CN111306996A - Ammunition flight resistance device - Google Patents

Abstract

The invention discloses an ammunition flight resistance device. An initial locking and unlocking mechanism is used to realize the initial locking of the resistance sheet through the structural cooperation between the initial locking and unlocking mechanism and the resistance sheet, and the axial movement of the initial locking and unlocking mechanism realizes The separation from the resistance sheet realizes the unlocking of the resistance sheet, maintains the structural integrity of the resistance sheet, and improves the synchronization of deployment; by adding a deployment locking mechanism, the deployment limit of the resistance sheet is realized, and the structure of the resistance device is simplified. The resistance control of ammunition flight has the characteristics of convenient operation and high reliability.

Description

A kind of ammunition flight resistance device

technical field

The invention belongs to the general technical field of small tactical ammunition structures, in particular to an ammunition flight resistance device.

Background technique

In order to realize the falling speed control of guided rockets at different ranges, projectile speed control devices are usually used. Its working principle is: in the initial stage after the guided rocket is launched, the speed control device is in a closed state to maintain a good aerodynamic shape of the missile body; after reaching the predetermined flight height, the missile-borne flight controller sends a signal to deploy the speed control device. After the projectile speed control device is deployed, the flight resistance coefficient of the guided rocket increases significantly, which can effectively control the terminal speed of the ammunition flight.

Generally, the technical solutions adopted by the bullet speed control device include: 1) D-ring resistance mechanism; 2) "iris" resistance mechanism; 3) Paddle-type resistance mechanism, etc. However, they each have some defects and limitations: the radial area of the D-ring resistance mechanism is small, the range correction ability is limited, and the resistance sheet needs a large centrifugal overload when unfolding, which is a passive unfolding mechanism; "iris" The structure design of the resistance mechanism is complex, the assembly precision is high, and it is difficult to ensure the synchronization of deployment, and there is a risk of ammunition instability during deployment; the paddle-type resistance mechanism is mainly unlocked by the fire actuator, and each resistance piece relies on the torsion spring at its root. The torque of the deployment mechanism realizes deployment, the mechanism is relatively complex, and there is a problem of poor synchronization of the resistance sheet deployment.

To sum up, there is no method in the prior art that can not only meet the requirement of good deployment synchronization, but also has the characteristics of simple structure, convenient operation and high reliability.

SUMMARY OF THE INVENTION

In view of this, the present invention provides a munition flight resistance device, which realizes a munition flight resistance device with high deployment synchronization.

An ammunition flight resistance device provided by the present invention includes an initial locking and unlocking mechanism, a deployment driving mechanism, a deployment locking mechanism, a resistance piece and a cabin. The initial locking and unlocking mechanism, the deployment driving mechanism and the deployment locking mechanism are all arranged in Inside the cabin; the resistance sheet is arranged on the outer surface of the cabin, and the resistance sheet is movably connected to the outer surface of the cabin:

The initial locking and unlocking mechanism is engaged with the resistance sheet; the initial locking and unlocking mechanism moves along the axial direction of the cabin under the control of the deployment signal, and the axial movement unlocks the resistance sheet; the deployment driving mechanism Using spring energy to extend to the outside of the cabin, the deployment driving mechanism cooperates with the resistance sheet to convert the extending movement into the expansion of the resistance sheet; the deployment locking mechanism uses spring energy to extend to the outside of the cabin. The cabin extends outside the cabin, and the deployment locking mechanism cooperates with the resistance sheet, the extension of the deployment locking mechanism limits the resistance sheet to the set deployment position, and the resistance sheet forms the resistance of the ammunition flying.

Further, the initial locking and unlocking mechanism includes a pin puller, a pin puller bracket, a snap ring and a snap ring compression spring, and the rear end of the pin puller and the pin puller bracket are gap-fitted through a cylindrical surface sleeve, and the The pin puller bracket is fixed in the cabin; the front end of the pin puller is fixedly connected with the snap ring; the snap ring is clamped with the resistance piece; the snap ring compression spring is compressed and sleeved on the pull pin In addition to the device, the snap ring compression spring provides a pre-tightening force for the snap connection between the snap ring and the resistance sheet.

Further, the device includes two or more of the resistance sheets, and one end of the resistance sheets connected to the cabin has a conical opening.

Further, the deployment locking mechanism includes a locking pin and a compression spring, the locking pin is preset in a blind hole in the root region of the cabin, and when the resistance sheet is deployed to a set position, the locking The tight pin moves into the tapered opening to lock the resistance piece.

Further, the initial locking and unlocking mechanism moves along the axial direction of the nacelle by pyrotechnic drive under the control of the deployment signal.

Beneficial effects:

The present invention realizes the initial locking of the resistance piece through the initial locking and unlocking mechanism and the structural cooperation between the initial locking and unlocking mechanism and the resistance piece, and realizes the separation from the resistance piece through the axial movement of the initial locking and unlocking mechanism to realize the resistance piece. Unlocking keeps the structural integrity of the resistance sheet and improves the synchronization of deployment; by adding a deployment locking mechanism, the deployment limit of the resistance sheet is realized, the structure of the resistance device is simplified, and the resistance control of the ammunition flight is easy to operate. , High reliability characteristics.

Description of drawings

FIG. 1 is a schematic diagram of a folded structure of an ammunition flight resistance device provided by the present invention.

FIG. 2 is a schematic diagram of a state in which the resistance piece of an ammunition flight resistance device provided by the present invention is unfolded by 25°.

Among them, 1- adapter ring, 2- snap ring, 3- nut, 4- pin puller, 5- snap ring compression spring, 6- resistance sheet, 7- pin puller bracket, 8- support, 9- top Rod, 10-opening spring, 11-blocking cover, 12-buffer spring, 13-rotating shaft, 14-locking pin, 15-cabin, 16-locking spring.

Detailed ways

The present invention will be described in detail below with reference to the accompanying drawings and embodiments.

An ammunition flight resistance device provided by the present invention, as shown in FIG. 1 , includes an initial locking and unlocking mechanism, a deployment driving mechanism, a deployment locking mechanism, a resistance piece and a cabin. The initial locking and unlocking mechanism, the deployment driving mechanism and the deployment locking mechanism are all arranged in the cabin, and the resistance sheet is arranged on the outer surface of the cabin and is movably connected to the outer surface of the cabin.

The initial locking and unlocking mechanism is arranged in the cavity in the middle of the resistance device cabin. The initial locking and unlocking mechanism includes a pin puller 4, a pin puller bracket 7, a snap ring 2 and a snap ring compression spring 5. The pin puller bracket 7 is fixedly connected, the pin puller bracket 7 is radially connected to the resistance device cabin through screws, the front end of the pin puller is sleeved with the cylindrical surface of the snap ring 2, and its axial displacement is restricted by the nut 3 and compressed The snap ring compression spring 5, the snap ring and the resistance piece are clamped, the snap ring pressure spring is compressed and sleeved outside the pin puller, under the common limit of the snap ring 2 and the pin puller bracket 7, the snap ring and the resistance piece are The snap-in provides initial preload. The snap ring 2 overlaps with the resistance sheet 6 under the elastic force of the snap ring compression spring 5 to realize the initial locking function of the resistance sheet. After the guided rocket is launched, the flight controller gives the ignition signal of the pin puller 4 at the predetermined time of the trajectory. Under the action of the gunpowder gas of the pin puller 4, the pin puller 4 overcomes the elastic force of the snap ring compression spring and drives the snap ring to move backwards , so that the resistance piece originally attached to the outer surface of the resistance device cabin and constrained by the snap ring can be unlocked by releasing the restraint.

The resistance pieces are generally 4 to 8 pieces, and in the initial stage of the flight of the ammunition, they are closely attached to the outer surface of the shell 15 of the bullet velocity control device under the restraint of the snap ring 2 .

The unfolding drive mechanism is placed in the middle of the cabin body 15 , and consists of a support 8 , a top rod 9 , an unfolding spring 10 and a blocking cover 11 . The support 8 is circumferentially connected to the resistance device housing 15 by means of screws. The top rod 9 equipped with the opening spring 10 is pre-pressed into the support and restrained by the cover 11. When the resistance sheet is in the closed state, the opening spring 10 is limited by the resistance sheet and is in a compressed state to store the spring force. When the resistance piece is unlocked, the top rod 9 provides an initial thrust for the resistance piece to unfold under the elastic force of the opening spring 10 , and pushes the resistance piece to rotate around the rotating shaft 13 . Due to the action of the ejector rod 9, the resistance sheet can also be deployed against aerodynamic resistance when the guided rocket has a certain angle of attack.

The deployment locking mechanism is composed of a locking pin 14, a locking spring 16 and a buffer spring 12. The locking pin 14 is preset in a blind hole in the root region of the resistance device cabin. Before the resistance piece is unfolded in place, the locking spring 16 is in a compressed state by the limit of the resistance piece to store the spring force; during the unfolding process of the resistance piece, the buffer spring 12 is attached to the outer surface of the resistance piece and elastically deforms to reduce the pressure on the resistance piece. Impact during the unfolding process of the small resistance piece; when the resistance piece is unfolded in place, the locking pin 14 pushes into the conical hole at the root of the resistance piece and locks under the elastic force of the locking spring 16 .

Example:

As shown in FIG. 1 , in a resistance device based on a pin puller according to a preferred embodiment of the present invention, the adapter ring 1 , the snap ring 2 , the resistance device cabin 15 , and the resistance sheet 6 are integral structures, made of aluminum alloys. 2A12-T4 machining type. The locking and unlocking mechanism is placed in the internal cavity structure of the resistance device cabin 15 , and consists of a pin puller 4 , a pin puller bracket 7 , a snap ring 2 , a snap ring lock spring 5 , a nut 3 , and an adapter ring 1 . At the rear of the resistance device cabin 15 , the rotating shaft 13 passes through the resistance device cabin 15 and the round holes on the resistance sheet 6 in turn, so that the resistance sheet 6 is connected with the resistance device cabin 15 . The resistance sheet 6 is also connected to the resistance device housing 15 through the rotating shaft 13 . Under the action of the elastic force of the snap ring compression spring 5, the two resistance sheets overlap with the snap ring 2 and are limited by the snap ring 2 to achieve the locking function and are in a fully closed state. The unfolding mechanism is composed of a support 8 , a top rod 9 , an opening spring 10 and a blocking cover 11 . The opening spring 10 and the ejector rod 9 are preliminarily placed in the support 8 and constrained by the blocking cover 11 , so that the opening spring 10 is in a compressed state to store the compression force. After the installation is completed, the deployment mechanism is connected to the resistance device housing 15 . The locking buffer mechanism is composed of a buffer spring 12 , a locking pin 14 and a locking spring 16 . Before the resistance sheet is installed, place the locking spring 16 and the locking pin 14 in the blind hole inside the resistance device housing 15, and the buffer spring 12 cooperates with the locking pin 14 and is fixed on the resistance device housing 15 with screws. After the installation of the two resistance pieces is completed, the locking spring 16 is in a compressed state due to the limitation of the resistance pieces and stores the compressive force.

After receiving the unlocking signal, the thrust generated by the action of gunpowder gas in the pin puller 4 overcomes the elastic force of the snap ring compression spring 5, and drives the snap ring 2 constrained by the nut 3 to move backward together, thereby releasing the locking of the resistance sheet. After the push rod 9 and the opening spring 10 preset in the support 8 are unlocked, the opening spring 10 loses its restraint, releases the pressure, and pushes the push rod 9 to move, so that the resistance sheet 6 rotates around the shaft 13 . The ejector rod 9 is pushed by a stroke of 16 mm, so that the expansion angle of the resistance sheet 6 reaches 25°, thereby ensuring that the resistance sheet of the resistance device can be initially deployed under the flight condition of the guided rocket with a small attack angle, as shown in Figure 2.

When the rotation angle of the resistance sheet 6 around the rotating shaft 13 reaches 25°, the aerodynamic force becomes the main driving force for the resistance sheet 6 to unfold. When the resistance sheet 6 is unfolded to 90°, the tapered hole on the resistance sheet 6 moves to the position coaxial with the locking pin 14, the locking spring 16 under each resistance sheet loses its restraint, releases the pressure, and the locking pin 14 Push into the conical locking hole at the root of the resistance piece to realize the locking of the resistance piece. At the same time, the buffer spring 12 realizes buffering and shock absorption during the unfolding process of the resistance piece, so as to ensure the normal unfolding and locking of the resistance piece.

To sum up, the above are only preferred embodiments of the present invention, and are not intended to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims (5)

1. An ammunition flight resistance device is characterized by comprising an initial locking and unlocking mechanism, an unfolding driving mechanism, an unfolding locking mechanism, a resistance sheet and a cabin body, wherein the initial locking and unlocking mechanism, the unfolding driving mechanism and the unfolding locking mechanism are all arranged in the cabin body; resistance piece set up in the external surface of cabin, resistance piece and the external surface swing joint of cabin:

the initial locking and unlocking mechanism is clamped with the resistance sheet; the initial locking and unlocking mechanism moves along the axial direction of the cabin under the control of a deployment signal, and the resistance sheet is unlocked through the axial movement; the unfolding driving mechanism utilizes spring energy storage to extend outwards of the cabin body, and is matched with the resistance plates to convert the extending movement into the unfolding of the resistance plates; the expansion locking mechanism utilizes spring energy storage to extend outwards the cabin body, the expansion locking mechanism is matched with the resistance plate, the extension of the expansion locking mechanism is used for limiting the resistance plate at a set expansion position, and the resistance plate forms the resistance of ammunition flight.

2. The device of claim 1, wherein the initial locking and unlocking mechanism comprises a pin puller, a pin puller bracket, a snap ring and a snap ring compression spring, the rear end of the pin puller is in sleeve clearance fit with the pin puller bracket through a cylindrical surface, and the pin puller bracket is fixed in the cabin body; the front end of the pin puller is fixedly connected with the clamping ring; the clamping ring is clamped with the resistance sheet; the snap ring pressure spring is compressed and sleeved outside the pin puller, and the snap ring pressure spring is connected with the snap ring and the resistance piece in a clamped mode to provide pretightening force.

3. The apparatus of claim 1, wherein said apparatus comprises more than two of said resistance pads, said resistance pads having a tapered opening at an end thereof connected to said enclosure.

4. The device of claim 3, wherein the deployment locking mechanism comprises a locking pin and a compression spring, the locking pin is pre-disposed in a blind hole in the root region of the cabin, and the locking pin moves into the tapered opening to lock the resistance tab when the resistance tab is deployed to the set position.

5. The apparatus of claim 1, wherein the initial locking and unlocking mechanism is actuated by a fire in an axial direction along the cabin under the control of a deployment signal.

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