Analysis and design of missile attitude control with sensor local mode slope

【作者】 张欢； 任革学；

【Author】 Huan Zhang;Gexue Ren;Tsinghua University School of Aerospace Engineering;

【机构】 Tsinghua University School of Aerospace Engineering；

【摘要】 Missiles are typically slender in shape to reduce aerodynamic drag and exist a typical "non-collocated actuator and sensor" control problem. The Inertial Measurement Unit(IMU) onboard measures the attitude signals include rigid body motion, flexible vibration and local deflection at IMU mounting location and feeds these signals back into the control loop. These flexible vibration and local deflection signals degrade the control system stability,and in the worst case,make the control system unstable. Structural flexible interaction with attitude control system via sensor location mode slope. These effects become more significant as the slenderness ratio of the rocket increases. Various efficient and advanced attitude control law are proposed by designer and experts for missile beam model and make the flexible bending vibration stable. Due to the evident difference between local mode at sensor mounting location and total mode of missile model derived by beam elements exists, a missile dynamical system including the local 3-D FEM of control unit and base is derived. The influence of structural mode slope on control system is presented and mode slope at IMU sensor mounting location is the dominant influence to control system stability. Control system considering local mode slope is designed. Then the flight dynamic is simulated and verified by multibody dynamic solver INSIDES.更多还原

【Abstract】 Missiles are typically slender in shape to reduce aerodynamic drag and exist a typical "non-collocated actuator and sensor" control problem. The Inertial Measurement Unit(IMU) onboard measures the attitude signals include rigid body motion, flexible vibration and local deflection at IMU mounting location and feeds these signals back into the control loop. These flexible vibration and local deflection signals degrade the control system stability,and in the worst case,make the control system unstable. Structural flexible interaction with attitude control system via sensor location mode slope. These effects become more significant as the slenderness ratio of the rocket increases. Various efficient and advanced attitude control law are proposed by designer and experts for missile beam model and make the flexible bending vibration stable. Due to the evident difference between local mode at sensor mounting location and total mode of missile model derived by beam elements exists, a missile dynamical system including the local 3-D FEM of control unit and base is derived. The influence of structural mode slope on control system is presented and mode slope at IMU sensor mounting location is the dominant influence to control system stability. Control system considering local mode slope is designed. Then the flight dynamic is simulated and verified by multibody dynamic solver INSIDES.更多还原