Control System Parameters Design And Ballistic Characteristics Analysis For Individual Simply Guided Rocket

Individual simply guided rocket plays an important role in modern war with its multiple applications, low cost and good damage effects. This kind of rocket mostly use the way of low-speed spinning to reduce the effect of thrust misalignment, mass eccentricity and asymmetrical aerodynamic force to trajectory. However, there will be a coupling phenomenon due to the spinning, which makes ballistic characteristics analysis and control system design to be a challenging issue. Consequently, this dissertation tries to carry out study on modeling and analysis of flight dynamics, trajectory optimization, guidance and control design and simulation for individual simply guided rocket system.First, in term of its feature of spinning, quasi-body coordinate and quasi-velocity coordinate systems are established. The 6DOF model of the rocket is established by analyzing the forces and moments acting on the rocket, which lays the foundation for the subsequent work in this dissertation.Second, considering the large distance-measuring error between the target and rocket, a research of trajectory optimization problem is carried out, and subsequently the trajectory optimization model, constraint condition and optimization objective are established. A kind of flat trajectory scheme is proposed, the optimal trajectory is achieved under the previous flight scheme by using the adaptive pseudo-spectral method. The result shows that the presented scheme has stronger robustness and broader applicability than traditional guide scheme.Third, disturbance equations and transfer functions are conducted by the linearization of the small perturbations, the responses to rudder and frequency characteristics of the rocket are analyzed. According to the factors and characteristics of coupling under the spinning condition, the steady rotation rate and control efficiency quantitatively are analyzed.Finally, based on the optimal trajectory, a virtual target tracking approach is proposed to track the reference trajectory, the guidance effectiveness of the presented method is evaluated by establishing an objective function, robustness analysis of the method is conducted. The decoupling law by means of feed forward and increment installation are designed, parameters of autopilot are obtained by using gain scheduling method. The simulation results indicate that guidance and control system meets the requirements of desired design. The research of this dissertation has important reference for further engineering design.