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研究了两种共面椭圆轨道最优转移方法——基于单纯推力的双脉冲对称转移和基于气动力辅助变轨技术的协同机动方法。推导了双脉冲对称转移问题中转移椭圆轨道的求解公式,采用遗传算法求解最优变轨点位置,给出了变轨脉冲的计算方法。将气动力辅助对称转移过程分为3段:真空飞行段、大气飞行段、真空飞行段。以能量最小为性能指标,将大气飞行段轨迹优化问题转化为标准最优控制问题模型,并利用Gauss伪谱法进行求解,得到“巡航+滑行+巡航+滑行”的大气最优飞行轨迹。最后对两种转移方法进行详细比较,指出初始椭圆轨道近地点越接近大气层,气动力辅助对称转移方法比双脉冲对称转移方法越节省能量。
The optimal transfer method for two kinds of coplanar elliptical orbits is studied. The two-pulse symmetrical transfer based on simple thrust and the coordinated maneuver based on aerodynamic force-assisted orbit-changing technology are studied. The solving formula of transfer elliptic orbit for double pulse symmetry transfer problem is deduced. The position of the optimal orbit change point is solved by genetic algorithm, and the calculation method of the orbit change pulse is given. The aerodynamic auxiliary symmetrical transfer process is divided into three sections: the vacuum flight section, the atmospheric flight section and the vacuum flight section. Taking the minimum energy as the performance index, the trajectory optimization problem in the flight section of the atmosphere is transformed into the standard optimal control problem model and solved by Gauss pseudospectral method to get the optimal trajectory of the atmosphere of “cruise + taxiing + cruising + taxiing” . Finally, a detailed comparison is made between the two transfer methods. It is pointed out that the closer the initial elliptical orbit near-atmosphere is to the atmosphere, the more energy-efficient the aerodynamic assisted symmetric transfer method can achieve than the two-pulse symmetric transfer method.