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运载火箭正常飞行情况,逃逸程序不启动,逃逸系统在预定的时刻直接被抛掉。为了提高逃逸燃料的利用率,可以在原逃逸系统作用时间范围的末端开启逃逸发动机提供辅助推力,提高火箭的入轨性能。基于CZ-2F运载火箭的塔式逃逸系统,建立了辅助入轨优化问题模型;针对优化问题对目标函数全局最优性及求解精度要求高的特点,提出了新的优化策略;对逃逸系统辅助入轨的关键指标——有效载荷增量与速度增量进行了定量分析,验证了方法的有效性。可作为逃逸系统设计以及运载火箭总体设计的参考。
Normal launch vehicle rocket flight, escape procedure does not start, the escape system at the scheduled time directly thrown away. In order to improve the utilization rate of fugitive fuels, an escape engine can be turned on at the end of the original escape system operating range to provide an auxiliary thrust to improve the orbital performance of the rocket. Based on the tower escape system of CZ-2F launch vehicle, a model of assisting the orbit optimization problem is established. Aiming at the global optimization of the objective function and the high precision of solving the problem, a new optimization strategy is proposed. The key indicators into orbit - the payload increment and speed increment were quantitatively analyzed to verify the effectiveness of the method. Can be used as escape system design and the overall design of the launch vehicle reference.