一种基于Hohmann最优交会的寻的制导方法
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摘要
针对交会对接远距离和近距离交接的寻的段制导,提出一种基于Hohmann最优交会的制导方法。先给出邻近圆轨道交会动力学方程;结合寻的段飞行时间特点给出Hohmann最优交会并分析其应用范围;针对寻的段存在相对测量的特点提出一种CW制导和Hohmann最优交会结合的多脉冲制导策略,并给出仿真算例,仿真结果验证了方案设计的有效性和正确性。
A homing guidance method based on Hohmann optimal rendezvous was proposed for rendezvous and docking from long distance to short distance. The dynamic equations for circular orbit rendezvous were given. According to the homing flight time, a Hohmann optimal rendezvous was given and its application scope was analyzed. In addition, a multi-impulse guidance strategy combining CW guidance with Hohmann optimal rendezvous was proposed considering the relative measurement in the homing phase. Then a simulation example was given and the effectiveness and accuracy of the guidance design was verified by the simulation results.
A homing guidance method based on Hohmann optimal rendezvous was proposed for rendezvous and docking from long distance to short distance. The dynamic equations for circular orbit rendezvous were given. According to the homing flight time, a Hohmann optimal rendezvous was given and its application scope was analyzed. In addition, a multi-impulse guidance strategy combining CW guidance with Hohmann optimal rendezvous was proposed considering the relative measurement in the homing phase. Then a simulation example was given and the effectiveness and accuracy of the guidance design was verified by the simulation results.
引文
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[12] 胡军,解永春,张昊,等.神舟八号飞船交会对接制导、导航与控制系统及其飞行结果评价[J].空间控制技术与应用,2011,37(6):1-5,13.Hu J,Xie Y C,Zhang H,et al.Shenzhou-8 spacecraft guidance navigation and control system and flight result evaluation for rendezvous and docking [J].Aerospace Control and Application,2011,37(6):1-5,13.(in Chinese)
[2] Prussing J E.Optimal four-impulse fixed-time rendezvous in the vicinity of a circular orbit.[J].AIAA Journal,1969,7(5):928-935.
[3] Prussing J E.Optimal two- and three-impulse fixed-time rendezvous in the vicinityof a circular orbit[J].AIAA Journal,1970,8(7):1221-1228.
[4] Prussing J E.Optimal impulsive linear systems:sufficient conditions and maximum number of impulses[J].The Journal of the Astronautical Science,1995,43(2):195-206.
[5] Carter T,Brient J.Optimal bounded-thrust space trajectories based on linear equations[J].Journal of Optimization Theory and Applications,1991,70(2):299-317.
[6] Prussing J E,Chiu J H.Optimal multiple-impulse time-fixed rendezvous between circular orbits[J].Journal of Guidance Control and Dynamics,1984,9(1):17-22.
[7] Prussing J E,Clifton R S.Optimal multiple-impulse satellite evasive maneuvers[J].Journal of Guidance Control and Dynamics,1994,17(3):599-606.
[8] Taur D,Shan C,Coverstonecarroll V,et al.Optimal impulsive time-fixed orbital rendezvous and interception with path constraints[J].Journal of Guidance Control and Dynamics,1995,18(1):54-60.
[9] 陈长青,解永春.一类椭圆轨道交会中的动力学方程研究[J].航天控制,2008,26(5):12-17.Chen C Q,Xie Y C.Dynamical equations for a kind of elliptic orbit rendezvous[J].Aerospace Control,2008,26(5):12-17.(in Chinese)
[10] 齐映红,曹喜滨.三脉冲最优交会问题的解法[J].吉林大学学报(工学版),2006,36(4):608-612.Qi Y H,Cao X B.Solution for optimal 3-impulse rendezvous problem[J].Journal of Jilin University(Engineering and Technology Edition),2006,36(4):608-612.(in Chinese)
[11] Chen C Q,Xie Y C.Optimal impulsive ellipse-to-circle coplanar rendezvous[J].Science China-technological Sciences,2009,52(5):1435-1445.
[12] 胡军,解永春,张昊,等.神舟八号飞船交会对接制导、导航与控制系统及其飞行结果评价[J].空间控制技术与应用,2011,37(6):1-5,13.Hu J,Xie Y C,Zhang H,et al.Shenzhou-8 spacecraft guidance navigation and control system and flight result evaluation for rendezvous and docking [J].Aerospace Control and Application,2011,37(6):1-5,13.(in Chinese)