High-performance missile synthesis with trajectory and propulsion system optimization

Abstract

Synthesis of a high-performance two-pulse-motor-propelled missile by simultaneous optimization of trajectory and propulsion systems in two operational scenarios is described. This work employed a quasiNewton parameter optimization scheme with penalty functions to meet terminal and path constraints. The trajectory control variables were parameterized using piecewise linear open-loop commands and piecewise constant linear feedback gains. The pulse motor parameters optimized were pulse split, average thrust levels, neutrality factors, pulse burn times, and the interpiilse delay. Optimization of the rocket motor thrust time curve in addition to the trajectory increased the range by up to 11% when compared with the trajectories optimized with originally specified rocket motor propulsion data.

A Novel Optimal Control Method for Impulsive-Correction Projectile Based on Particle Swarm Optimization

“…(5) Update the velocity of the variables in particles in terms of (10) and the position by using (11).…”

“…Nowadays, numerical optimization controls are categorized into two different classes with their own advantages and characteristics, that is, direct method based on mathematical programming and parameterization of state and control histories and indirect method grounded on solution of two-point boundary value problem (TPBVP) using optimal control principle [11][12][13]. They are of probability to be applied for achieving an optimal performance of such problem.…”

Velocity Control for Coning Motion Missile System Using Direct Discretization Method

“…With the advent of computers and evolution of modern theories of optimal control, the numerical computation techniques for optimal atmospheric trajectories have been an active research area since the early 1970s. The approaches on trajectory optimization are of two distinct categories such as direct method based on the mathematical programming and parameterization of state and control histories and the indirect method grounded on the solution of two-point boundary value problem (TPBVP) using optimal control principle [16][17][18]. Because the guess of the initial values of costate variables is random and there is a lack of physical implication, the TPBVP is difficult to solve especially when the optimal system is accompanied with high nonlinearity and multiple constraints (e.g., nonlinear trajectory optimization problem).…”

Energy management for multiple-pulse missiles

“…This method has been used to determine the range maximal motor parameters and open-loop trajectory shaping of a twopulse air-to-surface missile. 7 In that work the solution was subject to minimum dynamic pressure and average speed constraints for the high-altitude mission and a maximum altitude limit for the low-altitude mission.…”