RECOMmcnDiTion

TO THE AIR STAFF

AN EARLIER RECONNAISSANCE

SATELLITE SYSTEM

(S)

12 NOVEMBER 1957

U:S. • AIR FORCE

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SANTA MONICA • CALIFORNIA

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1 70 0 MAIN ST. • SANTA MONICA • CALIfORNIA

12 November 1957

Deputy Chief of SUM Development

Headquarters, United States Air Force

Washington 25, D. C.

SUBJECT: AN FARMER RECONNAISSANCE SATELLITE SYSTEM

In the light of recent events, RAND has reviewed national and military

intelligence problems, existing and proposed reconnaissance systems, and in

particular, the current USAF satellite reconnaissance program (WS 117L).

As a result of certain technical and conceptual breakthroughs, it is concluded that efficient satellite reconnaissance systems of considerable

military worthcan be obtained earlier and more easily then those envisioned

in the current 117L program.

The systems proposed in this recommendation differ substantially from the

current 117L system concept. ,

The proposed systems use a spin-stabilized payload stage.

They use a transverse panoramic camera of essentially

conventional design, fixed to spin with the final stage,

which scans across the line of flight.

Either the entire payload or the film is recovered.

The first of the proposed systems uses a 12-inch camera, carrying 500 feet

of 5-inch vide film. The extremely short ovum:, time--1/4000 sec--eliminates the need of attaining a precise altitude, exact imago speed synchronization, difficult performance characteristics, and related problems. It

will provide sharp photographs of about 60-ft givund resolution. Each ex,.

posure, covering same 300 miles across the line of flight, 'will photograph

same 18,000 aqui. The 500-ft roll will *Over some 4,000,000 aqui (almost

half the S.U.) and show major targets, airfields, lines of communication,

and urban and industrial areas. This satellite codld weigh about 300 lb

and be placed in a polar orbit at 180 1; 35 miles altitude by a combination

of rockets such as Thor plus second stage Vanguard plus a third stage smell

said rocket similar to the Vanguard's third stage. A one -day operation is

envisaged, with recovery by command firing of a braking rocket on the 16th

pass, so as to impact in a predictable ocean area.
Deputy Chief of Staff, Development 12 BOvether 1957

Page g

The next, more sophisticated, system mould use a 36-inch camera, carry much

more film, do more detailedroxamodimance—vith a ground resolution of

about 20 feet. This system can possibly be Thor boosted.

A third system—undoubtedly requiring Atlas-type boosting--would use a

120-inch camera and would have very large film capacity. This system will

be able to accomplish very high quality photo reconnaissance and, most important: will do it better than any Air Force system now in development or

in prospect will be able to do in the 1960,s.

The earliest and simplest of the several systems will collect at least as

vi mach information in its one-day operation as the "early" ilnvehicle will

in its useful life.

Because of our belief that the first system could be available about a

year from start of work, the second in less than two years, and the third

in about three years, we recommend that the U. S. Air Force begin Bork

immediately to accomplish this prevent.

Success of this type of system should result in refocus of the present •

components of the 1171, program to those tasks requiring the communication

link and cyclic talk-back facility of 1171;—warning, and daily surveillance

of selected targets, being the principal high priority tasks requiring such

an operation. Thus this new family of satellilttecand the type of satellite

at present sdheiaiiiiiiiidei7 II7L progisim Would be mutually complementary and

not competitive.

Descriptive diagrams and more detailed discussion of the proposed system

are contained in the attached appendix. A RAND ResearchiMmoranduk

R11-2012, is also available.

RAND is actively engaged in further and more detailed studies supporting

these proposals and mill help in every may possible with the fulfillment

of these objectives.

Yours very truly,

‘lefeige*

F. R. Collbdho
L'/ i2/5;

1

A:f EARLY RECOMMISSANCE SATELLITE SYSTEK

dclwr11:a A rfr-r.....naLnaa.h.te satellite syn l .:ma that vnuld

3'.ntple L . v:)uldq'au r:cespared

t: ,+. proviso, and vould ser..!! ma qxtremei::

tall: tit:— purpun.:. The system ::se a 'lac& ra esa•ntt ally e,:-

el a re:att ••el:, uncop:.:.0 1 ..1nated orb14.1.nr,

Lattne1.1:a: da%e a:Jout onc: year CrIn *.re da •

r..! of Inntrit:t 1.3 11!"*MplaZdd. •

c7:c.ine v'.11 prrAltee picturem a s.tale mad rasolut! 0:1 7.. a: • 14 11

Leld. 1-0 t..1.1 0:n1ne I 1A-rslaa•..1..:.: isholvt L arrte.s3 t

on.

RECOMAISSAJCB: htEDS 

The need for better :.nrelli.L.enee or. t:te USSR I s acknoviedixd,

a•e aerf reeonra•.ssruice 1.0e:-' a

•

l.. 1 - • 3 2r7eferz.-ed aear.s .

For cr.e zite area cceupied :ne

• 

U-:4..ca and 1 4.8 political •

sated: tes *.s . • ry larze aral, for the wet 1.nacnesatbin e.xcept

cr.'erf.12.cr:t. Secondly, La the !..mediate fut.ure 'be 7i-.41.1. for us

..tuov a Great deal &bout the p31:-..erns of use. :1s.:.al2.az.t.on, 7oncealtent of it Is ftssentl.al ve he' uttatled

informati,,n fr= time to -.Line -on. 0:1 rlraft-rtssiLe p:.as .. Str:!..et

7.1r.ion. We:- laust aharo.c.:er :ozaposL:lor. cf rte--eats

our .1:LTns sr.d- sec:Le. t;-.

dasc.1.;:ag ale,orne p..oto:•rtp:LL•: recannatssar_ce 3:,7311=S It is

corr:eritant way of de, eloPf.r.z, Opera-lor.al t1.1/..Ln terms

of four 01' rnconnaisse.nnet B. C. aud D.
11/12/57

Level A provides lar-e-area search, measured tn millions of &ooze

miles. Level B is limited-area search, measured in hundreds of thousands

of square mile°. Level C, spec.-point-objective yhotwzrapn •, is

measured in Undreds of square miles. And Level D, technieal-1:.telligenceobjective yhotocrapy,. provides coverage in blocks tens of square miles

or .less in sine.

The reconnaissance satellite system proposed permits us to press

systematically from Level A toward Level D In a series of swat= improve,-

ments. It will first enable its to cover millions of avare miles of the

So%-ict Union. zirtng us photocravis of such a scale and resolutLon that

significant intelligence information can 'le oitalned. Such missions can

be reported from time to time to r2-.-eal new developments in tae Soviet

posture. Reconnaissenee at Level A will also be valual%I.: prnridIng

infermaiAnn ve•erm to conduct more detailed re • oncelsaance. WOle the

2:13tent will not ;:roe de els leth varftin: t will help us

estimate Soviet eapabilities aftd ceri.atainds of mko r tarzeta.

2. MCA/EPA

rte cemern ?roresed for t:: '.:s isa nrsnevo-ae nanorerx".c lamer*

coatm!ninz m 12 1.n. focal-leng, hIcnly correctad ill .' lens v •: e:. ce-:ers

a fair14,- narrew enz,le of approxlmat*el-: decreer. rutsrmO.nv is

aecamt)its; :ed Iv the exped:ent of ranit.t: tte ins ecros3 ft111

the exposure. Lim:.

Pm- hrens”on.se anannin,.: of ..e 1-ro-trtd trims a satell:tc. , camera

must r7Wmte arowd the Icnsitlienal Pr es e the -.chicle. For t!'!e

'A in nropco•d to rotate entire 2n boil stage vitt the camera

st6acned, ..:enerahli...: a sweep ac:• es lime of flljtt.
U/2/5

3

It is not proposed to rotate the camera within its carrier.

Figures is and lb shoe the gecmetry of the camera, lens, a.ad focal

plane relationships. The lens is mounted perpendicular to the carrier's

roll axis behind a quartz window in the surface of the carrier. The lens

images the gentrid on a fixed slit in front of the focal plane, the slit

serving, in effect, as a very That shutter. When tne film is moved

during time soma exposure, at a rate exactly matching the Image motion

produced by *Manage of the carrier wer the ground, a continous, sharp

photograph is produced in the focal plane. During :rte portion of the

rotational per !'x: in which the lens does not 'Gee' the around, t• te slit Is

capped and a meseurod length of film is rolled off the supply spool in

readiness to: the next exposure. At the same time, the last exposure is

wound up on the '.ace-up spool.

Note List the tranoverso panoramic camera under discuss Ion does

not require the enual kind of nititude stabilization necessary for cameras

mounted :n aircraft. The entire carrier rotates; van is al important

distinction betleNmt this proposal and otaer proposals for camera.carrying

oatell!tos.

Spin is imparted to the payload stage to produce the scan alcessary

for prodaciec Oetographe across the llhe of flt6nt. In addition, spin

Imparted to the payload stage ctabil.zee L A inertial space. That Ls,

spin steailinatton serves the twofold purpose of stabiliziug t;:e attitude

of tree camera 1.9 space and sennainG the around at t.te proper rate.
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Pig. la Camera Geometry
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Fig. lb Camera Geometry
11-12-57

6

The proper stabilized attitude cf the camera in space is determined

by the geography of the area to be surveyed (see Fig. 2). The tremendous area occupied by the Soviet Union and its political satellites has

its major axis in longitude; that is, the area is stretched out in longitude and compressed in latitude. Most of the territory ve are interested

in, from a reconnaissance standpoint, lies between 40 degrees North and

70 degrees North. This fact turns out to be very fortunate as regards

attitude stabilization, for it means that if the payload vehicle can be

stabilized in an attitude horizontal to the surface of the earth at 55

degrees North—i.e., midway between the two latitudes—the camera will

produce acceptable pictures over the entire distance frost 40 degrees North

to 70 degrees North. (The satellite is considered to be on a polar

orbit, as will be discussed below.) Note from Fig. 2 that, when the

payload stage is at 40 degrees North, the vertical, with respect to the

long axis of the vehicle, is pointing back 15 degrees with respect to the

earth; at 70 degrees North, it points forward 15 degrees. These angles

result in very small errors in uncompensated image speed. These errors

can be completely disregarded in The photography, as discussed below.

Another important feature of the camera lies in tne employment of a

very high effective shutter speed, or short exposure time. This allows us

to ignore fairly substantial changes in altitude and =compensate& image

speed, changes in vehicle velocity over the surface of the earth, small

angular rates and displacements, and other such effeeta which, in any

customary reconnaissance vehicle, would certainly ruin photographic quality.

It appears, at first sight, that taking photccraphs from a satellite

moving at about 1;4000 miles .p.;:r h.ru: would be an extraordinarily difficult
Recovery

impulse

cad re-entry

.1

• 15 '

Orientation

and final .----.

boost

S

11-12-57

7

Fig. 2 TraZectory and Payload Attitude
11-12-57

job because of image blurring, the lack of sharpness, the lack of definition, and hence the lack of information-gathering capacity. This first

impression is not entirely erroneous. It is difftcult to take pictures

from an object moving at high speed--but not impossible. It can be done

if the image notion during exposure is kept as small as possible, consistent with the requirements for definition.

This satellite reconnaisscnce system is not intended to get

microscopic resolution at, say, levels of 100 lines per millimeter. The

goal, believed to be fairly easily attainable, is a modest 40 lines per

ma of film resolution. This compares vith certain specialized reconnaissance

systems nov in use.

A statistic commonly used in describing aerial reconnaissance systems

is ground resolution. Ground resolution is simply the ground dimension

that corresponds to one line of resolution in a focal plane. In this case

a 12-in. focal-lenzth lens and 40 lines per ma are being considered. Thus

the width of a ground element produced or projected 13ack on the ground

through the lens system is 1/40 mm as seen from a distance of 12 in. or

500 mm. For the design altitude we have in mind here, the resolution is

about 60 ft.

The effective design shutter speed for this camera is 1/4000 second.

This speed is obtained by. properly designing-the slit described earlier,

in conjunction with the film speed and rate of scan, or vehicle rotation.

This exposure speed is consistent with the choice of film emulsion--called

Plus-X Aerorecon--and the choice of lens speed, f/3.5. At the desigh

altitude, about t ft of forward motion are produced during the exposure

time of 1/4000 sec while the vehicle io moving at b,000 ft/sec. This is

. • 1/10 of the basic 60-ft resolution element, and can be tolerated, in fact

ignored, for purposes of photo into retation.
This extremely fast expopuretime makes it possible to ignore forward

image motion; :t also makes it possi • le to i,pore'altitude changes,

probable angular displacements, 7eloe.ty variations, and substantial

variations in film rate.

3. TSB ORBIT

A polar orhtt is preferred, with a firing south from Patrick APB or

from Camp Coolm. A dealgn altitude acceptable to the camera is l8 35

miles. Vaxiatio::s in altitade greater Can .g)ndles would not only affect

scale but result in c. ranges in the orbital period making it difficult to

regulate camera vperat:.ons wit pre-set timing. If the satellite went

mac:1 above 200 milee the broki► .; rocket propellant we: :t would have to be

increased and ;,round resolution would be degraded. If lover altttudea were

used tile sateilLto would encounter texlesirable aerodynamic forces.

The wcic.'A: of the camera and film inetallatton La about 8o pounds. A

tote.: pn7luad we.,-;ht of 300 pounds liss teen selected, leavIng about 220

pounds for pa.f.ead structural zomponenta, re-entry coattnz,brakini;rocket

prow:ant:to, 8,atteri.es to operate the film meennxism, beacon and transponder,

and associated near necessary .o operate t.ie camera and reco%er the package.

IL miz::t be :nosed at tnis point UAL tae power requirement for comers

is conservah:vel: estimated at 100 watt-hours, whica can i.e provided by a

few pounds of Latteries. Te;:le i cemmnrizes payload-stage welghts.

resDect to total time 1 : orbit, a =-day operation is envisaged.

In one (bk. the satellite w1.11 mea.1 about LJ revolutions around t.i.e earth,

GiX or sever of vhich would osr.ra. over the Soviet Union. The camera carries

a 500-foot rtlm load, , we ten will 7.arnit. 300 . exposures at a P.Im speed of

about 2? tic:es per peccr...d. pa.•losA rotates at about 20 revolutions
11/12/5i

10

table 1

Payload Szaue (lb)

Oroup Photographic installaiton 8o

Camera 38

Film 10

Environment. 7

AlLitude Sensor 10

Miscellaneous

Group B 6tructure 110

SAell 30

Fiberglas 80

Group C - Hecovery System 110

Impulse Roczet 65

Tracking Beacon 16

Recovery Beacon 9
per minute, Nith the =era timed to ma.:e an exposure e..ery tt..1rd revolution.

Each exposure viii produce a p:cture covering come 13,060 square miles

on the &Tound. Each pass over the So.-iet Union will cover about 3/4

miflion ever° miles on the ground, or nearly half the total land area of

the Soviet Union. Figure 3 .s a schematic representation of a 1-day

operation.

The b000ter combination proposed for the early reconnaissance satellite

Is the Thor I1 UN! and the secoud stage arVanumard, a small solid

rot:lint, similar to the third stage of Vanguard, to provide a final orbital

increment. T.-.e propulsion is t*::us provided by a liquid-liquid-solid

comblas.:.ion. Table 2 is a summary of vehicle weights.

From a proliniaary structural tzvesti:Azion it appears that the Thor

airframe and its major comoone.tts need not be modified for to satellite

1.11.3aiono T.:.or antopilos and cm-rtrol cyst= can be used for firststage 1,3;:ida.me, alt-ough here IS 3= posanility that t..is aye r.& vou2.d

require Dom: modif:antion :o arrow; .:.he heavier road on th.e rum.: of the

Thor :net in•::•cased load eacent .'Iro.,;ectory. For the

satellite thc Tao: system will not be required..

basic airframe of thc Iaacuard second sae aced not be modified for

Cita appl: hat:. vita ;;ho excentior. at the atz tnterconneet structure,

which will e..e designed to 32-1r.. diameter Vanguard with

tIte ..1.:.eme-;er Thor -Jost 71.o guidance system of the second.-

a zaGe Venu..ard v: _1d be used .:oa,:quction tri t. G.E. (107A) components.

s.: z of Cilia t:1111. Erovever, the

Veto...pm:1 fo. ev.age :R Chare4 : stf. concep:. a:: least, of the type

Table 2

Vehicle We= ht &unary

. Orbital payload 300 lbs

Third stage (solid) 375 lbs

Second stage: (Vanguard 2nd) 4,905 lbs

Initial stage (Thor) 110,910 lbs
11/12/7

14

of solid-propellent roo'set :aeet'.ns, reculremer.ts for satellite under

dftszussion.

pe.ylond-ctaco confieurat'.o.r. ol-faser for t‘af.scase is a double

cor.inal 0:-mpe -a-ith a as dienete.r of 3'3 incheo (see F:s. lb). A

s7r.mictri .:el body was chosen because of the desire:oil-1V of miniratzine

possible aerodFruse.e lift forces -.'ne relattvely b y orY.tal

natorial in assumed to be G.:7;0 .races um alloy coated with a ls.yer

of 7.7..beriAns-pls.stic conb:.r.at'ou .:71 the foriar'd end. for :scat protect4su..

T:-.e 1.r.e..udes a rot about 70 lb of .-yropell.ents.

A typl nal assert traZectory ! PS.G. 'rats povered-escent

tra..:ectory : s effected by to ecabf.:.atf.or of the Thor 'soormer: Vita firststez.:c nreprocrmuned for autopilot, oral sc2ond-stage

:.*.s own :;tre..dar.zo ;-.:r...ttLo-. vitt 4.1-n G..3. red:o system.

The bumont vrI%Ore: ty attained. t. /I IWO boosters 'la 2k,..n(W) ft/sec,

v1 th a tretcht of r.ltout,

After per: • d. of ,:osst to e. defr".;sr. altitude of r.bo...it 200 re.les, the

second state, t:-.e s7rin-lp and separation mezhent= for -the third.

d.:az..7, orients a r d splas the t:ttre .7 4:747: props-rat:cm for tr.c velocity

T..te 2..-01n7ed .:ets t...12 second staGe,

is pite•:1 7.4o 7cat.cle :.s parr-U.-I to tho feart..h's

s-trfane n+. north (or ho-...t.!.) lativide.. After crientat:on, acrd

Le-to-1 thn ,stage ft.res, ta,v. Q.C. t.te 13a-:loaa art op..nt around

roll sale needed. to stab'. l:ze t'. .to -chicle and

provide thr prop -r scan rate f...tr

yf the t.t.rd stec: :7'zt e secon'a steep and

mpart or'' :grunt: M 1217' .) tVrec milt:t rod. to

attaln the proper altitude (dliont 1E0 Si) over -;he 3o%-z-et Union. At thirdstace t.l.c7r4N11,, a small retro--..--- ' separatinc pa, load and
Boost phase Cuant Kick Satellite Orbit

1111•11111MMIIIMMII nn• nn•••••••.... •

n•••••

V - 2ne,300 ft/sec

h - 10,000 ft

7 - 4

AV 1300 ft/sec

h - 1d0 mi

v 15,op 3 rt/ aac

h • .:051,000 ft

y .. 10 •

,

500-laza X . 100 n sl 500 n

Fig. h //scout Trajectury
11/12h7

- 16

leavinG it, properly oriented and spin-stabilized, free in space.

I. Tricking and Recovery

Tracking will be required for essentially three reasons: to determine

the orbit accurately enough for coordination of photographic data; to trigger

the braking rocket at the proper time for the descent; and to establish the

descent path so that the impact point can be located.

The number of trackers required and the spacing between them is

dictated pertly by the guidance accuracy. To insure against guidance

inaccuracies in launching, it is proposed that tmo or three trackers be

used in an arrangement which places them generally with about a 200-mi

separation an a line normal to the orbit.

A second factor that must be considered in determining the number and

spacing of trackers is the deterioration of tracking accuracy at by

angles above the horizon. It is highly important that the satellite pass

ora

close enough to at least one station so that sufficient tracking data can

be obtained at angles of elevation greater than about 20 degrees. For a

nominal satellite altitude of 180 mi, this requires that the satellite

pass vithin roughly 5 degrees of the station, or vithin a ground range of

about 350 mi. Again, two or three trackers at intervals of 200 mi normal

to the orbit are dictated. •

Because the satellite is to be placed on a polar orbit, these

objectives can be net by a small weber of trackers near one of the poles.

It seems advisable to locate the tracking stations, say three of them, at

a high northern latitude such as in Alaska or Canada. Spacing should be

about 200 mi in longitude.

Tracking data would. be in the form of two angles and a range to

permit orbit prediction. The use of range information considerably relaxes
11/12/57

the requirement for angular accuracy. To obtain range, a transponder

in the satellite is required.

Descent from orbit is achieved by the commend firing of a braking

rocket in the satellite. Assume that the satellite is coming over the

pole, that it is picked up by our trackers in the north, and that an

impact point in the Pacific is desired. The braking rocket is then fired

forward and upward, imparting a downward and backward velocity impulse

superimposed on the orbital velocity. The resulting velocity vector

points downward, so that the vehicle is effectively in a ballisti; trajectory comparable to the 'low-angle', i.e., lover-than-optimum, path of

a long-range ballistic missile.

Tracking of the vehicle immediately after the beginning of descent

establishes a predicted vacuum path. This, together with predicted atmospheric effects, makes it possible to predict the approximate impact area.

The vehicle is protected against re-entry heating by a coating of suitable

vaporizing material; 8o ibs of Fiberglas-reinforced plastic, such as that

used an advanced designs of the ICBM nose cone and on-the Jupiter nose

cone, are suggested. Impact survival of the casing, film load, batteries,

and beacon is made feasible by the proper selection and arrangement of

structural components. Search aircraft are used to find and recover the

payload. This means that the radio beacon must operate after water impact,

and possibly that some type of dye marker should be released upon impact.

5. INTELLIGENCE ?MCP'S

Photographs produced by the system just described should enable us

to do a useful reconnaissance job at Level A, over areas measuring millions

of square miles. The scales and resolution that will be possible are

comparable . to those obtained with certain kinds of photographic mapping
11/12/57

equipment standard an Air Force reconnaissance aircraft today. They will

make it possible to identify major railroads, highways, and canals. Urban

centers, industrial areas, airfields, naval facilities, seaport areas,

and the like can be seen. Very likely, defense missile sites of the sort

found around the Moscow area will also be identifiable. Thus, with

repeated surveillance, it will be possible to find new major installationa,

perhaps to learn something about patterns of use of Soviet ICBM systems,

and certainly to obtain clues for the direction of other, higher-resolution

systems that can go beck and take another look.

5. CROWIR PCTOTIAL

Clearly, the major emphasis of this recommendation is on the easiest

and earliest recoverable photographic satellite system. This version,

the 12-in., t/3.5 camera using 500 ft of 5-in. film, and based an the

Thor booster, is seen as the first of a series of such cameras and systems.

This system is capable of photography at Reconnaissance Level A in adegusts detail. As the system is proved out, as confidence is gained in

satellite operations, and as environmental constraints and intelligence

problems become better understood, more advanced systems can be constructed.

The first system would be followed by a 56-in. focal-length system, using

1500 ft of 9-in. film. At this time it appears that this system can also

be put on orbit using a Thor-type booster, with a maximum payload weight

of about 300 lb.

This second system should provide reconnaissance at Level B, giving

adequate detail over areas GI' hundreds of thousands cf square miles. Eventually this system could evolve into one using a 10-ft focal-length lens

and about 2500 ft of 13-in, film, based no longer on the Thor but on the
11/12/57

1)

Atlaa booster, and doing a reconnaissance job at Level C, or over

specific point objectives. The time phasing of the several projects

should be about as follows: availability of the 12-in, system one year

from date of contract; availability of the 56-in. system in 18 months;

and availability of the 10-ft system 36 months after the start of the

program (Pig. 5).

To conclude, it is believed that the type of system proposed here

will mark, can be available quickly, and mill fill a vital military

reconnaissance need both in the near and in the distant future.
•

J..!0" - 4 lo" scule - 75,000

•

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 x J" ocalo - J.A,G00

I; wad - b.J. -

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Thor t yr

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Contritcri, jun • J621.

e . ni Liz si • 1.:111.th I
NRADOUANTINS UNITED VAT AIR PONCE

vmexmaroti 211.

25 November 1957

MEMORANDUM FOR MAJOR GENERAL SWOFFORD, AFDRD

SUBJECT: RAND Recommendation "An Earlier Reconnaissance

Satellite System (S)

General Putt has reviewed the attached report and

commented as follows:

"General Swofford:

"This is one we should start immediately.

Request ORD make recommendations to me as to how

we might proceed. I'd like DRD ideas before any

contact is made with ARDC. Please see me re this.

DLP"

Incl . ERRAND

Rand Rpt on Lt Colonel, USAF

above subj. Assistant Executive

DCS/Development