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This Defense Intelligence Reference Document, dated 1 November 2010, was produced by the Defense Intelligence Agency under its Advanced Aerospace Weapon System Applications (AAWSA) Program. It surveys propulsion technologies that include chemical, ion, and nuclear fission rockets, fusion schemes, aneutronic fusion, and antimatter propulsion. It also covers radiation shielding and speculates on research needs over the next 30 years for missions from low Earth orbit to Mars, Jupiter, Saturn, and Alpha Centauri. The document concludes that aneutronic fusion promises to be an important mechanism for future space propulsion.
UNCLASSIFIED/ /P91il 8PPll!ltllt '11815 8HL\f ry =(Thrust)= I_ Power V,, (LS) In choosing a rocket engine, as the specific impulse (Isp) or the exhaust velocity (Ve) increase, the corresponding efficiency (ry) decreases. The specific impulse for various fuels varies widely as shown in Table 1. 2, 3 Tsiolkovsky Rocket Equation For a spaceflight to Mars or other body, the exhaust velocity affects the time of flight and the amount of fuel that is needed to change the velocity of the spacecraft. The change in velocity (i'N) can be expressed in terms of the initial mass of the rocket (m;nitiat, rocket+ propellant) and the final total rocket mass (mrma1 rocket only): t, V = V In ( 111"'""'')n/r,11111 111 /111(1/ (L9) The mass of propellant used to generate thrust is given by: m1,, 0pdlam = 11111111ial - Jn /i1111/ (LlO) 1.\/! v,,,lwus/ T K,, ,&g,, (Lll) n' In e ,:i \i l\/,.,1,a,,<t J11wl = rn,wil (1.12) (L13) (1.14) In these equations, R is the thrust-to-weight ratio and t is the time required for an engine burn to produce a desired tN. These are the standard equations used for rocket engine performance. 4 UNCLASSIFIED//FQR QFFU!IAle 1!181! 9HE I
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Report, from the dia collection. The PDF is mirrored here; the original link is above. 50 pages are in the text index: search them above, or from the library's search.