Intelligent hypersonic aircraft reentry maneuver guidance method and system

A hypersonic and aircraft technology, applied in the direction of neural learning methods, special data processing applications, biological neural network models, etc., can solve problems that affect aircraft maneuverability and time-consuming calculations

Pending Publication Date: 2020-11-03
中国人民解放军火箭军工程大学
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Problems solved by technology

However, this kind of antennae method is used to detect the antenna length in the initial stage of the aircraft's re-entry flight is much larger than the length of the ant

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  • Intelligent hypersonic aircraft reentry maneuver guidance method and system
  • Intelligent hypersonic aircraft reentry maneuver guidance method and system
  • Intelligent hypersonic aircraft reentry maneuver guidance method and system

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Embodiment Construction

[0084] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0085] The purpose of the present invention is to provide an intelligent hypersonic vehicle re-entry maneuver guidance method and system, which is used to improve the antennae detection method using intelligent waypoints and hypersonic gliding vehicles, so that it has better robust performance And it can greatly reduce the calculation time of maneuver guidance.

[0086] In order to make the above objects, features and advantages of the present invention more c...

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Abstract

The invention discloses an intelligent hypersonic aircraft reentry maneuver guidance method and system. The method comprises the following steps: establishing a hypersonic gliding aircraft reentry kinetic model based on a geocentric rectangular coordinate system; according to the hypersonic gliding aircraft reentry kinetic model, establishing a hypersonic gliding aircraft reentry maneuvering guidance problem model under multiple constraint conditions based on endpoint constraints and path constraints; for different no-fly zones, solving the hypersonic gliding aircraft reentry maneuvering guidance problem model under the multi-constraint condition by using a GPOPS II toolkit to obtain optimized trajectory data sets under different no-fly zone conditions; learning the optimized trajectory data set by using a deep learning algorithm to obtain an intelligent road waypoint model; and designing a maneuvering guidance law based on the intelligent road waypoint model, multi-antenna detection and sideslip angle transient. By means of the method and system, the expected maneuvering guidance effect of avoiding the no-fly zone can be achieved.

Description

technical field [0001] The invention relates to the field of reentry maneuver guidance for hypersonic gliding aircraft, in particular to an intelligent reentry maneuver guidance method and system for hypersonic gliding aircraft. Background technique [0002] The re-entry maneuver guidance of hypersonic glide vehicle under multiple constraints is one of the core and key points of hypersonic glide vehicle research. The research on maneuver guidance under the condition of incomplete no-fly zone information is not only of great practical significance, but also has far-reaching theoretical significance . [0003] At present, many powerful countries in the world have successively produced hypersonic vehicles, but it is still difficult to design a maneuvering guidance system for hypersonic gliding vehicles under multiple constraints. Achieving effective maneuver guidance is a challenging problem, especially when considering incomplete information about no-fly zones. [0004] In t...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06N3/04G06N3/08
CPCG06F30/15G06N3/08G06N3/045Y02T90/00
Inventor 蔡光斌徐慧高杨杨小冈李小锋黄月平
Owner 中国人民解放军火箭军工程大学
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