CN111653901A

CN111653901A - Automatic separating mechanism

Info

Publication number: CN111653901A
Application number: CN202010560124.0A
Authority: CN
Inventors: 肖应富; 陈谋钦; 刘贲
Original assignee: Guizhou Space Appliance Co Ltd
Current assignee: Guizhou Space Appliance Co Ltd
Priority date: 2020-06-18
Filing date: 2020-06-18
Publication date: 2020-09-11
Anticipated expiration: 2040-06-18
Also published as: CN111653901B

Abstract

The invention provides an automatic separating mechanism which comprises a support, a floating plate, a locking mechanism and an unlocking mechanism, wherein the support comprises a top plate and a bottom plate, the top plate and the bottom plate are fixedly connected through a guide rod, the axial direction of the guide rod is vertical to the course of an elastic body, the floating plate is sleeved on the guide rod in a sliding mode, a separating spring is sleeved on the guide rod and located between the floating plate and the bottom plate, the locking mechanism is fixed on the top plate, one end of the locking mechanism is fixedly connected with the floating plate, the unlocking mechanism is arranged on the floating plate, and the course movement of the elastic body can push the unlocking mechanism to trigger the locking mechanism to unlock so as to remove the limitation on the movement. The invention provides an automatic separating mechanism, which realizes simultaneous launching of a projectile body and separation of an electric connector, saves launching time and is more suitable for the requirements of modern wars.

Description

Automatic separating mechanism

Technical Field

The invention belongs to the technical field of electric connectors, and particularly relates to an automatic separation mechanism which is used for connection locking and unlocking separation of an electric connector.

Background

Common modes of use for breakaway connectors used in modern airborne weapon systems are: the separation axis of the electric connector is vertical to the course of the projectile body, the electric connector is of a direct-insertion and direct-pull structure, and the electric connector is locked and separated through an electromagnetic locking separation mechanism on an airborne hanger when in use, for example, Chinese patent with publication number CN108258519A provides a plane floating mechanism of the separation connector in an airborne weapon system, which mainly comprises a base, a shell, a guide rod, a guide sleeve, a rotating cam, a locking sleeve, a locking end cover, a locking spring, a locking shaft sleeve, a locking steel ball, a locking ring, a floating plate, a power spring and other parts, is a novel purely mechanical type and touch plane floating mechanism, solves the problems of insertion and locking of the separation connector, but when in separation, mechanical force needs to be applied to the locking shaft sleeve to push the locking shaft sleeve to unlock, the mode needs the aircraft to supply extra power to a launching system, and the separation of the electric connector and the launching of a weapon need to be carried out in sequence, prolonging the firing time of the weapon is a fatal defect in modern war of minute and second.

Disclosure of Invention

In order to solve the technical problem, the invention provides an automatic separating mechanism, which realizes simultaneous launching of a projectile body and separation of an electric connector, saves launching time and is more suitable for the requirements of modern wars.

The invention is realized by the following technical scheme:

an automatic separation mechanism comprises a support, a floating plate, a locking mechanism and an unlocking mechanism, wherein the support comprises a top plate and a bottom plate which are fixedly connected through a guide rod, the axial direction of the guide rod is perpendicular to the course of a projectile body, the floating plate is slidably sleeved on the guide rod, the guide rod is sleeved with a separation spring, the separation spring is positioned between the floating plate and the bottom plate, the locking mechanism is fixed on the top plate, one end of the locking mechanism is fixedly connected with the floating plate, the unlocking mechanism is arranged on the floating plate, the course movement of the projectile body can push the unlocking mechanism to trigger the locking mechanism to unlock, the limitation on the movement of the floating plate is removed, the floating plate moves under the elastic force action of the separation spring, an electric connector is driven to realize separation, the launching of the projectile body is carried out simultaneously with the separation of the electric connector, the launching time; meanwhile, the invention is of a pure mechanical structure, reduces the power supply requirement of a weapon launching system and saves the circuit design and processing cost.

The locking mechanism comprises an outer sheath, a bushing and an ejector rod which are sequentially connected in a sliding mode from outside to inside, the upper end of the bushing is fixedly connected with the top plate, a locking spring is arranged between the top plate and the ejector rod, the upper portion of the ejector rod is abutted against the lower portion of the bushing, a steel ball is arranged on the lower portion of the bushing, the lower end of the outer sheath is fixedly connected with the floating plate, the upper portion of the outer sheath is abutted against the steel ball, the steel ball is limited in a space defined by the outer sheath, the bushing and the ejector rod, the elastic force of the locking spring is.

The top plate is provided with a boss, the locking spring is sleeved on the boss, the ejector rod is provided with a concave part for accommodating the locking spring, the locking spring is limited, and the influence of part shaking on the flight of the aircraft is reduced.

The axial length of the outer sheath is larger than the distance from the center of the steel ball to the top plate along the outer ring of the bushing, and the axial length of the ejector rod is larger than the distance from the center of the steel ball to the top plate along the inner ring of the bushing, so that the steel ball is always limited on the bushing, and hidden danger caused by the fact that the steel ball falls off to form redundancy is avoided.

The locking mechanism is last to offer the spout that link up oversheath and bush along the axial, and ejector pin upper portion is provided with the drive round pin, and the drive round pin passes and stretches out the spout, articulated on the roof have can promote the cam that the floating plate removed through rotating, be provided with the drive groove on the cam, drive round pin and drive groove slip joint, can drive the elasticity rebound that the ejector pin overcome locking spring through rotating the cam, and then unblock locking mechanism, again can manual unblock realize the dismouting of projectile body when the weapon is not launched, can go on under the condition that does not start the aircraft, improve the efficiency of maintaining the inspection, reduce the energy consumption, satisfy the development needs of modern airborne weapon system.

The size of the cam meets the requirement that the floating plate can be pushed to move until the locking mechanism is locked, and the locking mechanism can be locked by rotating the cam.

The rotating shaft of the cam is provided with a milling flat part, a square part or a hexagonal part, so that the cam can be conveniently rotated through a tool.

In order to simultaneously carry out projectile body launching and electric connector separation, the unlocking mechanism comprises a side link and an installation shell, the installation shell is hinged with the floating plate through the side link, the projectile body moves along the course direction to push the installation shell to rotate, and then the locking mechanism is triggered to unlock, so that the automatic separation of the electric connector is realized, and the launching time is saved.

Further, the side link size satisfies locking mechanism unblock back, and the installation shell can support and lean on and live locking mechanism, fixes a position the installation shell, avoids the installation shell to rock, influences the projectile transmission.

Furthermore, after the installation shell is abutted against the locking mechanism, the installation shell is in clearance fit with the projectile body, and the influence on the projectile body launching is avoided.

The invention has the beneficial effects that:

compared with the prior art, the unlocking mechanism is arranged, so that the projectile body is launched and the electric connector is separated and carried out simultaneously, the launching time is saved, and the requirements of modern wars are met; meanwhile, the invention is of a pure mechanical structure, reduces the power supply requirement of a weapon launching system and saves the circuit design and processing cost. Through setting up cam and ejector pin to slip joint, can rotate the cam and carry out the unblock, realized that manual unblock carries out the dismouting of projectile when the weapon is not launched, can go on under the condition of not starting the aircraft, improve the efficiency of maintaining the inspection, reduce the energy consumption, satisfy the development needs of modern airborne weapon system.

Drawings

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

FIG. 2 is a schematic view of the invention with the projectile-propelled release mechanism unlocked;

FIG. 3 is a schematic structural view of the present invention after unlocking;

FIG. 4 is a schematic view of the locking mechanism of the present invention in a locked state;

FIG. 5 is a schematic structural view of the locking mechanism of the present invention in an unlocked state;

FIG. 6 is a schematic structural view of the carrier rod of the present invention;

fig. 7 is a schematic view of the structure of the cam in the present invention.

In the figure: 1-bracket, 2-separation spring, 3-floating plate, 4-locking mechanism, 5-cam, 6-side link, 7-mounting shell, 11-guide rod, 12-top plate, 13-bottom plate, 14-boss, 41-outer sheath, 42-bush, 43-top rod, 44-locking spring, 45-steel ball, 46-sliding groove, 51-driving groove, 411-inner hole, 412-step hole, 413-first conical surface, 421-small end inner cavity, 422-large end inner cavity, 423-second conical surface, 424-mounting hole, 431-concave part, 432-driving pin, 433-small end excircle, 434-large end excircle, 435-third conical surface.

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.

As shown in fig. 1 to 7, an automatic separating mechanism comprises a support 1, a floating plate 3, a locking mechanism 4 and an unlocking mechanism, wherein the support 1 comprises a top plate 12 and a bottom plate 13, the top plate 12 and the bottom plate 13 are fixedly connected through a guide rod 11, the axial direction of the guide rod 11 is perpendicular to the heading of an elastomer, the axial direction of the guide rod 11 is generally referred to as vertical direction in the industry, the floating plate 3 is sleeved on the guide rod 11 in a sliding way, a separating spring 2 is sleeved on the guide rod 11, the separating spring 2 is positioned between the floating plate 3 and the bottom plate 13 and used for pushing the floating plate 3 to separate an electric connector inserted into the elastomer, the top plate 12 is fixedly provided with the locking mechanism 4, one end of the locking mechanism 4 is fixedly connected with the floating plate 3 and used for limiting the floating plate 3 to move to keep the electric connector inserted into the elastomer, the unlocking mechanism is arranged on the floating plate 3, and the heading of the, the limitation on the movement of the floating plate 3 is removed, the floating plate moves under the elastic force of the separation spring to further drive the electric connector to realize separation, and the launching of the projectile body and the separation of the electric connector are simultaneously carried out, so that the launching time is saved, and the requirements of modern wars are met; meanwhile, the invention is of a pure mechanical structure, reduces the power supply requirement of a weapon launching system and saves the circuit design and processing cost.

The locking mechanism 4 comprises an outer sheath 41, a bushing 42 and a push rod 43 which are connected in sequence in a sliding manner from outside to inside, in the embodiment, an inner cavity of the outer sheath 41 is provided with a through inner hole 411, the upper end of the inner hole 411 is provided with a step hole 412, the inner hole 411 and the step hole 412 are connected through a first conical surface 413, the bushing 42 is provided with a large-end inner cavity 422, the lower part of the large-end inner cavity 422 is closed to form a small-end inner cavity 421, the large-end inner cavity 422 and the small-end inner cavity 421 are connected through a second conical surface 423, the outer ring of the push rod 43 comprises a small-end outer circle 433 and a large-end outer circle 434 positioned at the top, the small-end outer circle 433 and the large-end outer circle 434 are connected through a third conical surface 435, the upper end of the bushing 42 is fixedly connected with the top plate 12, a locking spring 44 is arranged between the top plate 12 and the push rod 43, so, the steel ball 45 is arranged in the mounting hole 424, the mounting hole 424 is shielded by the excircle 434 at the large end, the lower end of the outer sheath 41 is fixedly connected with the floating plate 3, the first conical surface 413 at the upper part of the outer sheath 41 abuts against the steel ball 45, so that the steel ball 45 is limited in a space surrounded by the outer sheath 41, the bushing 42 and the ejector rod 43 to form locking connection capable of being triggered to unlock, and the unlocking is realized by exerting force on the ejector rod and overcoming the elastic force of the locking spring to slide upwards.

The top plate 12 is provided with a boss 14, the locking spring 44 is sleeved on the boss 14, the ejector rod 43 is provided with a concave part 431 for accommodating the locking spring 44, the locking spring is limited, and the influence of part shaking on the flight of the aircraft is reduced.

The axial length of the outer sheath 41 is greater than the distance from the center of the steel ball to the top plate 12 along the outer ring of the bush 42, and the axial length of the ejector rod 43 is greater than the distance from the center of the steel ball to the top plate 12 along the inner ring of the bush 42, so that the steel ball is always limited on the bush, and hidden danger caused by redundant materials formed by falling of the steel ball is avoided.

The locking mechanism 4 is last to offer the spout 46 that link up oversheath 41 and bush 42 along the axial, and ejector pin 43 upper portion is provided with drive round pin 432, and drive round pin 432 passes and stretches out spout 46, it has the cam 5 that can promote the floating plate 3 removal through rotating to articulate on the roof 12, is provided with drive groove 51 on the cam 5, and drive round pin 432 and drive groove 51 slip joint can drive the ejector pin through rotating the cam and overcome locking spring's elasticity rebound, and then unblock locking mechanism, again can manual unblock realize the dismouting of projectile body when the weapon is not launched, can go on under the condition that does not start the aircraft, improve the efficiency of maintaining the inspection, reduce the energy consumption, satisfy the development needs of modern airborne weapon system.

The size of the cam 5 is enough to push the floating plate 3 to move until the locking mechanism 4 is locked, and the locking mechanism can be locked by rotating the cam.

The rotating shaft of the cam 5 is provided with a milling flat part, a square part or a hexagonal part, so that the cam can be conveniently rotated through a tool.

The unlocking mechanism comprises a side link 6 and an installation shell 7, the installation shell 7 is hinged with the floating plate 3 through the side link 6 to form a planar hinge four-bar mechanism, the installation shell 7 can be pushed to rotate by the heading motion of the projectile body, the locking mechanism 4 is triggered to unlock, the automatic separation of the electric connector is realized, and the launching time is saved.

6 size of side link satisfies locking mechanism 4 unblock back, and installation shell 7 can support and lean on and withstand locking mechanism 4, fixes a position the installation shell, avoids the installation shell to rock, influences the projectile transmission.

After the installation shell 7 abuts against the locking mechanism 4, the installation shell 7 is in clearance fit with the projectile body, and the influence on projectile body launching is avoided.

The working principle of the invention is as follows:

when the projectile body is launched, the projectile body moves along the course to push the mounting shell 7, the projectile body is limited by the side link 6, the mounting shell 7 rotates to abut against the lower end face of the ejector rod, the mounting shell 7 continues to rotate to drive the ejector rod 43 to overcome the elastic force of the locking spring 44 and move upwards in the vertical direction, when the outer circle 433 of the small end of the ejector rod 43 moves to the position of the steel ball 45, the steel ball 45 loses the support of the outer circle 434 of the large end of the ejector rod 43, meanwhile, the separation spring 2 pushes the floating plate 3, the first conical surface 413 of the outer sheath 41 pushes the steel ball 45 to move inwards, the locking mechanism 4 is unlocked, and the floating plate 3 continues to move vertically under the elastic force of.

When the automatic separation mechanism needs to be unlocked manually, a torque is applied to the cam 5 through tools such as an auxiliary wrench, the driving groove 51 on the cam 5 drives the ejector rod to move vertically and upwards through the driving pin 432 on the ejector rod 43, when the outer circle 433 of the small end of the ejector rod 43 moves to the position of the steel ball 45, the steel ball 45 loses the support of the outer circle 434 of the large end of the ejector rod 43 to cause the locking mechanism 4 to be unlocked, and the separation spring 2 drives the floating plate 3 to move vertically and upwards to realize separation.

When the automatic separating mechanism needs to be locked again after being unlocked, a tool such as an auxiliary wrench is utilized to apply torque on the cam 5, the cam 5 drives the floating plate 3 to overcome the elasticity of the separating spring 2 to move downwards in the vertical direction, meanwhile, the outer sheath 41 is driven to move downwards in the vertical direction, when the stepped hole 412 of the outer sheath 41 passes over the steel ball 45, the ejector rod 43 pushes the steel ball 45 to move outwards under the elasticity of the locking spring 44, the third conical surface 435 continues to move downwards to be attached to the second conical surface 423, the steel ball 45 is positioned between the stepped hole 412 of the outer sheath 41 and the large-end outer circle 434 of the ejector rod 43, at the moment, the locking mechanism 4 is in a locking state, the position of the floating plate 3 relative to the support 1 is kept unchanged, and the positions of the connecting frame 6 and the mounting shell 7 mounted on.

According to the automatic separating mechanism provided by the invention, the unlocking mechanism is arranged, so that the launching of the projectile body and the separation of the electric connector are simultaneously carried out, the launching time is saved, and the automatic separating mechanism is more suitable for the requirements of modern wars; meanwhile, the invention is of a pure mechanical structure, reduces the power supply requirement of a weapon launching system and saves the circuit design and processing cost. Through setting up cam and ejector pin to slip joint, can rotate the cam and carry out the unblock, realized that manual unblock carries out the dismouting of projectile when the weapon is not launched, can go on under the condition of not starting the aircraft, improve the efficiency of maintaining the inspection, reduce the energy consumption, satisfy the development needs of modern airborne weapon system.

Claims

1. An automatic separating mechanism, its characterized in that: the floating type projectile launching device comprises a support (1), a floating plate (3), a locking mechanism (4) and an unlocking mechanism, wherein the support (1) comprises a top plate (12) and a bottom plate (13), the top plate (12) and the bottom plate (13) are fixedly connected through a guide rod (11), the axial direction of the guide rod (11) is perpendicular to the heading of a projectile body, the floating plate (3) is sleeved on the guide rod (11), a separation spring (2) is sleeved on the guide rod (11), the separation spring (2) is located between the floating plate (3) and the bottom plate (13), the top plate (12) is fixedly provided with the locking mechanism (4), one end of the locking mechanism (4) is fixedly connected with the floating plate (3), and the unlocking mechanism is arranged on the floating plate (3).

2. An automatic separating mechanism according to claim 1, characterized in that: locking mechanism (4) are including outer sheath (41), bush (42) and ejector pin (43) from outside to inside sliding connection in proper order, bush (42) upper end and roof (12) fixed connection, be provided with between roof (12) and ejector pin (43) locking spring (44), ejector pin (43) upper portion supports and leans on bush (42) lower part, bush (42) lower part is provided with steel ball (45), outer sheath (41) lower extreme and floating plate (3) fixed connection, outer sheath (41) upper portion supports and leans on steel ball (45), steel ball (45) restriction is in the space that outer sheath (41), bush (42) and ejector pin (43) enclose.

3. An automatic separating mechanism according to claim 2, characterized in that: the top plate (12) is provided with a boss (14), the locking spring (44) is sleeved on the boss (14), and the ejector rod (43) is provided with a concave part (431) for accommodating the locking spring (44).

4. An automatic separating mechanism according to claim 2, characterized in that: the axial length of the outer sheath (41) is greater than the distance from the center of the steel ball to the top plate (12) along the outer ring of the bushing (42), and the axial length of the ejector rod (43) is greater than the distance from the center of the steel ball to the top plate (12) along the inner ring of the bushing (42).

5. An automatic separating mechanism according to claim 2, characterized in that: the locking mechanism (4) is provided with a sliding groove (46) penetrating through the outer sheath (41) and the bushing (42) along the axial direction, the upper portion of the ejector rod (43) is provided with a driving pin (432), the driving pin (432) penetrates through and extends out of the sliding groove (46), the top plate (12) is hinged with a cam (5) capable of pushing the floating plate (3) to move through rotation, a driving groove (51) is formed in the cam (5), and the driving pin (432) is in sliding clamping connection with the driving groove (51).

6. An automatic separating mechanism according to claim 5, characterized in that: the size of the cam (5) is enough to push the floating plate (3) to move until the locking mechanism (4) is locked.

7. An automatic separating mechanism according to claim 5, characterized in that: a rotating shaft of the cam (5) is provided with a milling flat, a square or a hexagonal.

8. An automatic separating mechanism according to claim 1, characterized in that: the unlocking mechanism comprises a side link (6) and a mounting shell (7), and the mounting shell (7) is hinged with the floating plate (3) through the side link (6).

9. An automatic separating mechanism according to claim 8, characterized in that: the size of the side link (6) meets the requirement that the locking mechanism (4) is unlocked, and the mounting shell (7) can abut against the locking mechanism (4).

10. An automatic separating mechanism according to claim 9, characterized in that: after the mounting shell (7) abuts against the locking mechanism (4), the mounting shell (7) is in clearance fit with the projectile body.