Volume 36, Number 4, August 2018
|Page(s)||618 - 626|
|Published online||24 October 2018|
Hybrid Low Thrust Propulsion Trajectory Design and Optimization Using Virtual Gravity Method
School of Aerospace, Northwestern Polytechnical University, Xi’an 710072, China
2 Research & Development Institute of Northwestern Polytechnical University in Shenzhen, Shenzhen 518057, China
3 Shanghai Aerospace System Engineering Research Institute, Shanghai 201109, China
4 National Astronautical Observation, CAS Space Debris Observation and Application Center, CNSA 100012, China
a novel spacecraft trajectory design method using hybrid low thrust system is proposed in this paper. The hybrid system is constituted with a solar sail propulsion thruster and a solar electric propulsion thruster. In proposed method, the former one provides radical thrust and circumferential thrust to from a virtual gravity, while the later one provides a tangential thrust. In this way, the spacecraft is virtually motioned by constant tangential thrust in a virtual gravity field. Using proposed method, the thrusting trajectory can be parameterized, and a large number of feasible trajectories for circle to circle rendezvous problem can be obtained. To the end the steering law to minimize the fuel cost is found using Matlab optimization tools Fmicon function, and the result is compared with traditional pure solar electric propulsion method in terms of payload mass fraction. The simulation results show that the proposed method can reduced propellant consumption significantly compared with the pure SEP system.
Key words: continuous low thrust / MATLAB / parameterization, solar sail/solar electric propulsion / orbital rendezvous / trajectory optimization
关键字 : 连续小推力 / 太阳帆/电推进混合推进 / 轨道转移 / 轨道优化
© 2018 Journal of Northwestern Polytechnical University. All rights reserved.
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