国防科技大学学报2024，Vol.46Issue(4)：74-85,12.DOI:10.11887/j.cn.202404008
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
摘要
Abstract
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Key words
supersonic cruise missile/integrated online identification/aerodynamic/thrust分类
军事科技引用本文复制引用
江振宇,唐晓斌,刘双,杨承业..超声速巡航导弹气动力与推力参数一体化在线辨识[J].国防科技大学学报,2024,46(4):74-85,12.基金项目
国家自然科学基金联合基金资助项目(U21B2028) （U21B2028）
国家部委基金资助项目([2020]643号) （[2020]643号）
