CN217554187U - Transmission structure of tilt-rotor aircraft - Google Patents
Transmission structure of tilt-rotor aircraft Download PDFInfo
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- CN217554187U CN217554187U CN202220408117.3U CN202220408117U CN217554187U CN 217554187 U CN217554187 U CN 217554187U CN 202220408117 U CN202220408117 U CN 202220408117U CN 217554187 U CN217554187 U CN 217554187U
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Abstract
The utility model provides a transmission structure of gyroplane verts, include: first rotor mechanism, second rotor mechanism, jackshaft and annex transmission portion, the jackshaft is connected first derailleur and the second derailleur that verts, annex transmission portion includes first annex gear train and second annex gear train, the first annex gear train with first oil pump gear that verts the derailleur and be connected, with oil pump gear meshing's hydraulic pump gear and with hydraulic pump gear meshing's radiator gear, the second annex gear train is connected with the second derailleur that verts and the structure is the same with first annex gear train. The utility model discloses a setting and the multi-functional annex transmission portion that has that the derailleur is connected that verts, mutually supporting tandem work with oil pump, hydraulic pump and radiator, realized lubricating each friction position of gyroplane, control and dispel the heat the cooling to the cabin in the motion of pneumatic cylinder and verting of rotor.
Description
Technical Field
The utility model belongs to the technical field of the aircraft power transmission technique and specifically relates to a transmission structure of rotorcraft verts.
Background
The tilt rotor aircraft is a novel aircraft which has the functions of vertical take-off and landing and hovering of a helicopter and also has the high-speed flight capability of a fixed-wing aircraft. The tilting rotor aircraft has the technical characteristics of high speed and long range, and good economy, and has become the main development direction of the military and civil rotor aircraft.
At present, the tilt rotor aircraft driven by an engine in China is still in a starting stage, the function is not complete, the transmission setting on the functions of controlling a tilt part, dissipating heat in an engine cabin, lubricating a transmission system and the like is complex and incomplete, and the service performance and the safety performance of the aircraft are greatly influenced.
Therefore, there is a need for a transmission structure for a tiltrotor aircraft that overcomes the above-mentioned deficiencies.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a transmission structure of gyroplane verts.
According to an aspect of the utility model, a provide a transmission structure of rotorcraft verts, include:
a first rotor mechanism comprising a first speed change assembly comprising a first tilt transmission;
a second rotor mechanism comprising a second transmission assembly comprising a second tilt transmission;
an intermediate shaft connecting the first and second tilt transmissions;
an accessory drive comprising a first accessory gear train connected to a first tilt transmission for driving an accessory connected thereto.
Preferably, the first accessory gear train includes an oil pump gear connected to the first tilting transmission, a hydraulic pump gear engaged with the oil pump gear, and a radiator gear engaged with the hydraulic pump gear.
Preferably, the outer end of the first tilting transmission is provided with an accessory drive gear, and the oil pump gear is meshed with the accessory drive gear.
Preferably, the accessory drive further comprises a second accessory gear train connected to the second tilt transmission and having the same structure as the first accessory gear train.
Preferably, the first rotor mechanism further comprises a first rotor and a first engine, and the first rotor is in transmission connection with the first engine through the first speed change assembly;
the second rotor mechanism further comprises a second rotor and a second engine, and the second rotor is in transmission connection with the second engine through the second speed change assembly.
Preferably, the first transmission assembly further comprises a first transmission and a first connecting shaft connecting the first transmission and a first tilt transmission, the first tilt transmission being in driving connection with the intermediate shaft;
the second speed change assembly further comprises a second speed changer and a second connecting shaft for connecting the second speed changer and the second tilting speed changer, and the second tilting speed changer is in transmission connection with the intermediate shaft.
Preferably, the device further comprises a first rotor wing operating mechanism, a second rotor wing operating mechanism and a fixed plate, wherein one end of the first rotor wing operating mechanism is connected with the fixed plate, the other end of the first rotor wing operating mechanism is connected with the first connecting shaft and controls the first connecting shaft to tilt around the axis of the intermediate shaft;
second rotor operating device one end with the fixed plate is connected, the second rotor operating device other end with the second connecting shaft is connected and control second connecting shaft and incline around the axis of jackshaft and vert.
Preferably, the first transmission comprises a first gear train connected with the first engine, a second gear train connected with the first rotor, and a first planetary gear train connected with the planetary gear train;
the second transmission comprises a third variable-speed gear train, a fourth variable-speed gear train and a second planetary gear train, the third variable-speed gear train is connected with the second engine, the second planetary gear train is connected with the second rotor, and the fourth variable-speed gear train is connected with the second planetary gear train.
Preferably, the first gear train is connected with the second gear train through a first clutch, and the third gear train is connected with the fourth gear train through a second clutch.
Preferably, an intermediate transmission is arranged on the intermediate shaft, the intermediate transmission comprises a braking mechanism gear, an alternating current motor gear meshed with the braking mechanism gear and a direct current motor gear meshed with the alternating current motor gear, a first gear is arranged on the intermediate shaft, and the braking mechanism gear is meshed with the first gear.
Compared with the prior art, the utility model provides a pair of tilt rotor's transmission structure has following beneficial effect: through setting up the accessory transmission portion that has multiple functions of being connected with the derailleur that verts, mutually support oil pump, hydraulic pump and radiator and establish ties work, realized lubricating each friction position of gyroplane, control and dispel the heat the cooling to the cabin in the motion of pneumatic cylinder and verting of rotor.
Drawings
The invention will be described in further detail with reference to the following drawings and embodiments:
fig. 1 is a transmission structure diagram of a tiltrotor aircraft according to the present invention;
fig. 2 is a partial perspective view of the tiltrotor aircraft of the present invention;
fig. 3 is a transmission structure diagram of a first rotor mechanism of the tiltrotor aircraft according to the present invention;
fig. 4 is a transmission structure diagram of a second rotor mechanism of the tiltrotor aircraft according to the present invention;
fig. 5 is a transmission structure diagram of the intermediate speed reducer of the tiltrotor aircraft of the present invention.
1. First rotor, 2, first engine, 3, first transmission assembly, 31, first transmission, 311, first gear train, 3111, first driving gear, 3112, first idler gear, 3113, first driven gear, 312, second gear train, 3121, first transmission gear, 3122, first output gear, 313, first planetary gear train, 3131, sun gear, 3132, planetary gear train 3133, a ring gear, 3134, a planet carrier, 32, a first tilting transmission, 321, a first input bevel gear, 322, a first output bevel gear, 33, a first connecting shaft, 4, a second rotor, 5, a second engine, 6, a second speed change assembly, 61, a second speed changer, 611, a third speed change gear train, 6111, a second driving gear, 6112, a second idle gear, 6113, a third idle gear 6114, a second driven gear, 612, a fourth gear train, 6121, a second transmission gear, 6122, a second output gear, 613, a second planetary gear train, 62, a second tilting transmission, 63, a second connecting shaft, 7, an intermediate shaft, 8, an intermediate transmission, 81, a first gear, 82, a brake mechanism gear, 83, an alternating current motor gear, 84, a direct current motor gear, 91, a first clutch, 92, a second clutch, 101, a first rotor operating mechanism, 102, a second rotor operating mechanism, 103, a fixed plate, 104, a flexible connecting piece, 105, a fixed piece, 106, a first oil pump gear, 10, an accessory transmission part, 11, a first accessory gear train, 111, an accessory driving gear, 112, a second gear 113, a hydraulic pump gear, 114, a radiator gear, 12 and a second accessory gear train.
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 these drawings without creative efforts.
For the sake of simplicity, only the parts relevant to the present invention are schematically shown in the drawings, 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 meaning 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 embodiments of the present invention or technical solutions in the prior art, specific embodiments of the present invention will be described below with reference to the accompanying drawings. It is obvious that the drawings in the following description are only examples of the invention, and that for a person skilled in the art, other drawings and embodiments can be obtained from these drawings without inventive effort.
Referring to fig. 1, a rotorcraft includes a first rotor mechanism, a second rotor mechanism, an intermediate shaft 7, an intermediate transmission 8, and an attachment transmission portion 10, the intermediate shaft 7 connecting the first rotor mechanism and the second rotor mechanism, the intermediate transmission 8 being disposed on the intermediate shaft.
As shown in fig. 1, the first rotor mechanism includes a first rotor 1, a first engine 2, and a first transmission assembly 3. The first transmission assembly 3 comprises a first transmission 31, a first tilt transmission 32 and a first connecting shaft 33 connecting the first transmission 31 and the first tilt transmission 32. The first transmission 31 comprises a first gear train 311, a second gear train 312 and a first planetary gear train 313.
The first gear train 311 includes a first drive gear 3111 provided coaxially with the output shaft of the first engine 2, a first idle gear 3112 meshing with the first drive gear 3111, and a first driven gear 3113 meshing with the first idle gear 3112.
The second gear train 312 includes a first transmission gear 3121 coaxially disposed with the first driven gear 3113 and a first output gear 3122 meshed with the first transmission gear 3121, and the first driven gear 3113 is connected with the first transmission gear 3121 through the first clutch 91.
The first planetary gear train 313 includes a sun gear 3131, a planet gear 3131, a ring gear 3133, and a planet carrier 3134, which are coaxially disposed with the first output gear 3122, and the first rotor 1 is coaxially disposed with the planet carrier 3134.
The first tilt transmission 32 includes a first input bevel gear 321 and a first output bevel gear 322, the first input bevel gear 321 and the first output bevel gear 322 are engaged with each other and vertically disposed, the first input bevel gear 321 is disposed coaxially with the lower end of the first connecting shaft 33, the first output bevel gear 322 is disposed coaxially with one end of the intermediate shaft 7, and the upper end of the first connecting shaft 33 is engaged with the first output gear 3122 through a spur gear.
The first connecting shaft 33 and the intermediate shaft 7 are both fixed in a short cabin of the rotorcraft, the first connecting shaft 33 being perpendicular to the intermediate shaft 7 and being rotatable about the axis of the intermediate shaft 7.
As shown in fig. 2, the second rotor mechanism includes a second rotor 4, a second engine 5, and a second transmission assembly 6. The second transmission assembly 6 includes a second transmission 61, a second tilt transmission 62, and a second connecting shaft 63 connecting the second transmission 61 and the second tilt transmission 62. The second transmission 61 includes a third gear train 611, a fourth gear train 612 and a second planetary gear train 613.
The third gear train 611 includes a second driving gear 6111 coaxially disposed with the output shaft of the second engine 5, a second idle gear 6112 engaged with the second driving gear 6111, a third idle gear 6113 engaged with the second idle gear and a second driven gear 6114 engaged with the third idle gear 6113, and compared with the first gear train 311, the third gear train 611 adds an idle gear to ensure that the selection directions of the rotors are opposite.
The fourth gear train 612 includes a second transmission gear 6121 coaxially disposed with the second driven gear 6114 and a second output gear 6122 engaged with the second transmission gear 6121, and the second driven gear 6114 is connected with the second transmission gear 6121 through the second clutch 92.
The second planetary gear train 613 has the same structure as the first planetary gear train 313.
The second tilting transmission 62 has the same structure as the first tilting transmission 32.
The second connecting shaft 63 and the intermediate shaft 7 are both fixed in the short cabin of the rotorcraft, the second connecting shaft 63 being perpendicular to the intermediate shaft 7 and being rotatable about the axis of the intermediate shaft 7.
The rotorcraft further comprises a first rotor operating mechanism 101, a second rotor operating mechanism 102 and a fixing plate 103 for fixing the first rotor operating mechanism 101 and the second rotor operating mechanism 102, wherein one end of the first rotor operating mechanism 101 is connected with the fixing plate 103, the other end of the first rotor operating mechanism 101 is connected with the first connecting shaft 33 and controls the first connecting shaft 33 to tilt around the axis of the intermediate shaft 7; one end of the second rotor control mechanism 102 is connected with the fixing plate 103, and the other end of the second rotor control mechanism 102 is connected with the second connecting shaft 63 and controls the second connecting shaft 63 to tilt around the axis of the intermediate shaft 7. The first rotor wing control mechanism 101 and the second rotor wing control mechanism 102 have the same structure, are controlled by a single hydraulic cylinder rod, and control over the movement speed and direction of the hydraulic cylinder is realized through a control valve.
The first connecting shaft 33, the second connecting shaft 63 and the intermediate shaft 7 are respectively provided with a flexible connecting piece 104, and axial, radial and angular deviations between the two axes are compensated through the flexible connecting pieces 104, so that the wing has a certain angle of upwarping relative to the fuselage, and the whole fuselage meets the requirement of aerodynamic layout. Preferably, the flexible connection 104 employs a membrane disc coupling. The intermediate shaft 7 is fixed to the fixed plate 103 by a plurality of fixing members 105, one end of the fixing member 105 is connected to the flexible connecting member 104, and the other end of the fixing member 105 is fixed to the fixed plate 103.
The rotorcraft outputs power through the engine, performs first-stage speed reduction through the driving gear, the idler gear and the driven gear, performs second-stage speed reduction through the transmission gear and the output gear, and finally outputs the power to the rotor after performing third-stage speed reduction through the planetary gear train.
The utility model discloses a tilt gyroplane both sides are provided with the turboshaft engine respectively, and the power of engine can two-way circulation. When a single engine failure occurs, another engine powers both rotors. When the first engine 2 fails, the first clutch 91 is disconnected, the first gear train 311 and the second gear train 312 are disconnected, and the output power of the second engine 5 is transmitted from the third gear train 611 to the first rotor 1 through the second clutch 92, the fourth gear train 612, the second connecting shaft 63, the second tilting transmission 62, the intermediate shaft 7, the first tilting transmission 32, the first connecting shaft 33, the second gear train 312 and the first planetary gear train 313 in sequence, so that the two rotors rotate simultaneously.
When the second engine 5 fails, power is transmitted in the same manner as described above, in the opposite path, to drive the second rotor 4 to rotate.
When the first engine 2 and the second engine 5 simultaneously break down, the connection between the engines and the rotors is disconnected through the clutch, the first speed change assembly 3, the second speed change assembly 6 and the intermediate shaft 7 realize synchronous spinning and gliding of the two pairs of rotors, and stable landing is realized.
The second gear train 312 and the fourth gear train 612 are both connected with oil pumps, and the outer sides of the first transmission gear 3121 and the second transmission gear 6121 are both engaged with the first oil pump gear 106.
The accessory drive part 10 includes a first accessory gear train 11 and a second accessory gear train 12, and the first accessory gear train 11 includes a second oil pump gear 112 engaged with an accessory drive gear 111 coaxially disposed at an outer end of a first input bevel gear 321, a hydraulic pump gear 113 engaged with the second oil pump gear 112, and a radiator gear 114 engaged with the hydraulic pump gear 113.
The second oil pump gear 112 drives the oil pump to work, so that lubricating oil is delivered to each friction part of the rotorcraft for lubrication. Drive hydraulic pump work through hydraulic pump gear 113 to the motion to the pneumatic cylinder is controlled, makes the short storehouse of both sides rotate around the axis of jackshaft, realizes verting of rotor. The radiator gear 114 drives the radiator to work, and the radiator is preferably a fan, and cools the cabin.
The second accessory gear train is connected to the second tilting transmission 62 and is identical in structure to the first accessory gear train 11.
The intermediate transmission 8 includes a first gear 81, a brake mechanism gear 82, an ac motor gear 83, and a dc motor gear 84, the first gear 81 being provided on the intermediate shaft 7, the brake mechanism gear 82 being engaged with the first gear 81, the ac motor gear 83 being engaged with the first gear 81, and the dc motor gear 84 being engaged with the ac motor gear 83.
The brake gear 82 is connected with a brake disc of the rotorcraft, when in a braking state, the first clutch 91 and the second clutch 92 are disconnected, and the brake gear 82 inhibits the rotation of the gear train, so that the rotation speed of the intermediate shaft 7 is reduced, and the rotation speeds of wings on two sides are reduced until the wings are stopped. Alternating current motor gear 83 is connected with alternating current motor, and direct current motor gear 84 is connected with direct current motor, drives the rotation of each gear in the intermediate speed changer 8 through the rotation of jackshaft 7 to drive direct current motor and alternating current motor work, for the electronic equipment power supply on the rotor aircraft that verts.
It will be apparent to those skilled in the art that various modifications and variations can be made to the above-described exemplary embodiments of the present invention without departing from the spirit and scope of the invention. Thus, it is intended that the present invention cover the modifications and variations of this invention provided they come within the scope of the appended claims and their equivalents.
Claims (10)
1. A transmission structure of a tiltrotor aircraft, comprising:
a first rotor mechanism comprising a first speed change assembly comprising a first tilt transmission;
a second rotor mechanism comprising a second transmission assembly comprising a second tilt transmission;
an intermediate shaft connecting the first and second tilt transmissions;
an accessory drive comprising a first accessory gear train connected to a first tilt transmission for driving an accessory connected thereto.
2. The rotorcraft transmission structure of claim 1, wherein the first accessory gear train includes an oil pump gear connected to the first tilt transmission, a hydraulic pump gear meshed with the oil pump gear, and a radiator gear meshed with the hydraulic pump gear.
3. The rotorcraft transmission structure of claim 2, wherein an accessory drive gear is provided at an outer end of the first tilt transmission, and the oil pump gear is in mesh with the accessory drive gear.
4. The rotorcraft transmission structure of claim 3, wherein the accessory drive further includes a second accessory gear train connected to the second tilt transmission and having the same structure as the first accessory gear train.
5. The rotorcraft transmission structure of claim 1, wherein the first rotor mechanism further comprises a first rotor and a first engine, the first rotor being drivingly connected to the first engine through the first speed change assembly;
the second rotor mechanism further comprises a second rotor and a second engine, and the second rotor is in transmission connection with the second engine through the second speed change assembly.
6. The rotorcraft transmission arrangement of claim 1, wherein the first transmission assembly further includes a first transmission and a first connecting shaft connecting the first transmission and a first tilt transmission, the first tilt transmission being drivingly connected to the intermediate shaft;
the second speed change assembly comprises a second speed changer and a second connecting shaft which is connected with the second speed changer and the second tilting speed changer, and the second tilting speed changer is in transmission connection with the intermediate shaft.
7. The transmission structure of a rotorcraft according to claim 6, further comprising a first rotor operating mechanism, a second rotor operating mechanism, and a fixed plate, the first rotor operating mechanism having one end connected to the fixed plate and the other end connected to the first connecting shaft and controlling the first connecting shaft to tilt about the intermediate shaft axis;
second rotor operating device one end with the fixed plate is connected, the second rotor operating device other end with the second connecting shaft is connected and control second connecting shaft and incline around the axis of jackshaft and vert.
8. The rotorcraft transmission arrangement of claim 6, wherein the first transmission includes a first gear train coupled to the first engine, a second gear train coupled to the first rotor, and a first planetary gear train coupled to the planetary gear train;
the second transmission comprises a third variable-speed gear train, a fourth variable-speed gear train and a second planetary gear train, the third variable-speed gear train is connected with the second engine, the second planetary gear train is connected with the second rotor, and the fourth variable-speed gear train is connected with the second planetary gear train.
9. The rotorcraft transmission structure of claim 8, wherein the first gear train is coupled to the second gear train via a first clutch, and the third gear train is coupled to the fourth gear train via a second clutch.
10. The transmission structure of a rotary-wing aircraft according to claim 1, wherein an intermediate transmission is provided on the intermediate shaft, the intermediate transmission including a first gear provided on the intermediate shaft, a brake gear meshing with the first gear, an ac motor gear meshing with the first gear, and a dc motor gear meshing with the ac motor gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220408117.3U CN217554187U (en) | 2022-02-25 | 2022-02-25 | Transmission structure of tilt-rotor aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220408117.3U CN217554187U (en) | 2022-02-25 | 2022-02-25 | Transmission structure of tilt-rotor aircraft |
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| Publication Number | Publication Date |
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| CN217554187U true CN217554187U (en) | 2022-10-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202220408117.3U Active CN217554187U (en) | 2022-02-25 | 2022-02-25 | Transmission structure of tilt-rotor aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114655453A (en) * | 2022-02-25 | 2022-06-24 | 常州华创航空科技有限公司 | Tilt-rotor aircraft |
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2022
- 2022-02-25 CN CN202220408117.3U patent/CN217554187U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114655453A (en) * | 2022-02-25 | 2022-06-24 | 常州华创航空科技有限公司 | Tilt-rotor aircraft |
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