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Glidescope Orbit Design Based on the Differential Equation Approach in Near-Range Autonomous Rendezvous Mission

LIU Luhua1, HAN Hongwei2

1. College of Astronautical & Material Engineering, National University of Defense Technology, Changsha 410073, China;
2. The 61081 Unit of PLA，61081 unit，Beijing 100094，China

Received:1900-01-01 Revised:1900-01-01 Online:2009-06-26 Published:2009-06-26

Abstract

Abstract: Considering constraints of energy, time and line-of-sight angle, a near-range autonomous rendezvous glidescope orbit design method is studied based on the differential equation method. The glidescope equations of approach and retreat operations are deduced, the power function between the relative distance and velocity are designed, and the parameter determination method considering the energy consumption as the optimal index is put forward. Additionally, the approach reducing the line-of-sight angle is studied. Under the given constraints, the efficiency of differential equation method is validated by simulation.

Key words: rendezvous, differential equation method, glidescope orbit

CLC Number:

V412.4

LIU Luhua1, HAN Hongwei2. Glidescope Orbit Design Based on the Differential Equation Approach in Near-Range Autonomous Rendezvous Mission[J]., 2009, 35(3): 13-17.

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Glidescope Orbit Design Based on the Differential Equation Approach in Near-Range Autonomous Rendezvous Mission

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