CN114322675A - Deformable ejector rod and foldable control surface structure in foldable rudder of guided missile and guided missile - Google Patents
Deformable ejector rod and foldable control surface structure in foldable rudder of guided missile and guided missile Download PDFInfo
- Publication number
- CN114322675A CN114322675A CN202111449446.9A CN202111449446A CN114322675A CN 114322675 A CN114322675 A CN 114322675A CN 202111449446 A CN202111449446 A CN 202111449446A CN 114322675 A CN114322675 A CN 114322675A
- Authority
- CN
- China
- Prior art keywords
- rudder
- deformable
- missile
- rod
- folded
- 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.)
- Pending
Links
Images
Abstract
The invention provides a deformable ejector rod, a folding rudder surface structure and a missile in a missile folding rudder, wherein the deformable ejector rod in the missile folding rudder comprises a base, a first support rod and a second support rod; the first supporting rod and the second supporting rod are symmetrically arranged on the upper surface of the base; the deformable ejector rod has an initial state and a deformation state; when the support device is in an initial state, an included angle formed by the first support rod and the horizontal plane is a first angle theta, and a second angle delta formed by the first support rod and the horizontal plane is a second angle delta; when being in the deformation state, first bracing piece and second bracing piece are outside bending respectively. According to the invention, when the outer rudder is pulled and unfolded by the firer driving device, the first supporting rod and the second supporting rod can generate large plastic deformation, so that the outer rudder can be unfolded in place. According to the invention, under the working condition that the outer control surface is subjected to a flight load, the deformable ejector rod only makes small elastic deformation, and can bear all pneumatic torque loads of the outer control surface, so that the outer control surface is ensured not to be unfolded by mistake due to the pneumatic load during flight.
Description
Technical Field
The invention relates to the field of aircraft structure design, in particular to a deformable ejector rod and a folding rudder surface structure in a missile folding rudder and a missile.
Background
In order to meet the high-density embedded tactics and skills requirements of the stealth aircraft, the embedded missile needs to be structurally miniaturized through folding control surfaces and the like. The missile folding rudder technology is mature, but the folding rudder suitable for the airborne air-to-air missile of the embedded stealth aircraft has particularity, and is rarely reported at home and abroad at present. When the folding rudder of the embedded air-to-air missile is initially locked, due to the limitation of the use environment, the locking of the folding rudder surface can not be carried out by using the constraint in the cabin, the constraint of guide rails such as similar air-to-air missile barrels/boxes is not carried out, and the technical path of folding and locking the rudder surface with foreign matters detained such as wrapping belts can not be adopted, so that the rudder surface needs to be locked by the structure of the folding rudder surface, small disturbance load needs to be overcome in the embedded missile cabin of the folding rudder, the contour dimension of the rudder surface needs to be kept in accordance with the envelope requirement, the folding rudder surface needs to be unfolded at a high speed under the condition of a large load in the ejection process, the folding function can be realized in the design of the rudder surface, and no foreign matters fly out in the unfolding process. Therefore, the conventional constraint scheme by means of the guide rail, the technical scheme by means of the magnesium alloy wrapping belt and the technical scheme of the shearing screw rod do not meet the design requirements.
Patent document CN111238307A discloses an integrated missile storage and transportation launching box and a manufacturing method thereof, belonging to the field of launching devices. The invention relates to an integrated missile storage and transportation launching box, which comprises a guide rail, a box body and a bearing frame, wherein the guide rail is used for limiting the circumferential movement of a missile; the contact layers are filled with polyimide resin. However, the scheme still adopts a box type emission mode and cannot meet the requirements.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a deformable ejector rod, a folded rudder surface structure and a missile in a missile folded rudder.
The deformable ejector rod in the missile folding rudder provided by the invention comprises a base, a first supporting rod and a second supporting rod; the first supporting rod and the second supporting rod are symmetrically arranged on the upper surface of the base;
the deformable ejector rod has an initial state and a deformation state; when the support device is in an initial state, an included angle between the first support rod and the horizontal plane is a first angle theta, and a second angle delta is formed between the first support rod and the horizontal plane;
when being in the deformation state, first bracing piece and second bracing piece are outside bending respectively.
Preferably, the first support rod and the second support rod are both made of viscoelastic materials;
preferably, the base is integrally connected with the support rod.
Preferably, the first support rod and the second support rod are made of 1Cr18Ni9Cu9N material.
Preferably, the base is annular, the cross section of the annular shape is rectangular, and the rectangular shape is provided with a first notch; the first notch is arranged on the short edge of the rectangle, and the end part of the first supporting rod and the end part of the second supporting rod are respectively arranged on the two long edges of the rectangle.
Preferably, the first angle θ and the second angle δ are both 88.5 ° ± 3'.
Preferably, the thickness t of the first supporting rod and the thickness w of the second supporting rod are both 1.35 +/-0.1 mm.
According to the folding rudder surface structure provided by the invention, the deformable ejector rod in the missile folding rudder is adopted, and the folding rudder surface structure further comprises a folding rudder outer rudder, a folding rudder inner rudder and an initiating explosive driving device; the outer rudder of the folding rudder and the inner rudder of the folding rudder are rotatably connected through an initiating explosive driving device;
the inner rudder of the folding rudder is provided with an accommodating groove, and the deformable ejector rod and the initiating explosive driving device are both arranged in the accommodating groove;
the fire driving device comprises a shell, a connecting rod and a bottom plate, wherein an accommodating space is formed in the shell, the connecting rod is T-shaped, one end of the connecting rod is located in the accommodating space of the shell and is fixedly connected with the top of the bottom plate, the other end of the connecting rod penetrates through the accommodating space, penetrates through the shell and is rotatably connected with the outer rudder of the folding rudder, and the bottom of the bottom plate is in contact with the top of the deformable ejector rod;
the connecting rod can move between a first position and a second position in the accommodating groove along the height direction of the accommodating groove;
the folding rudder surface structure is provided with a folding state and an unfolding state, when the folding rudder surface structure is in the folding state, the connecting rod is located at a first position, the deformable ejector rod in the missile folding rudder is in an initial state, and the inner rudder of the folding rudder and the outer rudder of the folding rudder are folded oppositely;
when the missile folding rudder is in an unfolding state, the connecting rod is located at a second position, the deformable ejector rod in the missile folding rudder is in a deformation state, and the inner rudder of the folding rudder is parallel to the outer rudder of the folding rudder;
the first position is the position which is farthest away from the base in the motion trail of the connecting rod; the second position is the position closest to the base in the motion trail of the connecting rod.
Preferably, a groove is formed in the inner rudder of the folding rudder along the length direction of the inner rudder of the folding rudder, the groove is matched with the connecting rod, and when the connecting rod is located at the second position, the other end of the connecting rod is clamped into the groove.
The missile is characterized in that the folding control surface structure is adopted.
Compared with the prior art, the invention has the following beneficial effects:
1. the outer rudder adopts the viscoelastic material, and when the outer rudder is pulled and unfolded by the firer driving device, the first supporting rod and the second supporting rod can generate large plastic deformation, so that the outer rudder can be unfolded in place.
2. The deformable ejector rod has the advantages that no excess is released in the unfolding process.
3. According to the invention, under the working condition that the outer control surface is subjected to a flight load, the deformable ejector rod only makes small elastic deformation, and can bear all pneumatic torque loads of the outer control surface, so that the outer control surface is ensured not to be unfolded by mistake due to the pneumatic load during flight.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of the deformable carrier rod of the present invention in an initial state;
FIG. 2 is a structural diagram illustrating a deformed state of the deformable carrier rod according to the present invention;
FIG. 3 is a schematic front view of a deformable carrier rod according to the present invention;
FIG. 4 is a schematic structural diagram of a folded state of the folded rudder surface structure of the present invention;
FIG. 5 is a cross-sectional structural view of a folded control surface structure according to the present invention;
FIG. 6 is a schematic structural diagram of the folded control surface structure in an unfolded state;
FIG. 7 is a front view of the folded control surface structure of the present invention;
FIG. 8 is a schematic structural view of the folded control surface structure in an unfolded state;
the figures show that:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The invention provides a deformable ejector rod in a missile foldable rudder, which comprises a base 41, a first supporting rod 42 and a second supporting rod 43; the first support rod 42 and the second support rod 43 are symmetrically installed on the upper surface of the base 41, and both the first support rod 42 and the second support rod 43 are made of viscoelastic materials; in a preferred embodiment, the first supporting rod 42 and the second supporting rod 43 are made of 1Cr18Ni9Cu 9N. In a preferred embodiment, the base 41 is integrally connected to the supporting rod 42.
As shown in fig. 1-3, the deformable roof bar has an initial state and a deformed state; when in an initial state, an included angle between the first support rod 42 and the horizontal plane is a first angle θ, and the first support rod 42 and the horizontal plane are a second angle δ; the first angle theta and the second angle delta are both acute angles. When in the deformed state, the first support rod 42 and the second support rod 43 are bent outward respectively. In a preferred embodiment, the first angle θ and the second angle δ are both 88.5 ° ± 3', and the thickness t of the first supporting bar 42 and the thickness w of the second supporting bar 43 are both 1.35 ± 0.1 mm.
The base 41 is annular, the cross section of the annular shape is rectangular, and the rectangular shape is provided with a first notch 44; the first notch 44 is disposed on the short side of the rectangle, and the end of the first supporting rod 42 and the end of the second supporting rod 43 are respectively mounted on the two long sides of the rectangle.
The invention also provides a folding rudder surface structure, which adopts the deformable ejector rod 4 in the missile folding rudder, and also comprises a folding rudder outer rudder 1, a folding rudder inner rudder 2 and an initiating explosive driving device 3; the outer rudder 1 of the folding rudder and the inner rudder 2 of the folding rudder are rotatably connected through an initiating explosive drive device 3;
as shown in fig. 4, the inner rudder 2 of the folded rudder is provided with an accommodating groove 21, and the deformable ram 4 and the initiating explosive device 3 are both installed in the accommodating groove 21;
as shown in fig. 5, the fire driving device 3 includes a housing 31, a connecting rod 32 and a bottom plate 33, an accommodating space is provided in the housing, the connecting rod 32 is T-shaped, one end of the connecting rod 32 is located in the accommodating space of the housing 31 and is tightly connected to the top of the bottom plate 33, the other end of the connecting rod 32 passes through the accommodating space, penetrates through the housing 31 to the outside and is rotatably connected to the outer rudder 1 of the foldable rudder, and the bottom of the bottom plate 33 is in contact with the top of the deformable push rod 4;
the connecting rod 32 is movable within the accommodating groove 21 in a height direction of the accommodating groove 21 between a first position and a second position; the first position is the position farthest away from the base 41 in the motion trail of the connecting rod 32; the second position is a position closest to the base 41 in the movement locus of the connecting rod 32.
The folded rudder surface structure has a folded state and an unfolded state, as shown in fig. 4-5, when in the folded state, the connecting rod 32 is located at a first position, the deformable mandril 4 in the missile folded rudder is in an initial state, and the inner rudder 2 of the folded rudder and the outer rudder 1 of the folded rudder are folded oppositely;
as shown in fig. 6-8, when in the unfolded state, the connecting rod 32 is located at the second position, the deformable ram 4 in the missile rudder folder is in a deformed state, and the inner rudder 2 and the outer rudder 1 of the missile rudder folder are unfolded opposite to each other, i.e. the inner rudder 2 and the outer rudder 1 of the missile rudder folder are parallel;
as shown in fig. 8, a groove 22 is formed in the inner rudder 2 of the folded rudder along the length direction of the inner rudder 2 of the folded rudder, the groove 22 is matched with the connecting rod 32, and when the connecting rod 32 is located at the second position, the other end of the connecting rod 32 is clamped in the groove 22. The groove 22 is used to lock the folded rudder surface structure in the unfolded state.
The invention also provides a missile adopting the folding control surface structure.
The working process and principle of the invention are as follows:
when the missile is in a flying state and the folded rudder surface structure is in a folded state, the connecting rod 32 is located at the first position, the deformable ejector rod 4 in the missile folded rudder is in an initial state, and the deformable ejector rod 4 plays a supporting role for the bottom plate 33, so that the inner rudder 2 of the folded rudder and the outer rudder 1 of the folded rudder are ensured to be folded relatively. At the moment, even if the missile is subjected to flight load, the deformation mandril 4 only makes small elastic deformation due to the characteristics of materials, and can bear all pneumatic torque load of the outer rudder surface, so that the outer rudder cannot be unfolded by mistake due to the pneumatic load during flight.
When folding rudder face structure need switch into the expansion state from fold condition, gunpowder or other energy supply equipment that have in the firer drive arrangement 3 provide drive power, order about folding rudder face structure switches into the expansion state from fold condition, at this moment connecting rod 32 is moved to the second position by first position, drives bottom plate 33 pushes down, will first bracing piece 42 bends with second bracing piece 43, the controllable big deformation of structure takes place for the deformable ejector pin, release restriction folding rudder outer rudder 1 pivoted degree of freedom, folding rudder face structure realizes folding rudder face's expansion under firer drive arrangement 3's the effect promptly. The other end of the connecting rod 32 now snaps into the recess 22 in the inner rudder 2 of the folded rudder, locking the folded rudder surface structure in the unfolded state.
The invention realizes that under the condition of certain external load, the deformable ejector rod is stressed in an elastic deformation range, the deformable ejector rod limits the rotation displacement of the outer rudder 1 of the folding rudder, the outer rudder 1 of the folding rudder surface can not rotate and unfold, and the folding state of the structure of the folding rudder surface is locked; after receiving the unfolding instruction, the deformable ejector rod bears the force generated by the initiating explosive device 3, the first support rod 42 and the second support rod 43 are subjected to large deformation with controllable structures, and the degree of freedom for limiting the rotation of the outer rudder 1 of the folding rudder is released, namely the folding rudder surface structure realizes the unfolding of the folding rudder surface under the force action of the initiating explosive device 3. The invention can ensure the locking of the folded state of the folded control surface structure, and can also ensure the timely and accurate unfolding and locking of the control surface under the condition of receiving an unfolding instruction. And due to the adoption of the deformable ejector rod made of the high-viscoelasticity material, when the first supporting rod 42 and the second supporting rod 43 are deformed greatly in structure, the structural integrity can be still ensured, and the release of structural foreign matters is avoided in the unfolding process.
The first angle theta, the second angle delta, the thickness t of the first supporting rod 42 and the thickness w of the second supporting rod 43 of the deformable ejector rod are designed according to parameters such as the size, the weight and the like of a control surface; the folded control surface structure is locked to a folded state by only elastically deforming under the condition that the folded control surface structure bears a small load through a certain angle and thickness matched with a viscoelastic material; when the folded control surface structure performs unfolding motion according to instructions, the first support rod 42 and the second support rod 43 can meet large plastic deformation, and the materials are prevented from being broken. The folding control surface structure is not unfolded under stress under the condition of small load, and the large deformation and fracture can be avoided greatly under the action of large load provided by the fire driving device 3, the movement of the control surface is not hindered, no foreign matter flies out in the unfolding process, the gap between the control surfaces can be eliminated through final deformation, and the rigidity of the control surfaces is improved. The deformable ejector rod has the advantages of simple structure, convenience in manufacturing and processing, long service life, convenience in installation and operation and the like, and the safe separation of the guided missile and the carrier is ensured.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A deformable ejector rod in a missile folding rudder is characterized by comprising a base (41), a first supporting rod (42) and a second supporting rod (43); the first supporting rod (42) and the second supporting rod (43) are symmetrically arranged on the upper surface of the base (41);
the deformable ejector rod has an initial state and a deformation state; when the device is in an initial state, an included angle between the first supporting rod (42) and the horizontal plane is a first angle theta, and a second angle delta is formed between the first supporting rod (42) and the horizontal plane;
when the support bar is in a deformation state, the first support bar (42) and the second support bar (43) are bent outwards respectively.
2. Deformable ram in a missile rudder according to claim 1, characterised in that the first (42) and second (43) support rods are made of viscoelastic material.
3. Deformable ram in a missile rudder according to claim 1, characterised in that the base (41) is connected integrally to the support rod (42).
4. Deformable ram in a missile rudder according to claim 2, characterised in that the first (42) and the second (43) support rods are made of 1Cr18Ni9Cu9N material.
5. Deformable ram in a missile rudder according to claim 1 characterised in that the base (41) is annular, the cross section of the annulus being rectangular, the rectangle having a first notch (44); the first notch (44) is arranged on the short side of the rectangle, and the end part of the first supporting rod (42) and the end part of the second supporting rod (43) are respectively arranged on the two long sides of the rectangle.
6. A deformable ram in a missile rudder according to claim 1 wherein the first angle θ and the second angle δ are both 88.5 ° ± 3'.
7. Deformable ram in a missile rudder according to claim 1, characterised in that the thickness t of the first support bar (42) and the thickness w of the second support bar (43) are both 1.35 ± 0.1 mm.
8. The folded rudder surface structure is characterized in that a deformable mandril (4) in the missile folded rudder according to any one of claims 1 to 5 is adopted, and the structure further comprises an outer folded rudder (1), an inner folded rudder (2) and a fire driving device (3); the outer rudder (1) of the folding rudder and the inner rudder (2) of the folding rudder are rotatably connected through a firer driving device (3);
the inner rudder (2) of the folding rudder is provided with an accommodating groove (21), and the deformable ejector rod (4) and the initiating explosive device (3) are both arranged in the accommodating groove (21);
the fire driving device (3) comprises a shell (31), a connecting rod (32) and a bottom plate (33), an accommodating space is formed in the shell, the connecting rod (32) is T-shaped, one end of the connecting rod (32) is located in the accommodating space of the shell (31) and is fixedly connected with the top of the bottom plate (33), the other end of the connecting rod (32) penetrates through the accommodating space, penetrates through the outer portion of the shell (31) and is rotatably connected with the outer rudder (1) of the folding rudder, and the bottom of the bottom plate (33) is in contact with the top of the deformable ejector rod (4);
the connecting rod (32) can move between a first position and a second position in the accommodating groove (21) along the height direction of the accommodating groove (21);
the folded rudder surface structure has a folded state and an unfolded state, when the folded state is reached, the connecting rod (32) is located at a first position, the deformable mandril (4) in the missile folded rudder is in an initial state, and the inner rudder (2) and the outer rudder (1) of the folded rudder are folded oppositely;
when the missile folding rudder is in an unfolding state, the connecting rod (32) is located at a second position, a deformable ejector rod (4) in the missile folding rudder is in a deformation state, and the folding rudder inner rudder (2) is parallel to the folding rudder outer rudder (1);
the first position is the position farthest from the base (41) in the motion trail of the connecting rod (32); the second position is the position closest to the base (41) in the motion trail of the connecting rod (32).
9. The folded rudder surface structure according to claim 8, wherein a groove (22) is formed in the folded rudder inner rudder (2) along the length direction of the folded rudder inner rudder (2), the groove (22) is matched with the connecting rod (32), and when the connecting rod (32) is located at the second position, the other end of the connecting rod (32) is clamped in the groove (22).
10. A missile using the folded control surface structure of claim 8 or 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111449446.9A CN114322675A (en) | 2021-11-30 | 2021-11-30 | Deformable ejector rod and foldable control surface structure in foldable rudder of guided missile and guided missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111449446.9A CN114322675A (en) | 2021-11-30 | 2021-11-30 | Deformable ejector rod and foldable control surface structure in foldable rudder of guided missile and guided missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114322675A true CN114322675A (en) | 2022-04-12 |
Family
ID=81048987
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111449446.9A Pending CN114322675A (en) | 2021-11-30 | 2021-11-30 | Deformable ejector rod and foldable control surface structure in foldable rudder of guided missile and guided missile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114322675A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108760228A (en) * | 2018-06-08 | 2018-11-06 | 中国航天空气动力技术研究院 | A kind of rudder face dynamic force measurement device and test method folded during rudder is unfolded |
| US20190107374A1 (en) * | 2017-10-05 | 2019-04-11 | Overwatch Defense, LLC | Remotely controllable aeronautical ordnance loitering |
| CN113221243A (en) * | 2021-05-12 | 2021-08-06 | 上海机电工程研究所 | Simulation calculation method and system for transient synchronous unfolding of aircraft folded rudder |
| CN113357972A (en) * | 2021-07-16 | 2021-09-07 | 中国航空制造技术研究院 | Unfolding driving device and driving method for missile folding rudder or folding wing |
| CN113624074A (en) * | 2021-07-21 | 2021-11-09 | 上海机电工程研究所 | Locking and unlocking device for folding rudder of guided missile |
-
2021
- 2021-11-30 CN CN202111449446.9A patent/CN114322675A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20190107374A1 (en) * | 2017-10-05 | 2019-04-11 | Overwatch Defense, LLC | Remotely controllable aeronautical ordnance loitering |
| CN108760228A (en) * | 2018-06-08 | 2018-11-06 | 中国航天空气动力技术研究院 | A kind of rudder face dynamic force measurement device and test method folded during rudder is unfolded |
| CN113221243A (en) * | 2021-05-12 | 2021-08-06 | 上海机电工程研究所 | Simulation calculation method and system for transient synchronous unfolding of aircraft folded rudder |
| CN113357972A (en) * | 2021-07-16 | 2021-09-07 | 中国航空制造技术研究院 | Unfolding driving device and driving method for missile folding rudder or folding wing |
| CN113624074A (en) * | 2021-07-21 | 2021-11-09 | 上海机电工程研究所 | Locking and unlocking device for folding rudder of guided missile |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10336443B2 (en) | Retractable and deployable flight rotor system | |
| US8876039B2 (en) | Folding wing for aircraft | |
| US20220212797A1 (en) | Systems and methods for loading and unloading a cargo aircraft | |
| CN101712379B (en) | Folding small-sized unmanned aerial vehicle | |
| US7816635B2 (en) | Air vehicle wing pivot | |
| CN111086656B (en) | Combined adjustable grid rudder unfolding and locking mechanism | |
| US20090206193A1 (en) | Ballistically deployed telescoping aircraft wing | |
| CN110487131B (en) | Grid rudder unfolding and locking mechanism for aerospace transport vehicle | |
| CN110104161A (en) | Folding fin unfolding mechanism and its method of deploying | |
| CN106956776B (en) | Unmanned aerial vehicle jettisonings device and unmanned aerial vehicle | |
| CN101708779A (en) | Two-stage spiral repeatable folding and unfolding locking mechanism of solar wing | |
| US11530031B2 (en) | Folding trailing arm landing gear | |
| KR0179432B1 (en) | Aerodynamic lifting and control surface and control system using the same | |
| CN111114753B (en) | Power-source-free scissor type folding wing surface, unfolding method thereof and aircraft | |
| CN210833270U (en) | Synchronous transverse unfolding locking mechanism for submerged folding wings | |
| CN114322675A (en) | Deformable ejector rod and foldable control surface structure in foldable rudder of guided missile and guided missile | |
| CN111470031A (en) | Folding wing structure of unmanned aerial vehicle | |
| CN109436286A (en) | A kind of variation rigidity elastic force release acting device for ram-air turbine | |
| CN111721166A (en) | Carrier rocket upper-level recovery system and method and carrier rocket recovery system | |
| US20230211902A1 (en) | Deployable wing system for air vehicle | |
| CN112550666B (en) | Folding mechanism of unmanned aerial vehicle wing | |
| KR20230025004A (en) | Wing module for aircraft | |
| CN110884694B (en) | Can reduce compressing tightly release mechanism of spacecraft envelope | |
| CN214524413U (en) | Cold launching device suitable for aerial release of small-size folding wing unmanned aerial vehicle | |
| CN116573169A (en) | Catapulting and separating device for parallel spacecraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |