NDLI: A multi-impulse extended method for low-thrust trajectory optimization

Content Provider	IEEE Xplore Digital Library
Author	Jiang Xiao-yong Lian Yi-jun Zhang Hong-bo Tang Guo-jian
Copyright Year	2013
Description	Author affiliation: Coll. of Aerosp. Sci. & Eng., Nat. Univ. of Defense Technol., Changsha, China (Jiang Xiao-yong; Lian Yi-jun; Zhang Hong-bo; Tang Guo-jian)
Abstract	The low-thrust trajectory optimization is replaced by a multi-impulse one. After the multi-impulse trajectory was obtained by solving a nonlinear programming problem, the multi-impulse is extended directly to the low-thrust by Q-guidance. Starting with the first segment of the multi-impulse trajectory, the thrust direction is set to consist with the impulse direction. The thrust magnitude is at its maximum. By propagating the initial state with the thrust for 1.0 day, the state of the spacecraft will update to a new one. A new impulse is obtained by solving the Lambert's problem between the new state and the final state. The process is then repeated until the impulse reduces to zero. Finally, the multi-impulse trajectory is converted to the low-thrust one by applying this process to all the other segments. Numerical results for two rendezvous missions fully validate the availability and efficiency of the Multi-Impulse Extended method.
Sponsorship	IEEE Aerosp. Electron. Syst. Soc.
Starting Page	365
Ending Page	368
File Size	685054
Page Count	4
File Format	PDF
ISBN	9781467363952
e-ISBN	9781467363969
DOI	10.1109/RAST.2013.6581233
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2013-06-12
Publisher Place	Turkey
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Space vehicles Earth multi-impulse Venus Propulsion Vectors trajectory optimization Trajectory low-thrust Lambert's problem Optimization
Content Type	Text
Resource Type	Article

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