1. SPACE PROPULSION BASED ON HIGH-BETA MAGNETIC FUSION ROCKET I. V. Romadanov, S. V. Ryzhkov Bauman Moscow State Technical University E-mail: i.v.romadanov@gmail.com

2. Plasma thrusters Engine Trust, mN Specific impulse Isp, s Consumption, kW Weight, kgCountryYear СПД-20050025003…1515Russia1995 СПД-290150033005…3023Russia2000 СПД-2300982500-30002,33,5Russia1997 VASIMR5000 170300USA1979 – at pr. Liquid rocket engine Engine Trust, mN Specific impulse Isp, s Pressure, MPa Weight, kgCountryYear РД-170 740030925 10700 USSR1987-1988 РД-180 3900309 25 5756 Russia1994-1999 РД-701408033030,51 923 USSR1980 SSME19203635,42 2041 USA1977 F-1 69002656,87 8444 USA1959 Fission rocket engine Engine Trust, mN Specific impulse Isp, s Pressure, MPa Weight, kgCountryYear РД-0410 740309250 10700 USSR1957-1978 NERVA 85500-178USA1960-70 Parameters of modern rocket engines

3. The Variable Specific Impulse Magnetoplasma Rocket (VASIMR®) system http://www.adastrarocket.com/Plasma.html VX-200 –Plasma is Ar. Power 10 kW Engine

4. Designs of fusion rocket engine with magnetic confinement AuthorsYearConfigurationSpecific power (kW/kg) Thrust, NSpecific impulse, m/s Bussard et al.1990Riggatron tokamak3.95-7∙10 3 Teller et al.1991Pulse high density1.02.5∙10 5 2∙10 5 Carpenter et al.1994Gas dynamic trap4.0 Nakashima et al.1994FRC1.010 4 Kammash et al.1995Gas dynamic trap7.51.1∙10 5 Stepanov1995ENDVIS, Magnetoplasma fusion device Kukushkin, Rantsev-Kartinov 1996Spheromak Santarius, Logan1998Generic D-T and D- 3 He0.6-10 Williams1998Spherical tokamak Emrich et al.2000Gas dynamic trap1302.2∙10 3 1.4∙10 5 Lee, Slough2001FRC102.5∙10 5 Thio et al.2002MTF505∙10 4 Williams et al.2003Compact torus8.74∙10 4 Cheung et al.2004FRC1.59.61.4∙10 6 Shumlak et al.2006Z-pinch3003-6∙10 5 3.5∙10 6 Chang Dias et al.2009VASIMR, Magnetoplasma5-25 ∙10 3 5-10∙10 3 Gorelenkov et al.2009Spherical tokamak1523.3∙10 5 1.3∙10 6

5. Systems for Space Propulsion

6. Field Reversed Configurations: a) racetrack; b) Hills vortex/sphere, c) elongated Non-uniform FRC equilibria Open-filed lines (DEC) High β (plasma/magnetic pressure) Poloidal magnetic field

7. Distributions for Quasi-Equilibrium 1. Density: 2. Magnetic field: 3. Pressure: 4. Temperature: where U – common coordinate dependent from r and z., where  and M is parameters, which set type of configuration: Hill’s vortex or “racetrack”.

8. Magnetic Systems for Space Propulsion MTF. UAH PRC at Johnson Research Center 2006 W.J.Jr. Emrich. PRC at Marshall Space Flight Center 2007 Gas dynamic mirror fusion propulsion Plasma jets driven magneto-inertial fusion J. Slough. RPPL at UW 2000 The Star Thrust eXperiment Colliding beam fusion reactor space propulsion system A. Cheung. UCI 2004

9. Alternate systems with advanced fuels N. Rostoker et al. US Patent 7439678 (2008) Tri-alpha energy, IEC Bussard Fusion (EMC2 Polywell), General Fusion, LPP and Helionenergy – start up R.W. Bussard. 57 th Int. Astronaut. Congress. IAC 2006 M.G. Laberge. Patent US20060198483A1 (2006) http://www.generalfusion.com/ http://www.emc2fusion.org/General Fusion получили $ М13.9 http://www.lawrencevilleplasmaphysics.com/ Dense Plasma Focus Acoustis MTFPolywell Fusion Colliding Beam Fusion Reactor

10. Mechanism of thrust creation directly exhausting the fuel (the plasma can be used for both propulsion and direct energy conversion) - the advantage of this scheme is the high specific impulse. augmenting the exhaust with material to reduce specific impulse but increase thrust - fusion products mixing with propellant, e.g. hydrogen. strongly confining the plasma, generating heat on the walls, and transferring this heat to a fluid for use as propellant. propellant Thrust propellant

11. Model of Magnetic Fusion Rocket There are two ways to create thrust by the scheme 2. When the mixing chamber is combined with the reactor chamber. When chambers are separated. The first case is shown in Figure 1. Plasma 1 is formed in formation chamber 1. Then plasma is translated into the reactor chamber 3. Reactor chamber combined with mixing chamber. Injectors 5 in the reactor/mixing chamber are injected the hydrogen. Propellant is heated by the reaction products and going through the nozzle 4.

12. RACETA (Rocket As Compact Elongated Toroid Advanced project) Magnetic fusion rocket engine: 1 - reactor chamber; 2 - mixing chamber; 3 - hydrogen injectors; 4 - propellant; 5 - the nozzle; 6 - magnet system; 7 - plasma; 8 - fuel injectors. The another variant of thrust creation is shown in Figure 2. In the reactor chamber, the plasma configuration 7 confined in quasi-equilibrium that is sustained by fuel injection 8. Charged particles (reaction products and fuel) are translated into the mixing chamber 2 with hydrogen injectors 3. Propellant 4 is heated by the reaction products and going through the nozzle 5 and creating thrust.

13. Fuels D + T  n (14.07 MeV) + 4He (3.52 MeV), D + 3He  p (14.68 MeV) + 4He (3.67 MeV), D + D  n (2.45 MeV) + 3He (0.82 MeV), D + D  p (3.02 MeV) + T (1.01 MeV). m 3 /s T, keV

14. Plasma power balance The global plasma power balance is given by: Ratio of the fusion power total losses power for D- 3 He reactor. Ratio of the fusion power total losses power for D-T reactor As seen D- 3 He reactor more powerful then D-T and therein more less the power of loss. This is due to that on D- 3 He reaction more less neutron yield. Where is P f the fusion power, P i is the injection power, P n is the neutron power, P brem is the bremsstrahlung power, P tran is the charged-particle transport power P s is the synchrotron radiation power P t is the thrust power.

15. Conceptual Designs H. Momota, NIFS, 1992. J. Santarius, WISC, 2000. Parameters of RACETA’s reactors, comparison with FRC ParametersD-T RACETAD- 3 He RACETAArtemisFusion Wisc Fuel D-T D- 3 He D-T Specific fusion power P f, MW/m 3 18.214.929,7 12,3 24 24 8,11 Specific power of loss P l, MW/m 3 14,611.93,481,556,476,63 Fuel density n, m -3 1,24∙10 21 1,39∙10 21 1,08∙10 21 7.8∙10 20 5∙10 20 3∙10 20 Temperature T, keV 30 2020 807087.524 Fusion gain factor1,2491,248 99,771,3 Electric power P net, MW525415590670 1000 Magnetic field B, T 10 5 772,4 Beta 0,70,90,70,9 0,8

16. Cooperative Hybrid Systems - TMs and CTs One of the modern project, combined two systems: FRC and TM or GDM.

17. Conclusions RACETA’s (Rocket As Compact Elongated Toroid Advanced project) engine scheme was proposed. Mechanism of trust creation by heating injected propellant for magnetic fusion engine for this scheme was suggested. 2 schemes (reactor and reactor-mixing chamber) are considered Main parameters of reactor for magnetic fusion rocket were calculated. Comparison of D-T, D- 3 He FRC and DFP are presented. System with high beta and direct energy conversion can be used for open space purposes. Parameters of RACETA engine Parameter FuelD-TD– 3 He Temperature T, keV2070 Fuel density n, m -3 10 21 3∙10 20 Hydrogen flow, kg/s0,40,5 Specific impulse, m/s2280048120 Trust, Н 912024060