CN100503365C - Coaxial unmanned crane vertical lifting machine - Google Patents
Coaxial unmanned crane vertical lifting machine Download PDFInfo
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- CN100503365C CN100503365C CNB2003101216378A CN200310121637A CN100503365C CN 100503365 C CN100503365 C CN 100503365C CN B2003101216378 A CNB2003101216378 A CN B2003101216378A CN 200310121637 A CN200310121637 A CN 200310121637A CN 100503365 C CN100503365 C CN 100503365C
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Abstract
A coaxial robot helicopter for lifting and transporting goods features that its lower rotor is equipped with a power system composed of two or more engines, clutch, speed reducer and active gear, its upper rotor is driven by a gear engaged with said active gear, and the reactive force of upper rotor can drive the lower rotor to rotate in different direction, generating lifting force. Said helicopter can be remotely controlled.
Description
Technical field:
The present invention relates to a kind of aircraft, especially a kind of driving engine is with the coaxial unmanned lifting helicopter of wing rotation.
Background technology:
As everyone knows, have at present special lifting cargo crane, hang ship, but be not specifically designed to the helicopter of lifting cargo.Certainly, pure helicopter also can lifting cargo, but because of itself design-calculated purpose, not to be mainly used in lifting cargo, but carry cargo or personnel flight, thereby it generally will possess driving compartment, cabin, balance empennage etc. are arranged, and various communication navigation set, these devices just can be unnecessary for main helicopter to lift by crane and closely to transport goods.Because these devices had both increased the raw materials consumption of helicopter, also increased the weight of helicopter, reduced the efficient of helicopter, the productive costs of helicopter and operating costs are greatly improved.Moreover, the helicopter of existing helicopter, particularly heavy, all powerful engine installation of power demand, it can be made up of separate unit perhaps many driving engines, and existing helicopter is owing to be subjected to the restriction of its structural condition, also only installs three to four driving engines general at most, otherwise just seems too complicated and huge, so generally mostly adopt turboshaft engine to satisfy requirement to dynamic property, though this type of engine weight is light, power is big, its price, maintenance cost are all than higher, and noise is also bigger.
In addition, concerning existing co-axial helicopter, upper and lower two groups of rotors, one group is just changeed, and one group of counter-rotating requires the necessary balance of two groups of rotor moments of torsion, otherwise will cause hull rotation, influences flight safety.It is all might be because of other former thereby cause the overbalance of upper and lower rotor moment of torsion in real-world operation, thereby exists the fault rate of this respect.
Summary of the invention:
The purpose of this invention is to provide a kind of simple in structure, easy operation, stable and reliable operation, expense be few, be exclusively used in the coaxial unmanned lifting helicopter that lifting is transported goods.
The technical solution used in the present invention is:
The present invention is made of rotor, mast, driving engine, power-transfer clutch, retarder, driving gear, driven gear, alighting gear, inclinator, electric actuator etc.Rotate with rotor on one group of rotor by the engine installation more than two or two, and drive another group rotor rotation; Control setup is made up of electric actuator and the inclinator that is arranged at the helicopter top.Described rotor is made up of slurry hub, oar axle, blade, is divided into two groups up and down, and it is a rotor altogether that last propeller hub, oar axle and last paddle link to each other, rotor on the composition, and following propeller hub directly links to each other with following blade, is following rotor; Being provided with mast is tubulose, is used for the upper and lower two groups of rotors of device.Described driving engine, power-transfer clutch, driving gear symmetry or even distribution device are on following rotor; Described driven gear is loaded on the propeller hub of rotor; Described alighting gear is four footstool shapes, is used to support helicopter.Engine power is through power-transfer clutch, retarder, driving gear, drive driven gear and go up the rotor rotation, its antagonistic force also promotes to be equipped with the following rotor rotation of driving engine, power-transfer clutch, retarder, driving gear, form two groups of rotor contrarotations, produce lifting flight.
Control partly is made up of inclinator and electric actuator.Described inclinator overhead is in helicopter top; Described electric actuator apparatus by two axostylus axostyles that are nested through mast, is controlled inclinator between them in alighting gear top, and then realizes the control to helicopter attitude.
The present invention is the same with existing co-axial helicopter, and is little except that having size, need not tail-rotor, do not have the fault rate air-flow symmetry from tail-rotor, helps handling, and outside the hovering efficiency advantages of higher, also has following characteristics:
One, this helicopter center of gravity is almost consistent with the axle center, also just in time on the vertical line of the center of axle, during lifting cargo, hoist cable suspension hook, axle center, center of gravity almost connect being aligned to suspension hook, very steady, be in operation do not exist such as reduce because of fuel, goods moves the centre-of gravity shift problem that causes, and complete machine comprises that the weight of the overwhelming majority of fuel tank all rotating the likeness in form flying saucer, inertia is big, keeps original operation attitude easily.
Two, this helicopter structure simple, compact, from heavy and light, in driving system, all driving gears are driven gear of synteny all, and driving gear is except that driving the driven gear rotation, itself also rotates around driven gear, and its transmitting ratio is 1/2 of a similar helicopter; All driving engines all around being arranged in down around the propeller hub, make full use of its locus, have reduced the many roof beams structure that are used for supporting engine; Do not have driving compartment, cabin, empennage, driverless operation,, want much economical with respect to directly hang the cargo operation with pure helicopter as the instrument that a kind of lifting is transported goods.
Its three, this helicopter is because its structural characteristics, its engine installation can be made up of few driving engine to more than ten of 2, as many as.Under the situation that many driving engines are formed, the possibility of stopping simultaneously is very little for some reason, that is to say, and is very low from the unpowered fault rate that takes place; And help adopting the piston engine that price is low, noise is little.In addition, when zero load or underloading, can stop the work of part driving engine, help fuel saving.
They are four years old, this helicopter is because the characteristics that driving engine rotates with the wing, principle according to application force and antagonistic force, for keeping the balance of moment of torsion, upper and lower two groups of rotors can distribute rotating speed automatically according to different drag loadings, do not exist upper and lower two groups of rotors to cause the fault rate of hull rotation because of the moment of torsion overbalance; Driving engine rotates with the wing, also help air cooling engine fully cooled off, to keep effective output of engine power.
This helicopter can be applicable to the particular surroundings that common lifting tool equipment is difficult to carry out operation, as the high mountains and deep gullies pole erecting, and conveying robot equipment; Also can hang sprinkler and spray insecticide, hang water and spray fire extinguishing; When needing, also can carry out flight, photography or go sightseeing etc. by cage delivery personnel.
Description of drawings:
Fig. 1 is a perspective view of the present invention.
Fig. 2 is the I-I cross sectional plan view of Fig. 1.
Shown in the figure: control button 1, direction electric actuator 2, control box 3, lifting electric actuator 4, carbon brush 5, retarder 6, power-transfer clutch 7, following paddle 8, driving gear 9, throttle electric actuator 10, bearing 11, fuel tank 12, last blade 13, lifting control axostylus axostyle 14, direction control axostylus axostyle 15, inclinator 16, oar axle 17, adjusting screw(rod) 18, nut 19, mast 20, last propeller hub 21, driven gear 22, following propeller hub 23, driving engine 24, slip ring 25, alighting gear 26, storage battery 27, mobile electric actuator 28, suspension hook 29, neutral gear dead man 30, hydrofin 31.
The specific embodiment:
Describe concrete structure of the present invention and service condition in detail below in conjunction with accompanying drawing.
The present invention is made up of rotor system, power system, driving system, management system, alighting gear etc.
Rotor system produces lift, displacing force and the actuating force of helicopter.Rotor is by propeller hub 21,23, and oar axle 17 and blade 8,13 are formed. Propeller hub 21,23 two ends are placed with antifriction-bearing box 11, and mast 20 is behind the propeller hub 21,23 of packing into, by nut 19 lockings.The effect of oar axle 17 is to keep upper and lower rotor that enough spacings are arranged.Last blade 13 can freely rotate in certain angle, so that the manipulation of helicopter is controlled, its pitch angle can be regulated by adjusting screw(rod) 18.Following blade 8 should more than or be longer than blade 13 slightly, and make the maxim of its blade angle more than or equal to last blade angle, like this under any operating mode, the rotating speed of following rotor all is lower than the rotating speed of going up rotor, to avoid owing to gyroplane rotate speed is too high down, centnifugal force is excessive the influence of driving engine 24 working stabilitys.
Power system is made up of driving engine 24 and fuel tank 12.Driving engine 24 must be more than two or two, and should be same model and equivalent weight, and their symmetries or even distribution device are around following propeller hub 23.By propeller hub supporting down, and with its rotation.Driving engine is more when installing, when one deck is not arranged, also can adopt long mast 20, multilayer is arranged, then links to each other and a shared driving gear 9 with transmission shaft from top to bottom, drives driven gear 22 then together, can install many like this, and even more than ten driving engine, power is powerful, is fit to very much the needs of hoisting heavy.Fuel tank 12 is an annular arrangement, and oar axle 17 is through at the ring center, and is placed with bearing carrier ring, and it can be rotated on oar axle 17, allows weight by 17 supportings of oar axle, and links to each other with following rotor with strut, allows it with rotor rotation down.
Driving system is by power-transfer clutch 7, retarder 6, and driving gear 9, driven gear 22 is formed.Power-transfer clutch 7 is a centrifugal type automatic clutch, when driving engine 24 rotating speeds are high, engage automatically, automatically separate during low speed, can guarantee the unloaded starting of driving engine like this, can when the separate unit engine off, can separate automatically again, to guarantee that other start the function normal operation, and when contingency ran out of steam, the rotation of rotor energy was to reduce the glide ration of helicopter.
Retarder 6 is a cone gear reducer, and driving gear 9 is housed on the output shaft, drives the driven gear 22 that is connected with last rotor during work and rotates.Neutral gear dead man 30 is housed on the retarder 7, in separation sleeve is arranged, its effect is the time to pull out to Neutral Position at tune-up and debugging, does not allow the rotor rotation.
Management system, by inclinator 16, lifting control axostylus axostyle 14, direction control axostylus axostyle 15, electric actuator 2,4,10,28, control box 3, control button 1, carbon brush 5, slip ring 25, storage battery 27 and remote control equipment (RCE) are formed.Inclinator 16 places the helicopter top, by 14 supportings of lifting control axostylus axostyle, there is connecting rod to link to each other with last blade 13, rotate with last rotor, its upper and lower moving can change the angle that goes up blade 13, and direction control axostylus axostyle 15 upper and lower moving can make inclinator 16 tilt, when inclinator tilts, the leaf angle of the blade 13 in the rotation is constantly changed, thereby produce a power, helicopter is moved to a certain direction in a certain direction; When control axostylus axostyle 15 rotation directions, helicopter also turns to thereupon.Electric actuator is to be that power removes to realize the actuating unit controlled with the electricity, and electric actuator 4 is an attachment point with alighting gear 26, and its action can make lifting control axostylus axostyle 14 upper and lower moving; Electric actuator 28 is an attachment point with lifting control axostylus axostyle 14, and its action can make direction control axostylus axostyle 15 upper and lower moving; Electric actuator 2 is an attachment point with lifting control axostylus axostyle 14 also, and its action can make the 15 positive and negative rotations of direction control axostylus axostyle; Electric actuator 10 is fixed on the driving engine 24, and its action can make the throttle amount of driving engine 24 increase or reduce.
In the control box 3 relay is housed, components and parts such as receiver of remote-control sytem are with the control of control button 1 composition to each electric actuator.Control button 1 to the lead of control box 3 is advisable with 20～30 meters; Exceed this scope as use and then should use remote control equipment (RCE), its remote range generally can reach hundreds of rice; If range of use exceeds remote range, then configurable cage allows the people be sitting in top random operation.There is the common use of line control and wireless remote control can improve the reliability of helicopter operation control.
The effect of carbon brush 5 and slip ring 25 is to make the following rotor that rotating and the mutual UNICOM of circuit of control box 3.
Alighting gear 26 is four pin taper stands, and mast 20 is vertically connected on its center.Alighting gear 26 both sides symmetries are equipped with hydrofin 31, and it works to stablize alighting gear and makes the fore-and-aft direction sign.Suspension hook 29 is connected with alighting gear 26 upper ends, and is positioned on the mast 20 axle center vertical lines.
The control power supply is supplied with by driving engine 24 in-to-in electrical generators, and storage battery 27 plays subsidy power supply and burning voltage.
Helicopter after the assembling must carry out the gravity balance debugging, particularly motor-powered rotor down, make its center of gravity consistent with the axle center, otherwise will produce vibrations during rotation, when shaking force is little, can adopt and adjust 10 pairs of mast 20 squares of throttle electric actuator and adjust from the method for distance, as shake excessive, symmetry or the uniform property that then will proofread driving engine.
Service condition of the present invention is such:
Throttle is placed idle position, and fire an engine 24 one by one, press throttle " acceleration " key of control button 1, electric actuator 10 actions, and driving engine 24 rotating speeds improve gradually.When rotating speed reached certain, centrifugal clutch 7 engaged, and power is transported to driving gear 9 after cone gear reducer 6 slows down, and drove driven gear 22 and rotated, thereby make the rotor rotation; Meanwhile, driving gear 9 also produces an antagonistic force, and reversing sense promotes rotor rotation down, so upper and lower two groups of rotors form contrarotation, produces lift jointly.
When gyroplane rotate speed reaches one regularly, press " rising " key of control button 1, electric actuator 4 actions move on the lifting control axostylus axostyle 14, and last blade angle increases, and the rotating speed of following rotor is also corresponding thereupon to be increased, and raising force also increases thereupon.Constantly alternately by two above-mentioned keys, overcome deadweight and take off vertically until helicopter.
When needs move helicopter, then press " moving " key of control button 1, electric actuator 28 actions move on the direction control axostylus axostyle 15, pulling inclinator 16 tilts, last rotor will change blade angle when rotated automatically, so produce a displacing force, helicopter will move to a certain direction, so to front and back, still about, decide with the Directional Sign of the hydrofin on the alighting gear 26 31, mobile speed then will be controlled axostylus axostyle 15 amount of movements and decides with direction.
In the time will making helicopter change moving direction, then press " moving to left " or " moving to right " key of control button 1, electric actuator 2 actions.Direction control axostylus axostyle 15 rotates to the left or to the right, drives inclinator 16 and tilts to the left or to the right, and the moving direction of helicopter also changes thereupon.
In the time will making the helicopter landing, then press " decline " key of control button 1, electric actuator 4 actions, lifting control axostylus axostyle 14 moves down, and last blade 13 leaf angles reduce lift divergence; Then press throttle " deceleration " key, make electric actuator 10 actions, accelerator open degree reduces, and driving engine 24 slows down, and two keys are alternately pressed until helicopter landing ground, presses " deceleration " key at last to idling, and centrifugal clutch 6 thoroughly separates, the rotor stall.
Claims (3)
1, a kind of coaxial unmanned lifting helicopter, comprise upper and lower two groups of rotors, mast, driving engine, driving device, control setup, alighting gear, it is characterized in that: driving engine (24), driving gear (9) symmetry or even distribution device under organize rotor, the last rotor hub (21) of last rotor is provided with driven gear (22), and mast (20) is a tubular shafts, and control setup is provided with control box (3), carbon brush (5), slip ring (25), storage battery (27).
2, coaxial unmanned lifting helicopter according to claim 1 is characterized in that: mast (20) runs through and is provided with lifting control stalk (14) and the direction control stalk (15) that is nested.
3, coaxial unmanned lifting helicopter according to claim 1 is characterized in that: described control box (3) is carbon brush (5), slip ring (25) with UNICOM's circuit of following rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2003101216378A CN100503365C (en) | 2003-12-30 | 2003-12-30 | Coaxial unmanned crane vertical lifting machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2003101216378A CN100503365C (en) | 2003-12-30 | 2003-12-30 | Coaxial unmanned crane vertical lifting machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1556007A CN1556007A (en) | 2004-12-22 |
| CN100503365C true CN100503365C (en) | 2009-06-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2003101216378A Expired - Fee Related CN100503365C (en) | 2003-12-30 | 2003-12-30 | Coaxial unmanned crane vertical lifting machine |
Country Status (1)
| Country | Link |
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| CN (1) | CN100503365C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103072690A (en) * | 2013-01-23 | 2013-05-01 | 中国航空工业空气动力研究院 | Single-ducted coaxial rotor/propeller saucer-shaped aircraft |
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-
2003
- 2003-12-30 CN CNB2003101216378A patent/CN100503365C/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103072690A (en) * | 2013-01-23 | 2013-05-01 | 中国航空工业空气动力研究院 | Single-ducted coaxial rotor/propeller saucer-shaped aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1556007A (en) | 2004-12-22 |
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Granted publication date: 20090624 Termination date: 20111230 |