摘要
运载火箭采用“X”形布局发动机或为面对称构型时,在周向上存在控制能力薄弱方向,后者会导致周向静不稳系数不同,当允许摆角较小时,在飞越大风区的过程中容易发生摆角限幅引发不可控风险,降低飞行可靠性。本文提出了一种一级飞行段带滚动角飞行的方案,通过滚动定向在最危险高度将最大控制能力方向对准风向,利用最大控制能力的同时,根据惯组加速度信息生成修正俯仰偏航程序角增量进行姿态调整,减小气流与箭体纵轴的夹角,实现减载的目的并降低摆角限幅的概率。
When the rocket adopts an X-shaped layout engine,or the shape is plane symmetry,the control capability in the circumferential direction is different and weakness exists in some directions,the latter renders static instability characteristic differences.In the scenario of small limits of engine swing angle,saturation is prone to occur during the flight over high-speed wind areas,causing the rocket uncontrollable and reducing the flight reliability.This paper proposed a method in which a rocket flight’s roll angle is adjusted by wind direction,allowing the rocket to coincide the maximum control capability direction with wind direction at the most dangerous altitude.By using an accelerometer to generate additional pitch and yaw program angles,the rocket could utilize attitude adjustment to reduce the angle between the airflow and the longitudinal axis,which can successfully reduce the probability of engine saturation and aerodynamic load simultaneously.
作者
张志平
王道勇
薛宇
修观
匡东政
ZHANG Zhiping;WANG Daoyong;XUE Yu;XIU Guan;KUANG Dongzheng(Shanghai Aerospace System Engineering Institute,Shanghai 201109,China)
出处
《上海航天（中英文）》
CSCD
2023年第S01期28-32,共5页
Aerospace Shanghai（Chinese&English）
关键词
火箭
姿态控制
主动减载
滚动定向抗风
程序角修正
rocket
attitude control
load relief
rolling orientation anti-wind
program angle correction
作者简介
张志平(1991—),男,博士,主要研究方向为运载火箭姿态控制。
