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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.
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- p. 3 …Positron Mass .................................................................. 5
Figure 7. LOCAAS Turbojet Engine ......................................................................... 6
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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…
Electric Motor
Or11en
Compressor
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Concentric Annular Tungsten Heating
Curfaces Transfer Position Con,ersion
Heat Energ:, To Airflow
Turbine PoNered Electrical
Generator 1s Power Gou1ce
For Positron Ttap and Electric
Motor for Corrμresscr
~,haLJst
Position
Trap
Intake
Airflow
Compressor and turbine can be feathered to convert
tu1bo Jet to ramjet
Heated Arr expands thru
turbine and nozzle
Positron Conversion
Cha111be1
Figure 4. Details of the PTRE Engine (courtesy Positronics Research LLC) 12
A comparison with the combustion turbo-ramjet engine (Figure 5) shows that volume
used for combustion heating is used by PTREs for convection heating.
lurbojet
combust on chamber no77te
turho1et ramjet fuel inje.::ors
corn:xessor
turbojet
turbine ronJel combust1cn
chamber
Figure 5, Combustion Turbo-Ramjet {courtesy Positronics Research LLC)n
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About this file
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.