Level flight transition section guidance control method

Abstract

The invention discloses a level flight transition section guidance control method. The method includes the following steps of S1, online planning a trajectory, wherein the change trajectory of a missile is planned according to a certain rule after conditions for entering a transition section are met with the current skyward acceleration aH, skyward velocity VH and altitude H as initial states andthe preset level flight altitude HT and the tail end skyward velocity VH(tend) and the acceleration aH(tend) of the transition section as constraints; S2, pre-correcting guidance, wherein required overloads are calculated according to the difference value of the current skyward velocity VH and altitude H of a loitering munition and the preset level flight altitude HT, the missile is controlled togenerate corresponding overloads, and it is ensured that the missile stably enters the transition section; and S3, guiding the transition section, wherein after conditions for entering the transitionsection are met, a standard altitude and skyward speed trajectory generation instruction of the transition section is generated according to the planned trajectory, and trajectory tracking is realizedthrough altitude and speed control until the missile shifts to the level flight section. By means of the method, by online planning an altitude channel of the missile and tracking the missile in realtime, it is ensured that the loitering munition stably shifts from the transition section to the level flight section.

Description

technical field [0001] The invention relates to the field of missile guidance and control, in particular to a guidance and control method for a level flight transition section. Background technique [0002] Loitering missiles are the product of the combination of advanced missile technology and UAV technology. They can quickly reach the target area and perform single or multiple tasks such as patrol flight, reconnaissance and surveillance, damage assessment, air wireless relay and attacking targets. A smart ammunition with distinctive features that can meet the needs of future information-based operations. After the cruise missile is launched with rocket boost, it needs to go through a period of ballistic flight, and then turn to a predetermined altitude to enter the cruising state. The engine is turned on at the right time and flies to the target area. During the transition from ballistic flight to cruising flight, due to the existence of various deviations, it is impossib...

AI Technical Summary

Problems solved by technology

However, the anti-interference ability of the stability control loop itself is relatively limited, and the convergence time of the guidance law is relatively long, so it is difficult to achieve the desired effect.

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