CN100391790C

CN100391790C - Multi-rotor aerocraft

Info

Publication number: CN100391790C
Application number: CNB2006100804925A
Authority: CN
Inventors: 战强
Original assignee: Individual
Current assignee: Individual
Priority date: 2006-05-18
Filing date: 2006-05-18
Publication date: 2008-06-04
Anticipated expiration: 2026-05-18
Also published as: CN1843847A

Abstract

The present invention discloses an aircraft with multiple rotary wings, which comprises an organic body and a plurality of rotary wings arranged on an aircraft body, wherein the rotary wings are on the same horizontal plane; the number of the rotary wings is even, for example, N is equal to 2, 4, 6, 8, etc.; the rotary wings are composed of positive and negative rotary wings of the same geometric sizes and number. All rotary wings form 360 DEG or N DEG included angles, and are uniformly distributed on the periphery of the aircraft body. The positive rotary wings and the negative rotary wings are arranged in an alternative mode, the rotary directions of the positive rotary wings and the negative rotary wings are opposite, and the lift force faces upwards. Each rotary wing not only can be directly driven by a motor or an oil engine, but also can be driven by other parts on the aircraft body by motion transmission devices such as a synchronous belt, etc. The torsional moment among the multiple rotary wings of the aircraft with multiple rotary wings can be cancelled mutually without balance devices such as an empennage or a stroke propeller, etc. The present invention has the advantages of compact structure and flexible motion, and the ratio of the lift force to the weight of the aircraft is large. The aircraft with multiple rotary wings not only can lift and fall vertically and hover in the sky, but also can rotate in situ or fly level.

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, 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 this aircraft Aloft arbitrarily rotation does not need tail-rotor or empennage isoequilibrium device, therefore is easy to realize VTOL and sky In hover 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.