超声速巡航导弹气动力与推力参数一体化在线辨识  

Integrated online identification of aerodynamic and thrust parameters in supersonic cruise missile

作　　者：江振宇[1] 唐晓斌 刘双 杨承业 JIANG Zhenyu;TANG Xiaobin;LIU Shuang;YANG Chengye(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,湖南长沙410073

出　　处：《国防科技大学学报》2024年第4期74-85,共12页Journal of National University of Defense Technology

基　　金：国家自然科学基金联合基金资助项目(U21B2028);国家部委基金资助项目([2020]643号)。

摘　　要：为准确预示超声速巡航导弹飞行中的气动力和推力特性,提升飞行性能及任务适应性,提出了一种气动力与推力参数一体化在线辨识方法。建立了以固体火箭冲压发动机为动力的超声速巡航导弹在纵平面的运动模型,建立了巡航段气动力系数和推力系数多项式模型,采用无迹卡尔曼滤波算法,开展了气动力与推力参数一体化在线辨识仿真验证,基于飞行试验对辨识性能进行了比较验证。研究表明,对超声速巡航导弹进行气动力与推力参数一体化辨识是必要的和有效的,提出的方法可应用于飞行过程中参数在线辨识。To accurately predict the aerodynamic and thrust characteristics of supersonic cruise missile during flight,improve the flight performance and mission adaptability,an integrated online identification method for aerodynamic and thrust parameters was proposed.Motion model of supersonic cruise missile powered by a solid rocket ramjet engine in the longitudinal plane was established,and a polynomial model of aerodynamic and thrust coefficients in the cruise phase was established.The unscented Kalman filter algorithm was used to conduct online identification and simulation verification of aerodynamic and thrust parameters.The identification performance was compared and verified based on flight test data.Researches show that the integrated identification of aerodynamic and thrust parameters for supersonic cruise missile is necessary and effective,and the proposed method can be applied to online parameter identification during flight.

关 键 词：超声速巡航导弹 一体化在线辨识 气动力 推力 

分 类 号：TJ7[兵器科学与技术—武器系统与运用工程]