John Slough could have an experiment in 2012 with a net gain in fusion energy of 1.6. It will be an imploding liner experiment. For space propulsion he is targeting a 200 times gain in energy output from what is input. Mission profiles are for 30 day or 90 day missions to Mars with over 5000 ISP.
* Lowest mass fusion system is realized with FRC (Field Reversed Configuration) compressed by convergent array of magnetically driven metal foils - steps (a), (b)
*Fusion neutron and particle energy is directly transferred to the encapsulating, thick metal blanket - step (c)
−Provides spacecraft isolation from fusion process
−Eliminates need for large radiator mass
* Expansion of hot, ionized propellant in magnetic nozzle - step (d)
−Produces high thrust at optimal Isp
Fusions Assumption:
• Ionization cost is 75 MJ/kg
• Coupling Efficiency to liner is 50%
• Thrust conversation ~ 90%
• Realistic liner mass are 0.28 kg to 0.41 kg
• Corresponds to a Gain of 50 to 500
• Ignition Factor of 5
• Safety margin of 2: GF =GF(calc.)/2
Mission Assumptions:
• Mass of Payload= 61 mT
• Habitat 31 mT
• Aeroshell 16 mT
• Descent System 14 mT
• Specific Mass of capacitors ~ 1 J/kg
• Specific Mass of Solar Electric Panels 200 W/kg
• Tankage fraction of 10% (tanks, structure, radiator, etc.)
• Payload mass fraction =Play load Mass
• System Specific Mass = Dry Mass/SEP (kg/kW)
• Analysis for single transit optimal transit to Mars
• Full propulsive braking for Mar Capture - no aerobraking
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