CN114212267B - A single torsion spring energy-storage rotating cam safety switch mechanism for aircraft - Google Patents

Abstract

The invention relates to a single torsion spring energy storage rotary cam type safety switch mechanism of an aircraft, which comprises a rotating shaft, a torsion spring, a cam, an electric micro switch, a mechanism body and a switch rotating body, wherein the rotating shaft is arranged on the rotating shaft; the torsion spring, the cam and the switch rotator are sequentially arranged on the rotating shaft in series and are connected with the mechanism body through the rotating shaft; one end of the mechanism body is fixed on the side wall of the interior of the aircraft, two sides of the other end of the mechanism body are respectively fixed with an electric micro switch, and the two electric micro switches respectively correspond to the positions of the cam and the switch rotating body; the switch rotator is arranged in the cavity of the mechanism body, and the end part of the switch rotator passes through one end of the mechanism body and the long groove of the side wall of the aircraft and then contacts with the inner wall of the launching tube. The invention has the advantages of strong mechanism independence, convenient on-board layout, convenient and clear visual inspection of the mechanical state of the general assembly into the barrel, redundant backup of electric insurance and good platform transplanting universality, and is suitable for various in-barrel launching aircrafts such as vehicle-mounted launching, airborne launching, portable launching and the like.

Description

A single torsion spring energy-storage rotating cam safety switch mechanism for aircraft

Technical field

The invention belongs to the field of aircraft, and specifically relates to a single torsion spring energy-storage rotating cam type safety switch mechanism of an aircraft. It mainly relates to the storage and transportation status of the aircraft and the electrical isolation insurance of the on-board explosives before the aircraft is fired from the barrel and the electrical isolation after the aircraft is separated from the barrel. Quickly release the isolation insurance and switch to the security protection mechanism of Unicom state.

Background technique

There are many pyrotechnics on the canister-launched aircraft, and the on-board battery serves as the power supply component of the aircraft. In various environments such as the storage, transportation, and launch of aircraft, it is necessary to simultaneously meet the requirements of physical isolation of explosives and power sources in the barrel before launch, and the need to quickly turn on the electrical onboard after the launcher leaves the barrel.

Common isolation solutions: one is to activate the isolation switch for electric fire to switch isolation/conduction; the other is to install electrical micro switches on the folding wings and rudder wings to switch isolation/conduction when folding and opening. The limitations and shortcomings of these isolation solutions are obvious. The pyrotechnic isolating switch that isolates electrical power must be in a path state, resulting in no isolation, resulting in subsequent hidden dangers and obvious impact vibrations. The assembly accuracy of the rudder wing is strict and affects the aircraft. The movement of the rudder is limited by the position of the rudder on the aircraft, and the safety switch often cannot be set close to the tail of the aircraft, which conflicts with the fact that the aircraft is as far away from the barrel as possible to release the safety, etc.

Contents of the invention

The present invention provides a single torsion spring energy-storage rotating cam type safety switch mechanism for an aircraft. The technical problem to be solved is: it can not only meet the rapid transition of electrical isolation/conduction states within the aircraft barrel/out of the barrel, but also function as an independent The mechanism design can be widely used in different tube-launched aircraft after adaptive transformation. It has good versatility and can effectively accumulate reliability samples.

In order to solve the above technical problems, the present invention provides an aircraft single torsion spring energy-storage rotating cam safety switch mechanism, which is characterized by: including a rotating shaft 1, a torsion spring 2, a cam 3, an electrical micro switch 6, a mechanism body 7 and The switch rotary body 8; the torsion spring, the cam and the switch rotary body are arranged in series on the rotating shaft in sequence, and are connected to the mechanism body 7 through the rotating shaft; one end of the mechanism body 7 is fixed on the internal side wall of the aircraft, and an electrical microcomputer is fixed on both sides of the other end. The two electric micro switches correspond to the positions of the cam 3 and the switch rotary body respectively; the switch rotary body is arranged in the cavity of the mechanism body, and its end passes through one end of the mechanism body and the side wall of the aircraft The long groove is in contact with the inner wall of the launch tube.

Beneficial effects: The present invention uses the torsion spring in the cylinder to pre-twist energy, and the electric micro switch is in a free insurance state; the rotation limit of the torsion spring is released, and the potential energy of the torsion spring is released to drive the switch rotating body to prompt the cam to trigger the electric micro switch, so that It is converted from the insurance state to the working state to realize the on/off conversion of the circuit. The invention has the advantages of strong mechanism independence, convenient on-board layout, convenient and clear visual inspection of the mechanical status of the general loading barrel, redundant electrical insurance backup, and good platform transplant versatility, and is suitable for vehicle-mounted launch, airborne launch, portable launch, etc. Various types of tube-launched aircraft.

Description of the drawings

Figure 1 is a schematic diagram of the structure of the single torsion spring energy-storage rotating cam safety switch mechanism in the launch tube.

Figure 2 is a schematic diagram of the structure of the single torsion spring energy-storage rotating cam safety switch mechanism after it leaves the launch tube.

Figure 3 is a schematic structural diagram of a single torsion spring energy-storage rotating cam safety switch mechanism.

Detailed ways

In order to make the purpose, content and advantages of the present invention clearer, specific embodiments of the present invention will be described in further detail below.

The invention proposes an aircraft single torsion spring energy-storage rotating cam safety switch mechanism, which includes a rotating shaft 1, a torsion spring 2, a cam 3, a keyway lock block 4, a screw 5, an electrical micro switch 6, a mechanism body 7, and a switch rotation Body 8, mechanical retaining ring 9; the cam is an eccentric wheel; the switch rotating body is also equipped with a cam structure;

The torsion spring, cam and switch rotary body are arranged in series on the rotating shaft as needed, and are connected to the mechanism body 7 through the rotating shaft; one end of the mechanism body 7 is fixed on the internal side wall of the aircraft, and an electrical microswitch 6 is fixed on both sides of the other end. , the two electrical micro switches correspond to the positions of cam 3 and the switch rotating body respectively.

A mechanical retaining ring 9 is provided at the end of the rotating shaft. The cam is connected to the rotating shaft through the keyway lock block 4.

The switch rotary body is arranged in the cavity of the mechanism body, and its end passes through one end of the mechanism body and the long groove on the side wall of the aircraft and then contacts the inner wall of the launch tube.

In the present invention, a single torsion spring is designed on one side of the switch rotary body, which is an asymmetric design.

The safety switch mechanism is installed in the aircraft. When the rotational motion plane of the switch rotary body is parallel to and intersects with the axis of the aircraft (that is, the direction in which the aircraft moves along the launch tube), the reliability of the mechanism can be improved; when the switch rotary body protrudes into the launch tube and contacts the surface of the aircraft body The inner wall of the launch tube is in the torsion spring pre-torsion limit state. After the aircraft leaves the tube, the torsion spring drives the switch rotating body to rotate and reach the position. The switch safety mechanism does not protrude from the surface of the aircraft, and no separation objects from the mechanism separate from the body.

The torsion spring in the cylinder is used to pre-torque energy storage, and the electrical micro switch is in a free insurance state; when the rotation limit of the torsion spring is released, the potential energy of the torsion spring is released to drive the switch rotating body to trigger the cam (the switch rotating body can also contain its own cam feature). The electrical micro switch converts it from the insurance state to the working state and realizes the on/off conversion of the circuit.

The torsion spring provides the actuating energy of the mechanism, and the rotation of the cam changes the contact distance with the electrical micro switch, which can drive one or several electrical micro switches set as needed to achieve a redundant design.

By adapting the installation body of the mechanism, it can be transplanted to different aircraft. By adjusting the pendulum length

The launch tube of the in-tube launching aircraft mentioned in the present invention can also be a guide rail for rail launch or a launch box for box launch.

The invention adopts an asymmetric structure scheme in which a single torsion spring in the cylinder stores energy, and the torsion spring releases the limit cam from the cylinder and rotates to trigger independent multi-channel electrical micro switches. It has strong mechanism independence, convenient layout on the machine, and the mechanical state of the total installation into the cylinder. It has the advantages of convenient and clear visual inspection, redundant electrical insurance backup, and good versatility for platform transplantation. It is suitable for various types of in-tube launch aircraft such as vehicle-mounted launch, airborne launch, and portable launch, and has good application prospects.

The above are only preferred embodiments of the present invention. It should be noted that those of ordinary skill in the art can also make several improvements and modifications without departing from the technical principles of the present invention. These improvements and modifications It should also be regarded as the protection scope of the present invention.

Claims (10)

1. The utility model provides an aircraft single torsional spring energy storage rotary cam formula safety switch mechanism which characterized in that: comprises a rotating shaft (1), a torsion spring (2), a cam (3), an electric micro switch (6), a mechanism body (7) and a switch rotating body (8); the torsion spring, the cam and the switch rotator are sequentially arranged on the rotating shaft in series and are connected with the mechanism body (7) through the rotating shaft; one end of the mechanism body (7) is fixed on the side wall of the interior of the aircraft, two sides of the other end are respectively fixed with an electric micro switch (6), and the two electric micro switches respectively correspond to the positions of the cam (3) and the switch rotating body; the switch rotator is arranged in the cavity of the mechanism body, and the end part of the switch rotator passes through one end of the mechanism body and the long groove of the side wall of the aircraft and then contacts with the inner wall of the launching tube.

2. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the cam is an eccentric round wheel.

3. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the switch rotator is also provided with a cam structure.

4. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: an organic check ring (9) is arranged at the end part of the rotating shaft.

5. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the cam is connected with the rotating shaft through a key slot locking block (4).

6. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the plane of rotational movement of the switching rotator is parallel to and intersects the aircraft axis.

7. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: when the switch rotating body is in the launching tube, the surface of the protruding machine body contacts the inner wall of the launching tube and is in a torsion spring pretwisting limiting state, the torsion spring drives the switch rotating body to rotate and be in place after the aircraft leaves the launching tube, and the switch safety mechanism does not protrude out of the surface of the aircraft.

8. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the rotation of the cam changes the contact distance with the electric micro-switches, and can drive 1 or a plurality of electric micro-switches which are arranged according to the requirement.

9. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the swing length of the switch rotating body (8) is adjusted, so that the device can be suitable for in-cylinder launching aircrafts with different cylinder gaps.

10. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the launching tube can be replaced by a guide rail launched by a guide rail or a launching box launched in a box.