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

流体力学与飞行力学

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2.4 m跨声速风洞虚拟飞行试验技术研究

赵忠良, 吴军强, 李浩, 周为群, 毛代勇, 杨海泳

中国空气动力研究与发展中心高速空气动力研究所, 绵阳 621000

收稿日期:2015-03-09 修回日期:2015-07-01 出版日期:2016-02-15 发布日期:2015-07-31
通讯作者: 赵忠良,男,硕士,研究员,硕士生导师。主要研究方向:非定常空气动力学。Tel:0816-2462109,E-mail:zzzhao_cardc@sina.com E-mail:zzzhao_cardc@sina.com
作者简介:吴军强,男,硕士,研究员,硕士生导师。主要研究方向:大迎角空气动力学。Tel:0816-2462009,E-mail:cardc_wujunqiang@163.com
基金资助:
国家自然科学基金(91216203);国家"973"计划(61389)

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

ZHAO Zhongliang, WU Junqiang, LI Hao, ZHOU Weiqun, MAO Daiyong, YANG Haiyong

High Speed Aerodynamics Institue of China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2015-03-09 Revised:2015-07-01 Online:2016-02-15 Published:2015-07-31
Supported by:
National Natural Science Foundation of China(91216203);National Basic Research Program of China(61389)

摘要/Abstract

摘要：

风洞虚拟飞行试验(WTBVFT)技术是在风洞环境中对飞行器机动运动最逼真模拟的物理过程,它不仅可以更加有效模拟飞行器的机动运动过程、获取气动/运动耦合特性和揭示气动/运动耦合机理,而且能够实现气动/飞行力学集成的相容性研究。鉴于此,简要介绍了2.4 m跨声速WTBVFT技术,包括:相似准则和模拟方法、试验模型支撑技术、气动/运动参数测试技术和操纵控制技术等,并开展了典型导弹模型开环控制、姿态角闭环控制、加速度闭环控制、俯仰/滚转耦合与解耦控制以及靶试弹道验证等WTBVFT。研究结果表明:WTBVFT系统运动灵活,气动参数和运动参数测量结果准确可靠,能够有效模拟导弹实际飞行过程,具备闭环控制与耦合运动解耦控制的试验模拟能力,初步形成了气动/飞行力学一体化试验研究能力。同时,该研究也为开展控制方法优化与验证、数据修正与应用以及发展复杂构型的WTBVFT奠定了技术基础。

关键词: 飞行器, 导弹, 气动/运动耦合, 虚拟飞行试验, 风洞试验, 闭环控制

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

中图分类号:

V211.7

赵忠良, 吴军强, 李浩, 周为群, 毛代勇, 杨海泳. 2.4 m跨声速风洞虚拟飞行试验技术研究[J]. 航空学报, 2016, 37(2): 504-512.

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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E-mail：hkxb@buaa.edu.cn

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2.4 m跨声速风洞虚拟飞行试验技术研究

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

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