Adaptive Attitude Control Of Launch Vehicle Considering Uncertainty

With the progress of human society and the development of technology, aerospace technology get rapid development to be Benchmark measure of a country’s comprehensive national strength, launch vehicle is the most important means to enter space, launch vehicle attitude control system is the basement for sending payload the target. Based on the background of the attitude control system of the launch vehicle, designs for the attitude of adaptive control technology are investigated in detail.There are many uncertainty factors during the flight of the launch vehicle. For example the change of the flight height of launch vehicle, flight velocity, atmospheric conditions and the rocket body interference in the internal structure. All of these lead to a large degree of uncertainty in kinetic coefficient. These uncertainties may lead to deterioration of the control system in actual operation therefore adaptive control theory was used to the attitude control of launch vehicle. In this paper we study the uncertainty of rigid body first. Based on the theory of Lyapunov stability and Popov stability theory we design the model reference adaptive control system and give the corresponding adaptive control law. Then study the uncertainty of elastic vibration, based on recursive least squares method, design the adaptive notch filter. Finally combining the above two methods replace traditional PD controller and traditional structure filter in the attitude control system realize adaptive control system. The simulation results show that the design of the adaptive control system for a given range of uncertain model parameters and the frequency of elastic vibration, has maintained a stable margin and control performance, compared with the conventional attitude control system to the uncertainty of better adaptability and robustness. In this paper, the research will provide the beneficial reference for our new generation of large launch vehicle attitude control system.