自旋火箭弹横滚隔离系统的自抗扰控制

针对自旋火箭弹大俯仰角飞行情况下，斜坡或正弦扰动导致其横滚隔离系统的滚转陀螺超量程、隔离失效问题，提出了一种横滚隔离系统的自抗扰控制器。在建立采用PI控制器的横滚隔离系统数学模型的基础上，通过理论分析揭示了斜坡及正弦扰动导致滚转隔离失效的机理，并使用数学仿真对该失效机理进行了验证。设计了自旋火箭弹横滚隔离系统的自抗扰控制器，数值仿真结果表明，在自旋火箭弹大俯仰角飞行情况下，该横滚隔离系统可以有效应对斜坡或正弦扰动，并将横滚隔离系统的滚转角速度控制在1°/s的较小范围内，将滚转角控制在0°左右，保证了滚转隔离的有效性。

Active Disturbance Rejection Control of the Roll-isolated System of a Spinning Guided Rocket

Under large pitch angles, slope or sine interference disturbances can result in control failures of the roll-isolated system and saturation of the roll gyro. A roll-isolated active disturbance rejection controller (ADRC) is proposed for spinning rockets. Mathematical simulation and theoretical analysis of the PI roll-isolated system are used to reveal the mechanism of saturation of the roll gyro and the control failure. ADRC is designed for the roll-isolated system of the spinning rocket. Based on the numerical simulation results, the improved system is able to effectively handle slope or sine disturbances and ensure the effectiveness of roll isolation. The roll angular velocity can be controlled within a small range of 1°/s. The roll angle can be controlled at about 0°.