CN115060124B - Portable missile wing locking device of commonality - Google Patents
Portable missile wing locking device of commonality Download PDFInfo
- Publication number
- CN115060124B CN115060124B CN202210808048.XA CN202210808048A CN115060124B CN 115060124 B CN115060124 B CN 115060124B CN 202210808048 A CN202210808048 A CN 202210808048A CN 115060124 B CN115060124 B CN 115060124B
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- Prior art keywords
- clamping mechanism
- button
- locking
- missile wing
- box body
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- 230000007246 mechanism Effects 0.000 claims abstract description 93
- 230000005540 biological transmission Effects 0.000 claims abstract description 18
- 230000008054 signal transmission Effects 0.000 claims abstract description 14
- 230000008602 contraction Effects 0.000 claims abstract description 11
- 230000000903 blocking effect Effects 0.000 claims description 25
- 230000001960 triggered effect Effects 0.000 claims description 5
- 230000009471 action Effects 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 4
- 208000012260 Accidental injury Diseases 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Clamps And Clips (AREA)
Abstract
The invention relates to a missile wing locking device, in particular to a universal portable missile wing locking device. A universal portable missile wing locking device comprises a locking mechanism, wherein the locking mechanism comprises a box body, an operation panel, a signal transmission unit, a transmission mechanism and a clamping mechanism; the operation panel is arranged on the side surface of the box body and is used as an operation port of an operator; the signal transmission unit is arranged in the box body and used for transmitting an operation instruction of an operator to the transmission mechanism; the transmission mechanism is arranged in the box body and provides power for contraction and expansion of the clamping mechanism; the clamping mechanism is arranged below the box body, and the missile wing is nested in the clamping mechanism. The invention has the following advantages: 1) The universality of the device is reflected; 2) Realizing accurate control of locking force; 3) Portable carrying is realized; 4) The stress of the locking device can be displayed in real time; 5) The accident injury of personnel is effectively avoided.
Description
Technical Field
The invention relates to a missile wing locking device, in particular to a universal portable missile wing locking device.
Background
In recent years, along with the continuous development of missile technology, missiles start to develop towards the trend of intelligence, miniaturization and power. However, missile wingspan opening type missiles have large occupied space, missile wings are easy to collide, the development of miniaturization cannot be met, and the cost of the missiles in the guarantee process can be increased. Through the method of folding missile wings, researchers find that the volume of the missile in the transportation and storage processes can be reduced, interference with other hanging points can be avoided when the missile is hung on an airplane, and other hanging points can be fully utilized. This is particularly true in air-to-surface missiles and ground box launch. Therefore, the method of folding the missile wing can be successfully applied to various types of missiles rapidly.
The missile wing is folded before the missile is launched, and the missile wing is pushed open under the action of the actuating cylinder after the missile is launched, so that the pneumatic performance required by the missile during the missile flight is realized. But also with the occurrence of another problem during its safeguarding: under a complex electrostatic environment, the actuator cylinder is easy to accidentally trigger to cause the missile wingspan to open, so that surrounding technicians are accidentally injured, and particularly, after missile technology is changed, workers cannot stand around the missile wing, so that follow-up work is difficult to perform. The outfield staff often uses sticky tape, electrical tape or twine to bind the missile wing to this prevents that the unexpected expansion of missile wing from accidentally injuring the staff, so not only can't effectively prevent that the unexpected trigger of missile wing from expanding, and can have certain threat to the safety of staff. Therefore, it is of great importance to study a portable generic missile wing locking device.
Disclosure of Invention
The invention aims to provide a universal portable missile wing locking device which can lock a missile wing and ensure personal safety of staff.
In order to achieve the above purpose, the present invention adopts the following technical scheme: a universal portable missile wing locking device comprises a locking mechanism, wherein the locking mechanism comprises a box body, an operation panel, a signal transmission unit, a transmission mechanism and a clamping mechanism; the operation panel is arranged on the side surface of the box body and is used as an operation port of an operator; the signal transmission unit is arranged in the box body and used for transmitting an operation instruction of an operator to the transmission mechanism; the transmission mechanism is arranged in the box body and provides power for contraction and expansion of the clamping mechanism; the clamping mechanism is arranged below the box body, and the missile wing is nested in the clamping mechanism.
Preferably, the transmission mechanism comprises a motor driver, a self-locking motor, a rack and a gear; the motor driver receives the signal sent by the signal transmission unit, so as to control the rotating speed and the rotating direction of the self-locking motor; the output shaft of the self-locking motor is connected with the gear and is used for driving the gear to rotate; the gear is meshed with the rack; the racks are arranged at the bottom of the box body and can move under the action of the gears, and the number of the racks is two and the racks are oppositely arranged; the clamping mechanism is mounted on the rack and moves with the rack.
Preferably, a pressure sensor is arranged on the surface, facing the missile wing, of the clamping mechanism, the pressure sensor is connected with a display unit through a computing unit, and the computing unit is used for converting acting force acquired by the pressure sensor into digital quantity to be displayed on the display unit; the display unit is arranged on the side surface of the box body and used for displaying the contraction or expansion state of the clamping mechanism.
Preferably, the signal transmission unit comprises a signal acquisition module and a signal processing module; when an operator operates the operation panel, the signal acquisition module acquires the operation signal of the operation panel in real time, the operation signal is processed by the signal processing module, and the processed signal is transmitted into the transmission mechanism.
Preferably, the display unit comprises an LED display and an indicator light; the LED display is used for displaying a pressure change value in real time, when the pressure value exceeds a locking threshold value, the indicator light displays yellow to indicate that the missile wing is locked, and when the pressure value is greater than an unfolding threshold value, the indicator light displays red to indicate that the actuating cylinder is triggered, and an operator performs corresponding emergency plan processing.
Preferably, the operation panel comprises a power switch button, a charging socket, a locking button, a release button, a reset button and a full release button; the locking button is used for realizing the contraction of the clamping mechanism; the release button is used for realizing the opening of the clamping mechanism; the reset button is used for recovering the clamping mechanism to an initial position; the full release button is used to achieve maximum release of the clamping mechanism.
Preferably, the locking button comprises a locking rough adjusting button and a locking fine adjusting button, the locking rough adjusting button is used for rapidly realizing shrinkage of the clamping mechanism, and the locking fine adjusting button is used for realizing fine adjustment shrinkage of the clamping mechanism; the release button comprises a release rough button and a release fine button, the release rough button is used for realizing the quick release of the clamping mechanism, and the release fine button is used for slowly releasing the clamping mechanism.
Further, the secondary locking mechanism comprises a spring, a blocking plate, a cam and a safety pin, wherein the upper end of the spring is locked on the box body through a fixed shaft, and the lower end of the spring is connected with the blocking plate; the upper end of the blocking plate is contacted with the cam, and the lower end of the blocking plate is positioned above the rack; the center of the cam is limited with the box body through the fixed shaft and can rotate around the fixed shaft; when the spring is at the initial position, the space between the fixed shaft and the upper end of the blocking plate is smaller than the maximum radius of the cam; a safety pin inserting opening is formed in the box body, and when the safety pin is inserted into the safety pin inserting opening, the cam is pushed to rotate, so that the blocking plate is inserted into the rack space.
Preferably, the blocking plate is T-shaped.
Preferably, the number of the springs is two, and the springs are distributed on two sides of the cam.
Working principle: the self-locking characteristic of the self-locking motor is adopted, so that the gear rack is pushed to drive when the missile wing is accidentally unfolded, and the self-locking motor is further driven to rotate; on the other hand, the clamping mechanism is prevented from being pushed away by the missile wing by inserting the safety pin, the cam is pushed to rotate when the safety pin is inserted, the cam rotates to drive the blocking plate to move downwards, the blocking plate is inserted into the space between racks when moving downwards, the rotation of the racks is blocked, the movement of the missile wing pushing the clamping mechanism can be further prevented, and when the safety pin is pulled out, the spring is reset to pull the blocking plate to move upwards, and then the cam is pushed to rotate, so that the safety pin is restored to the original position.
Compared with the prior art, the invention has the following advantages:
1) According to the gear rack transmission principle, the opening size of the clamping mechanism is adjusted, and the locking device can tighten and release aiming at different types of missile wings, so that the universality of the device is reflected;
2) The locking degree of the clamping mechanism can be directly controlled through an external button, and coarse adjustment buttons and fine adjustment buttons are arranged to realize accurate control of locking force;
3) The locking function of the missile wing can be realized only by operating the button, the operation is simple and convenient, and the portable carrying is realized by a charging power supply mode;
4) The LED digital display can display the stress of the collected locking device in real time and judge whether the missile wing is accidentally unfolded or not;
5) The accident injury of personnel is effectively avoided, and after the missile wing actuating cylinder is installed, related work can be normally carried out without avoiding.
Drawings
FIG. 1 is a schematic diagram of an embodiment of the present invention;
FIG. 2 is a schematic diagram of an embodiment of the present invention;
FIG. 3 is a schematic view of an operation panel according to an embodiment of the present invention;
FIG. 4 is a schematic view of a secondary locking mechanism according to an embodiment of the present invention;
FIG. 5 is a side view of FIG. 4;
in fig. 1 to 5, 1, an operation panel; 2. a self-locking motor; 3. a motor driver; 5. an LED display; 6. a signal acquisition module; 7. a signal processing module; 8. a pressure sensor; 9. a calculation unit; 10. a clamping mechanism; 11. a gear; 12. rack, 13, cam, 14, safety pin inserting port; 15. a spring; 16. a blocking plate; 17. a spring fixing shaft; 18. a button; 19. a power switch; 20. an indicator light; 21. a case; 22. and a charging socket.
Description of the embodiments
In this embodiment, the terms "upper", "lower", and the like are described in accordance with the drawings, and do not limit the present invention.
The invention is further described in detail below with reference to fig. 1-5: a general portable missile wing locking device comprises a locking mechanism and a secondary locking mechanism; the locking mechanism comprises a box body 21, an operation panel 1, a signal transmission unit, a transmission mechanism and a clamping mechanism; the operation panel is arranged on the side surface of the box body and is used as an operation port of an operator; the signal transmission unit is arranged in the box body and used for transmitting an operation instruction of an operator to the transmission mechanism; the transmission mechanism is arranged in the box body and provides power for contraction and expansion of the clamping mechanism; the clamping mechanism is arranged below the box body, and the missile wing is nested in the clamping mechanism.
The specific structure is as follows:
as shown in fig. 1-3, the transmission mechanism comprises a motor driver 3, a self-locking motor 2, a rack 12 and a gear 11; the motor driver 3 receives signals sent by the signal transmission unit, so that the rotating speed and the rotating direction of the self-locking motor 2 are controlled; an output shaft of the self-locking motor 2 is connected with a gear 11 and is used for driving the gear to rotate; the gear 11 is meshed with the rack 12; the racks 12 are arranged at the bottom of the box body 21 and can move under the action of the gears 11, and the two racks are oppositely arranged, namely, the two racks 12 are positioned on the same horizontal line; the clamping mechanism 10 is mounted on the rack 12 for movement therewith; the racks 12 are oppositely arranged, so that the opening distance of the clamping mechanism can be ensured to the greatest extent, the missile wings of different sizes are nested in the clamping mechanism, and the locking of multiple missile wings is completed;
the pressure sensor 8 is arranged on the clamping mechanism and locks the clamping mechanism on the movable rack 12, the two racks are oppositely arranged, the rotation of the motor can drive the gear 11 to rotate, the gear can further drive the rack to move, and the movement of the rack can control the tightening and releasing of the clamping mechanism. Specifically, a pressure sensor 8 is installed on the surface of the clamping mechanism 10 facing the missile wing, the pressure sensor 8 is connected with a display unit through a calculating unit 9, and the calculating unit 9 is used for converting acting force acquired by the pressure sensor 8 into digital quantity to be displayed on the display unit; the display unit is arranged on the side surface of the box body 21 and used for displaying the contracted or expanded state of the clamping mechanism 10;
the display unit comprises an LED display 5 and an indicator light 20; the LED display 5 is used for displaying a pressure change value in real time, when the pressure value exceeds a locking threshold T1, the indicator light is yellow to indicate that the missile wing is locked, and when the pressure value is greater than a unfolding threshold T2, the indicator light is red to indicate that the actuator cylinder is triggered, and an operator performs corresponding emergency plan processing;
the signal transmission unit comprises a signal acquisition module 6 and a signal processing module 7; when an operator operates the operation panel, the signal acquisition module 6 acquires operation signals of the operation panel in real time, the operation signals are processed by the signal processing module 7, and the processed signals are transmitted into the motor driver 3;
the operation panel 1 comprises a power switch 19, a charging socket 22 and a button 18, wherein the button comprises a locking button, a release button, a reset button and a full release button; the power switch 19 is used to power up the whole device; the charging socket 22 is used for charging the rechargeable battery; the locking button is used for realizing the contraction of the clamping mechanism and comprises a locking rough adjusting button and a locking fine adjusting button, the locking rough adjusting button is used for rapidly realizing the contraction of the clamping mechanism, and the locking fine adjusting button is used for realizing the fine adjustment contraction of the clamping mechanism; the release button is used for realizing the opening of the clamping mechanism and comprises a release rough button and a release fine button, wherein the release rough button is used for realizing the rapid release of the clamping mechanism, and the release fine button is used for slowly releasing the clamping mechanism; the reset button is used for recovering the clamping mechanism to an initial position; the full release button is used to achieve maximum release of the clamping mechanism.
The secondary locking mechanism comprises a spring 15, a blocking plate 16, a cam 13 and a safety pin, wherein the upper end of the spring 15 is locked on the box body 21 through a spring fixing shaft 17, and the lower end of the spring is connected with the blocking plate 16; the upper end of the blocking plate 16 is contacted with the cam 13, and the lower end is positioned above the rack 12; the center of the cam 13 is limited by a spring fixing shaft 17 and a box 21 and can rotate around the spring fixing shaft 17; when the spring 15 is at the initial position, the distance between the spring fixing shaft 17 and the upper end of the blocking plate 16 is smaller than the maximum radius of the cam 13, namely, the distance between the center of the cam 13 and the upper end face of the blocking plate 16 is between the minimum radius and the maximum radius; the safety pin inserting opening 14 is formed in the box body 21, and when the safety pin is inserted into the safety pin inserting opening 14, the cam is pushed to rotate, so that the blocking plate 16 is inserted into the space between the racks 12;
in this embodiment, the blocking plate is T-shaped, and a reinforcing rib is additionally provided between the horizontal plate and the vertical plate.
In the present embodiment, the number of springs 15 is two, and the springs are distributed on both sides of the cam 13.
Working principle: pressing an external power switch 19, and powering up the device; when the operation panel button 18 is pressed, the signal acquisition module 6 acquires the pulse voltage of the button in real time, performs validity processing on the acquired voltage, and transmits the processed signal to the motor driver 3, so as to control the rotating speed and the rotating direction of the self-locking motor 2. The full release button is then pressed and the clamping mechanism 10 is opened to a maximum spacing, nesting the missile wing in the clamping mechanism. When the locking coarse adjustment button and the locking fine adjustment button are pressed, the clamping mechanism starts to shrink towards the middle, when the pressure sensor 8 on the clamping mechanism touches the missile wing, the LED display 5 starts to display the change value of the pressure in real time, and when the pressure exceeds the locking threshold T1, the indicator light displays yellow to indicate that the missile wing is locked.
The external secondary locking mechanism is realized by adopting a mode of a safety pin, and plays a role of a protection device. When the safety pin is inserted, the device does not work; the locking device can be operated only by pulling out the safety pin. When the indicator light is yellow, a safety pin is inserted to perform secondary locking. After secondary locking, an operator can normally develop work, and after the operator finishes working on the missile, the safety pin is pulled out, and the locking device is taken down.
When the locking device is taken down, the clamping device can be rapidly opened only by pressing a released rough adjusting button or a full releasing button, and the locking device can be taken down after the clamping device is opened at a specific interval.
When the actuating cylinder on the missile wing is accidentally triggered, the pressure sensor 8 receives larger impact force, the impact force is transmitted to the computing unit 9 through an electric signal, an abrupt pressure value is displayed on the LED display screen 5, according to logic calculation, if the generated pressure is greater than the unfolding threshold T2, the indicator light is displayed in red, the actuating cylinder is triggered, and an operator performs corresponding emergency plan processing.
The above examples are only preferred embodiments of the present invention and do not limit the present invention. Any extension, modification, etc. made by those skilled in the art without departing from the principles of the present invention should be included in the scope of the present invention.
Claims (10)
1. A general portable missile wing locking device is characterized in that: the locking mechanism comprises a box body, an operation panel, a signal transmission unit, a transmission mechanism and a clamping mechanism; the operation panel is arranged on the side surface of the box body and is used as an operation port of an operator; the signal transmission unit is arranged in the box body and used for transmitting an operation instruction of an operator to the transmission mechanism; the transmission mechanism is arranged in the box body and provides power for contraction and expansion of the clamping mechanism; the clamping mechanism is arranged below the box body, and the missile wing is nested in the clamping mechanism.
2. The universal portable missile wing locking device according to claim 1, wherein: the transmission mechanism comprises a motor driver, a self-locking motor, a rack and a gear; the motor driver receives the signal sent by the signal transmission unit, so as to control the rotating speed and the rotating direction of the self-locking motor; the output shaft of the self-locking motor is connected with the gear and is used for driving the gear to rotate; the gear is meshed with the rack; the racks are arranged at the bottom of the box body and can move under the action of the gears, and the number of the racks is two and the racks are oppositely arranged; the clamping mechanism is mounted on the rack and moves with the rack.
3. A universal portable missile wing locking device according to claim 1 or 2, wherein: the pressure sensor is arranged on the surface of the clamping mechanism facing the missile wing, and is connected with the display unit through the calculation unit, and the calculation unit is used for converting acting force acquired by the pressure sensor into digital quantity to be displayed on the display unit; the display unit is arranged on the side surface of the box body and used for displaying the contraction or expansion state of the clamping mechanism.
4. A universal portable missile wing locking device according to claim 1 or 2, wherein: the signal transmission unit comprises a signal acquisition module and a signal processing module; when an operator operates the operation panel, the signal acquisition module acquires the operation signal of the operation panel in real time, the operation signal is processed by the signal processing module, and the processed signal is transmitted into the transmission mechanism.
5. A universal portable missile wing locking device according to claim 3, wherein: the display unit comprises an LED display and an indicator lamp; the LED display is used for displaying a pressure change value in real time, when the pressure value exceeds a locking threshold value, the indicator light displays yellow to indicate that the missile wing is locked, and when the pressure value is greater than an unfolding threshold value, the indicator light displays red to indicate that the actuating cylinder is triggered, and an operator performs corresponding emergency plan processing.
6. The universal portable missile wing locking device according to claim 1, wherein: the operation panel comprises a power switch button, a charging socket, a locking button, a release button, a reset button and a full release button; the locking button is used for realizing the contraction of the clamping mechanism; the release button is used for realizing the opening of the clamping mechanism; the reset button is used for recovering the clamping mechanism to an initial position; the full release button is used to achieve maximum release of the clamping mechanism.
7. The universal portable missile wing locking device according to claim 6, wherein: the locking button comprises a locking rough adjusting button and a locking fine adjusting button, the locking rough adjusting button is used for rapidly realizing the shrinkage of the clamping mechanism, and the locking fine adjusting button is used for realizing the fine adjustment shrinkage of the clamping mechanism; the release button comprises a release rough button and a release fine button, the release rough button is used for realizing the quick release of the clamping mechanism, and the release fine button is used for slowly releasing the clamping mechanism.
8. The universal portable missile wing locking device according to claim 1, wherein: the secondary locking mechanism comprises a spring, a blocking plate, a cam and a safety pin, wherein the upper end of the spring is locked on the box body through a fixed shaft, and the lower end of the spring is connected with the blocking plate; the upper end of the blocking plate is contacted with the cam, and the lower end of the blocking plate is positioned above the rack; the center of the cam is limited with the box body through the fixed shaft and can rotate around the fixed shaft; when the spring is at the initial position, the space between the fixed shaft and the upper end of the blocking plate is smaller than the maximum radius of the cam; a safety pin inserting opening is formed in the box body, and when the safety pin is inserted into the safety pin inserting opening, the cam is pushed to rotate, so that the blocking plate is inserted into the rack space.
9. The universal portable missile wing locking device according to claim 8, wherein: the blocking plate is T-shaped.
10. The universal portable missile wing locking device according to claim 1, wherein: the number of the springs is two, and the springs are distributed on two sides of the cam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210808048.XA CN115060124B (en) | 2022-07-08 | 2022-07-08 | Portable missile wing locking device of commonality |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210808048.XA CN115060124B (en) | 2022-07-08 | 2022-07-08 | Portable missile wing locking device of commonality |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115060124A CN115060124A (en) | 2022-09-16 |
| CN115060124B true CN115060124B (en) | 2023-11-03 |
Family
ID=83206309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210808048.XA Active CN115060124B (en) | 2022-07-08 | 2022-07-08 | Portable missile wing locking device of commonality |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115060124B (en) |
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| US20210063114A1 (en) * | 2018-09-04 | 2021-03-04 | Raytheon Company | Aircraft armament system control electronics |
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| CN115060124A (en) | 2022-09-16 |
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