吸气式高超声速飞行器助推-巡航轨迹优化

Boost-cruise Trajectory Optimization of Air Breathing Hypersonic Vehicles

针对吸气式高超声速巡航飞行器建立了纵向平面内的二维轨迹优化模型(包括火箭助推段和吸气式飞行段),其中大气模型、气动力模型和发动机模型均建立了比较详细的模型,能够比较全面、准确地描述吸气式高超声速巡航飞行器的特征;基于配点法建立了适用于高超声速巡航飞行器助推-巡航轨迹优化的方法,在求解非线性规划时引入了规范化处理、稀疏分析和偏导数计算方法等,以提高优化效率;对吸气式高超声速飞行器助推-巡航轨迹进行了优化研究,分析了典型设计参数变化对最优轨迹的影响。仿真结果表明:所建立的方法能够快速、高精度求解吸气式高超声速巡航飞行器轨迹优化问题,并且能够方便地分析设计参数变化对最优轨迹的影响,可用于吸气式高超声速飞行器飞行剖面设计与优化。

A two-dimensional trajectory optimization model in the vertical plane is established for air-breathing hypersonic cruise vehicles,including the rocket boost phase and the air-breathing phase.The atmospheric model,the aerodynamic models and the thrust models are modeled in detail so that the features of air-breathing hypersonic cruise vehicles can be described comprehensively and accurately.A method based on the local collocation method is established for solving the boost-cruise trajectory optimization of air-breathing hypersonic cruise vehicles.Normalization scaling,sparsity analysis and an efficient partial derivative calculation method are utilized to help solve the nonlinear programming in order to improve the optimization efficiency.Numerical simulation is carried out for the boost-cruise trajectory optimization of air-breathing hypersonic cruise vehicles,and the influences of typical design parameters are analyzed.Simulation results show that the proposed method can solve the trajectory optimization problems of hypersonic cruise vehicles rapidly and accurately,and can be used to analyze the influences of different design parameter values on the optimal trajectory conveniently,demonstrating its application in the flight profile design and optimization of air breathing hypersonic vehicles.