斜置机翼变构飞行器纵向操稳特性分析  

Analysis of longitudinal controllability and stability of oblique wing morphing aircraft

作　　者：李勇 马绍贤[3] 贺旭照 刘鲁华 LI Yong;MA Shaoxian;HE Xuzhao;LIU Luhua(School of Aeronautics and Astronautics,Sun Yat-sen University,Shenzhen 518107,China;Shenzhen Key Laboratory of Intelligent Microsatellite Constellation,Sun Yat-sen University,Shenzhen 518107,China;Beijing Fluid Dynamic Scientific Research Center,Beijing 100011,China)

机构地区：[1]中山大学航空航天学院,广东深圳518107 [2]中山大学深圳市智能微小卫星星座技术与应用重点实验室,广东深圳518107 [3]北京流体动力科学研究中心,北京100011

出　　处：《飞行力学》2024年第1期55-61,共7页Flight Dynamics

基　　金：国家自然科学基金资助(61973326);深圳市科技计划资助(ZDSYS20210623091808026)。

摘　　要：以一类斜置机翼变构飞行器为研究对象,分析了变构对其气动特性和运动状态的影响及其操稳特性。运用牛顿-欧拉法建立了飞行器多刚体纵向动力学模型,突出了斜置机翼变构时所产生的模型差异;基于动力学模型,研究了斜置机翼变构对飞行器气动特性和飞行状态的影响规律;结合飞行器的气动数据对飞行器纵向操稳特性进行了分析。结果表明:对于机翼整体质心与机身质心在x_(1)O_(1)z_(1)平面重合的斜置机翼飞行器,机翼旋转变构对飞行器整体只产生了绕z轴方向的附加力矩,总的附加力为零;变构过程改变气动压心位置,使飞行器产生静不稳定;由于飞行器不同状态下对舵偏的传递函数中阻尼系数过小,导致飞行器的超调量和调节时间异常,需要进行修正。A class of oblique wing morphing vehicle is taken as the research object,and the effects of morphing on aerodynamic characteristics,motion state,controllability and stability are analyzed.The Newton-Euler method is used to establish a multi-rigid-body longitudinal dynamic model of the vehicle,which highlights the model differences arising from the oblique wing morphing.Based on the dynamic model,the influence of the oblique wing morphing on the aerodynamic characteristics and motion state of the vehicle is investigated.The longitudinal controllability and stability of the vehicle are analyzed by combining with the aerodynamic data of the vehicle.The results show that for the oblique wing vehicle whose overall center of mass of the wing and the center of mass of the fuselage are coincident in the x_(1)O_(1)z_(1) plane,the rotational morphing of the wing produces only additional moments around the z-axis direction,and the total additional force is zero;the morphing process changes the position of the aerodynamic center,which produces the static instability of the vehicle;and the value of damping coefficient in the transfer function of rudder deflection in different states of the vehicle is too small,which leads to abnormal overshoot and adjustment time of the vehicle in all flight states and needs to be corrected.

关 键 词：斜置机翼 变构飞行器 动力学建模 操纵性 稳定性 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]