Tilt actuation system of tilt-rotor aircraft

Abstract

The invention relates to a tilt actuation system of a tilt-rotor aircraft. The tilt actuation system comprises a tilt actuation unit, an active power input unit and a backup power input unit, the tilting actuation unit comprises a ball screw and a screw nut used in cooperation with the ball screw. The driving power input unit comprises a driving power input unit shell, driving power input equipment, a planetary gear train in transmission connection with an input shaft of the driving power input equipment and a first triple gear in transmission connection with the planetary gear train. The backup power input unit comprises a backup power input unit shell, backup power input equipment, a second triple gear in transmission connection with an input shaft of the backup power input equipment, and a worm and gear mechanism in transmission connection with the second triple gear; the problems that an existing tilting actuation system of the tilting rotor aircraft is poor in operability, low in control efficiency, poor in stability and prone to system failure, and consequently the flight safety cannot be guaranteed are solved.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace technology, and relates to a tilt-rotor aircraft tilt actuation system, and in particular to a tilt-rotor aircraft tilt actuation system with compact structure, good operability, high control accuracy, good stability and certain anti-failure capability. Background Art

[0002] In the field of aerospace, a tilt-rotor aircraft is a new type of aircraft that integrates fixed-wing aircraft and helicopter aircraft. It has both the vertical take-off and landing and air hovering capabilities of conventional helicopters and the high-speed cruising flight capabilities of turboprop aircraft. When the rotor tilt system components are in a vertical position, the tilt-rotor aircraft is similar to a twin-rotor horizontal helicopter, which can hover, fly sideways, fly backwards, and take off and land vertically, eliminating the need for a take-off and landing runway; when the rotor tilt system components are in a horizontal position, the tilt-rotor aircraft is equivalent to a fixed-wing aircraft, capable of high-speed long-distance flight and increasing the flight envelope.

[0003] The key core component for the tiltrotor aircraft to achieve mode conversion is the nacelle tilt actuation system, which is located between the engine nacelle and the wing end, and can drive the tiltrotor aircraft nacelle to tilt according to the control command. At present, the domestic tiltrotor aircraft tilt actuation system often uses a relatively simple transmission mechanism such as a gear mechanism to complete the tilt actuation, which has the disadvantages of poor operability, low control efficiency, and poor stability; at the same time, as a key component of the tiltrotor aircraft, the damage caused by the failure of the tilt actuation system is also huge. Therefore, it is necessary to propose a new type of tiltrotor aircraft tilt actuation system to solve the problems existing in the existing design. Summary of the invention

[0004] In view of this, the present invention provides a tilt-rotor aircraft tilt-actuation system in order to solve the problems of poor operability, low control efficiency, poor stability and easy system failure in the current tilt-rotor aircraft tilt-actuation system, which leads to the problem that flight safety cannot be guaranteed.

[0005] In order to achieve the above object, the present invention provides the following technical solutions:

[0006] A tilt-rotor aircraft tilt actuation system comprises a tilt actuation unit rotatably connected to a fuselage at a wing end, an active power input unit transmission-connected to the tilt actuation unit, and a backup power input unit, wherein the backup power input unit is rotatably connected to a tilt nacelle and is used to drive the tilt-rotor aircraft to smoothly switch between a helicopter mode and a fixed-wing mode;

[0007] The tilting actuating unit includes a ball screw and a screw nut used in conjunction with the ball screw;

[0008] The active power input unit includes an active power input unit housing, an active power input device, a planetary gear train drivingly connected to the input shaft of the active power input device, and a first triple gear drivingly connected to the planetary gear train, and the first triple gear is drivingly connected to the lead screw nut in the tilting actuating unit to ensure high efficiency and precise control of the aircraft tilting process;

[0009] The backup power input unit includes a backup power input unit housing, a backup power input device, a second triple gear transmission connected to the input shaft of the backup power input device, and a worm gear mechanism transmission connected to the second triple gear. The worm gear mechanism is connected to the ball screw transmission in the tilt actuator unit to realize redundant drive of the aircraft.

[0010] Furthermore, the planetary gear train includes a sun gear installed on the input shaft of the active power input device, a planetary gear meshing with the sun gear, a planetary carrier connected to the planetary gears, and a ring gear meshing with the planetary gears, the sun gear is meshingly connected to the inner side of the planetary gear, and the ring gear is meshingly connected to the outer side of the planetary gear; the first triple gear includes a first cylindrical gear connected to the planetary carrier, a second cylindrical gear meshing with the first cylindrical gear, and a third cylindrical gear connected to the second cylindrical gear, and the third cylindrical gear is drivingly connected to the lead screw nut in the tilt actuator unit.

[0011] Furthermore, the second triple gear includes a fourth cylindrical gear installed on the input shaft of the backup power input device, a fifth cylindrical gear meshing with the fourth cylindrical gear, and a sixth cylindrical gear meshing with the fifth cylindrical gear; the worm gear mechanism includes a meshing worm and a worm wheel, the worm is connected to the sixth cylindrical gear, and the worm wheel is connected to the ball screw transmission in the tilt actuator unit.

[0012] Furthermore, the screw nut is supported on the housing of the active power input unit through a tapered ball bearing, and the screw nut can rotate in the housing of the active power input unit.

[0013] Furthermore, the end of the ball screw is supported on the backup power input unit housing through a thrust bearing and a deep groove ball bearing, so that the ball screw can rotate in the backup power input unit housing. At the same time, when the backup power input unit is working, the thrust bearing bears axial force to cause the nacelle of the tilt-rotor aircraft to tilt.

[0014] Furthermore, a fuselage side hinge is fixedly installed on one side of the fuselage at the wing end, and the active power input unit housing is connected to the fuselage of the tilt-rotor aircraft through the fuselage side hinge, so that the tilt-rotor aircraft actuation system as a whole rotates around the fixed axis on the fuselage.

[0015] Furthermore, a nacelle side hinge is fixedly installed on one side of the tilt nacelle, and the backup power input unit shell is connected to the aircraft tilt nacelle through the nacelle side hinge, so that the backup power input unit can rotate on the tilt nacelle to compensate for installation errors.

[0016] Furthermore, the tilting actuating unit is a single-layer ball screw structure.

[0017] Furthermore, the tilt actuation unit is an inner and outer double-layer ball screw with the same lead, and a buffer device is installed on the active power input unit housing, the backup power input unit housing and the ball screw to reduce the impact of the tilt actuation system and the aircraft.

[0018] The beneficial effects of the present invention are:

[0019] 1. The tilt-rotor aircraft tilt-actuation system disclosed in the present invention adopts a dual power input design, including an active power input unit and a backup power input unit. Under normal working conditions, the active unit drives the tilt-actuation system, and when the active power input unit fails, the backup power input unit can automatically take over to ensure that the tilting action of the rotor is not interrupted, thereby improving flight safety. In addition, the system is also designed with a worm gear brake mechanism. When one of the transmission chains is working, the other transmission chain automatically maintains braking, avoiding the problem of tilting out of control due to external disturbances, and greatly improving the system's anti-failure ability and safety.

[0020] 2. The tilt-rotor aircraft tilt-actuation system disclosed in the present invention adopts planetary gear transmission and lead screw nut mechanism to ensure that the angle adjustment of the tilt-rotor is more accurate and stable. The planetary gear set can realize the smooth transmission of power, and the low friction characteristics of the ball screw enable the tilt-actuation system to be controlled with high precision, avoiding the control deviation caused by the accumulation of errors of the traditional gear mechanism.

[0021] 3. The tilting actuation system of a tilt-rotor aircraft disclosed in the present invention adopts a compact transmission structure design, and utilizes a combination of a planetary gear set and a worm gear mechanism to realize an actuation system with a smaller volume and higher transmission efficiency, so that it can be applied to tilt-rotor aircraft of different sizes and types. In addition, the present invention provides an optional double-layer ball screw design to enhance the mechanical rigidity and load-bearing capacity of the system in high-load applications, further improve the adaptability of the system, and at the same time add a buffer device to reduce the impact caused by the movement of the double-layer ball screw, thereby improving the stability and reliability of the entire system.

[0022] Other advantages, objectives and features of the present invention will be described in the following description to some extent, and to some extent, will be obvious to those skilled in the art based on the following examination and study, or can be taught from the practice of the present invention. The objectives and other advantages of the present invention can be realized and obtained through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to make the purpose, technical solutions and advantages of the present invention more clear, the present invention will be described in detail below in conjunction with the accompanying drawings, wherein:

[0024] Figure 1 It is an overall schematic diagram of the tilting actuation system of the tilt-rotor aircraft of the present invention;

[0025] Figure 2 A cross-sectional view of an active power input unit in a tilt-rotor aircraft tilt actuation system of the present invention;

[0026] Figure 3 A cross-sectional view of a backup power input unit in a tilt-rotor aircraft tilt actuation system of the present invention;

[0027] Figure 4 A schematic diagram of a main power input unit support in a tilt-rotor aircraft tilt actuation system of the present invention;

[0028] Figure 5 It is a schematic diagram of a backup power input unit support in the tilt-rotor aircraft tilt actuation system of the present invention.

[0029] Figure numerals: active power input unit 1, planetary gear train 11, planetary gear 111, sun gear 112, ring gear 113, planetary carrier 114, first triple gear 12, first cylindrical gear 121, second cylindrical gear 122, third cylindrical gear 123, active power input device 13, active power input unit housing 14, backup power input unit 2, second triple gear 21, fourth cylindrical gear 211, fifth cylindrical gear 212, sixth cylindrical gear 213, worm gear mechanism 22, worm 221, worm wheel 222, backup power input device 23, backup power input unit housing 24, tilt actuator unit 3, screw nut 31, ball screw 32, fuselage side hinge seat 4, nacelle side hinge seat 5. DETAILED DESCRIPTION

[0030] The following describes the embodiments of the present invention through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention.

[0031] like Figures 1 to 5A tilt-rotor aircraft tilt actuation system is shown, in which tilt nacelles are respectively installed at both ends of the wings extending from the fuselage of the tilt-rotor aircraft, and the rotors are respectively installed on the tilt nacelles. Driven by the tilt nacelles, the rotors dynamically tilt or position at a certain tilt angle. In the tilt-rotor aircraft in helicopter mode, the rotor axis of the rotor is perpendicular to the chord line of the wing; in the tilt-rotor aircraft in airplane mode, the rotor axis of the rotor is parallel to the chord line of the aircraft.

[0032] The tilt rotor aircraft tilt actuation system comprises a tilt actuation unit 3 rotatably connected to the fuselage at the wing end, an active power input unit 1 transmission-connected to the tilt actuation unit 3, and a backup power input unit 2, wherein the backup power input unit 2 is rotationally connected to the tilt nacelle.

[0033] The tilting actuating unit 3 includes a ball screw 32 and a screw nut 31 used in conjunction with the ball screw 32;

[0034] The active power input unit 1 includes an active power input unit housing 14, an active power input device 13, a planetary gear train 11 transmission-connected to the input shaft of the active power input device 13, and a first triple gear 12 transmission-connected to the planetary gear train 11. The planetary gear train 11 and the first triple gear 12 are arranged in the active power input unit housing 14.

[0035] Specifically, the planetary gear train 11 includes a sun gear 112 mounted on the input shaft of the active power input device 13, a planetary gear 111 meshed with the sun gear 112, a planetary carrier 114 connected to the planetary gear 111, and a ring gear 113 meshed with the planetary gear 111. The sun gear 112 is meshed and connected to the inner side of the planetary gear 111, and the ring gear 113 is meshed and connected to the outer side of the planetary gear 111. The first triple gear 12 includes a first cylindrical gear 121 connected to the planetary carrier 114, a second cylindrical gear 122 meshed with the first cylindrical gear 121, and a third cylindrical gear 123 connected to the second cylindrical gear 122. The third cylindrical gear 123 is drivingly connected to the lead screw nut 31 in the tilting actuator unit 3.

[0036] The backup power input unit 2 includes a backup power input unit housing 24, a backup power input device 23, a second triple gear 21 transmission-connected to the input shaft of the backup power input device 23, and a worm gear mechanism 22 transmission-connected to the second triple gear 21. The second triple gear 21 and the worm gear mechanism 22 are arranged in the backup power input unit housing 24.

[0037] Specifically, the second triple gear 21 includes a fourth cylindrical gear 211 installed on the input shaft of the backup power input device 23, a fifth cylindrical gear 212 meshing with the fourth cylindrical gear 211, and a sixth cylindrical gear 213 meshing with the fifth cylindrical gear 212; the worm gear mechanism 22 includes a meshing worm 221 and a worm wheel 222, the worm 221 is connected to the sixth cylindrical gear 213, and the worm wheel 222 is transmission-connected to the ball screw 32 in the tilt actuator unit 3.

[0038] The lead screw nut 31 is supported on the active power input unit housing 14 through a tapered ball bearing, and the lead screw nut 31 can rotate in the active power input unit housing 14. At the same time, when the backup power input unit 2 is working, the tapered roller bears the axial force, so that the nacelle of the tilt-rotor aircraft tilts. The end of the ball screw 32 is supported on the backup power input unit housing 24 through a thrust bearing and a deep groove ball bearing, so that the ball screw 32 can rotate in the backup power input unit housing 24. At the same time, when the backup power input unit 2 is working, the thrust bearing bears the axial force.

[0039] The active power input unit housing 14 is connected to the tiltrotor aircraft fuselage through the fuselage side hinge 4, so that the tiltrotor aircraft actuation system as a whole can rotate around the fixed axis on the fuselage. The backup power input unit housing 24 is connected to the aircraft tilt nacelle through the nacelle side hinge 5, so that the backup power input unit 2 can rotate on the tilt nacelle and compensate for certain installation errors.

[0040] The tilt actuator unit 3 can select an inner and outer double-layer ball screw with the same lead. This article only takes a single-layer ball screw as an example, but it should be noted that when using a double-layer ball screw, the positions of the upper and lower fulcrums of the system's tilt actuator unit are certain when it is actuated, but the relative positions of the inner and outer layer screws of the double-layer screw are chaotic, which may have a certain impact on the overall system. Therefore, it is necessary to add a buffer device to the active power input unit housing 14, the backup power input unit housing 24 and the ball screw 32 to reduce the impact of the impact on the system and the aircraft.

[0041] When the tilt-rotor aircraft's tilt actuation system works normally, the active power input device 13 inputs power to the system. At this time, the ball screw 32 is braked by the worm gear mechanism 22, and the power is transmitted to the screw nut 31 through the planetary gear train 11 and the first triple gear 12, causing the screw nut 31 to rotate forward or reverse, and the tilt actuation system completes the actuation work.

[0042] When the active power input unit 1 of the tilt-rotor aircraft's tilt actuation system fails or fails, the backup power input device 23 inputs power to the system. At this time, the screw nut 31 is braked by the active power input device 13, and the power is transmitted to the ball screw 32 through the second triple gear 21 and the worm gear mechanism 22, causing the ball screw 32 to rotate forward or reverse, and the tilt actuation system completes the actuation work.

[0043] When the tilt actuator unit 3 is retracted to the starting point of the stroke, the nacelle of the tilt rotor aircraft is at the bottom dead center, the rotor shaft is horizontal, and the aircraft is in fixed-wing mode; conversely, when the tilt actuator unit is extended to the end of the stroke, the nacelle of the tilt rotor aircraft is at the top dead center, the rotor shaft is vertical, and the aircraft is in helicopter mode.

[0044] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the purpose and scope of the technical solution, which should be included in the scope of the claims of the present invention.

Claims

1. A tilt-rotor aircraft tilt actuation system, characterized in that: It comprises a tilting actuating unit (3) rotatably connected to a fuselage at a wing end, an active power input unit (1) transmission-connected to the tilting actuating unit (3), and a backup power input unit (2), wherein the backup power input unit (2) is rotatably connected to the tilting nacelle and is used to drive the tilt-rotor aircraft to smoothly switch between a helicopter mode and a fixed-wing mode; The tilting actuation unit (3) comprises a ball screw (32) and a screw nut (31) used in conjunction with the ball screw (32); the active power input unit (1) comprises an active power input unit housing (14), an active power input device (13), a planetary gear train (11) drivingly connected to an input shaft of the active power input device (13), and a first triple gear (12) drivingly connected to the planetary gear train (11); the first triple gear (12) is drivingly connected to a screw nut (31) in the tilting actuation unit (3) to ensure high efficiency and precise control of the aircraft tilting process; the backup power input unit (2) comprises a backup power input unit housing (24), a backup power input device (23), a second triple gear (21) drivingly connected to an input shaft of the backup power input device (23), and a worm gear mechanism (22) drivingly connected to the second triple gear (21); the worm gear mechanism (22) is drivingly connected to a ball screw (32) in the tilting actuation unit (3) to achieve redundant driving of the aircraft.

2. The tilt-rotor aircraft tilt actuation system according to claim 1, characterized in that: The planetary gear train (11) comprises a sun gear (112) mounted on an input shaft of an active power input device (13), a planetary gear (111) meshing with the sun gear (112), a planetary carrier (114) connected to the planetary gear (111), and a ring gear (113) meshing with the planetary gear (111); the sun gear (112) is meshingly connected to the inside of the planetary gear (111), and the ring gear (113) is meshingly connected to the outside of the planetary gear (111); the first triple gear (12) comprises a first cylindrical gear (121) connected to the planetary carrier (114), a second cylindrical gear (122) meshing with the first cylindrical gear (121), and a third cylindrical gear (123) connected to the second cylindrical gear (122); the third cylindrical gear (123) is drivingly connected to a lead screw nut (31) in a tilting actuating unit (3).

3. The tilt-rotor aircraft tilt actuation system according to claim 2, characterized in that: The second triple gear (21) comprises a fourth cylindrical gear (211) mounted on the input shaft of the backup power input device (23), a fifth cylindrical gear (212) meshing with the fourth cylindrical gear (211), and a sixth cylindrical gear (213) meshing with the fifth cylindrical gear (212); the worm gear mechanism (22) comprises a meshing worm (221) and a worm wheel (222); the worm (221) is connected to the sixth cylindrical gear (213), and the worm wheel (222) is drivingly connected to a ball screw (32) in the tilting actuating unit (3).

4. The tilt-rotor aircraft tilt actuation system according to claim 3, characterized in that: The spindle nut (31) is supported on the active power input unit housing (14) via a tapered ball bearing, and the spindle nut (31) is rotatable in the active power input unit housing (14).

5. The tilt-rotor aircraft tilt actuation system according to claim 3, characterized in that: The end of the ball screw (32) is supported on the backup power input unit housing (24) via a thrust bearing and a deep groove ball bearing, and the ball screw (32) can rotate in the backup power input unit housing (24).

6. The tilt-rotor aircraft tilt actuation system according to claim 3, characterized in that: A fuselage side hinge seat (4) is fixedly mounted on one side of the fuselage at the wing end, and an active power input unit housing (14) is connected to the fuselage of the tilt-rotor aircraft via the fuselage side hinge seat (4), so that the tilt-rotor aircraft actuation system as a whole rotates around a fixed axis on the fuselage.

7. The tilt-rotor aircraft tilt actuation system according to claim 3, characterized in that: A nacelle side hinge seat (5) is fixedly mounted on one side of the tilting nacelle, and a backup power input unit housing (24) is connected to the aircraft tilting nacelle via the nacelle side hinge seat (5), so that the backup power input unit (2) can be rotated on the tilting nacelle to compensate for installation errors.

8. The tilt-rotor aircraft tilt actuation system according to claim 3, characterized in that: The tilting actuating unit (3) is a single-layer ball screw structure.

9. The tilt-rotor aircraft tilt actuation system according to claim 3, characterized in that: The tilt actuation unit (3) is an inner and outer double-layer ball screw with the same lead, and a buffer device is installed on the active power input unit housing (14), the backup power input unit housing (24) and the ball screw (32) to reduce the impact of the tilt actuation system and the aircraft.

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