CN108006203A - A kind of electric control stepless big payload helicopter variable speed gearbox - Google Patents

Abstract

The invention provides an electronically controlled stepless large-scale variable-speed gearbox for a helicopter, which includes a main reducer, a planetary gear reducer, a main control allocation unit and a first-stage transmission mechanism. Coaxial surface gear, the planetary gear reducer includes a sun gear and a ring gear, the sun gear is connected to the first bevel gear, several planetary gears are arranged between the sun gear and the ring gear, and the planet wheels mesh with the sun gear and the ring gear respectively, the master control blending unit includes an interconnected ring gear and a ring gear controller, the ring gear meshes with the ring gear, and the primary rotation mechanism includes A power input mechanism and a second bevel gear, the power input mechanism is provided with a gear, the gear meshes with the second bevel gear, and the second bevel gear is connected with the sun gear. The invention enables the stepless reduction of the rotation speed of the large unmanned helicopter to smoothly change to an ideal rotation speed when flying forward at high speed.

Description

An electronically controlled stepless variable speed gearbox for large helicopters

technical field

The invention belongs to the technical field of variable speed of helicopters, and in particular relates to an electronically controlled stepless large-scale variable-speed gearbox for helicopters.

Background technique

The traditional gearbox will have intermittent problems when changing the speed, which will affect the control of the helicopter and other issues. A patent for an unmanned helicopter or aeromodelling helicopter gearbox (publication number: CN203421149U) discloses that the upper shell is conical, the lower shell is cylindrical, and the main shaft passes downward from the top of the upper shell and passes through the main teeth and the lower shell in the lower shell. The input gear shaft meshes, and the input gear shaft cooperates with the synchronous wheel through a one-way bearing on the outer side of the lower shell side wall, and the end of the input gear shaft is connected to the gearbox of the machine tail through a coupling. The power transmitted to the tail of the utility model no longer passes through the gearbox, which saves the special tail drive shaft, greatly reduces the structural components, makes the shaft easy to manufacture, and saves costs, but it is easy to switch from high to low speed in the speed change When the torque cannot be supplemented, it will bring greater impact and other problems to the entire transmission system.

Contents of the invention

The purpose of the present invention is to provide an electronically controlled stepless large-scale helicopter variable speed gearbox, which solves the problem of the blade stall of the large unmanned helicopter in the state of high-speed forward flight, so that the large-scale unmanned helicopter can stepless when flying forward at high speed. Reduced RPM smoothly transitions to ideal RPM.

The present invention provides following technical scheme:

An electronically controlled stepless variable speed gearbox for large helicopters, including a main reducer, a planetary gear reducer, a main control allocation unit and a first-stage transmission mechanism, and the main reducer includes a first bevel gear and a coaxial surface gear, the planetary gear reducer includes a sun gear and a ring gear, the sun gear is connected to the first bevel gear, and several planetary gears are arranged between the sun gear and the ring gear, and the planetary gears are respectively connected with the The sun gear meshes with the ring gear, the main control blending unit includes a ring gear connected to each other and a ring gear controller, the ring gear meshes with the ring gear, and the primary rotation mechanism includes a power input mechanism and a second bevel gear, the power input mechanism is provided with a gear, the gear meshes with the second bevel gear, and the second bevel gear is connected with the sun gear.

Preferably, the coaxial face gear includes an upper rotor and a lower rotor, and the first bevel gear is arranged between the upper rotor and the lower rotor and meshes with the upper rotor and the lower rotor respectively.

Preferably, an idler wheel is further provided between the upper rotor and the lower rotor, and the idler wheel meshes with the upper rotor and the lower rotor respectively.

Preferably, a lower rotor output shaft is provided on the coaxial axis between the upper rotor and the lower rotor, and an upper rotor output shaft is provided on the axis of the upper rotor.

Preferably, the planetary gear reducer further includes a frame on which the planetary gear is arranged, and the frame is coaxially arranged with the ring gear and the first bevel gear.

Preferably, the power input mechanism includes a first power input mechanism and a second power input mechanism, the first power input mechanism and the second power input mechanism are respectively provided with the gears, and the second bevel gear and The sun gear is arranged coaxially.

The beneficial effects of the present invention are: the overall structure of the gearbox is simple, and the stepless reduction of the speed of the helicopter can be smoothly changed to the ideal speed when the helicopter is flying forward at high speed through the meshing between the gears; compared with the traditional helicopter gearbox, planetary gears are used to reduce The gearbox does not need to slide gears when changing gears, so the friction and wear are small, the service life is long, and the structure is simple and compact; because it is an electronically controlled planetary gear reducer, the transmission ratio changes continuously, and the change process is stable and basically has no impact, so the gearbox has high efficiency. High, good linearity, good controllability and so on.

Description of drawings

The accompanying drawings are used to provide a further understanding of the present invention, and constitute a part of the description, and are used together with the embodiments of the present invention to explain the present invention, and do not constitute a limitation to the present invention. In the attached picture:

Fig. 1 is a structural representation of the present invention;

Fig. 2 is a side view structural representation of the present invention;

Fig. 3 is a schematic view of the top view structure of the present invention;

Fig. 4 is a schematic structural diagram of the principle of the present invention;

Marked in the figure: 1. main reducer; 11. upper rotor; 111. upper rotor output shaft; 12. lower rotor; 121. lower rotor output shaft; 13. idler gear; 14. first bevel gear; 2. planet Wheel reducer; 21. Ring gear; 22. Planetary gear; 23. Sun gear; 24. Rack; 3. Main control allocation unit; 31. Ring gear controller; 32. Ring gear; 4. Primary transmission mechanism; 41. The second bevel gear; 42. The first power input mechanism; 43. The second power input mechanism.

Detailed ways

As shown in Figures 1 to 4, an electronically controlled stepless large-scale helicopter variable speed gearbox includes a main reducer 1, a planetary gear reducer 2, a main control allocation unit 3 and a primary transmission mechanism 4, and the main reducer 1 Comprising a first bevel gear 14 and a coaxial face gear meshing with each other, the coaxial face gear includes an upper rotor 11 and a lower rotor 12, the first bevel gear 14 is arranged between the upper rotor 11 and the lower rotor 12 and is connected to the upper rotor 11 respectively Mesh with the lower rotor 12. An idler 13 is also arranged between the upper rotor 11 and the lower rotor 12, and the idler 13 meshes with the upper rotor 11 and the lower rotor 12 respectively. A lower rotor output shaft 121 is provided on the coaxial between the upper rotor 11 and the lower rotor 12 , and an upper rotor output shaft 111 is provided on the axis of the upper rotor 11 . The planetary gear reducer 2 includes a sun gear 23 and a ring gear 21, the sun gear 23 is connected to the first bevel gear 14, and several planetary gears 22 are arranged between the sun gear 23 and the ring gear 21, and the planetary gears 22 are connected with the sun gear 23 and the gear ring respectively. The ring gear 21 meshes, and the main control allocation unit 3 includes a ring gear 32 and a ring gear controller 31 that are connected to each other. The ring gear 32 meshes with the ring gear 21. The planetary gear reducer 2 also includes a frame 24, and the planetary gear 22 is located on the frame 24, the frame 24 is coaxially arranged with the ring gear 21 and the first bevel gear 14. The primary rotating mechanism 4 includes a power input mechanism and a second bevel gear 41 , the power input mechanism is provided with a gear, the gear meshes with the second bevel gear 41 , and the second bevel gear 41 is connected with the sun gear 23 . The power input mechanism comprises a first power input mechanism 42 and a second power input mechanism 43, the first power input mechanism 42 and the second power input mechanism 43 are respectively provided with gears, and the second bevel gear 41 is coaxially arranged with the sun gear 23 to carry out transmission.

As shown in Figures 1-4, in an electronically controlled stepless large-scale helicopter variable speed gearbox: a first-stage transmission mechanism 4, the power of the aircraft is input from the first power input mechanism 42 and the second power input mechanism 43, through two The meshing of the bevel gears realizes that the power is aggregated to the same bevel gear, that is, to the second bevel gear 41; the output of the planetary gear reducer 2 and the primary transmission mechanism 4 is transmitted from the second bevel gear 41 to the planetary gear reducer 2 The input sun gear 23, the overall rotation of the four evenly distributed planetary gears 22 around the sun gear 23 is the output of the entire planetary gear reducer 2, when the input speed is constant, the speed of the ring gear 21 controls the speed of the planetary gear 22 Output; the main control allocation unit 3, the ring gear controller 3 controls the ring gear 32 through the motor, thereby driving the ring gear 21 to rotate to control the output of the planetary gear reducer, so when the speed of the ring gear controller 31 increases, The speed of the ring gear 21 increases, the output speed of the planetary gear reducer 2 decreases, and the control accuracy depends on the sensitivity of the ring gear controller 31; the main reducer 1 and the planetary gear reducer 2 output to the first bevel gear 14 through the planetary gear 22 , the first bevel gear 14 and the coaxial upper rotor 11 are meshed with the lower rotor 12 bevel gears, so that the speed of the first bevel gear 14 can be shunted to the two coaxial bevel gears, and the speeds are opposite. At this time, the helicopter can be realized. The power transmission of coaxial blades solves the problem of blade stall of large unmanned helicopters in high-speed forward flight state, so that the stepless speed reduction of large unmanned helicopters can smoothly change to the ideal speed when flying forward at high speed. Further, the final reducer 1 is provided with an idler 13 to increase the structural balance strength.

Furthermore, since it is a planetary gear reducer 2, all gears are always in mesh with each other, and there is no need to slide gears when shifting gears, so the friction and wear are small, the service life is long, and the structure is simple and compact.

Further, since there are four uniformly distributed planetary gears 22, the load is distributed to a large number of teeth, and the centrifugal inertial force generated by the revolution and the radial component of the reaction force between the tooth profiles can be balanced with each other, so The main shaft bears little force and the transmission power is large; and because it is an electronically controlled planetary gear reducer 2, the transmission ratio changes continuously, and the change process is stable and basically has no impact. In addition, because it adopts internal meshing gears, it makes full use of the transmission space, and the input and output shafts are in a straight line, so the space size of the entire gear train is much smaller than that of ordinary fixed-axis gear trains under the same conditions.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still understand the foregoing embodiments The recorded technical solutions are modified, or some of the technical features are equivalently replaced. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims (6)

1. a kind of electric control stepless big payload helicopter variable speed gearbox, it is characterised in that slow down including main gear reducer, planetary gear Machine, master control deployment unit and primary transmission mechanism, the main gear reducer include intermeshing first bevel gear and co-shaft-surface tooth Wheel, the planet-gear speed reducer include sun gear and gear ring, and the sun gear connects the first bevel gear, the sun gear and Some planetary gears are equipped between the gear ring, the planetary gear is engaged with the sun gear and the gear ring respectively, the master control Deployment unit includes the ring gear and ring gear controller being connected with each other, and the ring gear is engaged with the gear ring, institute Stating level-one rotating mechanism includes power input mechanism and second bevel gear, and the power input mechanism is equipped with gear, the gear Engaged with the second bevel gear, the second bevel gear is connected with the sun gear.

2. a kind of electric control stepless big payload helicopter variable speed gearbox according to claim 1, it is characterised in that described common Axial plane gear includes upper rotor part and lower rotor part, and the first bevel gear is located between the upper rotor part and the lower rotor part and difference It is intermeshed with the upper rotor part and the lower rotor part.

3. a kind of electric control stepless big payload helicopter variable speed gearbox according to claim 2, it is characterised in that on described Idle pulley is additionally provided between rotor and the lower rotor part, the idle pulley is intermeshed with the upper rotor part and the lower rotor part respectively.

4. a kind of electric control stepless big payload helicopter variable speed gearbox according to claim 2, it is characterised in that on described Coaxial between rotor and the lower rotor part is equipped with lower rotor part output shaft, and the upper rotor part axle center is exported equipped with upper rotor part Axis.

A kind of 5. electric control stepless big payload helicopter variable speed gearbox according to claim 1, it is characterised in that the row Star wheel reducer further includes rack, and the planetary gear is located in the rack, the rack and the gear ring and first cone Gear is coaxially disposed.

6. a kind of electric control stepless big payload helicopter variable speed gearbox according to claim 1, it is characterised in that described dynamic Power input mechanism includes the first power input mechanism and the second power input mechanism, first power input mechanism and described Two power input mechanisms are respectively equipped with the gear, and the second bevel gear is coaxially disposed with the sun gear.