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A double-sided flyable multi-rotor aircraft and its operating method

A rotorcraft and rotor technology, applied in the field of multi-rotor aircraft and its operation, can solve the problem that the aircraft cannot take off by itself

Active Publication Date: 2019-05-10
NANJING UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Aiming at the problem that the aircraft in the prior art cannot take off by itself when it is facing the ground, the present invention provides a multi-rotor aircraft capable of flying on both sides

Method used

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  • A double-sided flyable multi-rotor aircraft and its operating method
  • A double-sided flyable multi-rotor aircraft and its operating method
  • A double-sided flyable multi-rotor aircraft and its operating method

Examples

Experimental program
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Effect test

Embodiment 1

[0036] A double-sided flyable multi-rotor aircraft of the present embodiment includes a fuselage, a transmission mechanism and a rotor mechanism 6, and also includes a flight control device and a rotor fixed arm 4, wherein the center of the fuselage is provided with a flight control device, and the fuselage The center is connected with the first end of the rotor fixed arm 4 through a transmission mechanism, and the end of the rotor fixed arm 4 is connected with the rotor mechanism 6 .

[0037] The rotation of the rotor fixed arm 4 can only be 0 degree or 180 degree, which is mainly used for the situation that the aircraft can take off when landing on the front and back sides.

[0038] Such as figure 1 and 2 As shown, there are three rotor mechanisms 6 in this embodiment, and the three rotor mechanisms 6 are evenly distributed around the fuselage. The rotor protection frame 1 includes a support rod and an arc ring, the head end of the support rod is connected with the end of ...

Embodiment 2

[0057] A double-sided flyable multi-rotor aircraft and its operating method in this embodiment are similar to Embodiment 1, the difference is that, in order to ensure the stability when landing, each elastic rod has a clamping angle of about 30 degrees with the vertical direction. From a top view, the position of each elastic rod is in the middle of the outer contours of the two rotor protection frames, so that when the rotor protection frame 1 needs to rotate with the rotor fixed arm 4, the elastic rod will not block its rotation.

[0058] The landing supports are divided into two groups, one group is installed on the top of the middle of the aircraft fuselage, and one group is installed on the bottom of the middle of the aircraft fuselage. The undercarriage is used to provide support and protection when the aircraft lands. And when the aircraft lands on the reverse side, the landing bracket installed on the bottom can provide support; when the aircraft lands on the front sid...

Embodiment 3

[0062] A kind of two-sided flyable multi-rotor aircraft and its operating method of the present embodiment are similar to Embodiment 1, considering the situation that the rotor 5 is at a small angle with the ground (when the angle is too large, for example> 30 degrees , it is difficult for the aircraft to maintain stability after landing, and it may fall over). When this situation occurs, it is equivalent to that the aircraft is not in a stable state when it takes off. The function of the flight controller (ie, the flight control device) is to quickly adjust and stabilize the aircraft when the state of the aircraft is unstable. Therefore, for this situation, it can be seen that the flight state of the aircraft is unstable immediately after takeoff. At this time, it is only necessary to adjust the flight control device, and there is no major impact in actual use. For rotation around the axis, if the angle between the front of the plane where the rotor 5 is located and the verti...

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Abstract

The invention discloses a double-sided flightable multi-rotor aircraft and an operation method thereof and belongs to the field of aircrafts. The double-sided flightable multi-rotorcraft comprises an aircraft body, transmission mechanisms and rotor mechanisms, and further comprises a flight control device and rotor fixing arms; the flight control device is arranged at the center of the aircraft body, the center of the aircraft body is connected with the head end of each of the rotor fixing arms through the corresponding transmission mechanism, and the tail end of the rotor fixing arm is connected with the corresponding rotor mechanism; each of the rotor mechanisms comprises a rotor protecting frame; the rotor protecting frame comprises supporting rods and an arc-shaped ring, and is connected with the tail end of the corresponding rotor fixing arm, the first end of each of the supporting rods is connected with the tail end of the rotor fixing arm, the tail end of each of the supporting rods is connected with the inner surface of the arc-shaped ring, and the supporting rods in the same rotor protecting frame are of symmetrical structures; the rotor mechanisms are driven by motors, and output shafts of the motors are connected with rotors of the rotor mechanisms. Through changing the direction of force provided by the rotors, after being overturned, the aircraft still can normally take off.

Description

technical field [0001] The invention relates to the technical field of positioning, in particular to a double-sided flying multi-rotor aircraft and an operating method thereof. Background technique [0002] At present, the rotorcraft on the market are mainly fixed-wing, and the rotors are symmetrically distributed around the body. The rotors are on the same height plane, and the structure and radius of the rotors are the same. The motors are symmetrically installed at the end of the rotor fixed arm of the aircraft, and the flight control computer and external equipment are placed in the space where the head end of the fixed arm connects. Its power is provided by the rotation of the rotor driven by the motor. The rotor of the rotorcraft is generally coaxially installed on the rotor fixed arm with the motor, and the fixed arm is generally fixed to the fuselage. The multi-rotor aircraft sometimes falls due to improper control and contact with obstacles during flight. Since th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/08B64C27/12B64C27/32B64C13/18
CPCB64C13/18B64C27/08B64C27/12B64C27/32
Inventor 赵佳宝王心佐李维谈晓洁
Owner NANJING UNIV
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