DIRD_30-DIRD_Aneutronic_Fusion_Propulsion.pdf

UNCLASSIFIED / 502. @6EIGhHE-USE-ONEt Defense Intelligence Reference Document S(t efense Futures 01 Novernber 2010 ICOD: 20 July 2010 DIA-08-101 1-003 Aneutronic Fusion Propulsion UNCLASSIFIED / 2@R-OPERCERE USE ONLY

UNCLASSIFIED / / F-@R-@FEtGEAL-USE-ONES Aneutronic Fusion Propulsion The Defense Intelligence Reference Document provides nonsubstantive but authoritative reference information related to intelligence topics or methodologies. Prepared by: (b)(3):10 USC 424 Author: (b)(6) Administrative Notes: (U) COPYRIGHT WARNING: Further dissemination of the photographs in this publication is not authorized. This product is one in_a_serles of advanced technology reports produced in FY 2010 under the Defense Intelligence Agency, |(b)(3):10 USC 424 Advanced Aerospace Weapon System Applications (AAWSA) Program.…

UNCLASSIFIED / / B@R.@EELGEAHDSE BAe Contents INtrOCGUCtiON ....cscesessesseensesenasneeneansereeen saa nenaneuananenanas euanenenenanavenenenens wa vaeeseuauapeuansuenenens v Chapter 1: Theory .....cccserscurees vareravaveceuse vuvevever eveneserers vavevesenureeusususesesns avevevereveres wel Rocket Propulsion ..scssessnsenseee eeaue en snanaseanscananeuanecanauanenanecen a eanenauanenaeaceuenansneneuauanen 1 Comparison of Specific Impulse for Various Rocket DeSIGnS .......0cscssccsesevecerureses 5 Radiation Shielding .......cscsccesscceccerassssceenscenens ne wasanenenenanenes sua nenenecen…

UNCLASSIFIED / S2OR-@FFIGEEUSE-ONET LEO to the Moons of Jupiter and Saturn (460 to 940 million miles)...........00. 28 LEO to Alpha Centauri (4.22 light-years or 24.8 trillion Miles) ...cscrsssnenenensnerenes 2B Chapter 7: Conclusions... .cccsssscsccceereeneeeceeueeedeuvucnesereeusnesonenenennsenenecesgsennenseenenaeecenes 2D Appendix A: Relativistic ROCKetS ...c.cssscvcserencnesare cane nanensnensnananen snanenenananenereseneasnssas OO Appendix B: Aneutronic Fusion Rocket ....ccccssesscessenensnsneneeansneeneenaesenezeseauccseeeonneaes 32 Appendix C: Antimatter Annihilation RoOCKet....c.cscss…

UNCLASSIFIED/ / F@®-@552GEL-YSE-ON ES Tables Table 1: Specific Impulse for Various Rocket Engine Types .........s00sscessssssensees 3 Table 2: Rest Mass of Various Subatomic Particles ........ccsccssscssecusecusseesaseeeeues 10 Table 3: Specific Impulse for Selected Drives ............cccsccssseueseensesecneceseeeeneeens 35 iv UNCLASSIFIED / /5@R-@EFIGHH=USEONEY

UNCLASSIFIED / / POR OPPECERE USE ONnTY Aneutronic Fusion Propulsion Introduction Space exploration is limited by existing propulsion technology. Up to now, chemical rockets have been used to reach low-Earth orbit, the Moon, and the outer regions of the solar system. Chemical rockets can use either solid or liquid fuel. Regardless of the type of fuel, their design is similar to that shown in Figure 1. Oxygen is combined with hydrogen or a hydrocarbon fuel in a combustion chamber where high temperatures and pressures cause the exhaust to be ejected through a supersonic nozzle to provide thrust …

UNCLASSIFIED / /POROPPReRE Ser one space ship, and there is a high probability that neutrons produced by fusion reactors would escape into space without providing much of their energy to a hydrogen propellant. Other fusion reactions using isotopes of helium and lithium will generate only charged particles, such as protons, that travel very short distances before giving up all of their energy as heat. These "aneutronic fusion” reactions take place without neutron production and decrease the need to carry large amounts of radiation shielding material for the crew. The energy from charged particl…

UNCLASSIFIED / /®6R-@FFEGEA-UGE-ONE Chapter 1: Theory ROCKET PROPULSION It is difficult to compare propulsion technology without talking about how objects are accelerated in space. Within Earth’s atmosphere, aircraft use the air to generate lift and thrust. Propellers or turbofans move a mass of air rearward and Newton’s second and third laws require that the momentum in this exhausted air is equal to a thrust in ~ the opposite direction. In equation form, the thrust, F, is equal and opposite to the change in momentum over time. F- _ alm V) rans (1 . 1) at The momentum of the exhausted air is …