CN112665468B - Novel strong locking and weak unlocking mechanism - Google Patents
Novel strong locking and weak unlocking mechanism Download PDFInfo
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- CN112665468B CN112665468B CN202011521391.3A CN202011521391A CN112665468B CN 112665468 B CN112665468 B CN 112665468B CN 202011521391 A CN202011521391 A CN 202011521391A CN 112665468 B CN112665468 B CN 112665468B
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- connecting piece
- airfoil surface
- locking
- upper airfoil
- unlocking
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Abstract
The invention provides a novel strong locking and weak unlocking mechanism which consists of an actuator, a connecting piece, an upper airfoil surface, a lower airfoil surface and a fixed pin; the upper airfoil surface and the lower airfoil surface are provided with locking grooves, and in an initial working state, the two locking grooves are aligned; the connecting piece is arranged in the locking groove in a sliding way; pin holes corresponding to the positions of the upper airfoil surface and the connecting piece are arranged on the connecting piece; the fixing pin passes through the pin holes of the connecting piece and the upper airfoil surface to lock the positions of the upper airfoil surface, the lower airfoil surface and the connecting piece. The missile wing surface folding and unfolding mechanism has the advantages that the missile wing surface folding and unfolding mechanism has large locking force, and the missile wing surface folding and unfolding mechanism can be reliably locked under the condition of large external load in an initial state; when the mechanism moves, only a small unlocking force is needed to reliably unlock the mechanism.
Description
Technical Field
The invention belongs to the field of weaponry, relates to a locking mechanism of a missile wingspan mechanism, and particularly relates to a novel strong locking and weak unlocking mechanism.
Background
According to the increasingly severe use requirements of the current missile, the missile wing surface folding and unfolding mechanism must be reliably locked before being unfolded under the condition of heavy load, the folding state is kept, and after the actuator works, the mechanism is required to be reliably unlocked, so that the mechanism is unfolded in place.
According to investigation, the locking mechanisms of missile wingspan mechanisms which are conventionally used at home and abroad at present all adopt a shearing pin mode, the initial required locking force of a folding and unfolding mechanism is calculated and obtained by means of the shearing strength of shearing pin materials, then the locking mechanisms are processed into cylindrical shearing pins, and the cylindrical shearing pins are installed in pin holes to keep the initial folding state of the mechanism; the structure has the defects that the locking purpose is achieved by only relying on the strength of a shearing pin material, the locking force is large, the driving force of the required unlocking force is large, part of the driving force provided by the actuator is consumed on the unlocking force, and the driving force utilization efficiency is low; such shear pin arrangements would not be satisfactory if the required locking force were greater than the driving force provided by the actuator; in addition, other mechanisms with strong locking and weak unlocking have the defects of complex structure, more parts, low reliability and the like, and are not suitable for the development trend of the current flying missiles. Therefore, the novel locking mechanism with large locking force, small unlocking force and simple structure is the aim of the invention.
Disclosure of Invention
The invention mainly aims at providing a novel reliable locking and unlocking mechanism which can provide large locking force and small unlocking force and ensure the reliable locking and unlocking of an airfoil folding and unfolding mechanism aiming at the increasingly severe use condition of the existing missile and under the condition of heavy load, wherein the requirements of the reliable locking and unlocking of the airfoil folding and unfolding mechanism cannot be met in the prior art.
The technical solution of the invention for achieving the above purpose is as follows: the novel strong locking and weak unlocking mechanism consists of an actuator, a connecting piece, an upper airfoil surface, a lower airfoil surface and a fixed pin; the upper airfoil surface and the lower airfoil surface are provided with locking grooves, and in an initial working state, the two locking grooves are aligned; the connecting piece is arranged in the locking groove in a sliding way; pin holes corresponding to the positions of the upper airfoil surface and the connecting piece are arranged on the connecting piece; the fixing pin passes through the pin holes of the connecting piece and the upper airfoil surface to lock the positions of the upper airfoil surface, the lower airfoil surface and the connecting piece.
Further, the length of the connecting piece in the lock grooves of the upper airfoil surface and the lower airfoil surface is 5mm, so that the locking strength and the shearing force during unlocking are ensured.
Further, the structural strength of the connector is not less than 30000N, thereby ensuring strong locking capability to the airfoil.
Further, the connecting piece is of a rectangular structure, the material is alloy steel 30CrMnSiA, and the thickness is 4.8mm.
Further, the diameter of the fixing pin is 2mm, the structural strength is 800N-1200N, and the actuator pushes the connecting piece to shear the fixing pin, so that weak unlocking is realized.
The beneficial effects of the invention are as follows: compared with the prior art, the mechanism has the advantages of large locking force and reliable locking of the folding and unfolding mechanism in the initial state; the unlocking force is small, and the mechanism is reliably unlocked by the small unlocking force. Through a large number of tests carried out in a real mechanism, the structure can ensure the reliable locking and unlocking of the wingspan mechanism, and has simple structure and easy engineering realization.
Drawings
Fig. 1 is a structural diagram at the initial state;
FIG. 2 is a left cross-sectional view of FIG. 1;
fig. 3 is an isometric view of fig. 1.
In the figure: 1 upper airfoil surface, 2 connecting piece, 3 lower airfoil surfaces, 4 fixed pins, 5 actuators and 6 locking grooves.
Detailed Description
The invention is further described below with reference to the drawings and the detailed description.
The novel strong locking and weak unlocking mechanism comprises an actuator 5, a connecting piece 2, an upper airfoil surface 1, a lower airfoil surface 3 and a fixing pin 4; the upper airfoil surface 1 and the lower airfoil surface 3 are provided with locking grooves, and in an initial working state, the two locking grooves are aligned; the connecting piece 2 is arranged in the locking groove in a sliding way; pin holes corresponding to the positions of the upper airfoil surface and the connecting piece are arranged on the connecting piece; the fixing pin passes through the pin holes of the connecting piece and the upper airfoil surface to lock the positions of the upper airfoil surface, the lower airfoil surface and the connecting piece.
The length that the connecting piece is located upper airfoil face and lower airfoil face lock groove is 5mm, can guarantee the intensity of locking and the shearing force when unblock.
The locking force to the airfoil is mainly determined by the structural strength of the connecting piece, and the structural strength of the connecting piece is not less than 30000N, so that the strong locking capability to the airfoil is ensured.
The actuator drives the connecting piece to move after working, the fixing pins of the connecting piece and the upper airfoil surface are sheared, the connecting piece withdraws from the locking groove aligned by the upper airfoil surface and the lower airfoil surface after moving for 5mm, the folding and unfolding mechanism is in an unlocking state, and the unlocking force is 800N-1200N, so that weak unlocking is realized.
The working principle of the device is as follows, referring to the description of the present embodiment shown in fig. 1 to 3: in the initial locking state, the connecting piece 2 of the mechanism is arranged in the locking groove 6 aligned with the upper airfoil surface 1 and the lower airfoil surface 3 and is clamped between the upper airfoil surface 1 and the lower airfoil surface 3, and the relative movement relationship of the upper airfoil surface 1 and the lower airfoil surface 3 is restrained; and then the fixing pin 4 is arranged in the locking pin holes of the upper airfoil surface 1 and the connecting piece 2, so that the connecting piece 2 does not axially move, and the whole mechanism is in a locking state. After the actuator 5 works, the connecting piece 2 is pushed to move, the fixing pin 4 is sheared, the connecting piece 2 slides in the locking grooves 6 of the upper wing surface 1 and the lower wing surface 3 for 5mm of travel and then withdraws from the locking grooves 6, the fixed constraint relation between the upper wing surface 1 and the lower wing surface 3 is released, and the relative movement can be carried out, so that the folding and unfolding mechanism is unlocked.
Compared with the prior art, the invention has large locking force and ensures that the folding and unfolding mechanism in the initial state is reliably locked; the unlocking force is small, and the mechanism is reliably unlocked by the small unlocking force. Through a large number of tests carried out in a real mechanism, the structure can ensure the reliable locking and unlocking of the wingspan mechanism, and has simple structure and easy engineering realization. The large locking force is not less than 30000N, and the weak unlocking force is 800N-1200N.
Claims (4)
1. Novel strong locking weak unlocking mechanism, its characterized in that: the mechanism consists of an actuator, a connecting piece, an upper airfoil surface, a lower airfoil surface and a fixed pin; the upper airfoil surface and the lower airfoil surface are provided with locking grooves, and in an initial working state, the upper airfoil surface and the lower airfoil surface are folded, and the two locking grooves are aligned; the connecting piece is arranged in the locking groove in a sliding way; pin holes corresponding to the positions of the upper airfoil surface and the connecting piece are arranged on the connecting piece; the fixing pin penetrates through the pin holes of the connecting piece and the upper airfoil surface to lock the positions of the upper airfoil surface, the lower airfoil surface and the connecting piece;
the structural strength of the connecting piece is not less than 30000N, so that the strong locking capability of the airfoil surface is ensured;
the structural strength of the fixing pin is 800N-1200N, and the actuator pushes the connecting piece to shear the fixing pin, so that weak unlocking is realized;
and the connecting piece is driven to move after the actuator works, the fixing pins of the connecting piece and the upper airfoil surface are sheared, and the connecting piece is withdrawn from the locking groove aligned by the upper airfoil surface and the lower airfoil surface.
2. The novel strong-locking weak-unlocking mechanism according to claim 1, wherein: the length of the connecting piece in the lock grooves of the upper airfoil surface and the lower airfoil surface is 5mm, so that the locking strength and the shearing force during unlocking are ensured.
3. The novel strong-locking weak-unlocking mechanism according to claim 1, wherein: the connecting piece is of a rectangular structure, and is made of alloy steel 30CrMnSiA with the thickness of 4.8mm.
4. The novel strong-locking weak-unlocking mechanism according to claim 1, wherein: the diameter of the fixing pin is 2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011521391.3A CN112665468B (en) | 2020-12-21 | 2020-12-21 | Novel strong locking and weak unlocking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011521391.3A CN112665468B (en) | 2020-12-21 | 2020-12-21 | Novel strong locking and weak unlocking mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112665468A CN112665468A (en) | 2021-04-16 |
| CN112665468B true CN112665468B (en) | 2023-08-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011521391.3A Active CN112665468B (en) | 2020-12-21 | 2020-12-21 | Novel strong locking and weak unlocking mechanism |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101875404A (en) * | 2009-12-17 | 2010-11-03 | 北京理工大学 | Sealed small low-impact release screw bolt |
| CN110972544B (en) * | 2010-12-23 | 2013-11-13 | 中国兵器工业第二0三研究所 | Device for unfolding, locking and connecting missile wing |
| CN204078065U (en) * | 2014-09-17 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | A kind of unmanned airplane empennage foldable structure |
| CN204775993U (en) * | 2015-04-29 | 2015-11-18 | 北京威标至远科技发展有限公司 | Wing device is folded to aircraft |
| CN107128478A (en) * | 2017-05-23 | 2017-09-05 | 安徽中科中涣防务装备技术有限公司 | A kind of fast unfolding device of folded wing |
| CN110873090A (en) * | 2019-10-29 | 2020-03-10 | 北京星际荣耀空间科技有限公司 | Strong-connection weak unlocking device |
| CN111121560A (en) * | 2019-12-25 | 2020-05-08 | 兰州空间技术物理研究所 | Rocket control surface folding and unfolding rotary driving device |
| WO2020174448A1 (en) * | 2019-02-28 | 2020-09-03 | Tubitak | Wing deployment and locking system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10150556B2 (en) * | 2016-05-23 | 2018-12-11 | The Boeing Company | Low-profile wing hinge mechanism |
-
2020
- 2020-12-21 CN CN202011521391.3A patent/CN112665468B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101875404A (en) * | 2009-12-17 | 2010-11-03 | 北京理工大学 | Sealed small low-impact release screw bolt |
| CN110972544B (en) * | 2010-12-23 | 2013-11-13 | 中国兵器工业第二0三研究所 | Device for unfolding, locking and connecting missile wing |
| CN204078065U (en) * | 2014-09-17 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | A kind of unmanned airplane empennage foldable structure |
| CN204775993U (en) * | 2015-04-29 | 2015-11-18 | 北京威标至远科技发展有限公司 | Wing device is folded to aircraft |
| CN107128478A (en) * | 2017-05-23 | 2017-09-05 | 安徽中科中涣防务装备技术有限公司 | A kind of fast unfolding device of folded wing |
| WO2020174448A1 (en) * | 2019-02-28 | 2020-09-03 | Tubitak | Wing deployment and locking system |
| CN110873090A (en) * | 2019-10-29 | 2020-03-10 | 北京星际荣耀空间科技有限公司 | Strong-connection weak unlocking device |
| CN111121560A (en) * | 2019-12-25 | 2020-05-08 | 兰州空间技术物理研究所 | Rocket control surface folding and unfolding rotary driving device |
Non-Patent Citations (1)
| Title |
|---|
| 基于SimMechanics的折叠翼展开机构动力学仿真与试验分析;邓红林等;《中国科技论文》;20151130(第22期);第2620页 * |
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| CN112665468A (en) | 2021-04-16 |
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