基于信号辨识的运载火箭实时减载控制技术

The In-Flight Load Relief of Launch Vehicles Based on the Signal Identification

运载火箭在高空风区域飞行时,其自身结构载荷的约束对气动载荷提出了控制要求,为了降低高空风对运载火箭飞行的影响,减小运载火箭的气动载荷,保证其在高空区飞行的安全可靠,提出了一种简单可行的实时减载控制方法。首先,通过非线性状态观测器估计方法,获得箭体绕质心运动的角加速度信号以及捷联惯组相对质心的位置,计算出箭体绕质心运动产生的线加速度信号;其次,从运载火箭上捷联惯组测量到的视加速度信号中减去箭体绕质心运动产生的线加速度信号,消除箭体绕心运动产生的影响,进而获得箭体质心位置附近的视加速度信号,参与实时减载控制。仿真验证了该控制方法可以有效降低运载火箭的气动载荷,提高了运载火箭在高空风区域飞行的适应能力。

During the launch vehicle flying at high altitude wind area,the control requirements on aerodynamic load are proposed because of its structural load constraints. In order to reduce the effects of high altitude wind to the launch vehicle flight,reduce the vehicle aerodynamic load and ensure its safe and reliable in the high altitude area,a simple and feasible load relief method is presented in this paper. First of all,the algorithm involves an estimate of angular acceleration at the center of gravity through the use of nonlinear state observer,and obtains the location of the IMU related to the center of gravity and calculates the acceleration caused by angular acceleration. Secondly,the sensed acceleration through the IMU subtracts the term about angular acceleration,and the algorithm eliminates the adverse effects caused by angular acceleration,gets the acceleration at the center of gravity and then participates in load relief control. This control method can effectively reduce the aerodynamic load of the launch vehicle and improve its adaptability in the area of high altitude wind area.