带脉冲的三维引力辅助变轨研究

发布时间：2019-03-20 20:09

【摘要】：在引力辅助过程中施加脉冲可以有效地改善变轨效果.目前只能对施加小脉冲的情况进行近似计算,当脉冲大于近拱点速度的1%时无法进行分析.针对这一问题,提出了一种解析分析方法,可以计算施加任意大小和方向脉冲的三维引力辅助变轨.基于二体问题,建立了带任意脉冲的三维引力辅助模型,采用8个相互独立的参数对模型进行描述,其中5个参数表征三维引力辅助、一个参数表征脉冲的大小、两个参数表征脉冲的方向;建立了一组坐标系,可以方便地对轨道进行描述;以施加脉冲为界,将轨道划分为前后两段,分别进行公式推导;应用双曲线轨道动力学与坐标变换等技术方法,可以将飞行器的位置矢量和速度矢量表示为上述8个参数的解析公式,进而可以求出变轨导致的速度、能量和轨道倾角的变化量.通过与基于圆型限制性三体问题的数值仿真结果进行对比,验证公式的有效性.应用导出的解析公式分析了施加脉冲的大小和方向对飞行器能量和轨道倾角的影响,并给出了相应规律.结果表明:以最大能量改变为优化目标,施加脉冲的最优方向往往并不是该点速度方向;轨道倾角受到脉冲方向的影响显著.
[Abstract]:The effect of orbit-shifting can be effectively improved by applying a pulse in the gravity-assisted process. At present, the case of small pulse can only be approximately calculated, when the pulse is greater than 1% of the velocity near the arch point, the analysis can not be carried out. In order to solve this problem, an analytical method is proposed, which can be used to calculate three-dimensional gravity-assisted orbit transformation with arbitrary size and direction pulse. Based on the two-body problem, a three-dimensional gravity-assisted model with arbitrary pulses is established. Eight independent parameters are used to describe the model, in which five parameters represent the three-dimensional gravity assistance and one represents the pulse size. Two parameters indicate the direction of the pulse. A set of coordinate system can be set up to describe the orbit conveniently, and the orbit is divided into two segments with pulse as the boundary, and the formulas are deduced respectively. By means of hyperbolic orbit dynamics and coordinate transformation, the position vector and velocity vector of aircraft can be expressed as analytical formulas of the above eight parameters, and then the velocity caused by orbit change can be calculated. The amount of change in energy and orbital inclination. Compared with the numerical simulation results based on circular restricted three-body problem, the validity of the formula is verified. By using the derived analytical formula, the influence of the magnitude and direction of the pulse applied on the energy and orbit inclination of the vehicle is analyzed, and the corresponding rules are given. The results show that when the maximum energy change is taken as the optimization target, the optimal direction of the pulse is often not the velocity direction of the point, and the orbital inclination is significantly affected by the direction of the pulse.
【作者单位】：北京航空航天大学航空科学与工程学院;
【基金】：国家自然科学基金资助项目(11372018)
【分类号】：V412.41

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