KR20120037806A - Deployment apparatus, missile having the same and method of deploying a missile fin - Google Patents

Abstract

PURPOSE: A deploying device, a missile comprising the same and a blade deploying method are provided to reduce the weight and drag of a missile flying since if the deploying of a blade is completed, a deploying device is separated from the blade. CONSTITUTION: A deploying device comprises a housing(23), first and second cylinders(41,42), a fixing pin(30), first and second flow paths(27,28), a rotating shaft(32), and a drive shaft(25). The housing is detachably formed on one side of fuselage. If pneumatic pressure is provided through the pressure port (26) of the first cylinder, a fixing pin reciprocates along the inner circumference of the first cylinder. Pneumatic pressure passes through the first flow path when the fixing pin rises. If the pneumatic pressure is supplied through the first flow pipe, the second cylinder reciprocates along the inner peripheral surface of the first flow pipe by a piston shaft(43).

Description

DEPLOYMENT APPARATUS, MISSILE HAVING THE SAME AND METHOD OF DEPLOYING A MISSILE FIN}

Embodiments of the present invention relate to a deployment device for deploying the folded wings of the aircraft during flight, guided missiles and wings deployment method having the same.

In guided missiles using concentric launchers, the wings must be fired with their own folded state. The wing of these missiles must be able to prevent accidental damage by avoiding unnecessary contact with the launch tube, and must not only be released quickly when necessary, but also fully ensured deployment. Guided missiles with relatively large aeroplanes require greater deployment forces due to various factors that hinder wing deployment, such as operational speed and flight environment.

Therefore, in the situation where wing deployment is not required, it maintains a firm folded state to facilitate the operation of guided missiles such as storage and transportation, and generates a large deployment force at the time when wing deployment is required to ensure reliable wing deployment and rapid detachment after completion of deployment. A deployment apparatus with high reliability can be considered.

One embodiment of the present invention is to provide a deployment device having a reliable so that the wings can be fully deployed during flight of the aircraft.

In addition, one embodiment of the present invention is to maintain the folded state of the wing during launch, to provide a guided missile that can be rapidly deployed after the launch.

In order to achieve the above object of the present invention, the deployment apparatus according to an embodiment of the present invention is provided with a housing formed to be detachable on one surface of the body, and a pressure port on the inner peripheral surface, is formed inside the housing When the pneumatic pressure is supplied by the first cylinder and the pressure port, the fixing pin is formed to reciprocate along the inner circumferential surface of the first cylinder, and at a certain height of the side of the first cylinder, A second cylinder having a first flow passage formed to pass through, a piston shaft connected to one end of the first flow passage, and supplied with air pressure through the first flow passage, reciprocating along an inner circumferential surface; Is coupled to the piston shaft, when the piston shaft is reciprocating, the rotating shaft is formed to be rotatable and one end is coupled to the rotating shaft, the other end and the wing It includes drive shaft is the sum.

And the drive shaft is rotated by the pneumatic supply of the pressure port to fix or expand the blade.

According to an example related to the present invention, a plug portion is formed at one end of the first cylinder to abut the fixing pin.

According to an example related to the present invention, one end is coupled to the stopper, the other end is coupled to the fixing pin, and further includes a spring for elastically supporting the fixing pin.

According to an example related to the present invention, the one end coupled to the rotary shaft of the drive shaft further includes a third cylinder is formed to be reciprocating along the inner peripheral surface.

According to an example related to the present invention, the apparatus further includes a second flow channel formed to pass the supplied pneumatic pressure at a predetermined height of the third cylinder.

According to an example related to the present invention, a groove is provided on one surface of the drive shaft to supply the pneumatic pressure to the third cylinder.

According to an embodiment related to the present invention, when the pneumatic pressure is supplied to the third cylinder through the groove, one end of the drive shaft is provided with a hole on one surface of the housing surrounding the drive shaft to be retractable into the third cylinder do.

According to an example related to the present invention, a stop pin is provided on one surface of the drive shaft to prevent retreating into the third cylinder of the drive shaft until the deployment of the blade is completed.

According to an example related to the present invention, the combination of the rotary shaft and the drive shaft is splined so that the rotation of the rotary shaft is transmitted to the drive shaft.

According to an example related to the present invention, a pollution prevention part is formed to filter foreign matters in the first channel.

According to an example related to the present invention, the piston shaft is coupled to a slot formed at one end of the rotary shaft by a connecting pin, the reciprocating motion of the piston shaft is converted into the rotary motion of the rotary shaft.

According to an example related to the present invention, the first flow path further includes an orifice formed to delay the pneumatic rise of the second cylinder.

In addition, in order to realize the above object, the present invention, combined with one or both ends of the warhead portion, and the guidance guide to adjust the flight path correction and direction change device so that guided missile strikes the target and generating a thrust force Disclosed is a guided missile comprising a fuselage including an engine and a wing portion attached to one surface of the fuselage and the above-described deployment device coupled to the wing portion to fix or deploy the blade.

According to an example related to the present invention, the blade further includes a drive shaft coupled to one end of the wing portion and formed in the body to allow the wing portion to be rotatable.

In order to achieve the above object, the present invention, the pressure port receives the signal to supply the pneumatic pressure in the first cylinder, and the fixing pin is raised by the supply of the pneumatic pressure, the second passage passing through the first flow channel A wing comprising a step of supplying pneumatic pressure to the cylinder, rotating the rotary shaft while the piston shaft moves by the supply of the pneumatic pressure, and deploying a wing connected to one end of the drive shaft while the drive shaft engaged with the rotary shaft rotates. Disclosed is a development method of.

According to an example related to the present invention, in the method of deploying the vane, when the vane is fully developed, pneumatic pressure is supplied to the groove formed on one surface of the drive shaft through a second flow path tube, and the drive shaft is inserted into the third cylinder. Further comprising the step of retreating.

The deployment device according to at least one embodiment of the present invention configured as described above is fixed in the folded state by the fixing pin at the time of firing, thereby avoiding unnecessary contact with the launch tube, and after the launch of the wing quickly Since it is deployed, it is possible to provide a more reliable deployment device.

In addition, installation space can be minimized by using simple kinematic mechanism, and when the wing deployment is completed, it can be separated from the wing to control the guided missile wing in flight. Can be reduced.

In addition, it is possible to generate large deployment force by using pneumatic as the working medium, and by applying the initial fixed concept, it is not only easy to load and load / load guided missiles, but also change the deployment time of the wing as needed so that operability of guided missiles can be changed. Can be improved. In addition, the deployment force is automatically adjusted according to the reversal opening load added to the blade, thereby reducing the impact of the blade deployment without applying a separate shock absorber.

1 is a conceptual view showing a state in which the wing deployment apparatus mounted on the fuselage according to an embodiment of the present invention.
Figure 2 is a front view of the wing deployment apparatus according to an embodiment of the present invention.
3 is a detailed cross-sectional view taken along the line AA ′ of FIG. 2.
4 is a detailed cross-sectional view taken along the line BB ′ of FIG. 3.
Figure 5a is a cross-sectional view showing a first cylinder and a first flow path of the wing deployment device according to an embodiment of the present invention.
5B is a cross-sectional view illustrating the first cylinder and the first channel when the fixing pin is raised in FIG. 5A;
Figure 6 is a perspective view of the stop pin and the drive pin in the wing deployment apparatus according to an embodiment of the present invention.
FIG. 7 is a detailed sectional view taken along the line D-D 'of FIG. 3; FIG.
FIG. 8 is a view showing a state of FIG. 7 as viewed from the line E-E '. FIG.
9a to 9c is a view showing a drive shaft retraction process of the wing deployment apparatus according to the present invention.
10 is a conceptual view of a guided missile according to an embodiment of the present invention.

Hereinafter, a deployment apparatus according to an embodiment of the present invention, a method of deploying a missile and a wing having the same will be described in more detail with reference to the accompanying drawings. In the present specification, different embodiments are given the same or similar reference numerals for the same or similar configurations, and the description is replaced with the first description. As used herein, the singular forms "a", "an" and "the" include plural forms unless the context clearly indicates otherwise.

1 is a conceptual diagram showing a state in which the wing deployment device 20 according to an embodiment of the present invention is mounted on the body 11, Figure 2 is a wing deployment device 20 according to an embodiment of the present invention FIG. 3 is a detailed sectional view taken along the line AA ′ of FIG. 2, and FIG. 4 is a detailed sectional view taken along the line B ′ B ′ of FIG. 3.

As shown in FIG. 1, the deployment apparatus 20 according to the embodiment of the present invention is detachably attached to the fuselage 11 of the aircraft, and is formed to deploy the wings 12. When the drive shaft 25 protruding from one end of the deployment device 20 rotates the rear pairing 16 coupled with the hinge 17 of the wing 12, as shown in the folded state of the wing 12. Developed.

As shown in FIG. 3, the deployment apparatus 20 includes a housing 23, a fixing pin 30, a cylinder, a flow path tube, a rotation shaft 32, and a drive shaft 25.

The housing 23 is formed of a hard material to prevent deformation due to friction or heat, and is provided with detachable means on one surface to be coupled to the fuselage 11 of the vehicle.

The housing 23 has a plurality of cylinder spaces. The first cylinder 41 has a pressure port 26 through which pneumatic pressure is supplied, and the second cylinder 42 has a first flow passage 27. The piston shaft 43 is configured to move the piston shaft 43 under pressure.

The fixing pin 30 for maintaining the folded state of the wing by fixing the rotating shaft 32 is in contact with the inner circumferential surface of the first cylinder 41, and is formed to be ascending when pneumatic pressure is supplied through the pressure port 26. . When the fixing pin 30 is raised, the upper end of the fixing pin 30 formed to contact the stopper 38 is coupled with the spring 29 so that the fixing pin 30 can be elastically supported. A groove is provided so that 29 may be settled. The stopper 38 has a groove so that the spring 29 is seated while closing the first cylinder 41. In addition, the spring 29, the supply of the pneumatic pressure through the pressure port 26 should be more than a predetermined size, so as to move the fixing pin 30 to open the first flow path (27).

At a predetermined height of the side of the first cylinder 41, when the fixing pin 30 is raised, the first flow path 27 is formed so that the flow path is opened to allow the pneumatic pressure to pass through the pressure port 26. The first channel 27 extends from the hole in the side wall of the first cylinder 41 to the hole in the second cylinder 42 so that the pneumatic pressure passing through the pressure port 26 can be supplied to the second cylinder 42. Will be. 5A and 5B illustrate this process.

In addition, the first flow passage 27 is formed with a pollution prevention part (not shown) to filter out foreign substances that may enter the second cylinder 42.

And the orifice 22 is formed so that the pneumatic rise of the 2nd cylinder 42 may be delayed. That is, the orifice 22 delays the time for generating the pneumatic pressure in the second cylinder 42, and develops using only a low pressure when the reversal force is small, and is developed after sufficient pressure is generated as the reversal force is increased. . Therefore, the development force of the blade 12 is automatically adjusted according to the reversal opening load added to the blade 12.

The second cylinder 42 has a piston shaft 43 reciprocally formed along the inner circumferential surface of the cylinder. When air pressure flows in through the first flow passage 27, the piston shaft 43 is pressurized and straight. You exercise.

The piston shaft 43 is connected to the rotary shaft 32, each coupled with a separate means for converting the linear motion to the rotary motion. For example, as shown in FIG. 4, the piston shaft 43 is coupled to the slot 36 connected to the rotary shaft 32 by the connecting pin 33, and the second cylinder 42 receives the pneumatic pressure to receive the piston shaft ( When the 43 is moved, the rotating shaft 32 is rotated. The piston part 31 is formed in the end of the piston shaft 43.

In addition, one end of the rotary shaft 32 is coupled to the drive shaft 25, and transmits the rotation of the rotary shaft 32 to the drive shaft 25.

When a pneumatic pressure of a predetermined pressure or more is supplied to the pneumatic port through such a configuration, kinetic energy is transmitted to the piston shaft 43 through the cylinder and the flow path tube, and the drive shaft 25 uses the same to develop the blade 12. Let's go.

One end of the drive shaft 25 is connected to the rotary shaft 32, the other end is coupled to the wing 12, in particular coupled to the rear pairing 16 of the wing. As shown in FIG. 7, each drive shaft is splined so that rotation is accurately and reliably transmitted by grooves and protrusions of the drive shaft 25.

One end of the drive shaft 25 coupled with the rotating shaft 32 is formed in a piston shape. In addition, the coupling between the rotation shaft 32 and the drive shaft 25 is made in a separate third cylinder 44 in the housing 23.

The third cylinder 44 is connected through the first cylinder 41 and the second flow path 28, and as described above, if air pressure is continuously supplied after the wing 12 is deployed, the third cylinder ( 44) Pneumatic pressure is also supplied in the space so that the drive shaft 25 moves downward. 9A to 9C illustrate the retraction process of the drive shaft 25.

In addition, one surface of the drive shaft 25 is provided with a groove 37 so as to receive the pneumatic pressure from the second flow channel (28). Through this groove 37, due to the supplied pneumatic pressure, it is possible to continuously retract the drive shaft 25.

A stop pin 34 protruding from the outer circumferential surface is formed on one surface of the drive shaft 25, and the stop pin 34 has the drive shaft 25 extending into the third cylinder 44 until the blade 12 is fully deployed. It serves to prevent retreat.

At this time, the position of the groove 37 and the stop pin 34 is important, and the groove 37 is not formed at the rotational angle at which the blade 12 is fully developed by the drive shaft 25. Pneumatic pressure can be supplied from the stop pin 34 is also inserted into the hole 35 formed in one surface of the housing 23 surrounding the drive shaft 25 at the rotation angle, drive shaft 25 is You can retreat.

FIG. 10 is a conceptual view showing another embodiment of the deployment apparatus 20 according to the present invention, and illustrates an exemplary embodiment in a state where the deployment apparatus 20 is mounted in the missile. In this embodiment, the same or similar reference numerals are assigned to the same or similar components as the previous embodiment, and the description thereof is replaced with the first description.

Referring to this figure, the missile includes a fuselage 11, a wing and a deployment device 20. The fuselage 11 includes a warhead part, an induction adjusting device part that combines with one or both ends of the warhead part to adjust a flight path correction and direction change device so that the missile strikes a target, and an engine generating propulsion force.

The wing part is attached to one surface of the body 11, and includes a wing which is formed to be rotatable by receiving a signal from the fixed wing and the induction adjusting device part.

The wing 12 formed to be rotatable is rotatable by the drive shaft 15 embedded in the body 11.

The deployment method of the wing using the deployment device according to an embodiment of the present invention is as follows.

When the operator transmits a signal to the deployment apparatus 20 by using the adjusting device, the pressure port 26 supplies the pneumatic pressure in the first cylinder 41 by receiving the signal. Thereafter, while the fixing pin 30 is raised by the supply of pneumatic pressure, the pneumatic pressure is supplied to the second cylinder 42 through the first flow passage 27, and the piston shaft 43 is moved by the supply of the pneumatic pressure. While rotating the rotating shaft (32). Then, as the drive shaft 25 engaged with the rotation shaft 32 rotates, the blade 12 connected to one end of the drive shaft 25 is developed.

When the blade 12 is fully deployed, a pneumatic pressure is supplied to the groove formed on one surface of the drive shaft 25 through the second flow passage 28 so that the drive shaft 25 is retracted into the third cylinder 44. do. As a result, as the drive shaft 25 is retracted, the blade 12 and the deployment device 20 are separated from each other.

As described above, the deployment device, the guided missile having the same, and a method of deploying the wing may not be limitedly applied to the configuration and method of the embodiments described above, but the embodiments may be modified in various ways. All or part may be optionally combined.

11: fuselage 12: wings
15: wing drive shaft 20: wing deployment device
22: orifice 23: housing
24: deployment device body 25: drive shaft
27: first euro pipe 28: second euro pipe
29: spring 30: fixing pin
31: piston 32: rotating shaft
33: connecting pin 34: stop pin
41: first cylinder 42: second cylinder
43: piston shaft 44: third cylinder

Claims (16)

A housing formed to be detachable from one surface of the body;
A first cylinder having a pressure port on an inner circumferential surface and formed in the housing;
A fixed pin formed to reciprocate along an inner circumferential surface of the first cylinder when pneumatic pressure is supplied by the pressure port;
A first flow channel formed to pass through the pneumatic pressure when the fixing pin is raised at a predetermined height of the side of the first cylinder;
A second cylinder connected to one end of the first channel and having a piston shaft reciprocating along an inner circumferential surface when pneumatic pressure is supplied through the first channel;
A rotating shaft coupled to the piston shaft and formed to be rotatable when the piston shaft reciprocates; And
One end is coupled to the rotary shaft, the other end includes a drive shaft coupled to the wing,
And the drive shaft is rotated by the pneumatic supply of the pressure port to fix or expand the blade. The method of claim 1,
One end of the first cylinder is a deployment device of the blade, characterized in that the stopper is formed to abut the fixing pin. The method of claim 2,
One end is coupled to the stopper, the other end is coupled to the fixing pin, the deployment device of the wing, characterized in that it further comprises a spring for elastically supporting the fixing pin. The method of claim 1,
And a third cylinder having one end coupled to the rotation shaft of the drive shaft to reciprocate along an inner circumferential surface thereof. The method of claim 4, wherein
And a second flow passage configured to allow the supplied pneumatic pressure to pass through a predetermined height of the third cylinder. The method of claim 4, wherein
And a groove on one surface of the drive shaft to supply the pneumatic pressure to the third cylinder. The method according to claim 6,
When the pneumatic pressure is supplied to the third cylinder through the groove, one end of the drive shaft is provided with a hole on one surface of the housing surrounding the drive shaft to be able to retract into the third cylinder . The method of claim 7, wherein
A stopper is provided on one surface of the drive shaft to prevent the retreat into the third cylinder of the drive shaft until completion of deployment of the blade. The method of claim 1,
Combination of the rotary shaft and the drive shaft, the deployment device of the blade, characterized in that the spline connection so that the rotation of the rotary shaft is transmitted to the drive shaft. The method of claim 1,
The spreading device of the wing, characterized in that the pollution prevention portion is formed to filter foreign matter in the first channel. The method of claim 1,
The piston shaft is coupled to the slot formed on one end of the rotary shaft by a connecting pin, the reciprocating motion of the piston shaft, the deployment device of the blade, characterized in that converted to the rotary motion of the rotary shaft. The method of claim 1,
And an orifice formed in the first channel to further delay the pneumatic rise of the second cylinder. A fuselage including a warhead part, an induction adjusting device part which is coupled with one or both ends of the warhead part to adjust a flight path correction and direction change device so that the missile strikes a target;
A wing portion attached to one surface of the body; And
The missile is coupled to the wing, comprising a deployment device according to any one of claims 1 to 12 to fix or deploy the wing. The method of claim 13,
The missile is coupled to one end of the wing, the missile is characterized in that it further comprises a drive shaft formed in the body so as to be rotatable. Receiving a signal and supplying air pressure into the first cylinder by the pressure port;
The fixed pin is raised by the supply of the pneumatic pressure, and the pneumatic pressure is supplied to the second cylinder through the first channel;
Rotating the rotary shaft while the piston shaft moves by the supply of the pneumatic pressure; And
And a blade connected to one end of the drive shaft while the drive shaft engaged with the rotation shaft rotates. 16. The method of claim 15,
And when the blade is fully deployed, pneumatic pressure is supplied to a groove formed on one surface of the drive shaft, and the drive shaft is retracted into the third cylinder.

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