Power transmission and tilting structure of tilting rotorcraft
Through the tilt actuator driving the tilt part and parallel shaft design of the nacelle, the power transmission and safety problems of the tilt rotor aircraft during switching between different flight modes are solved, and the smooth switching between hover and front flight modes and safe flight of the tilt rotor aircraft under single-side engine failure is achieved.
Patent Information
- Application Number
- CN202510505667.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-22
- Publication Date
- 2025-07-08
AI Technical Summary
The prior art is difficult to achieve smooth switching between different flight modes of tilt rotor aircraft, especially safe flight in the event of engine failure.
A tilt rotor aircraft power transmission and tilt configuration is designed. The tilt actuator drives the tilt part of the nacelle to rotate within 90 degrees, and combines the parallel shaft to achieve power backup to ensure power transmission and safety when switching between different flight modes.
It realizes smooth switching between hover and forward flight modes, and ensures flight safety when the single-sided engine fails, and has the ability to fly at high speed and take-off and land.
Smart Images
Figure CN120270499A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a power transmission and tilting configuration of a tiltrotor aircraft, belonging to the field of overall design of aviation aircrafts. Background Art
[0002] A tiltrotor aircraft is a high-speed rotorcraft that can take off and land vertically. Its speed and range are twice that of a conventional configuration helicopter, and its transportation efficiency is much higher than that of a conventional configuration helicopter. It is particularly suitable for performing tasks such as troop / equipment assault transportation, combat search and rescue, special operations, logistics support, and medical evacuation.
[0003] The tiltrotor aircraft does not require an airport and a runway and has three flight modes: in the helicopter mode, the rotor provides lift, enabling vertical takeoff and landing and low-speed maneuverability; in the fixed-wing propeller aircraft mode, the rotor tilts forward to provide forward thrust, and the wing provides lift, enabling high-speed flight and low-drag and high-efficiency improvement of economy; the transition flight mode provides the function of switching between the helicopter and fixed-wing flight modes.
[0004] The tiltrotor aircraft combines the flight characteristics of a helicopter and a propeller aircraft. At different speed segments, the three flight modes are switched by tilting the rotor. Therefore, a power transmission route different from that of a conventional helicopter and a propeller aircraft needs to be designed. Driven by this power transmission route, the transition between different flight modes can be achieved, as well as the power required to transfer from the engine to the rotor for the rotor to hover or fly forward. Summary of the Invention
[0005] Object of the Invention: Conventional helicopters generally have a single-rotor with a tail rotor configuration: the engine outputs power to the main reduction gearbox, which distributes the power to the main rotor and the tail rotor. The main rotor generates lift to drive the helicopter to hover or fly forward, and the tail rotor controls the flight direction.
[0006] A propeller aircraft generally outputs power from the engine to the propeller to rotate and generate thrust to drive the aircraft to fly forward.
[0007] The present invention proposes a power transmission route and a tiltrotor configuration driven by this power transmission, enabling the tiltrotor to switch between the helicopter and fixed-wing flight modes and meet the power requirements. The tiltrotor aircraft can not only take off vertically like a helicopter but also fly forward at high speed like a fixed-wing propeller aircraft, thus possessing the characteristics and advantages of both types of aircraft.
[0008] Technical Solution:
[0009] Provide a power transmission and tilting configuration of a tiltrotor aircraft, including: a fuselage, a wing, and a nacelle;
[0010] The fuselage is the main structure of the tiltrotor aircraft, used to carry all the equipment and payload of the aircraft; the wings are horizontally arranged on both the left and right sides of the fuselage and installed on the upper part of the fuselage. Short nacelles are installed at both ends of the wings, and lift can also be generated by the wings when the tiltrotor aircraft is flying forward; the short nacelles are arranged at both ends of the wings and mainly install engines, main reducers, and rotor systems. The short nacelles are divided into a tiltable part and a fixed part:
[0011] Tiltable part: The tiltable part mainly includes the rotor system and the main reducer. The main reducer is installed on the upper outer side of the wing through two mounting brackets, and the main reducer can also be tilted downward by the tilt actuator based on these two mounting brackets; the rotor system is coaxial with the main reducer and installed on the upper part of the main reduction shaft of the main reducer. The main reducer transmits power from the main reduction to the rotation of the rotor through the main reduction shaft, thereby generating rotor thrust.
[0012] Fixed part: The fixed part mainly includes the engine, the engine power output shaft, the tilt axis, and the input shaft of the parallel shaft. The engine is installed outside the main reducer and is power-connected to the main reducer through the engine power output shaft at the front of the engine and the tilt axis. At the same time, it is also connected to the parallel shaft through the input shaft of the parallel shaft installed on the tilt axis.
[0013] Furthermore, the tiltable part of the short nacelle of the tiltrotor aircraft is tilted by the telescopic movement of the tilt actuator; the upper end of the tilt actuator is installed and fixed on the main reducer through a rotating shaft, and the lower end is installed on the outer side of the wing end through another rotating shaft.
[0014] Furthermore, the tilt actuator can perform telescopic movement under the drive of hydraulic power, and drive the tiltable part of the short nacelle to rotate within a range of 90 degrees through the rotating shafts fixed at both ends, realizing the switching between the forward flight cruise and hover modes of the tiltrotor aircraft.
[0015] Furthermore, when the tiltrotor aircraft switches between the forward flight cruise and hover modes, only the tiltable part tilts, while the engine remains fixed.
[0016] Furthermore, the main power transmission route for the forward flight and hover of the tiltrotor aircraft is as follows:
[0017] The engine generates power, which is transmitted to the tilt axis through the engine power output shaft and enters the main reducer. Inside the main reducer, the power is transmitted to the rotor system installed on the top of the main reducer through the main reduction shaft, driving the rotor to rotate and generate thrust, providing the power for the tiltrotor aircraft to hover or fly forward.
[0018] Furthermore, the backup power transmission route for the rotor systems at both ends of the wings of the tiltrotor aircraft is as follows:
[0019] In a tiltrotor aircraft, a parallel shaft that connects the left and right main reducers and the engine is installed inside the left and right wings. The outer end of the parallel shaft is connected to the tilt axis through the input shaft of the parallel shaft, enabling the power of the engines and main reducers on both sides of the wings to be connected. After one engine fails, through the parallel shaft, the rotors on the power failure side of the tiltrotor aircraft can still obtain power input, ensuring the flight safety of the tiltrotor aircraft.
[0020] Furthermore, as one of the force transmission routes, the tilt axis connects the engine power output shaft and the main reducer; the middle part of the tilt axis is also connected to the input shaft of the parallel shaft, and then through the parallel shaft, it connects the power systems at both ends of the wing to achieve power backup for the rotor systems on both sides of the wing.
[0021] Furthermore, the main structural components of the tiltrotor aircraft are: fuselage, wings and nacelles, engines, engine power output shafts, tilt axes, main reducers, input shafts of parallel shafts, parallel shafts, rotors, tilt actuators;
[0022] The engines installed in the outer nacelles at both ends of the wings generate power and output the power through the engine power output shafts installed at the front ends of the engines to the tilt axes connected to them; the tilt axes are installed on the fixed parts of the nacelles, and the other ends are connected to the main reducers. The engine power enters the main reducer through the tilt axes, and the power entering the main reducer drives the rotors installed on its top to rotate to generate rotor thrust, providing the power for the tiltrotor aircraft to hover and fly forward;
[0023] The middle part of the tilt axis is also connected to the input shaft of the parallel shaft. When the engine power enters the main reducer, it also simultaneously enters the parallel shaft installed in the wing and passing through the wing through the input shaft of the parallel shaft. Through the power transmission of the parallel shaft, the power at both ends of the wing is connected, realizing power backup on both sides of the wing and ensuring flight safety;
[0024] The tilting of the tiltable part of the nacelle is realized through the telescopic movement of the tilt actuators installed on the main reducer and the wing ends, enabling the tiltrotor aircraft to switch between the forward flight cruise and hover modes.
[0025] Advantageous effects: The invention can realize the power transmitted from the engine to the rotor required for the tiltrotor aircraft to hover or fly forward, as well as the nacelle movement mode for the tiltrotor aircraft to switch between different flight modes, effectively solving the key technologies in the development process of the tiltrotor aircraft. Description of the Drawings
[0026] Figure 1 It is a front view shaft side view of the helicopter flight mode.
[0027] Figure 2 It is a rear view shaft side view of the fixed-wing flight mode. 1 - fuselage, 2 - wing, 3 - nacelle, 4 - parallel shaft, 5 - engine, 6 - main reducer, 7 - rotor.
[0028] Figure 3 It is a schematic diagram of the nacelle configuration on the left side (heading) of the forward fuselage of a tiltrotor aircraft in hover state. 8 - Main reduction gear installation and rotating support, 9 - Input shaft of the parallel shaft, 10 - Tilt axis, 11 - Engine power output shaft, 12 - Main reduction gear shaft, 13 - Tilt actuator, 14 - Upper rotating shaft of the tilt actuator, 15 - Lower rotating shaft of the tilt actuator.
[0029] Figure 4 It is a schematic diagram of the nacelle configuration on the left side (heading) of the rear fuselage of a tiltrotor aircraft in forward flight state. Detailed implementation manner
[0030] The present invention provides a power transmission and tilt configuration for a tiltrotor aircraft, as Figures 1-4 shown, including: fuselage, wing and nacelle.
[0031] The fuselage is the main structure of the tiltrotor aircraft, used to carry all the equipment and loads of the aircraft.
[0032] The wings are transversely arranged on both the left and right sides of the fuselage and are installed on the upper part of the fuselage. Nacelles are installed at both ends of the wings; when the tiltrotor aircraft is in forward flight, lift can also be generated by the wings.
[0033] The nacelles are arranged at both ends of the wings. The nacelles mainly install engines, main reduction gears, rotor systems, etc. The nacelles are divided into a tilt part and a fixed part.
[0034] Tilt part: The tilt part is mainly the rotor system and the main reduction gear. The main reduction gear is installed on the upper part of the outer side of the wing through two installation supports. The main reduction gear can also be tilted downward under the drive of a tilt actuator based on these two installation supports; the rotor system and the main reduction gear are coaxial and are installed on the upper part of the main reduction gear shaft of the main reduction gear. The main reduction gear realizes the power transmission from the main reduction to the rotor rotation through the main reduction gear shaft, thereby generating rotor thrust.
[0035] Fixed part: The fixed part is mainly the engine, engine power output shaft, tilt axis, input shaft of the parallel shaft. The engine is installed outside the main reduction gear and is power-connected to the main reduction gear through the engine power output shaft at the front of the engine and the tilt axis. At the same time, it is also connected to the parallel shaft through the input shaft of the parallel shaft installed on the tilt axis.
[0036] When the tiltrotor aircraft in the present invention switches between forward flight cruise and hover modes, only the tilt part (rotor, main reduction gear) tilts under the drive of the tilt actuator, while the engine part remains fixed. The transmission routes of the power required to drive the tilt of the rotor and main reduction gear parts, as well as the forward flight and hover of the tiltrotor aircraft are as follows:
[0037] The engine (5) generates power, which is transmitted through the engine power output shaft (11) to the tilting shaft (10) and then enters the main reducer (6). Inside the main reducer, the power is transmitted to the rotor system through the main reducer shaft to drive the rotor to rotate, providing the power for the tiltrotor aircraft to hover or fly forward.
[0038] The tilting part of the tiltrotor nacelle realizes the tilting of the rotor and the main reducer part through the telescopic movement of the tilting actuator (13). The upper end of the tilting actuator (13) is installed and fixed on the main reducer through a rotating shaft (14), and the lower end is installed on the outside of the wing tip through another rotating shaft (15). The tilting actuator can perform telescopic movement under the drive of hydraulic power, and drives the tilting part of the nacelle (rotor, main reducer) to tilt within a range of 90 degrees through the rotating shafts fixed at both ends, realizing the switching of the tiltrotor aircraft between the forward flight cruise and hover modes.
[0039] Parallel shafts (4) connecting the left and right main reducers and the engine are installed inside the left and right wings of the tiltrotor aircraft. The outer end of the parallel shaft (4) is connected to the tilting shaft (10) through the input shaft (9) of the parallel shaft, enabling the power of the engines and main reducers on both sides of the wings to be connected. After one side of the engine fails, through the parallel shaft, the rotor on the power failure side of the tiltrotor aircraft can still obtain power input, ensuring the safe flight of the tiltrotor aircraft.
[0040] Key points of the present invention:
[0041] 1. The engine power enters the main reducer through the engine power output shaft and the tilting shaft, driving the rotor to rotate, providing the power for the tiltrotor aircraft to hover or fly forward;
[0042] 2. The tiltrotor aircraft drives the tilting part of the nacelle (rotor and main reducer part) to perform a rotational movement within a range of 90 degrees through the tilting actuator, realizing the switching of the tiltrotor aircraft between the forward flight cruise and hover modes;
[0043] The tiltrotor aircraft connects the engines and main reducers on both sides of the wings through the parallel shafts installed inside the left and right wings, ensuring the safe flight of the tiltrotor aircraft after one side of the engine fails.
[0044] To make the objectives, technical solutions, and advantages of the present application more clear, the following will describe the technical solutions in the embodiments of the present application in more detail in combination with the accompanying drawings in the embodiments of the present application. In the accompanying drawings, the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions from beginning to end. The described embodiments are part of the embodiments of the present application, rather than all of the embodiments. The embodiments described below by referring to the accompanying drawings are exemplary and are intended to explain the present application, and should not be construed as a limitation to the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present application. The following will explain the embodiments of the present application in detail in combination with the accompanying drawings.
[0045] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "axial direction", "vertical", "upper", "lower", "upper end", "bottom end", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the protection scope of the present invention.
[0046] After considering the specification and practicing the disclosure herein, those skilled in the art will readily conceive of other embodiments of the present disclosure. The present application is intended to cover any variations, uses, or adaptations of the present disclosure that follow the general principles of the present disclosure and include well-known knowledge or conventional technical means in the technical field not disclosed in the present disclosure. The specification and examples are only regarded as exemplary, and the true scope and spirit of the present disclosure are pointed out by the following claims.
[0047] It should be understood that the present disclosure is not limited to the exact structures already described and shown in the drawings, and various modifications and changes can be made without departing from its scope. The scope of the present disclosure is only limited by the appended claims.
Claims
1. A power transmission and tilting configuration of a tiltrotor aircraft, characterized in that, Comprising: Fuselage, wings and nacelles; The fuselage is the main structure of the tiltrotor aircraft, used to carry all the aircraft equipment and payloads; the wings are transversely arranged on both the left and right sides of the fuselage, installed on the upper part of the fuselage, and nacelles are installed at both ends of the wings. When the tiltrotor aircraft is flying forward, lift can also be generated by the wings; the nacelles are arranged at both ends of the wings, and mainly installed with engines, main reducers and rotor systems. The nacelles are divided into a tiltable part and a fixed part: Tiltable part: The tiltable part is mainly the rotor system and the main reducer. The main reducer is installed on the upper outer side of the wing through two mounting brackets, and the main reducer can also be tilted downward driven by a tilting actuator based on these two mounting brackets; the rotor system is coaxial with the main reducer and installed on the upper part of the main reduction shaft of the main reducer. The main reducer transmits power from the main reduction to the rotation of the rotor through the main reduction shaft, thereby generating rotor thrust; Fixed part: The fixed part is mainly the engine, the engine power output shaft, the tilting shaft, and the input shaft of the parallel shaft. The engine is installed outside the main reducer and is power-connected to the main reducer through the engine power output shaft at the front of the engine and the tilting shaft. At the same time, it is also connected to the parallel shaft through the input shaft of the parallel shaft installed on the tilting shaft.
2. The configuration according to claim 1, characterized in that, The tiltable part of the tiltrotor aircraft nacelle is tilted by the telescopic movement of the tilting actuator; the upper end of the tilting actuator is installed and fixed on the main reducer through a rotating shaft, and the lower end is installed on the outer side of the wing end through another rotating shaft.
3. The configuration according to claim 2, characterized in that The tilting actuator can perform telescopic movement driven by hydraulic power, and drives the tiltable part of the nacelle to rotate within a range of 90 degrees through the rotating shafts fixed at both ends, realizing the switching between the forward flight cruise and hover modes of the tiltrotor aircraft.
4. The configuration according to claim 3, characterized in that, When the tiltrotor aircraft switches between the forward flight cruise and hover modes, only the tiltable part tilts, while the engine remains stationary.
5. The configuration according to claim 1, characterized in that, The main power transmission route for the forward flight and hover of the tiltrotor aircraft is: The engine generates power, which is transmitted to the tilting shaft through the engine power output shaft and enters the main reducer. Inside the main reducer, the power is transmitted to the rotor system installed on the top of the main reducer through the main reduction shaft, driving the rotor to rotate and generate thrust, providing power for the tiltrotor aircraft to hover or fly forward.
6. The configuration according to claim 1, wherein The backup power transmission route for the rotor systems at both ends of the tiltrotor aircraft wings is: Parallel shafts connecting the left and right main reducers and the engines are installed inside the left and right wings of the tiltrotor aircraft. The outer ends of the parallel shafts are connected to the tilting shaft through the input shafts of the parallel shafts, enabling the power of the engines and main reducers on both sides of the wings to be connected. After one side of the engine fails, through the parallel shaft, the rotor on the power failure side of the tiltrotor aircraft can still obtain power input, ensuring the flight safety of the tiltrotor aircraft.
7. The configuration according to claim 6, characterized in that, As one of the power transmission routes, the tilting shaft connects the engine power output shaft and the main reducer; the middle of the tilting shaft is also connected to the input shaft of the parallel shaft, and then connects the power systems at both ends of the wings through the parallel shaft to realize the power backup of the rotor systems on both sides of the wings.
8. The configuration according to claim 1, wherein The main structural components of the tiltrotor aircraft are: fuselage, wings and nacelles, engines, engine power output shafts, tilting shafts, main reducers, input shafts of parallel shafts, parallel shafts, rotors, tilting actuators; The engines installed in the nacelles on the outer sides of both ends of the wing generate power, and the power is output through the engine power output shaft installed at the front end of the engine to the tilting shaft connected thereto; the tilting shaft is installed on the fixed part of the nacelle, and the other end is connected to the main reducer. The engine power enters the main reducer through the tilting shaft, and the power entering the main reducer drives the rotor installed on its top to rotate to generate rotor thrust, providing the power for the tiltrotor to hover and fly forward; The middle part of the tilting shaft is also connected to the input shaft of the parallel shaft. While the engine power enters the main reducer, it also synchronously enters the parallel shaft installed on the wing and passing through the wing through the input shaft of the parallel shaft. Through the power transmission of the parallel shaft, the power connection at both ends of the wing is realized, the power backup on both sides of the wing is realized, and the flight safety is guaranteed; The tilting of the tiltable part of the nacelle is realized through the telescopic movement of the tilting actuator installed on the main reducer and the wing end, enabling the tiltrotor to switch between the forward flight cruise and hover modes.