KR101388188B1 - Apparatus and system for regulating internal state of launching tube - Google Patents

Abstract

The present invention relates to an apparatus and a system for controlling the temperature, pressure, volume, etc. inside the launch tube. The present invention is a launch tube with an autonomous vehicle; An internal temperature measuring unit measuring an internal temperature of the launch tube; And an internal condition control unit for expanding or contracting the volume of the gas inside the launch tube based on the result obtained by comparing the measured internal temperature with a reference value. According to the present invention, moisture can be prevented from entering the inside of the launch tube from the outside, and the pressure inside the launch tube can always be maintained at atmospheric pressure without being affected by changes in the surrounding external environment.

Description

Apparatus and system for regulating internal state of launching tube}

The present invention relates to an apparatus and a system for adjusting a state inside a launch tube. More particularly, the present invention relates to an apparatus and a system for controlling the temperature, pressure, volume, and the like inside the launch tube.

The launch tube serves as a guide when launching a missile, and normally serves to protect the missile by sealing the built-in missile from the outside. Launch tubes are usually deployed in fields and exposed to the outside environment.

Since the inside of the launch tube is in equilibrium with the outside, it is sensitive to changes in the surrounding environment caused by day and night changes, weather changes, and seasonal changes. Thus, the inside of the launch tube is constantly changing temperature or pressure under the influence of the surrounding environment. This causes fatigue to continuously occur in the cover of the weak launcher tube, which causes the cover to break down due to the fatigue phenomenon.

In order to improve this, a method of increasing the cover strength so as not to be destroyed (hereinafter method A), a method of applying a brass valve to a launch tube (hereinafter method B), a method of applying a check valve to a launch tube (hereinafter method C), etc. Although proposed as an alternative, each alternative has the following problems.

If the launch tube diameter is increased even at the same pressure, the cover is increased by the diameter of the launch tube, so the force exerted by the cover becomes larger in proportion to the diameter. In the case of Method A, there is a limit to increase the strength of the cover, so there is a problem that can be applied only to a small launch tube. In addition, there is a problem in that the pressure generated by the temperature in addition to the atmospheric pressure should be considered when checking the condition of the bullet using the pressure sensor in the missile.

The brass valve is a valve having a semipermeable membrane that allows only air containing moisture to pass therethrough. Method B can prevent the cover from being easily broken by drilling a hole in the location of the surface of the launch tube and closing it with a brass valve. However, the method B has a problem that the external moisture is introduced into the launch tube through the brass valve to accelerate the replacement cycle of the dehumidifier. In addition, when the launch tube is disposed near the shore, the blockage of the semi-permeable membrane occurs frequently due to the salt, which also shortens the life of the brass valve.

The check valve has the function of closing at normal atmospheric pressure and opening at a certain pressure (valve selection criteria, which may select positive or negative pressure separately). For example, when the missile is first loaded into the launch tube and the assembly of the cover and the like is completed, the temperature at the time of closing is defined as the initial temperature. Low pressure creates a negative pressure, opens the valve when the specified pressure is reached, and changes the temperature at the point of opening back to the initial temperature of the launch tube. Method C can prevent the cover from being easily broken by drilling a hole in the location of the launch tube surface and closing it with a check valve. However, Method C, like Method B, has a problem in that the replacement cycle of the dehumidifying agent is faster than in the closed state. In addition, method C, like Method B, has difficulty in using special gas such as nitrogen instead of air as the gas inside the launch tube to increase missile storage efficiency.

The present invention has been made to solve the above problems, and an object of the present invention is to propose an apparatus and a system for controlling a condition inside a launch tube, which is connected to the inside of a launch tube to control temperature, pressure, volume, and the like within the launch tube.

However, the objects of the present invention are not limited to those mentioned above, and other objects not mentioned can be clearly understood by those skilled in the art from the following description.

The present invention has been made in order to achieve the above object, a launch tube in which the autonomous vehicle is built; An internal temperature measuring unit measuring an internal temperature of the launch tube; And an internal condition control unit for expanding or contracting the volume of the gas inside the launch tube based on the result obtained by comparing the measured internal temperature with a reference value.

Preferably, the internal state control unit, the cylindrical portion of the inside of the hollow cylinder; A piston part embedded in the cylinder part to reciprocate between one side and the other side; A volume expansion / contraction adjustment unit having a rod shape and coupled to one side of the piston unit through the cylinder unit; And a volume expansion / contraction adjustment control unit which pushes the volume expansion / contraction adjustment unit into the cylinder unit or pulls the cylinder unit out of the cylinder unit based on the result.

Preferably, scales are formed in a length direction along with numbers on one surface of the volume expansion / contraction adjusting unit, and the volume expansion / contraction control unit is one surface of the cylinder unit among the scales formed in the volume expansion / contraction adjusting unit. The volume expansion / contraction adjustment part is pushed into the cylinder part or pulled out of the cylinder part so that the scale meets the straight line obtained from the same.

Preferably, the volume expansion / contraction adjustment control portion uses a tangent to the hole formed in the cylinder portion for insertion of the volume expansion / contraction adjustment portion in the straight line.

Preferably, the launch tube internal condition control system is formed on one side of the connection pipe connecting the inside of the launch tube and the inside of the cylinder portion gas flow control unit for controlling the flow of gas entering and exits between the inside of the launch tube and the cylinder portion It further includes, wherein the internal state control unit, the cylindrical cylindrical portion as the inside is empty; A piston part embedded in the cylinder part to reciprocate between one side and the other side; A volume expansion / contraction adjustment unit having a rod shape and coupled to one side of the piston unit through the cylinder unit; And a volume expansion / contraction adjustment control unit which pushes the volume expansion / contraction adjustment unit into the cylinder part when contracting the volume of the gas.

Preferably, the internal condition controller uses the result of dividing the product of the reference pressure and the measured internal temperature by the reference temperature as the result.

Preferably, the launch tube, the launch tube body is provided with an empty space for the interior of the autonomous body; A cover part mounted to be opened and closed at one end of the launch tube body to allow the autonomous vehicle to be embedded; And a moisture removing unit mounted in a groove formed at one side of an inner surface of the launch tube body in contact with the space and removing moisture from the space.

In another aspect, the present invention provides an internal temperature measuring unit for measuring the internal temperature of the launch tube in which the autonomous vehicle is built; And an internal state control unit which expands or contracts the volume of the gas inside the launch tube based on the result obtained by comparing the measured internal temperature with a reference value.

The present invention can achieve the following effects by suggesting a device and system connected to the inside of the launch tube to control the temperature, pressure, volume, etc. inside the launch tube. First, moisture can be prevented from entering the inside of the launch tube from the outside. Second, the replacement period of the dehumidifier is longer than existing alternatives (methods B and C). Third, special gas such as nitrogen may be used instead of air as the gas inside the launch tube, thereby improving storage efficiency of autonomous vehicles such as missiles. Fourth, the pressure inside the launch tube can always be maintained at atmospheric pressure without being affected by changes in the surrounding environment.

1 is a block diagram schematically showing a launch tube internal condition control system according to a preferred embodiment of the present invention.
FIG. 2 is a block diagram specifically illustrating an internal configuration of an internal state controller of FIG. 1.
FIG. 3 is a block diagram specifically illustrating an internal configuration of the launch tube shown in FIG. 1.
4 is a structural diagram of a launch tube on which a missile is mounted.
5 is a conceptual diagram illustrating a connection configuration of a launch tube and a volume expansion / contraction device.
FIG. 6 is a conceptual diagram of the volume expansion / contraction device shown in FIG. 5.
7 to 9 illustrate the principle of operation of the volumetric expansion / contraction device.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In the drawings, the same reference numerals are used to designate the same or similar components throughout the drawings. In the following description of the present invention, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the subject matter of the present invention rather unclear. In addition, the preferred embodiments of the present invention will be described below, but it is needless to say that the technical idea of the present invention is not limited thereto and can be variously modified by those skilled in the art.

1 is a block diagram schematically showing a launch tube internal condition control system according to a preferred embodiment of the present invention. According to FIG. 1, the launch tube internal condition control system 100 includes a launch tube 110, an internal temperature measurer 120, an internal condition adjuster 130, and a main controller 140. 160).

Launch tube 110 is an autonomous vehicle is built. Autonomous vehicles are, for example, missiles.

The launch tube 110 may include a launch tube body 111, a cover 112, and a moisture removing unit 113 as shown in FIG. 3. FIG. 3 is a block diagram specifically illustrating an internal configuration of the launch tube shown in FIG. 1.

The launch tube body 111 is provided with an empty space for the interior of the autonomous vehicle.

The cover portion 112 is mounted to be opened and closed at one end of the launch tube body 111 to enable the autonomous vehicle to be built.

The moisture removing unit 113 is mounted in a groove formed at one side of the inner surface of the launch tube body 111 in contact with the space and serves to remove moisture from the space.

The internal temperature measuring unit 120 performs a function of measuring the internal temperature of the launch tube 110.

The internal condition controller 130 expands or contracts the volume of the gas inside the launch tube 110 based on a result obtained by comparing the measured internal temperature with a reference value. The internal condition controller 130 may use the result obtained by dividing the product of the reference pressure and the measured internal temperature by the reference temperature.

As shown in FIG. 2, the internal state controller 130 may include a cylinder 131, a piston 132, a volume expansion / contraction adjusting unit 133, and a volume expansion / contraction adjusting control unit 134. have. FIG. 2 is a block diagram specifically illustrating an internal configuration of an internal state controller of FIG. 1.

The cylinder part 131 is cylindrical and empty inside.

The piston part 132 is built in the cylinder part 131 to reciprocate between one side and the other side inside the cylinder part 131.

The volume expansion / contraction adjusting unit 133 is rod-shaped and is coupled to one side of the piston part 132 through the cylinder part 131.

The volume expansion / contraction adjustment control unit 134 pushes the volume expansion / contraction control unit 133 into the cylinder unit 131 or out of the cylinder unit 132 based on the result obtained by comparing the measured internal temperature with a reference value. Perform the pulling function.

On one surface of the volume expansion / contraction adjusting unit 133, graduations may be formed in the length direction along with the numbers. At this time, the volume expansion / contraction control control unit 134 is a volume expansion / contraction so that the scale that meets the straight line obtained from one surface of the cylinder portion 131 among the graduations formed in the volume expansion / contraction control unit 133 in accordance with the result The adjusting part 133 may be pushed into the cylinder part 131 or pulled out of the cylinder part 131. The volume expansion / contraction adjustment control unit 134 may use a tangent to the hole formed in the cylinder portion 131 for the insertion of the volume expansion / contraction adjustment unit 133 in the straight line. The scales in the above may be for example indicating temperature values.

The main controller 140 controls the overall operation of the internal temperature measuring unit 120 and the internal state control unit 130.

The launch tube internal condition control system 100 may further include a gas flow controller 150. The gas flow controller 150 is formed at one side of a connection pipe connecting the inside of the launch tube 110 and the inside of the cylinder 131 to control the flow of gas entering and exiting between the inside of the launch tube 110 and the inside of the cylinder 131. It performs the function. To this end, the gas flow control unit 150 may be implemented to include an opening and closing valve formed on one side of the connecting pipe.

When the launch tube internal condition control system 100 further includes a gas flow control unit 150, the volume expansion / contraction control unit 134 may contract the volume expansion / contraction control unit when contracting the volume of the gas inside the launch tube 110. Only a function of pushing the 133 into the cylinder 131 may be performed. The reason for this is as follows. When the volume of the gas inside the launch tube 110 is to be expanded, the temperature or pressure inside the launch tube 110 is greater than the ambient temperature or pressure. Thus, when opening and closing the valve on the connection pipe gas inside the launch tube 110 flows into the cylinder portion 131 through the connection pipe, the volume expansion / contraction control unit 133 is naturally pushed out of the cylinder portion 131 This happens. That is, the function of controlling the volume expansion / contraction control unit 134 to pull the volume expansion / contraction control unit 133 to the outside of the cylinder unit 131 may be achieved by opening and closing the valve on the connecting pipe.

Next, an embodiment of the launch tube internal condition control system described with reference to FIGS. 1 to 3 will be described.

4 is a structural diagram of a launch tube on which a missile is mounted. In Figure 4 (a) is a front view and (b) is a side cross-sectional view. According to FIG. 4, the launch tube 400 includes a missile 410, a cover 420, an air layer 430, and a dehumidifier 440.

The cover 420 is located at the front or the front / rear of the launch tube 400, and serves to maintain the confidentiality of the usual launch tube 400. The cover 420 is destroyed by the missile 410 explosion propulsion pressure in the launch tube 400 when the missile 410 is released, and the missile 410 is released from the launch tube 400 by the explosion propulsion pressure. Due to this functional feature, the cover 420 is usually manufactured in a structure having a small strength of a nonmetal material.

The launch tube 400 serves as a guide during the launch of the missile 410 and normally serves to protect the missile 410 from the external environment. In particular, the electronic component functions to protect many missiles 410 from external moisture.

The dehumidifier 440 absorbs moisture from the air layer 430 included in the launch tube 400 to keep the air inside the launch tube 400 dry. The dehumidifier 440 is installed in the launch tube 400 for the purpose of long-term storage of the missile 410, and is replaced with a new one if necessary (ex. When dehumidifier performance is degraded).

Inside the launch tube 400, there is an air layer 430 except for the missile 410. The air layer 430 is to expand / contract the volume in accordance with the temperature change outside the launch tube 400, the pressure is increased / decreased if the expansion / contraction is closed. Such a phenomenon can be expressed by the equation of the ideal gas state as follows.

Without volume expansion / contraction: P2 = (P1 × T2) ÷ T1

When volume expansion / contraction is possible: V2 = (V1 × T2) ÷ T1

In the above, P1 means initial pressure and P2 means pressure after change. T1 means initial temperature and T2 means temperature after change. V1 means initial volume and V2 means volume after change. The initial pressure, initial temperature, and initial volume may be defined as, for example, the pressure, temperature, and volume at the time when the missile 410 is initially charged into the launch tube 400 and the assembly of the cover 420 is completed and closed.

5 is a conceptual diagram illustrating a connection configuration of a launch tube and a volume expansion / contraction device. The volume expansion / contraction device 500 of FIG. 5 is a configuration corresponding to the launch tube internal condition control device 160 of FIG. 1. Through the connection configuration as shown in Figure 5 to completely block the external moisture, in conjunction with the external temperature change it is possible to expand / contract the volume of the air layer inside the launch tube 400. Connection configuration as shown in Figure 5 can be defined as a breathing tube.

FIG. 6 is a conceptual diagram of the volume expansion / contraction device shown in FIG. 5. In Figure 6 (a) is a side cross-sectional view and (b) is a front view. The following description refers to Fig. 5 and Fig.

The volume expansion / contraction device 500 includes a cylinder 510, a cylinder cover 520, a piston 530, a scale bar 540, a piston o-ring 550, an external open / close valve 560 and a fixing leg 570. It consists of The scale bar 540 may be formed by marking the scale including the operating temperature of the launch tube 400 is stamped on the bar. This volume expansion / contraction device 500 is connected to the launch tube 400 through a connection hose 580 and a plug 590.

7 to 9 illustrate the principle of operation of the volumetric expansion / contraction device. When the missile charging was performed at the initial temperature of 24 ° C. in the launch tube, after opening the external on / off valve 560, setting the scale bar 540 to 24 ° C. scale as shown in FIG. Complete the final task by blocking.

Since the volumetric expansion / shrinkage device 500 is contracted as shown in FIG. 8, when the tube is brought to a temperature of −17 ° C., the state when the tube is 42.5 ° C. is again as shown in FIG. 9. The expansion / contraction device 500 is expanded. This principle can be explained as V2 = (V1 × T2) ÷ T1.

-How to make

The maximum volume in the cylinder can be found by using the expression V2 = (V1 × T2) ÷ T1 in the case where the volumetric expansion / contraction is possible in the above-described launch tube internal state equation. For example:

If the field operational temperature of a missile loaded missile is -20 ~ 44 ℃, T1 and T2 are defined as below.

T1 (min): Room temperature -20 ℃ + 273

T2 (max): Operating Temperature 44 ℃ + 273

The definition of the volume of each part is as follows.

Vc: volume of air in the launch tube

Vh: volume of air in the connection hose

Vs: Volume in the volume expansion / contraction device

The volume amount V2 when the temperature of the launch tube reaches 44 ° C is calculated as follows.

V2 = (V1 × T2) / T1

V2 = ((Vc + Vh) × T2) / T1

Using the calculated V2, the maximum volume Vs required by the volume expansion / contraction device is obtained as follows.

Vs = V2-Vc-Vh

In addition, on the scale bar, the corresponding temperature of Vs (0%) to Vs (100%) is displayed (inscribed) based on the "temperature reading position" of FIG.

- How to use

1. First missile production

First, the missile is loaded into the launch tube and the cover is closed. Then, open the external on-off valve. The workplace temperature is then measured. The temperature of the scale bar is then adjusted to the workplace measurement temperature in the "temperature reading position". Thereafter, the external on-off valve is closed.

2. Field maintenance (repair of cover, dehumidifier, etc.)

First, complete the maintenance. Close the cover and open the external on / off valve. Thereafter, the outside air temperature is measured. The temperature of the scale bar is then adjusted to the measured temperature in the "temperature reading position". Thereafter, the external on-off valve is closed.

It is to be understood that the present invention is not limited to these embodiments, and all elements constituting the embodiment of the present invention described above are described as being combined or operated in one operation. That is, within the scope of the present invention, all of the components may be selectively coupled to one or more of them. In addition, although all of the components may be implemented as one independent hardware, some or all of the components may be selectively combined to perform a part or all of the functions in one or a plurality of hardware. As shown in FIG. In addition, such a computer program may be stored in a computer readable medium such as a USB memory, a CD disk, a flash memory, etc., and read and executed by a computer to implement an embodiment of the present invention. As the recording medium of the computer program, a magnetic recording medium, an optical recording medium, a carrier wave medium, and the like can be included.

Furthermore, all terms including technical or scientific terms have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined in the Detailed Description. Terms used generally, such as terms defined in a dictionary, should be interpreted to coincide with the contextual meaning of the related art, and shall not be interpreted in an ideal or excessively formal sense unless explicitly defined in the present invention.

It will be apparent to those skilled in the art that various modifications, substitutions and substitutions are possible, without departing from the scope and spirit of the invention as disclosed in the accompanying claims. will be. Accordingly, the embodiments disclosed in the present invention and the accompanying drawings are not intended to limit the technical spirit of the present invention but to describe the present invention, and the scope of the technical idea of the present invention is not limited by the embodiments and the accompanying drawings. . The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents should be construed as falling within the scope of the present invention.

100: launch tube internal condition control system 110: launch tube
111: launch tube body 112: cover
113: moisture removal unit 120: internal temperature measurement unit
130: internal state control unit 131: cylinder
132: piston portion 133: volume expansion / contraction control
134: volume expansion / contraction control unit 150: gas flow control unit
160: launch tube internal condition control device

Claims (8)

A launch tube having an autonomous vehicle;
An internal temperature measuring unit measuring an internal temperature of the launch tube; And
Internal condition control unit for expanding or contracting the volume of gas in the interior of the launch tube based on the result obtained by comparing the measured internal temperature with a reference value
Launcher internal condition control system comprising a. The method according to claim 1,
The internal state control unit,
A cylindrical part having a hollow inside as a cylindrical shape;
A piston part embedded in the cylinder part to reciprocate between one side and the other side;
A volume expansion / contraction adjustment unit having a rod shape and coupled to one side of the piston unit through the cylinder unit; And
A volume expansion / contraction adjustment control part which pushes the volume expansion / contraction adjustment part into the cylinder part or pulls out the cylinder part based on the result;
Launcher internal condition control system comprising a. 3. The method of claim 2,
On one surface of the volume expansion / contraction adjustment portion is formed in the longitudinal direction along with the numbers,
The volume expansion / contraction control part pushes the volume expansion / contraction control part into the cylinder part so that a scale which meets a straight line obtained from one surface of the cylinder part among the graduations formed in the volume expansion / contraction adjustment part corresponds to the result. Or pull out of the cylinder portion. The method of claim 3, wherein
And said volume expansion / contraction adjustment control part uses a tangent to a hole formed in said cylinder part for insertion of said volume expansion / contraction adjustment part into said straight line. 3. The method of claim 2,
The launch tube internal condition control system,
A gas flow controller formed at one side of a connection pipe connecting the inside of the launch tube and the inside of the cylinder to control the flow of gas entering and exiting between the inside of the launch tube and the inside of the cylinder;
A launch tube internal condition control system further comprising. The method according to claim 1,
And the internal condition control unit uses the result of dividing the product of the reference pressure and the measured internal temperature by the reference temperature as the result. The method according to claim 1,
The launch tube may include:
A launch tube body having an empty space for the interior of the autonomous vehicle;
A cover part mounted to be opened and closed at one end of the launch tube body to allow the autonomous vehicle to be embedded; And
Moisture removal unit is mounted in the groove formed on one side of the inner surface of the launch tube body in contact with the space to remove the moisture of the space
Launcher internal condition control system comprising a. An internal temperature measuring unit measuring an internal temperature of a launch tube in which an autonomous vehicle is embedded; And
Internal condition control unit for expanding or contracting the volume of gas in the interior of the launch tube based on the result obtained by comparing the measured internal temperature with a reference value
Launcher internal condition control device comprising a.

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