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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.
“Masse”17 pages
- p. 3 …Positron Mass .................................................................. 5
Figure 7. LOCAAS Turbojet Engine ......................................................................... 6
iii
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- 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…
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LN2 or Ne
(a)
(b)
(c)
H2
P<»itronTrap
Pb ENCASED e+
(d)
Figure 12. Fluid Systems. (a) One-fluid system of LN7 or Ne propellant; (b) Two-fluid system of LH, and LXe; (c)
Two-fluid flow-through system with LH2 at higher mass flow rates than LXe; and (d) One-fluid LH2 system with lead
encapsulated Ps (courtesy Positronics Research LLC) 36
15
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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.