Research On Design Of Integrated Missile Precision Guidance And Control For Maneuvering Target Defense

Further development of missile guidance and control system is an important prerequisties for the fast and precision attack weapon system. Realizing the design of integrated missile guidance and control system is of much significance with the increasing maneuverability of the target intercepted by missile, which requires full considerations of the interaction between guidance system and control system, and then the missile’s overall performance is greatly improved.With the background of the the low endo-atmospheric interception diving phase between some homing missile and maneuvering target, this thesis focuses on the research of missile guidance and control system traditional design method, approximate integrated guidance and control(IGC) design method and IGC design method by proposing some new and improved sliding mode control(SMC) techniques based on combining the existing SMC theories with dynamic surface control and active disturbance rejection control design concepts. The main results consist of the following four parts:First of all, missile six degrees of freedom nonlinear equations, relative kinematical model between missile and target and missile control system design model are deducted. Based on the three-channel independent design idea and by adopting the longitudinal and lateral accelerations to be the effect between the guidance system and the control system, the integrated guidance and control model for three-channel independent design is established, where the coupling items between three channels are regarded as the uncertainties with unknown bounds. Further, the integrated guidance and control model for three-channel coupling design is established from the point of view of nonlinear systems, which builds a veritable integrated model of the missile guidance and control systems.Then, the research on traditional missile guidance and control system design method is carried out. Based on finite time convergence theorem, a novel missile sliding mode guidance law on the basis of extended state observer(ESO) is derived to intercept maneuvering target, which is addressed by real-time estimation and dynamic compensation to target maneuvering acceleration via ESO. Meanwhile, based on dynamic surface control and SMC, an improved missile autopilot design approach is introduced, which doesn’t rely on time separation principle. The afore-mentioned missile control system is inset into sliding mode guidance system to achieve the goal of traditional missile guidance and control system design and realize the effective attack against maneuvering target in three-dimensional space.Sequentially, an improved global integral sliding mode control technique is presented, which solves the problem of the system transient performance deterioration and decreases steady state errors because of a combination of the advantages of integral sliding mode control and global sliding mode control. And then accounting for the autopilot dynamics and impact angle constraints, a novel global nonlinear integral sliding mode guidance law is proposed by introducing dynamic surface control method during the diving phase of missile when attacking maneuvering target, which comprehensively achieves IGC approximate design. Compared with traditional integral sliding mode guidance law and biased proportional navigation guidance law, simulation results verify the effectiveness and superiority of the proposed IGC approximate design.Finally, the design problem of integrated missile guidance and control is considered from two aspects, that is, IGC three-channel independent design and IGC three-channel active decoupling design. For the three-channel independent design problem of IGC, an adaptive dynamic surface control algorithm for the IGC subsystems of the pitch, yaw and roll channels is proposed with concerning all subsystems with unmatched uncertainties, respectively. Furthermore, the modified version of adaptive dynamic surface control technique is also given for IGC three-channel independent design, where the perturbations of the aerodynamic parameters are explicitly considered. In addition, IGC three-channel coupling design problem can be treated as a states regulation problem of a nonautonomous nonlinear system with matched/unmatched uncertainties. Based on ESO and sliding mode-dynamic surface control design method and by introducing ESO to estimate and compensate dynamic coupling items and uncertainties, an IGC three-channel active decoupling design approach based on ESO is generated, which realizes the active decoupling between each channel in the missile system. Compared with IGC three-channel independent design method and traditional guidance and control system design method, the simulation results validate the advantages and practicalities of IGC three-channel active decoupling design approach...