Four-rotor aircraft

A technology of four-rotor aircraft and eight-rotor aircraft, which is applied in the field of aircraft, can solve problems such as weak yaw ability, achieve the effect of improving yaw ability, reducing energy consumption, and improving yaw ability

Inactive Publication Date: 2013-11-13
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the problem of weak yaw ability existing in existing quadrotor aircraft, the present invention proposes a quadrotor aircraft with stronger yaw ability

Method used

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Examples

Experimental program
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Effect test

specific Embodiment approach 1

[0042] Specific implementation mode one, such as figure 1 As shown, set the center of mass of the aircraft as the origin o of the body coordinate system, the x-axis, y-axis, and z-axis are perpendicular to each other, the y-axis is to the left in the paper, the z-axis is perpendicular to the paper, and the x-axis is in the paper Upward, the xoy plane is divided into four quadrants, the x-axis direction is set as the nose direction of the aircraft, and the z-axis points upward along the longitudinal plane of the aircraft.

[0043] Four equal-length support arms are detachably mounted on the body 1 through a hinge structure, and each support arm is connected to the avionics system 2. The first support arm 401 and the third support arm 403 are on the xoy plane of the body coordinate system The projections of the second support arm 402 and the fourth support arm 404 are collinear in the body coordinate system xoy plane, and the projections of the first support arm 401 and the four...

specific Embodiment approach 2

[0052] Specific implementation mode two, such as image 3 As shown, set the center of mass of the aircraft as the origin o of the body coordinate system, the x-axis, y-axis, and z-axis are perpendicular to each other, the y-axis is to the left in the paper, the z-axis is perpendicular to the paper, and the x-axis is in the paper Upward, the xoy plane is divided into four quadrants, the x-axis direction is set as the nose direction of the aircraft, and the z-axis points upward along the longitudinal plane of the aircraft.

[0053] Four equal-length support arms are detachably mounted on the body 1 through a hinge structure, and each support arm is connected to the avionics system 2. The first support arm 401 and the third support arm 403 are on the xoy plane of the body coordinate system The projections of the second support arm 402 and the fourth support arm 404 on the body coordinate system xoy plane are collinear, and the projections of the first support arm 401 and the four...

specific Embodiment approach 3

[0061] Specific implementation mode three, such as Figure 5 As shown, set the center of mass of the aircraft as the origin o of the body coordinate system, the x-axis, y-axis, and z-axis are perpendicular to each other, the y-axis is to the left in the paper, the z-axis is perpendicular to the paper, and the x-axis is in the paper Upward, the xoy plane is divided into four quadrants, the x-axis direction is set as the nose direction of the aircraft, and the z-axis points upward along the longitudinal plane of the aircraft.

[0062] Four equal-length support arms are detachably mounted on the body 1 through a hinge structure, and each support arm is connected to the avionics system 2. The first support arm 401 and the third support arm 403 are on the xoy plane of the body coordinate system The projections of the second support arm 402 and the fourth support arm 404 on the body coordinate system xoy plane are collinear, and the projections of the first support arm 401 and the f...

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Abstract

The invention relates to a four-rotor aircraft, relates to the fields of aircrafts, and solves a problem that existing four-rotor aircrafts have weak yawing capability. The four-rotor aircraft comprises an aircraft body, an avionics system, a landing gear, a work loading module, four supporting arms and driving units, wherein the supporting arms are connected with the avionics system, the supporting arms expand along a center shaft of the aircraft body towards all around with equal angles, and the driving units are disposed at the front ends of the supporting arms. The included angles between the center shaft of the aircraft body and the supporting arms are the same, and are less than 90 degrees and greater than 0 degree. The projections of the supporting arms on the oxy plane are two axisymmetric and intersectant straight lines. The projections of the driving units on the xoy plane are respectively in the four quadrants or are respectively on the x positive axis, the y positive axis, the x negative axis and the y negative axis. A projection, of the spin axis of the driving units, on the yoz plane or the xoz plane respectively has an included angle theta with the z axis, wherein the theta is not more than 65 degrees and not less than -65 degrees, and 0 is not included. The projection, of a connecting line between the spin center and the origin of the aircraft body coordinate system, on the xoy plane is perpendicular to the projection of the spin axis of the driving units on the xoy plane. The yawing moment of the four-rotor aircraft is increased by an order of magnitude, and the yawing capability of the four-rotor aircraft is greatly enhanced.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a quadrotor aircraft. Background technique [0002] Quadrotor aircraft is the most common multi-rotor aircraft. It installs four rotors with fixed inclination angles on the same plane. It is safer, and the thrust generated by the four rotors can better realize the static hovering of the aircraft than the thrust generated by a single rotor. [0003] Quadrotor aircraft, by changing the speed of the four rotors to generate the lift and torque required for aircraft flight to achieve stable hovering and precise flight, from the perspective of motion, the quadrotor aircraft has six degrees of freedom in space and four controllable basic Motion state, the four basic motion states are vertical flight, longitudinal flight, lateral flight and horizontal rotation. The first three motion states are to realize the motion of the aircraft by changing the lift force of the four rotors to produ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/08B64C27/12
Inventor 高庆嘉白越孙强
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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