Aero light multi-mode hybrid parallel shaft structure transmission

Abstract

A lightweight multi-condition hybrid parallel shaft transmission for aviation belongs to the technical field of lightweight multi-mode hybrid parallel shaft transmissions for aviation. Its features include an output shaft and an input shaft. The output shaft side surface is fitted with an integrated propeller, oil seal, C2 clutch, and driven gear from left to right. A controller is connected to the center of the right end of the output shaft. A C1 clutch is connected to the left end of the input shaft. An engine is fixedly connected to the center of the right end of the input shaft. A motor shaft is connected to the left end of the C1 clutch. The motor shaft is fitted with a motor, drive motor, resolver, drive gear, and oil pump gear from right to left. Several bearings are inserted into the side surfaces of the output shaft, input shaft, and motor shaft, facilitating disassembly, assembly, maintenance, and repair, reducing the cost per use throughout the product's lifespan, further increasing product redundancy, and reducing the failure rate.

Description

Technical Field

[0001] This invention belongs to the technical field of lightweight multi-mode hybrid parallel shaft devices for aviation, specifically relating to a lightweight multi-condition hybrid parallel shaft structure transmission for aviation. Background Technology

[0002] Currently, low-altitude passenger transmissions have limited operating conditions, poor adaptability, and their safety performance needs further verification. Technological iteration and product launch are accelerating, but verification is insufficient, and design accumulation is lacking. The current shell is heavy and does not meet lightweight design requirements. The overall structure generally uses a three-axis structure, which is bulky, has low space utilization, and does not meet the principle of economy. Summary of the Invention

[0003] The purpose of this invention is:

[0004] 1. Thirteen different working conditions correspond to thirteen different modes, and the working conditions and corresponding modes have a positive correlation.

[0005] 2. Eliminate the separate motor shaft and integrate the motor into the input shaft to reduce the overall size and weight;

[0006] 3. The use of the relatively mature magnesium alloy AZ91D achieves a 1 / 3 reduction in shell weight;

[0007] 4. The parallel axis is perpendicular to the ground and symmetrical from left to right, consistent with the overall structure of the machine. At the same time, the ground clearance can be further adjusted through a set of gear parameters without the need for additional height, enabling take-off and landing functions in more scenarios.

[0008] 5. The brick structure design integrates the oil pump valve body and controller in the empty area, conforming to the slimmer structure of the model and making it more conducive to overall installation.

[0009] 6. No planetary gear set is required; a single set of gears provides safer and more reliable meshing.

[0010] 7. All bearings are sealed bearings with internal grease to prevent insufficient lubrication due to low air temperature and flight tilt.

[0011] 8. Simultaneously, the motor employs high-pressure cooling, which improves the heat exchange rate and thus increases motor efficiency. The technical solution is as follows:

[0012] A lightweight, multi-condition hybrid parallel-shaft transmission for aviation is characterized by comprising an output shaft 1 and an input shaft 11. From left to right, an integrated propeller 2, an oil seal 3, a C2 clutch 5, and a driven gear 8 are installed on the side surface of the output shaft 1. A controller 9 is connected to the center of the right end of the output shaft 1. A C1 clutch 12 is connected to the left end of the input shaft 11. An engine 10 is fixedly connected to the center of the right end of the input shaft 11. A motor shaft 19 is connected to the left end of the C1 clutch 12. From right to left, a motor, a drive motor 13, a resolver 15, a drive gear 16, and an oil pump gear 17 are installed on the motor shaft 19. Several bearings 4 are installed on the side surfaces of the output shaft 1, input shaft 11, and motor shaft 19. A sensing gear 6 is installed on the outer side of the C2 clutch 5. The motor and drive motor 13 are symmetrically connected to the side surfaces of the brake band 7 and the motor 13. The connector 14 is connected to the controller 6 by a high-voltage line. The motor and drive motor 13 are integrated with the resolver 15. The left end of the motor shaft 19 is inserted into the oil pump 18. The oil pump 18 and the motor shaft 19 are connected to each other by the oil pump gear 17. The oil pump 18 is provided with an oil pump valve body. The oil pump 18 is connected to the C2 clutch 5 and the C1 clutch 12 by a lubrication oil circuit and a drive oil circuit. A branch is provided on the side of the lubrication oil circuit between the oil pump 18 and the C2 clutch 5. The other end of the branch is connected to the oil seal 3. An oil pan for the operation of the oil pump valve body is provided below the motor shaft 19. The bearing 4 is a sealed bearing and is lubricated by grease.

[0013] The beneficial effects of this invention are as follows: through a series of integrated, simplified, and lightweight design innovations, using mature lightweight materials on the market, it is calibrated to match different modes and working conditions, has a simple structure, is easy to disassemble, install, maintain, and repair, reduces the cost of a single use during the product's life cycle, further increases product redundancy, and reduces the failure rate. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0015] Figure 2 This is a schematic diagram of the implementation process of the present invention;

[0016] Figure 3 This is a schematic diagram comparing two-axis and three-axis structures;

[0017] In the diagram: Output shaft 1, output shaft integrated propeller, oil seal 3, bearing 4, C2 clutch 5, induction gear 6, brake band 7, driven gear 8, controller 9, engine 10, input shaft 11, C1 clutch 12, motor, drive motor 13, connector 14, resolver 15, drive gear 16, oil pump gear 17, oil pump 18, motor shaft 19. Detailed Implementation

[0018] Reference Figures 1-3 The aforementioned lightweight multi-condition hybrid parallel-shaft transmission for aviation is characterized by comprising an output shaft 1 and an input shaft 11. The output shaft 1 has an integrated propeller 2, an oil seal 3, a C2 clutch 5, and a driven gear 8 inserted from left to right on its side surface. A controller 9 is connected to the center of the right end of the output shaft 1. A C1 clutch 12 is connected to the left end of the input shaft 11. An engine 10 is fixedly connected to the center of the right end of the input shaft 11. A motor shaft 19 is connected to the left end of the C1 clutch 12. The motor shaft 19 has a motor, a drive motor 13, a resolver 15, a drive gear 16, and an oil pump gear 17 inserted from right to left on its side surface. Several bearings 4 are inserted on the side surfaces of the output shaft 1, input shaft 11, and motor shaft 19. A sensing gear is inserted on the outer side of the C2 clutch 5. 6 and brake band 7, the motor and drive motor 13 are symmetrically connected to the side surface of the connector 14, the connector 14 is connected to the controller 6 by a high voltage line, the motor and drive motor 13 are integrated with the resolver 15, the left end of the motor shaft 19 is inserted into the oil pump 18, the oil pump 18 and the motor shaft 19 are connected to each other by the oil pump gear 17, the oil pump 18 is provided with an oil pump valve body inside, the oil pump 18 is connected to the C2 clutch 5 and the C1 clutch 12 by a lubrication oil circuit and a drive oil circuit, the lubrication oil circuit between the oil pump 18 and the C2 clutch 5 is provided with a branch on the side, the other end of the branch is connected to the oil seal 3, the motor shaft 19 is provided with an oil pan for the operation of the oil pump valve body, the bearing 4 is a sealed bearing, and is lubricated by grease.

[0019] Describe the logic of different working modes:

[0020] 1) When clutch 12 is closed in the drive oil circuit through oil pump 18 under the condition of executing all working conditions corresponding mode, clutch 12 is closed.

[0021] 2) When C2 clutch 5 is closed under the following eight conditions through the oil pump 18 in the driving oil circuit: engine direct drive mode and parallel direct drive mode corresponding to the positive transition of level flight; parallel direct drive mode corresponding to the climb condition; parallel direct drive mode and engine direct drive mode corresponding to the acceleration condition of level flight; engine direct drive mode corresponding to the cruise (long-distance flight) condition; drive + generator mode corresponding to the deceleration condition; and drive + generator mode corresponding to the glide condition, the output shaft integrated propeller 2 is driven. In the other modes, C2 clutch 5 is disengaged, and the output shaft integrated propeller 2 is not driven.

[0022] 3) In all the series-generated motors and drive motors 13 mentioned above, the motors through the controller 9 and the high-voltage line to the connector 14 all execute the power generation logic, and the drive motors all execute the drive lift propeller logic. In the hovering condition, the brake band 7 is operated through the oil pump 18.

[0023] 4) In all the above direct drive modes of the engine, clutch 12 of C1 is closed, clutch 5 of C2 is closed, the output shaft integrates propeller 2 for drive, the motor and drive motor 13 do not execute drive logic, and execute non-generator logic.

[0024] 5) In all the parallel direct drive modes mentioned above, clutch 12 of C1 is closed, clutch 5 of C2 is closed, the output shaft integrates propeller 2 for drive, and the motor and drive motor 13 execute drive logic and power generation logic.

[0025] 6) In all the above drive + power generation modes, clutch 12 of C1 is closed, clutch 5 of C2 is closed, propeller 2 is driven by the output shaft, and the motor and drive motor 13 do not execute drive logic, but execute power generation logic.

[0026] 7) The oil seal 3 ensures lubrication by connecting the oil seal oil circuit branch on the output shaft integrated propeller 14. The oil seal oil circuit branch is connected to the lubrication oil circuit of clutch 5 C2 and has the same pressure balance as the inner cavity.

[0027] 8) Bearing 4 is a sealed bearing, lubricated by grease, to prevent the loss of lubricating oil due to the angle of flight.

[0028] 9) The lubrication circuit of clutch 12 C1 uses oil pump 18 to input oil from the oil sump to shaft 11 to lubricate clutch 12 during all operating conditions.

[0029] 10) The oil pump 18 is driven by the oil pump gear 17. The oil pump gear 17 is directly driven by the engine 10 when the C1 clutch 12 is closed. That is, the closure of the C1 clutch 12 is a necessary condition for the operation of the whole vehicle.

[0030] 11) The driving gear 16 and the driven gear 8 are constantly meshed to transmit the torque of the input shaft 11 to the output shaft integrated propeller 2.

[0031] 12) The C2 clutch 5 integrates an integrated sensing tooth 6 for measuring the output speed.

[0032] 13) The resolver 15 is integrated on the right side of the motor shaft 19, reducing the axial arrangement space on the left side of the motor and drive motor 13.

[0033] 14) The oil pan is located at the bottom to collect oil for the operation of oil pump 18.

[0034] like Figure 2As shown, there are a total of 13 operating conditions. Vertical takeoff, hovering, level flight reverse transition, landing point adjustment, and vertical takeoff and landing correspond to series power generation modes. Among them, the hovering condition, which corresponds to the series power generation mode, requires the participation of brake band 6. The level flight positive transition condition corresponds to two modes: engine direct drive and parallel direct drive. The climb condition corresponds to the parallel direct drive mode. The level flight acceleration condition corresponds to two modes: parallel direct drive and engine direct drive. The endurance (long-range) condition corresponds to the engine direct drive mode. The deceleration and descent conditions correspond to the drive + power generation mode.

[0035] like Figure 3 As shown, the left side represents the three-axis layout space, and the right side represents the two-axis layout space. This invention upgrades the existing AHT22 architecture (left view) to the right view, saving space and weight, improving integration, simplifying the structure, and achieving lightweight design innovation. This is achieved through adjustments... Figure 2 The center distance can be changed by adjusting the parameters of the driving tooth 16 and the driven tooth 8.

[0036] Of course, the above description is not intended to limit the present invention, and the present invention is not limited to the examples given above. Any changes, modifications, additions or substitutions made by those skilled in the art within the scope of the present invention should also fall within the protection scope of the present invention.

Claims

1. A lightweight, multi-condition hybrid parallel-shaft transmission for aviation, characterized in that: It includes an output shaft (1) and an input shaft (11). The output shaft (1) is fitted with an integrated propeller (2), an oil seal (3), a C2 clutch (5) and a driven gear (8) from left to right on its side surface. A controller (9) is connected to the center of the right end of the output shaft (1). A C1 clutch (12) is connected to the left end of the input shaft (11). An engine (10) is fixedly connected to the center of the right end of the input shaft (11). A motor shaft (19) is connected to the left end of the C1 clutch (12). A motor, a drive motor (13), a resolver (15), a drive gear (16) and an oil pump gear (17) are fitted from right to left on the motor shaft (19). Several bearings (4) are fitted to the side surfaces of the output shaft (1), the input shaft (11) and the motor shaft (19).

2. The lightweight multi-condition hybrid parallel shaft transmission for aviation as described in claim 1, characterized in that: The C2 clutch (5) is fitted with an induction gear (6) and a brake band (7) on its outer side.

3. The lightweight multi-condition hybrid parallel shaft transmission for aviation as described in claim 1, characterized in that: The motor and drive motor (13) are symmetrically connected to connectors (14) on their side surfaces, and the connectors (14) are connected to the controller (6) by high-voltage lines.

4. The lightweight multi-condition hybrid parallel shaft transmission for aviation as described in claim 1, characterized in that: The motor, drive motor (13) and resolver (15) are integrated and connected.

5. The lightweight multi-condition hybrid parallel shaft transmission for aviation as described in claim 1, characterized in that: The left end of the motor shaft (19) is inserted into the oil pump (18), and the oil pump (18) and the motor shaft (19) are connected to each other by the oil pump gear (17).

6. The lightweight multi-condition hybrid parallel shaft transmission for aviation as described in claim 5, characterized in that: The oil pump (18) is equipped with an oil pump valve body. The oil pump (18) is connected to the C2 clutch (5) and the C1 clutch (12) by a lubricating oil circuit and a driving oil circuit. A branch is provided on the side of the lubricating oil circuit between the oil pump (18) and the C2 clutch (5). The other end of the branch is connected to the oil seal (3).

7. The lightweight multi-condition hybrid parallel shaft transmission for aviation as described in claim 6, characterized in that: An oil pan for the operation of the oil pump valve body is provided below the motor shaft (19).

8. The lightweight multi-condition hybrid parallel shaft transmission for aviation as described in claim 1, characterized in that: (4) Sealed bearing, lubricated by grease.

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