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以高超声速飞行器纵向运动的空气动力学模型和结构动力学模型为依据,采用数值分析的方法,研究了高超声速飞行器动力系统平衡点集的拓扑结构.首先根据高超声速飞行器在巡航阶段的飞行边界的限制条件得到在给定的飞行高度和马赫数下的平衡点集,由此近似估算出了高超声速飞行器的飞行包线.然后根据得到的平衡点集,分别研究了高超声速飞行器的迎角、升降舵偏角和发动机的燃料当量比与飞行马赫数和高度的关系,并进行了数值拟合,在此基础上分别描绘了以上三个拟合关系式的曲面关系图。
Based on the aerodynamic model and structural dynamics model of the hypersonic vehicle’s longitudinal motion, the topology of the equilibrium point set of the hypersonic vehicle’s power system is studied by means of numerical analysis.Firstly, based on the flight boundary of the hypersonic vehicle during the cruising phase The equilibrium point set at a given flight altitude and Mach number is obtained, and the flight envelope of the hypersonic vehicle is approximately estimated. Then based on the obtained equilibrium point set, the attack angle of the hypersonic vehicle , The declination angle of the elevator and the relationship between the fuel equivalence ratio of the engine and the Mach number and height of the flight were numerically fitted. On the basis of this, the surface relationships of the above three fitting relationships were respectively depicted.