CN216488729U - Airborne vehicle electric connector flap locking mechanism - Google Patents
Airborne vehicle electric connector flap locking mechanism Download PDFInfo
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- CN216488729U CN216488729U CN202122706530.6U CN202122706530U CN216488729U CN 216488729 U CN216488729 U CN 216488729U CN 202122706530 U CN202122706530 U CN 202122706530U CN 216488729 U CN216488729 U CN 216488729U
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- connecting rod
- transmission connecting
- plate spring
- locking mechanism
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Abstract
The utility model belongs to the field of airborne aircrafts, and particularly relates to a locking mechanism for a turnover cover of an airborne aircraft electric connector, in particular to a locking mechanism for a turnover cover of an airborne aircraft electric connector with large turnover cover angle, sealing requirement and stealth requirement. The cover locking mechanism comprises a lower plate spring buckle (5), and an upper plate spring buckle (3) is arranged on the cover (2); when the electric connector port of the aircraft is separated from the carrier, the upper plate spring buckle (3) falls into the lower plate spring buckle (5) to realize the locking of the port cover (2) under the action of the aerodynamic force and the inertial force of the port cover.
Description
Technical Field
The utility model belongs to the field of airborne aircrafts, and particularly relates to a locking mechanism for a turnover cover of an airborne aircraft electric connector, in particular to a locking mechanism for a turnover cover of an airborne aircraft electric connector with large turnover cover angle, sealing requirement and stealth requirement.
Background
The airborne aircraft electric connector plug is generally provided with a protective opening cover which can turn over or slide in order to meet the environmental requirements of sand prevention, dust prevention, water prevention and the like; to ensure that the flap can reliably perform its protective function when needed, such flaps are usually provided with a hold-down or locking mechanism.
At present, the cover locking mechanism of the electric connector plug is most commonly a torsion spring mechanism. The torsion spring mechanism has the characteristics of simple structure, low cost and convenient installation. But when driving flap through the torsional spring and compressing tightly the sealing washer and realize sealing, the sealing washer is close to the packing force that one end of torsional spring receives great, and the compression volume is great, and the packing force that one end receives of keeping away from the torsional spring is less, and the compression volume is less, and the influence that causes has: 1) the sealing effect is poor, and the risk of sealing failure exists; 2) there is the jump in flap and aircraft surface, influences the stealthy effect of structure.
SUMMERY OF THE UTILITY MODEL
The purpose of the utility model is that: the utility model provides an airborne vehicle electric connector flap locking mechanism to solve among the current flap hold-down mechanism that sealed effect is not good, the great problem that is unfavorable for structure stealth of flap jump.
The technical scheme is as follows: on one hand, the cover locking mechanism of the electric connector cover of the airborne aircraft comprises a lower plate spring buckle 5, and an upper plate spring buckle 3 is arranged on a cover 2; when the aircraft electric connector port breaks away from the carrier, under the action of aerodynamic force and inertial force of the port cover, the upper plate spring buckle 3 falls into the lower plate spring buckle 5 to realize locking of the port cover 2.
On the other hand, another onboard aircraft electric connector cover locking mechanism is provided, and the cover locking mechanism comprises an electromagnet 11, an upper transmission connecting rod 9 and a lower transmission connecting rod 12; the upper transmission connecting rod 9 and the lower transmission connecting rod 12 are connected through a magnetic rotating shaft 10; the upper transmission connecting rod 9 is rotatably connected with the connecting rod mounting bracket 14 or the aircraft; one end of the lower transmission connecting rod 12 is connected with a connecting rod mounting bracket 14 in a sliding way through a movement guide pin 13;
when the electric connector port of the aircraft is separated from the aircraft, under the action of aerodynamic force and inertial force of the port cover, the port cover 2 falls into the electric connector port sealing ring, the electromagnet 11 is electrified, and the lower transmission connecting rod 12 is pushed to press the upper plate spring buckle 3 arranged on the port cover 2.
Optionally, the lower transmission link 12 is in a hook-shaped structure, and the middle part of the lower transmission link 12 is hinged with the upper transmission link 9.
Optionally, a guide groove is arranged on the connecting rod mounting bracket 14, and the lower end of the lower transmission connecting rod 12 is slidably connected to the guide groove through a movement guide pin 13; the lower transmission connecting rod 12 can realize rotation and translation under the driving of the electromagnet.
Optionally, the cover locking mechanism further comprises a lower plate spring buckle 5, under the action of aerodynamic force and inertial force of the cover, the cover is turned over, and when the upper plate spring buckle 3 is in contact with the lower plate spring buckle 5 and the lower transmission connecting rod 12 presses the upper plate spring buckle 3; under the drive of the electromagnet, the lower transmission connecting rod 12 drives the upper plate spring buckle 3 to move downwards and fall into the lower plate spring buckle 5.
Optionally, the flap locking mechanism further comprises a return spring, one end of the return spring is connected with the upper transmission connecting rod 9 and the connecting rod mounting bracket 14 through the connecting rotating shaft, and the other end of the return spring is connected with the upper end of the lower transmission connecting rod 12, so that the lower transmission connecting rod 12 is reset after the electromagnet 11 is powered off.
The technical effects are as follows: the sealing rubber ring of the electric connector can be uniformly compressed by locking the upper plate spring buckle 3 and the lower plate spring buckle 5 and symmetrically tensioning the cover rotating shaft 4; by designing the compression amount of the rubber ring, the step difference between the cover 1 and the surface of the missile body of the airborne aircraft can be effectively controlled; thereby improving the reliability of sealing of the flap 1 and improving the concealing property of the edge of the flap 1.
Drawings
FIG. 1 is an isometric view of a flap in an open state;
FIG. 2 is an elevation view of the electromagnetic drive and locking mechanism;
fig. 3 is a front view of the locking mechanism locked in place.
Detailed Description
Example 1
In the embodiment, the electric connector port cover locking mechanism of the airborne aircraft is provided, and comprises a lower plate spring buckle 5 and a port cover 2, wherein an upper plate spring buckle 3 is arranged on the port cover 2; when the aircraft electric connector port breaks away from the carrier, under the action of aerodynamic force and inertial force of the port cover, the upper plate spring buckle 3 falls into the lower plate spring buckle 5 to realize locking of the port cover 2.
Example 2
In this embodiment, another onboard aircraft electrical connector cover locking mechanism is provided, where the cover locking mechanism includes an electromagnet 11, an upper transmission link 9, a lower transmission link 12, and a lower plate spring buckle 5; the upper transmission connecting rod 9 and the lower transmission connecting rod 12 are connected through a magnetic rotating shaft 10; the upper transmission connecting rod 9 is rotatably connected with the connecting rod mounting bracket 14 or the aircraft; one end of the lower transmission connecting rod 12 is connected with a connecting rod mounting bracket 14 in a sliding way through a movement guide pin 13;
when the electric connector port of the aircraft is separated from the aircraft, under the action of aerodynamic force and inertial force of the port cover, the port cover 2 falls into the electric connector port sealing ring, the electromagnet 11 is electrified, and the lower transmission connecting rod 12 is pushed to press the upper plate spring buckle 3 arranged on the port cover 2.
Under the action of aerodynamic force and inertial force of the cover cap, the cover cap is turned over, and when the upper plate spring buckle 3 is in contact with the lower plate spring buckle 5 and the lower transmission connecting rod 12 presses the upper plate spring buckle 3; under the drive of the electromagnet, the lower transmission connecting rod 12 drives the upper plate spring buckle 3 to move downwards and fall into the lower plate spring buckle 5.
In this embodiment, the lower transmission link 12 is a hook-shaped structure, and the middle of the lower transmission link 12 is hinged to the upper transmission link 9. The connecting rod mounting bracket 14 is provided with a guide groove, and the lower end of the lower transmission connecting rod 12 is connected with the guide groove in a sliding way through a movement guide pin 13; the lower transmission connecting rod 12 can realize rotation and translation under the driving of the electromagnet.
Furthermore, the flap locking mechanism further comprises a return spring, one end of the return spring is connected with the upper transmission connecting rod 9 and the connecting rod mounting bracket 14 through the connecting rotating shaft, and the other end of the return spring is connected with the upper end of the lower transmission connecting rod 12, so that the lower transmission connecting rod 12 is reset after the electromagnet 11 is powered off. In the attached drawings 1 and 2, a spring hook 8 is arranged at the position where the upper transmission connecting rod 9 and the connecting rod mounting bracket 14 are connected with the rotating shaft, and the other spring hook 8 is arranged at the upper end of the lower transmission connecting rod 12 and is used for connecting a return spring. When the locking opening cover and the electromagnet are powered off, the spring pulls the lower transmission connecting rod 12 to realize the reset of the lower transmission connecting rod 12.
The installation process of each part of this embodiment:
the upper plate spring buckle 3 and the cover 2 are riveted to realize installation; and the cover rotating shaft penetrates through the sealing washer, the base shaft hole, the tightening nut and the cover lug shaft hole, and then the tightening nut is screwed up to realize installation.
The shaft hole of the upper transmission connecting rod 9 penetrates through a boss of a connecting rod mounting bracket 14, the magnetic rotating shaft 10 with a flange sequentially penetrates through the shaft holes of the upper transmission connecting rod 9 and the lower transmission connecting rod 12, a nut is screwed into the thread of the magnetic rotating shaft 10, a 0.5mm gap is reserved, the upper transmission connecting rod 9, the lower transmission connecting rod 12 and the magnetic rotating shaft 10 are limited, the bottom hole of the lower transmission connecting rod 12 is aligned with a motion guide groove of the connecting rod mounting bracket 14, and a motion guide pin 13 is driven into the bottom hole.
And sequentially riveting the lower plate spring buckle 5, the electromagnet 11 and the connecting rod mounting bracket 14 provided with the upper transmission connecting rod 9 and the lower transmission connecting rod 12 on the base.
The working process of the embodiment:
as shown in fig. 2, in an initial locking state, the electromagnet 11 is energized, the upper transmission connecting rod 9 is driven to rotate by repulsive force with the magnetic rotating shaft 10, and the movable magnetic rotating shaft 10 moves in two directions to the right and downwards by the guidance of the movement guide pin 13 and the translation and rotation of the lower transmission connecting rod 12; when the lower transmission connecting rod 12 supporting arm moves rightwards, the upper plate spring buckle 3 is hooked, the opening cover 1 is driven to move downwards, until the convex shoulder of the upper plate spring buckle 3 falls into the groove of the lower plate spring buckle 5, the opening cover 1 is locked, and the uniformity of the pressing force of the rubber ring and the smoothness of the edge of the opening cover and the outer surface of the cabin body are ensured.
When the lower plate spring buckle 5 locks the opening cover and the electromagnet is powered off, the spring pulls the lower transmission connecting rod 12 to realize the reset of the lower transmission connecting rod 12.
Claims (6)
1. The locking mechanism of the electric connector port cover of the airborne aircraft is characterized by comprising a lower plate spring buckle (5), wherein an upper plate spring buckle (3) is arranged on a port cover (2); when the electric connector port of the aircraft is separated from the carrier, the upper plate spring buckle (3) falls into the lower plate spring buckle (5) to realize the locking of the port cover (2) under the action of the aerodynamic force and the inertial force of the port cover.
2. The locking mechanism of the electric connector port cover of the airborne aircraft is characterized by comprising an electromagnet (11), an upper transmission connecting rod (9) and a lower transmission connecting rod (12); the upper transmission connecting rod (9) and the lower transmission connecting rod (12) are connected through a magnetic rotating shaft (10); the upper transmission connecting rod (9) is rotationally connected with the connecting rod mounting bracket (14) or the aircraft; one end of the lower transmission connecting rod (12) is connected with the connecting rod mounting bracket (14) in a sliding way through a movement guide pin (13);
when the electric connector port of the aircraft is separated from the aircraft, under the action of aerodynamic force and inertial force of the port cover, the port cover (2) falls into the electric connector port sealing ring, the electromagnet (11) is electrified to push the lower transmission connecting rod (12) to press the upper plate spring buckle (3) arranged on the port cover (2).
3. The airborne aircraft electrical connector flap locking mechanism of claim 2 wherein the lower drive link (12) is of hook-like configuration, the middle portion of the lower drive link (12) being hinged to the upper drive link (9).
4. The aircraft electrical connector flap locking mechanism of claim 2 wherein the link mounting bracket (14) is provided with a guide slot to which the lower end of the lower drive link (12) is slidably connected by a motion guide pin (13); the lower transmission connecting rod (12) can realize rotation and translation under the driving of the electromagnet.
5. The aircraft electrical connector flap locking mechanism of claim 4 further comprising a lower leaf spring catch (5), wherein under the action of aerodynamic and inertial forces of the flap, the flap is flipped when the upper leaf spring catch (3) contacts the lower leaf spring catch (5) and the lower drive link (12) presses the upper leaf spring catch (3); under the drive of the electromagnet, the lower transmission connecting rod (12) drives the upper plate spring buckle (3) to move downwards and fall into the lower plate spring buckle (5).
6. The aircraft electrical connector flap locking mechanism of claim 5, further comprising a return spring, one end of the return spring is connected with the upper transmission connecting rod (9) and the connecting rod mounting bracket (14) through the connecting shaft, and the other end of the return spring is connected with the upper end of the lower transmission connecting rod (12) for realizing the return of the lower transmission connecting rod (12) after the electromagnet (11) is powered off.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122706530.6U CN216488729U (en) | 2021-11-05 | 2021-11-05 | Airborne vehicle electric connector flap locking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122706530.6U CN216488729U (en) | 2021-11-05 | 2021-11-05 | Airborne vehicle electric connector flap locking mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216488729U true CN216488729U (en) | 2022-05-10 |
Family
ID=81446219
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122706530.6U Active CN216488729U (en) | 2021-11-05 | 2021-11-05 | Airborne vehicle electric connector flap locking mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216488729U (en) |
-
2021
- 2021-11-05 CN CN202122706530.6U patent/CN216488729U/en active Active
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