Aviation heavy oil engine
By changing the output direction of the aviation heavy oil engine to be parallel to the piston running axis and optimizing the structure with self-sealing bearings, the problem of the engine being unable to be installed in the loitering munition was solved, and the effective loading of the engine in the narrow munition body and the compact structure were achieved.
Patent Information
- Application Number
- CN202423148731.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-20
- Publication Date
- 2025-11-28
- Estimated Expiration
- 2034-12-20
AI Technical Summary
The output shaft of an existing heavy oil aviation engine is at a 90° angle to the piston axis, making it impossible to fit into the narrow body of a loitering munition.
The output direction of the single-cylinder piston engine was changed to be parallel to the piston running axis. Self-sealing deep groove ball bearings and self-sealing deep groove ball bearings were used. The machining accuracy of the crankcase bearing housing was optimized, and a compact generator rotor structure was designed.
It enables the effective mounting of aviation heavy oil engines on narrow loitering munitions, improving the engine's structural compactness and coaxial accuracy.
Smart Images
Figure CN223608642U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to an aviation heavy oil engine. BACKGROUND
[0002] The cruise missile is a new concept of ammunition, which is a flight device with a long and narrow cylindrical shell. It can perform multiple tasks by "cruising" and "waiting" above the target. The preferred power unit of the cruise missile is a piston engine, which has longer endurance than electric motors and lower oil consumption and longer endurance than turbojet engines. However, the aviation heavy oil engine has a fatal flaw that the output shaft is at a 90° angle with the piston running axis. It cannot be installed in the body of the cruise missile.
[0003] In view of the above problems, the present application provides an aviation heavy oil engine, which changes the output direction of the single-cylinder piston engine from the conventional 90° output to the direction parallel to the piston running axis, which is beneficial to the loading of the engine into the long and narrow cruise missile. SUMMARY
[0004] The present application aims to provide an aviation heavy oil engine.
[0005] In order to achieve the above-mentioned purpose, the present application is implemented as follows: an aviation heavy oil engine, comprising an oil supply system, a cylinder head, a piston connecting rod system, a cylinder system, a crankshaft system, and a generator system, characterized in that: the oil supply system is located on the side of the cylinder head away from the generator system; the cylinder system comprises a cylinder block and a crankcase, the piston of the piston connecting rod system slides in the cylinder block, and the axis of the generator system is parallel to the sliding direction of the piston in the piston connecting rod system; the crankshaft system comprises an eccentric shaft deep groove ball bearing 1, a deep groove ball bearing 2 crankshaft assembly, an input spur gear, an intermediate shaft assembly, and an output shaft assembly.
[0006] Preferably, the eccentric shaft is located on the opposite side of the input spur gear, and the eccentric shaft is used to drive an auxiliary air pump not shown.
[0007] Preferably, the deep groove ball bearing 1 and the deep groove ball bearing 2 are self-sealing bearings, and the outer diameters are equal, which is beneficial to the one-cut machining of the crankcase bearing seat and ensures the coaxial accuracy.
[0008] Preferably, the intermediate shaft assembly comprises an intermediate shaft shaft body, a needle thrust bearing 1 intermediate shaft spur gear, a bevel gear, and a needle thrust bearing 2, wherein the input spur gear and the intermediate shaft spur gear are straight and helical gears.
[0009] Preferably, the output shaft assembly comprises a needle bearing 1, a needle thrust bearing 3, an output shaft body, and a deep groove ball bearing 3, wherein the deep groove ball bearing 3 is a self-sealing bearing.
[0010] Preferably, a needle bearing 2 is arranged between the intermediate shaft body and the bevel gear.
[0011] Advantages:
[0012] The generator rotor mounting structure of the aviation heavy oil engine has the following advantages:
[0013] 1. The eccentric shaft is located on the opposite side of the input spur gear, and the eccentric shaft is used to drive the auxiliary air pump not shown, so that the engine structure is compact.
[0014] 2. The deep groove ball bearing 1 and the deep groove ball bearing 2 are self-sealing bearings, and the outer diameters are equal, which is beneficial to the one-time machining of the crankcase bearing seat and ensures the coaxial accuracy.
[0015] 3. The aviation heavy oil engine changes the output direction of the single-cylinder piston engine from the conventional 90° output to the direction parallel to the piston operation axis, which is beneficial to the loading of the engine on the long and narrow cruise missile. BRIEF DESCRIPTION OF DRAWINGS
[0016] Fig. 1 It is an assembly drawing of the aviation heavy oil engine;
[0017] Fig. 2 It is an assembly drawing of the crankshaft system;
[0018] Fig. 3 It is an assembly drawing of the intermediate shaft assembly and the output shaft assembly.
[0019] In the drawings:
[0020] 1 - oil supply system 2 - cylinder head 3 - piston connecting rod system
[0021] 4 - cylinder body system 5 - crankshaft system 6 - generator system
[0022] 51 - eccentric shaft 52 - deep groove ball bearing 1 53 - crankshaft assembly
[0023] 54 - deep groove ball bearing 2 55 - input spur gear 56 - intermediate shaft assembly
[0024] 57 - output shaft assembly 561 - intermediate shaft body 562 - needle thrust bearing 1
[0025] 563 - intermediate shaft spur gear 564 - bevel gear 565 - needle thrust bearing 2
[0026] 566 - flat key 567 - needle bearing 2 571 - needle bearing 1
[0027] 572 - needle thrust bearing 3 573 - output shaft body 574 - deep groove ball bearing 3 DETAILED DESCRIPTION
[0028] The application will be further described below in connection with the accompanying drawings and examples.
[0029] The basic idea of the application is to combine an aviation heavy oil engine, the aviation heavy oil engine of the application, the output direction of the single-cylinder piston engine is changed from the conventional 90° output to the direction parallel to the piston operation axis, which is beneficial to the engine loading on the narrow and long cruise missile.
[0030] Embodiment: as shown in the figure provides an aviation heavy oil engine. Figs. 1-3
[0031] Among them, an aviation heavy oil engine, including oil supply system 1, cylinder head 2, piston connecting rod system 3, cylinder system 4, crankshaft system 5, generator system 6, characterized by: the oil supply system 1 is located on the side of the cylinder head 2 away from the generator system 6; the cylinder system 4 contains cylinder block and crankcase, the piston of the piston connecting rod system 3 slides in the cylinder block, and the axis of the generator system 6 is parallel to the sliding direction of the piston in the piston connecting rod system 3; the crankshaft system 5 contains eccentric shaft 51 deep groove ball bearing 152, deep groove ball bearing 254 crankshaft assembly 53, input spur gear 55, intermediate shaft assembly 56, output shaft assembly 57.
[0032] In this example, the aviation heavy oil engine, characterized by: the eccentric shaft 51 is located on the opposite side of the input spur gear, and the eccentric shaft 51 is used to drive the auxiliary air pump (not shown).
[0033] In this example, the aviation heavy oil engine, characterized by: deep groove ball bearing 152 deep groove ball bearing 254 is a self-sealing bearing, and the outer diameter is equal, which is beneficial to the crankcase bearing seat to be machined into a shape, ensuring the coaxial accuracy.
[0034] In this example, the aviation heavy oil engine, characterized by: the intermediate shaft assembly 56 contains intermediate shaft shaft body 561, needle thrust bearing 1562 intermediate shaft spur gear 563, bevel gear 564 and needle thrust bearing 2565, wherein the input spur gear 55 and the intermediate shaft spur gear 563 are straight and helical gears.
[0035] In this example, the aviation heavy oil engine, characterized by: the output shaft assembly 57 contains needle bearing 571, needle thrust bearing 3572, output shaft body 573, deep groove ball bearing 3574, wherein the deep groove ball bearing 3574 is a self-sealing bearing.
[0036] In this example, the aviation heavy oil engine, characterized by: the inner ring of the intermediate shaft spur gear 563 is interfered on the outer ring of the bevel gear 564 and transmits torque through two flat keys 566.
[0037] In the present instance, the aviation heavy oil engine is characterized in that a needle bearing 2 is arranged between the intermediate shaft body and the bevel gear.
[0038] Beneficial effects:
[0039] The generator rotor mounting structure of the aviation heavy oil engine has the following remarkable advantages:
[0040] 1. The eccentric shaft is located at the opposite side of the input spur gear, and is used for driving an auxiliary air pump (not shown), so that the engine structure is compact.
[0041] 2. The deep groove ball bearing 1 and the deep groove ball bearing 2 are self-sealing bearings, and the outer diameters are equal, so that the crankcase bearing seat is machined into a shape, and the coaxial precision is ensured.
[0042] 3. The aviation heavy oil engine changes the output direction of the single-cylinder piston engine from the conventional 90° output to the direction parallel to the piston operation axis, which is beneficial to loading the engine on a narrow and long cruise missile.
Claims
1. An aviation heavy oil engine, comprising a fuel supply system (1), a cylinder head (2), a piston connecting rod system (3), a cylinder block system (4), a crankshaft system (5), and a generator system (6), characterized in that: The oil supply system (1) is located on the side of the cylinder head (2) away from the generator system (6); the cylinder block system (4) includes a cylinder block and a crankcase, the piston of the piston connecting rod system (3) slides in the cylinder block, and the axial direction of the generator system (6) is parallel to the sliding direction of the piston in the piston connecting rod system (3); the crankshaft system (5) includes an eccentric shaft (51), a deep groove ball bearing 1 (52), a deep groove ball bearing 2 (54), a crankshaft assembly (53), an input spur gear (55), an intermediate shaft assembly (56), and an output shaft assembly (57).
2. The aviation heavy oil engine according to claim 1, characterized in that: The eccentric shaft (51) is located on the opposite side of the input spur gear and is used to drive the auxiliary air pump.
3. The aviation heavy oil engine according to claim 1, characterized in that: Deep groove ball bearing 1 (52) and deep groove ball bearing 2 (54) are self-sealing bearings with equal outer diameters, which is beneficial for the crankcase bearing housing to be machined in one piece and ensures coaxial accuracy.
4. The aviation heavy oil engine according to claim 1, characterized in that: The intermediate shaft assembly (56) includes an intermediate shaft body (561), a needle roller thrust bearing 1 (562), an intermediate shaft spur gear (563), a bevel gear (564), and a needle roller thrust bearing 2 (565), wherein the input spur gear (55) and the intermediate shaft spur gear (563) are spur helical gears.
5. The aviation heavy oil engine according to claim 1, characterized in that: The output shaft assembly (57) includes a needle roller bearing 1 (571), a needle roller thrust bearing 3 (572), an output shaft body (573), and a deep groove ball bearing 3 (574), wherein the deep groove ball bearing 3 (574) is a self-sealing bearing.
6. The aviation heavy oil engine according to claim 4, characterized in that: A needle roller bearing 2 (567) is provided between the intermediate shaft body (561) and the bevel gear (564).