CN114212268B - Rotary eccentric wheel type electric safety switch mechanism of in-cylinder launching aircraft - Google Patents

Abstract

The invention relates to a rotating eccentric wheel type electrical safety switch mechanism for an aircraft launched in a barrel, which includes a switch mounting body, a torsion spring, an eccentric wheel, a rotating shaft, a torsion arm plate, a switch rotating body and an electrical switch; the switch mounting body is arranged in the aircraft, One end of the switch installation body is fixedly connected to the inner wall of the aircraft, and the other end is fixed with electrical switches on both sides. This invention not only can meet the rapid conversion of electrical isolation/conduction status within the aircraft barrel/out of the barrel, but also as an independent mechanism design, After adaptive transformation, it can be widely used in different tube-launched aircraft, has good versatility, and can effectively accumulate reliability samples. It has a simple structure, stable and reliable operation, and is versatile and modular. It is very suitable for launching aircraft in the barrel and has good application prospects.

Description

A kind of rotating eccentric wheel type electrical safety switch mechanism for in-tube launching aircraft

Technical field

The invention belongs to the field of aircraft, and specifically relates to a rotating eccentric wheel-type electrical safety switch mechanism for an aircraft launched in a barrel. It mainly relates to the storage and transportation status of an aircraft launched in a barrel and the electrical isolation insurance of explosives on board before the aircraft launches and leaves the barrel. The final electrical quick-release isolation fuse is a safety protection mechanism that switches to the connected state and is used in in-tube launch aircraft.

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 to switch the isolation/conduction of the electric fire; the other is to install the electrical micro switch on the folding machine and the rudder wing to switch the 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 invention provides a rotating eccentric wheel type electrical safety switch mechanism for an in-cylinder launching aircraft. The technical problem to be solved is that it can be completely electrically and physically isolated, and can be separated from the actuating mechanism on the aircraft to perform their own duties without affecting each other.

In order to solve the above technical problems, the present invention provides a rotating eccentric wheel type electrical safety switch mechanism for launching aircraft in a barrel, which is characterized by: including a switch mounting body 1, a torsion spring 2, an eccentric wheel 5, a rotating shaft 7, and a torsion arm plate 8 , switch rotating body 9 and electrical switch 11; the switch installation body 1 is arranged in the aircraft, one end of the switch installation body 1 is fixedly connected to the inner wall of the aircraft, and the other end has electrical switches fixed on both sides; the switch installation body 1 has a connection end with the aircraft. A U-shaped groove has a long groove on the inner wall of the aircraft corresponding to the U-shaped groove; the rotating shaft is installed on the switch mounting body and is symmetrical to the center line of the switch mounting body; the rotating shafts on the left and right sides of the switch mounting body are symmetrically provided with Eccentric 5, torsion spring 2, torsion arm plate 8; the two eccentrics correspond to the positions of the electrical switch respectively; the switch rotating body 9 is fixed on the rotating shaft and is located in the U-shaped groove of the switch mounting body 1, and the switch rotates The end of the body 9 passes through the side wall of the aircraft and is in contact with the inner wall of the launch tube.

Beneficial effects: The present invention can not only meet the requirements of rapid conversion of electrical isolation/conduction states within the aircraft barrel/out of the barrel, but also as an independent mechanism design, it can be widely used in different barrel-launched aircraft through adaptive transformation. It has good versatility and can effectively accumulate reliability samples. It has a simple structure, stable and reliable operation, and is versatile and modular. It is very suitable for launching aircraft in the barrel and has good application prospects.

Description of the drawings

Figure 1 (a) and (b) are respectively the front view and the left view of the structural form of the present invention in the launch tube.

Figure 2 is a schematic diagram of the structure of the present invention after leaving the launch tube.

Figure 3 is a schematic diagram of the structure and composition of the present invention.

Figure 4 is a left view of Figure 3.

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 a rotating eccentric wheel type electrical safety switch mechanism for a launch aircraft in a barrel, which includes a switch mounting body 1, a torsion spring 2, a torsion arm fixed bracket 3, a switch rotating body locking pin 4, an eccentric wheel 5, and an eccentric wheel lock. Pin 6, rotating shaft 7, torsion arm plate 8, switch rotating body 9, stop pin 10, electrical switch 11, screw 12;

The switch installation body 1 is arranged in the aircraft. One end of the switch installation body 1 is fixedly connected to the inner wall of the aircraft, and the other end has electrical switches fixed on both sides. There is a U-shaped groove at the connection end of the switch installation body 1 and the aircraft, corresponding to the U-shaped groove. There are long slots on the inner wall of the aircraft;

The rotating shaft is installed on the switch mounting body, and is symmetrical relative to the center line of the switch mounting body; the rotating shafts on the left and right sides of the switch mounting body are symmetrically provided with eccentric wheels 5, torsion springs 2, and torsion arm plates 8; on the left and right sides of the switch mounting body There is a torsion arm fixed bracket 3 on the side corresponding to the eccentric wheel; one end of the torsion spring is fixed on the torsion arm plate 8, and the other end is fixed on the torsion arm fixed bracket; the two eccentric wheels correspond to the positions of the electrical switches respectively; The switch rotary body 9 is fixed on the rotating shaft through the switch rotary body locking pin 4 and is located in the U-shaped groove of the switch mounting body 1. The end of the switch rotary body 9 passes through the side wall of the aircraft and contacts the inner wall of the launch tube.

An eccentric wheel can also be provided on the switch rotating body, and an electrical switch can also be provided at its corresponding position.

The torsion spring pre-twists energy and the electrical micro switch is in a safe and secure 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 prompt the eccentric (the switch rotating body can also have its own eccentric feature) to trigger the electrical switch , converting it from the insurance state to the working state, realizing the on/off conversion of the circuit. The torsion spring provides the actuating energy of the mechanism, and the rotation of the eccentric changes the contact distance with the electrical micro switch. It can drive one or several electrical micro switches set as needed to achieve redundant design.

The electrical safety switch mechanism is installed in the aircraft. When the rotational motion plane of the switch rotating 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 rotating body is inside the launch tube, it protrudes from the surface of the aircraft body. The inner wall of the contact launch tube is in the torsion spring pre-torsion limit state. After the aircraft leaves the tube, the torsion spring drives the switch rotary body to rotate and reach the position. The electrical insurance safety mechanism does not protrude from the surface of the aircraft, and there is no separation of the mechanism from the body.

By adjusting the pendulum length

By adaptively changing the installation body of the switch, it can be transplanted to different aircraft. By changing 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 a symmetrical structure scheme of dual (arm) torsion springs in the cylinder to store energy, and the torsion springs released from the cylinder to release the limiting eccentric rotation and trigger independent multi-channel electrical micro switches. It has strong mechanism independence, convenient on-board layout, and convenient assembly. It has the advantages of convenient and clear visual inspection of the mechanical status of the in-tube, 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 launches, airborne launches, and portable launches.

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 (8)

1. An in-cylinder launching aircraft rotating eccentric wheel type electric safety switch mechanism is characterized in that: the electric switch comprises a switch mounting body (1), a torsion spring (2), an eccentric wheel (5), a rotating shaft (7), a torsion arm disc (8), a switch rotating body (9) and an electric switch (11); the switch installation body (1) is arranged in the aircraft, one end of the switch installation body (1) is fixedly connected with the inner wall of the aircraft, and two sides of the other end of the switch installation body are respectively fixed with an electric switch; a U-shaped groove is formed at the connecting end of the switch mounting body (1) and the aircraft, and a long groove is formed on the inner wall of the aircraft corresponding to the U-shaped groove; the rotating shaft is arranged on the switch installation body and is bilaterally symmetrical relative to the center line of the switch installation body; the rotating shafts on the left side and the right side of the switch mounting body are symmetrically provided with eccentric wheels (5), torsion springs (2) and torsion arm discs (8); the two eccentric wheels correspond to the positions of the electric switches respectively; the switch rotator (9) is fixed on the rotating shaft and is positioned in the U-shaped groove of the switch installation body (1), and the end part of the switch rotator (9) penetrates through the side wall of the aircraft to be in contact fit with the inner wall of the launching cylinder.

2. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the left side and the right side of the switch installation body are provided with torsion arm fixing brackets (3) corresponding to the eccentric wheels, one end of the torsion spring is fixed on the torsion arm disc (8), and the other end is fixed on the torsion arm fixing brackets.

3. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the switch rotator is provided with an eccentric wheel, and an electric switch is arranged at the corresponding position of the eccentric wheel.

4. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the torsion spring is pre-twisted for storing energy, and the electric micro switch is in a safety state; and the rotation limit of the torsion spring is released, and the potential energy of the torsion spring releases the driving switch rotating body to drive the eccentric wheel to trigger the electric switch.

5. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the plane of rotational movement of the switching rotator is parallel to and intersects the aircraft axis.

6. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: when the switch rotating body is in the launching cylinder, the surface of the protruding machine body contacts the inner wall of the launching cylinder and is in a torsion spring pretwisting limiting state, after the aircraft leaves the cylinder, the torsion spring drives the switch rotating body to rotate and be in place, and the electric safety mechanism does not protrude out of the surface of the aircraft.

7. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the swing length of the switch rotating body (9) is adjusted, so that the device can be suitable for the in-barrel launching aircrafts with different barrel machine gaps L.

8. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the launching tube of the launching aircraft in the tube is replaced by a guide rail launched by a guide rail or a launching box launched in a box.