Single-shot co-axial shaft four-rotor tilt unmanned aerial vehicle transmission system and rotorcraft

Abstract

The present application relates to a kind of single shot co-transmission shaft four-rotor tilt unmanned aerial vehicle transmission system and rotorcraft, include one engine output, connect to intermediate reduction unit, through two groups of coaxial horizontal transmission shaft connection left and right four reduction reversing units, four reduction reversing units are finally connected four rotors respectively;The transmission system adopts one engine output, through intermediate reduction unit and two groups of coaxial horizontal transmission shaft power transmission to left and right symmetrical four reduction reversing units, finally power is transmitted to rotor, realizes single power input, four direction power output;The configuration design of this single shot co-transmission shaft left and right four-rotor tilt unmanned aerial vehicle, so that four rotors mutually offset the influence of torque, and co-transmission shaft design is conducive to reducing the size of helicopter and miniaturization design, solve the current dual-rotor tilt unmanned aerial vehicle transmission system fuselage structure size larger and transmission system weight heavier and cause the problem of poor machine maneuverability.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology and relates to a transmission system for a single-engine, common-shaft quadrotor tilt-rotor unmanned aerial vehicle and a rotary-wing aircraft. Background Technology

[0002] In the aerospace field, conventional helicopters can hover and perform vertical takeoff and landing (VTOL), offering simple and flexible operation, but their flight speed is relatively slow. In contrast, fixed-wing aircraft are fast and have long range, but are limited by the choice of takeoff and landing sites and lack in safety and flexibility. Tiltrotor aircraft cleverly combine the advantages of both types, achieving both VTOL and high-speed flight, while also possessing low fuel consumption and long range. The tiltrotor aircraft of this invention employs a quadcopter structure. During VTOL, after reaching a certain altitude and speed, the rotors can smoothly turn to a horizontal position using ball screws, switching to fixed-wing mode propulsion. This design allows the power mechanism to be shared between helicopter and fixed-wing modes, effectively reducing weight and air resistance during flight, thereby greatly improving the aircraft's flight time and energy efficiency.

[0003] Given the stringent structural weight requirements of UAV transmission systems, most current domestic and international designs utilize single-engine, dual-rotor tiltrotor aircraft, which negatively impacts the overall power system efficiency. Therefore, it is necessary to propose a novel single-engine, common-shaft, quadrotor tiltrotor UAV transmission system to address the problems inherent in existing designs. Summary of the Invention

[0004] In view of this, in order to solve the problem of poor overall maneuverability caused by the large fuselage size and heavy weight of the current dual-rotor tilt-rotor UAV transmission system, the present invention provides a lightweight, compact, and highly efficient single-engine common-drive shaft quadrotor tilt-rotor UAV transmission system and rotorcraft.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A transmission system for a single-engine, common-drive shaft quadrotor tilt-rotor unmanned aerial vehicle includes an engine output unit, an intermediate reduction unit connected to the engine output unit, a drive shaft unit, and four reduction and reversing units symmetrically distributed on the left and right sides of the intermediate reduction unit.

[0007] The intermediate reduction unit includes a first-stage bevel gear shaft 1, a second-stage bevel gear shaft 8 that is driven on the first-stage bevel gear shaft 1, a third-stage bevel gear shaft 15 that is driven on both sides of the second-stage bevel gear shaft 8, and a first intermediate reduction unit output shaft 24 and a second intermediate reduction unit output shaft 36 that are driven on the third-stage bevel gear shaft 15 respectively.

[0008] The drive shaft unit includes a long drive shaft 38 located on both sides of the output shaft 36 of the second intermediate reduction unit and connected to it in a drive transmission, and a coupling for connecting the output shaft 36 of the second intermediate reduction unit and the long drive shaft 38.

[0009] Four deceleration and reversing units are symmetrically distributed on both sides of the middle deceleration unit, including the right outer deceleration and reversing unit, the right inner deceleration and reversing unit, the left outer deceleration and reversing unit with the same structure as the right outer deceleration and reversing unit, and the left inner deceleration and reversing unit with the same structure as the right inner deceleration and reversing unit.

[0010] Both the left outer deceleration and reversing unit and the right outer deceleration and reversing unit include an outer deceleration and reversing unit input shaft 46 that is driven and connected to the long drive shaft 38, and an outer rotor shaft 40 that is driven and connected to the outer deceleration and reversing unit input shaft 46; both the left inner deceleration and reversing unit and the right inner deceleration and reversing unit include an inner deceleration and reversing unit input shaft that is driven and connected to the first intermediate deceleration unit output shaft 24, an inner rotor shaft 29 that is driven and connected to the inner deceleration and reversing unit input shaft, and an inner planetary gear carrier 32.

[0011] Furthermore, the engine output unit includes an engine output shaft and an overrunning clutch. The engine output shaft is connected to the first-stage bevel gear shaft 1 of the intermediate reduction unit via the overrunning clutch, which enables the engine to engage and disengage.

[0012] Furthermore, a first-stage input bevel gear 4 is installed at one end of the first-stage bevel gear shaft 1 near the second-stage bevel gear shaft 8. A first-stage output bevel gear 5, meshing with the first-stage input bevel gear 4, is installed in the middle of the second-stage bevel gear shaft 8. Second-stage input bevel gears 11 are installed at both ends of the second-stage bevel gear shaft 8. Second-stage output bevel gears 13 are installed at the ends of the third-stage bevel gear shaft 15 near the second-stage input bevel gears 11. The second-stage input bevel gears 11 and 13 mesh. Third-stage input bevel gears 18 are installed at the ends of the third-stage bevel gear shaft 15 near the first intermediate reduction unit output shaft 24. Third-stage output bevel gears 22 are installed at the ends of the first intermediate reduction unit output shaft 24 near the third-stage input bevel gears 18. The third-stage input bevel gears 18 and 22 mesh. Intermediate planetary gear carriers 20 are installed at the ends of the first intermediate reduction unit output shafts 24 that are close to each other. The opposite ends of the intermediate planetary gear carriers 20 are connected to the corresponding second intermediate reduction unit output shafts 36.

[0013] Furthermore, a first-stage input bevel gear 4 is integrally formed and connected to one end of the first-stage bevel gear shaft 1 near the second-stage bevel gear shaft 8. A first-stage output bevel gear 5, meshing with the first-stage input bevel gear 4, is integrally formed and connected to the middle of the second-stage bevel gear shaft 8. Second-stage input bevel gears 11 are splined to both ends of the second-stage bevel gear shaft 8. Second-stage output bevel gears 13 are splined to one end of the third-stage bevel gear shaft 15 near the second-stage input bevel gears 11. The second-stage input bevel gears 11 and second-stage output bevel gears 13 mesh. The third-stage bevel gear shaft 15 is located near... One end of the first intermediate reduction unit output shaft 24 is integrally connected to a third-stage input bevel gear 18. The end of the first intermediate reduction unit output shaft 24 near the third-stage input bevel gear 18 is splined connected to a third-stage output bevel gear 22. The third-stage input bevel gear 18 and the third-stage output bevel gear 22 mesh. The ends of the first intermediate reduction unit output shaft 24 that are close to each other are splined connected to the intermediate planetary gear train planet carrier 20. The ends of the intermediate planetary gear train planet carrier 20 that are opposite to each other are splined connected to the corresponding second intermediate reduction unit output shaft 36.

[0014] Furthermore, an outer deceleration and reversing unit input bevel gear 44 and an outer ball screw are installed at the end of the outer deceleration and reversing unit input shaft 46, and an outer deceleration and reversing unit output bevel gear 42 that meshes with the outer deceleration and reversing unit input bevel gear 44 is installed at the end of the outer rotor shaft 40; an inner deceleration and reversing unit input bevel gear 26 and an inner ball screw are installed at the end of the first intermediate deceleration unit output shaft 24 away from the third stage input bevel gear 18, and an inner deceleration and reversing unit output bevel gear 28 that meshes with the inner deceleration and reversing unit input bevel gear 26 is installed at the end of the inner deceleration and reversing unit input shaft.

[0015] Furthermore, the outer deceleration and reversing unit input shaft 46 is integrally connected to the outer deceleration and reversing unit input bevel gear 44 and the outer ball screw at the end, and the outer rotor shaft 40 is integrally connected to the outer deceleration and reversing unit output bevel gear 42 that meshes with the outer deceleration and reversing unit input bevel gear 44 at the end; the first intermediate deceleration unit output shaft 24, away from the third stage input bevel gear 18, is integrally connected to the inner deceleration and reversing unit input bevel gear 26 and the inner ball screw at the end, and the inner deceleration and reversing unit input shaft is integrally connected to the inner deceleration and reversing unit output bevel gear 28 that meshes with the inner deceleration and reversing unit input bevel gear 26 at the end, and the inner deceleration and reversing unit input shaft and the inner rotor shaft 29 are connected by a coupling.

[0016] Furthermore, the first-stage bevel gear shaft 1, the second-stage bevel gear shaft 8, the third-stage bevel gear shaft 15, the first intermediate reduction unit output shaft 24, the second intermediate reduction unit output shaft 36, the outer reduction and reversing unit input shaft 46, the outer rotor shaft 40, and the inner reduction and reversing unit input shaft are equipped with back-to-back tapered roller bearings for support, and the inner rotor shaft 29 is equipped with cylindrical roller bearings and four-point contact ball bearings for support.

[0017] Furthermore, in the intermediate reduction unit, the output shaft 24 of the first intermediate reduction unit is splinedly connected to the planet carrier 20 of the intermediate planetary gear system, and the output shaft 36 of the second intermediate reduction unit is splinedly connected to the long transmission shaft 38; in the outer reduction and reversing unit, the input shaft 46 of the outer reduction and reversing unit is splinedly connected to the long transmission shaft 38; in the inner reduction and reversing unit, the planet carrier 32 of the inner planetary gear system is splinedly connected to the inner rotor shaft 29.

[0018] Furthermore, the output shaft 24 of the first intermediate deceleration unit and the output shaft 36 of the second intermediate deceleration unit adopt a coaxial design.

[0019] Furthermore, a deep groove ball bearing is installed on the long drive shaft 38 in the drive shaft unit to provide support.

[0020] A rotary-wing aircraft includes a fuselage and the aforementioned single-engine common-drive shaft quadrotor tilt-rotor unmanned aerial vehicle (UAV) transmission system, with the aforementioned single-engine common-drive shaft quadrotor tilt-rotor UAV transmission system housed within the fuselage.

[0021] The beneficial effects of this invention are as follows:

[0022] 1. The single-engine, common-drive shaft quadrotor tilt-rotor UAV transmission system disclosed in this invention employs a central engine output, which, through a central reduction unit and two sets of coaxial horizontal drive shafts, reduces and redirects power to four symmetrically positioned reduction and reversing units, ultimately transmitting power to the rotors. This achieves single power input and four-directional power output. Compared to traditional dual-rotor tilt-rotor aircraft transmission systems, this structure is more compact, has higher power utilization efficiency, and can significantly reduce system weight and structural size. This single-engine, common-drive shaft quadrotor tilt-rotor UAV configuration design allows the four rotors to cancel each other out torque effects, and the common-drive shaft design is beneficial for reducing the helicopter's size and miniaturizing the design. This solves the problem of poor overall aircraft maneuverability caused by the large fuselage size and heavy transmission system of current dual-rotor tilt-rotor UAV transmission systems.

[0023] 2. The single-engine common-drive shaft quadrotor tilt-rotor UAV transmission system disclosed in this invention has an overrunning clutch installed on the engine output shaft unit, which enables the engine to engage and disengage; it adopts a four-stage bevel gear pair and a one-stage planetary gear pair; the bevel gear pair is used for deceleration and reversal, and the planetary gear pair is used for high speed ratio deceleration, resulting in a compact structure and high transmission efficiency; the intermediate planetary gear train sun gear shaft is connected to the output shaft of the first intermediate reduction unit, and the planetary carrier shaft is connected to the output shaft of the second intermediate reduction unit, realizing a coaxial design of the transmission shaft, making the overall structure compact and achieving good weight reduction.

[0024] Other advantages, objectives, and features of the invention will be set forth in part in the description which follows, and in part will be apparent to those skilled in the art from the following examination, or may be learned from practice of the invention. The objectives and other advantages of the invention can be realized and obtained through the following description. Attached Figure Description

[0025] To make the objectives, technical solutions, and advantages of the present invention clearer, the preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings, wherein:

[0026] Figure 1 This is a schematic diagram of the transmission system of the single-engine, common-drive shaft quadrotor tilt-rotor UAV of the present invention;

[0027] Figure 2 This is a front view of the transmission system of the single-engine common-drive shaft quadrotor tilting UAV of the present invention;

[0028] Figure 3 This is a schematic diagram of the transmission principle of the single-engine, common-shaft quadrotor tilting UAV transmission system of the present invention.

[0029] Reference numerals: First-stage bevel gear shaft 1, first-stage input bevel gear 4, first-stage output bevel gear 5, second-stage bevel gear shaft 8, second-stage input bevel gear 11, second-stage output bevel gear 13, third-stage bevel gear shaft 15, third-stage input bevel gear 18, intermediate planetary gear train planetary carrier 20, third-stage output bevel gear 22, first intermediate reduction unit output shaft 24, inner reduction and reversing unit input bevel gear 26, inner reduction and reversing unit output bevel gear 28, inner rotor shaft 29, cylindrical roller bearing 30. Four-point contact ball bearing 31, inner planetary gear train planetary carrier 32, second intermediate reduction unit output shaft 36, deep groove ball bearing 37, transmission long shaft 38, outer rotor shaft 40, outer reduction and reversing unit output bevel gear 42, outer reduction and reversing unit input bevel gear 44, outer reduction and reversing unit input shaft 46, tapered roller bearings 2, 3, 6, 7, 9, 10, 12, 14, 16, 17, 19, 21, 23, 25, 27, 33, 34, 35, 39, 41, 43, 45. Detailed Implementation

[0030] The following specific examples illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and various details in this specification can be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of the present invention. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0031] The accompanying drawings are for illustrative purposes only and are schematic diagrams, not actual pictures. They should not be construed as limiting the invention. To better illustrate the embodiments of the invention, some parts in the drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. It is understandable to those skilled in the art that some well-known structures and their descriptions may be omitted in the drawings.

[0032] In the accompanying drawings of the embodiments of the present invention, the same or similar reference numerals correspond to the same or similar components. In the description of the present invention, it should be understood that if terms such as "upper," "lower," "left," "right," "front," and "rear" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, they are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the terms used to describe positional relationships in the drawings are only for illustrative purposes and should not be construed as limiting the present invention. For those skilled in the art, the specific meaning of the above terms can be understood according to the specific circumstances.

[0033] like Figures 1-3 The transmission system of the single-engine common drive shaft quadrotor tilt UAV shown includes an engine output unit, an intermediate reduction unit connected to the engine output unit via an overrunning clutch, and four reduction and reversing units symmetrically distributed on the left and right sides of the intermediate reduction unit.

[0034] The engine output unit includes an engine output shaft (not shown), and the engine output shaft is connected to the intermediate reduction unit via an overrunning clutch (not shown). Specifically, the engine output shaft is connected to the first-stage bevel gear shaft 1 of the intermediate reduction unit via an overrunning clutch.

[0035] The intermediate reduction unit adopts a symmetrical design with identical structures on both sides. The intermediate reduction unit includes a first-stage bevel gear shaft 1, a second-stage bevel gear shaft 8 that is driven on the first-stage bevel gear shaft 1, a third-stage bevel gear shaft 15 that is driven on both sides of the second-stage bevel gear shaft 8, and a first intermediate reduction unit output shaft 24 and a second intermediate reduction unit output shaft 36 that are driven on the third-stage bevel gear shaft 15 respectively.

[0036] Specifically, the first-stage bevel gear shaft 1 is integrally connected to the first-stage input bevel gear 4 at one end near the second-stage bevel gear shaft 8. The second-stage output bevel gear 5, which meshes with the first-stage input bevel gear 4, is integrally connected to the middle of the second-stage bevel gear shaft 8. The two ends of the second-stage bevel gear shaft 8 are splinedly connected to the second-stage input bevel gear 11. The third-stage bevel gear shaft 15 is splinedly connected to the second-stage output bevel gear 13 at one end near the second-stage input bevel gear 11. The second-stage input bevel gear 11 meshes with the second-stage output bevel gear 13. The third-stage bevel gear shaft 15 is adjacent to... One end of the first intermediate reduction unit output shaft 24 is integrally connected to a third-stage input bevel gear 18. The end of the first intermediate reduction unit output shaft 24 near the third-stage input bevel gear 18 is splined connected to a third-stage output bevel gear 22. The third-stage input bevel gear 18 and the third-stage output bevel gear 22 mesh. The ends of the first intermediate reduction unit output shaft 24 that are close to each other are splined connected to the intermediate planetary gear train planet carrier 20. The ends of the intermediate planetary gear train planet carrier 20 that are opposite to each other are splined connected to the corresponding second intermediate reduction unit output shaft 36.

[0037] In the intermediate planetary gear train, the sun gear shaft in the planet carrier 20 is connected to the output shaft 24 of the first intermediate reduction unit, and the planet carrier shaft is connected to the output shaft 36 of the second intermediate reduction unit, realizing a coaxial design of the transmission shaft, making the overall structure compact and achieving good weight reduction.

[0038] Tapered roller bearings 2 and 3 are installed on the first-stage bevel gear shaft 1 to provide support; tapered roller bearings 6 and 7 are installed at the connection between the second-stage bevel gear shaft 8 and the first-stage bevel gear shaft 1 to provide support; tapered roller bearings 9 and 10 are installed on the second-stage bevel gear shaft 8 at the connection between its two ends and the third-stage bevel gear shaft 15 to provide support; tapered roller bearings 12 and 14 are installed on the third-stage bevel gear shaft 15 at the connection between its two ends and the third-stage bevel gear shaft 15 to provide support. Support; tapered roller bearings 16 and 17 are installed on the third-stage bevel gear shaft 15 at the connection between the third-stage bevel gear shaft 15 and the output shaft 24 of the first intermediate reduction unit to provide support; tapered roller bearings 19, 21, and 23 are installed on the output shaft 24 of the first intermediate reduction unit at the connection between the third-stage bevel gear shaft 15 and the output shaft 24 of the first intermediate reduction unit to provide support; tapered roller bearing 35 is installed at the connection between the output shaft 24 of the first intermediate reduction unit and the output shaft 36 of the second intermediate reduction unit to provide support.

[0039] The drive shaft unit adopts a left-right symmetrical design, including a long drive shaft 38 located on both sides of the output shaft 36 of the second intermediate reduction unit and connected to it, and a coupling (not shown) for connecting the output shaft 36 of the second intermediate reduction unit and the long drive shaft 38.

[0040] Four deceleration and reversing units are symmetrically distributed on both sides of the middle decelerator unit, including the right outer deceleration and reversing unit, the right inner deceleration and reversing unit, the left outer deceleration and reversing unit, and the left inner deceleration and reversing unit. The left outer deceleration and reversing unit has the same structure as the right outer deceleration and reversing unit, and the left inner deceleration and reversing unit has the same structure as the right inner deceleration and reversing unit.

[0041] Both the left and right outer deceleration and reversing units include an outer deceleration and reversing unit input shaft 46 that is connected to the transmission long shaft 38 and an outer rotor shaft 40 that is connected to the outer deceleration and reversing unit input shaft 46.

[0042] Specifically, the input shaft 46 of the outer deceleration and reversing unit is integrally connected to the input bevel gear 44 of the outer deceleration and reversing unit and the outer ball screw (not shown), and the output bevel gear 42 of the outer deceleration and reversing unit is integrally connected to the end of the outer rotor shaft 40, which meshes with the input bevel gear 44 of the outer deceleration and reversing unit.

[0043] The outer ball screw is connected to the housing outside the machine body and the outer reduction and reversing unit, enabling the outer reduction and reversing unit to rotate within the range of 0°-95°.

[0044] Both the left inner deceleration and reversing unit and the right inner deceleration and reversing unit include an inner deceleration and reversing unit input shaft that is driven by the output shaft 24 of the first intermediate deceleration unit, an inner rotor shaft 29 that is driven by the input shaft of the inner deceleration and reversing unit, and an inner planetary gear carrier 32 that is driven by the input shaft of the inner deceleration and reversing unit. The inner rotor shaft 29 is splinedly connected to the inner planetary gear carrier 32.

[0045] Specifically, the end of the first intermediate reduction unit output shaft 24 away from the third-stage input bevel gear 18 is integrally connected to the inner reduction and reversing unit input bevel gear 26 and the inner ball screw (not shown). The end of the inner reduction and reversing unit input shaft is integrally connected to the inner reduction and reversing unit output bevel gear 28, which meshes with the inner reduction and reversing unit input bevel gear 26. The inner reduction and reversing unit input shaft and the inner rotor shaft 29 are connected by a coupling.

[0046] The inner ball screw is connected to the housing outside the machine body and the inner speed reduction and reversing unit, enabling the inner speed reduction and reversing unit to rotate within the range of 0° to 95°.

[0047] Tapered roller bearings 25 and 27 are installed on the output shaft 24 of the first intermediate reduction unit at the connection between the output shaft 24 of the first intermediate reduction unit and the inner rotor shaft 29 to provide support. Tapered roller bearings 33 and 34 are installed on the input shaft of the inner reduction reversing unit at the connection between the output shaft 24 of the first intermediate reduction unit and the inner rotor shaft 29 to provide support. Cylindrical roller bearing 30 and four-point contact ball bearing 31 are installed on the inner rotor shaft 29 to provide support. The output shaft 36 of the second intermediate reduction unit is connected to the transmission long shaft. A deep groove ball bearing 37 is installed at the connection point 38 to provide support; a tapered roller bearing 39 is installed at the connection point between the transmission long shaft 38 and the outer reduction reversing unit input shaft 46 to provide support; a tapered roller bearing 45 is installed on the outer reduction reversing unit input shaft 46 at the connection point between the outer reduction reversing unit input shaft 46 and the outer rotor shaft 40 to provide support; and tapered roller bearings 41 and 43 are installed on the outer rotor shaft 40 at the connection point between the outer reduction reversing unit input shaft 46 and the outer rotor shaft 40 to provide support.

[0048] The transmission system of this single-engine, common-shaft quadcopter tilt-rotor UAV receives power from the engine. Power is then transmitted via the first-stage bevel gear shaft 1, through the first-stage input bevel gear 4 and the first-stage output bevel gear 5, to the second-stage bevel gear shaft 8. Next, power is transmitted via the second-stage input bevel gear 11 and the second-stage output bevel gear 13, to the third-stage bevel gear shaft 15. Finally, power is transmitted via the third-stage input bevel gear 18 and the third-stage output bevel gear 22, to the output shaft 24 of the first intermediate reduction unit. At this point, the power is split, with a portion flowing through the inner side... The input bevel gear 26 of the deceleration and reversing unit and the output bevel gear 28 of the inner deceleration and reversing unit decelerate and reversal to transmit power to the inner planetary gear train 32. Finally, the power is decelerated and transmitted to the inner rotor shaft 29 through the inner planetary gear train 32. Another part is connected to the sun gear of the intermediate planetary gear train planet carrier 20 through the output shaft 24 of the first intermediate deceleration unit to decelerate and transmit power to the output shaft 36 of the second intermediate deceleration unit. The power is decelerated and reversal transmitted to the outer rotor shaft 40 through the input bevel gear 44 of the outer deceleration and reversing unit and the output bevel gear 46 of the outer deceleration and reversing unit.

[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A transmission system for a single-engine, common-shaft quadrotor tilt-rotor unmanned aerial vehicle, characterized in that, It includes an engine output unit, an intermediate reduction unit connected to the engine output unit, a drive shaft unit, and four reduction and reversing units symmetrically distributed on the left and right sides of the intermediate reduction unit. The intermediate reduction unit includes a first-stage bevel gear shaft (1), a second-stage bevel gear shaft (8) driven on the first-stage bevel gear shaft (1), a third-stage bevel gear shaft (15) driven on both sides of the second-stage bevel gear shaft (8), and a first intermediate reduction unit output shaft (24) and a second intermediate reduction unit output shaft (36) driven on the third-stage bevel gear shaft (15); the first intermediate reduction unit output shaft (24) and the second intermediate reduction unit output shaft (36) are coaxially designed. The third-stage bevel gear shaft (15) is equipped with a third-stage input bevel gear (18) at one end near the output shaft (24) of the first intermediate reduction unit. The first intermediate reduction unit output shaft (24) is equipped with a third-stage output bevel gear (22) at one end near the third-stage input bevel gear (18). The third-stage input bevel gear (18) and the third-stage output bevel gear (22) mesh with each other. The intermediate planetary gear carrier (20) is installed at one end of the first intermediate reduction unit output shaft (24) that is close to each other. The opposite ends of the intermediate planetary gear carrier (20) are connected to the corresponding second intermediate reduction unit output shaft (36). The drive shaft unit includes a long drive shaft (38) located on both sides of the output shaft (36) of the second intermediate reduction unit and connected to it in a drive, and a coupling for connecting the output shaft (36) of the second intermediate reduction unit and the long drive shaft (38). The four deceleration and reversing units are symmetrically distributed on both sides of the middle decelerator unit, including the right outer deceleration and reversing unit, the right inner deceleration and reversing unit, the left outer deceleration and reversing unit with the same structure as the right outer deceleration and reversing unit, and the left inner deceleration and reversing unit with the same structure as the right inner deceleration and reversing unit. Both the left outer deceleration and reversing unit and the right outer deceleration and reversing unit include an outer deceleration and reversing unit input shaft (46) that is connected to the transmission long shaft (38) and an outer rotor shaft (40) that is connected to the outer deceleration and reversing unit input shaft (46); both the left inner deceleration and reversing unit and the right inner deceleration and reversing unit include an inner deceleration and reversing unit input shaft that is connected to the first intermediate deceleration unit output shaft (24), an inner rotor shaft (29) that is connected to the inner deceleration and reversing unit input shaft, and an inner planetary gear carrier (32).

2. The single-engine, common-shaft quadrotor tilt-rotor UAV transmission system as described in claim 1, characterized in that, The engine output unit includes an engine output shaft and an overrunning clutch. The engine output shaft is connected to the first-stage bevel gear shaft (1) of the intermediate reduction unit via the overrunning clutch.

3. The single-engine, common-drive-shaft quadrotor tilt-rotor UAV transmission system as described in claim 1, characterized in that, The first-stage bevel gear shaft (1) is equipped with a first-stage input bevel gear (4) at one end near the second-stage bevel gear shaft (8). The second-stage output bevel gear (5) that meshes with the first-stage input bevel gear (4) is installed in the middle of the second-stage bevel gear shaft (8). The second-stage input bevel gears (11) are installed at both ends of the second-stage bevel gear shaft (8). The third-stage bevel gear shaft (15) is equipped with a second-stage output bevel gear (13) at one end near the second-stage input bevel gear (11). The second-stage input bevel gear (11) meshes with the second-stage output bevel gear (13).

4. The transmission system for a single-engine, common-shaft quadrotor tilt-rotor UAV as described in claim 1, characterized in that, The first-stage bevel gear shaft (1) is integrally connected to the first-stage input bevel gear (4) at one end near the second-stage bevel gear shaft (8). The second-stage bevel gear shaft (8) is integrally connected to the first-stage output bevel gear (5) that meshes with the first-stage input bevel gear (4) at the middle. The two ends of the second-stage bevel gear shaft (8) are splined to the second-stage input bevel gear (11). The third-stage bevel gear shaft (15) is splined to the end near the second-stage input bevel gear (11) to the second-stage output bevel gear (13). The second-stage input bevel gear (11) meshes with the second-stage output bevel gear (13). The third-stage bevel gear shaft (15) is... The first intermediate reduction unit output shaft (24) is integrally connected to the third-stage input bevel gear (18) at one end. The first intermediate reduction unit output shaft (24) is splined connected to the third-stage output bevel gear (22) at one end. The third-stage input bevel gear (18) and the third-stage output bevel gear (22) mesh with each other. The intermediate planetary gear system planet carrier (20) is splined at the ends of the first intermediate reduction unit output shaft (24) that are close to each other. The opposite ends of the intermediate planetary gear system planet carrier (20) are splined connected to the corresponding second intermediate reduction unit output shaft (36).

5. The single-engine, common-drive-shaft quadrotor tilt-rotor UAV transmission system as described in claim 3, characterized in that, The outer deceleration and reversing unit input shaft (46) is equipped with an outer deceleration and reversing unit input bevel gear (44), and the outer rotor shaft (40) is equipped with an outer deceleration and reversing unit output bevel gear (42) that meshes with the outer deceleration and reversing unit input bevel gear (44); the first intermediate deceleration unit output shaft (24) is equipped with an inner deceleration and reversing unit input bevel gear (26) at the end away from the third stage input bevel gear (18), and the inner deceleration and reversing unit input shaft is equipped with an inner deceleration and reversing unit output bevel gear (28) that meshes with the inner deceleration and reversing unit input bevel gear (26).

6. The single-engine, common-drive-shaft quadrotor tilt-rotor UAV transmission system as described in claim 4, characterized in that, The outer deceleration and reversing unit input shaft (46) is integrally connected to the end of the outer deceleration and reversing unit input bevel gear (44), and the outer rotor shaft (40) is integrally connected to the end of the outer deceleration and reversing unit output bevel gear (42) that meshes with the outer deceleration and reversing unit input bevel gear (44); the end of the first intermediate deceleration unit output shaft (24) away from the third stage input bevel gear (18) is integrally connected to the inner deceleration and reversing unit input bevel gear (26), and the end of the inner deceleration and reversing unit input shaft is integrally connected to the end of the inner deceleration and reversing unit output bevel gear (28) that meshes with the inner deceleration and reversing unit input bevel gear (26).

7. The single-engine, common-drive-shaft quadrotor tilt-rotor UAV transmission system as described in claim 1, characterized in that, The first-stage bevel gear shaft (1), the second-stage bevel gear shaft (8), the third-stage bevel gear shaft (15), the first intermediate reduction unit output shaft (24), the second intermediate reduction unit output shaft (36), the outer reduction reversing unit input shaft (46), the outer rotor shaft (40), and the inner reduction reversing unit input shaft are equipped with back-to-back tapered roller bearings for support, and the inner rotor shaft (29) is equipped with cylindrical roller bearings and four-point contact ball bearings for support.

8. The single-engine, common-drive-shaft quadrotor tilt-rotor UAV transmission system as described in claim 5, characterized in that, In the intermediate reduction unit, the output shaft (24) of the first intermediate reduction unit is splinedly connected to the planetary carrier (20) of the intermediate planetary gear system, and the output shaft (36) of the second intermediate reduction unit is splinedly connected to the long transmission shaft (38); in the outer reduction and reversing unit, the input shaft (46) of the outer reduction and reversing unit is splinedly connected to the long transmission shaft (38); in the inner reduction and reversing unit, the planetary carrier (32) of the inner planetary gear system is splinedly connected to the inner rotor shaft (29).

9. A rotary-wing aircraft, characterized in that, The device includes a fuselage and a single-engine, common-drive shaft, quadrotor, tilt-rotor unmanned aerial vehicle (UAV) transmission system as described in any one of claims 1 to 8, wherein the fuselage contains the single-engine, common-drive shaft, quadrotor, tilt-rotor UAV transmission system.

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