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Redundancy arbitration switching method and system of unmanned aerial vehicle and computer equipment

A technology of unmanned aerial vehicles and redundancy, which is applied in the direction of control/adjustment system, vehicle position/route/height control, non-electric variable control, etc. It can solve problems such as system program operation errors and failures, and improve redundancy Effect

Pending Publication Date: 2021-07-13
ZHEJIANG LAB +1
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  • Claims
  • Application Information

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Problems solved by technology

[0004] Aiming at the deficiencies of the prior art, the present invention proposes a redundant degree arbitration switching method, system and computer equipment for unmanned aerial vehicles, which are used to solve the problems caused by the failure of the main controller and the operation error of the system program during the flight of the unmanned aerial vehicle. Not only that, but the redundancy arbitration switching system can also be used for the optimal control of multi-sensors to realize data optimization and other algorithms, so as to screen out the optimal control system to meet the needs of different users

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  • Redundancy arbitration switching method and system of unmanned aerial vehicle and computer equipment
  • Redundancy arbitration switching method and system of unmanned aerial vehicle and computer equipment
  • Redundancy arbitration switching method and system of unmanned aerial vehicle and computer equipment

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[0025] The present invention will be described in detail below with reference to the accompanying drawings and preferred embodiments, and the purpose and effect of the present invention will become clearer. It should be understood that the specific embodiments described here are only used to explain the present invention and are not intended to limit the present invention.

[0026] The redundant degree arbitration switching method, system and computer equipment of unmanned aerial vehicles proposed by the present invention are applicable to various types of unmanned aerial vehicles. The unmanned aerial vehicles involved in the method and system of the present invention include several flight control subsystems, each Each flight control subsystem includes a UAV dynamic model, and the UAV dynamic model includes an attitude control loop and a position control loop. The method, system and equipment of the present invention will be described below by taking an eight-rotor UAV as an e...

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Abstract

The invention discloses a redundancy arbitration switching method and system of an unmanned aerial vehicle and computer equipment, the unmanned aerial vehicle comprises a plurality of flight control subsystems, each flight control subsystem comprises an unmanned aerial vehicle power model, and the unmanned aerial vehicle power model comprises an attitude control loop and a position control loop; the redundancy arbitration switching method comprises the following steps: receiving sensor data corresponding to a plurality of flight control subsystems in real time; performing fault-tolerant control on the sensor data, and determining corresponding optimal flight attitude data; and screening out an optimal control system based on the optimal flight attitude data so as to switch the optimal control system to perform flight control on the unmanned aerial vehicle in the current control period. The redundancy of the unmanned aerial vehicle sensor and the robustness of the unmanned aerial vehicle control system can be improved, and it is ensured that the multi-rotor unmanned aerial vehicle can safely and stably execute a certain specific task.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicle control, in particular to a method, system and computer equipment for redundancy arbitration switching of unmanned aerial vehicles. Background technique [0002] The quality of the flight control system (Flight Control System) directly determines whether the UAV can complete the scheduled flight mission, and the flight control computer (Flight Control Computer) is the core of the flight control system. The flight control computer collects original information such as airframe attitude, speed, and position from the on-board sensors, performs navigation calculations, and then performs control law calculations, and finally outputs control signals to the actuators to control the aircraft to fly according to the scheduled mission. Respond to mission devices. However, with the application of UAVs in military and industry, some missions are performed in extremely harsh environments, and the tasks ...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/101
Inventor 胡易人马宏军蔡建东谢安桓徐少杰
Owner ZHEJIANG LAB