CN105443593A - Drum type hinge mechanism with damping and locking functions - Google Patents
Drum type hinge mechanism with damping and locking functions Download PDFInfo
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- CN105443593A CN105443593A CN201410512705.1A CN201410512705A CN105443593A CN 105443593 A CN105443593 A CN 105443593A CN 201410512705 A CN201410512705 A CN 201410512705A CN 105443593 A CN105443593 A CN 105443593A
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Abstract
The invention relates to the technical field of spaceflight separation, in particular to a drum type hinge mechanism with damping and locking functions. The drum type hinge mechanism aims at solving the problems that according to an existing grid fin hinge, impact is too intense when grid fins are unfolded in place in the unfolding process, and the grid fins rebound after being unfolded in place. The drum type hinge mechanism is characterized in that the mechanism comprises a supporting and limiting part, a damping loading part and a locking part, wherein the damping loading part is located in the supporting and limiting part and makes contact with the supporting and limiting part; the locking part is located at 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 part is used for connecting a rocket structure and grid fins and limiting movement of the damping loading part and the locking part at the same time; the damping loading part is used for providing damping torque for rotation of the grid fins; the locking part is used for locking the grid fins after the grid fins are unfolded in place. The drum type hinge mechanism plays an important role in design of airfoil and control-surface unfolding mechanisms of the grid fins and design of other unfolding structures.
Description
Technical field
The present invention relates to space flight separation technology field, be specifically related to a kind of drum-type linkage that can realize damping and lock function.
Background technique
Lattice fin is as a kind of pneumatic special form, and the flight that the advantage such as to take up room after, quality high with its efficiency is light, folding little is usually used in guided missile and carrier rocket controls.
Generally chain connection is adopted between lattice fin and guided missile or carrier rocket.When guided missile or carrier rocket storage, lattice fin is by hinge folding and be adjacent to the outer wall of guided missile or carrier rocket, to save space.When guided missile or carrier rocket flight, lattice fin launches rapidly around hinge, for flight provides control moment.
Lattice fin generally relies on the flight aerodynamic force of guided missile or carrier rocket to launch.By the continuous action of aerodynamic force in lattice fin expansion process, and aerodynamic force increases along with expanded angle and increases gradually.The effect of aerodynamic force makes lattice fin launch to have very large kinetic energy when putting in place, and lattice fin stops operating can cause huge impact to guided missile or carrier rocket structure instantaneously, and this impact causes larger infringement to guided missile or carrier rocket interior instrument equipment, affects subsequent flights.Lattice fin is deployed into be positioned at after structural collision stops and can produces bounce-back under enormous impact simultaneously, and this is unfavorable for that the flight of lattice fin to guided missile or carrier rocket controls.Existing lattice fin hinge only can provide rotating shaft for lattice fin, cannot solve the problem.
Summary of the invention
The object of the invention is to solve existing lattice fin hinge cannot solve in lattice fin expansion process exist expansion put in place impact excessive and expansion put in place after bounce problem, there is provided a kind of and can provide at lattice fin expansion process the damping torque increased gradually by internal mechanism, greater impact is produced after preventing lattice fin expansion from putting in place, and lattice fin can be locked, the drum-type linkage that can realize damping and lock function preventing lattice fin from rebounding after lattice fin expansion puts in place.
The present invention is achieved in that
A drum-type linkage for damping and lock function can be realized, comprise support and limit position part, damping loading component and Lock Part; Wherein, damping loading component is positioned at support and limit position part is inner, contacts with support and limit position part; Lock Part is positioned at the right side of damping loading component and support and limit position part, is fixedly connected with damping loading component; Support and limit position part for connecting rocket structure and lattice fin, with the motion of limit damping loading component and Lock Part; Damping loading component is used for providing damping torque for the rotation of lattice fin; Lock Part is used for locking lattice fin after lattice fin expansion puts in place.
Support as above and limit position part comprise bearing, left end cap and right end cap; Bearing is the tubular structure with base, base has six circular holes, and bearing is fixedly connected with rocket structure by six circular holes; The inwall of bearing tubular structure is eccentric opening structure, along formation in inwall circumference two along the centrosymmetric wedge shape inner chamber of tubular structure; Bearing for connecting rocket structure and lattice fin, and provides support for the rotation of damping loading component; Left end cap entirety is loop configuration, and loop configuration is evenly equipped with mounting hole, and left end cap is fixedly connected on bearing left end by mounting hole; Right end cap entirety is loop configuration, be divided into inside loop and outside loop, outer ring thickness is greater than inner ring thicknesses, outer shroud is evenly equipped with mounting hole, inner ring is provided with two positioning boss along circle ring center's symmetry, position near positioning boss in inner ring is provided with two positioning holes along circle ring center's symmetry, and right end cap is fixedly connected on bearing right-hand member by mounting hole; Left end cap and right end cap are jointly for limiting the side-to-side movement of damping loading component, and right end cap is also for playing position-limiting action to Lock Part.
Damping loading component as above comprises mandrel, friction plate, rotating shaft and elastic element; Mandrel is cylindrical structure, cylndrical surface has two grooves along the distribution of cylinder axis Central Symmetry, respectively have a pin-and-hole in each groove, pin-and-hole is arranged along cylndrical surface length direction, and each bottom portion of groove respectively has one along the symmetrical deep trouth of cylindrical center; The eccentric opening that mandrel main body is positioned at bearing is inner, coaxial with eccentric opening; Respectively there is a square boss at the two ends, left and right of mandrel main body, and two boss all stretch out eccentric opening outside; The boss of mandrel left end is fixedly connected with the square groove of flange, and lattice fin is fixedly connected on flange, and lattice fin is rotated by flange band moving mandrel; The boss of mandrel right-hand member is fixedly connected with Lock Part; Friction plate is arc surfaced structure, the straight flange of arc surfaced structure is provided with one along the through hole on globoidal structure length direction; Friction plate has two, and be fixed on the pin-and-hole of mandrel respectively by two rotating shafts, friction plate is flexibly connected with mandrel, rotates centered by rotating shaft; The exterior arc surface of friction plate contacts with the inwall of bearing tubular structure; The surface friction drag of friction plate for providing mandrel to rotate; Elastic element has two, and be arranged in two deep trouths of mandrel respectively, one end of elastic element contacts with deep trouth bottom surface, and the other end contacts with the inner arc surface of friction plate; The positive pressure that elastic element loads bearing for providing friction plate.
Elastic element as above adopts rubber or spring to realize.
Lock Part as above comprises positioning block, locating stud and spring; Positioning block center is circular, and segment length's square structure is respectively stretched out at upper and lower two ends, and the length of positioning block and the internal diameter of right end cap outer shroud match, and the left end face of positioning block contacts with the inner ring surface of right end cap; The center of positioning block has a rectangular slot, and positioning block is fixedly connected with by the boss of rectangular slot with mandrel right-hand member; Two segment length's square structures of positioning block are respectively provided with a deep hole, and the distance in distance and right end cap two positioning hole centers of circle in two deep hole centers of circle is equal, the diameter of deep hole and the equal diameters of positioning hole; Locating stud and spring respectively have two, a locating stud and a spring are one group, have two groups, often group is respectively installed in two deep holes, spring is positioned at deep hole bottom, is in compressive state, and locating stud is positioned at the top of spring, locating stud one end and spring interface touch, and the other end contacts with the inner ring of right end cap; Positioning block is used for fixed locating stud and spring; Positioning block, locating stud and spring (10) acting in conjunction, realize the rotating position to mandrel.
The invention has the beneficial effects as follows:
The present invention includes support and limit position part, damping loading component and Lock Part, not only can provide for lattice fin rotates the damping torque increased gradually, prevent lattice fin rotational velocity excessive, effectively reduce the impact produced after lattice fin expansion puts in place, avoid causing damage to instrument and equipment, and after lattice fin expansion puts in place, lattice fin can be locked rapidly, lattice fin is not rebounded, thus ensure that lattice fin is to the flight control ability of rocket, also by simply adjusting the damping torque of elastic element adjustment lattice fin, thus the requirement that under tackling different aerodynamic force, lattice fin launches.The present invention designs the aerofoils such as lattice fin and rudder face development mechanism and other folding and expanding structural design has important positive role.
Accompanying drawing explanation
Fig. 1 is a kind of structural representation that can realize the drum-type linkage of damping and lock function of the present invention;
Fig. 2 is the first working state structure schematic diagram of damping loading component of the present invention;
Fig. 3 is the second working state structure schematic diagram of damping loading component of the present invention;
Fig. 4 is Lock Part structural representation of the present invention.
Wherein: 1. bearing, 2. mandrel, 3. friction plate, 4. rotating shaft, 5. elastic element, 6. left end cap, 7. right end cap, 8. positioning block, 9. locating stud, 10. spring, 11. rocket structures, 12. lattice fins, 13. flanges.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described further.
A drum-type linkage for damping and lock function can be realized, comprise support and limit position part, damping loading component and Lock Part.Wherein, damping loading component is positioned at support and limit position part is inner, contacts with support and limit position part; Lock Part is positioned at the right side of damping loading component and support and limit position part, is fixedly connected with damping loading component.Support and limit position part for connecting rocket structure 11 and lattice fin 12, with the motion of limit damping loading component and Lock Part; Damping loading component is used for providing damping torque for the rotation of lattice fin 12; Lock Part is used for locking lattice fin 12 after lattice fin 12 expansion puts in place.
As shown in Figure 1, support and limit position part comprise bearing 1, left end cap 6 and right end cap 7.Bearing 1 is the tubular structure with base, base has six circular holes, and bearing 1 is fixedly connected with rocket structure 11 by six circular holes; The inwall of bearing 1 tubular structure is eccentric opening structure, along formation in inwall circumference two along the centrosymmetric wedge shape inner chamber of tubular structure.Bearing 1 for connecting rocket structure 11 and lattice fin 12, and provides support for the rotation of damping loading component.Left end cap 6 entirety is loop configuration, and loop configuration is evenly equipped with mounting hole, and left end cap 6 is fixedly connected on bearing 1 left end by mounting hole.Right end cap 7 entirety is loop configuration, be divided into inside loop and outside loop, outer ring thickness is greater than inner ring thicknesses, outer shroud is evenly equipped with mounting hole, inner ring is provided with two positioning boss along circle ring center's symmetry, position near positioning boss in inner ring is provided with two positioning holes along circle ring center's symmetry, and right end cap 7 is fixedly connected on bearing 1 right-hand member by mounting hole.Left end cap 6 and right end cap 7 are jointly for limiting the side-to-side movement of damping loading component, and right end cap 7 is also for playing position-limiting action to Lock Part.
As shown in Figure 1, Figure 2 and Figure 3, damping loading component comprises mandrel 2, friction plate 3, rotating shaft 4 and elastic element 5.Mandrel 2 is cylindrical structure, cylndrical surface has two grooves along the distribution of cylinder axis Central Symmetry, respectively have a pin-and-hole in each groove, pin-and-hole is arranged along cylndrical surface length direction, and each bottom portion of groove respectively has one along the symmetrical deep trouth of cylindrical center.The eccentric opening that mandrel 2 main body is positioned at bearing 1 is inner, coaxial with eccentric opening.Respectively there is a square boss at the two ends, left and right of mandrel 2 main body, and two boss all stretch out eccentric opening outside.The boss of mandrel 2 left end is fixedly connected with the square groove of flange 13, and lattice fin 12 is fixedly connected on flange 13, and lattice fin 12 is with moving mandrel 2 to rotate by flange 13; The boss of mandrel 2 right-hand member is fixedly connected with Lock Part.Friction plate 3 is arc surfaced structure, the straight flange of arc surfaced structure is provided with one along the through hole on globoidal structure length direction.Friction plate 3 has two, and be fixed on the pin-and-hole of mandrel 2 respectively by two rotating shafts 4, friction plate 3 is flexibly connected with mandrel 2, rotates centered by rotating shaft 4.The exterior arc surface of friction plate 3 contacts with the inwall of bearing 1 tubular structure.The surface friction drag that friction plate 3 rotates for providing mandrel 2.Elastic element 5 has two, and be arranged in two deep trouths of mandrel 2 respectively, one end of elastic element 5 contacts with deep trouth bottom surface, and the other end contacts with the inner arc surface of friction plate 3.Elastic element 5 adopts rubber or spring to realize.Elastic element 5 is for providing the friction plate positive pressure that 3 pairs of bearings 1 load.
As shown in Figure 4, Lock Part comprises positioning block 8, locating stud 9 and spring 10.Positioning block 8 center is circular, and segment length's square structure is respectively stretched out at upper and lower two ends, and the length of positioning block 8 and the internal diameter of right end cap 7 outer shroud match, and the left end face of positioning block 8 contacts with the inner ring surface of right end cap 7.The center of positioning block 8 has a rectangular slot, and positioning block 8 is fixedly connected with by the boss of rectangular slot with mandrel 2 right-hand member.Two segment length's square structures of positioning block 8 are respectively provided with a deep hole, and the distance in distance and right end cap 7 two positioning hole centers of circle in two deep hole centers of circle is equal, the diameter of deep hole and the equal diameters of positioning hole.Locating stud 9 and spring 10 respectively have two, a locating stud 9 and a spring 10 are one group, have two groups, often group is respectively installed in two deep holes, spring 10 is positioned at deep hole bottom, is in compressive state, and locating stud 9 is positioned at the top of spring 10, locating stud 9 one end and spring interface touch, and the other end contacts with the inner ring of right end cap 7.Positioning block 8 is for fixed locating stud 9 and spring 10.Positioning block 8, locating stud 9 and spring 10 acting in conjunction, realize the rotating position to mandrel 2.
Working principle of the present invention is as follows:
Under original state, be adjacent to rocket structure 11 before lattice fin 12 launches.After rocket launching, lattice fin 12 starts to launch under Aerodynamic force action, and lattice fin 12 is with moving mandrel 2 to rotate, and mandrel 2 drives two friction plates 3 to rotate.In rotation process, friction plate 3 under the effect of bearing 1 inwall around two rotating shafts 4 to side oscillation in mandrel 2, elastic element 5 is extruded in two panels friction plate 3 swing process, make elastic element 5 that resiliently deformable occur and produce radial elastic power, thus produce circumferential frictional force between friction plate 3 and bearing 1 inwall.This frictional force acts on mandrel 2 can produce the friction torque with mandrel 2 direction of rotation, stops the rotation of mandrel 2.Along with lattice fin 12 is with moving mandrel 2 corner to increase, area of contact between friction plate 3 and bearing 1 inwall increases gradually, the resiliently deformable of elastic element 5 increases gradually, the radial elastic power produced increases gradually, thus the frictional force between friction plate 3 and bearing 1 is increased gradually, the rotation of restriction mandrel 2.After lattice fin 12 is with moving mandrel 2 to be rotated in place, the positioning block 8 being arranged on mandrel 2 end contacts with the positioning boss of two on right end cap 7, stops mandrel 2 to be rotated further, thus lattice fin 12 is stopped operating.Before mandrel 2 is rotated in place, be arranged on two locating studs 9 in positioning block 8 always with right end cap 7 sliding contact, make stage clip 10 be in compressive state.After mandrel 2 is rotated in place, lattice fin 12 launches completely, and two locating studs 9 outwards eject under the effect of spring 10, falls into two positioning holes of right end cap 7, make no longer to rotate between mandrel 2 and bearing 1, thus realize the positioning action of the lattice fin 12 after to expansion.
The present invention includes support and limit position part, damping loading component and Lock Part, not only can provide for lattice fin 12 rotates the damping torque increased gradually, reduce lattice fin 12 rotational velocity, effectively reduce the impact produced after lattice fin 12 expansion puts in place, avoid causing damage to instrument and equipment, and after lattice fin 12 expansion puts in place, lattice fin 12 can be locked rapidly, lattice fin 12 is not rebounded, thus ensure the flight control ability of lattice fin 12 pairs of rockets, the damping torque of lattice fin 12 is also adjusted by simply adjusting elastic element 5, thus the requirement that under tackling different aerodynamic force, lattice fin 12 launches.The present invention designs lattice fin 12 aerofoil such as grade and rudder face development mechanism and other folding and expanding structural design has positive role.
Claims (5)
1. can realize a drum-type linkage for damping and lock function, it is characterized in that: it comprises support and limit position part, damping loading component and Lock Part; Wherein, damping loading component is positioned at support and limit position part is inner, contacts with support and limit position part; Lock Part is positioned at the right side of damping loading component and support and limit position part, is fixedly connected with damping loading component; Support and limit position part for connecting rocket structure (11) and lattice fin (12), with the motion of limit damping loading component and Lock Part; Damping loading component is used for for the rotation of lattice fin (12) provides damping torque; Lock Part is used for locking lattice fin (12) after lattice fin (12) expansion puts in place.
2. the drum-type linkage that can realize damping and lock function according to claim 1, is characterized in that: described support and limit position part comprise bearing (1), left end cap (6) and right end cap (7); Bearing (1) is the tubular structure with base, base has six circular holes, and bearing (1) is fixedly connected with rocket structure (11) by six circular holes; The inwall of bearing (1) tubular structure is eccentric opening structure, along formation in inwall circumference two along the centrosymmetric wedge shape inner chamber of tubular structure; Bearing (1) for connecting rocket structure (11) and lattice fin (12), and provides support for the rotation of damping loading component; Left end cap (6) entirety is loop configuration, and loop configuration is evenly equipped with mounting hole, and left end cap (6) is fixedly connected on bearing (1) left end by mounting hole; Right end cap (7) entirety is loop configuration, be divided into inside loop and outside loop, outer ring thickness is greater than inner ring thicknesses, outer shroud is evenly equipped with mounting hole, inner ring is provided with two positioning boss along circle ring center's symmetry, position near positioning boss in inner ring is provided with two positioning holes along circle ring center's symmetry, and right end cap (7) is fixedly connected on bearing (1) right-hand member by mounting hole; Left end cap (6) and right end cap (7) are jointly for limiting the side-to-side movement of damping loading component, and right end cap (7) is also for playing position-limiting action to Lock Part.
3. the drum-type linkage that can realize damping and lock function according to claim 1, is characterized in that: described damping loading component comprises mandrel (2), friction plate (3), rotating shaft (4) and elastic element (5); Mandrel (2) is cylindrical structure, cylndrical surface has two grooves along the distribution of cylinder axis Central Symmetry, respectively have a pin-and-hole in each groove, pin-and-hole is arranged along cylndrical surface length direction, and each bottom portion of groove respectively has one along the symmetrical deep trouth of cylindrical center; The eccentric opening that mandrel (2) main body is positioned at bearing (1) is inner, coaxial with eccentric opening; Respectively there is a square boss at the two ends, left and right of mandrel (2) main body, and two boss all stretch out eccentric opening outside; The boss of mandrel (2) left end is fixedly connected with the square groove of flange (13), lattice fin (12) is fixedly connected on flange (13), and lattice fin (12) is rotated by flange (13) band moving mandrel (2); The boss of mandrel (2) right-hand member is fixedly connected with Lock Part; Friction plate (3) is arc surfaced structure, the straight flange of arc surfaced structure is provided with one along the through hole on globoidal structure length direction; Friction plate (3) has two, be fixed on the pin-and-hole of mandrel (2) respectively by two rotating shafts (4), friction plate (3) is flexibly connected with mandrel (2), rotates centered by rotating shaft (4); The exterior arc surface of friction plate (3) contacts with the inwall of bearing (1) tubular structure; Friction plate (3) is for providing the mandrel surface friction drag that (2) rotate; Elastic element (5) has two, and be arranged in two deep trouths of mandrel (2) respectively, one end of elastic element (5) contacts with deep trouth bottom surface, and the other end contacts with the inner arc surface of friction plate (3); The positive pressure that elastic element (5) loads bearing (1) for providing friction plate (3).
4. the drum-type linkage that can realize damping and lock function according to claim 3, is characterized in that: described elastic element (5) adopts rubber or spring to realize.
5. the drum-type linkage that can realize damping and lock function according to claim 1, is characterized in that: described Lock Part comprises positioning block (8), locating stud (9) and spring (10); Positioning block (8) center is circular, segment length's square structure is respectively stretched out at upper and lower two ends, the length of positioning block (8) and the internal diameter of right end cap (7) outer shroud match, and the left end face of positioning block (8) contacts with the inner ring surface of right end cap (7); The center of positioning block (8) has a rectangular slot, and positioning block (8) is fixedly connected with by the boss of rectangular slot with mandrel (2) right-hand member; Two segment length's square structures of positioning block (8) are respectively provided with a deep hole, and the distance in distance and right end cap (7) two positioning hole centers of circle in two deep hole centers of circle is equal, the diameter of deep hole and the equal diameters of positioning hole; Locating stud (9) and spring (10) respectively have two, a locating stud (9) and a spring (10) are one group, have two groups, often group is respectively installed in two deep holes, spring (10) is positioned at deep hole bottom, is in compressive state, and locating stud (9) is positioned at the top of spring (10), locating stud (9) one end and spring interface touch, and the other end contacts with the inner ring of right end cap (7); Positioning block (8) is for fixed locating stud (9) and spring (10); Positioning block (8), locating stud (9) and spring (10) acting in conjunction, realize the rotating position to mandrel (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410512705.1A CN105443593B (en) | 2014-09-29 | 2014-09-29 | A kind of drum-type linkage that can realize damping and lock function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410512705.1A CN105443593B (en) | 2014-09-29 | 2014-09-29 | A kind of drum-type linkage that can realize damping and lock function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105443593A true CN105443593A (en) | 2016-03-30 |
| CN105443593B CN105443593B (en) | 2018-07-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410512705.1A Active CN105443593B (en) | 2014-09-29 | 2014-09-29 | A kind of drum-type linkage that can realize damping and lock function |
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| CN (1) | CN105443593B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110486371A (en) * | 2019-08-21 | 2019-11-22 | 新乡市恒润机电有限公司 | Position-limit mechanism with unidirectional self-lock function |
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| JP2002364629A (en) * | 2001-06-08 | 2002-12-18 | Tokai Tsushin Kogyo Kk | Hinge device |
| US20040134031A1 (en) * | 2002-12-26 | 2004-07-15 | Taichi Nishihara | Hinge device |
| CN1862042A (en) * | 2005-05-13 | 2006-11-15 | 深圳富泰宏精密工业有限公司 | Hinge structure |
| CN201121646Y (en) * | 2007-11-06 | 2008-09-24 | 北京空间飞行器总体设计部 | Folding type rigid and semi-rigid sun wing quadratic expansion type hinge between plates |
| CN202007829U (en) * | 2010-12-31 | 2011-10-12 | 三一重工股份有限公司 | Hinge stopping mechanism and concrete pump truck utilizing hinge stopping mechanism |
| CA2807316A1 (en) * | 2010-08-05 | 2012-02-09 | Shaw Hwee, Hui-Fang | Adjustable torque hinge |
| CN203272421U (en) * | 2013-04-03 | 2013-11-06 | 杭州安费诺飞凤通信部品有限公司 | Novel friction rotating shaft hinge |
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2014
- 2014-09-29 CN CN201410512705.1A patent/CN105443593B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002364629A (en) * | 2001-06-08 | 2002-12-18 | Tokai Tsushin Kogyo Kk | Hinge device |
| US20040134031A1 (en) * | 2002-12-26 | 2004-07-15 | Taichi Nishihara | Hinge device |
| CN1862042A (en) * | 2005-05-13 | 2006-11-15 | 深圳富泰宏精密工业有限公司 | Hinge structure |
| CN201121646Y (en) * | 2007-11-06 | 2008-09-24 | 北京空间飞行器总体设计部 | Folding type rigid and semi-rigid sun wing quadratic expansion type hinge between plates |
| CA2807316A1 (en) * | 2010-08-05 | 2012-02-09 | Shaw Hwee, Hui-Fang | Adjustable torque hinge |
| CN202007829U (en) * | 2010-12-31 | 2011-10-12 | 三一重工股份有限公司 | Hinge stopping mechanism and concrete pump truck utilizing hinge stopping mechanism |
| CN203272421U (en) * | 2013-04-03 | 2013-11-06 | 杭州安费诺飞凤通信部品有限公司 | Novel friction rotating shaft hinge |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110486371A (en) * | 2019-08-21 | 2019-11-22 | 新乡市恒润机电有限公司 | Position-limit mechanism with unidirectional self-lock function |
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| CN105443593B (en) | 2018-07-27 |
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