航天器远程最优拦截方法研究

Research on spacecraft long-range optimal interception

有限推力和脉冲推力是研究航天器轨道拦截问题的两大类方法。该文基于C-W方程建立了航天器远程拦截的相对运动方程,并进行了无量纲化;以能量最省为性能指标,应用Legendre伪谱法对拦截轨道进行优化,并检验结果的最优性。仿真结果表明,该方法精度高、鲁棒性强,验证了Legendre伪谱法在航天器远程拦截轨道优化设计中的正确性和有效性。以固定时间拦截理论为基础,在脉冲推力假设下,提出了一种新的最优拦截方案,它以机动时刻和所需速度冲量表征。将其与Legendre伪谱法的优化结果进行了比较,指出新的最优拦截方案能够更灵活满足拦截任务要求。

Finite thrust and impulse th/ust are two kinds of methods of studying spacecraft orbital interception. Equations of relative motion during spacecraft interception were built based on C-W equations, and it was In this paper, with fuel-consumption as performance index, the interception trajectory is optimized using Legendre pseudospectral method, and the results were analyzed. Results show that the method possesses high precision and good robustness for designing spacecraft long-range intercept trajectory. Under the assumption of impulse thrust, a new optimal intercept scheme was proposed based on fixed-time interception theory, and it was characterized by maneuver epoch and needed Deha-V. Both methods were compared and the new scheme of interception could satisfy the requirement of mission flexibly.