摘要
针对飞行器大攻角与大舵偏角等不满足传统模型假设的飞行特点,采用小扰动法建立了飞行器刚柔耦合飞行动力学线性化模型,并与航天工程中常用模型进行了对比分析。推导了矩阵形式的动力学方程线性化的一般形式,得到了飞行器纵向动力学模型的方程系数。给出的舵面摆动惯性力与力矩的线性化表达式,精确描述了攻角与舵偏角的扰动对摆动惯性力与力矩的影响。通过在大攻角与大舵偏角条件下将该文推导的线性化模型、传统线性化模型与原始的非线性模型的仿真结果进行对比,验证了所提出的模型具有更高的仿真精度。该文指出了传统模型将攻角和操纵机构摆角视为小量可能导致较大误差,为飞行器制导与控制系统设计提供了高精度的线性化模型。
[Objective]With advancements in modern flight vehicle design,an increased demand for maneuverability is observed,often requiring flight vehicles to operate under conditions involving a high angle of attack and large rudder angle.However,the prevalent linearized model of flight vehicle longitudinal dynamics in aerospace engineering is primarily tailored for launch vehicles,relying on assumptions such as small angle of attack and control surface deflection.Consequently,establishing a linearized model of flight dynamics applicable under conditions of the high angle of attack and large rudder angle is necessary.[Methods] This paper uses the small perturbation method to establish a linearized model of the rigid-flexible coupling flight dynamics for flight vehicles,which is then compared and analyzed with the commonly used model in aerospace engineering.Initially,the vector-form flight dynamic equations are projected onto the specified coordinate system,resulting in matrix-form scalar equations.Subsequently,the general linearized form of the dynamic equations in matrix form is derived,and the equation coefficients for the longitudinal dynamic model are obtained.High-precision linearization of the nonlinear expressions for inertia forces and moments owing to control surface deflection is performed,yielding linearized expressions that accurately describe the influence of the perturbation in the angle of attack and rudder angle on these forces and moments.A rigid-flexible coupling multibody system comprising a flexible body and rigid rudder is used as an example to compare simulation results of the linearized model derived in this paper,the traditional linearized model,and the original nonlinear model under the high angle of attack and large rudder angle,verifying the high simulation accuracy of the proposed model.[Results]By comparing the coefficients of the dynamic equations derived in this paper with those in the commonly used model in aerospace engineering,we observe that when the angle of attack and the rudder angle
作者
安阳
王天舒
AN Yang;WANG Tianshu(School of Aerospace Engineering,Tsinghua University,Beijing 100084,China)
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2024年第9期1547-1554,共8页
Journal of Tsinghua University(Science and Technology)
基金
国家自然科学基金项目(12172213)。
关键词
飞行动力学
线性化
大攻角
大舵偏角
高精度
小扰动法
flight dynamics
linearization
high angle of attack
large rudder angle
high precision
small perturbation method
