CN115924071A - Tilt rotor aircraft hub system - Google Patents
Tilt rotor aircraft hub system Download PDFInfo
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- CN115924071A CN115924071A CN202310233633.6A CN202310233633A CN115924071A CN 115924071 A CN115924071 A CN 115924071A CN 202310233633 A CN202310233633 A CN 202310233633A CN 115924071 A CN115924071 A CN 115924071A
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- elastic bearing
- bearing
- central
- hub
- ball
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention relates to the field of aviation, and particularly discloses a hub system of a tilt rotor machine, which comprises a main shaft and a hub central part, wherein the main shaft and the hub central part are connected through a spherical hinge connecting device, the spherical hinge connecting device is fixedly arranged on the hub central part, the spherical hinge connecting device comprises an upper central elastic bearing, a lower central elastic bearing, a torque divider, a driving connecting rod elastic bearing assembly and a spherical hinge bracket, the centers of the upper central elastic bearing, the lower central elastic bearing and the torque divider are provided with spline holes matched with the main shaft, the upper central elastic bearing and the lower central elastic bearing are connected in series through the spherical hinge bracket and then fixed on the hub central part, the torque divider is clamped between the upper central elastic bearing and the lower central elastic bearing, and the torque divider and the spherical hinge bracket are connected through the driving connecting rod elastic bearing assembly.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a hub system of a tilt rotor aircraft.
Background
Articulated rotors are conventional rotor types, which have been developed more and more experientially in long-term applications. However, this form is not ideal due to the inherent disadvantages of complex structure, large maintenance workload, poor safety, low superlongitudinal efficiency and low angular velocity damping, and thus, hingeless rotors have been studied in all respects. In the 60's of the 20 th century, the proposition of using elastic bearings to simplify the hub was made by the american.
The rotor system of a rotorcraft may achieve aeroelastic stability and basic power modes of the aircraft. Pitch rotor stability is particularly important when tiltrotors fly at high speeds, where torsional and bending stiffness of the wing plays an important role. Tiltrotors must also correctly place the wing bending mode away from the original forcing frequency.
The elastic bearing is widely applied at home and abroad, is used as an important component of a helicopter rotor system, plays a role in flexible connection between a blade and a hub central part, is usually used under certain radial, torsional and bending loads, reduces torsional, flapping and shimmy loads generated to the central part in the rotating process of the blade, and has important influence on the dynamic property of the rotor system due to all-directional rigidity performance indexes of the elastic bearing.
In the prior art, the elastic bearing is generally used for connecting the blade and the hub central piece, the hub central piece is generally in rigid connection with the main shaft, and the defect that the abrasion of the hub central piece is serious in the actual use process, so that the service life of the hub central piece is seriously influenced, and the maintenance and replacement cost is high.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a hub system of a tilt rotor aircraft, which solves the problem that the service life of a hub central part is short due to the rigid connection of the hub central part and a main shaft, thereby prolonging the service life of the hub central part and reducing the cost.
The purpose of the invention is realized by the following steps: a hub system of a tilt rotor machine comprises a main shaft and a hub central piece, wherein the hub central piece is made of a composite material, the main shaft and the hub central piece are connected through a spherical hinge connecting device, the spherical hinge connecting device is fixedly installed on the hub central piece, the spherical hinge connecting device is composed of an upper central elastic bearing, a lower central elastic bearing, a torque divider, a driving connecting rod elastic bearing assembly and a spherical hinge support, spline holes matched with the main shaft are formed in the centers of the upper central elastic bearing, the lower central elastic bearing and the torque divider, the upper central elastic bearing and the lower central elastic bearing are fixed on the hub central piece after being connected in series through the spherical hinge support, the torque divider is clamped between the upper central elastic bearing and the lower central elastic bearing, and the torque divider and the spherical hinge support are connected through the driving connecting rod elastic bearing assembly.
As a preferred technical solution of the hub system of the tiltrotor aircraft according to the present invention, the driving link elastic bearing assemblies are provided with three sets, and are uniformly arranged between the torque divider and the spherical hinge bracket, each driving link elastic bearing assembly includes a driving link, one end of the driving link is connected to the torque divider through a first elastic bearing, and the other end of the driving link is connected to the spherical hinge bracket through a second elastic bearing.
As a preferred technical solution of the hub system of the tiltrotor aircraft according to the present invention, the first elastic bearing and the second elastic bearing are both spherical structures, the first elastic bearing and the second elastic bearing are respectively disposed inside two ends of the driving link, the first elastic bearing is connected to an outer side of the torque divider via a first ball-head link, and the second elastic bearing is connected to the ball-and-socket joint bracket via a second ball-head link.
As a preferable embodiment of the hub system of a tilt rotor aircraft according to the present invention, the central axes of the first elastic bearing and the second elastic bearing are perpendicular to the central axis of the spherical hinge connecting device.
As a preferred technical solution of the hub system of the tiltrotor aircraft according to the present invention, the upper central elastic bearing includes an upper stacked elastic body disposed between a large end of the upper central elastic bearing and a small end of the upper central elastic bearing, contact surfaces of the large end of the upper central elastic bearing, the upper stacked elastic body, and the small end of the upper central elastic bearing are all spherical structures, an upper support boss is disposed on a circumferential edge of the large end of the upper central elastic bearing, the upper support boss is connected to a top end of the spherical hinge bracket, and the small end of the upper central elastic bearing abuts against a top end of the torque splitter.
As a preferred technical solution of the hub system of the tiltrotor aircraft according to the present invention, the lower central elastic bearing includes a lower laminated elastic body disposed between a large end of the lower central elastic bearing and a small end of the lower central elastic bearing, contact surfaces of the large end of the lower central elastic bearing, the lower laminated elastic body, and the small end of the lower central elastic bearing are all spherical structures, a lower support boss is disposed on a circumferential edge of the large end of the lower central elastic bearing, the lower support boss is connected to a bottom end of the spherical hinge bracket, and the small end of the lower central elastic bearing abuts against a bottom end of the torque splitter.
As a preferred technical solution of the hub system of the tiltrotor aircraft according to the present invention, the torque splitter and the spherical hinge bracket are both of a sleeve structure.
As the preferred technical scheme of the hub system of the tilt rotor aircraft, the number of the spherical hinge supports is 3N, and N is more than or equal to 1.
Compared with the prior art, the invention has the beneficial effects that:
the main shaft and the hub central part (made of composite materials) are connected by the spherical hinge connecting device, functions of swinging hinge, swinging hinge and variable-pitch hinge are realized by a group of parts, and the stress of the hub central part is transferred to the spherical hinge connecting device under the condition of not influencing the normal work of the blade, so that the stress condition of the hub central part is greatly reduced, the abrasion of the hub central part is reduced, the service life of the hub central part is prolonged, and the maintenance cost is greatly reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a perspective view of the structure of the present invention.
FIG. 2 is a top view of the structure of the present invention.
Fig. 3 is a perspective view of the ball joint device of the present invention.
Fig. 4 is a front view of the ball joint coupling device of the present invention.
Fig. 5 isbase:Sub>A sectional view taken alongbase:Sub>A-base:Sub>A in fig. 4.
The spherical hinge comprises a 100 spherical hinge connecting device, a 101 upper central elastic bearing, a 101a upper central elastic bearing large end, a 101b upper central elastic bearing small end, a 101c upper laminated elastic body, a 101d upper supporting boss, a 102 lower central elastic bearing, a 102a lower central elastic bearing large end, a 102b lower central elastic bearing small end, a 102c lower laminated elastic body, a 102d lower supporting boss, a 103 torque divider, a 103a mounting seat, a 104 driving connecting rod elastic bearing assembly, a 104a driving connecting rod, a 104b first elastic bearing, a 104c first ball connecting rod, a 104d second elastic bearing, a 104e second ball connecting rod, a 105 spherical hinge support, a 105a mounting plate, a 106 screw rod and a 200 hub central piece.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
A tiltrotor hub system as shown in fig. 1-5 comprises a main shaft (not shown in the drawings) and a hub central member 200, the hub central member 200 is made of a composite material, the main shaft and the hub central member 200 are connected via a ball joint connecting device 100, the ball joint connecting device 100 is fixedly mounted on the hub central member 200, the ball joint connecting device 100 is composed of an upper central elastic bearing 101, a lower central elastic bearing 102, a torque divider 103, a driving link elastic bearing assembly 104 and a ball joint support 105, the centers of the upper central elastic bearing 101, the lower central elastic bearing 102 and the torque divider 103 are provided with splined holes which are matched with the main shaft, the upper central elastic bearing 101 and the lower central elastic bearing 102 are fixed on the hub central member 200 after being connected in series via the ball joint support 105, the torque divider 103 is clamped between the upper central elastic bearing 101 and the lower central elastic bearing 102, and the torque divider 103 and the ball joint support 105 are connected via the driving link elastic bearing assembly 104.
Specifically, the main shaft penetrates through the hub center piece 200 and is connected through a spline, the hub center piece 200 is of a three-fork structure and is respectively used for connecting three blades, the main shaft is in transmission connection with an engine output shaft, the torque divider 103 is of a sleeve structure, the spherical hinge support 105 is of a six-sleeve structure and is uniformly distributed on the periphery, the screw rods 106 penetrate through the sleeves, and the spherical hinge connecting device 100 is fixedly installed on the hub center piece 200.
It should be noted that, among other things, the upper central elastic bearing 101 assembly and the lower central elastic bearing 102 assembly provide the hub flapping stiffness, and the drive link 104a bearing assembly provides the hub shimmy stiffness; the spherical hinge connecting device 100 has six-degree-of-freedom static stiffness parameters, the torque divider 103 connects the upper central elastic bearing 101, the driving connecting rod elastic bearing assembly 104 and the lower central elastic bearing 102 to form an inner ball of a spherical hinge, and the main function of the spherical hinge connecting device is to transmit and distribute the torsion of a main shaft to the elastic bearing of the driving connecting rod 104 a; the spherical hinge bracket 105 connects the upper central elastic bearing 101, the driving connecting rod 104a elastic bearing and the lower central elastic bearing 102 into a whole to form an outer ball of the spherical hinge, and the spherical hinge bracket 105 is connected with the hub central piece 200, so that the spherical hinge bracket 105 can transmit the torque of the driving connecting rod 104a elastic bearing to the hub; the ball and socket joint assembly 100 essentially acts as a coupling that functions to connect the main shaft to the hub, the performance requirements of a rotor coupling are very challenging due to the high torque and misalignment requirements (referring to the hub center axis being at an angle to the main shaft center axis due to flapping), and a coupling that transmits power (with rotor disconnect capability) from the rotor gearbox to the rotor must also accommodate the angular misalignment caused by the flapping motion of the rotor; it has the following advantages: high torque is transmitted in two directions, and large angular deviation is adapted; the invention operates as a constant speed coupling, does not need lubrication, simplifies a propeller hub system, reduces the number of parts, improves the reliability, reduces the weight and resistance of the propeller hub, improves the performance, enables the blades and the machine body to move as a whole, and has quicker operation response; meanwhile, the stress of the hub central part 200 is transferred to the spherical hinge connecting device 100, so that the stress condition of the hub central part 200 is greatly reduced, the abrasion of the hub central part 200 is reduced, the service life of the hub central part is prolonged, and the maintenance and overhaul cost is greatly reduced; when the rotor rotates, a reaction torque is generated, so that the airframe of the airplane rotates in the direction opposite to the rotation direction of the rotor.
Further, three sets of driving connecting rod elastic bearing assemblies 104 are provided and are uniformly arranged between the torque divider 103 and the spherical hinge support 105, each driving connecting rod elastic bearing assembly 104 comprises a driving connecting rod 104a, one end of each driving connecting rod 104a is connected with the torque divider 103 through a first elastic bearing 104b, and the other end of each driving connecting rod 104a is connected with the spherical hinge support 105 through a second elastic bearing 104 d.
Specifically, the driving link 104a is a dumbbell-shaped structure, and the first elastic bearing 104b and the second elastic bearing 104d are disposed in spherical cavities at two ends.
It should be noted that the main function of the driving link elastic bearing assembly 104 is to reduce the flutter and static dispersion instability phenomena of the main shaft and the blades, and the driving link elastic bearing assembly 104 adjusts the oscillating dynamic torque generated due to the misalignment of the angle through the bending of the elastic bearings at the two ends, so that the oscillating torque in the assembly is counteracted.
Further, the first elastic bearing 104b and the second elastic bearing 104d are both spherical structures, the first elastic bearing 104b and the second elastic bearing 104d are respectively arranged inside two ends of the driving connecting rod 104a, the first elastic bearing 104b is connected with the outer side of the torque divider 103 through a first ball connecting rod 104c, and the second elastic bearing 104d is connected with the ball hinge support 105 through a second ball connecting rod 104 e.
Specifically, an installation seat 103a is arranged on the outer side of the torque divider 103, the root of a first ball head connecting rod 104c is fixed on the installation seat 103a, the ball head part extends into a spherical cavity at the end part of the driving connecting rod 104a, and an elastic body is arranged between the ball head part and the inner wall of the spherical cavity; the side of the spherical hinge support 105 is provided with a mounting plate 105a, the root of the second ball head connecting rod 104e is fixed on the mounting plate 105a, the head of the sphere extends into the spherical cavity at the other end of the driving connecting rod 104a, and the elastic body is arranged between the head of the sphere and the inner wall of the spherical cavity.
It should be noted that the above design can effectively avoid the resonance of the transmission system, reduce the noise of the transmission system, and balance the reaction moment.
Further, the central axes of the first elastic bearing 104b and the second elastic bearing 104d are perpendicular to the central axis of the ball-and-socket joint device 100.
It should be noted that such a design ensures the operational effect of the drive link elastomeric bearing assembly 104.
Further, the upper central elastic bearing 101 comprises an upper laminated elastic body 101c arranged between the upper central elastic bearing large end 101a and the upper central elastic bearing small end 101b, the contact surfaces of the upper central elastic bearing large end 101a, the upper laminated elastic body 101c and the upper central elastic bearing small end 101b are all of a spherical structure, an upper supporting boss 101d is arranged on the periphery of the upper central elastic bearing large end 101a, the upper supporting boss 101d is connected to the top end of the spherical hinge support 105, and the upper central elastic bearing small end 101b abuts against the top end of the torque divider 103.
Specifically, the upper laminated elastic body 101c is obliquely disposed between the upper central elastic bearing large end 101a and the upper central elastic bearing small end 101 b.
It should be noted that, by adopting such a design, the torsional rigidity of the connecting part of the shaft and the transmission system can be reduced, so that the natural frequency of the torsional vibration of the transmission system can be reduced, the torsional damping of the transmission system can be increased, the corresponding amplitude of the torsional resonance can be inhibited, and the transient torsional vibration generated by the collision can be attenuated.
Further, the lower central elastic bearing 102 includes a lower laminated elastic body 102c disposed between the lower central elastic bearing large end 102a and the lower central elastic bearing small end 102b, the contact surfaces of the lower central elastic bearing large end 102a, the lower laminated elastic body 102c and the lower central elastic bearing small end 102b are all spherical structures, a lower support boss 102d is disposed on the periphery of the lower central elastic bearing large end 102a, the lower support boss 102d is connected to the bottom end of the ball hinge support 105, and the lower central elastic bearing small end 102b abuts against the bottom end of the torque divider 103.
Specifically, the upper laminated elastic body 101c is obliquely disposed between the upper central elastic bearing large end 101a and the upper central elastic bearing small end 101 b.
It should be noted that, the design can reduce the torsional rigidity of the connecting part of the shaft and the transmission system, thereby reducing the natural frequency of the torsional vibration of the transmission system, increasing the torsional damping of the transmission system, inhibiting the corresponding amplitude of the torsional resonance, and attenuating the instant torsional vibration generated by the conflict.
The traditional main shaft is usually a hollow cylindrical metal shaft and is driven by a transmission device to extend upwards, the top of the main shaft is a mounting pivot of the blade, namely a hub, the two are important parts for directly transmitting the load of the blade to a machine body, the design eliminates the need of metal-to-metal contact and lubrication of the conventional hinged type, the workload of maintenance is greatly reduced, and the structure is self-stable.
The above description of the embodiments is only intended to facilitate the understanding of the method of the invention and its core idea. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, it is possible to make various improvements and modifications to the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (8)
1. A hub system of a tilt rotor aircraft comprises a main shaft and a hub central piece (200), and is characterized in that the hub central piece (200) is made of a composite material, the main shaft and the hub central piece (200) are connected through a spherical hinge connecting device (100), the spherical hinge connecting device (100) is fixedly installed on the hub central piece (200), the spherical hinge connecting device (100) consists of an upper central elastic bearing (101), a lower central elastic bearing (102), a torque divider (103), a driving connecting rod elastic bearing assembly (104) and a spherical hinge support (105), the centers of the upper central elastic bearing (101), the lower central elastic bearing (102) and the torque divider (103) are provided with spline holes matched with the main shaft, the upper central elastic bearing (101) and the lower central elastic bearing (102) are connected in series through the spherical hinge support (105) and then fixed on the hub central piece (200), and the torque divider (103) is clamped between the upper central elastic bearing (101) and the lower central elastic bearing (102) at the same time, and the torque divider (103) is connected with the spherical hinge support (105) through the driving connecting rod elastic bearing assembly (104).
2. A tiltrotor aircraft hub system according to claim 1, wherein the drive link elastomeric bearing assembly (104) comprises three sets, evenly disposed between the torque divider (103) and the ball-and-socket joint support (105), the drive link elastomeric bearing assembly (104) comprising a drive link (104 a), one end of the drive link (104 a) being connected to the torque divider (103) via a first elastomeric bearing (104 b), and the other end of the drive link (104 a) being connected to the ball-and-socket joint support (105) via a second elastomeric bearing (104 d).
3. The tiltrotor aircraft hub system according to claim 2, wherein the first resilient bearing (104 b) and the second resilient bearing (104 d) are both spherical structures, the first resilient bearing (104 b) and the second resilient bearing (104 d) are respectively disposed inside two ends of the driving link (104 a), the first resilient bearing (104 b) is connected to an outer side of the torque divider (103) via a first ball-end link (104 c), and the second resilient bearing (104 d) is connected to the ball-and-socket joint bracket (105) via a second ball-end link (104 e).
4. A tiltrotor aircraft hub system according to claim 3, wherein the central axes of the first and second elastomeric bearings (104 b, 104 d) are out of phase with the central axis of the ball-and-socket joint (100).
5. A tiltrotor aircraft hub system according to any of claims 1-4, wherein the upper central elastomeric bearing (101) comprises an upper stack of elastomers (101 c) disposed between an upper central elastomeric bearing big end (101 a) and an upper central elastomeric bearing small end (101 b), the contact surfaces of the upper central elastomeric bearing big end (101 a), the upper stack of elastomers (101 c), and the upper central elastomeric bearing small end (101 b) are all spherical structures, the periphery of the upper central elastomeric bearing big end (101 a) is provided with an upper support boss (101 d), the upper support boss (101 d) is connected to the top end of the ball-and-socket joint support (105), and the upper central elastomeric bearing small end (101 b) abuts against the top end of the torque divider (103).
6. A tiltrotor rotor hub system according to any one of claims 1-4, wherein the lower central elastic bearing (102) comprises a lower laminated elastic body (102 c) disposed between a lower central elastic bearing large end (102 a) and a lower central elastic bearing small end (102 b), the contact surfaces of the lower central elastic bearing large end (102 a), the lower laminated elastic body (102 c) and the lower central elastic bearing small end (102 b) are all spherical structures, the periphery of the lower central elastic bearing large end (102 a) is provided with a lower support boss (102 d), the lower support boss (102 d) is connected to the bottom end of the ball-hinge support (105), and the lower central elastic bearing small end (102 b) is abutted against the bottom end of the torque divider (103).
7. A tiltrotor aircraft hub system according to any one of claims 1-4, wherein the torque splitter (103) and the ball pivot mount (105) are of a sleeve construction.
8. A tiltrotor aircraft hub system according to any one of claims 1 to 4, wherein there are 3N ball joint brackets (105), N ≧ 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310233633.6A CN115924071A (en) | 2023-03-13 | 2023-03-13 | Tilt rotor aircraft hub system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310233633.6A CN115924071A (en) | 2023-03-13 | 2023-03-13 | Tilt rotor aircraft hub system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115924071A true CN115924071A (en) | 2023-04-07 |
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ID=86656195
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310233633.6A Withdrawn CN115924071A (en) | 2023-03-13 | 2023-03-13 | Tilt rotor aircraft hub system |
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| Country | Link |
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| CN (1) | CN115924071A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3759632A (en) * | 1972-07-05 | 1973-09-18 | United Aircraft Corp | Articulated helicopter rotor |
| US4203708A (en) * | 1978-06-26 | 1980-05-20 | United Technologies Corporation | Elastomeric rotor load reaction system |
| US4304525A (en) * | 1978-06-02 | 1981-12-08 | Societe Nationale Industrielle Aerospatiale | Helicopter rotor |
| US6030177A (en) * | 1998-12-18 | 2000-02-29 | Sikorsky Aircraft Corporation | Drive system for a variable diameter tilt rotor |
| US20140322010A1 (en) * | 2013-04-29 | 2014-10-30 | Bell Helicopter Textron Inc. | Constant-velocity joint link with reduced axial stiffness |
| US20180273160A1 (en) * | 2017-03-22 | 2018-09-27 | Bell Helicopter Textron Inc. | High Stiffness Hub Assembly for Proprotor Systems |
| US20190277343A1 (en) * | 2018-03-08 | 2019-09-12 | Bell Helicopter Textron Inc. | Drive link |
| US20210094680A1 (en) * | 2019-10-01 | 2021-04-01 | Bell Textron Inc. | Hub with integral elastomeric bearing |
| CN216805816U (en) * | 2021-12-20 | 2022-06-24 | 中国人民解放军总参谋部第六十研究所 | Rotor hub with elastic constraint |
-
2023
- 2023-03-13 CN CN202310233633.6A patent/CN115924071A/en not_active Withdrawn
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3759632A (en) * | 1972-07-05 | 1973-09-18 | United Aircraft Corp | Articulated helicopter rotor |
| US4304525A (en) * | 1978-06-02 | 1981-12-08 | Societe Nationale Industrielle Aerospatiale | Helicopter rotor |
| US4203708A (en) * | 1978-06-26 | 1980-05-20 | United Technologies Corporation | Elastomeric rotor load reaction system |
| US6030177A (en) * | 1998-12-18 | 2000-02-29 | Sikorsky Aircraft Corporation | Drive system for a variable diameter tilt rotor |
| US20140322010A1 (en) * | 2013-04-29 | 2014-10-30 | Bell Helicopter Textron Inc. | Constant-velocity joint link with reduced axial stiffness |
| US20180273160A1 (en) * | 2017-03-22 | 2018-09-27 | Bell Helicopter Textron Inc. | High Stiffness Hub Assembly for Proprotor Systems |
| US20190277343A1 (en) * | 2018-03-08 | 2019-09-12 | Bell Helicopter Textron Inc. | Drive link |
| US20210094680A1 (en) * | 2019-10-01 | 2021-04-01 | Bell Textron Inc. | Hub with integral elastomeric bearing |
| CN216805816U (en) * | 2021-12-20 | 2022-06-24 | 中国人民解放军总参谋部第六十研究所 | Rotor hub with elastic constraint |
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Application publication date: 20230407 |