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A multi-rotor aircraft based on coordinated control of rotor speed and variable pitch

A technology of multi-rotor aircraft and rotor speed, which is applied in the aviation field to achieve the effects of optimal energy efficiency, reduced control power consumption, and improved energy efficiency

Active Publication Date: 2017-11-14
BEIJING SANKUAI ONLINE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Also do not have the multi-rotor aircraft that can solve the above problems in the market at present

Method used

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  • A multi-rotor aircraft based on coordinated control of rotor speed and variable pitch
  • A multi-rotor aircraft based on coordinated control of rotor speed and variable pitch
  • A multi-rotor aircraft based on coordinated control of rotor speed and variable pitch

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Experimental program
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Effect test

Embodiment 1

[0027] One of the main goals of flight control is to achieve self-stabilization of the aircraft, that is, in a steady state, the aircraft can automatically correct the system's own steady-state error and external disturbances to maintain a stable flight attitude. Taking quadrotor as an example, such as figure 1 As shown in , the four rotors of the quadrotor are represented by A, B, C, and D respectively. Among them, a pair of rotors (A, D, B, C) on the diagonal have the same direction of rotation, and adjacent rotors have opposite directions of rotation. Through the rotors of opposite rotations, the sum of the counter-twist of the air effect on the rotors under the same pitch and rotational speed is zero, and the heading of the aircraft is guaranteed to be stable in a steady state. When the four rotors have the same pitch and the same speed and the lift force provided is equal to the body's own weight, hovering can be realized. By changing the pitch / speed of the rotors and a...

Embodiment 2

[0041] like Figure 4 Shown is a schematic diagram of the overall system structure of the electric variable pitch multi-rotor aircraft of the present invention, which is mainly composed of a main frame 1, a bracket 2, a motor mounting seat 3, a flight control system and a pitch control system 4. The design that differs from ordinary fixed-pitch quadrotors mainly lies in the variable-pitch system, among which the variable-pitch system (see Figure 5-6 ) includes: steering gear 7, rocker arm 9, connecting rod 10 and rotor clamp seat 8. The introduction of the steering gear is used to control the change of the pitch of the rotor. Practical applications show that the adjustment of the pitch of the rotor by the steering gear is much faster than the adjustment of the rotor speed, so the pitch control system realizes the rapid response of flight control.

[0042] The frame is composed of the main frame 1 and four brackets extending outward. The above brackets are evenly spaced to fo...

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Abstract

A multi-rotor aircraft based on the coordinated control of rotor speed and variable pitch, which includes a main frame, a bracket, a motor mount, a flight control system and a pitch control system, wherein the flight control system determines the lift control strategy according to the flight mode, and changes the pitch at the same time Adjust the lift of the rotor with the rotation speed. Due to the combination of the advantages of the rotation speed control and the variable pitch control, the response speed of the lift change and the energy efficiency of the rotor during flight control are improved, and the lift adjustment with optimal time and energy efficiency is realized, which improves the control response. Speed ​​and precision reduce control power consumption and optimize aircraft control performance.

Description

technical field [0001] The invention relates to the field of aviation technology, and more specifically, the invention relates to a multi-rotor aircraft. Background technique [0002] Because of its mechanical simplicity, stable flight, easy operation and miniaturization, multi-rotor aircraft has been widely used in recent years and has become a new type of electronic consumer goods and industrial equipment. Modern multi-rotor aircraft is driven by multiple motors, fixed-pitch rotors, and speed control is used to make the rotors generate different lifts to achieve flight control. This structure determines that its control bandwidth decreases with the increase of the moment of inertia of the rotor rotating mechanism, and due to the existence of the moment of inertia, the response speed of the speed adjustment is limited, which limits the flight performance of the multi-rotor aircraft, especially in terms of maneuverability . [0003] Variable-pitch aircraft can overcome the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/12B64C27/57B64C27/68
CPCB64C27/12B64C27/57B64C27/68B64U50/19
Inventor 赵恒徐志雄刘宝旭
Owner BEIJING SANKUAI ONLINE TECH CO LTD
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