CN107054643A

CN107054643A - Double lift lifting airscrew dynamic structure more self-balancing torque

Info

Publication number: CN107054643A
Application number: CN201611186390.1A
Authority: CN
Inventors: 黄鹏
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-12-16
Filing date: 2016-12-16
Publication date: 2017-08-18

Abstract

The lift lifting airscrew dynamic structure that doubles self-balancing torque is a kind of power rotor structure mode for significantly improving helicopter lift more, belongs to Helicopter Technology field.Current unmanned plane largely obtains lift and mechanomotive force using multiple propeller.And the limitation of power of motor and battery capacity makes take-off weight and airborne period all be not so good as people's will.Two (or multiple) propeller horizontal symmetricals are placed in the two ends (such as specification digest accompanying drawing) of rotor by the present invention, the drawing of generation horizontal direction, which (pushes away) power, makes rotor wing rotation, rotor produces the lift of vertical direction, and more than 10 times can be amplified to when horizontal direction pulling force is converted to lift in theory.This take-off weight for greatly to increase helicopter under same power of motor and battery condition or extension airborne period.Because two propellers are symmetrically placed in the two ends of rotor, the moment of torsion that motor rotation is produced is cancelled out each other, so whole helicopter is balanced without tail-rotor.Purposes of the present invention is helicopter (including nobody and have man-machine).

Description

Double lift lifting airscrew dynamic structure more self-balancing torque

Technical field：

The present invention (double lift lifting airscrew dynamic structure more self-balancing torque) is a kind of efficiently lifting helicopter liter The dynamic structure of power, belongs to Helicopter Technology field.

Background technology：

Current helicopter is divided into manned machine and unmanned plane.

Go straight up to manned machine to be driven by rotor centers axle usually using single rotor, reaction torque can be produced during driving, in order to balance Reaction torque typically sets tail-rotor.(tail-rotor is because chance failure or collision run out of steam security implication of the tail-rotor to helicopter very greatly When helicopter will under the driving of reaction torque at a high speed from then produce considerable risk).List rotor manned helicopter has skill at present Art is complicated, and oil consumption is high, the not good weakness of security.

Unmanned plane is gone straight up to generally using multiple (4,6,8 or more) brushless electric machines driving propeller (vertical direction installation) production Raw lift when motor-driven by increasing and decreasing the lift of some (or certain is several) propeller, it is necessary to be realized.Because propeller quantity is usual For even number and more than or equal to four, it is possible to which the direction rotated by setting propeller makes the reaction torque phase that propeller is produced Mutually offset.Unmanned plane is gone straight up to because simple, it is economical, it is convenient, efficiently wait many reasons more and more extensive using scope.But by The restriction of current power of motor and battery capacity and discharge capability is formed on, makes its take-off weight (load capacity) and airborne period All it is not so good as people's will.Unmanned plane take-off weight of going straight up to common at present is in 1-20 kgf scopes, and less than 5 kilograms unmanned planes of deadweight are stayed Generally at 30 minutes or so between space-time, more than 5 kilograms unmanned plane airborne periods of deadweight are generally at 10 minutes or so.

The pulling force that the present invention makes propeller total by the brand-new structure and mode different from existing scheme is converted to lift And improve many times (theoretical value can improve 10 times or so).This is allowed under the conditions of identical power of motor and battery capacity, Want take-off weight to increase many times, airborne period greatly prolong (propeller pulling force can reduce under same take-off weight, Supply voltage and electric current can all decline a lot, so the battery of same capacity can be used more long).

The content of the invention：

Two (or multiple) propeller horizontal symmetricals are placed in the two ends of rotor, the geometric center installation axle of rotor by the present invention Hold for carry body (such as Figure of description 1).Propeller rotation produces drawing of the horizontal direction along rotor wing rotation tangent line and (pushes away) power Rotor is set to be rotated around the geometric center of rotor, rotor wing rotation produces the lift of vertical direction, lift acts on body by bearing It is made to increase.Because the relation of rotor lift-drag ratio, propeller horizontal direction pulling force (is used to offset rotor wing rotation generation in theory Aerodynamic resistance) 10 times or so can be amplified to when being converted to the lift of rotor.This causes in same power of motor and electricity Greatly increase the take-off weight or airborne period of helicopter under the conditions of tankage.Because two propellers are symmetrically placed in rotor Two ends simultaneously rotate against and (such as rotated clockwise or counterclockwise on demand, such as Figure of description 2), the torsion for producing motor rotation Square is cancelled out each other, so although whole helicopter is that single rotor is balanced without tail-rotor.As long as connecting the axle of rotor and body Hold that frictional force is sufficiently small, the rotation torque of body can be ignored.Helicopter lifting action can be drawn by increasing and decreasing propeller Power (regulation motor rotating speed) causes rotor lift change to realize.Helicopter be horizontally diverted it is flat fly etc. it is motor-driven can be by body Variable-angle fin is installed come the reaction force for changing the direction of the part downwash flow of rotor and obtaining to realize that (specification is attached Fig. 3).It is whole straight to drive that one or more propellers and rudder (Figure of description 4) can also be horizontally mounted on body The horizontal maneuver of the machine of liter.Can also by set 4 (or more) rotor, make to go straight up to by changing the lift of certain several rotor Machine is motor-driven (Figure of description 5).Hinge arrangement tilting rotor (the motor-driven structure of general manned helicopter) can also be set real It is existing, and other modes etc..

The appropriate location that battery and electric machine control system (such as electricity tune, remote-control receiver etc.) may be mounted in rotor.Most Good mode is that, motor, electricity is adjusted, battery, and the power control system such as remote-control receiver is integrally formed, and handle is contoured to Streamlined (such as Figure of description 6).It can so make total succinct, simple installation.And because battery from motor with a distance from It is very short, the weight of conductive copper wire (or other conductive materials) can be saved, the electric energy wasted on conductor by resistance is also reduced, Extend airborne period.

Power resources on present apparatus rotor are not limited to battery motor, and micro internal combustion engine can also be used to drive spiral Oar, can also use turbofan or turbogenerator or recoil rocket engine of miniaturization etc..

Brief description of the drawings：

Figure of description 1：A kind of representational dynamic structure layout sketch of the present invention, two propeller horizontal symmetricals are put In the two ends of rotor, the geometric center of rotor installs bearing carry body.

Figure of description 2：Two propellers are symmetrically placed in the two ends of rotor and rotate against (the identical spiral shell of perfect condition Revolve oar, and identical rotary speed), the moment of torsion that motor rotation is produced is cancelled out each other

Figure of description 3：Change the direction of the part downwash flow of rotor by installing variable-angle fin on body And the reaction force obtained realizes the horizontal maneuver schematic diagram of helicopter.

Figure of description 4：A kind of representational dynamic structure layout of the present invention, two propeller horizontal symmetricals are placed in The two ends of rotor, the geometric center of rotor is installed is horizontally mounted a propeller and a direction on bearing carry body, body Rudder drives the horizontal maneuver of whole helicopter.

Figure of description 5：4 rotors are set, make whole wing sea level changes by changing the lift of certain two rotor Helicopter scheme of maneuver.

Figure of description 6：A kind of power assembly structural representation.By battery, (electricity is adjusted, distant for motor and electric machine control system Control receiver) it is arranged in a fairshaped metal cap (making to mitigate weight using magnesium alloy), motor shaft is in metal The front end of cover is stretched out, and propeller is installed on motor shaft.

Figure of description 7：The topology layout schematic diagram of embodiment.Two power assemblies are symmetrical (with rotor centers Point is reference point) it is arranged on the outer end of rotor.The face of motor shaft and rotor wing rotation is in approximately the same plane, and positioned at the circle of rotation The tangential direction in week, body is connected to one motor of assembling and propeller in front of rotor centers, body by a ball bearing, A variable-angle thin slice is assembled as the rudder of whole body in body rear.

Figure of description 8：For verifying that propeller horizontal pull is converted to whether rotor vertical direction lift has amplification Two motors are Xin Xida 2212 (2700KV) brushless electric machine in the experimental prototype of effect, figure, with 5045 carbon fiber oars, 3S (40C) electrokinetic cell, rotor is covered on aluminum skeleton with the thick PVC transparent films of 0.3mm, and upper surface is fixed wing aircraft aerofoil, Lower surface is not disposed, about 15 degree of rotor angle-of-attack (angle of attack), and artificial fixed rotor measures two propeller maximums with spring scale and drawn Power (remote control throttle 100%) is about 1500 gram forces, decontrols rotor, model machine, which is placed on, is used for the liter for measuring rotor generation on platform balance Power, actual measurement maximum lift is about 4800 gram forces (100% throttle), and lift lifts about 3.2 times.(some shakes of the rotor made by hand It is dynamic, the bottom plate of model machine is pushed down during test run with several books, the at this moment deadweight of model machine is about 6000 gram forces.

Embodiment：

1. first by battery, motor and electric machine control system (electricity is adjusted, remote-control receiver) are arranged on a fairshaped metal Cover in (making to mitigate weight using magnesium alloy), motor shaft is stretched out in the front end of metal cap, and spiral is installed on motor shaft Oar.We call this structural member " power assembly ".

2. making a rotor (two fins), the lift-drag ratio of aerofoil profile selects as far as possible big, and the angle of attack of the wing is in most favourable The angle of lift-drag ratio.The surface area of the wing is also big, in order to reduce the rotating speed of rotor under the conditions of same lift, makes power total Unbalanced stresses as far as possible small into the centrifugal force being subject in rotor wing rotation, that each structural member of power assembly can so be subject to It is smaller, improve the service life of structure.

3. two power assemblies symmetrical (using rotor centers point as reference point) are arranged on the two ends of rotor (close proximity to outer Hold to obtain the motive torque of maximum).The face of motor shaft and rotor wing rotation is in approximately the same plane, and positioned at the circumference rotated Tangential direction with obtain maximum power drive torque.

4. body is connected to rotor centers by a ball bearing.

5. one motor of assembling and propeller in front of body, and upper remote control and battery are connected, electricity is adjusted.Body rear is filled With rudder of the variable-angle thin slice as whole body.

Complete to be flown after above-mentioned installation steps.The electric power of wing tip power assembly, spiral shell are first connected using remote control Rotation oar rotation, which produces pulling force, makes rotor wing rotation, and rotor wing rotation produces lift, on helicopter can fly when lift is more than overall weight The supply voltage of motor is the lift of changeable rotor in sky, increase and decrease power assembly, rises or falls helicopter；On body Propeller and rudder be used for helicopter it is flat fly and turn to it is motor-driven, as shown in (Figure of description 7).

Claims

1. helicopter produces device power set on the fin of the rotor of lift, power set produce level along rotor wing rotation circular arc The power driving rotor of tangential direction rotates around the geometric center of rotor, and the rotor of rotation produces the lift of vertical direction, power dress Put including but not limited to motor, the propeller of the driving such as internal combustion engine；Also turbofan is included but is not limited to；Whirlpool Take turns jet engine；Turboaxle motor；Ramjet；Plasma engines etc..

2. helicopter produces device power set on the fin of the rotor of lift, the direction of power set pulling force (or thrust) is not The surfaces of revolution parallel to rotor but positioned at angle both horizontally and vertically, the pulling force (or thrust) of power set is in the horizontal direction Component driving rotor wing rotation, the lift and power set pulling force that the total lift of helicopter is produced from rotor wing rotation (or pushes away Power) in vertically-oriented component sum, power set include but is not limited to motor, the propeller of the driving such as internal combustion engine； Including but not limited to turbofan；Turbojet；Turboaxle motor；Ramjet；Deng from Sub- engine etc..

3. a power set be installed on rotor center or by paracentral position (power set or rotate together with rotor, The axle of power set is not as connection rotor and the axle of helicopter fuselage), (non-powered is filled by bearing for rotor and helicopter fuselage The rotating shaft put) connect, propeller is arranged on rotor fin (wing tip of the usual device in fin from rotor centers farther out), is passed through The rotating shaft of transmission device connecting power device and propeller, power set pass through actuator drives propeller rotational, propeller production Pulling force (or thrust) the driving rotor wing rotation of raw horizontal direction (or component of horizontal direction), the rotor of rotation produces Vertical Square To lift, power set include but is not limited to motor, the propeller of the driving such as internal combustion engine；Also whirlpool is included but is not limited to Take turns Duct-Burning Turbofan；Turbojet；Turboaxle motor；Ramjet；Plasma engines etc..

4. a power set is installed on installation axle in helicopter fuselage (power set are fixed on fuselage), the rotating shaft of power set Hold (inner ring that rotating shaft is fixed on bearing), the rotor (center for being located at rotor) of the outer ring connection helicopter of bearing, pacify on rotor Propeller is filled, propeller is connected with the rotating shaft of power set by transmission device, rotor wing rotation is not directly by power set Rotating shaft is directly driven, but the rotating shaft of power set is rotated by the propeller on actuator drives rotor, the spiral shell on rotor Revolve pulling force (or thrust) the driving rotor wing rotation that oar rotation produces horizontal direction (or component of horizontal direction), the rotor of rotation The lift of vertical direction is produced, this structure has reaction torque, and helicopter needs tail-rotor to balance, or it is anti-using double main rotors The reaction torque produced when carrying out balanced power device for roller driving to modes such as rotations.

It is arranged on 5. the technical characteristic of the present invention is the power set for driving rotor wing rotation on the fin for the rotor for producing lift simultaneously Rotated together with rotor, power set produce geometry of power driving rotor of the level along rotor wing rotation circular arc tangential line direction around rotor Central rotation, the rotor of rotation produces the lift of vertical direction, is arranged on by the quantity and power set that design rotor fin Direction (the power that position on fin, the quantity of power set and the size and power set of generation driving force rotate in itself Device irrotationality rotation member does not consider this factor then) balance the various moments of torsion of rotor.