Large-airspace high-dynamic navigation guidance and control integrated system and method

Abstract

The invention relates to a large-airspace high-dynamic navigation guidance and control integrated system and method. The system comprises an optical fiber inertia measurement unit, a multimode GNSS satellite receiver, a dual-core embedded flight control computer, a high-overload-resistant miniature black box, a combiner, a dual-path satellite antenna, a secondary power supply conversion module, abase and a shell. A navigation guidance and control program is run in the dual-core embedded flight control computer, the navigation program adopts a robust Kalman filtering algorithm to adjust Kalmanoptimal gain and posterior estimation error covariance on line, and the guidance and control program adopts a scheme attack angle on-line planning and self-adaptive control parameter design method. The system has the advantages of low cost, high integration level, small volume, high overload resistance, simplicity, economy, reliability and the like.

Description

technical field [0001] The invention belongs to the technical field of navigation guidance and control, and in particular relates to a large airspace high dynamic navigation guidance and control integrated system and method. Background technique [0002] With the normalization of high-intensity and high-density launches of launch vehicles around the world, more and more mature launch technologies have prompted people to explore the direction of low launch costs. Recycling and reuse of launch vehicles is one of the effective ways to reduce launch costs; at the same time When a traditional carrier rocket is launched, it is usually necessary to determine the range of the rocket wreckage landing area, and select a sparsely populated area of ​​more than one thousand square kilometers for evacuation of personnel, to facilitate the search for wreckage and reduce secondary accidents caused by wreckage. With the rapid economic development, It is very important to make the launch vehi...

AI Technical Summary

Problems solved by technology

[0003] The traditional navigation and guidance control system usually installs each subsystem independently and adopts a distributed structure, resulting in low integration and large volume of the system as a whole. Overall impact performance considerations, which affect the overall energy efficiency of the system

[0004] Existing public patents such as "flight control and navigation all-in-one machine" realize partial integration of navigation and control modules, but are usually used in the field of drones or missiles. , launch characteristics, system functions, etc. are inconsistent with the present invention, are not comparable, and cannot be used for the vertical recovery of the launch vehicle sub-stage and the precise control of the landing area

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