阅读说明：本技术 一种用于飞行器旋转部件的防松减振联轴器 (Anti-loosening vibration-damping coupler for aircraft rotating part ) 是由 李广良 于靖波 杨子盟 张子俊 刘兵兵 康国剑 张江 董金刚 秦永明 于 2021-06-28 设计创作，主要内容包括：本发明提供一种用于飞行器旋转部件的防松减振联轴器,使连接端头与传动轴固定连接后,再通过柔性铰链将两个连接端头进行连接,通过对连接端头与传动轴的连接方式、柔性铰链与连接端头的连接方式以及柔性铰链的减振结构,实现了复杂工况下设备动力传递过程中的缓冲减振,保证了在高速旋转、启停频繁且复杂振动工况下飞行器旋转部件的高定位精度、高可靠性和高使用寿命,同时本发明联轴器拆装简便,结构紧凑,在飞行器领域具有良好的应用前景。(The invention provides an anti-loosening vibration-damping coupler for a rotary part of an aircraft, which is characterized in that after a connecting end is fixedly connected with a transmission shaft, two connecting ends are connected through a flexible hinge, and through the connection mode of the connecting end and the transmission shaft, the connection mode of the flexible hinge and the connecting end and a vibration-damping structure of the flexible hinge, the buffering vibration damping in the power transmission process of equipment under a complex working condition is realized, and the high positioning precision, the high reliability and the high service life of the rotary part of the aircraft under the working conditions of high-speed rotation, frequent start and stop and complex vibration are ensured.)

1. A looseness-proof vibration-damping coupling for an aircraft rotating component is characterized by comprising a flexible hinge (1), a first connecting end head (31), a second connecting end head (32) and a safety positioning mechanism;

the first connecting end (31) and the second connecting end (32) are respectively matched with the first transmission shaft (5) and the second transmission shaft (6) and then fixedly connected through a safety positioning mechanism;

the flexible hinge (1) is cylindrical and is provided with an inner cavity penetrating through two end faces, and the connecting mechanisms arranged on the first connecting end (31) and the second connecting end (32) are respectively sleeved and connected with two ends of the flexible hinge (1);

a plurality of groups of openings are formed in the outer surface of the flexible hinge (1); each set of openings comprises a plurality of openings arranged circumferentially along the flexible hinge (1); the openings of each group are arranged in a staggered mode along the axial direction of the flexible hinge (1).

2. The anti-loosening and damping coupling for the rotating component of the aircraft as claimed in claim 1, wherein the flexible hinge (1) is provided with 2-6 groups of openings on the outer surface, and the size of each opening in the axial direction of the flexible hinge (1) is 0.6-0.8 mm; the distance between each group of openings along the axial direction of the flexible hinge (1) is 1-1.2 mm.

3. An anti-loosening and vibration damping coupling for an aircraft rotating component according to claim 1, characterized in that the connection means of the first connection end (31) and the second connection end (32) are cylindrical structures provided with tooth-like projections on their outer surfaces; the inner cavity of the flexible hinge (1) is provided with a dentate groove matched with the connecting mechanism.

4. The coupling as claimed in claim 3, wherein the tooth-like projections have a cross-sectional shape perpendicular to the axis of the coupling mechanism, which is rectangular, fan-shaped or trapezoidal.

5. The coupling of claim 3, wherein said coupling head further comprises a disc-shaped positioning mechanism disposed at one end of said coupling mechanism; the circular end face of the disc-shaped positioning mechanism is matched with the two ends of the flexible hinge (1) to realize the positioning of the connecting end and the flexible hinge (1).

6. A coupling according to any one of claims 3 to 5, characterised in that said safety positioning means are safety positioning pins (4);

the first connecting end (31) and the second connecting end (32) are respectively provided with an axial through hole which is in plug-in fit with the first transmission shaft (5) and the second transmission shaft (6); the connecting mechanism of the connecting end is provided with a first radial through hole, and the transmission shaft is provided with a second radial through hole; after the connecting end is in inserting fit with the transmission shaft, the safety positioning pin (4) is simultaneously matched with the first radial through hole and the second radial through hole, so that the connecting end is fixedly connected with the transmission shaft.

7. Anti-loose damping coupling for aircraft rotating parts according to claim 6, characterized in that the length of the safety dowel (4) is smaller than the radial dimension of the internal cavity of the flexible hinge (1).

8. The locking damping coupling for the aircraft rotating part of claim 5, characterized in that the locking damping coupling for the aircraft rotating part further comprises a damping limiting pad (2), wherein the damping limiting pad (2) is annular and is sleeved on a connecting mechanism arranged at the connecting end head;

the circular end face of the positioning device arranged at the connecting end is matched with the two ends of the flexible hinge (1) through the vibration reduction limiting pads (2).

9. An anti-loosening and vibration damping coupling for an aircraft rotating member according to any one of claims 1 to 8, characterized in that the cross-sectional shape of the drive shaft comprises a circle, a D-shape or a straight shape.

10. Anti-loosening and vibration damping coupling for rotating parts of aircraft according to claim 1, characterized in that said flexible hinge (1) has an outer diameter smaller than 18mm and an inner diameter greater than 6 mm; the length of the anti-loosening vibration-damping coupler formed after the flexible hinge (1) is matched with the first connecting end (31) and the second connecting end (32) along the axial direction is less than 25 mm.

11. The locking damping coupling for the rotating part of the aircraft of claim 8, wherein the other structures except the damping limiting pad (2) are made of metal.

Technical Field

The invention discloses an anti-loose vibration-damping coupler for a rotary part of an aircraft, belonging to the technical field of manufacturing of general mechanical products.

Background

The coupling is an important component of a mechanical transmission system, is commonly used for connecting two shafts or shafts and other rotating parts to transmit torque and motion, and is generally suitable for the fields of electromechanical equipment, aerospace and the like.

Couplings can be divided into two broad categories, rigid couplings and flexible couplings. The rigid coupling is composed of rigid parts, has no buffering and vibration damping effects, has higher requirement on the neutrality of two axis lines connected with the rigid coupling, and is only suitable for occasions with very small allowable relative displacement of the two axis lines. The rigid coupling has the advantages of simple structure, small volume and low manufacturing cost. The flexible coupling compensates the relative displacement of the two axes by the elastic deformation of the elastic element, and can buffer and damp vibration. At present, flexible couplings in the market are mainly divided into two types, namely, a metal elastic element configuration and a non-metal elastic element configuration. The metal element has high strength, large load transfer capacity and long service life; the metal elastic element has small size, the structural size of the coupling is small, and the cost is high.

Along with the rapid development of aerospace, the electromechanical equipment on the aircraft is subjected to more and more harsh working conditions, the requirements on equipment parts are higher and higher, particularly, the two-end structures connected with the coupler rotate at high speed along with the rotating parts of the aircraft when the two-end structures are started to rotate frequently, and the coupler is influenced by multi-directional vibration impact coupling and also influenced by impact loads such as start-stop impact, centrifugal force and the like. At present, the coupling on the market mostly adopts holding screw or screw and transmission shaft to carry out fastening connection, and the screw generally exposes, fasten through coupling side or axial direction, then generally satisfy the dimensional requirement of screw tightening to the integrative coupling of structure, the size is generally great, and need reserve the dismouting space, cause very big dog elbow to the sealed design of overall structure, then at high-speed rotation, when the vibration is violent to the coupling of components of a whole that can function independently structure, the screw is shaken loose very easily, the screw is thrown away very easily under the effect of centrifugal force, and then cause the unable work of coupling, dynamic balance can't satisfy the requirement scheduling problem, and then cause the damage to transmission shaft and relevant equipment. In addition, the shaft coupling generally adopts the pretightning force of screw to carry out the centre gripping to the transmission shaft, the moment of torsion that produces through the pretightning force transmits the moment of torsion that needs the transmission, as long as guarantee that the moment of torsion is far greater than the moment of torsion that needs the transmission can, nevertheless violently just open and stop frequently under the operating mode at the vibration, the shaft coupling passes through the running-in repeatedly with the transmission shaft, can cause the decline of screw pretightning force on the one hand, can wear out the material of the cooperation department of transmission shaft or shaft coupling on the one hand, all can cause the greatly reduced of moment of friction, and then cause the moment of torsion of transmission, the error appears in angle or rotational speed and even can't work. Therefore, the coupler on the market cannot meet the requirements on the reliability and the service life of the transmission torque, the rotation speed and the angle of the rotating part of the aircraft under the high-speed rotation of the whole equipment, and cannot ensure the normal use of the rotating part of the aircraft under complex working conditions of high-speed rotation, severe vibration and the like. In order to meet the working condition requirements of the rotating part of the aircraft, the requirements of vibration reduction, looseness prevention, disassembly and assembly space, positioning precision, compact size and the like of the coupler are design difficulties to be solved.

Disclosure of Invention

The invention aims to overcome the defects and provides an anti-loosening and vibration-damping coupler for an aircraft rotating part, wherein two connecting end heads are connected through a flexible hinge after the connecting end heads are fixedly connected with a transmission shaft, and the connection mode of the connecting end heads and the transmission shaft, the connection mode of the flexible hinge and the connecting end heads and a vibration damping structure of the flexible hinge are adopted, so that the buffering and vibration damping in the power transmission process of equipment under the complex working condition are realized, and the high positioning precision, the high reliability and the high service life of the aircraft rotating part under the working conditions of high-speed rotation, frequent start and stop and complex vibration are ensured.

In order to achieve the above purpose, the invention provides the following technical scheme:

a locking damping coupling for an aircraft rotating component comprises a flexible hinge, a first connecting end, a second connecting end and a safety positioning mechanism;

the first connecting end and the second connecting end are respectively matched with the first transmission shaft and the second transmission shaft and then fixedly connected through a safety positioning mechanism;

the flexible hinge is cylindrical and is provided with an inner cavity penetrating through two end faces, and the connecting mechanisms arranged at the first connecting end and the second connecting end are respectively sleeved and connected with two ends of the flexible hinge;

a plurality of groups of openings are formed in the outer surface of the flexible hinge; each set of openings comprises a plurality of openings arranged circumferentially along the flexible hinge; the openings of each group are arranged in a staggered mode along the axial direction of the flexible hinge.

Furthermore, the outer surface of the flexible hinge is provided with 2-6 groups of openings, and the axial size of each opening in the flexible hinge is 0.6-0.8 mm; the interval of each group of openings along the axial direction of the flexible hinge is 1-1.2 mm.

Furthermore, the connecting mechanism of the first connecting end and the second connecting end is a cylindrical structure with tooth-shaped bulges on the outer surface; the inner cavity of the flexible hinge is provided with a tooth-shaped groove matched with the connecting mechanism.

Further, the cross-sectional shape of the tooth-shaped protrusion perpendicular to the axis of the connecting mechanism comprises a rectangle, a fan or a trapezoid.

Furthermore, the connecting end also comprises a disc-shaped positioning mechanism arranged at one end of the connecting mechanism; the circular end face of the disc-shaped positioning mechanism is matched with the two ends of the flexible hinge, so that the positioning of the connecting end and the flexible hinge is realized.

Further, the safety positioning mechanism is a safety positioning pin;

the first connecting end and the second connecting end are respectively provided with an axial through hole which is in splicing fit with the first transmission shaft and the second transmission shaft; the connecting mechanism of the connecting end is provided with a first radial through hole, and the transmission shaft is provided with a second radial through hole; after the connecting end is in inserting fit with the transmission shaft, the safety positioning pin is simultaneously matched with the first radial through hole and the second radial through hole, and the connecting end is fixedly connected with the transmission shaft.

Further, the length of the safety positioning pin is smaller than the radial size of the inner cavity of the flexible hinge.

Furthermore, the anti-loose vibration damping coupler for the aircraft rotating component further comprises a vibration damping limiting pad, wherein the vibration damping limiting pad is annular and is sleeved on a connecting mechanism arranged at the connecting end head;

the circular end face of the positioning device arranged at the connecting end is matched with the two ends of the flexible hinge through vibration reduction limiting pads.

Further, the cross-sectional shape of the transmission shaft comprises a circle, a D shape or a straight shape.

Further, the outer diameter of the flexible hinge is less than 18mm, and the inner diameter of the flexible hinge is more than 6 mm; the length of the anti-loosening vibration-damping coupler formed after the flexible hinge is matched with the first connecting end and the second connecting end along the axial direction is less than 25 mm.

Furthermore, except the vibration-damping limiting pad, other structures in the anti-loosening vibration-damping coupler are made of metal materials.

Compared with the prior art, the invention has the following beneficial effects:

(1) the invention relates to an anti-loose vibration attenuation coupler for a rotary part of an aircraft, which is characterized in that a vibration attenuation structure of a flexible hinge is designed into a plurality of groups of annularly arranged openings, the specific size, arrangement mode and interval of the openings are determined through a plurality of tests, the anti-loose vibration attenuation coupler has radial and axial vibration attenuation functions under the condition of ensuring rigidity, and realizes the vibration attenuation in the power transmission process of equipment under complex working conditions such as severe vibration, frequent start and stop and the like;

(2) according to the anti-loose vibration reduction coupling for the rotating part of the aircraft, the flexible hinge is matched with the connecting end head through the tooth-shaped protrusion and the tooth-shaped groove, so that the torque, the angle and the rotating speed of the transmission shaft are accurately transmitted;

(3) according to the anti-loosening vibration attenuation coupler for the rotating part of the aircraft, the connecting end is fixedly connected with the transmission shaft through the safety positioning pin, so that the rigid connection between the connecting end and the transmission shaft is realized, and the problems of looseness prevention, high-speed centrifugal throwing, overlarge structural size and the like caused by the connection of screws and belts are solved;

(4) according to the anti-loosening vibration damping coupler for the rotating part of the aircraft, the vibration damping limiting pad is arranged between the flexible hinge and the connecting end, so that the axial vibration impact of the flexible hinge is relieved, the axial vibration isolation is carried out between the transmission shafts, and the anti-loosening vibration damping coupler is redundant in installation, simple in positioning and convenient to assemble and disassemble;

(5) according to the anti-loosening and vibration-damping coupler for the rotating part of the aircraft, the safety positioning pin is embedded in the inner cavity of the flexible hinge after being matched, so that the safety positioning pin is prevented from being thrown out of the coupler under the action of centrifugal force in high-speed rotation.

(6) The anti-loosening vibration attenuation coupler for the aircraft rotating part is compact in structure, free of screw connection, redundant in installation, simple in positioning and convenient to disassemble and assemble, has vibration attenuation design in the radial direction and the axial direction, achieves buffering vibration attenuation in the power transmission process of equipment under complex working conditions, and ensures high positioning accuracy, high reliability and long service life of the aircraft rotating part under high-speed rotation, frequent start and stop and complex vibration working conditions.

Drawings

FIG. 1 is an exploded view of a locking damping coupling for an aircraft rotating component;

FIG. 2 is a three-dimensional view of the structure of a looseness-proof vibration damping coupling for an aircraft rotating component; wherein fig. 2(a) is a top view of the anti-loosening and vibration damping coupling; FIG. 2(b) is a cross-sectional view taken along A-A of FIG. 2 (a); FIG. 2(c) is a cross-sectional view taken along line B-B of FIG. 2 (B);

FIG. 3 is a cross-sectional view of the overall construction of a looseness resistant vibration damping coupling for an aircraft rotating component.

Detailed Description

The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.

The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.

The traditional coupler adopts screws to fasten and connect the coupler from the radial direction or the axial direction, and is difficult to meet the requirements on vibration reduction, looseness prevention, dismounting space, structural size, positioning precision and the like.

In order to solve the problems, ensure the accurate transmission of the torque, the angle and the rotating speed of the transmission shafts at two ends of the coupler and realize the normal use of the coupler under the complex working conditions of high-speed rotation, severe vibration and the like, the invention discloses an anti-loosening and vibration-damping coupler for a rotary part of an aircraft, which comprises a flexible hinge, vibration-damping limiting pads, connecting end heads and safety positioning pins, wherein the vibration-damping limiting pads are respectively sleeved on the connecting end heads at two ends and are fixedly connected with the transmission shafts through the safety positioning pins, one end of the flexible hinge is coaxially sleeved with a cylindrical structure with tooth-shaped bulges arranged on the first connecting end head by utilizing an inner cavity, and then the other end is coaxially sleeved with the second connecting end head, so that not only the accurate transmission of the torque, the angle and the rotating speed of the transmission shafts at two ends is realized, but also the problems of large dismounting space, unreliable screw thread anti-loosening, overlarge coupler size and the like caused by the fastening of a screw and the traditional coupler and the transmission shaft are solved, the anti-loosening vibration attenuation coupling for the aircraft rotating part has the advantages of compact structure, redundant installation, simple positioning, convenient assembly and disassembly, overload protection, vibration attenuation design in the radial direction and the axial direction, buffer vibration attenuation in the power transmission process of equipment under complex working conditions, and high positioning precision, high reliability and long service life of the aircraft rotating part under the conditions of high-speed rotation, frequent start and stop and complex vibration.

Example 1

As shown in fig. 1, fig. 2(a), (b), (c) and fig. 3, the invention relates to an anti-loose vibration damping coupler for an aircraft rotating component, which comprises a flexible hinge 1, a vibration damping spacing pad 2, a connecting end 3 and a safety positioning pin 4; the connecting end 3 comprises a first connecting end 31 and a second connecting end 32 which have the same structure, and correspondingly, the number of the damping limiting pads 2 and the number of the safety positioning pins 4 are also 2.

The second connecting end 32 is sleeved with the vibration reduction limiting pad 2 and is fixedly connected with the second transmission shaft 6 through the safety positioning pin 4, one end of the flexible hinge 1 is sleeved with a coaxial fork tooth of the second connecting end 32, the coaxial fork tooth is of a cylindrical structure provided with a toothed bulge, and the safety positioning pin 4 is embedded in an inner cavity of the flexible hinge 1;

the first connecting end 31 is sleeved with the vibration reduction limiting pad 2 and is fixedly connected with the first transmission shaft 5 through the safety positioning pin 4, so that the coaxial fork teeth are sleeved with the other end of the flexible hinge 1, the safety positioning pin 4 is embedded in the inner cavity of the flexible hinge 1, and the situation that the safety positioning pin 4 is thrown out of the coupler under the action of centrifugal force in high-speed rotation is avoided.

The flexible hinge 1 is of a middle flexible hinge structure, tooth-shaped grooves arranged along the circumferential direction are symmetrically arranged at two ends of an inner cavity, the connecting end 3 is provided with tooth-shaped protrusions corresponding to the connecting end, the number of teeth is not limited, torque is transmitted through the inter-teeth, and the flexible hinge structure can buffer and damp under the working conditions of severe vibration, frequent start and stop and the like; the flexible hinge structure is provided with a plurality of groups of slit-shaped openings, each group comprises a plurality of annularly arranged slit-shaped openings, and the openings penetrate through the side wall of the cylindrical flexible hinge 1; the width of the openings (as shown in figure 1, the width is the dimension along the axial direction of the coupler) is 0.6-0.8 mm, and the openings of each group are arranged in a staggered manner; the gap between each group of gap-shaped openings along the axial direction is 1-1.2 mm, and the buffer damping effect is achieved under the condition that the rigidity is guaranteed.

One end of the connecting end 3 is a cylindrical structure which is correspondingly matched with the inner cavity of the flexible hinge 1 and is provided with a dentate bulge, and the other end of the connecting end is a waistcoat, specifically, the waistcoat is a disc with the diameter larger than that of the cylindrical structure, so that the flexible hinge 1 is prevented from being separated from the connecting end 3 along the axial direction. The center of the dentate bulge and the direction (radial direction) of the vertical axis of the transmission shaft are provided with corresponding positioning through holes, and the section shape of the dentate bulge vertical to the axial direction comprises a tooth shape, a rectangle, a fan shape or a trapezoid and the like.

The structure of damping spacing pad 2 is the ring, overlaps on connecting end 3 has the bellied cylinder structure of cusp, connects end 3 and is located between the circular terminal surface of sleeveless jacket and flexible hinge 1 terminal surface after 1 cooperation of flexible hinge, slows down 1 axial vibration of flexible hinge and strikes, carries out axial vibration isolation to the transmission shaft within a definite time, and installation redundancy, location are simple and easy dismounting, and the material is rubber, plastics or metal elastic element etc..

The structural strength of the safety positioning pin 4 can be designed according to the preset maximum transmission torque, and when the preset maximum transmission torque is reached, the safety positioning pin is sheared off, and the length of the safety positioning pin does not exceed the inner diameter of the inner cavity of the flexible hinge 1.

The section shape of the transmission shaft comprises a round shape, a D shape or a straight shape and the like, the section shape of the transmission shaft is correspondingly matched with the shape of an axial through hole of which the connecting end head 3 is used as a connecting hole, and when the section shape is the round shape, the safety positioning pin 4 can also play a role in overload protection; the diameter and the length of the transmission shaft can be different sizes, the shape can be different according to the working condition of use, and the connecting holes of the connecting end heads 3 correspondingly matched with the transmission shaft can be matched.

The flexible hinge 1 of the anti-loosening vibration-damping coupler has the outer diameter smaller than 18mm and the inner diameter larger than 6mm, the length of the coupler formed by matching the flexible hinge 1 and the connecting end 3 is within 25mm, the structure is compact, the structures except the vibration-damping limiting pad 2 are all made of metal materials, screws are not required to be installed, the angle positioning precision is within +/-0.05 degrees, and the high positioning precision, the high reliability and the long service life of an aircraft rotating part can be realized under the working conditions of high-speed rotation, frequent starting and stopping and complex vibration.

The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.

Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.