CN1843847A

CN1843847A - Multi-rotor aerocraft

Info

Publication number: CN1843847A
Application number: CN 200610080492
Authority: CN
Inventors: 战强
Original assignee: Individual
Current assignee: Individual
Priority date: 2006-05-18
Filing date: 2006-05-18
Publication date: 2006-10-11
Anticipated expiration: 2026-05-18
Also published as: CN100391790C

Abstract

The invention relates to a multi-rotor aircraft, which comprises an airframe and several rotors mounted on the airframe and in one level. Wherein, the number N of rotors is dual, as N=2, 4, 6, 8, etc, and formed by positive and passive rotors whose sizes and number are same; all rotors are uniformly distributed on the periphery of airframe in 360/N angle; the passive and positive rotors are alternatively arranged with reversed rotation directions and upward lifting force; each rotor can be directly driven by motor or oil engine, or driven by motion transmission device via synchronous belt; the torsion between rotors can be counteracted, without balance device as tail wing or scull, with tight structure, flexible motion, larger lifting force and weight ratio. The invention can rise vertically, suspend in air, rotate in one point or fly horizontally.

Description

Multi-rotor aerocraft

Technical field

The present invention relates to a kind of multi-rotor aerocraft that can be used for a plurality of fields such as scientific experiment, Aeronautics and Astronautics, industry, amusement, military affairs.

Background technology

Have vertical takeoff and landing and the aircraft of function such as hover take photo by plane, fields such as atmospheric seeing, celestial body detecting have application demand widely.The aircraft that has this class function at present mainly contains versions such as single-rotor helicopter, twin-rotor helicopter, tiltrotor, as the tiltrotor V-22 of MH-16 helicopter, Muscovite card-29 helicopter, Boeing Co. and the Bell Co. of U.S. McDonnell-Douglas Corporation and V-44 etc.Single-rotor helicopter or coaxial anti-oar helicopter need the tail-rotor structure to offset the torsion that rotor produces body, and tiltrotor need be peaceful the verting of rotor aerofoil that fly to carry out between state of taking off vertically.

The problem that above-mentioned design exists is that empennage is all arranged, and main oar diameter is very big with respect to body, the structure more complicated, and kinematic dexterity and stationarity are relatively poor, and the lift of aircraft and weight is lower, if be designed to small aircraft then load capacity is very poor.

Summary of the invention

Technology of the present invention is dealt with problems and is: the complex structure that solves existing vertical takeoff and landing, hovering flight device, main oar is big with respect to the body diameter, kinematic dexterity and stationarity are relatively poor, and lift is low with the ratio of this body weight, are designed to the weak problem of small aircraft load capacity.

Technical solution among the present invention is: multi-rotor aerocraft includes a body, and N (N is an even number, as 2,4,6,8 etc.) is the positive and negative rotor that horizontal fixed is installed on the body and forms, and all rotors are positioned on the same horizontal surface; The geometric configuration of positive and negative rotor is all identical with quantity, is the periphery that 360/N degree angle alternately is distributed on body, and the rotating shaft of each rotor equates with the distance of the geometric centre of body; Rotor both can also can wait driving device to drive from other positions of body by synchronous band by motor or oily machine direct drive; The hand of rotation of the positive and negative rotor of this aircraft is opposite, lift upwards, because the torsional moment direction that acts on the body in the positive and negative rotor rotary course is opposite, the mode of velocity magnitude that therefore can be by adjusting positive and negative rotor realizes that the torsional moment of closing of whole aircraft is zero, so do not need tail-rotor or empennage isoequilibrium device.For example, during, switched in opposite identical when the rotating speed of all positive and negative rotors, because it is opposite that positive and negative rotor acts on torsional moment equal and opposite in direction, the direction of body, and the quantity of positive and negative rotor equates, so the torsional moment of closing of whole aircraft is zero, the rotating speed that increase all rotors this moment can make aircraft take off vertically; If the rotating speed of one of them or several rotors reduces, then because the torsional moment overbalance, aircraft can rotate.Because the big or small transfer speed that the lift that rotor produces reaches the torsional moment of body has direct relation, so just can make aircraft produce motion required lift or moment of torsion by the rotative speed of adjusting rotor, thereby realize the vertical takeoff and landing of aircraft, hover, cw and left-hand revolution and flat flying.

Description of drawings

Below in conjunction with accompanying drawing the specific embodiment among the present invention is described in further detail.

Fig. 1 is the schematic appearance of multi-rotor aerocraft among the present invention;

Fig. 2 is the birds-eye view of multi-rotor aerocraft among the present invention;

Fig. 3 is the aircraft schematic appearance that rotor adopts the duct structure among the present invention.

The specific embodiment

As depicted in figs. 1 and 2, specific embodiments of the invention are: four

rotors

1,2,3,4 are the 90 angle symmetries of spending and are fixed on the body 7 of a crux, four rotors are positioned on the same horizontal surface and are distributed on one is on the circle in the center of circle with the cross bar intersection point, controller and battery etc. 6 is fixed on the center of body, and four

rotors

1,2,3,4 are by four motors, 5 difference individual drive;

Rotor

1,3 adopts positive oar, right-hand revolution, and

rotor

2,4 adopts anti-oar, the anticlockwise direction rotation, the lift that produces all is that upwards in the process of whole flight, turning to of all rotors is constant.When four rotors all rotated with the certain speed constant speed by direction shown in Figure 2, the torsional moment of closing of this aircraft was zero, can take off vertically, and the words of acceleration can rise, and the words of deceleration can descend, and the words of keeping speed can be hovered at certain altitude.As shown in Figure 2, when

rotor

1 and 3 steady accelerations and

rotor

2 and 4 speed when constant, the torsional moment of

rotor

1 and 3 pairs of bodies increases, this aircraft to close torsional moment non-vanishing, this aircraft is done the anticlockwise direction rotation around body center; And when

rotor

2 and 4 steady accelerations and the speed of

rotor

1 and 3 when constant, because it is non-vanishing to close torsional moment, this aircraft is done right-hand revolution around body center.As shown in Figure 2, when rotor 2 quickens, rotor 4 slows down, the speed that rotor 2 increases is identical with the speed that rotor 4 reduces, and the speed of

rotor

1 and 3 is when constant, and aircraft is flat to the right to fly; Otherwise when rotor 2 slows down and rotor 4 when quickening, aircraft is flat left to fly; When rotor 1 quickens, rotor 3 slows down, when the speed of increase and

speed rotor

2 and 4 identical with the speed of minimizing were constant, aircraft is flat downwards to fly; Otherwise when rotor 1 slows down and rotor 3 when quickening, aircraft is upwards flat to fly.Therefore this aircraft can realize vertical takeoff and landing neatly by adjusting the speed of different rotors, revolve stop, flat flying and motion such as original place rotation.This aircraft both can adopt remote operated mode to control flight, also can realize the autonomous flight control of this aircraft by the auxiliary employing auto-control mode of equipment such as gyroscope, GPS, magneto-meter or do the flight of more accurate track.

In addition, also can improve wind loading rating, the increase lift of aircraft by increase structures such as duct to rotor, and can prevent that rotor and environment obstacle from bumping, improve its safety, the aircraft surface structure as shown in Figure 3.

From the above, the multi-rotor aerocraft among the present invention has following advantage:

1. the aircraft among the present invention can be installed a plurality of rotors in little spatial dimension, and a plurality of rotors can produce bigger combination lift, and the ratio of lift and deadweight is bigger.

2. the aircraft among the present invention utilizes the mode that torsion is cancelled out each other between a plurality of rotors to prevent the arbitrarily rotation aloft of this aircraft, does not need tail-rotor or empennage isoequilibrium device, therefore is easy to realize vertical takeoff and landing and hovering, and compact conformation.

Aircraft among the present invention only by the speed of adjusting a plurality of rotors can realize this aircraft vertical takeoff and landing, hover, flatly fly, motion such as original place rotation, motion is flexibly and hover more steady.

4. the aircraft among the present invention is fit to have the design of the small aircraft of certain load-carrying capacity, is suitable for using in narrow environment.

Claims

1. multi-rotor aerocraft, it is characterized in that: it includes body, and the positive and negative rotor that quantity equates, geometric configuration is identical that N (N is an even number) level is installed on the body forms, and all rotors are positioned on the same horizontal surface; Positive and negative rotor is 360/N degree angle and alternately is distributed on the body periphery, and the rotating shaft of each rotor equates with the geometric centre of body distance; The hand of rotation of positive and negative rotor is opposite, and lift makes progress, and the torsion between each rotor can be cancelled out each other, and does not have tail-rotor or empennage isoequilibrium device; Each rotor both can also can wait driving device to drive from other positions of body by synchronous band by motor or oily machine direct drive.

2. according to the multi-rotor aerocraft described in the claim 1, it is characterized in that: the spoke shape that described body can be rectangle, circle or the bar that stretched out by middle mind-set periphery constitutes, but be not limited to these shapes.

3. according to the multi-rotor aerocraft described in the claim 1, it is characterized in that: the blade quantity on each rotor can be 1,2,3,4, or more.

4. according to the multi-rotor aerocraft described in the claim 1, it is characterized in that: each rotor can adopt the duct structure, to improve wind loading rating and to improve lift.