Aircraft canopy lock switch

Abstract

The utility model relates to an aircraft canopy lock switch which comprises a microswitch, a socket and a shell, the microswitch and the socket are both fixedly connected with the shell, the microswitch and the socket are electrically connected through a wire, and the wire is contained in the shell. By adopting the technical scheme provided by the utility model, the microswitch and the socket are jointly arranged on the surface of the shell, and the shell stably supports the microswitch and the socket and effectively protects a connecting lead between the microswitch and the socket, so that reliable electrical connection between the microswitch and the socket is kept; when the microswitch needs to be replaced or maintained, the socket is directly separated from a corresponding plug arranged in the control system, and the microswitch is taken down, so that the maintenance operation is more convenient.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft canopy lock switches, in particular to an aircraft canopy lock switch. Background Art

[0002] The function of the aircraft canopy lock system is to lock the canopy securely to the fuselage structure, bear and transmit the canopy load, and ensure that there will be no accidental unlocking under various flight conditions. Therefore, keeping the aircraft canopy lock system stable and reliably locked is a key factor to ensure that there will be no accidental unlocking during the flight of the aircraft. In the prior art, an electronic switch element is usually set to detect whether the aircraft canopy lock is correctly locked. If the electronic switch element detects that the aircraft canopy lock is correctly locked, it will send a confirmation message to the aircraft control system. If the electronic switch element detects that the aircraft canopy lock is not correctly locked, it will send a corresponding warning message or error message to the aircraft control system. The travel switch is a common type of electronic switch element. The travel switch is a pressure-activated fast-transfer switch. Because the contact spacing of the switch is relatively small, the common travel switch generally includes a trigger device and an electrical switching device. The trigger device is used to transmit external force to the electrical switching device, and the electrical switching device is used to achieve the switching of the electrical connection state.

[0003] In the prior art, the patent document with the announcement number "CN217823554U" discloses a travel switch socket, including: a socket body, the socket body is installed in the area to be installed; and a travel switch, the travel switch is connected to the socket body through a wire, the travel switch is placed in the area to be triggered and is in an initial open or closed state, and the state is switched after the travel switch is triggered in the area to be triggered; the travel switch is non-self-locking, and the socket body can be powered or de-powered based on the current state of the travel switch. This patented technology realizes the control of power on or off of the socket body by closing the travel switch, effectively disconnects the power supply circuit between the mains and the load, and avoids the generation of standby loss. However, since the actuation stroke of the travel switch is very short, when the travel switch contact rod is pressed, it is easy to cause the travel switch to be in an overvoltage state, thereby causing the travel switch to fail, and the travel switch has a small size. In specific applications, the travel switch is generally connected to the aircraft control system through a wire. When the travel switch is damaged and needs to be replaced or repaired, the corresponding connecting wire needs to be disconnected, which is inconvenient for maintenance. Utility Model Content

[0004] In order to solve the above technical problems, the utility model provides an aircraft canopy lock switch.

[0005] The utility model provides an aircraft canopy lock switch, comprising a micro switch, a socket and a shell. The micro switch and the socket are both fixedly connected to the shell. The micro switch and the socket are also electrically connected by a wire, and the wire is accommodated in the shell.

[0006] The aircraft canopy lock switch also includes a paddle, and the micro switch includes a touch rod. One side of the paddle is fixedly connected to the micro switch, and the other side of the paddle is abutted against the outer end surface of the touch rod.

[0007] The middle portion of the plectrum is formed by at least one bending process.

[0008] The paddle is in a V-shape as a whole.

[0009] The aircraft canopy lock switch also includes a fuse and a plurality of bolts, wherein the bolts are used to securely connect the socket to the housing, and the two ends of the fuse are respectively wound around the outer circumferences of two adjacent bolts.

[0010] An inclination angle of the fuse between two adjacent bolts relative to a centroid line between the corresponding two adjacent bolts is greater than zero.

[0011] The number of the bolts is four.

[0012] The number of the micro switches is 2, and the two micro switches are fixedly connected in parallel to the same side surface of the housing.

[0013] The shell is also fixedly connected to the line card, and the wire is also clamped between the shell and the line card.

[0014] At least one side of the shell is set as an open side. The shell is also fixedly connected to the cover plate, and the cover plate covers the open side of the shell.

[0015] The beneficial effect of the utility model is that: by adopting the technical solution provided by the utility model, the micro switch and the socket are installed together on the surface of the shell, the shell stably supports the micro switch and the socket, and effectively protects the connecting wires between the micro switch and the socket, so that a reliable electrical connection is maintained between the micro switch and the socket. When the micro switch needs to be replaced or repaired, the socket is directly separated from the corresponding plug built into the control system, and the micro switch is removed, making the maintenance operation more convenient. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is the front view of the utility model;

[0017] Figure 2 It is a top view of the utility model;

[0018] Figure 3 This utility model Figure 1The main view after removing the cover;

[0019] Figure 4 It is the internal electrical principle diagram of the micro switch of the utility model.

[0020] In the figure: 1- micro switch, 2- socket, 3- housing, 4- wire, 5- paddle, 6- contact rod, 7- fuse, 8- bolt, 9- wire card, 10- cover plate. DETAILED DESCRIPTION

[0021] The technical solution of the utility model is further described below in conjunction with the accompanying drawings, but the claimed protection scope is not limited to the above;

[0022] The utility model provides an aircraft canopy lock switch, such as Figures 1 to 4 As shown, it includes a micro switch 1, a socket 2 and a housing 3. The micro switch 1 and the socket 2 are both fixedly connected to the housing 3. The micro switch 1 and the socket 2 are also electrically connected using a wire 4, and the wire 4 is accommodated in the housing 3.

[0023] By adopting the technical solution provided by the utility model, the micro switch and the socket are installed together on the surface of the shell. The shell stably supports the micro switch and the socket and effectively protects the connecting wires between the micro switch and the socket, so that a reliable electrical connection is maintained between the micro switch and the socket. When the micro switch needs to be replaced or repaired, the socket is directly separated from the corresponding plug built into the control system, and the micro switch is removed, making the maintenance operation more convenient.

[0024] Specifically, the aircraft canopy lock switch further includes a paddle 5, and the micro switch 1 includes a contact rod 6. One side of the paddle 5 is fixedly connected to the micro switch 1, and the other side of the paddle 5 is in contact with the outer end surface of the contact rod 6. The middle part of the paddle 5 is also bent at least once, so that the paddle 5 has appropriate elastic deformation capacity. Preferably, the paddle 5 is in a V-shape as a whole. When an operating force is applied to the paddle 5, the operating force is transmitted to the contact rod 6, so that the micro switch 1 is triggered to achieve the switching of the circuit connection state. In addition, the number of micro switches 1 is 2, and the two micro switches 1 are fixedly connected to the same side of the housing 3 in parallel, so that the operating force acting on the paddle 5 can be shared by the two micro switches 1, preventing the micro switch 1 from pressing too much, and in the case where one of the micro switches 1 fails, the other micro switch 1 can also remain effective to ensure reliable electrical connection.

[0025] In addition, the aircraft canopy lock switch further comprises a fuse 7 and a plurality of bolts 8, wherein the bolts 8 are used to securely connect the socket 2 and the housing 3, and the two ends of the fuse 7 are respectively wound around the outer circumferences of two adjacent bolts 8. Specifically, the inclination angle of the fuse 7 between two adjacent bolts 8 relative to the centroid connection line between the corresponding two adjacent bolts 8 is greater than zero, and the number of the bolts 8 is preferably 4. On the one hand, the fuse 7 maintains a stable relative position between the two adjacent bolts 8, and the relative position between the socket 2 and the housing 3 is kept stable and reliable. On the other hand, the fuse 7 is wound around the outer circumference of each bolt 8 for at least three quarters of a circle, which can prevent the bolt 8 from rotating due to the torque, thereby preventing the bolt 8 from loosening and maintaining a reliable secure connection between the socket 2 and the housing 3.

[0026] In addition, the housing 3 is also fixedly connected to the line card 9, and the wire 4 is also clamped between the housing 3 and the line card 9. At least one side of the housing 3 is set as an open side, and the housing 3 is also fixedly connected to the cover plate 10, and the cover plate 10 covers the open side of the housing 3. Specifically, the number of wires 4 is 3, such as Figure 4 As shown, the A end of the micro switch 1 is a normally open end, the B end of the micro switch 1 is a normally closed end, the C end of the micro switch 1 is a common end, the corresponding A ends of the two micro switches 1 are connected in parallel, the corresponding B ends of the two micro switches 1 are connected in parallel, and the corresponding C ends of the two micro switches 1 are connected in parallel. When an operating force is applied to the paddle 5, the normally closed end of the micro switch 1 is disconnected and the normally open end is closed, thereby realizing the switching of the circuit state.

Claims

1. An aircraft canopy lock switch, characterized in that: The invention comprises a micro switch (1), a socket (2) and a housing (3); the micro switch (1) and the socket (2) are both fixedly connected to the housing (3); the micro switch (1) and the socket (2) are also electrically connected via a wire (4); and the wire (4) is accommodated in the housing (3).

2. An aircraft canopy lock switch according to claim 1, characterized in that: The aircraft canopy lock switch further comprises a paddle (5), the micro switch (1) comprises a touch rod (6), one side of the paddle (5) is fixedly connected to the micro switch (1), and the other side of the paddle (5) is in contact with the outer end surface of the touch rod (6).

3. An aircraft canopy lock switch as claimed in claim 2, characterized in that: The middle part of the plectrum (5) is also formed by at least one bending process.

4. An aircraft canopy lock switch as claimed in claim 2 or 3, characterized in that: The plectrum (5) is in a V-shape as a whole.

5. The aircraft canopy lock switch according to claim 1, characterized in that: The aircraft canopy lock switch also includes a fuse (7) and a plurality of bolts (8), wherein the bolts (8) are used to securely connect the socket (2) and the housing (3), and the two ends of the fuse (7) are respectively wound around the outer circumferences of two adjacent bolts (8).

6. An aircraft canopy lock switch as claimed in claim 5, characterized in that: The inclination angle of the fuse (7) between two adjacent bolts (8) relative to the centroid line between the corresponding two adjacent bolts (8) is greater than zero.

7. An aircraft canopy lock switch according to claim 5 or 6, characterized in that: The number of the bolts (8) is 4.

8. The aircraft canopy lock switch according to claim 1, characterized in that: The number of the micro switches (1) is two, and the two micro switches (1) are fixedly connected in parallel to the same side surface of the housing (3).

9. The aircraft canopy lock switch according to claim 1, characterized in that: The housing (3) is also fixedly connected to the line card (9), and the wire (4) is also clamped between the housing (3) and the line card (9).

10. The aircraft canopy lock switch according to claim 1, characterized in that: At least one side of the shell (3) is arranged as an open side, and the shell (3) is also fixedly connected to the cover plate (10), and the cover plate (10) covers the open side of the shell (3).

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