CN105443593B - A kind of drum-type linkage that can realize damping and lock function - Google Patents

Abstract

The invention relates to the field of spaceflight separation technology, in particular to a drum hinge mechanism capable of damping and locking functions. Bounce problem. It is characterized in that it includes a supporting and limiting part, a damping loading part and a locking part; wherein, the damping loading part is located inside the supporting and limiting part and is in contact with the supporting and limiting part; the locking part is located between the damping loading part and the supporting and limiting part. The right side of the positioning part is fixedly connected with the damping loading part; the supporting and limiting parts are used to connect the rocket structure and the grid wing, and at the same time limit the movement of the damping loading part and the locking part; the damping loading part is used for the rotation of the grid wing Provides damping torque; the locking part is used to lock the grid wings after they are deployed in place. The invention plays an important role in the design of the unfolding mechanism of the airfoil such as the grid wing and the rudder surface, and the design of other folding and unfolding structures.

Description

A Drum Hinge Mechanism Capable of Realizing Damping and Locking Functions

technical field

The invention relates to the field of aerospace separation technology, in particular to a drum hinge mechanism capable of realizing damping and locking functions.

Background technique

As a special form of aerodynamic surface, the grid wing is often used in the flight control of missiles and launch vehicles due to its advantages of high efficiency, light weight, and small space after folding.

Hinge connections are generally used between the grid wings and missiles or launch vehicles. When the missile or launch vehicle is stored, the grid wings are folded through hinges and attached to the outer wall of the missile or launch vehicle to save space. When the missile or launch vehicle is flying, the grid wings are rapidly unfolded around the hinges to provide control torque for the flight.

The grid wings generally rely on the flight aerodynamic force of missiles or launch vehicles to deploy. The grid wing is continuously affected by the aerodynamic force during the deployment process, and the aerodynamic force gradually increases with the increase of the deployment angle. The action of aerodynamic force makes the grid wings have a lot of kinetic energy when they are deployed in place. The moment the grid wings stop rotating, it will cause a huge impact on the structure of the missile or launch vehicle. The impact will cause great damage to the internal equipment of the missile or launch vehicle, affecting follow-up flight. At the same time, the grid wings will rebound under the huge impact after they are deployed to the structure collision stop, which is not conducive to the flight control of the grid wings to the missile or launch vehicle. The existing grid wing hinges can only provide a rotating shaft for the grid wing, and cannot solve the above problems.

Contents of the invention

The purpose of the present invention is to solve the problem that the existing grid wing hinge cannot solve the problem of excessive impact and rebound after deployment in place during the deployment process of the grid wing, and to provide an internal mechanism that can provide a gradually increasing The damping torque prevents large impact after the grid wings are deployed in place, and can lock the grid wings after the grid wings are deployed in place to prevent the grid wings from rebounding. It is a drum hinge mechanism that can realize damping and locking functions.

The present invention is achieved like this:

A drum hinge mechanism capable of realizing damping and locking functions, including a supporting and limiting component, a damping loading component, and a locking component; wherein, the damping loading component is located inside the supporting and limiting component, and is in contact with the supporting and limiting component; locking The component is located on the right side of the damping loading part and the support and limiting part, and is fixedly connected with the damping loading part; the supporting and limiting part is used to connect the rocket structure and the grid wing, while restricting the movement of the damping loading part and the locking part; the damping loading The component is used to provide damping torque for the rotation of the grid wing; the locking component is used to lock the grid wing after the grid wing is deployed in place.

The above-mentioned supporting and limiting parts include a support, a left end cover and a right end cover; the support is a cylindrical structure with a base, and there are six round holes on the base, and the support is fixedly connected with the rocket structure through the six round holes ;The inner wall of the cylindrical structure of the support is an eccentric hole structure, and two wedge-shaped inner cavities symmetrical along the center of the cylindrical structure are formed along the circumferential direction of the inner wall; Provide support; the left end cover is a ring structure as a whole, and there are installation holes evenly distributed on the ring structure, and the left end cover is fixedly connected to the left end of the support through the installation holes; the right end cover is a ring structure as a whole, divided into two rings, the outer ring is thicker than the inner ring There are mounting holes evenly distributed on the outer ring, two positioning bosses symmetrical along the center of the ring are set on the inner ring, and two positioning bosses symmetrical along the center of the ring are set on the inner ring near the positioning bosses. The positioning hole, the right end cover is fixedly connected to the right end of the support through the installation hole; the left end cover and the right end cover are used to limit the left and right movement of the damping loading part, and the right end cover is also used to limit the locking part.

The above-mentioned damping loading part includes a mandrel, a friction plate, a rotating shaft and an elastic element; the mandrel is a cylindrical structure, and two grooves are arranged symmetrically along the center of the cylinder axis on the cylindrical surface, and each groove has a There is a pin hole, and the pin holes are arranged along the length of the cylindrical surface. The bottom of each groove has a deep groove symmetrically distributed along the center of the cylinder; the main part of the mandrel is located inside the eccentric hole of the support and is coaxial with the eccentric hole; There is a square boss at the left and right ends of the main body of the mandrel, both of which protrude out of the eccentric hole; the boss at the left end of the mandrel is fixedly connected to the square groove of the flange, and the grid wing is fixedly connected to the flange On the top, the grid wing drives the mandrel to rotate through the flange; the boss at the right end of the mandrel is fixedly connected to the locking part; the friction plate is an arc-shaped structure, and a straight edge of the arc-shaped structure is provided with a length along the arc-shaped structure. There are two through holes in the direction; there are two friction plates, which are respectively fixed on the pin holes of the mandrel through two rotating shafts. The friction plates are movably connected with the mandrel and rotate around the rotating shaft; The inner walls of the cylindrical structure are in contact; the friction plate is used to provide the frictional resistance to the rotation of the mandrel; there are two elastic elements, which are respectively installed in the two deep grooves of the mandrel, one end of the elastic element is in contact with the bottom of the deep groove, and the other One end is in contact with the inner arc surface of the friction plate; the elastic element is used to provide the positive pressure of the friction plate to load the support.

The elastic elements as described above are realized with rubber or springs.

The above-mentioned locking part includes a positioning block, a positioning pin and a spring; the center of the positioning block is circular, and a section of rectangular structure protrudes from the upper and lower ends. The length of the positioning block matches the inner diameter of the outer ring of the right end cover, and the left side of the positioning block The side end surface is in contact with the inner ring surface of the right end cover; a rectangular groove is opened in the center of the positioning block, and the positioning block is fixedly connected with the boss at the right end of the mandrel through the rectangular groove; each of the two rectangular structures of the positioning block is provided with a deep Holes, the distance between the centers of the two deep holes is equal to the distance between the centers of the two positioning holes on the right end cover, and the diameter of the deep holes is equal to the diameter of the positioning holes; there are two positioning pins and two springs, one positioning pin and one spring are a set , There are two groups, each group is installed in two deep holes, the spring is located at the bottom of the deep hole, in a compressed state, the positioning pin is located above the spring, one end of the positioning pin is in contact with the spring, and the other end is in contact with the inner ring of the right end cover contact; the positioning block is used to fix the positioning pin and the spring; the positioning block, the positioning pin and the spring (10) work together to realize the rotation positioning of the mandrel.

The beneficial effects of the present invention are:

The invention includes supporting and limiting parts, damping loading parts and locking parts, which can not only provide gradually increasing damping torque for the rotation of the grid wings, prevent the rotation speed of the grid wings from being too high, and effectively reduce The resulting impact can avoid damage to instruments and equipment, and can quickly lock the grid wing after the grid wing is deployed in place, so that the grid wing does not rebound, thereby ensuring the flight control ability of the grid wing to the rocket. The elastic element is adjusted to adjust the damping torque of the grid wing, so as to meet the requirements of grid wing deployment under different aerodynamic forces. The invention has an important positive effect on the design of the unfolding mechanism of the airfoil such as the lattice wing and the rudder surface, and the design of other folding and unfolding structures.

Description of drawings

Fig. 1 is a structural schematic diagram of a drum hinge mechanism capable of realizing damping and locking functions of the present invention;

Fig. 2 is a structural principle diagram of the first working state of the damping loading part of the present invention;

Fig. 3 is a structural principle diagram of the second working state of the damping loading part of the present invention;

Fig. 4 is a structural schematic diagram of the locking part of the present invention.

Among them: 1. Support, 2. Mandrel, 3. Friction plate, 4. Rotating shaft, 5. Elastic element, 6. Left end cover, 7. Right end cover, 8. Positioning block, 9. Positioning pin, 10. Spring, 11. Rocket structure, 12. Grid wing, 13. Flange.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

A drum type hinge mechanism capable of realizing damping and locking functions, including a supporting and limiting part, a damping loading part and a locking part. Wherein, the damping loading part is located inside the supporting and limiting part, and is in contact with the supporting and limiting part; the locking part is located on the right side of the damping loading part and the supporting and limiting part, and is fixedly connected with the damping loading part. The supporting and limiting parts are used to connect the rocket structure 11 and the grid wing 12, while limiting the movement of the damping loading part and the locking part; the damping loading part is used to provide damping torque for the rotation of the grid wing 12; The grid wing 12 is locked after being unfolded into place.

As shown in FIG. 1 , the supporting and limiting components include a support 1 , a left end cover 6 and a right end cover 7 . The support 1 is a cylindrical structure with a base, and there are six round holes on the base, and the support 1 is fixedly connected with the rocket structure 11 through the six round holes; the inner wall of the cylindrical structure of the support 1 is an eccentric hole structure, along the inner wall Two wedge-shaped inner cavities symmetrical along the center of the cylindrical structure are formed in the circumferential direction. The support 1 is used to connect the rocket structure 11 and the grid wing 12, and provide support for the rotation of the damping loading part. The left end cover 6 has a ring structure as a whole, and mounting holes are evenly distributed on the ring structure, and the left end cover 6 is fixedly connected to the left end of the support 1 through the installation holes. The right end cover 7 has a ring structure as a whole, which is divided into inner and outer rings. The thickness of the outer ring is greater than that of the inner ring. Mounting holes are uniformly distributed on the outer ring, and two positioning bosses symmetrical along the center of the ring are arranged on the inner ring. Two positioning holes symmetrical along the center of the ring are provided on the inner ring close to the positioning boss, and the right end cover 7 is fixedly connected to the right end of the support 1 through the mounting holes. The left end cover 6 and the right end cover 7 are jointly used to limit the left and right movement of the damping loading part, and the right end cover 7 is also used to limit the locking part.

As shown in FIG. 1 , FIG. 2 and FIG. 3 , the damping loading component includes a mandrel 2 , a friction plate 3 , a rotating shaft 4 and an elastic element 5 . The mandrel 2 is a cylindrical structure, and there are two grooves distributed symmetrically along the center of the cylinder axis on the cylindrical surface. There is a pin hole in each groove, and the pin holes are arranged along the length direction of the cylindrical surface. Each bottom has a deep groove distributed symmetrically along the center of the cylinder. The main body of the mandrel 2 is located inside the eccentric hole of the support 1 and is coaxial with the eccentric hole. The left and right ends of the main body of the mandrel 2 respectively have a square boss, and both bosses protrude from the outside of the eccentric hole. The boss at the left end of the mandrel 2 is fixedly connected to the square groove of the flange 13, the grid wing 12 is fixedly connected to the flange 13, and the grid wing 12 drives the mandrel 2 to rotate through the flange 13; the protrusion at the right end of the mandrel 2 The platform is fixedly connected with the locking part. The friction plate 3 is an arcuate structure, and a through hole along the length direction of the arcuate structure is provided on the straight side of the arcuate structure. There are two friction plates 3 , which are respectively fixed on the pin holes of the mandrel 2 through two rotating shafts 4 . The friction plates 3 are movably connected with the mandrel 2 and rotate around the rotating shaft 4 . The outer arc surface of the friction plate 3 is in contact with the inner wall of the cylindrical structure of the support 1 . The friction plate 3 is used to provide frictional resistance to the rotation of the mandrel 2 . There are two elastic elements 5, which are respectively installed in two deep grooves of the mandrel 2. One end of the elastic element 5 is in contact with the bottom surface of the deep groove, and the other end is in contact with the inner arc surface of the friction plate 3. Elastic element 5 adopts rubber or spring to realize. The elastic element 5 is used to provide a positive pressure for the friction plate 3 to load the bearing 1 .

As shown in FIG. 4 , the locking component includes a positioning block 8 , a positioning pin 9 and a spring 10 . The center of the positioning block 8 is circular, and a section of rectangular structure is protruded from the upper and lower ends respectively. touch. The center of the positioning block 8 has a rectangular groove, and the positioning block 8 is fixedly connected with the boss at the right end of the mandrel 2 through the rectangular groove. Two sections of rectangular structures of positioning block 8 are respectively provided with a deep hole, and the distance of the center of circle of two deep holes is equal to the distance of the center of circle of two positioning holes of right end cover 7, and the diameter of deep hole is equal to the diameter of positioning hole. There are two locating pins 9 and two springs 10 each. A locating pin 9 and a spring 10 form a group. There are two groups in total. Each group is installed in two deep holes respectively. The spring 10 is located at the bottom of the deep hole and is in a compressed state. The pin 9 is positioned above the spring 10 , and one end of the positioning pin 9 is in contact with the spring, and the other end is in contact with the inner ring of the right end cap 7 . The positioning block 8 is used for fixing the positioning pin 9 and the spring 10 . The positioning block 8, the positioning pin 9 and the spring 10 work together to realize the rotation positioning of the mandrel 2.

The working principle of the present invention is as follows:

In the initial state, the grid wing 12 is closely attached to the rocket structure 11 before being deployed. After the rocket is launched, the grid wing 12 starts to unfold under the action of aerodynamic force, the grid wing 12 drives the mandrel 2 to rotate, and the mandrel 2 drives the two friction plates 3 to rotate. During the rotation process, the friction plate 3 swings around the two rotating shafts 4 to the inner side of the mandrel 2 under the action of the inner wall of the support 1, and the two friction plates 3 squeeze the elastic element 5 during the swing process, causing the elastic element 5 to elastically deform and produce The radial elastic force generates circumferential friction force between the friction plate 3 and the inner wall of the support 1 . The frictional force acting on the mandrel 2 can generate a frictional moment opposite to the direction of rotation of the mandrel 2 to prevent the mandrel 2 from rotating. As the grid wing 12 drives the mandrel 2 to increase the rotation angle, the contact area between the friction plate 3 and the inner wall of the support 1 gradually increases, the elastic deformation of the elastic element 5 gradually increases, and the radial elastic force generated gradually increases, thus The friction force between the friction plate 3 and the support 1 is gradually increased to limit the rotation of the mandrel 2 . When the grid wing 12 drives the mandrel 2 to rotate in place, the positioning block 8 installed at the end of the mandrel 2 contacts the two positioning bosses on the right end cover 7 to prevent the mandrel 2 from continuing to rotate, thereby stopping the grid wing 12 turn. Before the mandrel 2 rotates in place, the two positioning pins 9 installed in the positioning block 8 are always in sliding contact with the right end cover 7, so that the compression spring 10 is in a compressed state. When the mandrel 2 is rotated in place, the grid wings 12 are fully unfolded, and the two positioning pins 9 pop out under the action of the spring 10, and fall into the two positioning holes of the right end cover 7, so that the mandrel 2 and the support 1 There is no longer any rotation between them, so as to realize the positioning effect on the deployed lattice wings 12 .

The present invention includes supporting and limiting parts, damping loading parts and locking parts, which can not only provide gradually increasing damping torque for the rotation of the grid wing 12, reduce the rotation speed of the grid wing 12, and effectively reduce the deployment of the grid wing 12 in place The final impact can avoid damage to the instrument and equipment, and can quickly lock the grid wing 12 after the grid wing 12 is deployed in place, so that the grid wing 12 does not rebound, thereby ensuring the flight control ability of the grid wing 12 to the rocket , the damping torque of the grid wing 12 can also be adjusted by simply adjusting the elastic element 5, so as to meet the requirements for the grid wing 12 to expand under different aerodynamic forces. The invention has positive effects on the design of the grid wing 12 and other airfoil and rudder surface deployment mechanisms, as well as other folding and deployment structures.

Claims (2)

1. a kind of drum-type linkage that can realize damping and lock function, it is characterised in that：It include support and limiting component, Damp loading component and locking member；Wherein, damping loading component is located inside support and limiting component, with support and limiting section Part contacts；Locking member is located at damping loading component and the right side of support and limiting component, is fixedly connected with damping loading component； Support and limiting component limit damping loading component and locking member for connecting rocket structure (11) and lattice fin (12) Movement；Damping loading component is used to provide damping torque for the rotation of lattice fin (12)；Locking member is used in lattice fin (12) lattice fin (12) is locked after expanding in place；

The support and limiting component includes bearing (1), left end cap (6) and right end cap (7)；Bearing (1) is with pedestal Tubular structure, there are six circular holes, bearing (1) to be fixedly connected with rocket structure (11) by six circular holes on pedestal；Bearing (1) cylinder The inner wall of shape structure is eccentric pore structure, along being upwardly formed two inner wall week along the centrosymmetric wedge-shaped inner cavity of tubular structure；Branch Seat (1) provides support for connecting rocket structure (11) and lattice fin (12), and for the rotation for damping loading component；Left end cap (6) generally loop configuration, is evenly equipped with mounting hole, left end cap (6) is fixedly connected on bearing by mounting hole in loop configuration (1) left end；Right end cap (7) generally loop configuration is divided into inside loop and outside loop, and outer ring thickness is more than inner ring thicknesses, on outer shroud It is furnished with mounting hole, along the symmetrical positioning convex platform of circle ring center there are two settings in inner ring, close to positioning convex platform in inner ring There are two along the symmetrical location hole of circle ring center, right end cap (7) is fixedly connected on bearing (1) right side by mounting hole for position setting End；Left end cap (6) and right end cap (7) are provided commonly for the side-to-side movement of limitation damping loading component, and right end cap (7) is additionally operable to lock Determine component and plays position-limiting action；

The damping loading component includes mandrel (2), friction plate (3), shaft (4) and elastic element (5)；Mandrel (2) is circle Column body structure is opened on cylindrical surface there are two the groove that be distributed along cylinder axis central symmetry, in each groove respectively there are one Pin hole, pin hole arrange that each bottom portion of groove is respectively opened there are one along the symmetrical deep trouth of cylindrical center along cylindrical surface length direction； Mandrel (2) main part is located inside the eccentric orfice of bearing (1), coaxial with eccentric orfice；The left and right ends of mandrel (2) main part Square boss there are one each, two boss stretch out outside eccentric orfice；The boss of mandrel (2) left end is rectangular recessed with flange (13) Slot is fixedly connected, and lattice fin (12) is fixedly connected on flange (13), and lattice fin (12) is turned by flange (13) band moving mandrel (2) It is dynamic；The boss of mandrel (2) right end is fixedly connected with locking member；Friction plate (3) is arc surfaced structure, in the straight of arc surfaced structure There are one the through-holes on globoidal structure length direction for setting on side；There are two friction plate (3) is total, pass through two shafts respectively (4) it is fixed on the pin hole of mandrel (2), friction plate (3) is flexibly connected with mandrel (2), is rotated centered on shaft (4)；Friction The exterior arc surface of piece (3) is in contact with the inner wall of bearing (1) tubular structure；Friction plate (3) is used to provide rubbing for mandrel (2) rotation Wipe resistance；Elastic element (5) altogether there are two, be separately mounted in two deep trouths of mandrel (2), one end of elastic element (5) with Deep trouth bottom surface is in contact, and the other end is contacted with the inner arc surface of friction plate (3)；Elastic element (5) is right for providing friction plate (3) The normal pressure of bearing (1) load；

The locking member includes locating piece (8), positioning pin (9) and spring (10)；Locating piece (8) center is circle, up and down One section of long square structure is respectively stretched out at both ends, and the length and the internal diameter of right end cap (7) outer shroud of locating piece (8) match, locating piece (8) Left end face be in contact with the inner ring surface of right end cap (7)；The center of locating piece (8) is opened there are one rectangular slot, locating piece (8) it is fixedly connected with the boss of mandrel (2) right end by rectangular slot；Respectively it is arranged on two sections of long square structures of locating piece (8) It is equal at a distance from (7) two location hole centers of circle of distance and right end cap in two deep hole centers of circle there are one deep hole, the diameter of deep hole and The diameter of location hole is equal；There are two positioning pin (9) and spring (10) are each, a positioning pin (9) and a spring (10) are one Group shares two groups, and every group is respectively installed in two deep holes, and spring (10) is located at deep hole bottom, is in compressive state, positioning pin (9) it is located at the top of spring (10), positioning pin (9) one end is touched with spring interface, and the other end connects with the inner ring of right end cap (7) It touches；Locating piece (8) is used for fixed locating stud (9) and spring (10)；Locating piece (8), positioning pin (9) and spring (10) are made jointly With rotational positioning of the realization to mandrel (2).

2. the drum-type linkage according to claim 1 that can realize damping and lock function, it is characterised in that：Described Elastic element (5) is realized using rubber or spring.