Documents / Official release
This Defense Intelligence Reference Document, prepared in fiscal year 2010 by the Defense Intelligence Agency's Defense Warning Office under the Advanced Aerospace Weapon System Applications (AAWSA) Program, reviews aneutronic fusion as a way to propel spacecraft. It compares chemical, ion, fission, fusion and antimatter propulsion, and it also covers radiation shielding and relativistic rocket calculations. It looks at research needs over the next 30 years for missions from low Earth orbit to Mars, Jupiter and Alpha Centauri.
From the source:Release of 2026-09-18 Incident: 11/1/10, Las Vegas, Nevada. Released with redactions. This document is a Defense Intelligence Reference Document (DIRD), a technical reference format used by the Defense Intelligence Agency (DIA) to capture baseline knowledge on a specific topic for later analytic use. DIRDs are best understood as reference and synthesis products rather than as original research. It is one of 38 DIRDs produced under the Advanced Aerospace Weapon System Applications Program (AAWSAP) between 2009 and 2011. Because AAWSAP’s scope permitted a broad range of supporting topics, not every DIRD in the series directly concerns aerospace systems or future threat assessment. The following summary reflects the DIRD’s scope and framing at the time of writing and should not be read as implying current validation of the concepts discussed. This DIRD surveys aneutronic fusion as a possible advanced space-propulsion method, focusing on fusion reactions that release most of their energy in charged particles rather than neutrons and therefore offer potential advantages over more neutron-intensive fusion concepts, especially in radiation shielding, direct energy conversion, and thrust generation. The report reviews the underlying rocket physics, compares candidate fusion fuels and ignition conditions, and gives particular attention to proton-boron and related schemes, while also discussing Bussard’s concepts and other fusion projects as representative development paths. It also makes clear that the central obstacle remains ignition and sustained net-energy fusion under practical conditions, and it notes additional problems such as x-ray energy losses from the hot plasma, extreme temperature requirements, and the gap between theoretical specific impulse and what proposed systems had demonstrated experimentally. Overall, the document presents aneutronic fusion propulsion as an attractive long-range concept for deep-space travel, but one whose practical realization still depended on major unresolved advances in fusion engineering.
UNCLASSIFIED//POR. Offl@IAI:: ~S& Qptk\f shorter trips to the stars. Figure 14 shows how much time is required for the trip (one way) based on the required acceleration. These equations are independent of the specific impulse of the rocket. The mission cannot be less than 4.22 years in duration, since the spacecraft cannot exceed the speed of light. If a 10-year mission were chosen, the fuel usage would be tremendous, but the vehicle could attain an acceleration of 0.20 g. At this acceleration, t ime on the rocket would pass at 72% of the rate of time on Earth. To predict the amount of fuel required for the ideal fusion drive, the Bussard Aneutronic Propu lsion system, weighing 14 tons, is assumed to be coupled to a craft the same mass as the International Space Station. By assuming a very gradual acceleration of 0.001 g, the trip will take about 127 years attaining a maximum velocity of 6.5% of the speed of light. Even at this modest acceleration, 85% of the initial mass of the spacecraft will have to be fuel/propellant. The Mathcad spreadsheet used to pred ict these values is included in Appendix D as the "Relativistic Rocket Worksheet." Figure 15 shows the openi ng page of the worksheet. Any text in red can be modified to predict performance wit h different drives, vehicle mass, or distance tra veled. Relatlvlstlc Rocket calculator Maximum Velocity as aFunction of Fuel Consumption Value!> m Rt-d May be Ch~nged by :he Uwr A. Defi ne the Mass of the Rocket and the Engine 1. Pav load Mass I 370,000 (kg) 1 2. Engine and Fuel Mass 12,700 (kg ) 0.9 3. Total ~ocke1 Mass 382700 (kg) O.ll I I ~ 0.7 8. Define the Specific Impuls e of t he Engine -s 1. Sp ecific Impulse I .3639143.731 (sl .S'! 0.6 ::: 2. 1,,jc I I 0.119 ~ 0.5 I I E 0.4 /C. Defin e the Distance to th e Star j 0.3 l . Dist ance I 4.22 llghtveaa ) ~ 0.2 2. Dist ance I 3.99246EH 6 (m) ---0.1 I I D. Defi ne the Max imu m Accele rati on 0 l . Acce lerati on/g I O.OOJ 0 0.1 0.2 0.3 o.• 0.5 0.6 0.7 O.ll 0.9 1 2. Accelerat ion I 0.00981 (m/ s' ) 6m/minltill I I Acceleration and Rocket Time versus Earth Time E. Co mpute the Tim e Required for the M issi on l 1. Mi ssion Time (Earth nme } 4036935068 (s) = 128.0104 (years) 12. Mission nme (Rocket nme)I 4034009639 (s) = 127.9176 (vears 0.9 I I la ~-F. Calculate the Velodtv at the Midpoint V .,. 1. Ve locity at M id point ( m/s) 'a'.7 /19758174.9 ::, - troc ke tearth I 2. Ve locitv/c I 6.6% i 6 I I I , 5 G. Calculate the Energy Re quired .. \-a. 1. Lorentz Factor I 1.002175889 .2 I \ 12. EnerllV from Fuel I L49888E•20 (J) ! 1 \H. Calculate the Mass o f Fuel Re oul red l 2 l. De ll a-V I 19758174.9 ( m/s) ., I'..0.1 -2. Mass Rati o (flnal/init ial ) L 74E.OO I 3. Fi nal Mass I 2.20E-+-05 (kg) 0 4. Mass of Fu el Consumed 3.26E>-05 (kg) 0 5 10 15 20 25 30 35 40 45 50 5. Fue l Mass/ lnltl al Rocket Mass 85.1% Eilrtti Time lyrl Figure 15. Sprea dsheet for Sample Mission to Alpha Centauri. 34 UNCLASSIFI ED/ fF&A &FFI€il.t.k W&& Qptk\f
Not linked to a story yet.
Official release, from the pursue 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.