飞行器发动机破损连带滚转舵机故障仿真研究

Simulation Study on Coupled Failure of the Rolling Servo Actuator Induced by Nozzle Damage in a Flight Vehicle’s Solid Rocket Motor

摘要:

使用数值仿真方法研究了飞行器发动机喷管扩散段破损连带舵机受影响对其飞行弹道的影响,分别建立了发动机喷管破损推力模型、因喷管破损而诱发的滚转舵机故障数学模型,并将两者耦合集成至飞行器六自由度动力学模型中进行综合仿真；结果表明：喷管扩散段破损达1/2,滚转舵机正常时,在喷管破损段将只将产生破口方向偏离理论弹道的扰动；喷管扩散段破损达1/2连带滚转舵机卡死时,在破损段会诱导飞行器产生滚摆运动,导致飞行器姿态与控制系统设计姿态相差越来越大,控制失效,落点远远偏离目标点；喷管扩散段破损达1/2,连带滚转舵机输出滞后90°时,飞行器会进入荷兰滚模态,随着飞行时间的增加,最终控制失效飞行器落点偏离目标点；喷管扩散段破损达1/2,喷管破损连带滚转舵机卡死时对飞行器弹道影响最严重,会使飞行器严重偏离目标落点；

Abstract:

This paper employs numerical simulation methods to investigate the impact of damage to the nozzle diffuser section of an aircraft engine on its flight trajectory, taking into account the influence on the rudder mechanism. Specifically, a thrust model for engine nozzle damage and a mathematical model for roll rudder failure induced by nozzle damage are established, and these are coupled and integrated into a six-degree-of-freedom dynamic model of the aircraft for comprehensive simulation. The results indicate that when the nozzle diffuser section is damaged by 1/2 and the roll rudder is functioning normally, the nozzle damage section will only produce a disturbance deviating from the theoretical trajectory in the direction of the damage. When the nozzle diffuser section is damaged by 1/2 and the roll rudder is jammed, the damaged section induces roll-pitch motion in the aircraft, leading to a growing discrepancy between the aircraft"s attitude and the designed attitude of the control system, resulting in control failure and a landing point far from the target. When the nozzle diffuser section is damaged by 1/2 and the roll rudder output lags by 90°, the aircraft enters a Dutch roll mode. As flight time increases, control failure occurs, and the landing point deviates significantly from the target. The most severe impact on the aircraft"s trajectory occurs when the nozzle diffuser section is damaged by 1/2 and the nozzle damage is accompanied by a jammed roll rudder, causing the aircraft to deviate significantly from the target landing point.