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Defense Intelligence Reference Document Space Access Where We ve Been And Where We Could Go

Defense Intelligence Agency · 56 pages · text from the file's own layer

This Defense Intelligence Reference Document, prepared by the Defense Intelligence Agency and dated 8 March 2010, was produced under the Advanced Aerospace Weapon System Applications (AAWSA) Program. It gives a historical and technical review of how to reach space and return. It covers hypersonic gliders, air-breathing and rocket propulsion, thermodynamics and materials, and launch options. It argues that reliable, schedulable access to low Earth orbit is mainly a hardware and propulsion problem rather than a technology one.

  • p. 2 …FY 2009 Advanced Aerospace uestions pertaining to AAWSA Program Bldg 6000, Washington, under the Defense Intelligence…
  • p. 5 …Among the many advances in space access that will be possible in the future,' the key…
  • p. 10 UNCLASSIFIED/,Sf81il 8ffll!ltllt ~!II!! SHLY McDonnell Aircraft Advanced Design Dept. 1958 to 1967 Mr. H…
  • p. 11 …Louis) Advanced Design organization. The vehicle concept initially conceived in the late 1950s and early 1960s…
  • p. 23 …The photo in Figure 16 is from a Society of Automotive Engineers book titled Advanced Engine…
  • p. 30 …to advance beyond a demonstration tube ended in frustration. Any attempt to open the tube results…
  • p. 32 …Propulsion The photo in Figure 27 is from the Society of Automotive Engineers book, Advanced Engine…
  • p. 38 …These solution areas represent the entire propulsion spectrum, from all-rocket (far right) to advanced air…
  • p. 39 …the launcher can return with payload and fuel residuals onboard), use legacy correlations from McDonnell Advanced…
  • p. 45 …why have we advanced so little (as illustrated in Figure 43)? Like the pioneers' Conestoga wagons…
  • p. 47 …to advance beyond a solitary orbital station with limited capabilities. Figure 44 identifies the elements necessary…
  • p. 56 …6 KOchemann, D., "The Aerodynamic Design of Aircraft - A Detailed Introduction to the Current Aerodynamic Knowledge…
UNCLASSIFIED/ /FSA: SFFlil.t.k 'l!ilE 8HLV
Figure 18, radiation equilibrium skin temperature is the skin temperature that results
when the radiated thermal energy stemming from the skin temperature equals the
input aerodynamic heating minus any conduction into the airframe.
1,000°F--
"4,300'F _/
ALE :0,5 In.
1,000°F\
1,200° F \
1,500"F ·~\
.. *6,40Q°F
900'F
900° F
800°F-
\~
~2,200'F
"3,800' F
RL[ = 1.6 in.
1,000"F-
RN= 0.5 in. /'
f:0.7 _/ \2,500'F J2,400°F
2.600°F-
- - 1,2oo·F-
\_2300°F
' \__ 2,200" F
2,400°F-
Upper
Surface
I
I
I
'Lower
Surface
L2.4oo•F
Figure 18. FDL-7C/D, Model 176 Entry Temperature Distribution. Upper-surface heating is minimized by
cross-section geometry.
Figure 19 is a thermographic phosphor
image of the model in Figure 17 at a 12-
degree angle of attack (maximum L/D
ratio) at mach 12. Even at mach 12,
there are vortices embedded in the
boundary layer. The three black dots are
heat transfer gauges that were used to
establish the value for qredn Figure 19.
The stagnation heat transfer was 25
times the reference value. This
technique, when calibrated with the
reference heat transfer gauges, provided
a rapid and accurate means to determine
heat transfer distributions with a
minimum of installed gauges. The
technique was adopted by other wind
tunnel facilities, including the Arnold
Engineering Development Center at
Tullahoma, Tennessee.
19
COHOOUS> OF
Figure 19. Even at Mach 12, Embedded Vortices in
the Boundary Layer Alter the Local Heat Transfer
UNCLASSIFIED/ ,u;sa SFFIGIPL IP&'i SIik¥

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Report, from the dia collection. The PDF is mirrored here; the original link is above. 56 pages are in the text index: search them above, or from the library's search.