二级入轨航天运载器最优分离飞行状态研究

OPTIMAL STAGING CONOITIONS OF TSTO VEHICLES

研究水平起降二级入轨航天运载器分离飞行状态（飞行高度、轨迹倾角、马赫数）对轨道器在分离点处的质量（包括结构质量、燃料质量等）的影响。主要内容包括：针对以火箭发动机为动力的轨道器，建立了上升段运动方程。采用静态可变误差多面体算法加上动态共轭梯度法数值优化了轨道器上升段轨迹，优化的性能指标是分离点处轨道器的总质量最小，初始条件受到载机上升段走廊的约束，终端约束是某指定的目标轨道。对分离状态与轨道器总体方案（升阻比、推力、比冲等）对轨道器总质量的影响作了大量数值仿真。针对某飞行器模型，得到了一组最优分离飞行状态。拟合出估算分离状态对轨道器总体方案的影响计算公式。得到了合理选择分离飞行状态的结论。

The staging conditions of a two-stag-to-orbit(TSTO)launch vehiclewith horizontal take-off are studied for the influence on the total weight of the orbitor.The following contents are studied:Ascent equations of motion are given for the orbitor with rocket engines.Conjugategradient numerical calculation method and static varied tolerance polyhedrons algorithm areomployed to optimize the ascent trajectorics of the orbitor.The performance is minimlze thetotal mass of the orbitor on staging point.The initial conditions are restained by the ascentcorridor of the first stage,and the final conditions are the target orbit.Based on numerical results of the ascent corridor of the first stage and the optimal as-cent trajectories,the paper obtained a large amount of numerical mutual relations amongstaging conditions and total performance of the orbitor.A set of pararmeters of optimal stag-ing condition are obtained for a certain orbitor.The formula of approximate mutual relationis obtained about staging conditions and total performance of the orbitor. The gerneral con-clusion is obtained about choosing staging conditions.