Multiphase trajectory optimization for gun-launched glide guided projectiles

Abstract

In this paper, an approach that considered both the continuous and discrete variables using the Gauss pseudospectral method is presented for multiphase trajectory optimization of gun-launched glide guided projectiles. The entire projectile trajectory is divided into four flight phases that connect to each other sequentially to ensure continuity. Continuous variables are utilized to describe the projectile's state and control. Meanwhile, discrete variables are proposed to express the initial flight path angle and switching times between different flight phases. The trajectory optimization problem is posed as a constrained multiphase nonlinear optimal control problem, which is then transcribed into a nonlinear programming problem using the Gauss pseudospectral method and is finally solved using the interior point algorithm. Simulation results demonstrate the feasibility and effectiveness of this approach, as well as a detailed analysis of the key features of the trajectory parameters.

Correction-Efficiency-Coefficient-Based Trajectory Optimization for Two-Dimensional Trajectory Correction Projectile

“…Costello M [12] took the falling velocity as the constraint and the maximum range as the objective function to optimize the trajectory of the guided projectile. Based on the Gaussian pseudo-spectral method (GPM), Chaoyue Liu [13] et al proposed a multistage trajectory optimization method to optimize the multistage trajectory of a two-stage booster rocket and obtain the feasible optimal trajectory; Qi Chen [14] et al optimized the multiphase trajectory of a gliding guided projectile by considering continuous and discrete variables; Qiuping Xu [15] et al optimized the gliding trajectory of a gliding guided projectile by using the compose efficiency factor model; Bradley T. Burchett [16] et al designed a trajectory prediction method that can accurately and quickly predict the trajectory of a rotating stable projectile with high launch height and transonic speed; based on the maximum/minimum principle, J Yao [17] et al deduced the trajectory correction optimal control strategy with minimum undershoot and minimum energy as an objective function. Yu Wu [18] et al proposed a hybrid PSO-GPM algorithm to deal with the reentry trajectory optimization problem.…”

Stabilized Inertial Guidance Solution for Rolling Projectile Based on Partial Strapdown Platform

“…A miniature rugged integrated GPS/INS has been applied in short-range, slow-rolling rockets and missiles [14]. An air-to-surface tactical missile named the High-Speed Anti-Radiation Missile (HARM) has received a GPS/INS upgrade that improves its effectiveness and minimizes friendly-fire accidents [15].…”