ADVANCED AERODYNAMIC RECONNAISSANCE SYSTEMS A COMPARATIVE ANALYSIS OF QUICK REACTION-SURVIVABLE SYSTEM CONCEPTS

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP71B00822R000200140015-6
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 5
• Document Creation Date: December 15, 2016
• Document Release Date: September 4, 2003
• Sequence Number: 15
• Publication Date: April 21, 1969
• Content Type: REQ

Approved For EW4ease 2003/09/30: CIA-RDP71 800822,00200140015-6
ADVANCED AERODYNAMIC RECONNAISSANCE SYSTEMS
A COMPARATIVE ANALYSIS
OF
QUICK REACTION-SURVIVABLE SYSTEM CONCEPTS
21 April 1969
NRO review(s) completed.
Approved For Release 2003/09/30 : CIA-RDP71 B00822R000200140015-6
 Approved FoQelease 2003/09/30 : CIA-RDP71 8008000200140015-6
A. OBJECTIVES
proposes to conduct a two-phase
study of quick reaction-survivable reconnaissance systems which wi:l
provide In Phase I - the synthesis and comparative evaluation of an
appropriate number of candidate vehicle system concepts which are cap-
able of accomplishing a penetration through techniques (profiles ard
tactics) to be defined by the sponsor. The interactions of specific
operational requirements and constraints with several candidate system
designs will be systematically evaluated. A rating of all candidate
systems will be established.
In Phase II - a refinement of the selected reconnaissance system(E)
to amplify analysis of crucial areas and define technology status,
provide specific definition of major subsystems in cooperation with
qualified suppliers, and provide a consolidated system definition &.nd
technical substantiation, including capabilities for alternate opera-
tional uses.
B. SCHEDULE
The Phase I study will be completed in six months. The last Two
months of this phase would be characterized by intensive review by the
sponsor and iterative analysis
to validate those items which
have major impact on the comparative rating of competing quick reactior.-
survivable vehicle system concepts.
The Phase II study would be initiated approximately one month
after completion of the Phase I study. Its duration would be six months,
completing the in-depth definition of the most promising reconnaissance
system concept(s) identified in Phase I.
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C. APPROACH - PHASE I
Rapid identification of candidate flight vehicle concepts wh:.ch
can provide the flight profile and tactics defined by the sponsor is
to the complete aerodynamic flight spectrum. After definition of
./Z,
conceptual baseline vehicle systems ae-,completed, a comprehensiv,=
synthesis of complete systems will be accomplished, including major
subsystems. It is expected that a comprehensive matrix of compet:_ng
vehicle system concepts will be established to achieve the desired
flight profiles. The complete flight spectrum -- including high
supersonic to oa-7,4hyperson:ic velocities, can be assessed through
synthesis of realistic and practical vehicle concepts. Past work
provides a ready source of key technical building blocks which can be
substantiated in depth. For each specific vehicle concept, major tech-
nical element requirements which will be considered in achieving
balanced system design include:
a) Takeoff/boost propulsion system
b) Propellant system
c) Vehicle structural concept
d) Aerodynamic shape
e) Payload installation requirements
f) Propulsion mixes/staging
g) Vehicle recovery system
h) Flight control system - manned/unmanned options
Performance objectives, including flight profile requirements
such as range, flight profile variability, navigational accuracy, and
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maneuver capability, will be established for each candidate system
in conjunction with the sponsor.
Each candidate system will be established as a balanced design
in appropriate depth to permit, determination of system costs (de-
velopment, investment, and operating).
of each vehicle system to accomplish alternate missions.
The comparative vehicle evaluation will include assessment cf
the design impact of operational factors such as:
o Reaction time for tee- readiness postures
o Turnaround capability
o Basing requirements
o Data retrieval options
o Unmanned/manned options
Design options will be dependent upon the flight profile obj c-
tives, but major interactions expected to be appropriate for anal.rsis
are:
o Reaction time
o Radar cross section
o Vehicle launch alternates
o Vulnerability/Survivability
o Integral power vs. expendables
o Landing aids, including thrust augmentation
o Conceptual sensor alternates
o ECM alternates
o Communication links
o Payload variations
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Factors to be considered in ranking candidate systems will
include:
o Capability to achieve desired flight profiles and tactics
o Mission frequency
o Mission versatility
o Turnaround time
o Reliability/mission confidence
o Development time span
o Development cost
o Investment cost
o Operating cost
o Overall data collection system capability
o Collection confidence
A key feature of the approach used in this program will be a
disciplined approach to consolidate many diverse design and opera-
tional elements. While emphasis on key and/or critical design anc.
operational elements (range, survivability, reaction time, etc.) rill
be necessary, full visibility to all those elements having a stras.g
influence on the quality (mission and collection confidence, etc.; of
the system concepts is also necessary to achieve credible and conrpletE
results of primary use to decision makers. In other words, an ob,aec-
tive and practical evaluation, predicated upon satisfying critical
1,1 Crl
e7zaluationswill be accomplished.
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