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针对火箭基组合动力(RBCC)可重复使用运载器(RLV)轨迹多段、多控制变量、推力与飞行轨迹耦合,飞行轨迹设计困难的问题,提出了基于高斯伪光谱方法的数值优化求解模型和求解方法,并获得满足要求的上升段燃料最省轨迹。将该轨迹分为3部分,分别由引射火箭、亚燃冲压和超燃冲压发动机提供动力,以攻角和燃料秒流量为控制变量,根据轨迹任务和各模态发动机启动及工作条件建立优化模型、设定各段末端和路径约束,利用高斯伪谱法求解最优轨迹并利用特殊方法计算边界控制变量。通过与传统方法所得轨迹的对比表明,所建立的优化模型和方法可快速求解出RBCC运载器上升段最优轨迹,优化结果符合RBCC运载器工作特点。
Aiming at the multi-section, multi-control variables of RLV trajectory, the coupling of thrust and flight trajectory and the difficulty of flight trajectory design, a numerical optimization solving model based on Gaussian pseudo-spectral method and its solution Method, and get to meet the requirements of the rising section of the fuel-saving trajectory. The trajectory is divided into three parts, respectively, by the rocket launch, sub-combustion and scramjet scramjet engine to provide power, the angle of attack and the second flow of fuel as the control variable, according to trajectory tasks and various modal engine startup and working conditions to establish optimization Model, set the end of each segment and path constraints, the use of Gaussian pseudo-spectral method to find the optimal trajectory and the use of special methods to calculate the boundary control variables. The comparison with the trajectory obtained by the traditional method shows that the optimized model and method can quickly find the optimal trajectory of RBCC carrier ascending stage, and the optimization result accords with the operating characteristics of RBCC carrier.