Performance Analysis Of Multimode Electric Propulsion System For Geostationary Orbit Transfer Mission

Electric propulsion was first envisioned100years ago, and throughout most of the20th century was considered the technology of the future for spacecraft propulsion.In the past20years, with the development of technology, advanced electricpropulsion system (EPS) has past the period while the EPS only operating in somerestricted spacecrafts or being selected as the alternate option, the application ofelectric propulsion has made a continuously extension in space mission.In the applications of space mission, Hall thruster has a most widely applicationand the highest technology readiness level. The application of Hall thruster is veryextensive, such as atmospheric drag compensation, orbital maneuver of spacecraftsoperating in low earth orbit (LEO) and medium earth orbit and medium earth orbit(MEO), orbit injection, north-south and east-west station keeping, deorbit control atthe end of life of geostationary (GEO) satellite and the main propulsion of deepspace probes.Firstly, a comprehensive analysis has been made for requirements of EPS basingon several GEO mission constraints. Systematical study is conducted respectively formission constraints of the near-earth space environment, mission duration and powerlimitation. Analysis has been made for the limitation of LEO-GEO transfer missionapplication of EPS because of these constraints. Assessments of feasibility andnecessity have been made for the application of chemical-electric propulsion in LEO-GEO transfer mission.Secondly, introduction and analysis have been conducted for the structure andprinciple of Hall thruster. Experimental research on the performance characteristicsof a typical Hall thruster has been conducted. A mathematical model suitable forspace missions has been established basing on the data processing. An extensiveperformance experiment has been conducted on a typical Hall thruster. Performancecharacteristics of Hall thruster on different operating points have been obtained.Furthermore, an expected performance boundary of this Hall thruster has been gotafter data processing basing on the several external constraints (power limitation,thrust, specific impulse and efficiency restrictions). Basing on the relationships ofdifferent parameters on the performance boundary, a performance model for Hall thrusters under similar design technique in wide-range power level has been made bynumeral extrapolation.Thirdly, basing on Tsiolkovsky’s rocket equation and theories of EPS, theoreticalresearch has been made for the LEO-GEO transfer based on chemical-electricpropulsion. The general and specific expression of optimal specific impulse (Isp)making the maximum mass of payload have been derived for a mixed propulsionmission. General Analysis has been conducted for the effect of variational parameterson the optimal Isp of EPS. Optimization analysis has been made for the problem incontinuous-thrust transfer between general circular orbits. The optimizationexpression has been derived for the general orbit transfer between initial and targetorbit parameters. The variation of the important orbit parameters in the missionduration has been analyzed by numerical simulation.Finally, on the basis of the previous experiment and theoretical research and thedevelopment tendency of international communication satellite, analysis of a specificLEO-GEO transfer mission has been conducted. Analysis for the orbit transferstrategy and numerical simulation has been conducted under the given initial andtarget mission parameters. The performance parameters conforming to the optimalconditions of the EPS have been acquired...