两种J_2摄动模型下卫星编队相对位置误差分析

为了研究一个轨道周期内卫星和卫星编队的运动规律,在J2摄动理论基础之上,采用摄动加速度分析方法,给出了J2瞬时摄动模型。以近地太阳同步轨道卫星和双星编队为例,与只考虑J2一阶长期项的平均摄动模型比较,仿真分析结果表明,对卫星而言,一个轨道周期内,卫星半长轴相对平均半长轴漂移达到18km,偏心率相对平均偏心率漂移达到10-3量级,轨道倾角相对平均轨道倾角漂移达到0.01°,即由于J2瞬时摄动的影响,卫星运动发生了摄动;对双星编队而言,一个轨道周期内,两星相对位置的径向误差达到5km,沿迹向误差达到19km,法向误差相对较小,在10-2量级上,相对距离的误差达到了19km,随着时间的推移,误差会越来越大。

椭圆参考轨道的卫星编队队形保持控制设计

以Lawden方程作为动力学模型,建立状态方程,利用线性二次型性能指标最优控制(LQR)对卫星编队队形进行保持控制。首先对近地轨道的主要摄动J2项摄动和大气阻力摄动进行描述,得到了影响编队队形的相对摄动的表达式。然后通过合理的选择控制加权矩阵R,用无约束的线性二次型优化方法解决了电推力火箭有控制约束的优化问题。仿真结果表明,这种控制方法是有效的。

Perturbation to Unified Symmetry and Adiabatic Invariants for Relativistic Hamilton Systems

Based on the concept of adiabatic invariant, the perturbation to unified symmetry and adiabatic invariants for relativistic Hamilton systems are studied. The definition of the perturbation to unified symmetry for the system is presented, and the criterion of the perturbation to unified symmetry is given. Meanwhile, the Noether adiabatic invariants, the generalized Hojman adiabatic invariants, and the Mei adiabatic invariants for the perturbed system are obtained.

Perturbation to Symmetries and Adiabatic Invariants of Nonholonomic Dynamical System of Relative Motion

Based on the theory of symmetries and conserved quantities, the exact invariants and adiabatic invariants of nonholonomic dynamical system of relative motion are studied. The perturbation to symmetries for the nonholonomic dynamical system of relative motion under small excitation is discussed. The concept of high-order adiabatic invariant is presented, and the form of exact invariants and adiabatic invariants as well as the conditions for their existence are given. Then the corresponding inverse problem is studied.