Multi-rotor aircraft

A multi-axis aircraft and airframe technology, applied in the field of aircraft, can solve problems such as poor maneuverability, increased flight resistance, and increased windward area, and achieve the effects of improving safety and reliability, flexible attitude control, and saving energy consumption

Active Publication Date: 2017-03-08
ZHUHAI PANSHI ELECTRONICS TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing multi-axis aircraft basically only adjust the flight attitude by changing the rotor speed, and the attitude response speed is low. If the diameter of the blade is too large, the attitude response speed of the rotor will be further delayed. Translational flight needs to tilt the fuselage, thus increasing the The windward area of ​​the fuselage leads to the increase of flight resistance, which makes the action response of the multi-axis aircraft slow and the maneuverability is poor. The frequent acceleration and deceleration of the motor causes a large loss of kinetic energy, large heat loss of the motor, and low

Method used

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Examples

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Example

[0028] First embodiment

[0029] Such as figure 1 As shown, the aircraft includes a fuselage 1 and a power unit. The fuselage has an upper support plate 11 and a lower support plate 12. The tripod 13 is installed below the lower support plate 12. The power unit includes three power units 2 symmetrically arranged about the axis of the aircraft. , One of the power units 2 is arranged on the axis of the aircraft, and each power unit 2 has three variable-pitch rotors 21. The power unit 2 is connected to the fuselage 1 through the arm 3, and a fairing 4 for protecting the internal structure is provided on it.

[0030] Such as figure 2 with image 3 As shown, the fixing frame 14 is connected to one end of the arm 3, and the fixing frame 14 is firmly connected with the upper support plate 11 and the lower support plate 12 through a plurality of connecting pieces. Each power unit 2 has a tilt to drive it to tilt. The rotating drive mechanism, wherein each tilting drive mechanism is respe...

Example

[0034] Second embodiment

[0035] The structure of this embodiment is substantially the same as that of the first embodiment, and the number of power units is different.

[0036] Such as Image 6 As shown, the aircraft has four power units 2, and the four power units 2 are arranged symmetrically in a cross shape. Each power unit 2 is connected to a fixed frame 14 fixed on the fuselage 1 through an arm 3 for tilting the power unit. The rotating tilting drive mechanism is arranged in each fixing frame 14. Each power unit 2 has a variable-pitch rotor 21 and a variable-pitch control device, and the variable-pitch steering gear is arranged on the arm 3.

Example

[0037] The third embodiment

[0038] The structure of this embodiment is substantially the same as that of the first embodiment, and the structure for tilting each power unit is different.

[0039] Such as Figure 7 As shown, the power plant of the aircraft includes three power units 2 arranged symmetrically about the axis of the aircraft, one of the power units 2 is arranged on the axis of the aircraft, and each power unit 2 has three variable-pitch rotors 21. The power unit 2 is connected to the fuselage 1 through the arm 3, and a fairing 4 for protecting the internal structure is provided on it. The fixed frame 14 is connected to one end of the arm 3, and the tilting drive mechanism 7 that drives each power unit 2 to tilt is arranged at the center of the fuselage 1, and the rotating shaft 75 connected to each arm 3 passes through the fixed frame 14 and The fixed frame 14 is rotatably supported, and preferably the supporting part on the fixed frame 14 is set to two or more to ma...

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PUM

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Abstract

The invention discloses an aircraft. The aircraft comprises an aircraft body and a power device, wherein the power device comprises a plurality of power units, every power unit is connected with the aircraft body through an aircraft arm and comprises variable-pitch rotors and a variable-pitch control device, and the aircraft body is provided with tilting driving mechanisms for controlling tilting of the power units. The aircraft is rapid to act and respond and flexible in flight attitude control.

Description

technical field [0001] The invention relates to an aircraft, in particular to a multi-axis aircraft. Background technique [0002] The take-off of multi-axis aircraft is limited by the site, and it can also hover in the air to achieve positioning and aerial photography, so it is getting more and more applications. Existing multi-axis aircraft basically only adjust the flight attitude by changing the rotor speed, and the attitude response speed is low. If the diameter of the blade is too large, the attitude response speed of the rotor will be further delayed. Translational flight needs to tilt the fuselage, thus increasing the The windward area of ​​the fuselage leads to the increase of flight resistance, which makes the action response of the multi-axis aircraft slow and the maneuverability is poor. The frequent acceleration and deceleration of the motor causes a large loss of kinetic energy, large heat loss of the motor, and low efficiency. [0003] In order to improve the...

Claims

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Application Information

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IPC IPC(8): B64C27/08B64C27/59B64C27/14
CPCB64C27/08B64C27/14B64C27/59
Inventor 何春旺
Owner ZHUHAI PANSHI ELECTRONICS TECH CO LTD
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