CN111874239A - Coaxial double-rotor-wing propeller transmission system with tail and helicopter - Google Patents
Coaxial double-rotor-wing propeller transmission system with tail and helicopter Download PDFInfo
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- CN111874239A CN111874239A CN202010711619.9A CN202010711619A CN111874239A CN 111874239 A CN111874239 A CN 111874239A CN 202010711619 A CN202010711619 A CN 202010711619A CN 111874239 A CN111874239 A CN 111874239A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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Abstract
The invention belongs to the field of helicopters, and discloses a coaxial double-rotor-wing propeller transmission system with a tail and a helicopter, wherein the transmission system comprises a first bevel gear, a first reversing bevel gear, a second reversing bevel gear, a third reversing bevel gear, a first planetary gear train, a second planetary gear train, a third bevel gear and a tail push output shaft, and the first reversing bevel gear is meshed with the first bevel gear; the second bevel gear is in transmission connection with the first reversing bevel gear and meshed with the second reversing bevel gear and the third reversing bevel gear; the first planetary gear train is in transmission connection with a second reversing bevel gear, and the second planetary gear train is in transmission connection with a third reversing bevel gear; the third bevel gear is meshed with the second reversing bevel gear and the third reversing bevel gear, and the tail pushing output shaft is in transmission connection with the third bevel gear. According to the invention, the tail push transmission is set as two-stage transmission output, and the coaxial dual rotors are set as three-stage transmission output, so that the transmission requirements of the tail push and the coaxial dual rotors can be met simultaneously.
Description
Technical Field
The invention relates to the field of helicopters, in particular to a coaxial double-rotor tail propeller transmission system and a helicopter.
Background
At present, most helicopters are in a single main rotor wing configuration with a tail propeller, the main rotor wing provides lift force for the helicopters and controls flight attitude, and the tail propeller is mainly used for balancing reaction torque generated by the main rotor wing. Because the paddle of main rotor one side is in advancing all the time, and the paddle of one side is in the back, high-speed flight can not be realized to this kind of aerodynamic layout, and the tail-rotor function only balances the effect of rotor reaction torque, causes certain power waste. In order to solve the problem of high-speed flight of helicopters, helicopters have come to use coaxial dual-rotor tail-belt propeller configurations, however, the current transmission system of single main-rotor tail-belt propeller cannot be directly applied to coaxial dual-rotor tail-belt propellers, and therefore, it is necessary to develop a transmission system of coaxial dual-rotor tail-belt propeller.
Disclosure of Invention
The invention aims to provide a coaxial double-rotor tail propeller transmission system and a helicopter, which can meet the power output requirements of a tail propeller and a coaxial double rotor simultaneously.
The technical scheme provided by the invention is as follows:
in one aspect, a coaxial dual rotor tailed propeller drive system is provided, comprising:
the first-stage reversing transmission mechanism comprises a first bevel gear and a first reversing bevel gear, the first bevel gear is used for being connected with the power input shaft, and the first reversing bevel gear is meshed with the first bevel gear;
the two-stage reversing transmission mechanism comprises a second bevel gear, a second reversing bevel gear and a third reversing bevel gear, the second bevel gear and the first reversing bevel gear are fixed on the same transmission shaft, and the second bevel gear is meshed with the second reversing bevel gear and the third reversing bevel gear simultaneously;
the coaxial dual-rotor output mechanism comprises a first planetary gear train and a second planetary gear train, wherein the first planetary gear train is in transmission connection with an outer rotor shaft of the coaxial dual-rotor, the second planetary gear train is in transmission connection with an inner rotor shaft of the coaxial dual-rotor, the first planetary gear train is in transmission connection with the second reversing bevel gear, and the second planetary gear train is in transmission connection with the third reversing bevel gear;
and the tail pushing output mechanism comprises a third bevel gear and a tail pushing output shaft, the third bevel gear is simultaneously meshed with the second reversing bevel gear and the third reversing bevel gear, and the tail pushing output shaft is in transmission connection with the third bevel gear.
In the scheme, the contra-rotating function of the coaxial double rotors is realized through a one-driving-two bevel gear structure, the function of balancing the contra-rotating of the main rotor by the traditional tail rotor is replaced, and the flying efficiency is improved; the double-layer main rotor wing enables the left side and the right side of the helicopter to be provided with forward propellers, provides a power output function for the tail propeller and can meet the requirement of high-speed flight of the helicopter; in addition, the transmission system can simultaneously meet the power output requirements of a tail propeller and a coaxial double rotor wing.
Further preferably, the number of the primary reversing transmission mechanisms is multiple, and each primary reversing transmission mechanism is connected with one power input shaft;
the number of the second bevel gears is multiple, each second bevel gear is in transmission connection with one first reversing bevel gear, and the second bevel gears are simultaneously meshed with the second reversing bevel gear and the third reversing bevel gear.
In the scheme, multiple inputs are arranged, and the second reversing bevel gear and the third reversing bevel gear are used for outputting in parallel, so that the high-power transmission requirement of the tail propulsion paddle can be met.
Further preferably, the first planetary gear train includes a first sun gear, a first planetary gear, a first internal gear ring and a first planet carrier, the first sun gear and the second reversing bevel gear are fixed on the same transmission shaft, the first planetary gear is externally engaged with the first sun gear, the first planetary gear is internally engaged with the first internal gear ring, the first planetary gear is connected with the first planet carrier, and the first planet carrier is used for being in transmission connection with the external rotor shaft.
Further preferably, the second planetary gear train includes a second sun gear, a second planetary gear, a second internal ring gear and a second planet carrier, the second sun gear and the third reversing bevel gear are fixed on the same transmission shaft, the second planetary gear is externally engaged with the second sun gear, the second planetary gear is internally engaged with the second internal ring gear, the second planetary gear is connected with the second planet carrier, and the second planet carrier is used for being in transmission connection with the internal rotor shaft.
Further preferably, the tail pushing output mechanism further comprises a first cylindrical gear, a second cylindrical gear and a third cylindrical gear, the first cylindrical gear and the third bevel gear are fixed on the same transmission shaft, the second cylindrical gear is meshed with the first cylindrical gear, the third cylindrical gear is meshed with the second cylindrical gear, and the tail pushing output shaft is fixedly connected with the third cylindrical gear.
Further preferably, the number of the second cylindrical gears is two, and the two second cylindrical gears are simultaneously meshed with the first cylindrical gear and the third cylindrical gear.
Further preferably, the first cylindrical gear, the second cylindrical gear and the third cylindrical gear are all helical gears.
Further preferably, the helicopter further comprises a shell and a supporting rod, wherein the first-stage reversing transmission mechanism, the second-stage reversing transmission mechanism, the coaxial dual-rotor output mechanism and the tail pushing output mechanism are all arranged in the shell, one end of the supporting rod is connected with the shell, and the other end of the supporting rod is used for being connected with a helicopter so as to install the shell on the helicopter.
Further preferably, the supporting rods are V-shaped, the number of the supporting rods is four, and the housing is mounted on the helicopter through the four supporting rods.
In another aspect, a helicopter is also provided, comprising the coaxial dual-rotor tail-rotor propeller transmission system.
The invention has the technical effects that: the transmission system comprises three stages of speed reduction, wherein the first stage of speed reduction is positioned at an input stage and adopts a bevel gear for speed reduction and reversing, the second stage adopts a one-to-two bevel gear structure for speed reduction and reversing and realizes coaxial contra-rotation, the third stage adopts two sets of planetary gear trains for realizing speed reduction output so as to drive coaxial double rotors, and the output power in the second stage of transmission drives a tail propeller so as to realize the simultaneous driving of the tail propeller and the coaxial double rotors; in addition, the planetary gear train driving the coaxial double rotors is arranged at the rear end, so that vibration can be inhibited, a centering effect is achieved, and the coaxial double rotors cannot generate radial deflection.
Drawings
The invention is described in further detail below with reference to the following figures and detailed description:
FIG. 1 is a drive schematic of a coaxial dual rotor tailed propeller drive system of the present invention;
FIG. 2 is a schematic view of a coaxial dual rotor tailed propeller drive system of the present invention from one perspective;
FIG. 3 is a schematic view of a coaxial dual rotor tailed propeller drive system of the present invention from another perspective;
FIG. 4 is a cross-sectional view of a coaxial dual rotor tailed propeller drive system of the present invention;
fig. 5 is a schematic external structural view of a coaxial dual rotor tailed propeller drive system of the present invention.
The reference numbers illustrate:
1. a power input shaft; 2. an outer rotor shaft; 3. an inner rotor shaft; 4. a housing; 5. a support bar; 11. a first bevel gear; 12. a first reversing bevel gear; 21. a second bevel gear; 22. a second reversing bevel gear; 23. a third reversing bevel gear; 30. a first planetary gear train; 31. a first sun gear; 32. a first planetary gear; 33. a first inner ring gear; 34. a first carrier; 40. a second planetary gear train; 41. a second sun gear; 42. a second planetary gear; 43. a second inner ring gear; 44. a second planet carrier; 51. a third bevel gear; 52. the tail pushes the output shaft; 53. a first cylindrical gear; 54. a second cylindrical gear; 55. a third cylindrical gear.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and they do not represent the actual structure as a product. In addition, in order to make the drawings concise and understandable, components having the same structure or function in some of the drawings are only schematically illustrated or only labeled. In this document, "one" means not only "only one" but also a case of "more than one".
It should be further understood that the term "and/or" as used in this specification and the appended claims refers to and includes any and all possible combinations of one or more of the associated listed items.
In this context, it is to be understood that, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, in the description of the present application, the terms "first", "second", and the like are used only for distinguishing the description, and are not intended to indicate or imply relative importance.
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will be made with reference to the accompanying drawings. It is obvious that the drawings in the following description are only some examples of the invention, and that for a person skilled in the art, other drawings and embodiments can be derived from them without inventive effort.
The invention provides an embodiment of a coaxial double-rotor tail propeller transmission system, which comprises a primary reversing transmission mechanism, a secondary reversing transmission mechanism, a coaxial double-rotor output mechanism and a tail pushing output mechanism, wherein the primary reversing transmission mechanism comprises a first bevel gear 11 and a first reversing bevel gear 12, the first bevel gear 11 is used for being connected with a power input shaft 1, and the first reversing bevel gear 12 is meshed with the first bevel gear 11;
the two-stage reversing transmission mechanism comprises a second bevel gear 21, a second reversing bevel gear 22 and a third reversing bevel gear 23, the second bevel gear 21 and the first reversing bevel gear 12 are fixed on the same transmission shaft, and the second bevel gear 21 is meshed with the second reversing bevel gear 22 and the third reversing bevel gear 23 simultaneously;
the coaxial dual-rotor output mechanism comprises a first planetary gear system 30 and a second planetary gear system 40, wherein the first planetary gear system 30 is in transmission connection with an outer rotor shaft 2 of the coaxial dual rotor, the second planetary gear system 40 is in transmission connection with an inner rotor shaft 3 of the coaxial dual rotor, the first planetary gear system 30 is in transmission connection with a second reversing bevel gear 22, and the second planetary gear system 40 is in transmission connection with a third reversing bevel gear 23;
the tail pushing output mechanism comprises a third bevel gear 51 and a tail pushing output shaft 52, the third bevel gear 51 is meshed with the second reversing bevel gear 22 and the third reversing bevel gear 23 simultaneously, and the tail pushing output shaft 52 is in transmission connection with the third bevel gear 51.
Specifically, the first-stage reversing transmission mechanism comprises a first bevel gear 11 and a first reversing bevel gear 12, the first bevel gear 11 is connected with the power input shaft 1, the power input shaft 1 is an output shaft of an engine, the power input shaft 1 drives the first bevel gear 11 to rotate when rotating, the first reversing bevel gear 12 is meshed with the first bevel gear 11, and the first bevel gear 11 drives the first reversing bevel gear 12 to rotate when rotating, so that power input reversing is realized.
The two-stage reversing transmission mechanism comprises a second bevel gear 21, a second reversing bevel gear 22 and a third reversing bevel gear 23, the second bevel gear 21 and the first reversing bevel gear 12 are fixed on the same transmission shaft, the first reversing bevel gear 12 drives the second bevel gear 21 to rotate when rotating, the second bevel gear 21 is arranged between the second reversing bevel gear 22 and the third reversing bevel gear 23, and the second bevel gear 21 is meshed with the second reversing bevel gear 22 and the third reversing bevel gear 23 simultaneously. When the second bevel gear 21 rotates, the second reversing bevel gear 22 and the third reversing bevel gear 23 are driven to rotate, and the rotating directions of the second reversing bevel gear 22 and the third reversing bevel gear 23 are opposite.
The coaxial dual-rotor output mechanism comprises a first planetary gear system 30 and a second planetary gear system 40, wherein the first planetary gear system 30 is respectively connected with a second reversing bevel gear 22 and an outer rotor shaft 2, the second planetary gear system 40 is respectively connected with a third reversing bevel gear 23 and an inner rotor shaft 3, the rotating directions of the second reversing bevel gear 22 and the third reversing bevel gear 23 are opposite, so that the coaxial rotation of the outer rotor shaft 2 and the inner rotor shaft 3 of the coaxial dual-rotor is realized, and the rotating directions of the outer rotor shaft 2 and the inner rotor shaft 3 are opposite.
The tail pushing output mechanism comprises a third bevel gear 51 and a tail pushing output shaft 52, the third bevel gear 51 is meshed with the second reversing bevel gear 22 and the third reversing bevel gear 23 simultaneously, the third bevel gear 51 is driven to rotate when the second reversing bevel gear 22 and the third reversing bevel gear 23 rotate, the tail pushing output shaft 52 is in transmission connection with the third bevel gear 51, the tail pushing output shaft 52 is driven to rotate when the third bevel gear 51 rotates, and the tail pushing output shaft 52 is connected with a tail propeller to achieve power output of the tail propeller.
In the embodiment, the first stage adopts a first-stage reversing transmission mechanism for speed reduction and reversing, the second stage adopts a one-to-two bevel gear structure for speed reduction and reversing and realizes coaxial contra-rotation, and the third stage adopts two sets of planetary gear trains to realize speed reduction output through a planet carrier so as to drive coaxial double rotors; and the tail propeller is driven by the output power of the bevel gear in the second-stage transmission, so that the tail propeller and the coaxial double rotors are driven simultaneously.
In addition, because the rear end is in a low-rotation-speed state and the transmission torque is large, the load of the rear end is relatively harsh, and the embodiment can inhibit vibration by placing the planetary gear train at the rear end, thereby achieving a centering effect and preventing the coaxial double rotors from generating radial deflection.
Preferably, as shown in fig. 3, the number of the primary reversing transmission mechanisms is multiple, and each primary reversing transmission mechanism is connected with one power input shaft 1; the number of the second bevel gears 21 is multiple, each second bevel gear 21 is in transmission connection with one first reversing bevel gear 12, and the multiple second bevel gears 21 are simultaneously meshed with a second reversing bevel gear 22 and a third reversing bevel gear 23. In the embodiment, multiple power inputs are adopted, and the power is output through the second reversing bevel gear 22 and the third reversing bevel gear 23 in a parallel mode, so that the power is converged, and the power and the rotating speed are transmitted to the tail propeller and the coaxial double rotors.
As shown in fig. 1 to 3, the first planetary gear system 30 includes a first sun gear 31, a first planetary gear 32, a first inner ring gear 33, and a first carrier 34, the first sun gear 31 and the second reversing bevel gear 22 are fixed on the same transmission shaft, the first planetary gear 32 is externally engaged with the first sun gear 31, the first planetary gear 32 is internally engaged with the first inner ring gear 33, the first planetary gear 32 is connected with the first carrier 34, and the first carrier 34 is adapted to be drivingly connected with the outer rotor shaft 2.
The second reversing bevel gear 22 rotates to drive the first sun gear 31 to rotate, the plurality of first planet gears 32 are meshed with the first sun gear 31, the first sun gear 31 rotates to drive the plurality of first planet gears 32 to rotate along the first inner gear ring 33 to achieve power splitting, the plurality of first planet gears 32 are connected with the first planet carrier 34, the plurality of first planet gears 32 rotate to drive the first planet carrier 34 to rotate to achieve power converging, and the first planet carrier 34 rotates to drive the outer rotor shaft 2 to rotate.
As shown in fig. 1 to 4, the second planetary gear train 40 includes a second sun gear 41, a second planetary gear 42, a second internal gear 43, and a second carrier 44, the second sun gear 41 and the third reverse bevel gear 23 are fixed on the same transmission shaft, the second planetary gear 42 is externally engaged with the second sun gear 41, the second planetary gear 42 is internally engaged with the second internal gear 43, the second planetary gear 42 is connected with the second carrier 44, and the second carrier 44 is used for being in transmission connection with the internal rotor shaft 3.
The third reversing bevel gear 23 drives the second sun gear 41 to rotate when rotating, the plurality of second planet gears 42 are meshed with the second sun gear 41, the second sun gear 41 drives the plurality of second planet gears 42 to rotate along the second inner gear ring 43 when rotating, power division is realized, the plurality of second planet gears 42 are connected with the second planet carrier 44, the plurality of second planet gears 42 drive the second planet carrier 44 to rotate when rotating, power confluence is realized, and the second planet carrier 44 drives the inner rotor shaft 3 to rotate when rotating. A plurality of planet gears are meshed with the sun gear, each planet gear transmits less power, and the volume of each gear is smaller.
As shown in fig. 3, the tail pushing output mechanism further includes a first cylindrical gear 53, a second cylindrical gear 54 and a third cylindrical gear 55, the first cylindrical gear 53 and the third bevel gear 51 are fixed on the same transmission shaft, the second cylindrical gear 54 is engaged with the first cylindrical gear 53, the third cylindrical gear 55 is engaged with the second cylindrical gear 54, and the tail pushing output shaft 52 is fixedly connected with the third cylindrical gear 55.
The second reversing bevel gear 22 and the third reversing bevel gear 23 drive the third bevel gear 51 to rotate when rotating, the third bevel gear 51 drives the first cylindrical gear 53 to rotate when rotating, the first cylindrical gear 53 drives the second cylindrical gear 54 to rotate when rotating, the second cylindrical gear 54 drives the third cylindrical gear 55 to rotate when rotating, the third cylindrical gear 55 drives the tail push output shaft 52 to rotate when rotating, and the tail push output shaft 52 is connected with the tail propeller to realize the power output of the tail propeller.
Preferably, as shown in fig. 3, the number of the second cylindrical gears 54 is two, and two second cylindrical gears 54 are simultaneously engaged with the first cylindrical gear 53 and the third cylindrical gear 55. The two second cylindrical gears 54 are meshed with the first cylindrical gear 53 to achieve power splitting, and the two second cylindrical gears 54 are meshed with the third cylindrical gear 55 to achieve power converging. The first cylindrical gear 53, the second cylindrical gear 54, and the third cylindrical gear 55 are all helical gears.
As shown in fig. 5, the coaxial dual-rotor tail-equipped propeller transmission system further includes a housing 4 and a support rod 5, the first-stage reversing transmission mechanism, the second-stage reversing transmission mechanism, the coaxial dual-rotor output mechanism and the tail-pushing output mechanism are all disposed in the housing 4, one end of the support rod 5 is connected with the housing 4, and the other end of the support rod 5 is connected with the helicopter so as to install the transmission system on the helicopter. The supporting rods 5 are V-shaped, the number of the supporting rods 5 is four, and the transmission system is installed on the helicopter through the four V-shaped supporting rods 5.
The transmission process of the coaxial double-rotor tail propeller transmission system of the embodiment is as follows:
the power input shaft 1 drives the first bevel gear 11 to rotate when rotating, the first bevel gear 11 drives the first reversing bevel gear 12 to rotate when rotating, speed reduction and reversing of power are achieved, the first reversing bevel gear 12 rotates to drive the second bevel gear 21 to rotate, the second bevel gear 21 rotates to drive the second reversing bevel gear 22 and the third reversing bevel gear 23 to rotate simultaneously, the rotation directions of the second reversing bevel gear 22 and the third reversing bevel gear 23 are opposite, the second reversing bevel gear 22 drives the first sun gear 31 to rotate when rotating, the first sun gear 31 rotates to drive the first planetary gear 32 to rotate, the first planetary gear 32 rotates to drive the first planet carrier 34 to rotate, and the first planet carrier 34 rotates to drive the outer rotor shaft 2 to rotate. When the third reversing bevel gear 23 rotates, the second sun gear 41 is driven to rotate, the second sun gear 41 rotates to drive the second planetary gear 42 to rotate, the second planetary gear 42 rotates to drive the second planetary carrier 44 to rotate, and the second planetary carrier 44 rotates to drive the inner rotor shaft 3 to rotate, so that coaxial contrarotation of the outer rotor shaft 2 and the inner rotor shaft 3 is realized.
When the second reversing bevel gear 22 and the third reversing bevel gear 23 rotate, the third bevel gear 51 is driven to rotate, the third bevel gear 51 rotates to drive the first cylindrical gear 53 to rotate, the first cylindrical gear 53 rotates to drive the plurality of second cylindrical gears 54 to rotate, the plurality of second cylindrical gears 54 rotate to drive the third cylindrical gear 55 to rotate, and the third cylindrical gear 55 rotates to drive the tail propeller output shaft 52 to rotate, so that the power output of the tail propeller is realized.
The present invention also provides a helicopter embodiment, as shown in fig. 1 to 5, comprising a power input mechanism, a tail rotor, a coaxial dual rotor mechanism and a coaxial dual rotor tailed propeller drive system as described in the above embodiments. The power input mechanism comprises a power input shaft 1, and the power input shaft 1 is in transmission connection with the first bevel gear 11 and drives the first bevel gear 11 to rotate. The power input mechanism may be plural to form multiple inputs.
The outer rotor shaft 2 of the coaxial double rotor is connected with the first planet carrier 34 of the first planetary gear system 30, and the inner rotor shaft 3 is connected with the second planet carrier 44 of the second planetary gear system 40, so that the outer rotor shaft 2 and the inner rotor shaft 3 are coaxially and oppositely rotated.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A coaxial dual rotor tailed propeller drive system, comprising:
the first-stage reversing transmission mechanism comprises a first bevel gear and a first reversing bevel gear, the first bevel gear is used for being connected with the power input shaft, and the first reversing bevel gear is meshed with the first bevel gear;
the two-stage reversing transmission mechanism comprises a second bevel gear, a second reversing bevel gear and a third reversing bevel gear, the second bevel gear and the first reversing bevel gear are fixed on the same transmission shaft, and the second bevel gear is meshed with the second reversing bevel gear and the third reversing bevel gear simultaneously;
the coaxial dual-rotor output mechanism comprises a first planetary gear train and a second planetary gear train, wherein the first planetary gear train is in transmission connection with an outer rotor shaft of the coaxial dual-rotor, the second planetary gear train is in transmission connection with an inner rotor shaft of the coaxial dual-rotor, the first planetary gear train is in transmission connection with the second reversing bevel gear, and the second planetary gear train is in transmission connection with the third reversing bevel gear;
and the tail pushing output mechanism comprises a third bevel gear and a tail pushing output shaft, the third bevel gear is simultaneously meshed with the second reversing bevel gear and the third reversing bevel gear, and the tail pushing output shaft is in transmission connection with the third bevel gear.
2. A coaxial dual rotor tailed propeller drive system according to claim 1,
the number of the primary reversing transmission mechanisms is multiple, and each primary reversing transmission mechanism is connected with one power input shaft;
the number of the second bevel gears is multiple, each second bevel gear is in transmission connection with one first reversing bevel gear, and the second bevel gears are simultaneously meshed with the second reversing bevel gear and the third reversing bevel gear.
3. A coaxial dual rotor tailed propeller drive system according to claim 1,
the first planetary gear train comprises a first sun gear, a first planetary gear, a first inner gear ring and a first planet carrier, the first sun gear and the second reversing bevel gear are fixed on the same transmission shaft, the first planetary gear is externally meshed with the first sun gear, the first planetary gear is internally meshed with the first inner gear ring, the first planetary gear is connected with the first planet carrier, and the first planet carrier is in transmission connection with the outer rotor shaft.
4. A coaxial dual rotor tailed propeller drive system according to claim 1,
the second planetary gear train comprises a second sun gear, a second planetary gear, a second inner gear ring and a second planet carrier, the second sun gear and the third reversing bevel gear are fixed on the same transmission shaft, the second planetary gear is externally meshed with the second sun gear, the second planetary gear is internally meshed with the second inner gear ring, the second planetary gear is connected with the second planet carrier, and the second planet carrier is in transmission connection with the inner rotor shaft.
5. A coaxial dual rotor tailed propeller drive system according to claim 1,
the tail pushing output mechanism further comprises a first cylindrical gear, a second cylindrical gear and a third cylindrical gear, the first cylindrical gear and the third bevel gear are fixed on the same transmission shaft, the second cylindrical gear is meshed with the first cylindrical gear, the third cylindrical gear is meshed with the second cylindrical gear, and the tail pushing output shaft is fixedly connected with the third cylindrical gear.
6. A coaxial dual rotor tailed propeller drive system according to claim 5,
the number of the second cylindrical gears is two, and the two second cylindrical gears are simultaneously meshed with the first cylindrical gear and the third cylindrical gear.
7. A coaxial dual-rotor tailed propeller drive system according to claim 5, wherein said first cylindrical gear, said second cylindrical gear, and said third cylindrical gear are helical gears.
8. A coaxial twin rotor tailed propeller drive system as defined in claim 1, further comprising a housing and a support rod, wherein the primary reversing gear, the secondary reversing gear, the coaxial twin rotor output and the tailed thrust output are disposed within the housing, one end of the support rod is connected to the housing, and the other end of the support rod is adapted to be connected to a helicopter for mounting the housing on the helicopter.
9. A coaxial twin rotor tailed propeller drive system as defined in claim 8, wherein said support rods are V-shaped and said number of support rods is four, said housing being mounted to the helicopter by four of said support rods.
10. A helicopter comprising a coaxial twin rotor tailed propeller drive system according to any of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010711619.9A CN111874239A (en) | 2020-07-22 | 2020-07-22 | Coaxial double-rotor-wing propeller transmission system with tail and helicopter |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010711619.9A CN111874239A (en) | 2020-07-22 | 2020-07-22 | Coaxial double-rotor-wing propeller transmission system with tail and helicopter |
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| CN111874239A true CN111874239A (en) | 2020-11-03 |
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| CN202010711619.9A Pending CN111874239A (en) | 2020-07-22 | 2020-07-22 | Coaxial double-rotor-wing propeller transmission system with tail and helicopter |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113483059A (en) * | 2021-07-07 | 2021-10-08 | 重庆大学 | Torque-dividing transmission speed reducing device for coaxial helicopter |
| WO2023164862A1 (en) * | 2022-03-03 | 2023-09-07 | 罗灿 | Dual-propeller universal transmission device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101101047A (en) * | 2007-08-06 | 2008-01-09 | 刘淮滨 | Constant-speed differential speed double-axis reverse output transmission method and device |
| US20090057482A1 (en) * | 2007-08-29 | 2009-03-05 | Charles Lin | Transmission Device for a Twin-Rotor Helicopter |
| CN105173070A (en) * | 2015-07-30 | 2015-12-23 | 北京航空航天大学 | Combined coaxial unmanned helicopter |
| CN109707798A (en) * | 2019-01-07 | 2019-05-03 | 南京航空航天大学 | The coaxial rotor transmission device of bevel gear-roller gear power dividing twice |
| CN111301670A (en) * | 2020-03-19 | 2020-06-19 | 常州华创航空科技有限公司 | Coaxial double-rotor helicopter main speed reducer and helicopter |
-
2020
- 2020-07-22 CN CN202010711619.9A patent/CN111874239A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101101047A (en) * | 2007-08-06 | 2008-01-09 | 刘淮滨 | Constant-speed differential speed double-axis reverse output transmission method and device |
| US20090057482A1 (en) * | 2007-08-29 | 2009-03-05 | Charles Lin | Transmission Device for a Twin-Rotor Helicopter |
| CN105173070A (en) * | 2015-07-30 | 2015-12-23 | 北京航空航天大学 | Combined coaxial unmanned helicopter |
| CN109707798A (en) * | 2019-01-07 | 2019-05-03 | 南京航空航天大学 | The coaxial rotor transmission device of bevel gear-roller gear power dividing twice |
| CN111301670A (en) * | 2020-03-19 | 2020-06-19 | 常州华创航空科技有限公司 | Coaxial double-rotor helicopter main speed reducer and helicopter |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113483059A (en) * | 2021-07-07 | 2021-10-08 | 重庆大学 | Torque-dividing transmission speed reducing device for coaxial helicopter |
| WO2023164862A1 (en) * | 2022-03-03 | 2023-09-07 | 罗灿 | Dual-propeller universal transmission device |
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