CN216443817U - Automatic locking device based on suspension integral lifting - Google Patents
Automatic locking device based on suspension integral lifting Download PDFInfo
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- CN216443817U CN216443817U CN202122927329.0U CN202122927329U CN216443817U CN 216443817 U CN216443817 U CN 216443817U CN 202122927329 U CN202122927329 U CN 202122927329U CN 216443817 U CN216443817 U CN 216443817U
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Abstract
The utility model belongs to the technical field of airborne suspension control, and particularly relates to an automatic locking device based on integral lifting of a suspended object, which comprises a locking component, a lifting component, a positioning component and a suspension interface; the locking component is provided with a locking hook component which is in a pincer shape and is connected with the positioning component, and the positioning component moves to open and close the locking hook component; the lifting assembly is connected with the lifting suspension interface, the suspension interface contacts the positioning assembly to enable the positioning assembly to move, the two sides of the suspension interface are locked with the closed locking hook assembly in a shape matching mode, one-time hanging and mounting can be achieved, manual burden is relieved, potential safety hazards in hanging and mounting operation are eliminated, and airplane operational use efficiency is improved.
Description
Technical Field
The utility model belongs to the technical field of airborne suspension control, and particularly relates to an automatic locking device based on integral lifting of a suspended object.
Background
The reliable butt joint and locking of the weapon suspension launching device and the mechanical interface of the airplane are the prerequisites for realizing the suspension carrying, launching and launching of the weapon by the airplane, and the installation butt joint form and the locking degree of the mechanical interface between the airplane and the frame play an important role in the weapon suspension carrying capacity of the airplane, the weapon suspension operation efficiency and the weapon launching reliability.
In the existing airplane design, the operation modes of manual lower lifting, manual operation, single-point butting and step-by-step installation and locking are adopted for the hanging operation of weapons in the airplane body, maintenance and guarantee personnel need to stand below the airplane body in the hanging mode, the weapons to be installed are hung and launched devices are lifted manually, bolt/screw butting and fastening of mechanical interfaces between the weapon hung and launched devices and the airplane are completed in a narrow operation space in a manual mode, then installation and butting and interface locking of the weapons and the weapon hung and launched devices are completed by means of ground guarantee equipment, a plurality of weapons are hung and installed, and repeated operation of the personnel is needed. The machine/frame mechanical interface in the existing weapon hanging operation has the following problems: 1. the weapon suspension launching device is installed in a lower lifting mode, and due to the limitation of the internal space of the airplane body, an area with inaccessible manual sight exists, the condition of installation and butt joint in place cannot be observed, and the risk of damage to the structure of the airplane body exists in related installation operation; 2. the single-point butt joint mode is adopted, the number of installation interfaces on the machine is large, the maintenance operation is complex, the requirement on the operation and maintenance space is high, maintenance personnel need to operate and maintain for many times, and potential safety hazards exist when the maintenance personnel are located below a suspended object; 3. the butt joint and the locking operation are carried out manually, the reliability of the installation and locking of the mechanical interface between the machine/the frame is difficult to guarantee, and the installation gap exists between the machine/the frame, so that an initial disturbance factor can be formed for weapon emission, and the control of the emission attitude is not facilitated.
SUMMERY OF THE UTILITY MODEL
In order to solve the problems, the application provides an automatic locking device based on the integral lifting of a suspended object, which is characterized by comprising a locking assembly, a lifting assembly and a suspension interface;
the locking component is provided with a locking hook component which is in a pincer shape and comprises two states of opening pincers and closing pincers;
the lifting assembly is connected with a lifting suspension interface, the suspension interface contacts the locking assembly to enable the locking hook assembly to move from the opening clamp to the closing clamp, and the locking hook assembly clamps the suspension interface when the clamping clamp is closed.
Preferably, the locking assembly further comprises a positioning assembly, the locking hook assembly is connected with the positioning assembly through a link mechanism, the lifting assembly contacts the positioning assembly and enables the positioning assembly to displace, and the displacement of the positioning assembly enables the locking hook assembly to move from the opening clamp to the closing clamp.
Preferably, the locking hook assembly comprises two locking hooks which are mirror images, the middle parts of the two locking hooks are hinged to the lifting assembly, one ends of the two locking hooks are hinged to the connecting rod mechanism, and the other ends of the two locking hooks are hook-shaped.
Preferably, the lifting assembly includes a motor, a drum assembly connected to the motor, the drum assembly having a first lifting cable and a second lifting cable, the first lifting cable and the second lifting cable being connected to two sides of the hanging interface, respectively.
Preferably, the linkage mechanism and positioning assembly comprise a rack and pinion connection.
Preferably, the locking assembly has a microswitch controlled by the position of the lifting assembly, the microswitch controlling the lifting assembly to stop when the lifting assembly is raised to a predetermined position.
Preferably, the suspension interface has a groove corresponding to the shape of the positioning component at the contact position with the positioning component.
Preferably, the contact end of the positioning component and the suspension interface is in a contraction shape.
Preferably, two locking hooks are in an 'F' shape, the tail end of the hanging interface extends towards two ends to form a boss, and the boss is matched with the 'F' end of each locking hook in a shape.
Preferably, the lifting component directly contacts the locking hook component during lifting, and the lifting component displaces to enable the locking hook component to be contacted from the opening clamp to the closing clamp.
The advantages of the present application include: due to the adoption of the weapon hanging scheme of integral automatic lifting, the repeated operation of single multiple hanging and butt joint in the traditional weapon hanging operation is reduced, and the use maintainability of the weapon hanging maintenance operation is improved; the mechanical interface at the upper part of the suspension object and the interface at the hanging point of the airplane are designed into an automatic locking butt joint mode, so that one-time hanging can be realized, the manual burden is reduced, the potential safety hazard in hanging operation is eliminated, and the operational efficiency of the airplane is improved.
Drawings
Fig. 1 is a front view of an automatic locking device based on the overall lifting of a suspension;
FIG. 2 is a top view of the automatic locking device based on the lifting of the entire suspension;
FIG. 3 is a locked state of the automatic locking device based on the lifting of the entire suspension;
fig. 4 is an unlocked state of the automatic locking device based on the lifting of the whole of the suspension;
FIG. 5 is a schematic view of the motor and reel assembly.
Wherein, 1-locking component, 2-lifting component, 3-positioning component, 4-locking hook component, 5-link mechanism, 6-winding drum component, 7-pulley component, 8-first lifting steel cable, 9-second lifting steel cable, 10-motor, and 11-suspension interface.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
A weapon hanging and installing technology based on the integral lifting of a suspended object and the automatic locking of an aircraft mechanical interface comprises two groups of locking and lifting systems. Each group of locking lifting systems comprises a group of locking components 1, a group of lifting components 2 and a group of positioning components 3 which are installed and integrated together through fasteners such as bolts and the like.
The locking assembly 1 is internally provided with a pair of locking hooks 4, and the locking state and the unlocking state are realized through the movement of an internal link mechanism 5. The butt joint locking part interface of the locking hook 4 is matched with the mechanical interface at the upper part of the suspension.
The hoist assembly 2 comprises 1 motor 10, 1 drum assembly 6, 1 pulley assembly 7 and 1 first hoist cable 8 and 1 set of second hoist cables 9. The motor 10 and the drum assembly 6 are nested together, the first lifting steel cable 8 and the second lifting steel cable 9 are wound in the lifting steel cable slot on the drum assembly 6, and the lifting interface end of the second lifting steel cable 9 is pulled to the pulley assembly 7, and the lifting interface end interface form of the first lifting steel cable 8 and the second lifting steel cable 9 is designed to be matched with the lifting interface on the suspension object. Through the rotation of motor 10, drive the rotation of reel subassembly 6, drive the winding or the release of first lifting steel cable 8 and second lifting steel cable 9 then, realize that the first lifting steel cable 8 and the second lifting steel cable 9's promotes the interface end position vertical rising and descend.
The two groups of locking lifting systems are respectively arranged on a bearing frame beam structure in the airplane body as installed components. When the combined bullet rack is used, firstly, the weapon suspension launching device and a weapon are subjected to butt joint and combined assembly of mechanical/electrical interfaces to form a bullet rack assembly, and the combined and assembled bullet rack assembly is conveyed to a proper position below an aircraft weapon hanging point; the connection between the lifting steel cable joint on the lifting component 2 and the lifting interface of the elastic frame assembly is manually finished; the motor 10 is driven and controlled to start and work through electrical equipment and drives the winding drum component 6 to rotate, the first lifting steel cable 8 and the second lifting steel cable 9 are wound on the winding drum component, the bullet frame assembly (suspension) is lifted to a certain height, and the horizontal stable lifting of the bullet frame assembly (suspension) is realized through the coordination of corresponding software algorithm programs configured in the motor 10 in the front/rear groups of lifting components arranged on the machine in the lifting process; after the bullet frame assembly (suspension) is lifted to a certain height, the positioning hole of the upper mechanical interface is firstly contacted with the positioning component 3 to start positioning and butt joint, and the horizontal guide of the butt joint position of the bullet frame assembly (suspension) is completed through the conical structure shape of the positioning component 3 so as to ensure that the bullet frame assembly (suspension) has an accurate and stable lifting track to enter the locking component 1; after the mechanical interface at the upper part of the elastic frame assembly enters the locking assembly 1, the mechanical interface is in physical contact with a locking hook 4 in the locking assembly 1 along with continuous lifting, and meanwhile, a rotating force is applied to the locking hook 4, so that the locking hook 4 automatically rotates to a locking position under the action of a link mechanism 5 in the locking assembly 1; the locking component 1 is provided with a corresponding microswitch, the contact between the lifting and the microswitch of the elastic frame assembly (the suspension) and the contact between the microswitch and the locking position of the locking hook 4 respectively indicate that the elastic frame assembly (the suspension) is lifted to be in place and locked to be in place, and simultaneously, the motor 10 in the lifting component 2 stops working after the elastic frame assembly (the suspension) is locked to be in place according to the two in-place signals fed back by the software algorithm program.
The utility model solves the maintainability problem existing in the weapon hanging and mounting by adopting a manual or semi-manual mode, provides a weapon hanging and mounting technology that a mechanical interface between a hanging object in a fuselage and a fuselage structure of an airplane can be automatically locked and fixed, and adopts the ground to finish the combined assembly of a weapon hanging and launching device and a bullet rack of a weapon to be hung in advance, so as to carry out the hanging and mounting of the bullet rack combined whole, thereby reducing the number of mounting interfaces of hanging points on the airplane and the operation steps of dismounting and mounting; after the bullet frame assembly is hung and loaded to be close to the hanging point structure, hanging, positioning and automatic locking and fastening of the bullet frame assembly and the airplane hanging point structure are automatically completed, manual operation is reduced, weapon hanging and loading use efficiency is improved, and potential safety hazards are eliminated.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. An automatic locking device based on the integral lifting of a suspended object is characterized by comprising a locking assembly (1), a lifting assembly (2) and a suspension interface (11);
the locking assembly (1) is provided with a locking hook assembly (4), the locking hook assembly (4) is in a clamp shape, and the locking hook assembly (4) comprises two states of opening a clamp and closing the clamp;
the lifting assembly (2) is connected with a lifting suspension interface (11), the suspension interface (11) is in contact with the locking assembly (1), the locking hook assembly (4) is enabled to move from the open clamp to the closed clamp, and when the locking hook assembly (4) is in a closed clamp state, the locking hook assembly (4) clamps the suspension interface (11).
2. The automatic locking device based on the integral lifting of the suspension object as claimed in claim 1, wherein the locking assembly (1) further comprises a positioning assembly (3), the locking hook assembly (4) is connected with the positioning assembly (3) through a link mechanism (5), the lifting assembly (2) contacts the positioning assembly (3) and displaces the positioning assembly (3), and the displacement of the positioning assembly (3) causes the locking hook assembly (4) to move from the open jaw to the closed jaw.
3. The automatic locking device based on the integral lifting of the suspension according to claim 2, characterized in that the locking hook component (4) comprises two locking hooks which are mirror images of each other, the middle parts of the two locking hooks are hinged on the lifting component (2), one ends of the two locking hooks are hinged with the link mechanism (5), and the other ends of the two locking hooks are hook-shaped.
4. The automatic locking device based on the integral lifting of the suspended object as claimed in claim 1, wherein the lifting assembly (2) comprises a motor (10), and a drum assembly (6) connected to the motor (10), the drum assembly (6) has a first lifting steel cable (8) and a second lifting steel cable (9), and the first lifting steel cable (8) and the second lifting steel cable (9) are respectively connected to two sides of the suspension interface (11).
5. The automatic locking device based on the integral lifting of the suspended object as claimed in claim 2, wherein the link mechanism (5) is connected with the positioning assembly (3) through a rack and pinion.
6. The automatic locking device based on the lifting of the whole of the suspension according to claim 1, characterized in that the locking assembly (1) has a microswitch controlled by the position of the lifting assembly (2).
7. The automatic locking device based on the integral lifting of the suspended object as claimed in claim 1, wherein the contact part of the suspension interface (11) and the positioning component (3) is provided with a groove corresponding to the shape of the positioning component (3).
8. The automatic locking device based on the integral lifting of the suspended object as claimed in claim 1, wherein the contact end of the positioning component (3) and the suspension interface (11) is in a contraction shape.
9. The automatic locking device based on the integral lifting of the hanging object as claimed in claim 3, wherein the two locking hooks are in an 'F' shape, the tail end of the hanging interface (11) extends towards the two ends to form a boss, and the boss is matched with the 'F' end of the locking hook in a shape.
10. The automatic locking device based on the integral lifting of the suspension object as claimed in claim 1, wherein the lifting component (2) directly contacts the locking hook component (4) during the lifting process, and the lifting component (2) is displaced to enable the locking hook component (4) to be contacted from the opening clamp to the closing clamp.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122927329.0U CN216443817U (en) | 2021-11-24 | 2021-11-24 | Automatic locking device based on suspension integral lifting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122927329.0U CN216443817U (en) | 2021-11-24 | 2021-11-24 | Automatic locking device based on suspension integral lifting |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216443817U true CN216443817U (en) | 2022-05-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122927329.0U Active CN216443817U (en) | 2021-11-24 | 2021-11-24 | Automatic locking device based on suspension integral lifting |
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| CN (1) | CN216443817U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115092399A (en) * | 2022-05-25 | 2022-09-23 | 兰州万里航空机电有限责任公司 | Airborne suspension device lifting system |
-
2021
- 2021-11-24 CN CN202122927329.0U patent/CN216443817U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115092399A (en) * | 2022-05-25 | 2022-09-23 | 兰州万里航空机电有限责任公司 | Airborne suspension device lifting system |
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