CN103786879B - A kind of displacement aircraft - Google Patents

A kind of displacement aircraft Download PDF

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Publication number
CN103786879B
CN103786879B CN201410045464.4A CN201410045464A CN103786879B CN 103786879 B CN103786879 B CN 103786879B CN 201410045464 A CN201410045464 A CN 201410045464A CN 103786879 B CN103786879 B CN 103786879B
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CN
China
Prior art keywords
lever
synchronous pulley
sliding
support
fin
Prior art date
Application number
CN201410045464.4A
Other languages
Chinese (zh)
Other versions
CN103786879A (en
Inventor
杨华东
许剑
吴奇才
赵江
Original Assignee
江苏艾锐泰克无人飞行器科技有限公司
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Application filed by 江苏艾锐泰克无人飞行器科技有限公司 filed Critical 江苏艾锐泰克无人飞行器科技有限公司
Priority to CN201410045464.4A priority Critical patent/CN103786879B/en
Publication of CN103786879A publication Critical patent/CN103786879A/en
Application granted granted Critical
Publication of CN103786879B publication Critical patent/CN103786879B/en

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C39/00Aircraft not otherwise provided for
    • B64C39/02Aircraft not otherwise provided for characterised by special use
    • B64C39/024Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/04Helicopters
    • B64C27/12Rotor drives
    • B64C27/14Direct drive between power plant and rotor hub
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/54Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58Transmitting means
    • B64C27/59Transmitting means mechanical
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/02Unmanned aerial vehicles; Equipment therefor characterized by type of aircraft
    • B64C2201/027Flying platforms
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/10Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means
    • B64C2201/108Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means using rotors, or propellers

Abstract

This application discloses a kind of displacement aircraft, comprising: support, be installed on the multiple rotors on described support, described each rotor comprises axle drive shaft, first fin, second fin, propeller hub and drive division, described drive division comprises the first sliding part, described first sliding part is sheathed on described axle drive shaft, and be positioned at the below of described propeller hub, described drive division also comprises the engine installation that described first sliding part can be driven to rise, described engine installation comprises the second sliding part, distance-variable rocker arm, connecting rod and steering wheel, the bilateral symmetry of described second sliding part is provided with the first connecting portion and the second connecting portion, distance-variable rocker arm has the first support arm being rotationally connected with the first connecting portion and the second support arm being rotationally connected with the second connecting portion.Distance-variable rocker arm of the present invention is two selection structures, and the power that distance-variable rocker arm is acted on the second sliding part is symmetrical, increases the service life of engine installation.

Description

A kind of displacement aircraft
Technical field
The application belongs to the field of taking photo by plane, and particularly relates to a kind of Multi-axis aircraft of variable-distance.
Background technology
Each axle of the Multi-axis aircraft in existing technical scheme is by corresponding screw propeller and drive the motor of corresponding screw propeller to form.The attitude of aircraft flight keeps and maneuver controls each motor speed (rotation direction of each motor of existing Multi-axis aircraft is contrary in pairs, to offset spinning moment) respectively by flight control system to reach attitude of flight vehicle and action control.The attitude of vertically taking off and landing flyer comprises level, tilts.Maneuver comprises flat flying, and rises, and declines, spin (vertical axis around self Z axis, i.e. housing construction horizontal surface).The rise and fall action of Multi-axis aircraft the synchronization of all motors is promoted or declines to realize; The horizontal flight of aircraft is that the paired rotating speed official post aircraft that must increase by two motors on diagonal line keeps certain level lateral attitude cornerwisely to point to Low speed electric motor direction by pot motor along this and move and realize; Cw (conter clockwise) spin increases (minimizing) complete machine all cws (conter clockwise) rotary electric machine rotating speed simultaneously and minimizing (increase) complete machine all conter clockwises (cw) rotary electric machine rotating speed realizes simultaneously.Using the application force that the lift that each motor-driven screw propeller produces varies in size as, using the rotating speed of each motor as positive and negative moment one by one, controlling the attitude of aircraft and action is exactly that the size of the size and each moment constantly increasing and decreasing each application force realizes.
Prior art uses direct motor drive separately by each screw propeller, and aviation brushless motor causes allowing the rotating speed of all motors be consistent due to its principle of work, and existing manufacturing process makes the speed difference of each motor larger.In existing technical scheme, if whole motor speed is consistent or difference is very little, all kinds of Flight Control Softwares being very beneficial for current use control it, and now the efficiency of complete machine is the highest.If the speed difference of each motor is very large, the burden of Flight Control Software will be increased the weight of, because the flying platform that it will allow a sky be born with very unstable keeps stable.Also can fly although it is so, but if coordinate various different maneuver, fly control and will carry out each motor speed control very frequently, accelerate the power consumption speed of complete machine.
Summary of the invention
Object of the present invention provides a kind of Multi-axis aircraft, solve unmanned vehicle weight in prior art large, take photo by plane unintelligible, power consumption fast, rotor synchronism difficulty controls and cannot the problem of displacement.
For achieving the above object, the invention provides following technical scheme:
The embodiment of the present application discloses a kind of displacement aircraft, comprising:
Support;
Be installed on the multiple rotors on described support, described each rotor comprises axle drive shaft, the first fin, the second fin, propeller hub and drive division, described propeller hub is fixed on described axle drive shaft, described first fin and the second fin are symmetrically set in the both sides of described propeller hub, described drive division can act on described first fin and the second fin simultaneously and drive described first fin and the second fin to stir along contrary clockwise
The both sides of described propeller hub are rotatably provided with the first oar chuck and the second oar chuck respectively, and described first fin and the second fin are individually fixed on described first oar chuck and the second oar chuck,
Described drive division comprises the first sliding part, described first sliding part is sheathed on described axle drive shaft, and be positioned at the below of described propeller hub, described first sliding part is extended with the first crab claw and the second crab claw respectively in the symmetrical both sides of axle drive shaft, described first oar chuck and the second oar chuck are respectively equipped with the first rotation section and the second rotation section, be rotatably connected between described first rotation section and the first crab claw the first attaching parts, be rotatably connected between described second rotation section and the second crab claw the second attaching parts, described drive division also comprises the engine installation that described first sliding part can be driven to rise,
Described engine installation comprises the second sliding part, distance-variable rocker arm, connecting rod and steering wheel, described second sliding part is sheathed on described axle drive shaft, and be positioned at the below of described first sliding part, described distance-variable rocker arm is rotatably installed on described support, and one end of described rocking arm and the first sliding part are rotatably connected, described connecting rod is connected between described steering wheel and the other end of rocking arm
The bilateral symmetry of described second sliding part is provided with the first connecting portion and the second connecting portion, and distance-variable rocker arm has the first support arm being rotationally connected with the first connecting portion and the second support arm being rotationally connected with the second connecting portion.
Preferably, in above-mentioned displacement aircraft, described support comprises the first side lever and the second side lever that be arranged in parallel, and is fixed on the mobile jib between described first side lever and the second side lever, and the two ends of described mobile jib are individually fixed in the middle part of described first side lever and the second side lever.
Preferably, in above-mentioned displacement aircraft, also comprise drive system, described drive system is installed on described support, described drive system comprises a motor and four rotors, described four rotors are installed on four ends of described first side lever and the second side lever respectively, described motor drives described multiple rotor synchronously to rotate by synchronous drive mechanism, described synchronous drive mechanism comprises can by the main shaft of described motor-driven rotation, a synchronous drive belt is respectively equipped with between described main shaft with each rotor, described synchrodrive belt is located in described first side lever or the second side lever.
Preferably, in above-mentioned displacement aircraft, described rotor and main shaft are fixed with the first synchronous pulley and the second synchronous pulley respectively, the two ends of described synchrodrive belt are sheathed on described first synchronous pulley and the second synchronous pulley respectively, the inside face of described synchrodrive belt is provided with teeth groove, and the outside face of described first synchronous pulley and the second synchronous pulley is respectively equipped with the teeth groove be meshed with described synchrodrive belt inner surface.
Preferably; in above-mentioned displacement aircraft; described support also comprises four the first supports; described four the first supports are installed on four ends of described first side lever and the second side lever respectively; described first support has the first guard space, and described first synchronous pulley is located in described first guard space.
Preferably; in above-mentioned displacement aircraft; described support also comprises two the second supports; described two the second supports are individually fixed between described first side lever and mobile jib and between described second side lever and mobile jib; described second support has the second guard space, and described second synchronous pulley is located in described second guard space.
Preferably, in above-mentioned displacement aircraft, the both sides of described synchrodrive belt are provided with guide wheel.
Preferably, in above-mentioned displacement aircraft, the second transmission device is connected with between described main shaft and motor, described second transmission device comprises the 3rd synchronous pulley and the 4th synchronous pulley, described 3rd synchronous pulley is fixed on the output shaft of described motor, described 4th synchronous pulley is fixed on described main shaft, is connected with the second synchrodrive belt between described 3rd synchronous pulley and the 4th synchronous pulley.
Compared with prior art, the invention has the advantages that:
Unmanned vehicle of the present invention is provided with a motor, and drives all rotors synchronously to rotate by this motor, and owing to only arranging a motor, cost is low, lightweight; And relative to multiple motor, the impact of high-frequency vibration on visibility of taking photo by plane that motor produces obtains larger weakening; In addition, drive all rotors to rotate by a motor, each rotor synchronism is almost completely the same simultaneously.
Displacement rotor of the present invention can play by changing pitch the effect making fin aerodynamic force optimum in rotating speed one segment limit, and relative to the immutable aircraft of pitch, aircraft of the present invention has higher efficiency.
Synchrodrive belt is arranged in the cavity in the middle of the first side lever and the second side lever by the present invention, and the first synchronous pulley is located in the first guard space of the first support, when aircraft surprisingly collides, and can available protecting synchrodrive belt and the first synchronous pulley.Additionally by arranging guide wheel, effectively can limit the spacing between belt, avoiding the contact of itself and the first side lever or the second side lever.
Distance-variable rocker arm is two selection structures, and the power that distance-variable rocker arm is acted on the second sliding part is symmetrical, increases the service life of engine installation.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present application or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, the accompanying drawing that the following describes is only some embodiments recorded in the application, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Figure 1 shows that the perspective view of aircraft in the specific embodiment of the invention;
Figure 2 shows that the lateral plan of aircraft in the specific embodiment of the invention;
Figure 3 shows that the exploded perspective figure of drive system in the specific embodiment of the invention;
Figure 4 shows that the schematic perspective view of rotor in the specific embodiment of the invention;
Figure 5 shows that the exploded perspective view of rotor in the specific embodiment of the invention.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be described in detail the technical scheme in the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under the prerequisite not making creative work, all belongs to the scope of protection of the invention.
Shown in ginseng Fig. 1 to Fig. 5, aircraft comprises support 10 and the drive system 20 that is installed on support and rotor 30.
Support 10 is a support platform, can be fixed with alighting gear, holder for aerial photographing etc. below it, can carry the parts such as power supply, circuit card above it.
Support 10 comprises the first side lever 11 of be arrangeding in parallel and the second side lever 12, first side lever 11 is two Hollow circular beam that length is identical, diameter is identical with the second side lever 12.Be fixed with mobile jib 13 between first side lever 11 and the second side lever 12, mobile jib 13 is a Hollow circular beam, and its two ends are individually fixed in the midway location of the first side lever 11 and the second side lever 12, and mobile jib 13 is preferably perpendicular to the first side lever 11 and the second side lever 12.
Support 10 also comprises four ends that four the first supports, 14, four the first supports 14 are installed on the first side lever 11 and the second side lever 12 respectively, and the middle part of the first support 14 is formed with the first guard space 141.
Support 10 also comprises two the second supports, 15, two the second supports 15 and is individually fixed between the first side lever 11 and mobile jib 13 and between the second side lever 12 and mobile jib 13, is formed with the second guard space 151 in the middle part of the second support 15.
In other embodiments, mobile jib 13 also can be not orthogonal to the first side lever 11 and the second side lever 12.The material of the first side lever 11, second side lever 12 and mobile jib is preferably carbon fiber, is easy to it is contemplated that under the prerequisite meeting support strength, and the first side lever 11, second side lever 12 and mobile jib 13 can adopt other materials, such as aluminium material, more light better.
Above-mentioned support 10, only adopts three round bars be that H-shaped is fixed, and structure simply, and maximizedly reduces weight.
Shown in ginseng Fig. 3, drive system 20 comprises a motor 21, the 3rd synchronous pulley 22, the 4th synchronous pulley 23, second synchrodrive belt 24 and a main shaft 25.3rd synchronous pulley 22 is installed on the output shaft of motor 21, main shaft 25 rotates to be located in mobile jib 13,4th synchronous pulley 23 to be sheathed on main shaft 25 and to fix with main shaft 25,3rd synchronous pulley 22 is positioned at directly over the 4th synchronous pulley 23, realizes interlock between the 3rd synchronous pulley 22 and the 4th synchronous pulley 23 by the second synchrodrive belt 24.In order to prevent skidding between the second synchrodrive belt 24 and the 3rd synchronous pulley 22 and the 4th synchronous pulley 23, the inside face of the second synchrodrive belt 24 is provided with between the outside face of the 3rd synchronous pulley 22 teeth groove be meshed, and the outside face of the 4th synchronous pulley 23 is also provided with the teeth groove be meshed with the second synchrodrive belt 24 inside face.
Motor 21 is powered by power supply, motor 21 can rotate by Direct driver the 3rd synchronous pulley 22,3rd synchronous pulley 22 drives the 4th synchronous pulley 23 to rotate by the second synchrodrive belt 24, and the 4th synchronous pulley 23 rotates and then drives main shaft 25 to rotate.
Rotor 30 is installed on the first support 14, and each rotor 30 comprises an axle drive shaft 31 vertically, and the bottom of axle drive shaft 31 is sheathed and fix one first synchronous pulley 32, first synchronous pulley 32 and be located at protectively in the first guard space 141.Main shaft 25 is fixed with four the second synchronous pulleys 26, a synchronous drive belt 27 is provided with between each second synchronous pulley 26 and the first synchronous pulley 32 of corresponding rotor, the two ends of synchrodrive belt 27 are sheathed on the first synchronous pulley 32 and the second synchronous pulley 26 respectively, the inside face of synchrodrive belt 27 is provided with teeth groove, and the outside face of the first synchronous pulley 32 and the second synchronous pulley 26 is respectively equipped with the teeth groove be meshed with synchrodrive belt 27 inside face.The two ends of main shaft 25 are respectively provided with two the second synchronous pulleys 26, and two the second synchronous pulleys 26 being wherein positioned at one end are located at the second guard space 151 protectively, and two the second synchronous pulleys 26 being positioned at one end are near setting, preferably one-body molded.
Synchrodrive belt 27 will through the first side lever 11 and the second side lever 12 inside, in order to coordinate deceleration effort, the diameter of the first synchronous pulley 32 arranges larger, synchrodrive belt 27 is easily come in contact with the inner wall surface of the first side lever 11 or the second side lever 12 or opening part, when high-speed operation, synchrodrive belt 27 is easy to damage.In order to improve the service life of synchrodrive belt, a pair guide wheel 28 is respectively equipped with at the two ends of synchrodrive belt 27, every a pair guide wheel 28 is arranged at the both sides of synchronous belt 27, with the spacing of control synchronization belt ends, thus avoid the contact of synchrodrive belt 27 and the first side lever 11 or the second side lever 12, improve the service life of synchrodrive belt 27.
The start principle of above-mentioned drive system is as follows: motor 21, by Power supply, directly drives the 3rd synchronous pulley 22 to rotate; 3rd synchronous pulley 22 drives the 4th synchronous pulley 23 to rotate by the second synchrodrive belt 24 further, by adjusting the diameter ratio of the 3rd synchronous pulley 22 and the 4th synchronous pulley 23, can control revolution ratio; Because the 4th synchronous pulley 23 and main shaft 25 are fixed, main shaft 25 therefore can be driven further to rotate; Main shaft 25 drives four the second synchronous pulleys 26 be fixed on main shaft to carry out synchronous axial system, each second synchronous pulley 26 drives corresponding first synchronous pulley 32 to rotate respectively by a synchrodrive belt 27 again, the first synchronous pulley 32 and then drive corresponding fin to rotate.
Export propulsive effort to main shaft by a motor, and control the rotation of main shaft, main shaft outputs power to four rotors further by four synchrodrive belts.Can expect thus, technical scheme of the present invention goes for the aircraft with other quantity rotors equally, can according to the quantity of rotor on main shaft, correspondence is provided with the synchronizing wheel of identical number, such as: can increase by a pair second synchronous pulleys at the middle part of main shaft, simultaneously, the medium position of mobile jib can vertically fix a round bar, the two ends of this round bar are rotated respectively and are arranged a rotor, and so, main shaft can drive six rotors to carry out synchronous axial system simultaneously.
Unmanned vehicle of the present invention is provided with a motor, and drives all rotors synchronously to rotate by this motor, and owing to only arranging a motor, cost is low, lightweight; And relative to multiple motor, the impact of high-frequency vibration on visibility of taking photo by plane that motor produces obtains larger weakening; In addition, drive all rotors to rotate by a motor, synchronism easily controls simultaneously.
Shown in ginseng Fig. 4 and Fig. 5, rotor 30 comprises axle drive shaft 31, first synchronous pulley 32, first fin 331, second fin 332, propeller hub 34 and drive division.
First synchronous pulley 32 is fixed on the bottom of axle drive shaft 31, under the driving of synchrodrive belt 27, axle drive shaft 31 can be driven to rotate together.
Propeller hub 34 is a cylinder, the axis of its axes normal axle drive shaft 31, the middle part of propeller hub 34 vertically offers through hole or groove, and is formed fixing by the top that this through hole or groove are sheathed on axle drive shaft 31, and the rotation of axle drive shaft 31 can drive propeller hub 34 to rotate together.
The both sides of propeller hub 34 are rotatably provided with the first oar chuck 351 and the second oar chuck 352 respectively, first oar chuck 351 and the second oar chuck 352 are respectively equipped with holding part, and the first fin 331 and the second fin 332 are removably fixed on two holding parts respectively by screw.
Drive division comprises the first sliding part 36, first sliding part 36 is sheathed on axle drive shaft 31, and be positioned at the below of propeller hub 34, first sliding part 36 is extended with the first crab claw 361 and the second crab claw 362 respectively in the symmetrical both sides of axle drive shaft 31, first oar chuck 351 and the second oar chuck 352 are respectively equipped with the first rotation section 3511 and the second rotation section 3521, be rotatably connected between first rotation section 3511 and the first crab claw 361 second attaching parts 372 that to be rotatably connected between first attaching parts 371, second rotation section 3521 and the second crab claw 362.
Drive division also comprises the engine installation that the first sliding part 36 can be driven to rise.Engine installation comprises the second sliding part 381, distance-variable rocker arm 382, connecting rod 383 and steering wheel 384, second sliding part 381 is sheathed on axle drive shaft 31, and be positioned at the below of the first sliding part 36, distance-variable rocker arm 382 is rotatably installed on support 10, and the first end of distance-variable rocker arm 382 and the first sliding part 36 are rotatably connected, connecting rod 383 is connected between steering wheel and the second end of distance-variable rocker arm 382.
The bilateral symmetry of the second sliding part 381 is provided with the first connecting portion 3811 and the second connecting portion 3812, and distance-variable rocker arm 382 has the first support arm 3821 being rotationally connected with the first connecting portion 3811 and the second support arm 3822 being rotationally connected with the second connecting portion 3812.
Distance-variable rocker arm 382 is in rotation process, the symmetrical both sides of the second sliding part 381 can be acted on simultaneously, this pair of selection structure makes distance-variable rocker arm act on the power symmetry on the second sliding part 381, even if when a whole set of displacement part has gap, also can ensure that both sides rotor wing rotation there will not be lift cyclical variation in one week, increased the service life of engine installation simultaneously.
Drive division can act on the first fin 331 and the second fin 332 simultaneously and drive the first fin 331 and the second fin 332 to stir along contrary clockwise.Thus the control realized fin pitch.
In sum, displacement Multi-axis aircraft of the present invention, its advantage is:
1, flight control system again in order to control the attitude of complete machine and action and frequently change the rotating speed of each motor, need not save the power consumption of complete machine, is delayed cruise duration;
2, reduce the performance requriements to flying-controlled box, make the flying-controlled box exploitation of Multi-axis aircraft and use cost reduce a lot;
3, single motor-driven displacement Multi-axis aircraft cost when occurring such as to crash is low, prior art is that each motor is by each screw propeller of Hard link, encounter any object once crash screw propeller due to high rotating speed inertia at once to damage, can damage with screw propeller each motor hardwired further, the cost of the spare and accessory parts that such complete machine is changed in repair process will increase greatly simultaneously;
4, nonuniform pitch propeller is adopted can to allow motor under different rotating speeds, make the Aerodynamic force action of screw propeller optimum;
5, adopt nonuniform pitch propeller to control to make the movement posture corresponding speed of aircraft much sensitiveer than prior art, add the maneuvering performance of aircraft, can realize turning flight around;
6, adopt nonuniform pitch propeller, decrease the loss that motor is used, extend the service life of Multi-axis aircraft;
7, the body cross bar of the fixing screw propeller of H type and body vertical pole have certain flexibility.When the Propeller variable pitch of one end of body cross bar increases thrust, will make body cross bar, around body vertical pole, certain distortion occur, this distortion as a child will recover in the asymmetric thrust of body certainly.This slight and the housing construction that can recover distortion solves the key that variable-distance multiaxis H type airframe configuration scheme realizes spinning action just.
8, be arranged at by synchrodrive belt in the cavity in the middle of the first side lever and the second side lever, the first synchronous pulley is located in the first guard space of the first support, when aircraft surprisingly collides, and can available protecting synchrodrive belt and the first synchronous pulley.Additionally by arranging guide wheel, effectively can limit the spacing between belt, avoiding the contact of itself and the first side lever or the second side lever.
9, distance-variable rocker arm is two selection structures, and the power that distance-variable rocker arm is acted on the second sliding part is symmetrical, increases the service life of engine installation.
It should be noted that, in this article, the such as relational terms of first and second grades and so on is only used for an entity or operation to separate with another entity or operational zone, and not necessarily requires or imply the relation that there is any this reality between these entities or operation or sequentially.And, term " comprises ", " comprising " or its any other variant are intended to contain comprising of nonexcludability, thus make to comprise the process of a series of key element, method, article or equipment and not only comprise those key elements, but also comprise other key elements clearly do not listed, or also comprise by the intrinsic key element of this process, method, article or equipment.When not more restrictions, the key element limited by statement " comprising ... ", and be not precluded within process, method, article or the equipment comprising described key element and also there is other identical element.
The above is only the detailed description of the invention of the application; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the application's principle; can also make some improvements and modifications, these improvements and modifications also should be considered as the protection domain of the application.

Claims (8)

1. a displacement aircraft, is characterized in that, comprising:
Support;
Be installed on the multiple rotors on described support, described each rotor comprises axle drive shaft, the first fin, the second fin, propeller hub and drive division, described propeller hub is fixed on described axle drive shaft, described first fin and the second fin are symmetrically set in the both sides of described propeller hub, described drive division can act on described first fin and the second fin simultaneously and drive described first fin and the second fin to stir along contrary clockwise
The both sides of described propeller hub are rotatably provided with the first oar chuck and the second oar chuck respectively, and described first fin and the second fin are individually fixed on described first oar chuck and the second oar chuck,
Described drive division comprises the first sliding part, described first sliding part is sheathed on described axle drive shaft, and be positioned at the below of described propeller hub, described first sliding part is extended with the first crab claw and the second crab claw respectively in the symmetrical both sides of axle drive shaft, described first oar chuck and the second oar chuck are respectively equipped with the first rotation section and the second rotation section, be rotatably connected between described first rotation section and the first crab claw the first attaching parts, be rotatably connected between described second rotation section and the second crab claw the second attaching parts, described drive division also comprises the engine installation that described first sliding part can be driven to rise,
Described engine installation comprises the second sliding part, distance-variable rocker arm, connecting rod and steering wheel, described second sliding part is sheathed on described axle drive shaft, and be positioned at the below of described first sliding part, described distance-variable rocker arm is rotatably installed on described support, and one end of described rocking arm and the first sliding part are rotatably connected, described connecting rod is connected between described steering wheel and the other end of rocking arm
The bilateral symmetry of described second sliding part is provided with the first connecting portion and the second connecting portion, and distance-variable rocker arm has the first support arm being rotationally connected with the first connecting portion and the second support arm being rotationally connected with the second connecting portion.
2. displacement aircraft according to claim 1, it is characterized in that: described support comprises the first side lever and the second side lever that be arranged in parallel, and the mobile jib be fixed between described first side lever and the second side lever, the two ends of described mobile jib are individually fixed in the middle part of described first side lever and the second side lever.
3. displacement aircraft according to claim 2, it is characterized in that: also comprise drive system, described drive system is installed on described support, described drive system comprises a motor and four rotors, described four rotors are installed on four ends of described first side lever and the second side lever respectively, described motor drives described multiple rotor synchronously to rotate by synchronous drive mechanism, described synchronous drive mechanism comprises can by the main shaft of described motor-driven rotation, a synchronous drive belt is respectively equipped with between described main shaft with each rotor, described synchrodrive belt is located in described first side lever or the second side lever.
4. displacement aircraft according to claim 3, it is characterized in that: described rotor and main shaft are fixed with the first synchronous pulley and the second synchronous pulley respectively, the two ends of described synchrodrive belt are sheathed on described first synchronous pulley and the second synchronous pulley respectively, the inside face of described synchrodrive belt is provided with teeth groove, and the outside face of described first synchronous pulley and the second synchronous pulley is respectively equipped with the teeth groove be meshed with described synchrodrive belt inner surface.
5. displacement aircraft according to claim 4; it is characterized in that: described support also comprises four the first supports; described four the first supports are installed on four ends of described first side lever and the second side lever respectively; described first support has the first guard space, and described first synchronous pulley is located in described first guard space.
6. displacement aircraft according to claim 4; it is characterized in that: described support also comprises two the second supports; described two the second supports are individually fixed between described first side lever and mobile jib and between described second side lever and mobile jib; described second support has the second guard space, and described second synchronous pulley is located in described second guard space.
7. displacement aircraft according to claim 3, is characterized in that: the both sides of described synchrodrive belt are provided with guide wheel.
8. displacement aircraft according to claim 3, it is characterized in that: between described main shaft and motor, be connected with the second transmission device, described second transmission device comprises the 3rd synchronous pulley and the 4th synchronous pulley, described 3rd synchronous pulley is fixed on the output shaft of described motor, described 4th synchronous pulley is fixed on described main shaft, is connected with the second synchrodrive belt between described 3rd synchronous pulley and the 4th synchronous pulley.
CN201410045464.4A 2014-02-08 2014-02-08 A kind of displacement aircraft CN103786879B (en)

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CN201410045464.4A CN103786879B (en) 2014-02-08 2014-02-08 A kind of displacement aircraft
PCT/CN2014/094218 WO2015117509A1 (en) 2014-02-08 2014-12-18 Variable-pitch flight unit

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CN103786879B true CN103786879B (en) 2015-09-30

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