CN220809826U - Unfolding and locking mechanism for folding missile-borne equipment - Google Patents
Unfolding and locking mechanism for folding missile-borne equipment Download PDFInfo
- Publication number
- CN220809826U CN220809826U CN202322361033.6U CN202322361033U CN220809826U CN 220809826 U CN220809826 U CN 220809826U CN 202322361033 U CN202322361033 U CN 202322361033U CN 220809826 U CN220809826 U CN 220809826U
- Authority
- CN
- China
- Prior art keywords
- piece
- rotating
- locking
- mounting seat
- rotating piece
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 49
- 238000009434 installation Methods 0.000 abstract description 9
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000000306 component Substances 0.000 description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000013011 mating Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 241001330002 Bambuseae Species 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 210000003484 anatomy Anatomy 0.000 description 1
- 239000011425 bamboo Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000000806 elastomer Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001256 stainless steel alloy Inorganic materials 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Landscapes
- Aerials With Secondary Devices (AREA)
Abstract
The utility model discloses an unfolding and locking mechanism for folding missile-borne equipment, which comprises a mounting seat, a rotating piece and a driving mechanism, wherein the rotating piece is arranged on the mounting seat; the mounting seat is provided with a mounting groove, and the rotating piece is arranged in the mounting groove and is rotationally connected with the mounting seat; the driving mechanism is arranged in the mounting seat and comprises an elastic piece and a locking piece, and the locking piece is abutted with the rotating piece when the rotating piece is in a folded state; one side of the mounting groove is provided with a first limiting part, the rotating piece is abutted with the first limiting part after being unfolded and limited by the first limiting part, and the locking piece is abutted with the rotating piece to lock the rotating piece after the rotating piece is unfolded; in the utility model, the installation seat limits the rotation angle of the rotating piece, so that the rotating piece can only rotate in a rotation interval; a driving mechanism is arranged in the mounting seat and used for driving the rotating piece to rotate; the driving mechanism can lock the unfolded rotating piece, so that the rotating piece is kept stable in an unfolded state; the mounting seat and the rotating piece are simple in structure and small in design, and can be used for unfolding and locking the wing panel, the rudder piece or the antenna.
Description
Technical Field
The utility model belongs to the technical field of aviation, and particularly relates to an unfolding and locking mechanism for folding missile-borne equipment.
Background
When the missile-borne equipment is usually a wing piece, a rudder piece or an antenna, the folding missile-borne equipment can reduce the sizes of a missile body and a launching platform and enlarge the design size of the wing piece or the rudder piece; the expansion and locking mechanism of the wing plate, the rudder piece and the antenna belongs to an important core component on the projectile body, and the expansion and fixing effect of the expansion and locking mechanism on the projectile body on the missile-borne equipment directly influences the precision of the projectile body.
The existing unfolding and locking mechanism on the missile body is large in size and weight, the locking effect on the missile-borne equipment after the missile-borne equipment is unfolded is poor, the unfolded missile-borne equipment is unstable on the missile body and easy to shake, and the control efficiency and the trajectory of the missile can be influenced.
Disclosure of utility model
The utility model aims to provide a unfolding and locking mechanism for folding missile-borne equipment, which can unfold and lock the missile-borne equipment, has a simple and small structure and is stable and reliable in unfolding and locking the missile-borne equipment.
The utility model is realized by the following technical scheme: an unfolding and locking mechanism for folding missile-borne equipment comprises a mounting seat, a rotating piece and a driving mechanism; the mounting seat is provided with a mounting groove communicated with the outside, and the rotating piece is arranged in the mounting groove and is rotationally connected with the mounting seat; the driving mechanism is arranged in the mounting seat and comprises an elastic piece and a locking piece, the elastic piece is connected with the locking piece, and the locking piece is abutted with the rotating piece when the rotating piece is in a folded state; the mounting groove one side is provided with first spacing portion, rotate the piece after expanding with first spacing portion butt and by first spacing portion spacing, rotate the piece after rotating open the locking piece with rotate the piece butt and with rotating the piece locking.
The working principle of the technical scheme is as follows: the mounting seat is connected with the projectile body, and the mounting seat is used for fixing the projectile-loaded equipment, and the projectile-loaded equipment generally includes fin, rudder piece, and the rotating member is used for connecting the projectile-loaded equipment and driving it to expand or be closed, is provided with the mounting groove on the mounting seat, rotates the piece and rotates in the mounting groove, and actuating mechanism is used for driving the rotating member and rotates, and actuating mechanism includes elastic component and locking piece, and the elastic component provides the driving force, and locking piece and rotating member butt and promotion rotate, and first spacing portion is used for spacing the rotating member of expanding.
In order to better realize the utility model, further, the locking part is arranged on the locking piece, the matching part is arranged on the rotating piece, and the locking part is in abutting fit with the matching part after the locking piece is rotated and unfolded. The locking part can be attached to the matching part of the rotating part, so that the rotating part is better fixed in the unfolding state.
In order to better realize the utility model, further, the mounting seat is provided with a second limiting part, and the rotating part is abutted with the second limiting part when the rotating part is in a folded state. The second limiting part is arranged on the mounting seat and is used for limiting the rotating piece in the folded state.
In order to better realize the utility model, the mounting seat is further provided with a third limiting part, and the rotating piece is abutted with the first limiting part and the third limiting part after being unfolded. The third limiting part is arranged inside the mounting seat and located below the driving mechanism, the driving mechanism is arranged between the second limiting part and the third limiting part, and the third limiting part is used for further limiting the unfolded rotating piece.
In order to better realize the utility model, the rotating piece is further connected with the mounting seat in a rotating way through a rotating shaft. The rotating shaft is used for enabling the rotating piece to rotate on the mounting seat.
In order to better realize the utility model, further, one end of the mounting seat is provided with a tail cover, and the tail cover is connected with an elastic piece of the driving mechanism. The tail cover is used for fixing the driving mechanism.
In order to better realize the utility model, the mounting seat is further provided with a positioning piece. The locating piece is used for fixing the mounting seat.
In order to better realize the utility model, further, the mounting seat is provided with supporting feet which are movably connected with the elastic body. The legs are used to connect the mount to the projectile body.
In order to better realize the utility model, when the missile-borne equipment is an antenna, a cable is arranged below the antenna, the rotating piece is provided with a wiring hole, and the cable passes through the wiring hole of the rotating piece to be connected with the missile body. The wiring hole is used for passing through the cable and can prevent the cable from being extruded by the rotating piece.
Compared with the prior art, the utility model has the following advantages:
(1) The rotating piece is arranged in the mounting seat, and the mounting seat can limit the rotating angle of the rotating piece so that the rotating piece can only rotate in a rotating interval; meanwhile, a driving mechanism is arranged in the mounting seat, and can drive the rotating member to rotate, and in addition, the driving mechanism can lock the unfolded rotating member, so that the rotating member is kept stable in an unfolded state; the mounting seat and the rotating piece are simple in structure, small in design and low in manufacturing cost, and can be used for unfolding and locking the wing sheet, the rudder sheet or the antenna.
(2) In the utility model, when the wing piece, the rudder piece or the antenna is folded in the launching tube, the wing piece, the rudder piece or the antenna is limited only by using the side wall of the launching tube, and an additional limiting structure is not needed, thereby reducing the production and manufacturing cost of the missile.
(3) According to the utility model, the unfolding angle of the wing piece, the rudder piece or the antenna can be adjusted, and only the size of the mounting groove on the mounting seat and the parameters of the elastic piece are required to be adjusted, so that the application range is wide, and the device can adapt to different types of elastic bodies.
Drawings
Other features, objects and advantages of the present utility model will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic view of a folded state of a wing panel according to the present utility model;
FIG. 2 is a top view of FIG. 1;
FIG. 3 is a schematic view of a sail deployment configuration of the present utility model;
FIG. 4 is a schematic view of the structure of the locking member according to the present utility model;
FIG. 5 is a schematic illustration of the anatomy of the mount of the present utility model;
FIG. 6 is a schematic diagram of a folded antenna structure in accordance with the present utility model;
fig. 7 is a schematic diagram of an antenna in an unfolded state according to the present utility model.
Wherein: the device comprises a mounting seat 2-a first limiting part 21-a second limiting part 23-a third limiting part 24-a mounting groove 25-a positioning piece 26-a supporting leg 3-a rotating piece 31-a wing piece 32-an antenna 33-a rotating shaft 34-a matching part 35-a wiring hole 4-a tail cover 5-an elastic piece 6-a locking piece 61-a locking part 7-a cable.
Detailed Description
Embodiments of the present utility model are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the utility model.
In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, the definition of "first", "second" is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly including one or more such features. In the description of the present utility model, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present utility model, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; or may be directly connected, or may be indirectly connected through an intermediate medium, or may be communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.
Example 1:
The main structure of the present embodiment, as shown in fig. 1 to 3, includes a mount 2, a rotary member 3, and a driving mechanism; the mounting seat 2 is provided with a mounting groove 24 communicated with the outside, and the rotating piece 3 is arranged in the mounting groove 24 and is in rotating connection with the mounting seat 2; the driving mechanism is arranged in the mounting seat 2 and comprises an elastic piece 5 and a locking piece 6, the elastic piece 5 is connected with the locking piece 6, and the locking piece 6 is abutted with the rotating piece 3 when the rotating piece 3 is in a folded state; the mounting groove 24 is provided with a first limiting part 21 on one side, the rotating piece 3 is abutted against the first limiting part 21 and limited by the first limiting part 21 after being unfolded, and the locking piece 6 is abutted against the rotating piece 3 to lock the rotating piece 3 after the rotating piece 3 is unfolded.
In particular, the missile-borne equipment is typically a fin 31 or rudder blade. The installation seat 2 is installed on the projectile body, the installation seat 2 is provided with an installation groove 24, the rotating piece 3 is arranged in the installation groove 24 and can rotate on the installation seat 2, the end part of the rotating piece 3 is connected with the projectile-carrying equipment, in the embodiment, the rotating piece 3 is connected with the wing piece 31 or the rudder piece, and the rotating piece 3 is rotated and unfolded under the driving force of the driving mechanism, so that the wing piece 31 or the rudder piece is unfolded; the driving mechanism comprises an elastic piece 5 and a locking piece 6, wherein the elastic piece 5 is usually a spring, and the compression length of the spring is not more than 70% of the original length when the wing piece 31 or the rudder piece is folded in the launching tube; after the wing sheets 31 or rudder pieces are unfolded, the compression length of the springs is not less than 30% of the original length, and the proper compression ratio parameters of the springs are set, so that the service lives of the springs are longer; the locking piece 6 can do linear motion under the action of the elastic force of the elastic piece 5, pushes the rotating piece 3 to be abutted against the rotating piece 3 after being unfolded, locks the rotating piece 3, one side of the rotating piece 3 is abutted against the first limiting part 21 on the mounting seat 2 after being unfolded, and the wing piece 31 or the rudder piece is pushed by the driving force of the elastic piece 5 and the axial aerodynamic force of missile flight together to be quickly unfolded and locked the rotating piece 3.
Example 2:
The present embodiment further defines a driving mechanism on the basis of the above embodiment, as shown in fig. 1 and 4, the locking member 6 is provided with a locking portion 61, the rotating member 3 is provided with a mating portion 34, and the locking member 6 is rotated and unfolded, and then the locking portion 61 is in abutting engagement with the mating portion 34. The locking piece 6 is provided with a locking part 61 with an arc inclined surface structure, the rotating piece 3 is provided with a matching part 34 matched with the locking part 61, and the locking part 61 can be abutted with the matching part 34 to lock the rotating piece 3 in a unfolding state after the rotating piece 3 is unfolded. Other portions of this embodiment are the same as those of the above embodiment, and will not be described here again.
Example 3:
In this embodiment, on the basis of the foregoing embodiment, a second limiting portion 22 is further added, as shown in fig. 1 and 5, a second limiting portion 22 is disposed on the mounting base 2, and the rotating member 3 abuts against the second limiting portion 22 when in a folded state. The second spacing portion 22 sets up on mount pad 2, and when rotating piece 3 was in the folded condition, second spacing portion 22 can carry out spacingly to rotating piece 3, prevents to rotate piece 3 excessively folding in the transmission section of thick bamboo, influences the expansion effect. Other portions of this embodiment are the same as those of the above embodiment, and will not be described here again.
Example 4:
In this embodiment, on the basis of the foregoing embodiment, a third limiting portion 23 is further added, the mounting seat 2 is provided with the third limiting portion 23, and the rotating member 3 abuts against the first limiting portion 21 and the third limiting portion 23 after being unfolded. The third limiting part 23 is arranged in the middle of the rotating member 3, the driving mechanism is arranged between the second limiting part 22 and the third limiting part 23, when the rotating member 3 is in a unfolding state, the first limiting part 21 and the third limiting part 23 can limit the rotating member 3 at the same time, and under the locking action of the driving mechanism, the rotating member 3 is fixed in the unfolding state. Other portions of this embodiment are the same as those of the above embodiment, and will not be described here again.
Example 5:
the present embodiment further defines a rotating member 3 on the basis of the above embodiment, and as shown in fig. 3, the rotating member 3 is rotatably connected with the mounting base 2 through a rotating shaft 33. The rotating member 3 is arranged in the mounting groove 24 and is rotationally connected with the mounting seat 2 through a rotating shaft 33, the rotating shaft 33 is formed by machining high strength such as stainless steel or titanium alloy rods, the tail end of the rotating shaft is connected with a hexagonal nut, and the threaded part of the rotating shaft 33 is coated with medium-strength anaerobic adhesive so as to prevent impact vibration. Other portions of this embodiment are the same as those of the above embodiment, and will not be described here again.
Example 6:
In this embodiment, on the basis of the above embodiment, a tail cover 4 is further added, as shown in fig. 2, one end of the mounting seat 2 is provided with the tail cover 4, and the tail cover 4 is connected with an elastic member 5 of the driving mechanism. One end of an elastic piece 5 on the driving mechanism is connected with a tail cover 4, and the mounting seat and the tail cover 4 are formed by processing high-strength aluminum alloy or titanium alloy; in order to facilitate the installation of the driving mechanism, the tail cover 4 and the installation seat 2 are fixed by screws, when the driving mechanism is installed, the driving mechanism is inserted between the second limiting part 22 and the third limiting part 23, and then the tail cover 4 and the installation seat 2 are fixed by screws. Other portions of this embodiment are the same as those of the above embodiment, and will not be described here again.
Example 7:
In this embodiment, on the basis of the above embodiment, a positioning member 25 is further added, as shown in fig. 5, and the mounting base 2 is provided with the positioning member 25. The positioning member 25 is preferably of cylindrical configuration, the positioning member 25 being insertable into the projectile and the positioning member 25 on the mounting block 2 being adapted to position the mounting block 2 on the projectile. Other portions of this embodiment are the same as those of the above embodiment, and will not be described here again.
Example 8:
The present embodiment further defines a mounting seat 2 on the basis of the above embodiment, as shown in fig. 2, the mounting seat 2 is provided with a supporting leg 26, and the supporting leg 26 is movably connected with the elastomer. The support legs 26 are provided with threaded holes, the mounting seat 2 is movably connected with the projectile body through screws, and the support legs 26 are matched with the positioning pieces 25, so that the mounting seat 2 is more stable on the projectile body. Other portions of this embodiment are the same as those of the above embodiment, and will not be described here again.
Example 9:
This embodiment is based on the above embodiment in that the missile-borne device is an antenna 32. Further add the wiring hole 35, as shown in fig. 6 and 7, when the missile-borne equipment is the antenna, be provided with cable 7 below the antenna, rotating member 3 is provided with the wiring hole 35, and cable 7 passes the wiring hole 35 of rotating member 3 and is connected with the missile body. In this embodiment, when the rotating member 3 is connected to the antenna 32, the antenna 32 is provided with a cable 7 for communication, and the rotating member 3 is provided with a wiring hole 35 for passing through the cable 7, so as to prevent the rotating member 3 from damaging the cable 7 during rotation; meanwhile, when the missile-borne equipment is the antenna 32, the locking piece 6 on the driving mechanism can be replaced by the existing steel ball or steel ball, so that the manufacturing cost of the unfolding and locking mechanism can be saved. Other portions of this embodiment are the same as those of the above embodiment, and will not be described here again.
It will be appreciated that the principle of operation and the course of operation of components such as springs and screws in a deployment and locking mechanism for a folding missile-borne device according to the present utility model are well known to those skilled in the art and will not be described in detail herein.
While embodiments of the present utility model have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the spirit and principles of the utility model, the scope of which is defined by the claims and their equivalents.
Claims (9)
1. The unfolding and locking mechanism for the folding missile-borne equipment is characterized by comprising a mounting seat (2), a rotating piece (3) and a driving mechanism; the mounting seat (2) is provided with a mounting groove (24) communicated with the outside, and the rotating piece (3) is arranged in the mounting groove (24) and is rotationally connected with the mounting seat (2); the driving mechanism is arranged in the mounting seat (2) and comprises an elastic piece (5) and a locking piece (6), one side of the mounting seat is of a closed structure, the elastic piece (5) is abutted with the closed structure of the mounting seat (2), the elastic piece (5) is connected with the locking piece (6), and when the rotating piece (3) is in a folded state, the locking piece (6) is abutted with the rotating piece (3); the mounting groove (24) one side is provided with first spacing portion (21), rotate piece (3) expansion back, rotate piece (3) and first spacing portion (21) butt and by first spacing portion (21) spacing, rotate piece (3) after rotating, locking piece (6) and rotate piece (3) butt and will rotate piece (3) locking.
2. The unfolding and locking mechanism for a folding missile-borne device according to claim 1, characterized in that the locking piece (6) is provided with a locking part (61), the rotating piece (3) is provided with a matching part (34), and the locking part (61) is in abutting fit with the matching part (34) after the locking piece (6) is unfolded in a rotating way.
3. The unfolding and locking mechanism for a folding missile-borne device according to claim 1 or 2, characterized in that the mounting base (2) is provided with a second limiting part (22), and the rotating member (3) is abutted with the second limiting part (22) when the rotating member (3) is in a folded state.
4. The unfolding and locking mechanism for a folding missile-borne device according to claim 1 or 2, characterized in that a third limiting part (23) is arranged on the mounting seat (2), and the rotating piece (3) is abutted with the first limiting part (21) and the third limiting part (23) after being unfolded.
5. A deployment and locking mechanism for a folding missile-borne device according to claim 1, characterized in that the rotating member (3) is rotatably connected to the mounting seat (2) by means of a rotating shaft (33).
6. A deployment and locking mechanism for a folding missile-borne device according to claim 1, characterized in that the closing structure of the mounting seat (2) is provided with a tail cap (4), said elastic element (5) being in abutment with the tail cap (4).
7. A deployment and locking mechanism for a folding missile-borne device according to claim 1, characterized in that the mounting (2) is provided with a positioning element (25).
8. A deployment and locking mechanism for a folding missile-borne device according to claim 1, characterized in that the mounting (2) is provided with feet (26), said feet (26) being movably connected to the projectile body.
9. The unfolding and locking mechanism for a folding missile-borne device according to claim 1, characterized in that when the missile-borne device is an antenna (32), a cable (7) is arranged below the antenna, the rotating member (3) is provided with a wiring hole (35), and the cable (7) passes through the wiring hole (35) of the rotating member (3) to be connected with a missile body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322361033.6U CN220809826U (en) | 2023-08-31 | 2023-08-31 | Unfolding and locking mechanism for folding missile-borne equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322361033.6U CN220809826U (en) | 2023-08-31 | 2023-08-31 | Unfolding and locking mechanism for folding missile-borne equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220809826U true CN220809826U (en) | 2024-04-19 |
Family
ID=90672080
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322361033.6U Active CN220809826U (en) | 2023-08-31 | 2023-08-31 | Unfolding and locking mechanism for folding missile-borne equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220809826U (en) |
-
2023
- 2023-08-31 CN CN202322361033.6U patent/CN220809826U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106915438B (en) | Unmanned plane | |
| EP0214888B1 (en) | Missile folding wing configuration | |
| CN112520072B (en) | Satellite sailboard unfolding device | |
| CN104089547A (en) | Unfolding and locking device for foldable rudder face | |
| US10337555B2 (en) | Folding and unfolding mechanism | |
| CN112319768A (en) | Embedded folding wing mechanism | |
| CN101708779A (en) | Two-stage spiral repeatable folding and unfolding locking mechanism of solar wing | |
| CN109539902B (en) | Electric-drive folding wing system with large aspect ratio | |
| CN116119052A (en) | Fixed wing unmanned aerial vehicle with foldable wings | |
| CN104677200B (en) | One twice-folded aerofoil horizontal spreading mechanism | |
| CN109592008B (en) | Hinge mechanism, folding wing and emitter | |
| CN112964138A (en) | Rotary folding tail wing of small-caliber rocket | |
| CN220809826U (en) | Unfolding and locking mechanism for folding missile-borne equipment | |
| CN110411287B (en) | Spiral sunken wing folding and unfolding mechanism | |
| CN201545193U (en) | Solar wing double-stage spiral repeated folding-deploying locking-unlocking mechanism | |
| CN210833270U (en) | Synchronous transverse unfolding locking mechanism for submerged folding wings | |
| CN109263858A (en) | A kind of coaxial wingfold mechanism | |
| CN111891335A (en) | Compact folding wing unfolding and locking mechanism | |
| CN204461240U (en) | Twice-folded aerofoil horizontal spreading mechanism | |
| CN215323255U (en) | Folding wing unfolding and locking mechanism | |
| CN218937193U (en) | Grid rudder and rocket | |
| CN115637903B (en) | Cube star solar wing chain and cube star sailboard | |
| CN209225381U (en) | A kind of coaxial wingfold mechanism | |
| CN114458684B (en) | Hinge mechanism | |
| CN207943167U (en) | A kind of collapsible connection module and unmanned plane of unmanned aerial vehicle body and horn |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |