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 efficiency.
[0003] In order to improve the above situation, a kind of aircraft has appeared. Two rotors are symmetrically arranged on the front side of the aircraft, and a tiltable ducted fan is installed at the tail end. The horizontal component force is obtained by tilting the ducted fan to achieve high-speed level flight. However, the diameter of the blades of the ducted fan is much smaller than that of the front rotor blades, and the response speed of the aircraft has been improved. However, only the ducted fan can be tilted, the flight attitude control is not flexible enough, and the flight stability is still limited.

Method used

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Examples

Experimental program
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no. 1 example

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

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

no. 2 example

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

[0036] Such as Figure 6 As shown, the aircraft has four power units 2, and the four power units 2 are symmetrically arranged in a cross shape. Rotating tilting drive mechanism is arranged in each fixed 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 machine arm 3 .

no. 3 example

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

[0039] Such as Figure 7As shown, the power plant of the aircraft includes three power units 2 arranged symmetrically about the axis of the aircraft, one of which is arranged on the axis of the aircraft, and each power unit 2 has three rotors 21 with variable pitch. The power unit 2 is connected to the fuselage 1 through the machine arm 3, and a fairing 4 is arranged on it to protect the internal structure. The fixed mount 14 is connected with one end of the machine arm 3, and the tilting drive mechanism 7 that drives each power unit 2 to tilt is arranged at the central position of the fuselage 1, and the rotating shaft 75 connected with each machine arm 3 passes through the fixed mount 14 and It is rotatably supported by the fixed frame 14, preferably two or more supporting parts on the fixed frame 14, so as to make ...

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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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