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Multi-rotor drone control system and method with tiltable wings and rotors

A multi-rotor UAV and control system technology, applied in the field of multi-rotor UAV and control system, can solve problems such as solving difficulties

Inactive Publication Date: 2016-03-02
HEFEI INSTITUTES OF PHYSICAL SCIENCE - CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Based on the coupling effect of the existing design layout, this relationship is described by a set of nonlinear equations, which may lead to difficulties in solving

Method used

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  • Multi-rotor drone control system and method with tiltable wings and rotors
  • Multi-rotor drone control system and method with tiltable wings and rotors
  • Multi-rotor drone control system and method with tiltable wings and rotors

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Embodiment Construction

[0058] The present invention will be further described below by taking the six-rotor UAV as an example.

[0059] Such as figure 1 As shown, a tiny six-rotor UAV with tiltable wings and rotors includes a fuselage 1, two wings 2 symmetrically arranged on the left and right sides of the fuselage 1, and symmetrically arranged on the fuselage 1 Four connecting rods 3 and six rotors 4 in the periphery, the rotors 4 are composed of rotor paddles 41 and rotor motors 42, and the rotor motors 42 adopt DC brushless motors. Two of the rotors 4 are respectively symmetrically installed on the ends of the two wings 2 away from the fuselage 1 , and the remaining four rotors 4 are respectively symmetrically installed on the ends of the four connecting rods 3 away from the fuselage 1 .

[0060] Fuselage 1 adopts a streamlined hollow cylinder structure to reduce air resistance during flight. The wing 2 is rotatably connected to the fuselage 1, and its plane shape is rectangular. The two wings...

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Abstract

The invention provides a multi-rotor unmanned airplane with inclined wings and rotors. The structure of the unmanned airplane comprises a plurality of rotors, a pair of wings and two rotors, wherein the plurality of rotors are arranged on a connecting rod, the wings are symmetrically arranged on the left and right sides of a fuselage and can be inclined between the directions perpendicular to the fuselage and parallel to the fuselage, and the two rotors are installed on the wings and can be synchronously inclined with the wings. The invention further provides a control system and a control method of the multi-rotor unmanned airplane with the inclined wings and the rotors. The attitude of the unmanned airplane provided by the invention is fully completed by a rotor system which is symmetrically arranged on the connecting rod, the rotors arranged on the wings only provide thrust, the attitude is not influenced, thereby decoupling the attitude control and the speed control, the complexity and the control difficulty of a dynamic model are reduced, additional lifting force is provided by utilizing an aerodynamic effect of the wings, and the flight speed, the bearing capacity and the endurance efficiency of the multi-rotor unmanned airplane are improved.

Description

technical field [0001] The invention relates to the technical field of aviation power machinery, in particular to a multi-rotor unmanned aerial vehicle with tiltable wings and rotors, a control system and a method. Background technique [0002] Combined with the advantages that helicopters can take off and land vertically in a small space, hover, and fixed-wing aircraft can use the aerodynamic effect of the wings to generate lift to improve performance, since the 1950s, people began to develop a combination of these two advantages. Manned aircraft with variable structure. Most of these aircraft adopt the fuselage design of traditional fixed-wing aircraft, and two angles of rotors that can be tilted forward are installed at the ends of the two main wings. When taking off and landing, the rotor faces up to provide lift; while in level flight in the air, the rotor face tilts forward until it is perpendicular to the fuselage, providing horizontal thrust, thereby generating lift...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/22
Inventor 刘明魏璇刘海伟双丰
Owner HEFEI INSTITUTES OF PHYSICAL SCIENCE - CHINESE ACAD OF SCI
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