CN220955819U - Generator rotor mounting structure of aviation piston engine - Google Patents
Generator rotor mounting structure of aviation piston engine Download PDFInfo
- Publication number
- CN220955819U CN220955819U CN202322823557.2U CN202322823557U CN220955819U CN 220955819 U CN220955819 U CN 220955819U CN 202322823557 U CN202322823557 U CN 202322823557U CN 220955819 U CN220955819 U CN 220955819U
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- Prior art keywords
- generator
- generator rotor
- screw
- connecting shaft
- piston engine
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Links
- 238000009434 installation Methods 0.000 claims description 7
- 239000003921 oil Substances 0.000 description 7
- 239000010720 hydraulic oil Substances 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention discloses a generator rotor mounting structure of an aviation piston engine, which comprises a crankshaft assembly, a generator rotor assembly, a generator connecting shaft and a propeller, and is characterized in that: the crankshaft assembly comprises a crankshaft, a screw 1 and a gasket, the generator connecting shaft is connected with the crankshaft through a conical surface and is clamped with the gasket through the screw 1, the generator rotor assembly comprises a generator rotor and a screw 2, the generator rotor is arranged on the inner side of the generator connecting shaft and is clamped through the screw 2, the propeller is arranged on the other side of the generator connecting shaft, the generator connecting shaft is provided with an inner hole, and the centering is realized through the inner hole and the propeller. The generator rotor mounting structure of the aviation piston engine can enable the engine to be compact in structure.
Description
Technical Field
The invention relates to a generator rotor mounting structure of an aviation piston engine.
Background
The aviation piston engine is an important power type of an unmanned aerial vehicle system, and higher requirements are put on the weight and the light weight of the engine and all subsystems. The generator system is an accessory system that is an important component of an aviation piston engine and is typically directly connected or in the form of a belt connection to transmit power to drive the generation of electricity. The generator rotor that often directly links is connected with a middle transition structure with the screw in general, and the belt is connected just more loaded down with trivial details, and the accessory is many. This results in a heavy construction and a bulky aero-piston engine. Therefore, the ratio of the power to the weight of the engine is influenced, the performance of the engine is influenced, and the actual requirements of the aviation piston engine cannot be met. In view of the above, the present invention provides a generator rotor mounting structure for an aviation piston engine.
Disclosure of Invention
The invention aims to provide a generator rotor mounting structure of an aviation piston engine.
In order to achieve the above object, the present invention is achieved by: the utility model provides an aero-piston engine's generator rotor mounting structure, includes bent axle assembly, generator rotor assembly, generator connecting axle, screw, its characterized in that: the crankshaft assembly comprises a crankshaft, a screw 1 and a gasket, the generator connecting shaft is connected with the crankshaft through a conical surface and is clamped with the gasket through the screw 1, the generator rotor assembly comprises a generator rotor and a screw 2, the generator rotor is arranged on the inner side of the generator connecting shaft and is clamped through the screw 2, the propeller is arranged on the other side of the generator connecting shaft, the generator connecting shaft is provided with an inner hole, and the centering is realized through the inner hole and the propeller. Preferably, the crankshaft assembly consists of a crankshaft, a screw 1 and a gasket, wherein the screw 1 is screwed on the internal thread of the crankshaft.
Preferably, the crankshaft is provided with a conical surface which is matched with the conical surface of the generator connecting shaft.
Preferably, the generator connecting shaft is provided with two planes, and is connected with the propeller and the generator rotor.
Preferably, the generator connecting shaft is provided with an inner hole, and the generator connecting shaft and the propeller form a fit to realize centering.
Preferably, the generator connecting shaft is provided with a threaded hole, one side is used for clamping the generator rotor, and the other side is used for clamping the propeller.
Preferably, the generator connecting shaft is provided with an oil filling hole, so that the oil filling and the disassembly are convenient.
In addition, a generator rotor mounting structure of aviation piston engine, including the generator rotor mounting structure of above-mentioned aviation piston engine, its characterized in that: the method comprises the following steps of:
firstly, installing a generator rotor to a generator connecting shaft to tighten a screw 2;
and secondly, mounting a generator connecting shaft on a crankshaft, and clamping the screw 1 and the gasket.
And thirdly, installing the propeller on the generator connecting shaft.
Advantageous effects
The generator rotor mounting structure of the aviation piston engine has the following remarkable advantages:
The generator rotor is arranged at the front end of the generator connecting shaft, and the propeller is arranged at the rear end, so that the engine is compact in structure.
Hydraulic oil is injected into the oil injection hole of the generator connecting shaft, so that the generator connecting shaft can be effectively and quickly disassembled.
The generator connecting shaft is provided with one end with a conical surface and one end with an inner hole, the generator connecting shaft is connected with the crankshaft through the conical surface, and the generator connecting shaft is connected with the propeller through the inner hole, so that centering is effectively guaranteed.
Drawings
FIG. 1 is an assembly view of a generator rotor mounting structure;
FIG. 2 is a front view of a generator connection shaft;
FIG. 3 is a cross-sectional view A-A of the generator connection shaft.
In the figure:
1-crankshaft Assembly 11-crankshaft 12-screw 1
13-Gasket 2-generator rotor assembly 21-generator rotor
22-Screw 2 3-generator connecting shaft 4-propeller
31-Oil filling hole 32-threaded hole 33-mounting inner hole
34-Conical surface
Detailed Description
The invention is further described below with reference to the drawings and examples.
The basic idea of the invention is to combine a generator rotor mounting structure of an aviation piston engine, fully utilize the space structure and make the engine more compact.
Examples: a compact aircraft piston engine generator rotor mounting structure is provided as shown in fig. 1-3.
The utility model provides an aero-piston engine's generator rotor mounting structure, includes bent axle assembly 1, generator rotor assembly 2, generator connecting axle 3, screw 4, its characterized in that: the crankshaft assembly 1 comprises a crankshaft 11, a screw 1 and a gasket 13, the generator connecting shaft 3 is connected with the crankshaft through a conical surface 34 and is clamped with the gasket 13 through the screw 1, the generator rotor assembly 2 comprises a generator rotor 21 and a screw 2, the generator rotor 21 is arranged on the inner side of the generator connecting shaft 3 and is clamped through the screw 222, the propeller 4 is arranged on the other side of the generator connecting shaft 3, and the generator connecting shaft 3 is provided with an installation inner hole 33 and is centered with the propeller 4 through the installation inner hole 33.
In this example, the crankshaft assembly 1 is composed of a crankshaft 11, a screw 1, 12, and a gasket 13, wherein the screw 1 is screwed on the internal thread of the crankshaft 11.
In this example, the crankshaft 11 is provided with a conical surface 34, which cooperates with the conical surface 34 of the generator connection shaft 3.
In this example, the generator connection shaft 3 is provided with two planes, one for connection to the propeller 4 and one for connection to the generator rotor 21.
In this example, the generator connection shaft 3 is provided with a mounting bore 33 which cooperates with the propeller 4 to achieve centering.
In the present example, the generator connection shaft 3 is provided with a threaded bore 32, one side for clamping the generator rotor 21 and one side for clamping the propeller 4. In this example, the generator connecting shaft 3 is provided with an oil filling hole 31, so that the oil filling and dismounting are facilitated.
In addition, in this example, a generator rotor mounting structure of an aviation piston engine includes the generator rotor mounting structure of an aviation piston engine, and is characterized in that: the method comprises the following steps of:
Firstly, installing a generator rotor 21 on a generator connecting shaft 3 to screw a screw 2 22;
And secondly, mounting the generator connecting shaft 3 on the crankshaft 11, and clamping the screw 1 and the gasket 13.
And thirdly, mounting the propeller 4 on the generator connecting shaft 3.
Advantageous effects
The generator rotor mounting structure of the aviation piston engine has the following remarkable advantages:
The generator rotor 21 is mounted to the front end of the generator connection shaft 3, and the propeller 4 is mounted to the rear end, so that the engine is compact.
The hydraulic oil is injected through the oil injection hole 31 of the generator connecting shaft 3, so that the generator connecting shaft can be effectively and quickly disassembled.
The generator connecting shaft 3 is provided with one end with a conical surface 34, one end is provided with an installation inner hole 33, the generator connecting shaft is connected with the crankshaft 11 through the conical surface 34, and the generator connecting shaft is connected with the propeller 4 through the installation inner hole 33, so that centering is effectively ensured.
Claims (6)
1. The utility model provides an aero-piston engine's generator rotor mounting structure, includes bent axle assembly (1), generator rotor assembly (2), generator connecting axle (3), screw (4), its characterized in that: the utility model provides a crank assembly (1) includes bent axle (11), screw 1 (12), gasket (13), generator connecting axle (3) link to each other with the bent axle through conical surface (34), press from both sides tightly with gasket (13) through screw 1 (12), generator rotor assembly (2) include generator rotor (21) and screw 2 (22), generator rotor (21) are installed in the inboard of generator connecting axle (3), press from both sides tightly through screw 2 (22), screw (4) are installed at the opposite side of generator connecting axle (3), generator connecting axle (3) set up installation hole (33), realize centering with screw (4) through installation hole (33).
2. The structure for mounting a generator rotor of an aero-piston engine according to claim 1, wherein: the crankshaft assembly (1) consists of a crankshaft (11), a screw 1 (12) and a gasket (13), wherein the screw 1 (12) is screwed on an internal thread of the crankshaft (11).
3. The structure for mounting a generator rotor of an aero-piston engine according to claim 1, wherein: the generator connecting shaft (3) is provided with two planes, and is connected with the propeller (4) and the generator rotor (21).
4. The structure for mounting a generator rotor of an aero-piston engine according to claim 1, wherein: the generator connecting shaft (3) is provided with an installation inner hole (33) which is matched with the propeller (4) to realize centering.
5. The structure for mounting a generator rotor of an aero-piston engine according to claim 1, wherein: the generator connecting shaft (3) is provided with a threaded hole (32), one side is used for clamping the generator rotor (21), and the other side is used for clamping the propeller (4).
6. The structure for mounting a generator rotor of an aero-piston engine according to claim 1, wherein: the generator connecting shaft (3) is provided with an oil filling hole (31) which is convenient to fill oil and disassemble.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322823557.2U CN220955819U (en) | 2023-10-20 | 2023-10-20 | Generator rotor mounting structure of aviation piston engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322823557.2U CN220955819U (en) | 2023-10-20 | 2023-10-20 | Generator rotor mounting structure of aviation piston engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220955819U true CN220955819U (en) | 2024-05-14 |
Family
ID=90977216
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322823557.2U Active CN220955819U (en) | 2023-10-20 | 2023-10-20 | Generator rotor mounting structure of aviation piston engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220955819U (en) |
-
2023
- 2023-10-20 CN CN202322823557.2U patent/CN220955819U/en active Active
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| GR01 | Patent grant |