Gliding missile online closed-loop guidance method based on hp-RPM algorithm

Abstract

The invention belongs to the field of projectile guidance, and particularly relates to a gliding projectile online closed-loop guidance method based on an hp-RPM algorithm. Comprising the following steps: (1) calculating a multi-constraint optimal control law taking a current ballistic parameter as an initial condition by adopting an hp-RPM algorithm; (2) the measurement system takes the moment when the hp-RPM program runs each time as a sampling point, and the sampling period is equal to the hp-RPM algorithm calculation time in the current period; and (3) the attitude adjustment of the projectile is realized by controlling the rudder deflection angle, so that the uncertainty interference in the actual flight process is inhibited, and the fixed-point target striking of the projectile is realized. The method is used for inhibiting the influence of uncertain factors such as environment interference and model errors possibly occurring in the flying process of the gliding projectile on various parameters of a trajectory, the projectile achieves a preset terminal combat index, meanwhile, various constraints in the flying process are met, the principle is simple, implementation is easy, the projectile combat performance can be guaranteed, and meanwhile the performance of the gliding projectile is improved. And rapid and accurate guidance control and accurate target striking are realized.

Description

technical field [0001] The invention belongs to the field of projectile guidance, and in particular relates to an online closed-loop guidance method for gliding projectiles based on the hp-RPM algorithm. Background technique [0002] The gliding guided projectile is an unmanned aerial device that is guided and controlled by a navigation and guidance system to fly to a designated target. Ballistic optimization is to design a control mechanism that enables the projectile to achieve tactical indicators under specific constraints. Constraint conditions usually refer to certain ballistic parameters of the projectile in a certain stage of the flight process meeting the requirements, and tactical indicators usually include the range, accuracy, speed, and attitude of the missile when hitting the target. During the actual flight of the projectile, due to calculation errors, model errors and external interference, the actual trajectory of the projectile will deviate from the pre-calcu...

AI Technical Summary

Problems solved by technology

The existing feedback control for real-time optimization of nonlinear dynamic models needs to linearize the nonlinear system along the optimal trajectory to provide closed-loop feedback control, which will limit some performance of the system to a certain extent, such as reducing the maximum safe reachable area, etc.

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