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针对火箭基组合循环(RBCC)发动机比冲和推进剂质量流量随飞行条件改变而不断变化的特点,提出了通过增广拉格朗日遗传算法优化飞行器飞行轨迹的方法,在飞行器气动参数和发动机比冲已知、最大飞行动压给定等条件下,进行了火箭基组合循环发动机—液体火箭(RKT)发动机推进的水平起飞两级入轨(TSTO)飞行器飞行轨迹优化计算。研究结果表明:在飞行俯仰角和发动机推进剂质量流量变化范围已知的情况下,利用该方法能够在较好满足给定约束条件的情况下,优化得到飞行俯仰角和发动机流量随时间的变化关系,为飞行轨迹初步设计提供参考。
Aiming at the characteristics of RBCR and propellant mass flow changing with the change of flight conditions, a method based on Augmented Lagrangian Genetic Algorithm is proposed to optimize the flight path of the aircraft. The aerodynamic parameters of the RBCC engine and the engine (TSTO) aircraft trajectory optimization with rocket-based combined cycle engine-liquid propellant (RKT) engine propulsion under the condition of known specific thrust, known impulse, known impulse maximum and given maximum flight pressure. The results show that the change of flight pitch angle and engine flow rate with time can be optimized under the condition that the pitch angle of flight and the range of mass flow of engine propellant are known. Relationship, provide a reference for the preliminary design of flight path.