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Embedded dual-core flight control software architecture method based on high-speed Linkport ports

A flight control and software architecture technology, applied in vehicle position/route/altitude control, software design, program control devices, etc., can solve problems such as poor system scalability and flexibility, low system reliability, system collapse, etc., to avoid Thread waiting causes timeout problems, reduces data volume, and improves real-time performance

Active Publication Date: 2017-05-31
SICHUAN AEROSPACE SYST ENG INST
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AI Technical Summary

Problems solved by technology

However, as applications become increasingly complex and control precision requirements continue to increase, limited system resources become the biggest bottleneck for system performance improvement
Through the analysis of the current traditional single-core flight control software, there are mainly the following shortcomings: 1) When a single CPU handles flight control tasks, due to the need to process a large amount of data, there is a problem of low real-time performance when a single core handles the above tasks; 2) Single-core When handling flight tasks, if there is a problem with the CPU, the entire system will crash, resulting in a problem of low system reliability; 3) When single-core processing flight tasks, because the system resources of the single-core itself are preempted by the flight tasks, the system expansion of the single-core Poor sex and flexibility

Method used

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  • Embedded dual-core flight control software architecture method based on high-speed Linkport ports
  • Embedded dual-core flight control software architecture method based on high-speed Linkport ports
  • Embedded dual-core flight control software architecture method based on high-speed Linkport ports

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[0032] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0033] Any feature disclosed in this specification (including any appended claims, abstract and drawings), unless expressly stated otherwise, may be replaced by alternative features which are equivalent or serve a similar purpose. That is, unless expressly stated otherwise, each feature is one example only of a series of equivalent or similar features.

[0034] The specific implementation manners of the present invention will be described in detail below in conjunction with the drawings and embodiments.

[0035] This embodiment discloses an embedded dual-core flight control software architecture method based on a high-speed Linkport interface, wherein the UAV dual-core flight control system uses two chips with double-precision floating-point capabilities based on the DSP6713B core, and uses th...

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Abstract

The invention discloses an embedded dual-core flight control software architecture method based on high-speed Linkport port. The method comprises the following steps: step one, dual-core flight control software task partitioning; step two, flight control software dual-core communication mechanism designing; step three, a flight control software dual-core data sharing mechanism; and step four, flight control software dual-core reliability designing. Flight control software architecture designing is carried out according to the method in a dual-core hardware condition, so that the single-core usage rate can be obviously reduced, the dual-core CPU occupancy rate trends to be average, and the program obtains higher time performance.

Description

technical field [0001] The invention relates to the field of UAV flight control software, in particular to an embedded dual-core flight control software architecture method based on a high-speed Linkport interface. Background technique [0002] The flight control computer is the core part of the UAV flight control system. With the expansion of the UAV flight envelope and the increasingly complex mission environment, new and higher requirements are put forward for the performance of the hardware platform and software platform of the flight control computer, and its performance directly determines whether the UAV is reliable. complete the flight mission. In the traditional control system, the single-core processor architecture is the mainstream. In addition to improving the response speed of the system by increasing the main frequency of the processor, software methods such as using a preemptive real-time operating system, introducing multi-threading, and improving system tas...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F9/44G06F11/36G06F11/07G05D1/10G06F15/17
CPCG05D1/101G06F8/20G06F11/0757G06F11/3692G06F15/17
Inventor 张波姚天问敖永才钟敏
Owner SICHUAN AEROSPACE SYST ENG INST
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