KR101083224B1 - Auto Loading Equip Launcher for Attatching and Detatching in Helicopter, and Horizon Moving System Using the same - Google Patents

Abstract

The present invention relates to an automatic feeder armed vehicle that can be detachably attached to military personnel and material transport helicopters, and a horizontal transport apparatus using the same, which is generated by armed installation if necessary to equip military personnel / material transport helicopters (anti-tank missiles, rockets, etc.). In order to minimize the effects of drag and maneuverability (Roll maneuver), it is possible to transfer to the automatic fired and fired position of the armed in the cabin.

Automatic grenades equipped with the present invention for this purpose, at least one rail mounting the missile; And first and second horizontal moving elements installed in parallel to transport the rail from an aircraft or helicopter to an external launch pad or vice versa, wherein the rail is inclined at an angle when the rail is transported. It characterized in that for controlling the operation of the first and second horizontal moving element to be transferred to.

IRAMS, rail, guide hole, guide part, line part, first horizontal moving element, first rotating axis, second horizontal moving element, second rotating axis, aircraft structure, missile.

Description

Auto loading Equip Launcher for Attatching and Detatching in Helicopter, and Horizon Moving System Using the same}

The present invention relates to an automatic feeder armed vehicle that can be detachably attached to military personnel and material transport helicopters, and a horizontal transport apparatus using the same. More specifically, when equipped with military personnel / material transport helicopters (anti-tank missiles, rockets, etc.) required Automatic ammunition armed and detachable to military personnel and material transport helicopters capable of being transported to armed automatic firing and firing positions in the cabin to minimize the effects of drag and roll maneuver caused by armed mounting; It relates to a horizontal transfer device using the same.

In general, an armed helicopter is a modification of a transport or reconnaissance helicopter equipped with weapons to perform cover missions. This refers to the case where helicopters developed without the intention of securing the attack capability at the time of the first development are pursuing the attack capability through additional modification to secure various mission capabilities after the development of the helicopter.

The main features of the armed helicopters include a side-by-side cockpit arrangement and a large personnel / material (armed) internal loading space, which can be used for personnel / material transport in addition to attack purposes.

In the case of securing an attack capability through the installation of missiles, etc. in an aircraft for transporting personnel or materials such as a helicopter, as shown in FIG. 1A, a separate armed wing is installed and an armed pylon is installed there. In general, the fixed operation method was used in which the necessary weapons were exposed to the outside.

However, the fixed operation method exposed to the outside of the aircraft has a problem of lowering the aerodynamic performance to the seaport generated during the flight and lowering the ROLL characteristics of the aircraft.

Therefore, in order to solve such a problem, the armed retraction design for a helicopter or the like, that is, a mechanism for loading missiles, such as missiles, into the cabin of the aircraft during flight, and transporting missiles, such as missiles, to the outside when necessary to be fired. This is necessary.

In recent years, the United States developed the IRAMS (Integrated Retracrable Aircraft Munition System, 10), which is a GooseNeck Type Hinge-type open / close door with a RAH-66 Comanche helicopter.

As the IRAMS 10 is inevitable to apply a large door and structure cutout to fit the size of the mounted missile, it is difficult to apply a monocoque structure that is widely used in existing aircraft, as shown in FIG. 1B. The internal main structure was developed into a unique structure with several box-shaped frames.

As shown in FIG. 2, the IRAMS 10 includes a Hydra-70 Universal Rail Launcher (HURL, 11), a Stinger Universal Launcher (SUL, 12), and a Hellfire Rail (13) in a DOOR equipped with a GooseNeck Type Hinge. Include.

In case of developing Hinge-Door attachment type as in the case of RAH-66 development in USA, (i) It is impossible to apply monocoque structure that transmits the load like the structure of general aircraft, and (ii) Penalty in heavy weight or strength. (I) There is a problem that requires the design of a separate load-bearing structure.

In addition, (i) the IRAMS is a matter that can be applied to a newly developed aircraft or a structure of the existing developed aircraft, there is a problem that can not be applied.

3 is a schematic illustration of a conventional four-arm Hellfire missile launcher (Launcher) for armed / attack helicopters.

Table 1 below is the main specifications of the Hellfire missile launchers.

 The launch pad consists of a total of four missile mounting rails, a support structure, a missile controller, and a wire harness, and is a slide mounting structure that is pushed and loaded through a rail groove from the front.

After the warlord pushes the missile onto the mounting rail, the latch switch in the lower part of FIG. 3 rotates the wire harness and the missile for data communication. Of course, it is a structure that slides forward when firing and leaves naturally.

Although it is very efficient in operation, it has a large number of external protrusions, which may be a major factor in reducing the aerodynamic characteristics of an armed / attack helicopter.

Therefore, the shape to be proposed in the present invention is assumed to be an armed helicopter operating the Hellfire missile to derive an efficient concept shape and transport mechanism.

The present invention has been made to solve the problems of the prior art, the object of the present invention is the effect of drag and maneuverability (Roll maneuver) caused by armed installation when armed (anti-tank missile, rocket, etc.) equipped with military personnel / material transport helicopter In order to minimize the need to provide automatic weapons of the armed and stowed in the room to provide a military personnel and material transport helicopters that can be attached to the removable automatic weapons equipped with a weapon and a horizontal transfer device using the same.

In addition, another object of the present invention is to equip an aircraft, such as a helicopter, such as missiles in the aircraft cabin of the aircraft (Cabin) of the aircraft armed, military personnel and materials to be transported to launch only missiles used outside The present invention provides an automatic coal-fired weapon mount equipped with a removable helicopter and a horizontal transportation device using the same.

In addition, another object of the present invention is to overcome the narrow price of the main structure without the installation of a separate load-bearing structure in the existing aircraft to transport military personnel and materials that can be launched by transporting weapons such as missiles from the inside to the outside of the aircraft The present invention provides an automatic feeder weapon mount equipped with a helicopter and a horizontal transport apparatus using the same.

In addition, another object of the present invention is that the size of the object to be transported as well as the size of the fixed structure to pass through, if the size is larger than the destruction of the fixed structure or installation of a separate structure to enter or exit the object to be transported To provide a detachable automatic grenades equipped with detachable military personnel and material transport helicopters, and a horizontal transfer device using the same.

As a means for solving the above problems, the automatic feed weapon armed vehicle according to the present invention, at least one rail to mount the missile; And first and second horizontal moving elements installed in parallel to transport the rail from an aircraft or helicopter to an external launch pad or vice versa, wherein the rail is inclined at an angle when the rail is transported. It characterized in that for controlling the operation of the first and second horizontal moving element to be transferred to.

The first and second horizontal moving elements respectively form a first rotating shaft and a second rotating shaft coupled to one end and the other end of the rail, and the rail includes a guide having a guide hole coupled to the first rotating shaft. part; And a line portion coupled with the second rotation shaft to correspond to a change in displacement of the second rotation shaft with respect to the first rotation shaft by separate operations of the first and second horizontal moving elements.

Each of the first and second horizontal moving elements is controlled using a linear motion module and a step motor.

The first and second horizontal moving elements are characterized in that composed of any one of a ball screw (Screw), a chain, a belt.

As a means for solving the above problems, the horizontal transfer apparatus according to the present invention, at least one rail; And first and second horizontal moving elements installed in parallel to convey the rail in a horizontal direction, wherein the rails are conveyed in an inclined state at an angle when the rail is conveyed. It characterized in that to control the operation of the horizontal movable element, respectively.

The first and second horizontal moving elements are characterized in that composed of any one of a ball screw (Screw), a chain, a belt.

According to the present invention, an aircraft such as a helicopter is equipped with an armed weapon, such as a missile, and transports and launches only a transport target such as a missile used when necessary to prevent the degradation of aerodynamic performance and roll characteristics of the aircraft. It can work.

In addition, an aircraft such as a helicopter for transporting existing personnel or materials may be equipped with missiles, etc., and may be used by transporting only the objects to be used when needed, without changing load supporting structures or aircraft structures. It has an effect.

In addition, there is an effect that can be effectively transported from the inside to the outside or from the outside to the inside without changing the structure in the situation that the transfer object to pass through the narrow structure as well as the armed transfer to the aircraft.

The terms or words used in this specification and claims are not to be construed as limiting in their usual or dictionary meanings, and the inventors may appropriately define the concept of terms in order to best explain their invention in the best way possible. It should be interpreted as meaning and concept corresponding to the technical idea of the present invention based on the principle that the present invention. In the drawings, parts irrelevant to the description are omitted in order to clearly describe the present invention, and the same reference numerals will be used for components having the same functions and functions when describing the embodiments of the present invention.

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

In general, to simplify the structure of the missile and launcher (Launcher) mounted on the helicopter, the missile is mounted on the rail (Rail), the rotating shaft (Fitting) of the launcher (Launcher) equipped with the rail (Titting) two points (Point) Supported by

Figure 4 is a block diagram of a rail (Rail) mounted on the horizontal transfer apparatus capable of posture control according to the present invention.

As shown in Figure 4, the rail (Rail, 20) is mounted on the horizontal transfer apparatus capable of posture control according to the present invention is a guide portion 23 formed with a guide hole (Guid Hole, 21) in the existing rail shape As a shape added with, it is the basis of the following basic mechanism configuration.

5 is a view showing the basic mechanism of the horizontal transfer apparatus capable of posture control according to the present invention.

In Fig. 5, the x-axis direction is the direction of movement of the object to be transported, and the y-axis direction is perpendicular to the x-axis and is in the direction of the aircraft such as a helicopter or the direction of movement of the object.

As shown in FIG. 5, the rail 20 is fixed to the first rotary shaft 31 and the second rotary shaft 41. In this case, the first rotation shaft 31 serves as a rotation reference axis when the rail 20 performs a rotational movement. That is, the length in the y-axis direction of the rail 20 in the state fixed by the first rotary shaft 31 and the second rotary shaft 41 corresponds to A.

When any one of the horizontal moving elements to which the first rotary shaft 31 or the second rotary shaft 41 is fixed moves in the x-axis direction, the rail 20 is set based on the first rotary shaft 31 as a reference axis. Is rotated and the second rotary shaft 41 is moved to the point of the second rotary shaft 41 corresponding to the rotary motion. Therefore, the A in the y-axis direction at the initial position has the effect of reducing to B.

That is, the y-axis direction is the direction of the aircraft, the x-axis direction is the direction of movement of the object to be transported, the spacing of the structure of the aircraft (eg, the aircraft body door) through which the object to be transported is greater than the A When narrow and longer than B, as shown in FIG. 4, the rail 20 is rotated about the first axis of rotation 31 as a reference axis so that the length in the y-axis direction is reduced from A to B so that Can pass through the structure.

In addition, the rail 20 of the present invention separately configured a special type of rail as shown in FIG. 6 for automatic connection of the data transmission connector of the Hellfire missile at the time of loading.

Briefly explaining the connection mechanism of the signal transmission connector of the rail, see FIG.

1. Maintain the attitude of ① until the missile is fully loaded into the rail.

2. After that, combine Data Transfer Connector as ②-> ③.

Here, rolling bearings were applied to the upper end for smooth loading.

The missile transfer mechanism was configured using the above basic mechanism, and the concept of operation is shown in FIG. 7.

7 is a configuration diagram of a specific armed transfer mechanism of a horizontal transfer apparatus capable of controlling posture according to the present invention, and two horizontal moving elements 30 and 40 capable of two precise controls for horizontal movement of the fitting. And a horizontal moving device with a step motor.

The horizontal moving elements 30 and 40 are horizontally disposed, and the rail 20 is fixed by the first rotation shaft 31 and the second rotation shaft 41. The guide hole 21 is coupled to the first rotating shaft 31 formed on the first horizontal moving element 30, and the line portion is formed on the second rotating shaft 41 formed on the second horizontal moving element 40. 27 of FIG. 4 is combined.

The first and second horizontal moving elements 30 and 40 may be independently controlled and may use two linear control modules and a step motor.

The present invention can be applied to a fixed wing aircraft such as a conventional transport aircraft with the same configuration and operation, in this case, not only bombs to be launched free-fall, but also transported objects such as missiles that need to be fired in front of the aircraft loaded inside the aircraft. Application is possible.

In addition, the present invention can be applied to all objects requiring automatic transfer in the situation where the object to be passed through the structure, such as a door of a narrow width, as well as armed such as aircraft.

For example, by designing a conveyor belt, it is possible to design automation by the same configuration and operation as the present invention. In this case, the first and second horizontal moving elements can control the attitude of the object to be conveyed using a belt or a chain.

The transfer process of the mechanism of the present invention is as follows.

First, in a state where the first horizontal moving element 30 is stationary, the second horizontal moving element 40 is moved in the x-axis direction so that the posture of the missile 70, which is the object to be transferred, is changed from (a) to (b). To convert. As a result, the y-axis direction of the missile 70 becomes shorter than a gap between aircraft structures.

Then, the first and second horizontal moving elements 30 and 40 are simultaneously moved in the x-axis direction to move the position from (b) to (c). In this case, the missile 70 passes between the narrow aircraft structures 50.

Then, the second horizontal moving element 40 stops and moves only the first horizontal moving element 30 in the x-axis direction to change the attitude of the missile 70 from (c) to (d). Here, the direction of the missile 70 transferred to the outside is parallel to the y-axis direction that is the direction of the aircraft again.

Then, the first and second horizontal moving elements 30 and 40 are simultaneously moved in the x-axis direction to move to the (e) position of the firing position.

Then, after launching the missile 70, the rail 20 is moved in the reverse order of the first step to the fourth step to return to the position (a).

By the above mechanism, the missile 70, which is the object to be transported, may be transported to the outside by passing through a narrow helicopter structure inside the helicopter and launched.

In addition, the horizontal control device capable of controlling the attitude according to the present invention, as shown in Figures 8 and 9 to simplify the structure, by utilizing the first and second horizontal moving elements (30, 40) The structure can be simplified by serving as a spar to support the structural load between the ribs of the ribs.

This mechanism allows a long missile to pass through the narrow inter-structure openings (doors) as in the model of FIG. 8.

In addition, the LM module used as shown in Figure 9 for the simplicity of the structure was designed to serve as a spar (Spar) to support the structural load between the wing rib (Wing Rib).

The dimensions of the Linear Motion Module used in the concept design are applied to the MKK model (manufactured by Hansol LM System) as shown in the following figure. Sufficient support and fast transfer can be seen in the main product specifications described below. Many advantages, such as speed and simple structure, confirm that this type of dynamic component application is sufficiently possible (see FIG. 10).

-Length: up to 12m,

-Cross section width x width: 65mm × 85mm

-Load and moment: Load C 48,700 N, longitudinal moment ML 2,900 Nm, torsion moment Mt 1,040 Nm

Static load capacity: up to 1,000 kg

Speed: up to 10 m / s

-Precision: repeatability up to 0.005mm, positioning accuracy up to 0.01mm

In addition, in order to effectively utilize the mechanism, it is necessary to configure an additional mechanism for loading missiles into the available space in the aircraft cabin and automatically loading them.

Thus, the automatic loading mechanism mechanism of the concept as shown in FIG.

This mechanism designs a missile loading box with missile loading, up / down movement and control mechanisms behind a wing structure that traverses the cabin and moves horizontally forward and backward with the rail in the initial loading position. It was configured by adding a push mechanism.

The pushing mechanism was also designed using a ball screw (see FIG. 12).

The conceptual design as shown in FIG. 13 was completed by combining the above mechanisms.

In addition, modeling of the comparison target to which the existing concept is applied is performed as shown in FIG. 14 to compare / analyze the effect when the new concept is applied.

The existing concept is to install the missile launcher on the lower part of the wing, so that the wing is positioned higher than the new concept model to secure the minimum ground clearance.

Indeed, additional structural reinforcement is inevitable to support the load when the wing is mounted above the middle height of the fuselage. However, this model excludes the reinforcement of the fuselage for the conservative comparison of the new conceptual model.

Therefore, this study only reflects the weight added to missiles, wings, launchers, etc., and does not consider the reinforcement of the fuselage structure.

The following describes the effects that occur when applying the armless concept of the present invention.

1. Overview

The aerodynamic performance of a rotorcraft can be identified by the total required horsepower [HP] for each flight type and consists of the sum of the required horsepower as shown below.

Total horsepower required [HP] = [HP Induced Power] + [HP Profile Power] + [HP Parasite Power]

-Induced Power: The power required to produce the lifting thrust

-Profile Power: The power required to overcome rotor torque

-Parasite Power: The power required to overcome fuselage drag

The helicopter demand horsepower for a helicopter having one main rotor and tail rotor of the present invention consists of the sum of the main rotor demand horsepower, tail rotor demand horsepower and transmission loss.

The horsepower required for tail rotor is calculated using the following required horsepower formula for 60kts or less, and for speeds above 10% of main horsepower is generally applied.

(1) FORWARD FLIGHT

The total required power during the forward flight is expressed as the sum of the induced power, the profile power, and the parasite power required to overcome the main rotor induced drag, the main rotor profile drag, and the fuselage parasite drag as described above. The focus is on reducing parasite power.

When Parasite Drag is D _P , the following relation is established.

The following table shows flat plate area values for several aircraft (four helicopters and one fixed wing) in forward flight.

In Table 2, helicopters generally have a very large flat plate area compared to fixed-wing aircraft, and in addition, the flat plate area of the AH-64 attack helicopter is larger (about 1.5 times) than the SH-3 of similar weight. It can be inferred that the drag caused by the external attachment (armed) can have a very large effect on the forward drag.

Figure 15 shows the relationship between the required power factors for the forward speed of a 20,000lb helicopter with a 3-lobed rectangular blade, showing a general trend.

As can be seen from FIG. 15, it can be seen that the higher the forward speed, the higher the required Parasite Power due to the drag generated in the fuselage. It can be seen that if the forward drag of the fuselage and external installation is reduced, the required power can be reduced at high speed forward flight, resulting in high fuel economy and high speed.

2. Method of comparing and analyzing the effects of new armed concept vs existing concept

When the concept newly proposed in the present invention is applied, Parasite Drag is expected to be drastically reduced compared to an aircraft that mounts and operates all of the missiles outside as in the conventional method by flying only one missile on one armed wing. In order to be able to confirm the difference accordingly, a quantitative comparison was further performed.

Therefore, by using the aerodynamic performance data and related analysis tools of KUH aircraft currently under development in Korea, the effects of quantitative analysis were compared by comparing the aircraft with the new concept with the aircraft with the existing concept.

For this, the analysis was carried out through the following process.

i) Incorporate new concepts and perform modeling at the concept design level using CATIA S / W. At this time, modeling as close as possible to the physical appearance by utilizing the specifications of Hellfire Missile

ii) Additional modeling of existing concepts for comparison

iii) Calculate Flat Plate Drag Area using aerodynamic analysis S / W

iv) Design the weight DB of each component of the designed model (CATIA)

v) Perform key point performance comparison / analysis using aircraft performance analysis S / W as input value of aerodynamic analysis result and weight prediction value

3. Aerodynamic Analysis

(1) CFD S / W used

The computational fluid analysis program used in the fuselage / fitting aerodynamic analysis to compare the effects of the new concept and the existing concept is SC / Tetra, an CFD program based on an unstructured mesh developed by CRADLE in Japan in 1998.

SC / Tetra adopts node-based FVM and consists of the latest numerical algorithm.

This CFD S / W is the S / W applied to the KUH development project. The CFD S / W is the S / W that is validated / appropriate through the use / verification of wind tunnel test results of the fuselage model shown in FIG.

(2) CFD analysis conditions

Solver and main analysis conditions used in CFD analysis are as follows.

* CFD Analysis S / W: SC / TETRA

Unstructured Grid (Tetra Grid, with Prism Layer)

-Incompressible Navier-Stock solver

MP k-e Turbulence model

Scale: 1/1

* CFD Analysis Information

Element Number

New concept case (2 missile)-about 8 million

Old concept case (16 missile)-about 13 million

V∞ = 72 m / s (140 knot), AoA = 0 °

Convergence: 10-4

* CFD Analysis Results

-Drag, Cp

The grating consists of an unaligned grating. The number of grids used is about 8 million to 13 million, and y + is less than 10. 17 and 18 show the size of the calculation region and the grid distribution around the fuselage for the fuselage analysis.

(3) CFD analysis result

19 is a view showing a mechanism applied model front drag distribution of the present invention, Figure 20 is a view showing a mechanism applied model aerodynamic analysis results of the present invention.

Fuselage: X.XXX m ²

Wing (2EA): 0.197 m ²

Armless Rail ① ~ ②: 0.0072, 0.0073 m ²

Missile ① ~ ②: 0.0090, 0.0090 m ²

=> Total: Fuselage + (Wing + Rail + Missile) = x.xxx + 0.023 m ²

FIG. 21 is a diagram illustrating a model front drag distribution of a conventional concept comparison object, and FIG. 22 is a diagram illustrating aerodynamic analysis results of a conventional concept comparison object model.

The results of the previous drag distribution and aerodynamic analysis are as follows.

Fuselage: X.XXX m ²

Wing (2EA): 0.327 m ²

Armed Pylon ① ~ ④: 0.1293, 0.1352, 0.1348, 0.1295 m ²

Missile ① ~ ④: 0.0521, 0.0563, 0.0556, 0.0539 m ²

=> Total: Fuselage + (Wing + Armed Pylon + Missile) = x.xxx + 1.074 m ²

4. Weight / MOI Analysis

(1) Conceptual Model Breakdown and Weight / C.G. / MOI Measurement of the Present Invention

FIG. 23 is a view showing a model index of a missile, a wing skin, and a pusher according to the present invention, FIG. 24 is a view showing a model index of a pusher detail, and FIG. 25 is a view of a wing rib ( FIG. 26 is a view showing a model index of Rib), FIG. 26 is a view showing a model index of an LM module and a step motor, and FIG. 27 is a view showing track and fitting details.

Table 3 below shows additional component weight / C.G / MOI measurement results.

Table 4 below shows the results of the mechanism application model weight / C.G. / MOI analysis of the present invention.

(2) Breakdown of existing conceptual models and measurement of weight / C.G. / MOI

28 to 34 show the blackdown and index of the existing conceptual model, FIG. 28 shows the model index 1 of the missile, launch pad, and wing skin, and FIG. 29 shows the wing ribs. Fig. 30 shows the model index 2 of the missile, the wing skin, and the pusher, Fig. 31 shows the model index 2 of the pusher detail, and Fig. 32 shows the model index 2 of the wing rib. 33 is a diagram showing a model index 2 of the LM module and the step motor, and FIG. 34 is a diagram showing a model index 2 of the track and fitting details.

Table 5 below shows the weight / C.G. / MOI measurement results for each additional component when applying the existing concept.

Table 6 below shows the weight / C.G. / M.O.I. The analysis results are shown.

5. Major Point Performance Prediction Results

30 is a result of comparing the main performance of the concept of the present invention and the existing concept.

The old concept refers to the existing concept application model, and the new concept refers to the new draft concept application model. Sea Level, Standard Atmosphere (ISA). This performance was calculated using the performance prediction S / W used in KUH and the power performance of KUH.

Looking at the results of the analysis, when the new concept is applied, a partial weight increase is reflected as a conservative prediction of the additional mechanism configuration, and the vertical performance (VROC, HOGE), etc., the concept of new design shows a slightly lower performance, but the forward speed and range However, Endurance shows a fairly high number of new concepts. (About x kts difference between top speeds)

The numerical values in this analysis were treated as "xxx" for security reasons as a characteristic of military aircraft under development.

As described above, the present invention has developed and embodied a new concept of a mechanism that has not been attempted in the past for the purpose of overcoming the shortcomings identified through the case analysis of the armed helicopter, and predicted the effect by the analytical technique.

The armed concept of the existing armed helicopters was a structure that had to be lost in many aspects, such as the flight performance and maneuverability of the aircraft.

Except for some advanced countries, it is difficult to acquire / operate expensive attack-only helicopters, which shows interest in armed helicopters.However, this loss is not limited to decision makers, despite the advantages of armed helicopters (multi-purpose, low acquisition cost, etc.). It has been a serious factor that hesitates the acquisition of.

In order to overcome the drawbacks, the concept of the new design was constructed / concrete as described above, and the effect thereof was confirmed. As a result, a high flight performance improvement was confirmed.

In particular, as many advances were made in forward flight performance, it was also confirmed that there were no problems with the existing maneuverable helicopters and braided operation.

In order to increase the accuracy of the present invention, the concept design was carried out by concretely designing the main concept, and the adequacy of the design level was additionally confirmed by weighing and integrating the result.

In the case of applying the concept of the present invention, a considerable improvement in maneuverability is expected due to the movement of a large number of heavy items (armed) near the rotor axis, and thus, further confirmation is required. Of course, there are still several stages until the practical use, but if the materialization / utilization is promoted based on the concept derived from this study, it will be able to help to secure differentiated competitiveness related to the armed / attack helicopter in the future.

The present invention can be applied to a fixed wing aircraft such as a conventional transport aircraft in the same concept, in this case, as well as the bomb to launch free-fall can be easily applied to the type of missile that needs to be launched in the aircraft inside.

In addition, the armed transfer mechanism of the present invention is applicable not only to armed but also to all objects requiring automatic transfer in similar situations (which must pass through a narrow door).

For example, in the design of the conveyor belt, an automation design is possible by applying the above concept (which enables posture change by controlling two feed shafts separately). In this case, it is possible to control posture through separate control by dividing belt / chain etc. into two parts instead of applying linear guide.

Preferred embodiments of the present invention described above are disclosed to solve the technical problem, and those skilled in the art to which the present invention pertains (man skilled in the art) various modifications, changes, additions, etc. within the spirit and scope of the present invention. It will be appreciated that such modifications, changes and the like should be regarded as falling within the scope of the following claims.

The present invention can be applied to the military rotorcraft aircraft improvement development project, it is possible to apply to the design of armed or various external protrusion equipment when developing a military fixed-wing aircraft.

In addition, when the length of the object to be conveyed is larger than the space to pass through it is possible to remove the obstacles during the transfer.

In addition, a wide range of applications of armed transfer mechanisms are possible.

In addition, when the military helicopter possession country for transporting existing personnel / materials to secure the attack capability through the installation of the helicopter, it is possible to secure the international market competitiveness through the application of the present invention by securing excellent attack performance and maneuverability.

Figure 1a is a real photograph equipped with an armed to the outside of the helicopter according to the prior art

1B is a view illustrating a structure in which several box-shaped frames are connected to an internal main structure

2 is a block diagram of an integrated retractable aircraft munition system (IRMSS) according to the prior art

3 is a schematic diagram of a conventional four-armed Hellfire missile launcher for an armed / attack helicopter;

4 is a block diagram of a rail of the horizontal transfer apparatus capable of posture control according to the present invention

5 is an explanatory view of the operating mechanism of the horizontal transfer apparatus capable of posture control according to the present invention

6 is a configuration diagram showing a specific operation structure of the rail

Figure 7 is a configuration diagram for a specific configuration and transport process of the horizontal transfer apparatus capable of posture control according to the present invention

8 and 9 is a simplified configuration of the structure of the horizontal transfer apparatus capable of posture control according to the present invention

10 is a configuration diagram for the MKK model

11 is a schematic diagram of the autoload mechanism;

12 is a schematic view of a pushing mechanism

13 is a conceptual design to which the mechanism according to the present invention is applied

14 is a configuration diagram applying the mechanism according to the present invention to an existing helicopter

Fig. 15 shows the relationship between the required power factors for the forward speed of the helicopter.

16 is a photograph of the KUH fuselage wind tunnel test model

17 is a diagram showing the results of grid comparison model comparison of the existing concept

18 is a diagram showing the results of the mechanism application model grid generation of the present invention

19 is a diagram showing a drag application front drag distribution of a mechanism applied model of the present invention.

20 is a view showing aerodynamic analysis results of the mechanism application model of the present invention

21 is a diagram showing a drag distribution in front of the existing concept comparison model

22 is a view showing the results of aerodynamic analysis model comparison target

23 to 27 illustrate model blackdown and index of the present invention.

FIG. 23 is a diagram illustrating a model index of a missile, a wing skin, and a pusher.

24 is a diagram illustrating a model index of a pusher detail,

25 is a view showing a model index of the wing rib (Rib),

26 is a diagram illustrating a model index of an LM module and a step motor,

FIG. 27 is a diagram showing track and fitting details. FIG.

28 and 29 illustrate blackdown and index of the existing conceptual model.

28 is a view showing a model index of the missile, the launch pad, the wing skin,

It is a figure which shows the model index of a blade rib.

30 is a result of comparing the main performance of the concept of the present invention and the existing concept.

[Description of Code for Major Parts of Drawing]

10: IRAMS 11: HURL

12: SUL 13: Hellfire Rail

20: rail 21: guide hole

23: guide portion 27: line portion

30: first horizontal moving element 31: first rotating shaft

40: second horizontal moving element 41: second axis of rotation

50: aircraft structure (Door) 70: missile (transportation object)

Claims (6)

In the automatic grenades, At least one rail on which the missile is mounted; And First and second horizontal moving elements arranged in parallel to transport the rails from inside an aircraft or helicopter to an external launch pad or vice versa, When transporting the rail, it characterized in that for controlling the operation of the first and second horizontal moving element, respectively, so that the rail is transported in an inclined state at an angle, The first and second horizontal moving elements respectively form a first rotational shaft and a second rotational shaft coupled to one end and the other end of the rail, The rail may include: a guide part forming a guide hole coupled to the first rotation shaft; And a line part coupled with the second rotation shaft to correspond to a change in displacement of the second rotation shaft with respect to the first rotation shaft by the separate movement of the first and second horizontal moving elements. delete The method of claim 1, wherein the first and second horizontal moving elements are: An automatic feed tank equipped with a linear motion module and a step motor, wherein each motion is controlled. The method of claim 1, wherein the first and second horizontal moving elements are: Automatic grenades equipped with either ball-screws, chains or belts. In the horizontal feeder, At least one rail; And And first and second horizontal moving elements installed in parallel to transport the rail in a horizontal direction. When transporting the rail, it characterized in that for controlling the operation of the first and second horizontal moving element, respectively, so that the rail is transported in an inclined state at an angle, The first and second horizontal moving elements respectively form a first rotational shaft and a second rotational shaft coupled to one end and the other end of the rail, The rail may include: a guide part forming a guide hole coupled to the first rotation shaft; And a line part coupled to the second rotation shaft to correspond to a change in displacement of the second rotation shaft with respect to the first rotation shaft by separate operations of the first and second horizontal moving elements. The method of claim 5, wherein the first and second horizontal moving element, Horizontal transfer device, characterized in that consisting of any one of the ball screw (Ball-Screw), chain, belt.

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