KR101292078B1 - Deployment bag, parachute having the same and assembly method for the same - Google Patents

Abstract

The deployment bag of the parachute according to an embodiment of the present invention is a body that is formed so that the canopy is accommodated therein, the first wind pocket and the length of the body is attached to the side of the body, and formed to expand under drag when falling By including a coupling part attached to one end of the direction and fitted with the parachute of the parachute, it is possible to reduce the deployment impact force during the initial deployment of the parachute, and to reduce the shaking of the carrier by the impact.

Description

Unfolding bag, parachute assembly having same and assembly method thereof {DEPLOYMENT BAG, PARACHUTE HAVING THE SAME AND ASSEMBLY METHOD FOR THE SAME}

Embodiments of the present invention relate to a deployment bag of a parachute and a method of assembling the parachute, which is mounted on a vehicle to reduce the speed of falling of the vehicle.

When the carrier and the vehicle are separated in a high speed flight, a parachute is used to control the speed of falling of the vehicle. In particular, in the case of guided missiles used for hitting a distant target, the vehicle including the warhead reaches the speed of the subsonic level, so rapid deployment of the parachute and deceleration of the sufficient vehicle by the parachute are required.

In general, when the parachute is deployed at the same time as the line with the parachute exposed to the outside, impact type drag force and deceleration occur at the moment when the parachute is dragged, which is a design range that the carrier and the parachute can withstand in general. Very likely to escape.

Therefore, within the scope of design constraints and reliability of the carrier and the parachute, a parachute deploying device that can achieve rapid deployment and deceleration during deployment of the parachute can be considered.

One embodiment of the present invention is to provide a parachute having a deployment device that reduces the deployment impact force generated during deployment of the parachute, and can reduce the fluctuation of the carrier body due to the impact.

In addition, it is to provide a deployment apparatus that exhibits a sufficient deployment mechanism so as not to interfere with the parachute and the carried body at the time of deployment.

In order to achieve the above object of the present invention, the deployment bag of the parachute according to an embodiment of the present invention and the body is formed so that the canopy is accommodated therein, and is attached to the side of the body, it is unfolded under drag when falling It is attached to the first wind pocket is formed so as to be attached to one end in the longitudinal direction of the body, the fitting portion is fitted with the line of the parachute.

According to an example related to the present invention, the body is formed in a trapezoidal shape by attaching a plurality of fabrics in the width direction.

According to an example related to the present invention, it is attached to the other end in the longitudinal direction of the body, and comprises a connecting ring coupled to the parachute assembly cover.

According to an example related to the present invention, the side of the body further includes a second wind pocket attached to one side spaced apart from the first wind pocket, and having a vent hole on one surface of the container to maintain the shape of the deployment bag.

The present invention also discloses a parachute including a canopy, mountain lines fastened to the bottom of the canopy, and the parachute deployment bag.

In addition, the present invention in order to realize the above object is formed in a cylinder with an open top, the housing for receiving the parachute therein, the housing is coupled to the housing, the cover and one end connected to one end of the deployment bag is the cover Connected to the other end discloses a parachute assembly comprising a pull line having a ring connected to the carrier and the parachute described above.

According to an example related to the present invention, the pull string has both ends divided into a plurality of strings, and is connected to the cover and the carrier, respectively.

According to an example related to the present invention, before the carrier is spaced from the lid, the pull string is coupled to the lid and the carrier by shear chambers, respectively, so that the lid is not separated from the housing.

In addition, in order to realize the above object, the present invention, coupled to the warhead portion and one or both ends of the warhead and the guide vehicle including a guide adjustment device for adjusting the flight path correction and direction change device so that the missile strikes the target; Guided vehicle including a carrier for transmitting power to the carrier and one end is coupled to the carrier, the other end is coupled to the carrier, the separation parachute assembly to reduce the falling speed of the carrier when the carrier is separated. Initiate.

In addition, in order to achieve the above object, the present invention is the step of folding the gore of the canopy so that the lines are two lines, and pulling one end of the canopy into the development bag, the step of inserting the lines to the engaging portion of the development bag respectively And making a loop so that the lines are not entangled with each other and making the loop neatly into the housing of the parachute assembly, stacking the deployment bag and inserting it into the housing of the parachute assembly, and connecting the connection bag of the deployment bag to the parachute. Disclosed is a method of assembling a parachute assembly comprising connecting with a cover of the assembly.

The deployment bag, the parachute apparatus and the guided missile according to the present invention configured as described above can reduce the deployment impact force at the initial deployment of the parachute, and reduce the shaking of the carrier body due to the impact.

In addition, the air bag attached to the outside of the deployment bag is designed to pull the carrier back out of the parachute, so that after the deployment of the parachute through the deceleration and trajectory change, the parachute and the carrier to be spaced apart from each other to avoid interference.

1 is a conceptual diagram of a deployment bag according to an embodiment of the present invention.
2 is a conceptual diagram of a parachute assembly according to an embodiment of the present invention.
3 is a front view in a state in which FIG. 2 is assembled;
Figure 4 is a plan view of Figure 3;
5 is a conceptual diagram of a guided missile according to an embodiment of the present invention.
FIG. 6 is a conceptual diagram sequentially illustrating a process of deploying a parachute in a missile as an embodiment of FIG. 5; FIG.
7 is a graph showing the deployment impact force at the time of deployment of a conventional parachute.
8 is a graph showing the deployment impact force when the parachute is deployed when using the deployment bag according to an embodiment of the present invention.
9 is a conceptual diagram showing a method of assembling the parachute assembly according to an embodiment of the present invention.

Hereinafter, a deployment bag according to an embodiment of the present invention, a parachute assembly having the same, and a method of assembling thereof will be described in detail with reference to the accompanying drawings. In the present specification, the same or similar reference numerals are given to different embodiments in the same or similar configurations.

As used herein, the singular forms "a", "an" and "the" include plural referents unless the context clearly dictates otherwise.

One embodiment of the present invention relates to a parachute that slows down a drop speed when dropped from a guided missile mounted on a power generating vehicle and fired toward a distant target, when the vehicle is dropped from the carrier, including a warhead.

In general, when the vehicle is separated while the guided missile is flying at high speed, rapid deployment of the parachute and sufficient deceleration of the vehicle are required. In this case, if the parachute is deployed at the same time as the line exposed to the outside, impact type drag force and deceleration occur at the moment when the drag acts on the parachute, which is outside the design range that the carrier and the parachute can withstand. This exists.

Since it is difficult to apply a separate device for reducing the impact impact when deploying the missile in terms of design and reliability of the missile, adopting a method of connecting the deployment bag to the carrier and the parachute as a solution for this, and the structure of the deployment bag will be described later. By taking as follows, the above problems were solved.

1 is a conceptual diagram of a deployment bag 10 according to an embodiment of the present invention.

Referring to FIG. 1, the deployment bag 10 includes a body 13, a first wind pocket 12, and a coupling part 15.

The body 13 is formed by attaching both ends to each other in the width direction using a cloth made of a durable material. For example, two cloths having a trapezoidal shape may be attached in a width direction.

The first wind bag 12 serves to separate the deployment bag 10 and the parachute 20 by a drag during deployment, and are separately attached to both front and rear sides of the body 13.
At this time, the first wind bag 12 is formed in a smaller area than the body 13 to further generate a second drag force to increase the release rate of the deployment bag from the canopy when the separated carrier retracts to the first drag. Can be.

At the moment when the carrier 200 and the carrier 300 are separated, the drag of the carrier 200 is relatively larger than that of the carrier 300, so that the carrier 200 quickly retreats back and connected with the carrier 200. The pulling line 17 pulls the cover 120 of the parachute housing to start the deployment of the parachute 20. However, when the parachute 20 is deployed and drag is generated, the relative speed of the carrier 200 and the carrier 300 decreases or is reversed so that the carrier 200 interferes with the parachute 20 to the parachute 20. It may cause damage.

Therefore, by additionally installing a wind bag to increase the drag outside the deployment bag 10, the deployment bag 10 to increase the release rate from the parachute 20 when separated and thereby different from the carrier 300 The drop trajectory was taken.

By further adding the second wind bag 14 at a position spaced apart from the first wind bag 12, the above-described effect, that is, the speed at which the deployment bag 10 is separated from the parachute 20 can be further increased. In addition, when the deployment bag 10 is separated from the parachute 20, since the deployment bag 10 needs to maintain a constant shape to facilitate separation, one surface of the second wind bag 14 is provided with a vent.

Coupling portion 15 is formed on one end of the body 13 is coupled to the line 22 of the parachute (20). Coupling portion 15 is provided with a locking lock (lock) so that the lines 22 are not entangled with each other during storage and maintenance of the parachute assembly 100. In addition, while wrapping the lower portion of the deployment bag 10, it takes a form similar to the opening of the envelope so that it can be separated when subjected to drag, so that the parachute 20 can be easily released when the parachute 20 is deployed.

2 is a conceptual view of the parachute assembly 100 according to an embodiment of the present invention, Figure 3 is a front view of the assembled state of Figure 2, Figure 4 is a plan view of FIG.

As shown, the parachute 20 includes a canopy 21, a line 22 and a deployment bag 10. Here, the specifications of the canopy 21 and the line 22 is as follows. The canopy 21 is a solid type with a nominal diameter of 1.5m to 2m and a total transmittance of 0% composed of eight gore, and the line 22 has a total of eight and each length is 4m to 5.5m. The strength of one line 22 is between 1000 lbf and 2000 lbf.

As shown, the parachute assembly 100 includes a housing 110, a cover 120, a pull string 17, and the parachute 20 described above.

In one example, the housing 110 is formed in a cylindrical top is opened, it is formed to fold the parachute 20 to a predetermined size to accommodate therein. The housing 110 is an integral type of side plate thickness 2 ~ 5 mm, lower plate thickness 4 ~ 9 mm and has a thin thickness at the limit that can withstand the high-pressure air ejected from the launch tube and the impact of the acquisition using aluminum-based materials. It was designed to be.

The cover 120 covering the housing 110 is fitted to the housing and is connected to one end of the deployment bag 10 through a connection portion 16.

Pull string 17 is one end is connected to the cover 120, the other end is connected to the carrier 200. In one example, the length of the pulling string 17 was 3200 to 6000 mm, and the tensile strength of the pulling string 17 itself was 500 lbf or more. The pull string 17 is divided into a plurality of branches at each end. For example, when both ends of the pull string 17 are bifurcated, the cover 120 may be pulled and separated from the housing 110 regardless of the position or the trajectory of the carrier 200.

In addition, the pull line 17 is provided with shear chambers 18 that are broken when a predetermined force or more is applied, so that the cover 120 is not separated from the housing before the carrier 200 is spaced apart from the cover 120, The shear chambers 18 couple the pull string 17 to the cover 120 or the carrier 200. The shear chambers 18 are secured so that the pulling strings 17 are not entangled with each other as described above, and are broken by the impact force caused by the deployment of the parachute 20, and the pulling strings 17 cover the cover 120 and the carrier. To separate from (200).

5 is a conceptual view of a guided missile according to an embodiment of the present invention, FIG. 6 is a conceptual view sequentially illustrating a process of deploying the parachute 20 in the guided missile as the embodiment of FIG. 5, and FIG. 7 is a conventional parachute. 8 is a graph showing the deployment impact force at the time of deployment, and FIG. 8 is a graph showing the deployment impact force at the deployment of the parachute 20 when using the deployment bag 10 according to an embodiment of the present invention.

As shown, the missile includes a vehicle 300, a carrier 200, and the parachute assembly 100 described above.

The carrier body 300 includes a warhead part and an induction control unit that adjusts the flight path correction and the direction change device to combine with one or both ends of the warhead part so that the missile strikes the target. The warhead portion includes a warhead having means for inflicting a physical, chemical or biological blow on the target. The induction adjusting device unit is formed including a radome, a searcher, a navigation system, an induction adjusting device, and the like, which is mainly disposed in front of the warhead, or the components are separated and disposed in front of and behind the warhead.

The carrier 200 transmits power to the carried object 300, and mainly uses solid fuel, and a ramjet engine or a scramjet engine may be used according to a propulsion method.

In the guided missile according to an embodiment of the present invention, the carrier 200 and the carrier 300 are separated and dropped as follows.

 When the guided missile approaches the target and the power is transmitted by the carrier 200, the vehicle 300 except for the carrier 200 must drop while maintaining a sufficient dropping speed without sudden impact.

To this end, first, the carrier 200 is separated from the carrier 300, when the drag is applied, the pulling speed 17 is expanded while the separation speed is increased. When a predetermined force or more is transmitted to the pulling string 17, the cover 120 is separated from the housing by the pulling string 17 connected to the carrier 200. At the same time, the deployment bag 10 connected with the cover 120 is released from the housing, and the line 22 is unfolded.

At this time, even if the line 22 is completely unfolded so that the deployment bag 10 retreats backward, the length of the pull line 17 should not be long enough to reach the carrier 200.

When the line 22 is fully deployed, the coupling part 15 of the deployment bag 10 is released, and the canopy 21 exits from the deployment bag 10, and the parachute 20 is unfolded momentarily, and the parachute is deployed. By 20, the falling speed of the carried object 300 is reduced.

The developing bag 10 is then completely separated from the canopy 21, and flows toward the carrier 200 by elasticity. Finally, the carrier 200 is effectively decelerated while maintaining drag by the wind bag of the deployment bag 10.

7 and 8, when the parachute 20 is deployed by the parachute assembly 100 according to the exemplary embodiment of the present invention, the parachute assembly 100 may have an initial stage than the parachute assembly 100 having no deployment bag 10. It can be seen that the deployment impact force is reduced to a considerable extent.

9 is a conceptual diagram illustrating a method of assembling the parachute assembly 100 according to an embodiment of the present invention in order.

As shown, in the parachute assembly (a) in which the lines 22 are firmly coupled, first, the gores of the parachute 20 are arranged and folded so that the lines 22 are positioned at the center of the canopy 21 in two lines ( b). Connect the end of the canopy 21 with a string, pull it and insert it into the interior of the deployment bag 10 (c). The lower end of the development bag 10 is folded, the canopy 21 is sealed, and the line 22 is inserted into the locking loop so that the line 22 does not fall out (d). The line 22 is divided into two groups, and the line 22 is arranged and fixed using a rubber band or the like (e). The lines 22 are looped so that they are not entangled and arranged neatly in the housing 110 (f). While nesting the deployment bag 10 into which the canopy 21 has been inserted, it is inserted into the housing 110 and connects the connecting ring 11 of the deployment bag 10 with the cover 120 of the parachute assembly 100 ( g).

Such a deployment bag, a parachute assembly having the same, and a method for assembling the same are not limited to the configuration and method of the above-described embodiments, but the embodiments are all or part of each of the embodiments so that various modifications can be made. It may be configured in combination.

Claims (11)

A first body and a second body coupled to each other with the parachute assembly interposed therebetween;
A parachute received in the parachute assembly and having one end coupled to the first body;
A pull string connecting the lid and the second body of the parachute assembly to each other;
When the first body and the second body are separated from each other, the shear chamber for coupling the pull string to the cover so that the pull string pulls the cover while being broken; And
A deployment bag received in the parachute assembly and connected to the lid;
The development bag,
A body accommodated therein in a folded state of the canopy of the parachute; And
A first wind pocket is formed on at least one side of the body,
The first wind pocket,
When the separated second body retracts with the first drag, the second body is further formed to have a smaller area than the body to further generate a second drag to speed up the release bag from the canopy,
The pull string is,
The canopy is formed over a predetermined length so that the parachute and the second body do not come into contact when the parachute is deployed while the canopy exits from the body of the deployment bag,
The second body is a vehicle, characterized in that the vehicle for transmitting power to the first body. The method of claim 1,
The body is characterized in that the plurality of cloth is formed in a trapezoidal shape is attached in the width direction. The method of claim 1,
Attached to the other end in the longitudinal direction of the body, characterized in that it comprises a connecting ring coupled to the parachute assembly cover. The method of claim 1,
And a second wind bag spaced apart from the first wind bag and attached to one side of the body to maintain a shape of the deployment bag, and having a vent formed on one surface thereof.


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