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对于采用吸气式超燃冲压发动机的高超声速飞行器,其发动机推力可能与机身弹性发生耦合影响,从而引起所谓的推力耦合气动伺服弹性(ASE)问题。为对其耦合原理及影响进行研究,以简化的飞行器纵向模型为对象,考虑结构弹性、非定常气动力、冲压发动机以及控制系统之间的相互耦合作用,建立了推力耦合的高超声速飞行器气动伺服弹性问题的一般建模框架和分析流程。采用牛顿冲击理论计算高超声速非定常气动力,基于准一维流动假设分析发动机性能。算例结果表明,考虑发动机推力的耦合影响后,飞行器的短周期特性和气动伺服弹性特性均有明显改变,气动伺服弹性稳定裕度下降可达16%,应当引起飞行控制系统设计部门的重视。
For hypersonic vehicles using aspirated scramjet engines, their engine thrust may be coupled to the fuselage elasticity causing so-called thrust-coupled aerodynamic servo-elastic (ASE) problems. In order to study the principle and influence of the coupling, a simplified longitudinal model of the aircraft is taken as the object. Considering the mutual coupling between the structure elasticity, unsteady aerodynamics, ramjet and control system, a thrust-coupled hypersonic aerodynamic servo General modeling framework and analysis process for resilience issues. Hypersonic unsteady aerodynamics are calculated using Newton’s impact theory and engine performance is analyzed based on the quasi-one-dimensional flow assumptions. The results of numerical examples show that the short-period and aerodynamic characteristics of the aircraft obviously change after considering the coupling effect of the engine thrust. The stability margin of the aerodynamic servo elasticity can drop by 16%, which should be paid more attention to by the flight control system design department.