Research On Sensor Layout And Adaptive Augmenting Control Of A Launch Vehicle

In order to meet the needs of missions such as manned moon landings and deep space exploration,it is imperative to develop heavy launch vehicles.Heavy-duty launch vehicles have their unique dynamic characteristics than traditional launch vehicles.On the one hand,the frequency of elastic vibration modes is lower and the low-order elastic vibration modes are dense;on the other side some key dynamics model parameters cannot be accurately obtained,and these parameters will change during the flight process.The above factors increase the difficulty of the launch vehicle attitude controller design.In this work,the sensor layout optimization and adaptive augmentation control of a heavy launch vehicle are carried out to solve the above problems.The main research contents are as follows:(1)Dynamic modeling of a heavy launch vehicle.The Newton-Euler method is used to establish the rigid body dynamic equations in the launch channel of the launch vehicle.Based on this model,the elastic vibration is introduced to obtain the rigid-elastic coupling dynamic equations of the launch vehicle pitch channel.(2)Sensor layout optimization.The strength of the additional attitude signal generated by the elastic vibration in the measurement signal,is depending on the positions of sensors.A good sensor layout can effectively eliminate or reduce the elastic component in the measurement signal,thereby reducing the design difficulty of the rocket attitude controller and improving control effect.Taking the layout of a two-rate gyro sensor as an example,the sensor layout optimization algorithm is studied,and the internal mechanism of the algorithm is developed.Based on the optimization of the sensor layout,the controller and the correction network are designed for the rocket attitude dynamic model,and a variety of working conditions are simulated to verify the effectiveness of the above design.(3)Adaptive Augmenting Control(AAC)mechanism analysis and controller design.The mechanism of action of AAC is analyzed in detail,and the stability proof is provided for the basic form of AAC.Based on the improvement of the controller structure,the advantages of the improved form are studied.In order to improve the attitude control performance of the launch vehicle,the adaptive augmentation controller was designed.The adaptive augmented controllers based on both the basic form and the improved form are studied separately,and the effectiveness of the designed controller is verified by combining a variety of typical working conditions.At the same time,it is compared with the traditional attitude controller of the PD + correction network form.Simulation results show that adaptive augmented control can effectively reduce the impact of parameter uncertainty on attitude control,and the control performance is better.