KR20240068383A - Separable aircraft interface system of store and operating method thereof - Google Patents

Abstract

The purpose of the present invention is to make the aircraft interface system for aircraft-launched weapons in the form of a detachable module, so that while the weapons are mounted on the aircraft, they function in a combined form with the weapons, and after being separated from the aircraft, the weapons can be separated. The goal is to provide a detachable interface system for mounting on aircraft that does not degrade the original functionality of the weapon.
In order to achieve the above object, a detachable interface system for mounting on an aircraft according to the present invention includes a lug that can be mounted on a weapons mount of an aircraft; and a sway brace support connected to the lower part of the lug, and is characterized in that it is modularized so that weapons can be attached to or detached from the sway brace support.

Description

Separable interface system for mounting on aircraft and method of operation thereof {SEPARABLE AIRCRAFT INTERFACE SYSTEM OF STORE AND OPERATING METHOD THEREOF}

The present invention relates to a detachable interface system for mounting on an aircraft and a method of operating the same, and more specifically, to a detachable interface system for mounting on an aircraft in which an aircraft interface system for aircraft-launched weapons is formed in the form of a detachable module, and a method of operating the same. will be.

In general, flying vehicles such as guided missiles and bombs that are operated and launched by being mounted on an aircraft (hereinafter referred to as 'aircraft-launched weapons') must meet standard interface specifications for being mounted on an aircraft.

Therefore, in the case of aircraft-launched armament, not only the original shape as armament for flight and mission after launch, but also the shape required for standard interface with the aircraft, such as lugs and wave races, must be additionally reflected.

In the case of most aircraft-launched armaments, the shape required for the aircraft interface is applied in addition to the basic shape as the original armament, but this is accompanied by various types of performance degradation, such as increased weight and volume, and reduced aerodynamic and flight performance.

In other words, the structure for the aircraft interface is only needed while it is mounted on the aircraft, and becomes an unnecessary additional structure after the aircraft-launched weapons are separated from the aircraft.

Therefore, in aircraft-launched weapons, the interface portion for mounting on the aircraft exists only while it is mounted on the aircraft, and the most efficient configuration is if the interface can be removed at the stage when only the original function as an aircraft-launched weapon is required after being launched from the aircraft. can be implemented.

Republic of Korea Patent Publication No. 10-2052430

The purpose of the present invention to solve the conventional problems as described above is to form an aircraft interface system for aircraft-launched weapons in the form of a detachable module, so that while the weapons are mounted on the aircraft, they function in a combined form with the weapons, The aim is to provide a detachable interface system for mounting on an aircraft and a method of operating the same, which prevents the original function of the armament from being degraded by being separated from the armament after being separated from the aircraft.

In order to achieve the above object, a detachable interface system for mounting on an aircraft according to the present invention includes a lug that can be mounted on a weapons mount of an aircraft; A frame connected to the rug; And a sway brace support extending from the frame at a predetermined angle along the longitudinal direction, and is characterized in that it is modularized so that the armament can be mounted or detached.

In addition, the detachable interface system for mounting on an aircraft according to the present invention is characterized by including a fixing part that is connected to the frame and the sway brace support, and wraps around the perimeter of the armament and is in close contact.

In addition, in the detachable interface system for mounting on an aircraft according to the present invention, the fixing part is characterized in that it has a structure in the form of a rigid ring or a metal band.

In addition, the detachable interface system for mounting on an aircraft according to the present invention is characterized by including a restraining part that couples both ends of the fixing part to each other and adds a tightening force to provide a restraining force.

Additionally, in the detachable interface system for mounting on an aircraft according to the present invention, the restraint portion includes restraint members that are separated from each other when the restraint force is released; and a separation member broken to separate the constraint member.

In addition, in the detachable interface system for mounting on an aircraft according to the present invention, the binding force of the restraining unit is released when a command to separate the restraining unit from the armament is applied.

In addition, in the detachable interface system for mounting on an aircraft according to the present invention, the restraining unit is characterized in that when a command to separate from the armament is applied, the separation member is broken and the binding force of the restraining unit is released.

In addition, in order to achieve the above object, the armament of the detachable aircraft mounting interface system according to the present invention maintains a coupling force with the armament while it is mounted on the aircraft, and is separated from the armament after being separated from the aircraft. It is characterized by what can be done.

In addition, in order to achieve the above object, a method of operating a detachable interface system for mounting on an aircraft according to the present invention includes: a first step of separating an interface system for mounting on an aircraft including weapons from a weapons mount on an aircraft; A second step in which, when a command to separate from the armament is approved, the restraining force of the restraining portion of the aircraft mounting interface system is released or the separation member is broken, thereby releasing the binding force of the restraining portion; A third step in which the armament and the interface system for mounting the aircraft are separated.

In addition, in the operating method of the detachable interface system for mounting on an aircraft according to the present invention, the interface system for mounting on an aircraft is characterized in that the interface system for mounting on an aircraft surrounds the circumference of the armament and is in close contact with the weapon by a fixing part.

In addition, in the operating method of the detachable interface system for mounting on an aircraft according to the present invention, the interface system for mounting on an aircraft is characterized in that both ends of the fixing part are coupled to each other by a restraining part and a tightening force is added to provide a restraining force. .

In addition, in the operating method of the detachable interface system for mounting on an aircraft according to the present invention, the restraint unit includes: restraint members that are separated from each other when the restraint force is released; and a separation member broken to separate the constraint member.

In addition, in order to achieve the above object, according to the operating method of the detachable interface system for mounting on an aircraft according to the present invention, the coupling force with the weapon is maintained while the weapon is mounted on the aircraft, and after it is separated from the aircraft, It is characterized in that it can be separated from the armament.

Meanwhile, in order to achieve the above object, the detachable interface system for mounting on an aircraft according to the present invention operates by a method of operating a detachable interface system for mounting on an aircraft.

Specific details of other embodiments are included in “Specific Details for Carrying Out the Invention” and the attached “Drawings.”

The advantages and/or features of the present invention and methods for achieving them will become clear by referring to the various embodiments described in detail below along with the accompanying drawings.

However, the present invention is not limited to the configuration of each embodiment disclosed below, but may also be implemented in various different forms. However, each embodiment disclosed in this specification ensures that the disclosure of the present invention is complete, and the present invention It is provided to fully inform those skilled in the art of the present invention, and it should be noted that the present invention is only defined by the scope of each claim.

According to the present invention, the aircraft interface system of the aircraft-launched weapon is in the form of a detachable module, so that while the weapon is mounted on the aircraft, it functions in a combined form with the weapon, and after it is separated from the aircraft, it is separated from the weapon and the weapon is used. It has the effect of preventing deterioration of its original function.

In addition, by separating the aircraft interface structure that becomes unnecessary after the armament is separated from the aircraft, effects such as reducing the weight and volume of the armament and improving aerodynamic characteristics are achieved, ultimately maximizing the original performance required for the armament. There is an effect that can be done.

1 is a diagram showing a state in which the aircraft interface system combined with armament is mounted on an aircraft in the detachable interface system for mounting on an aircraft according to the present invention.
Figure 2 is a diagram showing a state in which the interface system for mounting an aircraft is mounted on a weapons mount of an aircraft in the detachable interface system for mounting on an aircraft according to the present invention.
Figure 3 is a diagram showing a state in which the armament and the aircraft interface system are combined in a detachable interface system for mounting on an aircraft according to the present invention, immediately after the armament is removed from the aircraft.
Figure 4 is a diagram showing a state in which the armament and the aircraft interface system are separated in the detachable interface system for mounting on an aircraft according to the present invention.
Figure 5 is a perspective view showing the schematic shape of the aircraft interface system in the detachable interface system for mounting on the aircraft according to the present invention.
Figure 6 is a side view showing the schematic shape of the aircraft interface system in the detachable interface system for mounting on an aircraft according to the present invention.
Figure 7 is a front view showing the schematic shape of the aircraft interface system in the detachable interface system for mounting on the aircraft according to the present invention.
Figure 8 is a diagram showing the state of the aircraft interface system for fixing weapons in the detachable interface system for mounting on an aircraft according to the present invention.
Figure 9 is an enlarged view of the area indicated by the dotted line in Figure 8 in the detachable interface system for mounting on an aircraft according to the present invention.
Figure 10 is a diagram showing the state of the aircraft interface system for separating weapons in the detachable interface system for mounting on an aircraft according to the present invention.
11 is a flow chart showing the overall flow of the operation method of the detachable interface system for mounting on an aircraft according to the present invention.

Before explaining the present invention in detail, the terms or words used in this specification should not be construed as unconditionally limited to their ordinary or dictionary meanings, and the inventor of the present invention should not use the terms or words in order to explain his invention in the best way. It should be noted that the concepts of various terms can be appropriately defined and used, and furthermore, that these terms and words should be interpreted with meanings and concepts consistent with the technical idea of the present invention.

That is, the terms used in this specification are only used to describe preferred embodiments of the present invention, and are not used with the intention of specifically limiting the content of the present invention, and these terms refer to various possibilities of the present invention. It is important to note that this is a term defined with consideration in mind.

In addition, it should be noted that in this specification, singular expressions may include plural expressions, unless the context clearly indicates a different meaning, and may include singular meanings even if similarly expressed in plural. .

Throughout this specification, when a component is described as “including” another component, it does not exclude any other component, but includes any other component, unless specifically stated to the contrary. It could mean that you can do it.

Furthermore, if a component is described as being "installed within or connected to" another component, it means that this component may be installed in direct connection or contact with the other component and may be installed in contact with the other component and may be installed in contact with the other component. It may be installed at a certain distance, and in the case where it is installed at a certain distance, there may be a third component or means for fixing or connecting the component to another component. It should be noted that the description of the components or means of 3 may be omitted.

On the other hand, when a component is described as being “directly connected” or “directly connected” to another component, it should be understood that no third component or means is present.

Likewise, other expressions that describe the relationship between each component, such as "between" and "immediately between", or "neighboring" and "directly neighboring", have the same meaning. It should be interpreted as

In addition, in this specification, terms such as "one side", "other side", "one side", "the other side", "first", "second", etc., if used, refer to one component. It is used to clearly distinguish it from other components, and it should be noted that the meaning of the component is not limited by this term.

In addition, in this specification, terms related to position such as "top", "bottom", "left", "right", etc., if used, should be understood as indicating the relative position of the corresponding component in the corresponding drawing. Unless the absolute location is specified, these location-related terms should not be understood as referring to the absolute location.

In addition, in this specification, when specifying the reference numeral for each component in each drawing, the same component has the same reference number even if the component is shown in different drawings, that is, the same reference is made throughout the specification. The symbols indicate the same component.

In the drawings attached to this specification, the size, position, connection relationship, etc. of each component constituting the present invention is exaggerated, reduced, or omitted in order to convey the idea of the present invention sufficiently clearly or for convenience of explanation. It may be described, and therefore its proportions or scale may not be exact.

In addition, hereinafter, in describing the present invention, detailed descriptions of configurations that are judged to unnecessarily obscure the gist of the present invention, for example, known technologies including prior art, may be omitted.

Hereinafter, embodiments of the present invention will be described in detail with reference to the related drawings.

Figure 1 is a diagram showing a state in which the aircraft interface system combined with armament is mounted on an aircraft in the detachable interface system for mounting on an aircraft according to the present invention.

Referring to FIG. 1, it can be seen that in the detachable interface system 200 for mounting on an aircraft according to the present invention, the aircraft interface system 200 combined with the armament 300 is mounted on the aircraft 100. there is.

That is, the aircraft 100 is equipped with weapons 300.

At this time, the armament 300 is mounted on the aircraft 100 through the armament mount 400 of the aircraft 100, and the present invention provides an aircraft interface system for mounting such armament 300 on the armament mount 400. It is about (200).

This aircraft interface system 200 is modularized into an anti-aircraft structure surrounding the armament 300.

Here, the aircraft interface system 200 must basically meet the standard specifications (MIL-STD-8591, etc.) required for mounting aircraft launch weapons on the aircraft 100.

That is, it consists of a lug 210, a sway brace supporter 220, and an injection pin supporter (not shown) of the type required by the standard interface standard, and a structure to support them.

In addition, the aircraft interface system 200 must be capable of being combined with and separated from the armament 300, so it must have a modular, separate structure, and the surface coupled to the armament must have a shape that can be in close contact with the outer surface of the armament.

Let us explain this in more detail.

Figure 2 is a diagram showing a state in which the aircraft mounting interface system is mounted on the weapons mount of an aircraft in the detachable aircraft mounting interface system according to the present invention, and Figure 3 is a detachable aircraft mounting interface according to the present invention. In the system, it is a diagram showing the state immediately after the armament is separated from the aircraft and the armament and aircraft interface system are combined.

Referring to FIG. 2, it can be seen that the aircraft mounting interface system 200 is mounted on the weapons mount 400 of the aircraft 100.

Of course, this aircraft-mounted interface system 200 is modularized to surround the weapon 300.

Referring to FIG. 3, it can be seen that the aircraft mounting interface system 200 is separated from the weapons mounting base 400 of the aircraft 100.

That is, the interface system 200 for mounting on an aircraft, which is modularized while surrounding the armament 300, is mounted on the aircraft in a modular manner while wrapping the armament 300 when separated from the armament mount 400 of the aircraft 100. The interface system 200 itself is separated.

Figure 4 is a diagram showing a state in which the armament and the aircraft interface system are separated in the detachable interface system for mounting on an aircraft according to the present invention.

Referring to FIG. 4, in the detachable interface system 200 for mounting on an aircraft according to the present invention, it can be seen that the armament 300 is separated from the aircraft interface system 200.

That is, as will be explained in more detail later, when the separation member 242 of the interface system 200 for mounting on the aircraft is broken, the restraining member 241 is divided into two and separated, and the armament 300 is attached to the aircraft interface system 200. ) is separated from.

The configuration in which the aircraft mounting interface system 200 is separated from the weapons mounting base 400 of the aircraft 100 will be described in more detail with reference to FIGS. 5 to 10.

Figure 5 is a perspective view showing a schematic shape of the aircraft interface system in the detachable interface system for mounting on an aircraft according to the present invention, and Figure 6 is a schematic view of the aircraft interface system in the detachable interface system for mounting on an aircraft according to the present invention. It is a side view showing the shape, and Figure 7 is a front view showing the schematic shape of the aircraft interface system in the detachable interface system for mounting on an aircraft according to the present invention.

5 to 7, the detachable interface system 200 for mounting on an aircraft according to the present invention includes a lug 210, a sway brace support 220, and a frame 221.

The lug 210 can be mounted on the weapons mount 400 of the aircraft 100.

That is, the weapon mounting base 400 and the lug 210 are connected.

The lug 210 is connected to the frame 221.

The sway brace support 220 extends from the frame 221 at a predetermined angle along the longitudinal direction.

The armament 300 is modularized so that it can be mounted or detached from the sway brace support 220.

The sway brace-lug 210 mounting structure is such that as the clutch bolt (not shown) is tightened, the sway brace pushes the aircraft exterior attachment in the axial force direction, and the lug 210 of the aircraft exterior attachment pulls the weapons mount 400. It is a fixed boundary condition.

A sway brace (not shown) is one of the components of the weapons mount 400 and serves to mount and secure external attachments to the aircraft.

The lug 210 is one of the components of the external aircraft attachment that satisfies the MIL-STD-8591 standard and serves to combine with the weapons mount 400.

The lug capable of mounting external attachments is tapped and combined with the weapon mount 400 of the aircraft 100.

The weapons mount 400 of the aircraft 100 is connected to two lugs 210, and when the weapons mount 400 of the aircraft 100 is viewed from the side, the lugs 210 are mounted in a vertical direction.

In the present invention, the lug 210, the sway brace support 220, and the frame 221 are formed as shown in FIGS. 5 to 7 for ease of explanation, but are not limited thereto, and the lug 210 has various shapes. ), a sway brace support 220, and a frame 221 can be formed.

However, the lug 210 must be connected to the weapons mount 400 of the aircraft 100, and the frame 221 connected to the sway brace support 220 must be connected to the lug 210.

Figure 8 is a diagram showing the state of the aircraft interface system for fixing weapons in the detachable interface system for mounting on an aircraft according to the present invention.

Referring to FIG. 8, the detachable interface system 200 for mounting on an aircraft according to the present invention includes a fixing part 230.

One side of this fixing part 230 is connected to the frame 221 and the sway brace support 220, and wraps around the circumference of the armament 300 and is in close contact.

This fixing part 230 may have a structure in the form of a rigid ring or metal band.

That is, since the shape of the middle region of the armament 300 has a cylindrical shape, in order to surround the armament 300, the fixing part 230 has a rigid ring shape or a metal band surrounds the outer surface of the armament 300. It may have a structure of the form.

Meanwhile, the restraint part 240 is connected to the other side of the fixing part 230.

Referring to FIG. 8, the member located within the circle of the dotted line is the constraint portion 240.

This restraint part 240 will be described in more detail with reference to FIG. 9 .

FIG. 9 is an enlarged view of the area indicated by a dotted line in FIG. 8 in the detachable interface system for mounting on an aircraft according to the present invention.

Referring to FIG. 9, the detachable interface system 200 for mounting on an aircraft according to the present invention includes a restraining portion 240.

Here, the restraining part 240 couples both ends of the fixing part 230 to each other and adds a tightening force to provide a binding force.

That is, one end of the plurality of fixing parts 230 is connected to both sides of the frame 221 and the sway brace support 220, and the other end of the plurality of fixing parts 230 is connected to the restraint part 240, respectively.

In the present invention, the restraint portion 240 is described as having the shape shown in FIG. 8 for ease of explanation, but is not limited thereto. The restraint portion 240 includes a fixing portion 230 surrounding the armament 300. It serves as a finishing treatment so that the armament (300) can be closely attached.

That is, the restraining part 240 serves to restrain the fixing part 230 so that the fixing part 230 can surround and adhere to the armament 300.

This restraint part 240 includes a restraint member 241 and a separation member 242.

Here, the restraining members 241 are formed in plural pieces, and are separated from each other when the restraining force is released.

Additionally, the separation member 242 is broken to separate the restraining member 241.

That is, when the separation member 242 is broken, the binding force of the restraining member 241 is released and the plurality of restraining members 241 are separated.

Thereby, the armament 300 is separated from the interface system 200 for mounting on the aircraft.

Meanwhile, an elastic member (not shown) may be further included between the outer surface of the armament 300 and the fixing part 230 in the form of a rigid ring or metal band.

Such elastic members may be mechanical springs or other attachments that have a separating force.

These elastic members can add separation force when the binding force is released.

More specifically, when the restraining members 241 of the restraining unit 240 are separated from each other when the binding force is released, or the separation member 242 is broken, the binding force of the restraining member 241 of the restraining portion 240 is released. This causes the plurality of restraining members 241 to be separated.

In this way, when the binding force of the restraining member 241 is released and they are separated from each other, or the separation member 242 is broken and the binding force of the restraining member 241 is released, a position is located between the outer surface of the armament 300 and the fixing portion 230. The elastic member adds further separation force.

That is, when the binding force of the restraint part 240 is released, the elastic member further adds a separation force between the armament 300 and the restraint part 240 using elastic force.

Meanwhile, as a member that maintains the connection or enables separation, various methods are applied, such as a method using a pyro as an operating source such as an explosion bolt or pyro pusher, a method using pneumatic pressure, and a method using electric driving force. can do.

Thereby, the armament 300 is separated from the interface system 200 for mounting on the aircraft.

In other words, the fixing part 230, the restraining member 241 and the separating member 242 of the restraining part 240 firmly couple the armament 300 and the aircraft interface system 200, and then the separation signal is transmitted. When delivered, it must have a function to allow the weapons 300 and the aircraft interface system 200 to be smoothly separated by adding the necessary separation force after releasing the restraints.

The fixing part 230 and the restraining part 240 are formed in a ring shape made of a flexible structure such as a rigid body or a metal band, so that they surround the circumference of the armament 300 and adhere closely to the outer surface to maintain a strong connection. Apply.

The fixing part 230 and the restraining part 240 of this type are divided into two parts so that they can be separated and combined to maintain a restrained state, and the restraint is maintained by applying a separation function when necessary by applying a separable member. Make sure to release it.

As a member that maintains the connection or enables separation, various methods can be applied, such as a method using a pyro as an operating source such as an explosion bolt or pyro pusher, a method using pneumatics, or a method using electrical driving force. there is.

Figure 10 is a diagram showing the state of the aircraft interface system for separating weapons in the detachable interface system for mounting on an aircraft according to the present invention.

Referring to FIG. 10, when a command to separate the above-described restraint unit 240 from the weapon 300 is issued, the binding force of the restraint unit 240 is released and the restraint unit 240 is separated.

More specifically, the restraining member 241 of the restraining portion 240 is separated, and the binding force of the restraining portion 240 is released and separated.

Thereby, the weapon 300 is separated from the aircraft interface system 200.

In addition, in the detachable interface system 200 for mounting on an aircraft according to the present invention, when a command to separate the restraint portion 240 from the armament 300 is applied, the separation member 242 is broken and the restraint portion 240 is Binding may be lifted.

That is, when the separation command is applied, the separation member 242 of the restraint part 240 is broken.

Due to such rupture of the separation member 242, the restraining member 241 of the restraining portion 240 may be separated, thereby releasing the binding force of the restraining portion 240.

Thereby, the armament 300 is separated from the aircraft interface system 200.

Meanwhile, the detachable interface system 200 for mounting on an aircraft according to the present invention maintains a coupling force with the armament 300 while the armament 300 is mounted on the aircraft 100, and interfaces for mounting the aircraft on the aircraft 100. After the system 200 is separated, it can be separated from the armament 300.

Figure 11 is a flow chart showing the overall flow of the operation method of the detachable interface system for mounting on an aircraft according to the present invention.

Referring to FIG. 11, the operating method of the detachable interface system 200 for mounting on an aircraft according to the present invention includes three steps.

In the first step (S100), the aircraft mounting interface system 200 including weapons 300 is separated from the weapons mounting base 400 of the aircraft 100.

In the second step (S200), when a command to separate from the armament 300 is approved, the binding force of the restraint portion 240 of the aircraft-mounted interface system 200 is released or the separation member 242 is broken and the restraint portion is separated. The binding force of (240) is lifted.

In the third step (S300), the weapon 300 and the interface system 200 for mounting on the aircraft are separated.

Through these three steps, the detachable interface system 200 for mounting on an aircraft according to the present invention is operated, and other components have the same functions as described above.

For example, in the method of operating the detachable aircraft-mounted interface system 200 according to the present invention, the fixing portion 230 of the aircraft-mounted interface system 200 surrounds the circumference of the weapon 300 and is in close contact with it.

In addition, the restraint part 240 of the interface system 200 for mounting on an aircraft couples both ends of the fixing part 230 to each other and adds a tightening force to provide a restraint force.

At this time, the restraint part 240 may include a restraint member 241 that is separated from each other when the restraint force is released, and a separation member 242 that is broken to separate the restraint member 241.

Meanwhile, an elastic member (not shown) may be further included between the outer surface of the armament 300 and the fixing part 230 in the form of a rigid ring or metal band.

Such elastic members may be mechanical springs or other attachments that have a separating force.

These elastic members can add separation force when the binding force is released.

Meanwhile, as a member that maintains the connection or enables separation, various methods are applied, such as a method using a pyro as an operating source such as an explosion bolt or pyro pusher, a method using pneumatic pressure, and a method using electric driving force. can do.

More specifically, when the restraining members 241 of the restraining unit 240 are separated from each other when the binding force is released, or the separation member 242 is broken, the binding force of the restraining member 241 of the restraining portion 240 is released. This causes the plurality of restraining members 241 to be separated.

In this way, when the binding force of the restraining member 241 is released and they are separated from each other, or the separation member 242 is broken and the binding force of the restraining member 241 is released, a position is located between the outer surface of the armament 300 and the fixing portion 230. The elastic member adds further separation force.

That is, when the binding force of the restraint part 240 is released, the elastic member further adds a separation force between the armament 300 and the restraint part 240 using elastic force.

According to the operation method of the detachable interface system 200 for mounting on an aircraft according to the present invention, the interface system 200 for mounting on an aircraft is configured to operate the weapon 300 and the weapon 300 while the weapon 300 is mounted on the aircraft 100. After maintaining the coupling force and the armament 300 is separated from the aircraft 100, the aircraft mounting interface system 200 may be separated from the armament 300.

Meanwhile, the detachable interface system 200 for mounting on an aircraft according to the present invention operates according to the operation method of a detachable interface system for mounting on an aircraft.

In this way, according to the present invention, the aircraft interface system of the aircraft-launched weapon is in the form of a detachable module, so that while the weapon is mounted on the aircraft, it functions in a combined form with the weapon, and after it is separated from the aircraft, the weapon is separated. This has the effect of preventing the original function of the armament from being degraded.

In addition, by separating the aircraft interface structure that becomes unnecessary after the armament is separated from the aircraft, effects such as reducing the weight and volume of the armament and improving aerodynamic characteristics are achieved, ultimately maximizing the original performance required for the armament. There is an effect that can be done.

Above, various preferred embodiments of the present invention have been described by giving some examples, but the description of the various embodiments described in the "Detailed Contents for Carrying out the Invention" section is merely illustrative and the present invention Those skilled in the art will understand from the above description that the present invention can be implemented with various modifications or equivalent implementations of the present invention.

In addition, since the present invention can be implemented in various other forms, the present invention is not limited by the above description, and the above description is intended to make the disclosure of the present invention complete and is commonly used in the technical field to which the present invention pertains. It is provided only to fully inform those with knowledge of the scope of the present invention, and it should be noted that the present invention is only defined by each claim in the claims.

100: aircraft
200: Interface system for aircraft mounting
210: rug
220: Sway brace support
221: frame
230: fixing part
240: Restraint part
241: member of restraint
242: Separating member
300: Armed
400: Armed mount

Claims (14)

Lugs that can be mounted on an aircraft's weapon rack;
A frame connected to the rug; and
It includes a sway brace support extending from the frame at a predetermined angle along the longitudinal direction,
Characterized by being modularized so that the armament can be mounted or detached.
Detachable interface system for aircraft mounting.
According to claim 1,
Characterized in that it includes a fixing part that is connected to the frame and the sway brace support, and wraps around the perimeter of the armament and is in close contact with the armament.
Detachable interface system for aircraft mounting.
According to claim 2,
The fixing part is characterized in that it has a structure in the form of a rigid ring or metal band.
Detachable interface system for aircraft mounting.
According to claim 2,
Characterized in that it includes a restraining part that couples both ends of the fixing part to each other and adds a tightening force to provide a binding force.
Detachable interface system for aircraft mounting.
According to claim 4,
The restraint part,
Constraint members separated from each other when the restraint force is released; and
Characterized in that it includes a separation member that breaks to separate the constraint member.
Detachable interface system for aircraft mounting.
According to claim 5,
The restraint part,
Characterized in that when the command to separate from the armament is approved, the binding force of the restraint part is released,
Detachable interface system for aircraft mounting.
According to claim 5,
The restraint part,
Characterized in that when the command to separate from the armament is approved, the separation member is broken and the binding force of the restraint portion is released.
Detachable interface system for aircraft mounting.
The weapon according to any one of claims 1 to 7, characterized in that it maintains a coupling force with the weapon while the weapon is mounted on the aircraft and can be separated from the weapon after it is separated from the aircraft.
Detachable interface system for aircraft mounting.
A first step in which an interface system for mounting an aircraft including weapons is separated from a weapons mount on the aircraft;
A second step in which, when a command to separate from the armament is approved, the restraining force of the restraining portion of the aircraft mounting interface system is released or the separation member is broken, thereby releasing the binding force of the restraining portion;
A third step in which the armament and the interface system for mounting the aircraft are separated,
Method of operation of a detachable aircraft mounting interface system.
According to clause 9,
The interface system for mounting on the aircraft is characterized in that it surrounds the circumference of the armament and adheres closely to it by a fixing part.
Method of operation of a detachable aircraft mounting interface system.
According to claim 10,
The interface system for mounting on an aircraft is characterized in that both ends of the fixing part are coupled to each other by a restraining part and a tightening force is added to provide a restraining force.
Method of operation of a detachable aircraft mounting interface system.
According to claim 11,
The restraint part,
Constraint members separated from each other when the restraint force is released; and
Characterized in that it includes a separation member that breaks to separate the constraint member.
Method of operation of a detachable aircraft mounting interface system.
Characterized in that, according to any one of claims 9 to 12, the armament maintains a coupling force with the armament while it is mounted on the aircraft, and can be separated from the armament after being separated from the aircraft.
Method of operation of a detachable aircraft mounting interface system.
A detachable aircraft-mounted interface system operated by the method of operating a detachable aircraft-mounted interface system according to any one of claims 9 to 12.

Images