Tangent-impulse transfer from elliptic orbit to an excess velocity vector  

作　　者：Zhang Gang Zhang Xiangyu Cao Xibin 

机构地区：[1]Research Center of Satellite Technology, Harbin Institute of Technology [2]National and Local United Engineering Research Center of Small Satellite Technology

出　　处：《Chinese Journal of Aeronautics》2014年第3期577-583,共7页中国航空学报（英文版）

基　　金：supported in part by the China Postdoctoral Science Foundation funded project (No. 2012M520753);the Fundamental Research Funds for the Central Universities (No. HIT.NSRIF.2014307);the Open Fund of National Defense Key Discipline Laboratory of Micro-Spacecraft Technology (No. HIT.KLOF.MST.201303)

摘　　要：The two-body orbital transfer problem from an elliptic parking orbit to an excess veloc-ity vector with the tangent impulse is studied. The direction of the impulse is constrained to be aligned with the velocity vector, then speed changes are enough to nullify the relative velocity. First, if one tangent impulse is used, the transfer orbit is obtained by solving a single-variable function about the true anomaly of the initial orbit. For the initial circular orbit, the closed-form solution is derived. For the initial elliptic orbit, the discontinuous point is solved, then the initial true anomaly is obtained by a numerical iterative approach; moreover, an alternative method is proposed to avoid the singularity. There is only one solution for one-tangent-impulse escape trajectory. Then, based on the one-tangent-impulse solution, the minimum-energy multi-tangent-impulse escape trajectory is obtained by a numerical optimization algorithm, e.g., the genetic method. Finally, several examples are provided to validate the proposed method. The numerical results show that the minimum-energy multi-tangent-impulse escape trajectory is the same as the one-tangent-impulse trajectory.The two-body orbital transfer problem from an elliptic parking orbit to an excess veloc-ity vector with the tangent impulse is studied. The direction of the impulse is constrained to be aligned with the velocity vector, then speed changes are enough to nullify the relative velocity. First, if one tangent impulse is used, the transfer orbit is obtained by solving a single-variable function about the true anomaly of the initial orbit. For the initial circular orbit, the closed-form solution is derived. For the initial elliptic orbit, the discontinuous point is solved, then the initial true anomaly is obtained by a numerical iterative approach; moreover, an alternative method is proposed to avoid the singularity. There is only one solution for one-tangent-impulse escape trajectory. Then, based on the one-tangent-impulse solution, the minimum-energy multi-tangent-impulse escape trajectory is obtained by a numerical optimization algorithm, e.g., the genetic method. Finally, several examples are provided to validate the proposed method. The numerical results show that the minimum-energy multi-tangent-impulse escape trajectory is the same as the one-tangent-impulse trajectory.

关 键 词：Elliptic orbit Escape trajectory Excess velocity vector Orbital transfer Tangent impulse 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]