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Variable-pitch aircraft

A technology of variable-pitch aircraft and fins, which is applied in the field of aerial photography, can solve the problems of difficult control of rotor synchronization, heavy weight of unmanned aerial vehicles, and unclear aerial photography, etc., and achieve optimal aerodynamic force, light weight and low cost of the fins Effect

Active Publication Date: 2014-05-14
海门卡汶纺织品有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a multi-axis aircraft, which solves the problems of unmanned aircraft in the prior art, such as heavy weight, unclear aerial photography, fast power consumption, difficult control of rotor synchronization and inability to change pitch

Method used

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Embodiment Construction

[0031] The technical solutions in the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0032] ginseng Figure 1 to Figure 5 As shown, the aircraft includes a frame 10, and a drive system 20 and a rotor 30 mounted on the frame.

[0033] The support 10 is a supporting platform, under which a landing gear, an aerial photography platform, etc. can be fixed, and above which, parts such as a power supply and a circuit board can be carried.

[0034] The bracket 10 includes a first side bar 11 and a second side bar 12 arranged in parallel, and the first...

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Abstract

The invention discloses a variable-pitch aircraft which comprises a bracket, and multiple rotor wings arranged on the bracket, wherein each rotor wing comprises a driving shaft, a first wing panel, a second wing panel, a propeller hub and a driving part; each driving part comprises a first sliding piece; each driving shaft is sleeved with each first sliding piece which is positioned below each propeller hub; each driving part also comprises a power device which can drive each first sliding piece to rise; each power device comprises a second sliding piece, a variable-pitch rocker arm, a connecting rod and a steering engine; a first connecting part and a second connecting part are symmetrically arranged on two sides of each second sliding piece; each variable-pitch rocker arm is provided with a first support arm which is rotatably connected to the first connecting part and a second support arm which is rotatably connected to the second connecting part. The variable-pitch rocker arm is in a double-push structure, so that the forces of the variable-pitch rocker arms acting on the second sliding pieces are symmetrical, and the service life of the power devices is prolonged.

Description

technical field [0001] The application belongs to the field of aerial photography, and in particular relates to a variable-distance multi-axis aircraft. Background technique [0002] Each axis of the multi-axis aircraft in the existing technical solution is composed of a corresponding propeller and a motor driving the corresponding propeller. The attitude maintenance and maneuvering action of the aircraft flight is to control the speed of each motor separately through the flight control system (the rotation directions of the various motors of the existing multi-axis aircraft are in pairs to counteract the spin torque) to achieve the attitude and action control of the aircraft of. The attitude of the vertical take-off and landing aircraft includes level and tilt. Maneuvering actions include level flight, ascent, descent, and spin (around its own Z axis, that is, the vertical axis of the horizontal plane of the body structure). The ascent and descent actions of the multi-ax...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/08B64C27/12B64C27/54
CPCB64C27/14B64C27/59B64U10/14B64U50/27B64U30/296B64U2101/30
Inventor 杨华东许剑吴奇才赵江
Owner 海门卡汶纺织品有限公司
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