CN210971557U - Aircraft power system - Google Patents
Aircraft power system Download PDFInfo
- Publication number
- CN210971557U CN210971557U CN201921655520.0U CN201921655520U CN210971557U CN 210971557 U CN210971557 U CN 210971557U CN 201921655520 U CN201921655520 U CN 201921655520U CN 210971557 U CN210971557 U CN 210971557U
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- China
- Prior art keywords
- bevel gear
- aircraft
- sleeve
- propeller
- driving
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- 230000008878 coupling Effects 0.000 claims abstract description 14
- 238000010168 coupling process Methods 0.000 claims abstract description 14
- 238000005859 coupling reaction Methods 0.000 claims abstract description 14
- 230000005540 biological transmission Effects 0.000 claims description 6
- 230000002146 bilateral effect Effects 0.000 claims description 2
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Abstract
The utility model relates to an aircraft driving system, including aircraft fuselage and two motors and the screw of setting in aircraft fuselage inside, the screw includes screw one and screw two that the interval set up, all be provided with steering wheel assembly on screw one and the screw two, still including being used for two the power coupling of motor output carries out the power coupling device who distributes, power coupling device includes drive unit, drive unit and casing. The utility model discloses a rotational speed of two motors in the adjustment aircraft fuselage forces two screws to rotate along with the casing, and steering angle is unrestricted, has increased the gesture control means of aircraft, and to a great extent has improved the adaptability of aircraft to the environment.
Description
Technical Field
The utility model relates to an aircraft technical field, concretely relates to aircraft driving system.
Background
The electronic double rotor aircraft of tradition adopts coaxial double-oar formula screw design more, sets up two screws along same axial interval promptly, by the rotatory lift that produces of two motor drive screw in the aircraft fuselage to the pitch through steering wheel subassembly control paddle realizes the adjustment of self gesture, however, the pure dependence parallel operation gear that relies on when two motors carry out parallel operation carries out the coupling, and the screw can only rotate a certain fixed angle, can not adjust as required and turn to the angle, and is poor to the adaptability of environment.
Disclosure of Invention
The utility model discloses a solve among the current aircraft screw can only rotate a certain fixed angle, can not adjust as required and turn to the angle, to the poor problem of adaptability of environment, provide one kind can adjust the aircraft driving system of screw steering angle as required.
In order to realize the purpose, the technical scheme of the utility model is that:
an aircraft power system comprises an aircraft body, two motors and propellers, wherein the two motors and the propellers are arranged in the aircraft body, the propellers comprise a first propeller and a second propeller which are arranged at intervals, steering engine assemblies are arranged on the first propeller and the second propeller, the aircraft power system also comprises a power coupling device which is used for coupling and distributing power output by the two motors, and the power coupling device comprises a transmission unit, a driving unit and a shell;
the transmission unit comprises a first driving bevel gear and a second driving bevel gear which are positioned in the shell, the first driving bevel gear is fixedly connected with a first power output shaft, one end of the first power output shaft penetrates through the shell and the first sleeve to be connected with one motor, the second driving bevel gear is fixedly connected with a second power output shaft, and one end of the second power output shaft penetrates through the shell and the second sleeve to be connected with the other motor;
the driving unit comprises a first driven bevel gear and a second driven bevel gear which are positioned in the shell, the first driven bevel gear is connected to the first propeller through a first driving shaft, and the second driven bevel gear is connected to the second propeller through a second driving shaft.
Furthermore, the first driving bevel gear and the second driving bevel gear are arranged in the shell in a bilateral symmetry manner, the first driven bevel gear and the second driven bevel gear are meshed with the first driving bevel gear and the second driving bevel gear together, and the axes of the first driving bevel gear, the second driving bevel gear, the first driven bevel gear and the second driven bevel gear are in a cross shape.
Furthermore, the first power output shaft is located in the first sleeve, the second power output shaft is located in the second sleeve, one ends of the first sleeve and the second sleeve are fixedly connected with the aircraft body, and the other ends of the first sleeve and the second sleeve are both in threaded connection with the shell.
Furthermore, the inner wall of one end of the threaded connection of the first sleeve and the shell is provided with a forward thread, and the inner wall of one end of the threaded connection of the second sleeve and the shell is provided with a reverse thread.
Further, the axial both ends of casing along screw one and screw two all are equipped with the bearing, every the bearing sets up respectively in the end cover, the end cover lock is outside at the casing.
Through the technical scheme, the beneficial effects of the utility model are that:
the utility model has simple and compact structure, on one hand, two motors in the aircraft body couple the power through the power coupling device and then respectively transmit the power to the two propellers, and the flight power is normally provided for the aircraft; on the other hand, the two propellers are forced to rotate along with the shell by adjusting the rotating speeds of the two motors, the steering angle is not limited, the attitude adjusting means of the aircraft is increased, and the adaptability of the aircraft to the environment is improved to a great extent.
Drawings
FIG. 1 is a schematic diagram of an aircraft power system of the present invention;
fig. 2 is a schematic diagram of a power coupling device in an aircraft power system according to the present invention.
The reference numbers in the drawings are as follows: the aircraft comprises an aircraft body 1, a first propeller 2, a second propeller 3, a steering engine assembly 4, a shell 5, a first driving bevel gear 6, a second driving bevel gear 7, a first power output shaft 8, a first sleeve 9, a second power output shaft 10, a second sleeve 11, a first driven bevel gear 12, a second driven bevel gear 13, a first driving shaft 14, a second driving shaft 15, a bearing 16 and an end cover 17.
Detailed Description
The invention will be further explained with reference to the drawings and the detailed description below:
as shown in fig. 1-2, an aircraft power system comprises an aircraft body 1, and two motors and propellers arranged inside the aircraft body 1, wherein the propellers comprise a first propeller 2 and a second propeller 3 which are arranged at intervals, and steering engine assemblies 4 are arranged on the first propeller 2 and the second propeller 3; the power coupling device is used for coupling and distributing power output by the two motors and comprises a transmission unit, a driving unit and a shell 5.
Specifically, the transmission unit comprises a first driving bevel gear 6 and a second driving bevel gear 7 which are positioned in a shell 5, the first driving bevel gear 6 is fixedly connected with a first power output shaft 8, one end of the first power output shaft 8 penetrates through the shell 5 and a first sleeve 9 to be connected with one of the motors, the second driving bevel gear 7 is fixedly connected with a second power output shaft 10, and one end of the second power output shaft 10 penetrates through the shell 5 and a second sleeve 11 to be connected with the other motor; the drive unit comprises a first driven bevel gear 12 and a second driven bevel gear 13 located within the housing 5, the first driven bevel gear 12 being connected to the first propeller 2 by a first drive shaft 14, the second driven bevel gear 13 being connected to the second propeller 3 by a second drive shaft 15.
In this embodiment, the first driving bevel gear 6 and the second driving bevel gear 7 are symmetrically arranged in the housing 5, the first driven bevel gear 12 and the second driven bevel gear 13 are engaged with the first driving bevel gear 6 and the second driving bevel gear 7, and the axes of the first driving bevel gear 6, the second driving bevel gear 7, the first driven bevel gear 12 and the second driven bevel gear 13 are in a cross shape.
Specifically, a first power output shaft 8 is positioned in a first sleeve 9, a second power output shaft 10 is positioned in a second sleeve 11, one ends of the first sleeve 9 and the second sleeve 11 are fixedly connected with an aircraft fuselage 1, the other ends of the first sleeve 9 and the second sleeve 11 are both in threaded connection with a shell 5, meanwhile, the inner wall of one end of the threaded connection of the first sleeve 9 and the shell 5 is provided with a forward thread, and the inner wall of one end of the threaded connection of the second sleeve 11 and the shell 5 is provided with a reverse thread; in addition, the two axial ends of the first propeller 2 and the second propeller 3 of the shell 5 are respectively sleeved with a bearing 16, each bearing 16 is arranged in an end cover 17, and the end covers 17 are buckled outside the shell 5.
In the actual flight of the aircraft, the rotating speeds of two motors in the aircraft body 1 are the same in size but opposite in direction, the rotating speeds of the first driving bevel gear 6, the second driving bevel gear 7, the first driven bevel gear 12 and the second driven bevel gear 13 are the same in size, the rotating directions of the first propeller 2 and the second propeller 3 are opposite in direction, and the first propeller and the second propeller jointly act to provide lift force for the aircraft; when the rotating speeds of the two motors in the aircraft body 1 are different, the rotating speeds of the first driving bevel gear 6 and the second driving bevel gear 7 are inevitably different, the first driven bevel gear 12 forces the first driving shaft 14 to generate acting force along the circumferential direction of the first power output shaft 8, correspondingly, the second driven bevel gear 13 forces the second driving shaft 15 to generate acting force along the circumferential direction of the first power output shaft 8, the two acting forces are mutually overlapped to drive the shell 5 to rotate, the first propeller 2 and the second propeller 3 rotate along with the shell 5, and therefore the adjustment of the steering angle of the propellers in the aircraft is achieved by adjusting the rotating speeds of the two motors in the aircraft body 1.
The above embodiments are merely preferred embodiments of the present invention, and not intended to limit the scope of the invention, so that equivalent changes and modifications made according to the structure, characteristics and principles of the present invention are all included in the scope of the present invention.
Claims (5)
1. An aircraft power system comprises an aircraft body (1), two motors and two propellers arranged inside the aircraft body (1), wherein each propeller comprises a first propeller (2) and a second propeller (3) which are arranged at intervals, and a steering engine assembly (4) is arranged on each of the first propeller (2) and the second propeller (3), and the aircraft power system is characterized by further comprising a power coupling device which is used for coupling and distributing power output by the two motors, wherein the power coupling device comprises a transmission unit, a driving unit and a shell (5);
the transmission unit comprises a first driving bevel gear (6) and a second driving bevel gear (7) which are positioned in a shell (5), the first driving bevel gear (6) is fixedly connected with a first power output shaft (8), one end of the first power output shaft (8) penetrates through the shell (5) and a first sleeve (9) to be connected with one of the motors, the second driving bevel gear (7) is fixedly connected with a second power output shaft (10), and one end of the second power output shaft (10) penetrates through the shell (5) and a second sleeve (11) to be connected with the other motor;
the driving unit comprises a first driven bevel gear (12) and a second driven bevel gear (13) which are positioned in a shell (5), wherein the first driven bevel gear (12) is connected to the first propeller (2) through a first driving shaft (14), and the second driven bevel gear (13) is connected to the second propeller through a second driving shaft (15).
2. The aircraft power system according to claim 1, wherein the first driving bevel gear (6) and the second driving bevel gear (7) are arranged in the housing (5) in a bilateral symmetry manner, the first driven bevel gear (12) and the second driven bevel gear (13) are meshed with the first driving bevel gear (6) and the second driving bevel gear (7) together, and the axes of the first driving bevel gear (6), the second driving bevel gear (7), the first driven bevel gear (12) and the second driven bevel gear (13) are in a cross shape.
3. The aircraft power system according to claim 1, characterized in that the first power take-off shaft (8) is located in the first sleeve (9), the second power take-off shaft (10) is located in the second sleeve (11), one end of the first sleeve (9) and one end of the second sleeve (11) are fixedly connected to the aircraft fuselage (1), and the other end of the first sleeve (9) and the other end of the second sleeve (11) are both in threaded connection with the housing (5).
4. The aircraft power system according to claim 3, characterized in that the first sleeve (9) is threaded with the housing (5) in a forward direction on the inner wall of one end and the second sleeve (11) is threaded with the housing (5) in a reverse direction on the inner wall of one end.
5. The aircraft power system according to claim 1, characterized in that the housing (5) is provided with bearings (16) at both axial ends of the first propeller (2) and the second propeller (3), each bearing (16) is arranged in an end cover (17), and the end covers (17) are fastened outside the housing (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921655520.0U CN210971557U (en) | 2019-09-30 | 2019-09-30 | Aircraft power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921655520.0U CN210971557U (en) | 2019-09-30 | 2019-09-30 | Aircraft power system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210971557U true CN210971557U (en) | 2020-07-10 |
Family
ID=71455172
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921655520.0U Expired - Fee Related CN210971557U (en) | 2019-09-30 | 2019-09-30 | Aircraft power system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210971557U (en) |
-
2019
- 2019-09-30 CN CN201921655520.0U patent/CN210971557U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200710 |