design and development cost. Trade-off studies will 1 

· · · . '' : be used to optimize development solutions. .. · , . 

. • 'i'. b. Manufacturing Cost Factors I 

. Experience derived from construction of repre- . , , / . · '., sentative panels and test sections will provide data " · .. ;. "··.for developing manufacturing cost factors and refining .· · ... program estimates. Comparative cost criteria will be · · ' . used to select the most effective manufacturing 

,. 

. methods and best materials. . ~ . 

. ' ' \ . ··: .. . , .· '. 

c. System Cost . .. ~. . . . · ... 

Initial cost estimates for the complete system . .f. .. '.: 

will be progres~ively refined as the system design . ·. "·, 

and operational requirements are defined. These ,;1 

. r - -.. i"' .. >*The cost o{ these items is included .in the costs · , -: ·quoted for: t~ previous paragraphs,. " j ~· ' ' 

" . ~·" 

-:;.',,. 

.. ' . f• '. ~ ' : ... 

l .. 

' ' . ' .. ..· .... 

. ., :0. ' I 

,I' ., , . l ~ :f .• . ». • .. · 

·.' ,- .. . : .·' ·~' ' . . • .-.,. ". -'~~-~ ... ·i, • .• ·. 

. _, ·"'· .· .... ... .. ·• HANDLE VLf .. 'BYEMAM"'·• "~•· ·•.:.~ . 

'1 •• 

' :'; :: , ·.:; : ". CONTROL SYSTEM, · : . ,· 

..: . ISINGLASS -· .. :.. ,,, · .. · . . 'FOP SBORB'f · ·; . :·: ' .:: . . . .. ;' 

11 .. :: ... ·. "· -. ' 

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. • • '·'-t . ... . ~e41&,; .... ... 

. Approved for Release: 2017 /01 /25 C05096211 

?OP SECR:E'f . ISINGLASS 

. c • ·• ~ f 

HANDLE VIA BYEMAN 

CONTROL SYSTEM Attachment to .... · , .. . BYE-2100-66 . ; 

. ' . 

, '· .. 

·,. ' 

' .... i '•' t 

.. ; :·-· .. :.· 

:;···· ... ' '"' ' .• '. ..... : ... ·1 , . ~· .... 

7 ..... • 

'. ,'~. • ..., : , ! ~ 

estimates will be frequently revised to maintain an· : · i ·· · · 

up ... to\ 1ata program oost picture. ,.,.. ~ 1! I 

Estimates based on historical and statistical·r .... data will be cross checked with detailed staffing .'._.' 

and material requirements developed during this 

.Program. * ( 

f :· 

d •. Schedule Analy~is ' >,·' . , 

'', •' 

A master program schedule for the flight vehicle·.; ·:, · 

and supporting systems will be refined and updated as ·: .·. results of this research and development program · .· : 

become available, to a level of detail and definition ..... '. ., . _.,.. that gives high confidence of achieving the major .:. ·· 

. ;.; ,;- -.. . .... : ,·:·'.>·.. ·program milestones. Subsidiar:y schedules will be ",·· .. I 

.:' ·'" •, 1' 

.') 

: .·· 

·:· ·- .-··,. maintained ·for major subsystems. Analysis of detail ... .. ) ,,,. schedules will encompass outside development and .. i 

production of both CFE and GFE subsystems. Coordi- , . r. 

nation meetings will be conducted by McDonnell as .. · · ~' 

Pr am Mana r and will provide necessary interchange··· ·· · ;, 

of ~ta pert nt to the detailed elements of the · · :. · · 1 

schedule so as to assure that all significant effects ' / r· 

are included in the overall planning. .,., :· ... ' 

Revie~s and Documentation ·-:,: · · ·· fi J • ' J ~. 

of program effort will be .·' '· ~ 

. /··--~>t' s • 

··" .. ,., . . P · ess and results .. ; : <·:1 :· ;; presente in concise form at frequent intervals as shown ·· !:.' 

, .. :.· : . ._ 

. . 

. · · · in the schedule. Reviews ·. ·: of• · ·:·:"/ ' .. ~ . .'. and documentation will consist . r .. ', • '.'·' ; I ~ 

~· 

a.·. 

I[ 

.... ~ .. : ~ f? · .. ; '· . 

·-~ ....... . 

Bi-monthly pr am reviews at McDonneli in · '. ·:. 

which all sig ficant milestone accomplishments \' 

and program decision elements will be presented,. , ". '.·; 

These will be supplemented with informal reviews~ ·.j · '. 

of all program activities. · >:, ".· ... · , " ~ 

••• <;. ~ •• • 1 ; 

'\1 :.: .. b.·..- A final summary t report cont.aining all . · !, 

:·.; . -'· .· :\;·· .. , .!~o~am. accomplis n~·s,-·:: '..~_::, .. :· · ::. : . [ ' .... 

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DESCRIPI'ION 

1ASKS . . ; .. \"'..• 

'. ., '''111''1' ·11·1·:·:·"'1_1>.· :'.: 

~·srstems Et.rootivoneos : ; · :! 

1

:" 

·:' Miooion Ei"t'octivenesa ...... '. ... '. ~ .. 

;:·.: Survivabili~v ............. ..;: ~.· ·.:. '.:. ·~ ,..;·. fl'! . • , I' •I.· •. ". , Systems Evaluation ....... ·a. t, .. .,._. ... '· . . . . ' ... ·~. \ " 

~~ . ' '.,.·· ·; : ;· "i Oonrigu:ration Dotinition 1 · • : • 

1... Pe:rt'o:rmanc e .............. .,;· .... ·;.. .. 

'·Design Sonait1v1t;,y ....... ·~ ',,; ·~ ·~ 

: . Lnnding Cho.:raoto:riatio1 ..... • ... ~ · •• 

Co.:r:rie:r Airo:ratt _ ...... · .. .: · •. ~ .;, 

:Photogrnphio Po:rtormanoe.,J~ \.· ... 

st:ructu:ro.l Element.a .... ;; :;i:,:·::.' ... •• ·, •• • .t 1· ... e ··~~ . · · ~-, · Returbiahme~,t ..... ". .. ...... .:. ;;;; '. ~ ;..: · .. ·~ i ·!lt't~ J" · I'' -·, 

i.,. . ·(,~,I ' I '. ,, I . • . . }'· .;.·' 

'" ~ ·; . ··::. 

~.~ecijriology Demonstration · '.. ~ · · - :i ."• .· ·; St,,ructure •• _ · •••• a.. • .. · •.. ,.. ·• .. .. 

· ~ ·. Heat Pro~ection •••• .J ... ·• ·.~ · .. .. 

... . Manu.t'a!ltu:r1ng .. ,~ ........ ;,, ·~ .~ 

'·: .. Cryogenic ...... _ ~ .............. .,'.:. .. ;.. 

(. ._''• ·,''. ;•e ";; ~' I • • ' ·, ·, f ,· ~ .' ~ _' • 

t . I 1 

_':.. Coot/Schodule Substantiation". : ·. · 

\ Enginod:r1ng Coot Faotor ~ ... ·: ~ ..... 

... '· Manuto.cturirtg Cost Faoiora..:. ~ .. ;.. . . . .. . . .r ..... .., .·. System Coat_ _ _ _ ... · · .. 1 ~ (.:. '...;. · 

, I · '• 't 

Schedule Anai,aia ... · ....... ;.;.·;.;.,;·\-'.:. """ ' ... :. : .. (. : :J.-~~·/'' :'.:·,• . . ~\ 'I !'.' T ' 

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1. 2.1. 

3. 

4. 

Operations Plan 

Targeting Analysis Targeting Analysis Targeting COl'Qputer 

·.. Survivability .,, Systems Evaluation . ' -: . ~ -· . . ., ~.,. . 

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. , .. · : . ' : ' ·~ -. ·, .. : .. 

~; .!' • •• •• • , 

1. 

2. 

3 • 

4. 

Li.ft/Drag Ratio Established 

Flying Qualities Established . . Flight Envelope Established 

Operational Performance Established ,•;.,, 

\ '. " ' ~ ,. :·' 

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1, 

1. 

2. 

3. 

Weight Sensitivities 

Performance Sensitivities 

Sensor, Engine, and Equipment Install. Verified 

'! .. 15 •• i 

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4. Vehicle Size and Shape Defined 

·'Landing Characteristics 

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. , · .. ·· 1. Visibility Techniques Defined .. i. 

2. Low Speed Lift/Drag Ratio Established , .. · .. 19 

30 

39 

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-~ ~' ,; ' . :. ·-

:· ·, 

,,, 

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3. Landing Techniques Established ,. ~ 1 ' \ . ~ ~ .· 

<', Carrier Aircraft . 

1. Performance Summary · . · .. 2.. Launch Techniques Defined 

' '" 

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Approved for Releas~: 2017 /01 /25 C05096211 

._:. . . ·. i.. • 

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.... . -........ :,. ~ .... HANDLE·:·V\Dt· BYEMAM··~•··• ·; 

CONTROL SYSTEM • 

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Approved for Release: 2017 /01 /25 C05096211 

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ISINGLASS . ··· ·:.; '·· 

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HANDLE VIA BYEMAN 

CONTROL SYSTEM 

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.... , .... ' 

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· Phetegraphie Ferf a~manee 

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•. ·'.· ,·· ".. 

1. 

2. 

3. 

4. 

5. 

Cool~ng System Analysis Boundary Layer and Shock Flow Field 

Characteristics Defined 

Cooling System Performance Verified 

Boundary Layer Effects Determined 

Window Cavity Configuration Defined 

Structural Elements 

. 1.' 

2. 

. 3. ' 

4. 

Roll Bond Mechanical Properties Verified 

Nose Cone Material Properties Defined.-. .·· 

Alternate Structural Concept Analysis . Shingle Characteristics Completed .. , ~.d 

,_«:·!< . . '.,Refurbishment . . ~ .. ···: .. ·.·· ...... . ' j ~ 1. Initial Maintenance Requirements >,. , 

Defined • 

' .• "'1• .•• , 

. . • .. '.. "<::·\:> 26 '< .... -'1•: 

. < .: >~-., " . 

2. 

3. 

Refurbishment Quantities Defined·· Mat'.~rial Replacement Schedule :· : · Established 

) . ,.. 1,_ ' • J ' • ' ~ ' 

· :. ,, · · · -~>· · : .. ~ ~': Strμcturer' 

. ,· '·. 

: ' ~ •' 

. 1. 

: .. .,. 1·2 . ? . ' . Producibility Studies Complete Structural Section Engineering Complete 

. Heat Protection •'f. ·.:,, 

1. 

2. 

'· .. '35 

39 

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-- ·-,·''."'.I 34 

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Initial Water Wick Efficiency Test 

Initial Cryogenic Insulation 

·Efficiency Test 

3. Water Wick/Structural Element Development 1'. " • 

23 \ . .., . 

26 

35. 

! ~' .. 

... . ·. 

'• .. ' 

. (· .' . ' 

' · Test 

. " 

4. 

5 • 

External Ueat Transfer Rates Defined Ex~ernal Temperature Levels Defined 

' ;' Ma,nufacturing 

j,. 

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39 .1, :,_ ·; · .. .'' :.· .. 

'. . I 

1.,,. Roll, Bond Development 2. : ':. Inspection Techniques 

Completed 22 

Defined;:... 24 , ... ' · ,_ 

·, · ... : 

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. . ~ . ' . ' . ~ . \·. . .'·· . , :· " :. 1:' . . .· .. -•,.'I' 

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. ISINGLASS .• 

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· Approye.d for Release: 2017 /01 /25 ~~50?6211 

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Attachment to 

BYE-2100-66 

·WEEKS FROM .. GO-AHEAQ ' . . ., t ··'' 

. ·' 

... ·, 

.• ~- . 3. 

4. Repair Fabrication Techniques Verified ~~~26 

Shingle Fabrication Techniques Verified ' · 39 

;, . ::,~· Cryogenics . . :· ~· ,• . ', 

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·, l ~~. ~ .:: ... 

·":······;,: 

-~ ... : ....... 

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2. 

3. 

Initial Volume and Ullage Analysis 

Initial Insulation Qualities Defined . " 

Initial .Cryo. System Helium Press. and ... · Trans. Tests ., ..... 

Cost Factors 

Cost Factors~:· f. 

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Engineeri 

Manuf actur 

System Cost 

. "··~· ;.

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Approved for Release: 2017 /01 /25 C05096211 

HANDLE '.·VIR-"' B'IEMAN• ...... · • . ; 

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BYE-2100-66 .. ;'., :- ''···. 

: I, i11 idiWlii Stydis1 . 1, I ' :: .. 

Internal Turbulence $118 000 , ·.··~,'- .· · .. >,,. 

9 , ... ': •, :. 

.,.;_;; . . . Tests and analysis will be conducted to .. evaluate the effects of the internal turbulence 

'' ,····. '' '., ......... _·;·-..._,,_;· ...... ,.;,_,.· 

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· · · generated by the heated window. In conjunction ... with the window tests below, this will allow 

reasonable balance i~ window design between 

-degradation from window distortions and degradation 

from internal turbulence • 

" . . ··:·,:.. ·:, ·, .. ·, l . ~' I 

, . ..,· .' : ... :. ',.. ' :; 2. Tests and .0,. ''l', :·~- . ', '.", .·:! ;.' •' ,' :.. ~It 'tf,j,·~ I'' 

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$32,000 . ~. '\ ': 

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·· · ·. ·1 · ' These tests will eva.,luate the degrading effects . <, ··<· " ;, :·. 1

· . •• .. • of window. gradient and means of reduction of this · '" .... ·.~ degradat£on, using wind tunnel data for evaluation 

,• ·' ..... , :1,. ··' 

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of heat flux distribution. Current estimates are · ":·. ;_.··:·::, 

·• .. ~hat the~ .. window will be the limiting factor on ground ·":· · . · resoluti9n. In conjunction with M.A.C .• , the effects .'~·· 

of the boundary layer on optical rf ormance will be . ; .. ·· evaluated. Current estimates of dary layer · effects, considered negligible, are based on extra-

.,k: .. · ,. polations of existing data at.relatively low speeds ' .. '' ·~ 

· .." · and altitudes. · . .I' ' 

' . ~ . 

··. '•:' 

. ' .. ~, 

The above three efforts, at a total of $150,000 · ' 

can best be done by Perkin Elmer'· who have done ... ·. -. extensive ·prelimihary work, and are leaders in t~~s .:1 ' 

. _: field,,.: · ·· · " ., •c." 

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Payload Weight· 

Payload Resolutiml 

Range. 

Altitude over. 

.. -- . ""' . Ta.rget. · ~ . :'' . ·t· . -· .. · ""'· .. ' 

-~peed'<: __ .:' 

hicle Weight . ~~ 

. , .. ':·· . . . Launch Vehicle .. ~ - ' ..... _-:··::£°·~---.':·>--:::-.: .. :=~~-·'-\-'..;-: ":· :··1·: _,.';..;·.-. 

Total LaUJ?-Ch Weight> '. _,. ': ... ~ .. ,,. .. -. '·"':" ... ":-·:-;;.;,..;. ... ;_ :.-~-

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TAG BOARD 

~·- . .... . 

1 '-1.5 1 .. 

3000 . 

80-95,000• 

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ISIOOLASS 

1.5 ·s·· .. 4 .· =': . 

S-103(l) 

500 • t~ ,· 

:· .'· '{1-:'~· ~. . 4.:.61 . 

7000- Orbital 

2051000 1 descending 60-SO NM 

· to 125,000~. . .. 

. . M 21 slowing to •. 

M 7 .. : ;.':·· .. : • •· 

.- : - .... ·:·.· ;·.,'::.,·;" ... _ . ~ ...... ·, .. 

B-52 

,-.- ........ 

.Propulsion Ralljet (MA20S-4 .LOX,-H2· (Ne1'} . '~ - . --~- -. . . .. 

.. 

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. ' " - . . ~-~- ·"'. .... -·~ •.. ~ ... :_: .. : • _'> _ '." < •• "".· 

Development Cosd4r · (Millions) .: , . . :; . . ~ ·, . "' 

-· Development.Trine: 

(Months) 

) S-l03 Air taimch Reconnaissanqe 

(2) 

(3) 

. (4) 

s--104 ·.Boast Glide ·vebicie .. 

S-105 Ramjet· -

, 

.<:_s) :!111, l~Jn 

' . . ~ -· ' . ~-~ .-:-·.' 

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g., 1: 

. 500. 

'4-6• 

Orbital 

60 NM· 

• - 0 

. . Approve'd for Rele~se: 2ch7/01/25 cos696211 

500 

4-6• 

7000 

60 NM 

., .. ·' ~ ' ·.:· •. 

500 ~ ! . ... '• 

4-6•j' 

OrbiiS.l 

60 NM~ 

. ' ... _ .. · .. 

S-

. ' 

500 fc 

_/ .. -"_-·4~ .. · 

. :3-4,C 

9!)-llC 

5500 

·. B.:..5g 

94QO 

Ramje~ 

. Skybo:i 

45 
. \ . , . · ...... . .":· .. ~ -"~··- :~ ·• »,·, .:· ":. ' ,-... · . ,_, 

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·. -~·:~.·~~~-.\:~-··~-~~· .~.. ' . ··.· .. . ..:·.:··: . ,·\ ~' :.· .. -~> ···<·:_-:~~- -~.:. 

AIR · AIR . . ' . GROUND 

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TAG BOARD ISINGLASS S-103(l) .. (;t2N_C1

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420 1545 500 ~00 500. 500 

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l t __ }.,~;·.·: .. 4-6 f 

_ 7000 Orbi tar 

205;000' descending 60-8o·NM 

to 125,0001 

M 21-slowing to· 

M 7 . : 

Orbital 

. -~- .. , ~- . 

. 25,450 1080 

B-52 

.-. ·, 

... ·-132,770 ;, 

Ramjet (MA20S~4 LOX-H2 (New) 

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- 60 ~lM· 

Orbital · 

-...... ·- .. · 

B-52 

4-6• 

7000 

60 NM 

25,500 fps . 

'· . 

6800" 

B-52 

4-6• . Orbital 

60 NM 

Orbit.al 

4340 

Approved to~ Release: 2017101125 coso96211 · 

~- - . ... . ~ . 

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500 

'"' ·4.:01 " 

3-4,0.00 

9~-llID,,©00 

5500 

. B-58 .,... _ _.ft 

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