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高机动飞行器非指令运动及其控制的研究进展

邓学蓥, 竹军, 王延奎, 马宝峰

邓学蓥, 竹军, 王延奎, 马宝峰. 高机动飞行器非指令运动及其控制的研究进展[J]. 力学与实践, 2012, 34(3): 1-8. DOI: 10.6052/1000-0879-12-060
引用本文: 邓学蓥, 竹军, 王延奎, 马宝峰. 高机动飞行器非指令运动及其控制的研究进展[J]. 力学与实践, 2012, 34(3): 1-8. DOI: 10.6052/1000-0879-12-060
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DENG Xueying, ZHU Jun, WANG Yankui, MA Baofeng. THE PROGRESS OF STUDIES OF UNCOMMANDED MOTION AND ITS SUPPRESSION OF FLYING VEHICLE WITH HIGH MANUEVERABILITY[J]. MECHANICS IN ENGINEERING, 2012, 34(3): 1-8. DOI: 10.6052/1000-0879-12-060
Citation: DENG Xueying, ZHU Jun, WANG Yankui, MA Baofeng. THE PROGRESS OF STUDIES OF UNCOMMANDED MOTION AND ITS SUPPRESSION OF FLYING VEHICLE WITH HIGH MANUEVERABILITY[J]. MECHANICS IN ENGINEERING, 2012, 34(3): 1-8. DOI: 10.6052/1000-0879-12-060
shu
邓学蓥, 竹军, 王延奎, 马宝峰. 高机动飞行器非指令运动及其控制的研究进展[J]. 力学与实践, 2012, 34(3): 1-8. CSTR: 32047.14.1000-0879-12-060
引用本文: 邓学蓥, 竹军, 王延奎, 马宝峰. 高机动飞行器非指令运动及其控制的研究进展[J]. 力学与实践, 2012, 34(3): 1-8. CSTR: 32047.14.1000-0879-12-060
shu
DENG Xueying, ZHU Jun, WANG Yankui, MA Baofeng. THE PROGRESS OF STUDIES OF UNCOMMANDED MOTION AND ITS SUPPRESSION OF FLYING VEHICLE WITH HIGH MANUEVERABILITY[J]. MECHANICS IN ENGINEERING, 2012, 34(3): 1-8. CSTR: 32047.14.1000-0879-12-060
Citation: DENG Xueying, ZHU Jun, WANG Yankui, MA Baofeng. THE PROGRESS OF STUDIES OF UNCOMMANDED MOTION AND ITS SUPPRESSION OF FLYING VEHICLE WITH HIGH MANUEVERABILITY[J]. MECHANICS IN ENGINEERING, 2012, 34(3): 1-8. CSTR: 32047.14.1000-0879-12-060
shu

高机动飞行器非指令运动及其控制的研究进展

  • 北京航空航天大学航空科学与工程学院, 北京 100191

基金项目: 国家自然科学基金资助项目(10432020, 10872019, 11172030).
详细信息
    通讯作者:

    邓学蓥

  • 中图分类号: V249.122.3

THE PROGRESS OF STUDIES OF UNCOMMANDED MOTION AND ITS SUPPRESSION OF FLYING VEHICLE WITH HIGH MANUEVERABILITY

  • School of Aeronautic Science and Engineering, BUAA, Beijing 100191, China

摘要

    摘要
  • 摘要: 高机动飞行器往往都是通过大攻角飞行来实现高机动科目的, 在发展高机动飞行器的过程中, 其非指令运动是伴随着大攻角飞行而常常出现的运动形态. 为此, 应在飞行器设计的早期阶段, 充分研究所设计布局的大攻角流动性态及其相应的非指令运动的形态；揭示这类运动形态的主控流动；在此基础上形成和发展流动控制新技术, 以达到抑制非指令运动的目的. 由于大攻角前体非对称涡往往与非指令运动密切相关, 为此本文首先指出前体非对称涡流动对头部微扰动十分敏感, 以致长期以来让人们误认为这类流动具有不确定性. 研究表明, 通过设置人工微扰动可使前体非对称涡流动具有可重复性, 并揭示该流动随扰动周向角变化的响应、演化规律. 通过利用大、小后掠翼两类翼身组合体的典型布局形式, 研究它们所呈现的摇滚运动形态, 揭示其摇滚运动的不同主控流动机理, 在此基础上分别发展了抑制小、大后掠翼身组合体摇滚运动的流动控制技术: 快速旋转头部扰动和适当设置扰动位使翼、身的两对非对称涡处于反相. 在抑制非指令运动的研究中, 深入理解和揭示头部微扰动对非对称涡流动的响应、演化机理是至关重要的, 应予以特别关注.
    Abstract: High maneuver ability might be achieved by a flying vehicle at high angles of attack. The uncom-manded motions of aircraft can be generated at high angles of attack in flying with high maneuver ability. Therefore this problem should be considered in the early phase of aircraft design and the complicated flow behaviors and characteristics of uncommanded motions of the designed configuration will be studied to reveal the dominant flows to drive uncommanded motions. The flow control techniques are developed to suppress the uncommanded motions. In the present paper it is pointed out that the forebody asymmetric vortices are very sensitive to the micro-perturbation on the model nose. For a long time it is wrongly believed that the forebody asymmetric vortex flow is non-deterministic. It is found that if a micro-manual-perturbation is added on the nose tip of model the asymmetric vortex flow can be reproduced. Based on the manual-perturbation technique the evolution of the asymmetric vortices related with the circumferential angle of perturbation is revealed. The dominant flows are discovered, which drive the uncommanded motions of two typical configura-tions. The perturbation control techniques are developed to suppress those uncommanded motions by rotating the tip-perturbation and setting tip-perturbation on a proper location to make two pair of asymmetric vortices in the phase reversal. The micro-perturbation plays a very important role in the non-liner separated and vortex flows at high angles of attack. The roles of micro-perturbation are the key in controlling the non-linear vortex flows, which drive the uncmmande motions.
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    • 参考文献(20)
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出版历程
  • 收稿日期:  2012-02-14
  • 发布日期:  2012-06-14

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