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为在高超声速飞行器设计初期快速地获得推力和推力矩,以满足控制相关分析和建模需要.提出一种推进系统建模方法,基于激波/膨胀波相交理论来建模与机身耦合的进气道模型;用有摩擦变截面加热管来描述双模态燃烧室;将内喷管建模成一维变截面摩擦管,采用动量定理估算推力,并通过曲线拟合得到推力的解析表达式.与CFD计算结果相比,该模型计算得到双模态冲压发动机入口气流马赫数和温度误差小于5%,压强误差小于10%;计算得到的推力随马赫数、燃油当量比和迎角的增大而增加,随高度增加而减小,单个状态平均计算时间小于0.5s.计算结果表明:该建模方法满足面向控制建模的效率和精度需求,有助于此类飞行器设计初期的动力学和控制相关的分析和设计.
In order to meet the needs of control-related analysis and modeling, a propulsive system modeling method is proposed to model thrusting and pushing moment quickly in the design of hypersonic aircraft based on the shock / expansion wave theory The inlet nozzle model is described; the bimorph combustion chamber is described by using a frictional variable-section heating tube; the inner nozzle is modeled as a one-dimensional variable cross-section friction tube, the thrust is estimated by the momentum theorem and the analytical expression of the thrust is obtained by curve fitting Compared with the CFD calculation results, the model calculates the Mach number and temperature error of the inlet air flow of the bimodal ramjet engine to less than 5% and the pressure error less than 10%. The calculated thrust increases with Mach number, fuel equivalence ratio and angle of attack The calculation results show that this modeling method meets the requirements of efficiency and accuracy for control modeling and is helpful to the dynamics of the initial design of such aircraft Control-related analysis and design.