CN209929237U - Relay for general aircraft - Google Patents

Abstract

The utility model discloses a general relay for aircraft, the on-line screen storage device comprises a base, the upper portion fixed mounting of base has the shell, the bottom fixed mounting of base has the stitch, the inside fixed mounting of shell has armature, one side of armature is close to bottom position fixed mounting and has lower connecting block, the inside fixed mounting of armature has the iron core coil, the inside of shell is located one side position fixed mounting of armature and has the pillar, the bottom fixed mounting of iron core coil has binding post, the top of armature moves the iron sheet through first hinge swing joint, the one end fixed mounting who moves the iron sheet has last connecting block. A general relay for aircraft, be equipped with go-between, hemisphere and recess, at first can avoid moving the phenomenon that the iron sheet kick-backs to appear, secondly can avoid when producing the vibration, transient separation phenomenon appears in static contact and moving contact.

Description

Relay for general aircraft

Technical Field

The utility model relates to a relay field, in particular to general relay for aircraft.

Background

The relay for the general airplane is a relay used on the general airplane, the relay is an electric control device, it is an electrical apparatus which makes the controlled quantity produce the predetermined step change in the electric output circuit when the change of the input quantity meets the stipulated requirement, it is a kind of "automatic switch" which uses the small current to control the large current to operate actually, it is a kind of control tool commonly used in the electric power system; rely on iron core coil outage back spring to pull away the movable contact from the static contact when the outage of relay, but the spring has elasticity, current relay only has a spring and the part that corresponds to cooperate and accomplishes the outage work, after the outage of iron core coil, a spring can be because the undulant phenomenon of resilience appears in inertia, can let the movable contact touch the static contact again, the phenomenon of instantaneous switch will appear like this, cause the damage to the power consumption setting easily, the security is not high, secondly, the contact surface of movable contact and static contact is the plane, if the external vibration that produces, probably lead to transient phenomenon of breaking away from, the result of use is relatively poor.

SUMMERY OF THE UTILITY MODEL

The utility model discloses a main aim at provides a general relay for aircraft can effectively solve the xxxxxxxxx problem among the background art.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

a relay for a general airplane comprises a base, wherein a shell is fixedly mounted on the upper portion of the base, a pin is fixedly mounted at the bottom of the base, an armature is fixedly mounted inside the shell, a lower connecting block is fixedly mounted close to the bottom of one side of the armature, an iron core coil is fixedly mounted inside the armature, a pillar is fixedly mounted inside the shell at one side of the armature, a wiring terminal is fixedly mounted at the bottom of the iron core coil, a moving iron sheet is movably connected to the top of the armature through a first hinge, an upper connecting block is fixedly mounted at one end of the moving iron sheet, a first spring is arranged between the upper connecting block and the lower connecting block, a connecting ring is arranged between the moving iron sheet and the upper connecting block, a straight block portion is arranged at one end of the connecting ring, a second hinge is arranged in front of the connecting ring and the upper connecting block portion, and a second spring is movably mounted, the movable contact type switch is characterized in that a movable contact terminal is fixedly mounted on the upper portion of the movable iron sheet, a movable contact is fixedly mounted at one end of the movable contact terminal, a hemisphere is fixedly mounted at the lower portion of the movable contact, a fixed contact terminal is fixedly mounted at a position, close to the upper portion, of the rear portion of the support, a fixed contact is fixedly mounted at one end of the fixed contact terminal, and a groove is formed in the upper surface of the fixed contact.

Preferably, the connecting terminal is fixedly connected with the pin, and the output end of the connecting terminal is electrically connected with the input end of the iron core coil.

Preferably, the groove is matched with the hemispheroid, and a third hinge is arranged between the static contact terminal and the support.

Preferably, a mounting piece is fixedly mounted on one side of the shell, and a mounting hole is formed in the front surface of the mounting piece.

Preferably, the upper connecting block and the lower connecting block are arranged in parallel.

Compared with the prior art, the utility model discloses following beneficial effect has: the utility model discloses in, go-between through the setting, the one end fixed connection of go-between moves the iron sheet, be equipped with the second spring between the straight piece portion of the other end of go-between and the last connecting block, the second spring can supply the pulling force on the one hand, avoid moving the iron sheet and appearing the phenomenon of kick-backing because of inertia after iron core coil outage, on the other hand also can play the work load that reduces first spring, hemisphere and recess through setting up, hemisphere and recess phase-match, when moving contact and static contact, the hemisphere stretches into in the recess, the enlarged area of contact that can be better, avoid under the condition that vibrations appear, the phenomenon of short separation appears in moving contact and static contact, the practicality is higher.

Drawings

Fig. 1 is a schematic diagram of an overall structure of a general aircraft relay according to the present invention;

fig. 2 is a schematic diagram of an internal structure of a general aircraft relay according to the present invention;

fig. 3 is an enlarged view of a in fig. 2 of a general aircraft relay according to the present invention.

In the figure: 1. a base; 2. a housing; 3. mounting a sheet; 4. mounting holes; 5. a stitch; 6. an armature; 7. a lower connecting block; 8. an upper connecting block; 9. a first spring; 10. an iron core coil; 11. a pillar; 12. a wiring terminal; 13. a moving iron sheet; 14. a first hinge; 15. a connecting ring; 16. a straight block portion; 17. a second hinge; 18. a second spring; 19. a movable contact terminal; 20. a moving contact; 21. a hemisphere; 22. a stationary contact terminal; 23. static contact; 24. and (4) a groove.

Detailed Description

In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

As shown in fig. 1-3, a general aircraft relay includes a base 1, an outer casing 2 is fixedly mounted on the upper portion of the base 1, a pin 5 is fixedly mounted on the bottom of the base 1, an armature 6 is fixedly mounted inside the outer casing 2, a lower connecting block 7 is fixedly mounted on one side of the armature 6 close to the bottom, an iron core coil 10 is fixedly mounted inside the armature 6, a pillar 11 is fixedly mounted on one side of the armature 6 inside the outer casing 2, a connecting terminal 12 is fixedly mounted on the bottom of the iron core coil 10, a moving iron sheet 13 is movably connected to the top of the armature 6 through a first hinge 14, an upper connecting block 8 is fixedly mounted at one end of the moving iron sheet 13, a first spring 9 is arranged between the upper connecting block 8 and the lower connecting block 7, a connecting ring 15 is arranged between the moving iron sheet 13 and the upper connecting block 8, a straight block part 16 is arranged at one end of the connecting ring 15, a second hinge 17 is arranged in front of the connecting ring 15 and the upper connecting block 8, a second spring 18 is movably mounted at the upper part of the straight block part 16, a movable contact terminal 19 is fixedly mounted at the upper part of the movable iron sheet 13, a movable contact 20 is fixedly mounted at one end of the movable contact terminal 19, a hemisphere 21 is fixedly mounted at the lower part of the movable contact 20, a fixed contact terminal 22 is fixedly mounted at the position, close to the upper part, of the rear part of the strut 11, a fixed contact 23 is fixedly mounted at one end of the fixed contact terminal 22, and a groove 24 is formed in the upper surface of the fixed contact;

the connecting terminal 12 is fixedly connected with the pin 5, and the output end of the connecting terminal 12 is electrically connected with the input end of the iron core coil 10; the groove 24 is matched with the hemisphere 21, and a third hinge is arranged between the static contact terminal 22 and the pillar 11; a mounting piece 3 is fixedly mounted on one side of the shell 2, and a mounting hole 4 is formed in the front surface of the mounting piece 3; the upper connecting block 8 and the lower connecting block 7 are arranged in parallel.

It should be noted that, the utility model relates to a general purpose aircraft relay, when using, at first install the whole relay, when installing, use the external bolt to pass through the mounting hole 4 and utilize the installation piece 3 to fix the shell 2, then connect the binding post 12, the movable contact terminal 19, the stationary contact terminal 22 to the external power supply respectively, after the binding post 12 is electrified, the iron core coil 10 forms the magnetic field to adsorb the movable iron piece 13, thereby drive the movable contact 20 to contact with the static contact 23 through the movable contact terminal 19, the hemisphere 21 stretches into the inside of recess 24 at this moment, can increase the contact area of the movable contact 20 and the static contact 23, avoid the movable contact 20 and the static contact 23 producing the transient separation in the vibration, the practicality is higher, after the movable contact 20 and the static contact 23, the movable contact terminal 19 and the stationary contact terminal 22 have produced the circular telegram phenomenon, when people need to cut off the power supply, namely, the connecting terminal 12 can be powered off, the iron core coil 10 loses the magnetic field due to power failure after power failure, thereby the moving iron sheet 13 is released, then the moving iron sheet 13 is pulled and tilted through the first hinge 14 through the elastic force of the first spring 9, thereby the moving contact 20 and the static contact 23 are separated, the phenomenon of power failure is realized, when the first spring 9 rebounds, the second spring 18 also pulls the connecting ring 15 through the second hinge 17, thereby the connecting ring 15 also applies force to the moving iron sheet 13 to pull the moving iron sheet back, through the cooperation of the first spring 9 and the second spring 18, on one hand, after the iron core coil 10 is powered off, the moving contact 20 and the static contact 23 are contacted again due to inertia on the way of rebounding of the moving iron sheet 13, on the other hand, the working load of the first spring 9 can also be reduced, and the service life of the whole.

The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims (5)

1. A general relay for an aircraft is characterized in that: comprises a base (1), the upper portion fixed mounting of base (1) has shell (2), the bottom fixed mounting of base (1) has stitch (5), the inside fixed mounting of shell (2) has armature (6), one side of armature (6) is close to bottom position fixed mounting and has lower connecting block (7), the inside fixed mounting of armature (6) has iron core coil (10), one side position fixed mounting that the inside of shell (2) is located armature (6) has pillar (11), the bottom fixed mounting of iron core coil (10) has binding post (12), the top of armature (6) has moving iron sheet (13) through first hinge (14) swing joint, the one end fixed mounting of moving iron sheet (13) has last connecting block (8), it is equipped with first spring (9) to go up between connecting block (8) and lower connecting block (7), move and be equipped with go-between (15) between iron sheet (13) and last connecting block (8), the one end of go-between (15) is equipped with straight piece portion (16), go-between (15) and last connecting block (8) are equipped with second hinge (17) before, the upper portion movable mounting of straight piece portion (16) has second spring (18), the upper portion fixed mounting of moving iron sheet (13) has movable contact terminal (19), the one end fixed mounting of movable contact terminal (19) has movable contact (20), the lower part fixed mounting of movable contact (20) has hemispheroid (21), the rear portion of pillar (11) is close to top position fixed mounting and has stationary contact terminal (22), the one end fixed mounting of stationary contact terminal (22) has static contact (23), the upper surface of static contact (23) is seted up flutedly (24).

2. The relay for a general-purpose aircraft according to claim 1, wherein: binding post (12) and stitch (5) fixed connection, the output of binding post (12) is in the input electric connection of iron core coil (10).

3. The relay for a general-purpose aircraft according to claim 1, wherein: the groove (24) is matched with the hemispheroid (21), and a third hinge is arranged between the static contact terminal (22) and the strut (11).

4. The relay for a general-purpose aircraft according to claim 1, wherein: one side fixed mounting of shell (2) has installation piece (3), mounting hole (4) have been seted up to the front surface of installation piece (3).

5. The relay for a general-purpose aircraft according to claim 1, wherein: the upper connecting block (8) and the lower connecting block (7) are arranged in parallel.

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