CN110683049B - Hub device for small-sized tilt rotor aircraft - Google Patents
Hub device for small-sized tilt rotor aircraft Download PDFInfo
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- CN110683049B CN110683049B CN201910870728.2A CN201910870728A CN110683049B CN 110683049 B CN110683049 B CN 110683049B CN 201910870728 A CN201910870728 A CN 201910870728A CN 110683049 B CN110683049 B CN 110683049B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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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
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Abstract
The embodiment of the invention discloses a hub device for a small-sized tilt rotor aircraft, relates to the technical field of rotor aircrafts, and can realize the pitch change of each blade and improve the operation reliability. The invention includes: the hub device is formed by assembling an upper part and a lower part which are separated from each other, and the upper part and the lower part are restrained by a circular ring; the lower part of the hub device is connected with the rotor shaft through a bolt; the Y-shaped shaft is arranged between the upper portion and the lower portion of the propeller hub, wherein a first gasket, a deep groove ball bearing, a sleeve, a deep groove ball bearing, a thrust bearing, a second gasket and a screw are sequentially arranged on the Y-shaped shaft from the propeller hub portion (the central position) to the outside; the inner side of the blade clamp is provided with a boss structure, and the boss structure is positioned between the second deep groove ball bearing and the thrust bearing. And a variable pitch rocker is arranged outside the root part of the blade clamp, wherein the size of the variable pitch rocker is matched with the relative position of the operating node. The invention is suitable for operation of small tiltrotor aircraft.
Description
Technical Field
The invention relates to the technical field of rotorcraft, in particular to a hub device for a small-sized tilt rotor aircraft.
Background
The helicopter has the advantages of vertical take-off and landing and hovering, and the fixed-wing aircraft has the characteristic of high flying speed. The tilt rotor aircraft is a novel aircraft integrating a fixed-wing aircraft and a helicopter, and has the functions of vertical take-off and landing, hovering and high-speed cruising flight capacity. In a helicopter mode (vertical flight and low-speed flight), the flight speed is low, a fixed wing surface is difficult to provide lift required by flight, and a rotor wing is used as a main lift surface, so that the control of an aircraft is required to be completed by an automatic helicopter tilter and a hub system; in a fixed-wing airplane mode (high-speed flight), the aircraft is operated in a propeller airplane mode, the fixed wing is used for generating lift force, the efficiency is higher, and the change of the flight speed is realized by changing the rotating speed of the propeller to adjust the thrust; and in the tilting transition state, stable flight is realized by adjusting the total distance and the rotating speed.
In the helicopter mode, if the control demand of the tilt rotor aircraft is ensured, if the control is carried out in a variable rotating speed mode, the lift force of the rotors on two sides is asymmetric, so that the roll moment is generated on the fuselage, the requirement on ground control is high, and yaw and side flight control cannot be realized quickly. In the fixed wing mode, if the operation is performed by an automatic tilter, on the one hand, the characteristic of the high-speed wing profile of the blade tip cannot be fully exerted, and on the other hand, the problem of coupling vibration caused by the operation of the rotor is large.
Therefore, it is an urgent need to study how to satisfy the requirements of maneuvering requirements and strength conditions, especially the problem of maneuvering reliability of a tiltrotor aircraft in a helicopter mode.
Disclosure of Invention
Embodiments of the present invention provide a hub device for a small-sized tilt rotor machine, which can realize pitch variation of each blade and improve handling reliability.
In a first aspect, embodiments of the present invention provide a hub device for a small tiltrotor aircraft, the hub device being formed by assembling two parts separated from each other, the upper part and the lower part being constrained by a circular ring;
the lower part of the hub device is connected with a rotor shaft (7) through a bolt (3);
the Y-shaped shaft is arranged between the upper portion and the lower portion of the propeller hub, wherein a first gasket, a deep groove ball bearing (6), a sleeve, the deep groove ball bearing (6), a thrust bearing (4), a second gasket and a screw are sequentially arranged on the outer side of the Y-shaped shaft and the portion close to the propeller hub from inside to outside;
the inner side of the blade clamp (1) is provided with a boss structure, the boss structure is positioned between the second deep groove ball bearing (6) and the thrust bearing (4), the thrust bearing (4) is used for bearing the centrifugal force generated by each blade when the rotor rotates, and the boss structure is used for transmitting the centrifugal force load to the thrust bearing (4);
and a variable pitch rocker (2) is arranged on the outer side of the root part of the blade clamp (1), wherein the size of the variable pitch rocker (2) is matched with the relative position of the operating node.
With reference to the first aspect, in a first possible implementation manner of the first aspect, an end of the blade clamp (1) is connected to the blade through a bolt (3), while the other end of the blade clamp (1) is connected to the hub through an intermediate connecting shaft, and the bolt (3) is used for fixing a part on the intermediate connecting shaft; one end of the variable pitch rocker arm (2) is connected to the blade clamp (1) through a bolt (3), and the other end of the variable pitch rocker arm (2) is connected with the variable pitch pull rod and is inclined through the automatic inclinator.
With reference to the first possible implementation manner of the first aspect, in a second possible implementation manner, the deep groove ball bearings (6) are installed in pairs, and a section of sleeve is installed in the middle of each deep groove ball bearing (6) and is used for bearing the moment, in a force couple manner, generated by the blade and transmitted to the hub; a specially designed shim (5) is mounted at the shaft end.
With reference to the first aspect, in a third possible implementation manner of the first aspect, the automatic inclinator includes a movable ring (8) and a stationary ring (12), the stationary ring (12) is divided into an upper portion and a lower portion and connected by a screw, the stationary ring (12) is nested on a spherical hinge, and a roller is installed between the movable ring (8) and the stationary ring (12).
Specifically, a motor is connected below the rotor shaft (7) and used for transmitting the torque output by the motor; a torque arm is formed by a movable ring (8), a first fish-fork-shaped component (9) and a second fish-fork-shaped component (10) of the automatic inclinator and is used for driving the movable ring (8) to rotate along with the rotor wing.
In the embodiment, three separation shafts are combined into a Y-shaped shaft, centrifugal force can be balanced in the structure, torque transmitted by the rotor shaft (7) is mainly transmitted by two bolts (3) at the hub, and the requirement on the appearance above the rotor shaft (7) is low. As shown in figure 6, the head shape of the rotor shaft (7) is designed to be in fit with the Y-shaped shaft, the hub is divided into an upper part and a lower part, and the upper part and the lower part of the hub are connected through a circular connecting ring. The circular connecting ring is designed to be in a tapered form, and the displacement and deformation of the hub are limited by the structural geometric shape. Thereby realizing the pitch change of each blade, and the rotating speed is driven by the motor to be input.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is an exploded view of a hub system provided by an embodiment of the present invention;
FIG. 2 is a three-dimensional and isometric view of a hub system provided by an embodiment of the present invention;
FIG. 3 is a schematic view of a blade clamp and a hub connection provided by an embodiment of the invention;
FIG. 4 is a schematic diagram of a torsion arm and a follower device according to an embodiment of the present invention;
FIG. 5 is a schematic view of an automatic recliner provided in accordance with an embodiment of the present invention;
FIG. 6 is a view of the hub components and assembly provided by an embodiment of the present invention.
Detailed Description
In order to make the technical solutions of the present invention better understood, the present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention. As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may also be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or coupled. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items. It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
Embodiments of the present invention provide a hub assembly for a small tiltrotor aircraft, such as the tiltrotor hub and steering mechanism shown in fig. 1 and 2, which is formed by assembling two parts separated from each other, with an annular ring between the upper and lower parts.
The lower part of the hub device is connected with the rotor shaft (7) through a bolt (3).
The ring (15) is used to connect the upper part (13) and the lower part (14), and the specific shape parameters of the ring depend on the specific parameters and load conditions of the hub. When the load on the propeller hub is larger, the circular ring has larger sectional area and smaller inclination of the inner wall surface; in addition, the inner wall surface has enough roughness to better limit the deformation of the hub. Roughness is positively correlated with the ability to limit deformation. Due to the existence of the circular ring, no hole needs to be formed in the Y-shaped shaft for connection, the strength is not weakened, and the weight of the structure can be greatly reduced.
The Y-shaped shaft is installed between the upper portion and the lower portion of the propeller hub, wherein a first gasket, a deep groove ball bearing (6), a sleeve, the deep groove ball bearing (6), a thrust bearing (4), a second gasket and a screw are installed on the Y-shaped shaft from the center position of the propeller hub to the outside in sequence.
The Y-shaped shaft is arranged between the upper portion and the lower portion of the propeller hub, wherein a first gasket, a deep groove ball bearing (6), a sleeve, the deep groove ball bearing (6), a thrust bearing (4), a second gasket and a screw are sequentially arranged on the outer side of the Y-shaped shaft and the portion close to the propeller hub from inside to outside.
The inboard that the paddle presss from both sides (1) is convex structure, convex structure is located between second deep groove ball bearing (6) and footstep bearing (4), and footstep bearing (4) are used for assuming the rotor when rotatory, the produced centrifugal force of every paddle, convex structure is used for transmitting centrifugal force load to footstep bearing (4).
And a variable pitch rocker (2) is arranged on the outer side of the root part of the blade clamp (1), wherein the size of the variable pitch rocker (2) is matched with the relative position of the operating node.
At present, the hub development at home and abroad is also quicker, the configuration of providing the flapwise, shimmy and deformation freedom degree of the blade by using the elastic bearing is more advanced at present, but the flapwise, shimmy and pitch-variable hinges are mainly arranged in application. Dongri Hua et al have designed a section of vert for rotor constant speed universal hinge oar hub, have mainly solved the undulant problem of rotational speed. The tilting rotor aircraft has a specific and better operation mode under different modes, and if the tilting rotor aircraft is operated in a single mode, the operation performance has certain limitation. Aiming at the characteristic, based on the light tilting rotorcraft, a design scheme of a hub and a control system which can realize different control modes under different flight states is provided, and the control requirements of the tilting rotorcraft on different flight states are realized. In this embodiment, based on the propeller hub structure of conventional helicopter, to the manipulation demand of the gyroplane that verts, designed a section and be applicable to the small-size gyroplane that verts' propeller hub system for realize the gyroplane that verts in the manipulation of flight in-process, the rotor hub that verts that designs in this case simple structure, the response is very fast, can satisfy displacement and variable speed and control, is applicable to the small-size gyroplane that verts of rigid paddle. Taking a scaling model of a certain type of tilt rotor aircraft as an example, intensity checking is carried out, and a calculation result shows that: the hub configuration can meet the operation requirement and the strength condition in each flight state, and has higher reliability. Meanwhile, a flow cover can be designed and installed on the outer side of the hub, so that the resistance caused by the separation of the air flow of the hub part in the flying process is reduced.
To solve the problem of maneuvering a tiltrotor aircraft in helicopter mode, the amount of maneuvering that each hub and maneuvering mechanism must provide is typically: total pitch, transverse periodic pitch, longitudinal periodic pitch, and rotation speed. The hub device designed by the embodiment aims to realize the pitch change of each blade.
In particular, for a conventional two-bladed rotor, one optical axis runs through the rotor shaft (7), on which the rotor centrifugal forces are balanced. For a three-bladed rotor, the blades are typically attached by means of three separate shafts. However, the configuration depends on the connection of the bolts (3) when the shaft is connected with the hub, and the mechanical property of the shaft is greatly influenced by the holes formed in the shaft, so that the embodiment combines three separated shafts into a Y-shaped shaft, the centrifugal force can be balanced in the structure, and the torque transmitted by the rotor shaft (7) is mainly transmitted by the two bolts (3) at the hub, and the requirement on the appearance above the rotor shaft (7) is lower. As shown in figure 6, the head shape of the rotor shaft (7) is designed to be in fit with the Y-shaped shaft, the hub is divided into an upper part and a lower part, and the upper part and the lower part of the hub are connected through a circular connecting ring. The circular connecting ring is designed to be in a tapered form, and the displacement and deformation of the hub are limited by the structural geometric shape. The part of the rotor shaft (7) protruding out of the hub is used for connecting and mounting a fairing.
The connection relationship between the blade clamp (1) and the hub is shown in fig. 3, the end of the blade clamp (1) is connected with the blade through a bolt (3), the other end of the blade clamp (1) is connected to the hub through an intermediate connecting shaft, and the bolt (3) is used for fixing a part on the intermediate connecting shaft.
One end of the variable-pitch rocker arm (2) is connected to the blade clamp (1) through a bolt (3), the other end of the variable-pitch rocker arm (2) is connected with the variable-pitch pull rod, and the automatic inclinator is inclined so as to transfer operation to the blades, and control of the blade pitch of each blade is achieved.
The deep groove ball bearings (6) are installed in pairs, and a section of sleeve is installed in the middle of each deep groove ball bearing (6) and bears the moment generated by the blades and transmitted to the hub in a force couple mode in the structure. A specially designed shim (5) is mounted at the shaft end.
The main parameter of this section is the diameter D of the Y-axiszAnd the distance l between two deep groove ball bearings (6)qz。DzThe size of the middle connecting shaft influences the centrifugal force limit born by the middle connecting shaft and the type selection of the deep groove ball bearing (6) and the thrust bearing (4) < CHEM > toqzThe size of the deep groove ball bearing (6) influences the size of the hub moment which can be borne by the deep groove ball bearing.
In this embodiment, as shown in fig. 5, the automatic inclinator comprises a movable ring (8) and a fixed ring (12), the fixed ring (12) is divided into an upper part and a lower part and is connected by a screw, and the fixed ring (12) is nested on a ball hinge to ensure the continuity of movement. Rollers are arranged between the movable ring (8) and the fixed ring (12) to realize relative rotation. The automatic inclinator part is composed of a movable ring and a fixed ring. The two are connected by a cylindrical roller to realize relative rotation. The fixed ring is divided into an upper part and a lower part, a small screw necklace is arranged between the upper part and the lower part and is embedded on the spherical hinge, and the rotation between the fixed ring and the spherical hinge is realized.
The main parameters of the automatic recliner are the radius R of the central spherical hinge, and the half height h. The mutual relationship between the two needs to be satisfied
To ensure the automatic inclinator to have a + -15 deg. operating space.
As further shown in fig. 4, a motor is connected below the rotor shaft (7),for transmitting the torque output by the motor. A torque arm is formed by a movable ring (8), a first harpoon-shaped component (9) and a second harpoon-shaped component (10) of the automatic inclinator and is used for driving the movable ring (8) to rotate along with the rotor. The torque cannot be borne because the variable-pitch pull rod is a two-force rod, so that the necessity of the mechanism is seen. The torsion arm is essentially a crank rocker mechanism, and as can be seen from fig. 4 (b), the torsion arm retains the freedom of rotation of the rotating ring around the spherical hinge in addition to transmitting torque while the rotor shaft (7) rotates. In the design of the mechanism, the main parameters are four-segment rod length: l1、 l2、l3、l4. In the design of four lever lengths, the need for steering should be determined: the amount of operation of the automatic tilter is typically + -15 deg., so3And l4Is (75 degrees, 105 degrees); to ensure the transfer efficiency of the mechanism,/1And l2The included angle (acute angle) between the two is a transmission angle, and at least 40 degrees is required; l4The length of the control node determines the outward extension of the control node and is reasonably selected according to the size of the hub part; l1、l2、l4The length of the three rods indirectly reflects the mass of the mechanism, and the smaller the length, the lower the mass. Therefore, the length of the four-segment rod should be comprehensively selected according to the design parameters of the rotor hub and the operation requirement.
As shown in fig. 6, the hub is designed mainly according to the load, working environment, safety factor, etc. when the rotor is working. Because the rotor wing aerodynamic environment is complex and the alternating load is serious, the value of the safety factor is between 1.5 and 2.0. The rotor shaft (7) is simple in structure, but is loaded in a complex manner, main loads on the rotor shaft (7) of the tilt rotor aircraft are tension and torque in a helicopter mode and a fixed wing mode, and the influence of the bending moment on the rotor shaft (7) in the tilt transition process is also large. Meanwhile, the connection mode of the propeller hub and the rotor shaft (7) is considered to be bolt (3) connection, so that the weakening of the shaft performance of the hole must be considered. The main loads of the hub part are the hub force transferred by the rotation and rotation of the rotor, the hub moment and the centrifugal force, and the torque transferred by the rotor shaft (7). And estimating the aerodynamic load according to a rotor slip flow theory, and solving the hub force, the hub moment and the centrifugal force. The size of the hub part is designed according to torsion and bending at the same time, and the result with larger size is selected as the design result. The load condition of the middle connecting shaft is simpler, but the influence factors in the design process are more. The main loads of the intermediate connection shaft are the pulling force (rotor centrifugal force) and the shearing action at the connection with the hub. Factors that influence are the weight of the connecting shaft, the inner diameter of the bearing, the material, etc. The paddle clamp (1) is mainly designed in a functional mode, a ball bearing and a thrust bearing (4) need to be installed in a sufficient space inside the paddle clamp, and a variable pitch rocker arm (2) and a variable pitch pull rod are connected to the outside of the paddle clamp to achieve a variable pitch function.
Hub strength was checked by test experiments:
assuming that the takeoff weight of a certain type of tilt rotor aircraft is 90kg, the radius of a blade is 0.7m, and estimating the concentrated load of the blade according to an aerodynamic model of a momentum theory:
TABLE 1 estimation of basic parameters and loads of blades
The hub materials are selected as shown in the following table:
TABLE 2 propeller hub material selection parameter table
Under the load condition shown in the table 1, static strength checking is carried out on the most complex part of the hub, according to the checking result, the most severe position of the load is on a Y-shaped shaft, the maximum stress is 143.28Mpa, the safety factor is considered to be 2, and the material is selected from 45 steel for safety. The maximum displacement of the outer side of the blade clamp (1) is 0.35 mm.
It can be seen from a second time that in this example: firstly, because the tilt rotor aircraft combines two lift systems of a rotor wing and a fixed wing, the aerodynamic environment is complex in the flight process, particularly in a transition state, the total aircraft can provide more than ten control quantities, which exceed 6 control quantities of common balancing, and the attitude controllability in the flight process is ensured.
Secondly, due to the design space constraints, it is difficult for conventional hubs to limit weight while maintaining strength under heavy loads. Because the Y-shaped shaft is utilized, the connection mode of the bolt (3) is cancelled, the performance weakening of the shaft is reduced, the diameter of the connecting shaft can be effectively reduced, the types of corresponding standard components such as a deep groove ball bearing (6) and a thrust bearing (4) are correspondingly reduced, and the weight reduction of the whole propeller hub is facilitated.
And then, the conical ring at the hub has an obvious constraint effect on structural displacement, when the blade flaps and each isolated vertical shaft of the Y-shaped shaft bends upwards, the upper part and the lower part of the hub tend to separate, and the ring moves outwards due to the existence of the taper to push the blade clamp (1) to return to the original position. Or that the presence of the taper when the shaft is bent upwards prevents the ring from sliding inwards, limiting the separation of the upper and lower hubs.
All the embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the apparatus embodiment, since it is substantially similar to the method embodiment, it is relatively simple to describe, and reference may be made to some descriptions of the method embodiment for relevant points. The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (5)
1. A hub device for small tiltrotor aircraft, characterized in that it is formed by assembling two parts separated one above the other, constrained by a ring (15) between an upper part (13) and a lower part (14), possibly supplemented by gluing;
a ring (15) for connecting the upper part (13) and the lower part (14);
the lower part (14) of the hub device is connected with the rotor shaft (7) through a bolt (3);
the Y-shaped shaft is arranged between the upper portion and the lower portion of the propeller hub, wherein a first gasket, a first deep groove ball bearing, a sleeve, a second deep groove ball bearing, a thrust bearing (4), a second gasket and a screw are sequentially arranged on the Y-shaped shaft from the center of the propeller hub to the outside;
the inner side of the blade clamp (1) is provided with a boss structure, the boss structure is positioned between the second deep groove ball bearing and the thrust bearing (4), the thrust bearing (4) is used for bearing the centrifugal force generated by each blade when the rotor rotates, and the boss structure is used for transmitting the centrifugal force load to the thrust bearing (4);
and a variable pitch rocker (2) is arranged on the outer side of the root part of the blade clamp (1), wherein the size of the variable pitch rocker (2) is matched with the relative position of the operating node.
2. Hub device for small tiltrotor aircraft according to claim 1, characterized in that the end of the blade clamp (1) is connected to the blade by means of a bolt (3), while the other end of the blade clamp (1) is connected to the hub by means of an intermediate connecting shaft, the bolt (3) being used to fix a part on said intermediate connecting shaft;
one end of the variable pitch rocker arm (2) is connected to the blade clamp (1) through a bolt (3), and the other end of the variable pitch rocker arm (2) is connected with the variable pitch pull rod and topples over through the automatic inclinator.
3. The hub arrangement for a small tiltrotor aircraft according to claim 2, wherein the first and second deep-groove ball bearings are mounted in pairs, with a sleeve mounted intermediate the first and second deep-groove ball bearings to bear in the structure, in the form of a couple of forces, the moment of the lift generated by the blades transmitted to the hub;
a specially designed gasket (5) is arranged at the outer end of the Y-shaped shaft.
4. The hub arrangement for a small tiltrotor aircraft according to claim 1, wherein the automatic tilter comprises a movable ring (8) and a stationary ring (12), the stationary ring (12) is divided into an upper portion and a lower portion and is connected by a screw, the stationary ring (12) is nested on a ball joint, and a roller is installed between the movable ring (8) and the stationary ring (12).
5. Hub device for small tiltrotor aircraft according to claim 4, characterized in that the electric motor is connected below the rotor shaft (7) for transmitting the torque output by the electric motor;
a torque arm is formed by a movable ring (8), a first fish-fork-shaped component (9) and a second fish-fork-shaped component (10) of the automatic inclinator and is used for driving the movable ring (8) to rotate along with the rotor wing.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910870728.2A CN110683049B (en) | 2019-09-16 | 2019-09-16 | Hub device for small-sized tilt rotor aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910870728.2A CN110683049B (en) | 2019-09-16 | 2019-09-16 | Hub device for small-sized tilt rotor aircraft |
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| CN110683049A CN110683049A (en) | 2020-01-14 |
| CN110683049B true CN110683049B (en) | 2022-07-12 |
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| CN112478154B (en) * | 2020-12-05 | 2022-04-12 | 北京航空航天大学 | Rotor propeller suitable for tilt-rotor aircraft |
| CN112550688B (en) * | 2020-12-16 | 2022-11-29 | 范家铭 | Coaxial helicopter and rotor system thereof |
| CN113942641B (en) * | 2021-10-09 | 2023-09-26 | 中国直升机设计研究所 | Elastic universal hinge |
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| CN110683049A (en) | 2020-01-14 |
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