采用二次修正的立方星拦截仿真研究

Simulation Research on Interception of Cubesat with Quadratic Correction

针对空间攻防背景下立方星拦截问题,提出了一种Lambert求解与C-W方程结合的以燃料-时间为约束的拦截轨道快速设计方法。该方法首先在Lambert求解框架下,以燃料和拦截时间为限,建立了立方星转移时间与速度增量的模型,生成了初始拦截轨道;随后根据末端拦截精度需求,通过C-W方程进行末段导引,施加二次脉冲,对拦截轨道末端进行误差修正,使得最终误差可以满足任务要求。最后通过GMAT构建的轨道力学环境,在Matlab算法驱动下进行联合仿真验证,分析表明该算法在燃料和时间的共同约束下可获得一条优化轨道,并能兼顾末端拦截精度,具有工程借鉴意义。

Regarding the interception problem of CubeSat under the background of space attack and defense, a fuel-time-constrained fast interception orbit design method is proposed, which combines Lambert solution with C-W equation. In this method, firstly, in the Lambert solution framework and under the limits of the fuel and interception time, the model of the CubeSat transfer time and velocity increment is established, and the initial interception orbit is generated. Secondly, end-segment guidance is completed by the C-W equation, secondary pulses are applied and correct the error at the end of the interception track so that the final error can meet the mission requirements.Finally, through the orbital mechanics environment established by GMAT, the co-simulation verification is implemented during the driving of the Matlab algorithm. The analysis result shows that the algorithm can obtain an optimal orbit under the joint constraints of fuel and time and can take into account the terminal interception precision, which can serve as a engineering reference.