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Quick high-precision simulation method for flight profile of unmanned aerial vehicle

A simulation method and UAV technology, applied in the field of flight mechanics, to achieve the effect of fast and high-precision simulation evaluation

Pending Publication Date: 2021-05-14
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
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Problems solved by technology

[0004] The purpose of this application is to provide a fast and high-precision simulation method for UAV flight profiles to solve at least one problem in the prior art

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  • Quick high-precision simulation method for flight profile of unmanned aerial vehicle
  • Quick high-precision simulation method for flight profile of unmanned aerial vehicle

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Embodiment Construction

[0028] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the technical field of flight mechanics, and particularly relates to a quick high-precision simulation method for a flight profile of an unmanned aerial vehicle. Comprising the steps of 1, constructing a simulation calculation model, performing parameter initialization on the simulation calculation model, and defining a flight profile simulation calculation ending position; step 2, acquiring current flight state parameters of the unmanned aerial vehicle, wherein the flight state parameters comprise position parameters; 3, judging whether the flight state parameters reach a flight profile simulation calculation ending position or not, if yes, ending, and if not, continuing; 4, acquiring a current flight stage according to a position parameter in the flight state parameters; 5, determining a flight constraint mode according to the current flight stage, and calculating a time step length based on the capability characteristics of the platform; 6, the simulation calculation model calculates the current flight state parameters according to the time step length; and 7, returning to the step 2 until an end condition is met. The calculation precision and the calculation efficiency are improved.

Description

technical field [0001] The application belongs to the technical field of flight mechanics, and in particular relates to a fast and high-precision simulation method for the flight profile of an unmanned aerial vehicle. Background technique [0002] The flight profile of a conventional UAV mainly includes three stages: climb, cruise, and slide. The flight modes and platform capability characteristics of each stage have different requirements for the simulation step size, resulting in slow calculation speed under small step size and calculation accuracy under large step size. low, and even cause system divergence. [0003] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art. Contents of the invention [0004] The purpose of this application is to provide a fast and high-precision simulation method for the flight profile of an unmanned aerial vehicle, so as to solve at least o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F111/04
CPCG06F30/20G06F2111/04
Inventor 孙智孝刘云飞白杨张世辉刘泽石
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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