2.4 m跨声速风洞虚拟飞行试验技术研究

doi:10.7527/S1000-6893.2015.0196

Abstract

Abstract:

The wind tunnel-based virtual flight testing(WTBVFT) is an experimental technique, which is used to simulate vehicles' maneuvering movements in wind tunnels efficiently, to obtain the coupling characteristics between aerodynamic and kinetic behavior and to discover the coupling mechanism, but also to implement the consistent research about the integration of aerodynamics and flight mechanics. In this paper, the experimental techniques of WTBVFT platform in 2.4 m transonic wind tunnel are introduced briefly that consist of the similarity law and simulation methods, the supporting means for test models, the measuring skills of aerodynamic parameters and motion parameters, as well as the drive and control techniques, and then some experiments of typical missiles' model using WTBVFT are presented, such as open-loop control tests, closed-loop control tests for angle of attack and normal acceleration, pitching and rolling coupled motion and their decoupled control tests, and verification tests of real-flight. The tests' results show that the motions of WTBVFT platform are very agile, the measurement tests of aerodynamic parameters and the motion parameters are credible, and WTBVFT platform is able to repeat the real-flight of missile effectively and has the capability to conduct closed-control and decoupled control tests. WTBVFT has the primarily experimental ability for integrated simulation of aerodynamics and flight dynamics for missile model, and provides a technical basis for verification and optimization of flight control law, data correction and application, and development of WTBVFT for flight vehicles with complex shape.

Key words: flight vehicle, missile, aerodynamic and motion coupling, virtual flight testing, wind tunnel test, closed-loop control

CLC Number:

V211.7

ZHAO Zhongliang, WU Junqiang, LI Hao, ZHOU Weiqun, MAO Daiyong, YANG Haiyong. Investigation of virtual flight testing technique based on 2.4 m transonic wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(2): 504-512.

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Investigation of virtual flight testing technique based on 2.4 m transonic wind tunnel

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