Method for designing quasi-gliding trajectory based on landing angular velocity constraint

Abstract

The invention discloses a method for designing a quasi-gliding trajectory based on landing angular velocity constraint, which comprises the following steps of: constructing a simulation model to forma quasi-gliding trajectory with a climbing stage, a maneuvering guidance stage and an aiming stage; initializing design parameters of the aircraft model; after the aircraft model simulates flight on the quasi-gliding trajectory according to the initialized design parameters and preset control conditions, the actual landing speed, obtaining the actual firing range and the trajectory of the quasi-gliding trajectory of the aircraft model; judging whether the actual falling speed, the actual firing range and the form of the trajectory formed in the maneuvering guidance stage meet preset conditionsor not, and if so, determining that the corresponding design parameters meet expectation; if not, correspondingly updating the design parameters, and enabling the aircraft model to simulate flight again on the simulated gliding trajectory according to the updated design parameters until all the design parameters meet the expectation; and outputting the design parameters updated last time to finish the design of the simulated gliding trajectory.

Description

technical field [0001] The invention relates to the field of simulated ballistic design, in particular to a design method of a quasi-gliding ballistic based on corner velocity constraints at landing. Background technique [0002] In order to achieve the purpose of reducing costs and improving penetration and damage capabilities, modern missile technology usually requires missiles to have specific flight attitudes while being able to accurately hit the target, such as anti-tank missiles vertically hitting weak front armor, anti-ship missiles from the side Attack ships etc. [0003] The Chinese patent with the application number 201811394403.3 discloses a trajectory optimization method with constraints. The trajectory optimization method is used to reduce the transition speed of the interceptor mid-term guidance. The method includes the following steps: according to the set constraints In order to optimize the trajectory of the mid-guidance, the full trajectory motion equatio...

AI Technical Summary

Problems solved by technology

In this patent publication, when there is a difference between the height of the interception and the height of the target, different constraint strategies are adopted, and the optimization design method involves many variables, and the optimization design method is relatively complicated

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