To improve the target capture speed of the guided projectile under the condition of large landing angle and reduce the angle deviation of the starting point of the terminal guidance

considering the terminal guidance section

a trajectory programming method considering multiple constraints of the seeker (TPM-CS) is proposed based on the traditional guided projectile trajectory programming method (TPM). The starting point constraint of the terminal guidance is established according to the maximum detection distance of the seeker

and the attack path constraint is established according to the geometric relationship between the projectile and the target as well as the angle of view of the seeker. Additionally

an objective function of minimizing the amplitude of leading angle and the amplitude of control variables is established. In order to achieve the best matching of parameters such as the initial trajectory inclination angle

deflection angle

rocket ignition time

gliding start-up time and seeker opening time of the guided projectile

a five-phases trajectory programming model is established

and the multi-phases Radau pseudo-spectrum method is used to transform the trajectory programming problem into a nonlinear programming problem. Finally

the nonlinear programming solver SNOPT is used to solve the problem. The seeker with different constrains parameters is selected for simulation

and the effect of the maximum detection range of the seeker and the angle of view of the seeker on the trajectory of the scheme are analyzed. The method proposed in this paper is compared with the traditional trajectory programming method for simulation. The simulation results show that compared with the traditional method

the initial angle deviation of the terminal guidance of the proposed trajectory programming scheme is reduced by 71.590%

and the time for the seeker to keep the target illuminated is prolonged by 6.120 times

which verifies the effectiveness and superiority of the proposed trajectory programming method.