【摘要】 以火箭基组合循环(RBCC)发动机为动力的高超声速巡航飞行器的气动力、推进系统、结构之间存在很强的耦合作用,文中基于二维无粘可压缩流理论和单步有限化学反应模型对此飞行器在巡航状态进行了一体化数值计算以分析这种耦合特性。考虑了不同飞行攻角、不同燃料流率下气动参数,包括升力系数、阻力系数和俯仰力矩系数的变化规律。结果显示,增加飞行攻角,可以提高飞行器升力,同时阻力也相应提高,但升阻比是先快速增加,然后逐渐达到某一最大值,俯仰力矩随飞行攻角的增大而减小;增加发动机的燃料流率,飞行器升力将相应提高,而阻力基本没有变化,升阻比提高,而俯仰力矩降低。更多还原

【Abstract】 Numerical calculation on a rocket-based combined-cycle(RBCC)powered cruise vehicle has been done to analyze the coupling characteristics based on 2-D inviscid compressible flow theory and one-step finite rate chemistry model.The change rules of aerodynamic parameters including lift coefficient,drag coefficient and pitch moment coefficient have been analyzed when angle of attack and fuel flow rate is changed.Results show that with the increase of attack angle,lift,drag will increase and pitching moment will decrease,while lift-to-drag increase rapidly firstly and then reach a maximum.With the increase of fuel mass flow rate,lift and lift-to-drag will augment and pitching moment will decrease,while drag will change little.更多还原