CN108128472B

CN108128472B - Universal impact closer

Info

Publication number: CN108128472B
Application number: CN201711384326.9A
Authority: CN
Inventors: 石云陆
Original assignee: Guizhou Aerospace Electronic Technology Co Ltd
Current assignee: Guizhou Aerospace Electronic Technology Co Ltd
Priority date: 2017-12-20
Filing date: 2017-12-20
Publication date: 2020-12-04
Anticipated expiration: 2037-12-20
Also published as: CN108128472A

Abstract

The invention provides a universal impact closer which comprises a pressure spring, an inertia trigger piece, a ball, an upper contact pin, a welding column and a lower contact pin, wherein the upper contact pin is arranged on the lower contact pin; the inertia trigger piece is sleeved with a pressure spring, the lower end of the pressure spring is fixed at the bottom of the inertia trigger piece, a ball is placed on the bottom surface of the inertia trigger piece, the upper end of the inertia trigger piece extends into the lower end of the welding column, the inertia trigger piece is not in contact with the welding column in a balanced state, the ball is in electric contact with the lower contact pin, and the top end of the welding column is electrically connected with and fixed with the upper contact pin. The invention has the functions of large range of induction impact overload direction, wide range of impact overload and the like, meets the requirements of different use environments, has simple structure, small volume, convenient installation, light weight and high reliability, and is beneficial to the miniaturization design of aircrafts.

Description

Universal impact closer

Technical Field

The invention relates to a universal impact closer.

Background

In the launching and flying process of the aircraft, different types of closers are needed to be used for sensing overload or impact overload so as to perform the next action of the aircraft, the impact closers are important components of a certain trigger part and other safety parts in the aircraft, and the trigger part can be enabled to perform subsequent actions such as trigger action and the like only when the impact closers are closed. The traditional impact closer can close only by sensing the impact overload in front, has small range of sensing direction, and is difficult to meet the requirements of environments such as lateral over-impact closing and the like when an aircraft lands on the ground. In addition, the traditional impact closer is often large in design volume, complex in structure, heavy in weight and high in matching precision requirement, and the miniaturization development trend of an aircraft is difficult to meet.

1) The traditional universal mechanism can only point to the front direction of the aircraft, cannot detect the rear flying object or the flying objects on the left side and the right side, cannot react the rear flying object or the flying objects on the left side and the right side into corresponding systems, and cannot control and detect the rear flying object;

2) the traditional universal mechanism adopts a mechanical structure, and has the advantages of large designed volume, complex structure, heavy weight, more intermediate transmission links, high requirement on matching precision and lower response characteristic;

3) the closed-loop control system is complex and has low reliability.

Disclosure of Invention

In order to solve the technical problems, the invention provides the universal impact closer which can realize that a certain trigger part and other safety parts are applied to the aircraft to sense the overload impact force in different directions, simplify the structure, reduce the volume and the weight and meet the requirements of the miniaturization design of the aircraft and the overload impact in different directions.

The invention is realized by the following technical scheme.

The invention provides a universal impact closer which comprises a pressure spring, an inertia trigger piece, a ball, an upper contact pin, a welding column and a lower contact pin, wherein the upper contact pin is arranged on the lower contact pin; the inertia trigger piece is sleeved with a pressure spring, the lower end of the pressure spring is fixed at the bottom of the inertia trigger piece, a ball is placed on the bottom surface of the inertia trigger piece, the upper end of the inertia trigger piece extends into the lower end of the welding column, the inertia trigger piece is not in contact with the welding column in a balanced state, the ball is in electric contact with the lower contact pin, and the top end of the welding column is electrically connected with and fixed with the upper contact pin.

The ball is positioned at the center of the bottom of the inertia trigger piece.

The inertia trigger piece and the welding column are sleeved in the insulating sleeve, a step-shaped protrusion is arranged in the middle of the insulating sleeve between the inertia trigger piece and the welding column, and the upper end of the pressure spring is fixed on the step-shaped protrusion of the insulating sleeve.

The insulating sleeve is fixed in the shell, and the ball is arranged at the bottom in the shell.

And the top edge of the insulating sleeve is provided with an insulating adhesive, and the insulating sleeve is fixed on the shell through the insulating adhesive.

The lower contact pin is fixed outside the bottom end of the shell.

The inertia trigger piece and the pressure spring are coaxially arranged.

The invention has the beneficial effects that: the induction impact overload direction sensing device has the functions of large induction impact overload direction range, wide impact overload range and the like, meets different use environment requirements, and is simple in structure, small in size, convenient to install, light in weight, high in reliability and beneficial to miniaturization design of an aircraft.

Drawings

FIG. 1 is a schematic structural view of the present invention;

in the figure: the method comprises the following steps of 1-a shell, 2-an insulating sleeve, 3-a pressure spring, 4-an inertia trigger, 5-a ball, 6-an upper contact pin, 7-an insulating adhesive, 8-a welding column and 9-a lower contact pin.

Detailed Description

The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.

The universal impact closer shown in fig. 1 mainly comprises a shell 1, an insulating sleeve 2, a pressure spring 3, an inertia trigger 4, a ball 5, an upper contact pin 6, an insulating adhesive 7, a welding column 8 and a lower contact pin 9. The welding post 8 is pressed on the insulating sleeve 2, the ball 5, the inertia trigger piece 4 and the pressure spring 3 are sequentially arranged in the shell 1, the insulating sleeve 2 is arranged, the shell 1 is riveted on the end face, matched with the insulating sleeve 2, of the shell 1, the insulating sleeve 2 is fixed in the shell 1, and the riveting end face of the shell 1 is sealed by using an insulating adhesive 7 and the welding post 8 is fastened in a hole of the insulating sleeve 2. The upper pin 6 and the lower pin 9 are welded in the end surface groove of the welding column 8 and the bottom surface groove of the shell 1 respectively.

The inertia trigger piece 4 and the ball 5 are parts which can slide when the impact closer is impacted, the inertia trigger piece 4 has certain design quality, the inertia trigger piece 4 firstly senses various environmental stresses, and then whether the inertia trigger piece 4 slides or even triggers towards the welding column 8 is determined according to the resistance of the pressure spring 3.

Under the general state, the upper contact pin 6 and the lower contact pin 9 are not conducted, when the inertia trigger piece 4 slides into the hole of the welding column 8 under the action of the inertia force of front impact, the ball 5 at the bottom end of the inertia trigger piece 4 rotates under the action of slight lateral force, the inertia trigger piece 4 is communicated with the shell 1 through the ball 5, and the front end of the inertia trigger piece 4 is in close contact with the inner hole of the welding column 8, so that the upper contact pin 6 is conducted with the lower contact pin 9. When the inertia trigger piece 4 slides to the hole of the welding column 8 under the action of the inertia force of lateral impact, the bottom end of the inertia trigger piece 4 rotates around the ball 5, and the lateral side of the inertia trigger piece 4 is respectively in close contact with the inner hole wall matched with the shell 1 and the inner hole wall of the welding column 8, so that the upper contact pin 6 is communicated with the lower contact pin 9.

The action process of the impact closer is as follows: under the mechanical environment conditions of an initial aircraft and the aircraft, the resistance of the pressure spring is designed to be larger than various stresses borne by the inertia trigger piece and sliding in the direction of the welding column, so that the inertia trigger piece cannot slide into the hole of the welding column, and the safety of the aircraft is ensured; when the aircraft collides with a target in a preset direction, the impact inertia force borne by the inertia trigger is designed to be larger than the resistance force of the pressure spring, the inertia trigger slides to the position in the welding column hole under the action of the impact force, and a circuit channel is formed between the upper contact pin 6 and the lower contact pin 9.

Thus, the present invention:

1) the structure is simple, the volume is small, and the induction impact overload can be from several g to hundreds of g according to different use environments; the impact overload range is large;

2) the ball body is matched with the inertia trigger piece, so that the impact in different directions can be met, and the universal impact function can be realized by adopting the installation in a plurality of different directions in the use process;

3) and the design of pin connection is adopted, so that the direct welding is convenient to install on the printed board, and the assembly is convenient.

Claims

1. The utility model provides a universal impact closer, includes pressure spring (3), inertia trigger piece (4), ball (5), goes up contact pin (6), welding post (8), contact pin (9) down, its characterized in that: the cover has pressure spring (3) on inertia trigger spare (4), and pressure spring (3) lower extreme is fixed in inertia trigger spare (4) bottom, and ball (5) have been laid to the bottom surface of inertia trigger spare (4), and in inertia trigger spare (4) upper end extended to the lower extreme of welding post (8), and inertia trigger spare (4) and welding post (8) contactless under the balanced state, ball (5) electrical contact in lower contact pin (9), welding post (8) top electricity is connected and is fixed with last contact pin (6).

2. The gimbal impact closer of claim 1, wherein: the ball (5) is positioned at the center of the bottom of the inertia trigger piece (4).

3. The gimbal impact closer of claim 1, wherein: the inertia trigger piece (4) and the welding column (8) are sleeved in the insulating sleeve (2), a step-shaped protrusion is arranged in the middle of the insulating sleeve (2) between the inertia trigger piece (4) and the welding column (8), and the upper end of the pressure spring (3) is fixed on the step-shaped protrusion of the insulating sleeve (2).

4. The gimbal impact closer of claim 3, wherein: the insulating sleeve (2) is fixed in the shell (1), and the ball (5) is arranged at the bottom in the shell (1).

5. The gimbal impact closer of claim 4, wherein: the top edge of the insulating sleeve (2) is provided with an insulating adhesive (7), and the insulating sleeve (2) is fixed on the shell (1) through the insulating adhesive (7).

6. The gimbal impact closer of claim 4, wherein: the lower contact pin (9) is fixed outside the bottom end of the shell (1).

7. The gimbal impact closer of claim 1, wherein: the inertia trigger piece (4) and the pressure spring (3) are coaxially arranged.