Turnover type unplugging mechanism

Abstract

The utility model provides a turnover type unplugging mechanism. The turnover type unplugging mechanism comprises a body, the body is rotatably connected to the front end of the transition rotating arm, the rear end of the transition rotating arm is rotatably connected to the rotating arm, a baffle is fixed to the position below the connecting point of the body and the transition rotating arm, an electric connector is installed at the lower end of the baffle, the rear end of the electric connector is fixed to the lower end of the rotating arm, and a lock is arranged on the baffle and used for locking and inserting the electric connector into an aircraft electric socket. The electric connector is of a pure mechanical structure and is high in reliability, good in integrity, light in weight, convenient to install and adjust and capable of achieving reliable plug-in connection of the electric connector and a socket on an aircraft in a limited space. The unplugging and plugging mechanism can be locked by the straight pin lock after being reset, so that the unplugging and plugging mechanism is prevented from being ablated by gas flow of the aircraft after reciprocating motion, the use requirements of the aircraft are met, and the requirements of economy, manufacturability, practicability and operability are met.

Description

Technical Field

[0001] The utility model relates to a flip-type plugging and unplugging mechanism, belonging to the technical field of mechanical design and manufacturing. Background Art

[0002] At present, the unplugging structural modes of the electrical connector between the aircraft and the storage and transportation box are mainly divided into two types: unplugging along the axial direction of the aircraft and unplugging along the radial direction of the aircraft. When the electrical connector is installed at the tail of the aircraft, axial unplugging can be realized by using the movement of the aircraft itself. Considering problems such as the installation space at the tail, the direct ablation of the electrical connector by the gas flow, it is difficult to solve the problems of limited installation space at the tail and the electrical connector being pulled out from the electrical socket of the aircraft and automatically rotating counterclockwise, resulting in easy ablation by the gas flow of the aircraft and poor reliability. Content of the Utility Model

[0003] To solve the above technical problems, the utility model provides a flip-type plugging and unplugging mechanism, which can meet the requirements of plugging and unplugging separation of electrical connectors of different models of aircraft. The response speed of plugging and unplugging separation is fast, the installation height can be adjusted by adjusting gaskets, the mechanism is stable and reliable, and it can realize the radial unplugging of the aircraft and the electrical connector and the reliable plugging of the electrical connector and the socket on the aircraft under limited space conditions.

[0004] The utility model is realized through the following technical solutions.

[0005] A flip-type plugging and unplugging mechanism provided by the utility model includes a body; the body is rotatably connected to the front end of a transition swing arm, the rear end of the transition swing arm is rotatably connected to a swing arm, a baffle is fixed at a position below the connection point of the body and the transition swing arm, an electrical connector is installed at the lower end of the baffle, the rear end of the electrical connector is fixed to the lower end of the swing arm, and there is a lock on the baffle for locking the electrical connector to be plugged into the electrical socket of the aircraft.

[0006] A tension spring is connected to the front end of the body and the transition swing arm on the body.

[0007] The body is connected to the transition swing arm through a rotating shaft.

[0008] The connection structures of the body, the transition swing arm and the swing arm form an L shape.

[0009] A torsion spring is sleeved on the rotating shaft for resetting.

[0010] There is a locking hook on the baffle for cooperating with the lock to lock.

[0011] A top screw for pressing against the baffle passes through and is threadedly engaged with the swing arm.

[0012] The electrical connector is connected to the swing arm through a connecting screw.

[0013] A direct-sale lock is installed on the baffle to limit the rotation of the transition swing arm.

[0014] The beneficial effects of the present utility model are as follows: The pure mechanical structure has high reliability, good integrity, light weight, and high reliability. It mainly consists of three springs and two rotating pairs, which are convenient for installation and adjustment; it can realize the reliable insertion of the limited-space electrical connector and the socket on the aircraft; after the plugging and unplugging mechanism is reset, it can be locked by the direct-sale lock to prevent it from being ablated by the aircraft gas flow after reciprocating motion; it can ensure the unplugging requirements of the storage box and the electrical connector while avoiding the direct ablation of the electrical connector by the gas flow generated by the aircraft, meeting the usage needs of the aircraft and conforming to the requirements of economy, processability, practicability, and operability. Description of the Drawings

[0015] Figure 1 is a schematic structural diagram of at least one embodiment of the present invention;

[0016] Figure 2 is Figure 1 the top view of

[0017] Figure 3 is Figure 1 the three-dimensional structural diagram of

[0018] In the figure: 1 - electrical connector, 2 - locking hook, 3 - baffle, 4 - body, 5 - tension spring, 6 - direct-sale lock, 7 - rotating shaft, 8 - transition swing arm, 9 - torsion spring, 10 - tightening screw, 11 - swing arm, 12 - lock, 13 - connecting screw. Detailed Embodiments

[0019] The technical solutions of the present utility model are further described below, but the scope of protection is not limited thereto.

[0020] Embodiment 1

[0021] As Figures 1 to 3 shown, a flip-type plugging and unplugging mechanism includes a body 4; the body 4 is rotatably connected to the front end of a transition swing arm 8, the rear end of the transition swing arm 8 is rotatably connected to a swing arm 11, a baffle 3 is fixed at a position below the connection point of the body 4 and the transition swing arm 8, an electrical connector 1 is installed at the lower end of the baffle 3, the rear end of the electrical connector 1 is fixed to the lower end of the swing arm 11, and a lock 12 is provided on the baffle 3 for locking the electrical connector 1 to be inserted into the aircraft electrical socket.

[0022] Embodiment 2

[0023] Based on Embodiment 1, a tension spring 5 is provided on the body 4 and is connected to the front end of the body 4 and the transition swing arm 8.

[0024] Furthermore, the body 4 is connected to the transition swing arm 8 through a rotating shaft 7.

[0025] Furthermore, the connection structure of the main body 4, the transition swing arm 8, and the swing arm 11 forms an L shape.

[0026] Furthermore, a torsion spring 9 is sleeved on the rotating shaft 7 for resetting.

[0027] Embodiment 3

[0028] Based on Embodiment 1, a locking hook 2 is provided on the baffle 3 for cooperating with the lock 12 for locking.

[0029] Furthermore, a tightening screw 10 that passes through and is threadedly engaged with the swing arm 11 and presses against the baffle 3 is provided.

[0030] Furthermore, the electrical connector 1 is connected to the swing arm 11 by a connecting screw 13.

[0031] Furthermore, a straight pin lock 6 is installed on the baffle 3 for limiting the rotation of the transition swing arm 8.

[0032] Embodiment 4

[0033] Based on the above embodiments, after the aircraft is loaded into the storage and transportation box and reliably locked by the locking mechanism, the baffle 3 is installed. After the baffle is installed, the locking hook 2 is adjusted to ensure reliable contact between the locking hook and the aircraft; the plugging and unplugging mechanism is operated to insert the electrical connector 1 into the electrical socket of the aircraft, and the lock 12 is reliably locked by the locking hook 2 to ensure the plugging of the electrical connector 1 and the electrical socket of the aircraft; the connecting screw 13 is adjusted to continue inserting the electrical connector 1 into the electrical socket of the aircraft and ensure that the gap is less than 2.5 mm; the tightening screw 10 is adjusted to contact the baffle 3 to eliminate the longitudinal gap of the plugging and unplugging mechanism and prevent the plugging and unplugging mechanism from vibrating longitudinally during transportation; after the aircraft ignites and moves forward, the locking hook 2 rotates clockwise along the rotating shaft to release the constraint on the lock 12, and the plugging and unplugging mechanism is unlocked. Under the action of the elastic force of the tension spring 5 and the torsion spring 9, the plugging and unplugging mechanism pulls out the electrical connector 1 from the electrical socket of the aircraft and rotates counterclockwise. After the plugging and unplugging mechanism is reset, it is locked by the straight pin lock 6 to prevent it from being eroded by the gas flow of the aircraft after reciprocating movement.

[0034] After verification, it can meet the requirements of the plugging and unplugging separation of electrical connectors for different models of aircraft. The response speed of the plugging and unplugging separation is fast, the installation height can be adjusted by adjusting the gasket, the mechanism is stable and reliable, and it can realize the radial pulling-off of the aircraft and the electrical connector and the reliable plugging of the electrical connector and the upper socket on the aircraft under limited space conditions. In addition, after the plugging and unplugging mechanism is reset, it is locked by the straight pin lock to prevent it from being eroded by the gas flow of the aircraft after reciprocating movement, without affecting the launch of the aircraft.

Claims

1. A flip - type plug - in and unplugging mechanism, comprising a body (4), characterized in that: The body (4) is rotatably connected to the front end of the transition arm (8), and the rear end of the transition arm (8) is rotatably connected to the arm (11). A baffle (3) is fixed at a position below the connection point of the body (4) and the transition arm (8). An electrical connector (1) is installed at the lower end of the baffle (3), and the rear end of the electrical connector (1) is fixed to the lower end of the arm (11). A lock (12) is provided on the baffle (3) for locking and plugging the electrical connector (1) into the aircraft electrical socket.

2. The flip-type insertion and extraction mechanism according to claim 1, characterized in that: A tension spring (5) is provided on the body (4) and is connected to the front end of the body (4) and the transition arm (8).

3. The flip-type insertion and extraction mechanism according to claim 1, wherein: The body (4) is connected to the transition arm (8) through a rotating shaft (7).

4. The flip-type insertion and extraction mechanism according to claim 1, wherein: The connection structure of the body (4), the transition arm (8), and the arm (11) forms an L shape.

5. The flip-in and out mechanism according to claim 3, characterized in that: A torsion spring (9) is sleeved on the rotating shaft (7) for resetting.

6. The flip-type insertion and extraction mechanism according to claim 1, wherein: A locking hook (2) is provided on the baffle (3) for cooperating with the lock (12) for locking.

7. The flip-type insertion and extraction mechanism according to claim 1, characterized in that: A top screw (10) that passes through and is threadedly engaged with the baffle (3) is provided on the arm (11).

8. The flip - type insertion and extraction mechanism according to claim 1, wherein: The electrical connector (1) is connected to the arm (11) through a connection screw (13).

9. The flip - type insertion and extraction mechanism according to claim 1, wherein: A direct sales lock (6) is installed on the baffle (3) for limiting the rotation of the transition arm (8).

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