Research On Trajectory Optimization & Guidance Of Gliding Guided Bombs

This paper follows the latest research achievements of gliding guid ed bombs,and combines the research situation of gliding guid ed bombs,the trajectory optimization method,and the mid-end guidance method with the needs of practical engineering problems.In view of the development characteristics of gliding guid ed bombs,the gliding guided bombs developed at home and abroad were inves tigated and analyzed.The development of trajectory optimization techniques,trajectory tracking methods,and adaptive guidance technologies with angle constraints were investigated and summarized.Firstly,the mission profile of the gliding guided bomb an d the conversion relationship between the coordinate system and the coordinate system involved in the modeling are introduced.The dynamics and kinematics equations of the gliding guided bomb are deduced,and the three are given on the premise of the instantaneous balance principle.The degree of freedom model serves as the basis for the development of trajectory optimization designs and guidance methods.Then the gliding guided bomb trajectory optimization method was studied.For the trajectory optimization problem,the application of sequential quadratic programming method is more extensive,but this method is greatly affected by the initial value,and the performance for solving complex optimization problems is not satisfactory.For this reason,the trajectory optimization method based on sequential convex optimization method is studied.This method converts the constraints of the original problem based on the trajectory linearization principle and has a high convergence speed.To optimize the optimality of the trajectory optimization,the trajectory tracking guidance law is required to support it.Therefore,the trajectory tracking guidance technology based on the adaptive dynamic surface is studied theoretically.The adaptive dynamic surface control principle based on backstepping method and multi-sliding sliding mode control is studied.The characteristics of no-driving underactuation control of gliding-guided bomb are also considered.The path-following control model is deduced and the hierarchical contr ol based on the traditional backstepping method is designed.The dynamic surface realizes compensation through adaptive estimation of modeling error and filtering error,and finally proves the stability of the guidance law.Aiming at the demand of angular constrained self-adaptive guidance with large falling angle and high precision under various interference deviations,the falling angle constrained terminal guidance technology based on non-singular fast terminal sliding mode was studied.Combining with the precise control of the falling angle,based on the analysis of the performance of each sliding mode function,the non-singular fast terminal sliding mode surface is selected to make the sliding mode asymptotically stable and meet the end angle constraint and the miss distance constraint.Using the approach law derived from the fast terminal sliding mode function transformation,the system trajectory can quickly converge from the initial state to the sliding mode surface,and the non-singular fast terminal sliding mode guidance law is obtained.Simulations for fixed targets and moving targets validate the effectiveness of the method.