Unmanned aerial vehicle attitude control system, flight control system and attitude control method

An unmanned aerial vehicle and attitude control technology, which is applied in attitude control, control/adjustment system, non-electric variable control, etc., can solve the problems of unmanned aerial vehicle transportation, launch inconvenience, installation obstacles, etc.

Active Publication Date: 2021-02-09
成都云鼎智控科技有限公司
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AI Technical Summary

Problems solved by technology

At present, for UAVs that are long in shape and usually fly along their own length direction, the propulsion system and rudder system are usually set far apart in the length direc

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  • Unmanned aerial vehicle attitude control system, flight control system and attitude control method

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Embodiment Construction

[0025] The present invention will be clearly and completely described below in conjunction with the accompanying drawings. Those skilled in the art will be able to implement the present invention based on these descriptions. Before the present invention is described in conjunction with the accompanying drawings, it should be pointed out that:

[0026] The technical solutions and technical features provided in each part of the present invention, including the following description, can be combined with each other under the condition of no conflict.

[0027] In addition, the embodiments of the present invention involved in the following descriptions are usually only a part of the embodiments of the present invention rather than all the embodiments. Therefore, based on the embodiments of the present invention, those skilled in the art will not make any All other embodiments obtained under the premise of creative labor shall belong to the protection scope of the present invention...

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Abstract

The invention discloses an unmanned aerial vehicle attitude control system, a flight control system and an attitude control method. The unmanned aerial vehicle attitude control system is used for controlling pitching, yawing and rolling of an unmanned aerial vehicle, and comprises a main control system, a rudder system and a feedback system; the steering system is provided with at least three steering engines, the at least three steering engines are arranged at the tail of the unmanned aerial vehicle in a centralized mode, a rudder piece rotating shaft of each steering engine in the at least three steering engines is designed to be arranged in the mode of intersecting with the central axis of the tail of the unmanned aerial vehicle, and the included angles between any two adjacent rudder piece rotating shafts are equal. A rudder sheet driving control circuit of each steering engine in the rudder system is in signal connection with the main control system, and the rudder sheet of each steering engine in the rudder system is controlled by a corresponding attitude control instruction sent by the main control system to cooperatively rotate so as to enable the unmanned aerial vehicle torealize pitching, yawing and rolling motions required by attitude control; and the rudder system further comprises a steering engine positioning module.

Description

technical field [0001] The invention relates to an unmanned aerial vehicle attitude control system, an unmanned aerial vehicle flight control system and an unmanned aerial vehicle attitude control method. Background technique [0002] The flight control system of UAV usually includes main control system, propulsion system, rudder system and feedback system. Among them, the propulsion system is used to provide thrust to keep the UAV flying; the rudder system is used to realize the steering of the UAV; the main control system is used to control the operation of the propulsion system and the rudder system; the feedback system is used to feed back to the main control system Control results for unmanned aerial vehicles. The UAV flight control system needs to match the type of UAV. At present, for UAVs that are long in shape and usually fly along their own length direction, the propulsion system and rudder system are usually set far apart in the length direction of UAVs, which i...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0808
Inventor 唐冰刘以建
Owner 成都云鼎智控科技有限公司
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