Missile Trajectory Design And 3D Realtime Simulation

Missile Trajectory Design and Simulation, as one of the important subjects of the development and testing of a missile, provides many important performance and parameter bases for general missile design and plays an important role throughout all the phases of a missile development and testing. With the increasing development and complexity of missile armed Equipment, how to obtain the variation of the parameters of the ballistic trajectory through effective simulation means, is an important subject to evaluate and study the performance of the corresponding guidance law and control system, which put forward many higher requirements for Modeling and Simulation of the ballistic trajectory. Based on this background, this paper mainly researched on the design of guidance law and Numeric Calculation of the ballistic trajectory under the condition of small perturbations, then designed and developed a 3D real-time simulation platform for its simulation verification. And the simulation results performed well in real-time, human-computer interaction, and the 3D effect. Firstly, this paper briefly introduced the basic knowledge related, including the definition of coordinate systems and conversion relationship among them, the forces and torques acting on the missile, etc. and deduced the simplified equation of motion under the ballistic coordinate system finally. Secondly, this paper researched on the standard trajectory design and its numerical calculation. The standard trajectory is the missile’s expected ballistic trajectory under the standard conditions. Firstly, a missile’s overall parameters, its flight mission and its aerodynamic parameters were obtained by a relevant literature. Then, based on these data, aerodynamic parameter Calculation and standard ballistic trajectory design were carried out. Finally serial numerical calculations were introduced briefly, then the numerical calculation of the standard trajectory was realized by programming and the dynamic change regularities of the related motion parameters were obtained. Thirdly, this paper researched on the Perturbed Guidance Law under the condition of small perturbations. In the reality, there are always many deviations between the missile’s real flight conditions and the standard conditions, which can be considered as small perturbations effected on the missile when they are very small.And these deviations can make the real ballistic trajectory deviated from the standard trajectory when no Guidance Law is applied. Thus, the Perturbed Guidance Law was applied to correct the impacts caused by these small perturbations in this paper Firstly, the missile’s motion models were linearized, according to the small perturbations theory. Then, the optimal feedback gain- K and corrected guidance command- ?u at each sampling time were calculated by LQR optimal guidance law. As a result, the missile could still flight around the standard trajectory until the missile-target encounter under the condition of these small perturbations. Finally, a missile 3D real-time simulation platform was designed and developed based on the Networked Control System Lab –NCSLAB. The platform can be used in the real-time simulation of Missile Trajectory and Web access and 3D monitor display. Then, based on MATLAB/Simulink, a control program of the missile longitudinal motion according to the 3rd and 4th chapter’s knowledge for the simulation verification of the platform was designed, and the simulation results performed well.