高机动导弹气动/运动/控制耦合的风洞虚拟飞行试验技术

Wind tunnel based virtual flight testing of aerodyanmics,flight dynamics and flight control for high maneuver missle

解决先进飞行器大迎角高机动飞行时的气动/运动非线性耦合问题,需要发展基于非线性理论的风洞试验技术,即风洞虚拟飞行试验技术。该试验能够实现较为逼真的模拟飞行器机动运动过程,气动和运动参数的实时同步测量,以及飞行控制律的集成验证与优化,从而达到探索气动/运动耦合特性和机理的目的。本文介绍了风洞虚拟飞行试验的模拟方法、关键技术及其解决措施,并针对典型导弹模型开展了虚拟飞行验证试验。试验结果表明:目前已经初步具备适用于导弹模型跨声速气动/运动/飞行控制一体化研究的风洞虚拟飞行试验能力。

Strongly nonlinear coupling phenomenon between the aerodynamic parameters and the motion parameters are generally existed during the complex maneuvers for a modern highperformance flight vehicle,therefore the integrative wind tunnel test technique becomes essential for aerodynamics and flight dynamics.The technique of wind tunnel based virtual flight testing（WTBVFT）provides the capability to research those corresponding nonlinear couple problems between aerodynamic and motion parameters.The test model will experience freely all three degree-of-freedom rotational motion,the control surfaces can be real time controlled according to the flight control systems demands,while the aerodynamic loadings and motion parameters are measured simultaneously during the test.The WTBVFT tests the response and the control characters of the vehicle,achieves the aim of integrated research on the aerodynamics and the flight dynamics,and explores the aerodynamics/flight dynamics coupling mechanism.The technical issues,corresponding platform and verification tests of WTBVFT are introduced.The test results show that WTBVFT has the primarily experimental ability for integrated simulation of aerodynamics and flight dynamics for a missile mode.