Defense Intelligence Reference Document Positron Aerospace Propulsion

Defense Intelligence Agency · 35 pages · text from the file's own layer

This unclassified Defense Intelligence Reference Document from the Defense Intelligence Agency is dated 2 March 2010. It was produced in FY 2009 under the Advanced Aerospace Weapon System Applications (AAWSA) Program. The report reviews work on using positrons as aerospace fuel. It covers air-breathing turbojet and ramjet engines, unmanned aircraft, missiles, single-stage reusable vehicles, positron rockets and a crewed Mars mission, along with how positrons could be produced and stored. It concludes that a first positron-powered flight around the globe could be possible within 10 years.

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“Masse”17 pages

p. 3 …Positron Mass .................................................................. 5 Figure 7. LOCAAS Turbojet Engine ......................................................................... 6 iii UNCLASSIFIED//F81it 8FFIIIAI!: 1!181! &••1…
p. 4 …Total Positron Requirement for SSRV With a Dry Mass of 60,500 kg ....... 10 Table 4…
p. 6 …Hence, when Ps self-annihilates, there is 100 percent conversion of mass into electromagnetic energy given…
p. 7 …5 At sea level for a fuel-air mass ratio of 0.068, it is 500…
p. 10 …1.00 Positron Mass (mg) ./V 1.50 Figure 6. UAV Range Versus Positron Mass (courtesy…
p. 12 …nonstop flights are possible. • Increase in structural mass allows more electronics/passenger amenities. RAMJET-ASSISTED MISSILE…
p. 13 …Improving payload mass requires reducing propellant and structural mass, both of which can be accomplished using…
p. 14 …GLOW for Chemical SSRV21 Vehicle Component Structure Thermal Protection Propulsion (4 engines) Electronics TOTAL DRY MASS…
p. 15 …24 The positron mass budget for a 60,500-kg dry mass for ascension to LEO…
p. 17 …First, a reduction in the engine mass for a given thrust is realized; second, there is…
p. 19 …lead-cartridge concepts show promise if the mass flow rate of the hydrogen propellant exceeds that…
p. 20 …flow-through system with LH2 at higher mass flow rates than LXe; and (d) One-fluid…
p. 21 …A separate Brayton-cycle positron energy conversion system provides power to the pellet mass driver and…
p. 22 …Comparison of Three Positron Propulsion Concepts for Mars Mission lsp Thrust e+ mass Special Notes Solid…
p. 24 …On board propellant requires an overall interplanetary system mass that prohibits use of any type of…
p. 25 …This gives significant mass savings or an equivalent reduction in Mars-to-Earth return time for…
p. 26 …Mars reference mission 53 , 54 considered payload masses of 60,000 kg for 2015 missions. This…

UNCLASSIFIED/ ,'F811. 8FFll!l*L 1!1!11! t!IIU:!Y
,000
!cc1530sec
v = 7600 msec.140 km
t .. 146sec
M = 1 8. 10000m
0, 1 J I
t=1200sec
M = 8, 38 km
I
I ---- J
I
I
Time
''1500 SC'C
Figure 9. Positron SSRV Flight Profile (courtesy Positronics Research LLC) 23
1 = 1650 sec
300km
The SSRV takes off horizontally (Figure 9) from Edwards Air Force Base, accelerates to
mach 1.8 as a turbojet, and then goes to the ramjet mode. At mach 8 the rocket is
ignited and takes the vehicle into LEO. 24 The positron mass budget for a 60,500-kg dry
mass for ascension to LEO is 86.9 mg (Table 3).
Table 3. Total Positron Requirement for SSRV With a Dry Mass of 60,500 kg 25
Mission Mode
Turbojet - Launch
Ramjet
10% margin (turbojet mode upon
landing, inclination changes, etc.)
TOTAL
Mass Of e!
2.5 mg
76.5 mg
7.9 mg
86.9 mg
An artist's rendition of the SSRV is provided in Figure 10.
10
UNCLASSIFIED/ ,'F811. 8FFll!l*L 1!181! 811L¥

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Report, from the dia collection. The PDF is mirrored here; the original link is under it. 35 pages are in the text index: search them above, or from the library's search.