CN109696088B

CN109696088B - Compact missile wing contraction and expansion mechanism and missile

Info

Publication number: CN109696088B
Application number: CN201811496609.7A
Authority: CN
Inventors: 许泉; 傅建明; 张璐璐; 刘广; 邹仁珍; 梁伟; 唐海敏; 李欣益; 张晓宏; 任智毅; 伍彬
Original assignee: Shanghai Institute of Electromechanical Engineering
Current assignee: Shanghai Institute of Electromechanical Engineering
Priority date: 2018-12-07
Filing date: 2018-12-07
Publication date: 2021-06-08
Anticipated expiration: 2038-12-07
Also published as: CN109696088A

Abstract

The invention provides a compact missile wing contraction and expansion mechanism and a missile, which can increase the range of a tactical missile, expand the combat airspace, increase the available overload, improve the maneuvering capability, save the external space and facilitate the buried mounting. The invention discloses a compact missile wing contraction and expansion mechanism, which is mainly characterized in that: the explosion-proof device comprises a telescopic wing, a connecting rod, a piston sleeve, a piston rod, a shaft, a bracket, a spring, a push disc, an explosion initiator, a stop pin, a stop block and the like. The compact missile wing contraction and expansion mechanism can meet different requirements of the launching safety and the large mobility of the tail end simultaneously under the condition of limited size in the expansion direction.

Description

Compact missile wing contraction and expansion mechanism and missile

Technical Field

The invention relates to the general technical field of missiles, in particular to a compact missile wing contraction and expansion mechanism. In particular to a compact missile wing contraction and expansion mechanism of an intelligent aircraft.

Background

Increasingly complex battlefield environments put higher and higher requirements on the operational performance of tactical missiles, and the flight envelope of the tactical missiles is forced to be further expanded, so that new technology application is continuously emerged. In order to increase the missile range, expand the combat airspace, increase the available overload, improve the maneuvering capability, save the external space and facilitate the buried mounting. No missile in the prior art adopts a telescopic wing mechanism.

Disclosure of Invention

In view of the shortcomings in the prior art, it is an object of the present invention to provide a compact missile wing retraction mechanism.

According to the invention, the compact missile wing contraction and expansion mechanism comprises: missile wing, bracket, shaft piece and explosion initiator;

the missile wing rotating shaft of the missile wing is arranged on the bracket, and the missile wing is connected and arranged on a shaft piece with the consistent axis of the missile body through a piston rod, a piston sleeve, a connecting rod and a push disc;

when the missile wing is in a contracted state, the explosion starter fixes the push disc at the initial position of the shaft.

Preferably, when the explosion starter receives an on-bomb computer unfolding instruction, the working pin of the explosion starter retracts into the explosion starter body, the push disc moves along the shaft under the pushing action of the spring, the connecting rod is pushed, the opening angle of the piston sleeve is increased, and the piston rod is pushed out, so that the missile wing is pushed to rotate out of the bomb body around the support; the missile wing is unfolded in place, the inner edge of the missile wing clings to the inner groove of the stop block on the bracket to complete sealing, the pressed stop pin is pinned into the inner edge hole of the missile wing to fix the missile wing, and the stop pin is connected with an internal missile circuit after extending out to give a feedback signal that the missile wing is unfolded in place.

According to the missile provided by the invention, the compact missile wing contraction and expansion mechanism is adopted.

Compared with the prior art, the invention has the following beneficial effects:

the invention adopts a compact missile wing contraction and expansion mechanism, and can simultaneously meet different requirements of the launching safety and the large maneuverability of the tail end under the condition of limited size in the expansion direction. The invention can increase the missile range, expand the combat airspace, increase the available overload, improve the maneuvering capability, save the external space and facilitate the embedded mounting.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic view of a compact missile wing retraction and extension mechanism of the invention.

The figures show that:

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

As shown in fig. 1, which is a schematic structural diagram of a compact missile wing extending and retracting mechanism of a missile of the invention, in fig. 1, a missile wing rotating shaft is fixed in a cabin body through a support, missile wings are connected and fixed on a shaft with the same axis of a missile body through a piston rod, a piston sleeve, a connecting rod and a push disc, and when the missile wings are in a contracted state, an explosion initiator fixes the push disc at the initial position of the shaft. When the explosion starter receives the on-bomb computer unfolding instruction, the working pin of the explosion starter retracts into the explosion starter body, the push disc moves along the shaft under the action of the pushing of the spring, the connecting rod is pushed, the opening angle of the piston sleeve is enlarged, and the piston rod is pushed out, so that the missile wing is pushed to rotate out of the bomb body around the support. The missile wing is unfolded in place, the inner edge of the missile wing is tightly attached to the inner groove of the stop block to complete sealing, the pressed stop pin is pinned into the inner edge hole of the missile wing to fix the missile wing, and the stop pin is connected with an internal missile circuit after extending out to give a feedback signal that the missile wing is unfolded in place.

The compact missile wing retraction and extension mechanism is characterized in that before receiving a missile-borne computer extension instruction, the missile wing is completely retracted into a missile body, after receiving the missile-borne computer extension instruction, the missile wing is rapidly extended, and the missile wing locking and sealing functions are completed. In order to achieve the purpose, the technical scheme adopted by the invention is that before the on-missile computer unfolding instruction is not received, the telescopic wing is connected with the push disc through the connecting rod, the piston sleeve and the piston rod and is placed on the shaft fixed on the axis of the missile body, and the push disc is fixed through the initiating explosive device to ensure that the missile wing is completely retracted into the missile body at the moment when the missile wing does not receive the on-missile computer instruction. After the explosion starter receives a wing surface unfolding instruction, the pin is unlocked, the telescopic wing is quickly and safely unfolded in place by the push disc under the action of the spring, after the telescopic wing is completely unfolded in place, the inner edge of the missile wing is attached to the inner groove of the stop block, and the stop pin is pinned into the inner edge hole of the missile wing after the telescopic wing is completely unfolded in place, so that the locking function is completed. And the inner edge of the missile wing is tightly attached to the inner groove of the stop block to meet the requirement of the sealing performance of the missile wing.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.

Claims

1. A compact missile wing contraction and expansion mechanism is characterized by comprising: missile wing, bracket, shaft piece and explosion initiator;

when the missile wing is in a contracted state, the explosion starter fixes the push disc at the initial position of the shaft;

when the explosion starter receives an on-missile computer unfolding instruction, the working pin of the explosion starter retracts into the explosion starter body, the push disc moves along the shaft under the pushing action of the spring, the connecting rod is pushed, the opening angle of the piston sleeve is enlarged, and the piston rod is pushed out, so that the missile wing is pushed to rotate out of the projectile body around the support; the missile wing is unfolded in place, the inner edge of the missile wing is tightly attached to the inner groove of the stop block on the bracket to complete sealing, the pressed stop pin is pinned into the inner edge hole of the missile wing to fix the missile wing, and the stop pin is connected with an internal missile circuit after extending out to give a feedback signal that the missile wing is unfolded in place;

before receiving no computer unfolding instruction on the missile, the telescopic wing is connected with the push disc through the connecting rod, the piston sleeve and the piston rod and is placed on a shaft fixed on the axis of the missile body, and the push disc is fixed through an initiating explosive device to ensure that the missile wing is completely retracted into the missile body at the moment when the computer unfolding instruction on the missile is not received; after the explosion starter receives a wing surface unfolding instruction, the pin is unlocked, the telescopic wing is quickly and safely unfolded in place by the push disc under the action of the spring, after the telescopic wing is completely unfolded in place, the inner edge of the missile wing is attached to the inner groove of the stop block, and the stop pin is pinned into the inner edge hole of the missile wing after the telescopic wing is completely unfolded in place, so that the locking function is completed; and the inner edge of the missile wing is tightly attached to the inner groove of the stop block to meet the requirement of the sealing performance of the missile wing.

2. A missile using the compact missile wing retraction and extension mechanism of claim 1.