KR102181031B1 - A ground test device for upper-stage rocket engine - Google Patents

Abstract

The present invention relates to a device for a ground test of a high-altitude liquid rocket engine and, more specifically, to a device for a ground test of a high-altitude liquid rocket engine, capable of testing a high-altitude nozzle on the ground without manufacturing a separate high-altitude simulation testing device or a nozzle for a ground test of a high-altitude nozzle. The present invention can reduce preparation time before a test by a simple equipment structure, can perform the test using a nozzle actually used in a high altitude to save equipment space and costs, and can obtain more accurate test results.

Description

A ground test device for upper-stage rocket engine.

The present invention relates to an apparatus for ground test of a liquid rocket engine for high altitude, and an engine development test at low cost by making a separate nozzle for ground engine testing for an engine having a high altitude nozzle or using it without a high altitude simulation facility. It relates to a device for doing.

The liquid rocket engine used as the propulsion engine of the space launch vehicle is an engine that obtains a reaction by converting the heat energy generated by burning and ejecting the propellant into kinetic energy.Since the oxidizing agent is supplied together with the fuel, it operates without supplying oxygen from the outside. There is a characteristic.

In general, when a liquid rocket engine is manufactured, it must be installed in a test facility to verify its performance before it is launched, and a combustion test must be performed.The ground combustion test to verify the operability of the engine refers to a combustor, a gas generator, a turbopump, and Checking whether engine components such as pyrostarter, igniter, valves, etc. show normal functions when connected to the system, and checks the characteristics of system variables indicated by engine system implementation such as precooling, start/stop, purge, and differential pressure. Means that. The engine test to be performed on the ground differs in the test apparatus according to the pressure at the nozzle outlet and the expansion ratio of the nozzle, and can generally be classified into a high altitude engine and a ground engine.

The expansion ratio of the nozzle is the area of the engine nozzle outlet divided by the engine nozzle neck. Engine nozzles used on the ground have a small expansion ratio, so that the pressure at the outlet of the engine nozzle is similar to the atmospheric pressure, so combustion tests can be performed without other equipment. However, since the engine nozzle used in high altitude has a large expansion ratio and the pressure at the outlet of the engine nozzle is significantly lower than the atmospheric pressure during engine combustion, the atmospheric pressure is affected. This may cause peeling in the nozzle, and cause a problem in that the enlarged nozzle portion is damaged or destroyed due to the peeling.

Conventionally, in order to test a high altitude rocket engine, a rocket engine is installed in a vacuum chamber, and the inside of the vacuum chamber is made into a vacuum state to form a pressure of a high altitude condition to minimize the effect of atmospheric pressure before proceeding with the test. However, in order to use the vacuum chamber, it requires a lot of equipment and space compared to the size of the engine, and it takes a long time to make the inside of the vacuum chamber into a vacuum state, and because the equipment is complex, there is enormous cost in manufacturing and operation. There is a drawback of being costly.

In addition, Korea Patent Registration No. 11434171 ("Top Rocket Engine Ground Combustion Test System") is a top-level rocket engine ground combustion test system equipped with a thrust wall, a rocket engine control and measurement part, and an over-expansion auxiliary nozzle part. A test method using a plurality of auxiliary rocket engines along the edge of is disclosed. However, the prior literature has a disadvantage in that it is impossible to recycle because the auxiliary rocket engine must be manufactured differently according to the enlargement ratio of the nozzle, and because it requires a separate facility and space, it is expensive to manufacture and operate.

Korean Patent Registration No. 11434171 ("Top Rocket Engine Ground Combustion Test System")

The present invention has been conceived to solve the above problems, and an object of the present invention is for a combustion test on the ground for a nozzle equipped with a high altitude liquid rocket engine used at high altitude and provided at the top of a space launch vehicle, It is to provide a high-altitude liquid rocket engine ground combustion test device capable of testing high-altitude nozzles without requiring a separate facility space.

The space launcher is a high altitude liquid rocket engine ground combustion test apparatus equipped with a liquid rocket engine, and a high altitude liquid rocket engine for the combustion test of a high altitude nozzle formed in a conical shape gradually widening from the nozzle neck to the nozzle outlet. In the combustion test apparatus, the upper part or the whole is formed into a cone, and the conical part is inserted into the inside of the high-altitude nozzle to reduce the nozzle outlet area when the high-altitude nozzle burns and discharges gas. ; A cooling water pipe connected to allow external cooling water to flow into the center body; And a guide formed as a cylinder extending in the vertical direction and formed to accommodate the center body, wherein the guide is formed to extend in the vertical direction from the outside of the guide, and is formed to be connected to the cooling water pipe. Guide piping; And a guide inner wall formed to be spaced apart from the inside of the guide.

In this case, the cooling water pipe may include at least one external pipe passing through the center body and connecting the outside and the inside of the center body; And an internal transfer pipe connected to one or more of the external pipes located inside the center body and configured to move and eject coolant to the upper end of the center body.

In addition, the center body is characterized in that the inner wall is formed to be spaced a predetermined distance inward, the inner wall is formed to be opened from the upper portion of the center body.

At this time, the upper end of the inner transfer pipe and the upper end of the inner wall are connected, and the cooling water introduced into the inner transfer pipe moves to the lower portion of the center body along the gap between the center body and the inner wall. .

In addition, a center body channel, which is a regeneration cooling channel composed of a plurality of capillaries, is formed between the center body and the inner wall.

In this case, the center body channel is characterized in that it is formed in a spiral shape along the inner surface of the center body.

In addition, the cooling water pipe is characterized in that the cross section is in the form of an airfoil in order to reduce resistance to the gas discharged from the nozzle.

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At this time, the guide is characterized in that it has the same diameter as the lowermost diameter of the nozzle for the high hole.

In addition, the guide is characterized in that it is connected to the lowermost end of the high hole nozzle through a sealing member.

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At this time, the guide pipe is formed as a cylinder in which the cooling water introduced into the cooling water pipe is movable upward along the guide, and the guide inner wall is connected to the guide pipe at an upper end of the guide, and the cooling water is And it is characterized in that it moves to the lower portion of the guide along the inner wall of the guide.

In addition, a guide channel, which is a regeneration cooling channel composed of a plurality of capillaries, is formed between the guide and the guide inner wall.

In addition, the guide channel is characterized in that it is formed in a spiral shape along the inner surface of the guide.

At this time, each capillary tube of the guide channel further includes an ejecting member at a lower end of the guide, and the ejecting member changes the cooling water helically flowing along each capillary tube of the guide channel in a vertical direction at high speed. It is characterized by spraying.

In addition, a cooling water pipe is connected to the center body in which the center body is not inserted into the high hole nozzle.

The liquid rocket engine ground combustion test apparatus for high altitude of the present invention having the above configuration does not require a separate facility space for ground combustion test of the high altitude nozzle, and can be reused, thereby saving facility space and cost. In addition, the preparation time before the test can be shortened due to the simple structure of the equipment, and since the test can be performed using a nozzle that is actually used in high altitude, there is an effect of obtaining more accurate test results.

1 is a front view of a high altitude nozzle and a center body
2 is a conceptual diagram of a high altitude nozzle and a center body
3 is a cross-sectional view of a cooling water pipe
4 is a perspective view of the center body
5(a), (b), (c), and (d) are examples 1, 2, 3, 4 in which a cooling water pipe and a double wall are provided inside the center body.
6 is a cross-sectional view of the center body
7 is a cross-sectional view taken along AA′ of FIG. 6
8 is a perspective view of an embodiment of a center body channel
9 is a flow chart of cooling water inside the center body
10 is a perspective view of a center body and a guide
11 is a front view of a high altitude nozzle, center body and guide
12 is a cross-sectional view taken along BB′ of FIG. 11
13 is a flow chart of cooling water inside the center body and guide
14 is a cross-sectional view of an ejecting member

Hereinafter, the technical idea of the present invention will be described in more detail using the accompanying drawings. Prior to this, terms or words used in the specification and claims should not be construed as being limited to their usual or dictionary meanings, and the inventors appropriately explain the concept of terms in order to explain their own invention in the best way. Based on the principle that it can be defined, it should be interpreted as a meaning and concept consistent with the technical idea of the present invention.

Accordingly, the embodiments described in the present specification and the configurations shown in the drawings are only the most preferred embodiment of the present invention, and do not represent all the technical spirit of the present invention, and thus various alternatives that can be substituted for them at the time of application It should be understood that there may be variations.

Hereinafter, the technical idea of the present invention will be described in more detail using the accompanying drawings. The accompanying drawings are only an example shown to describe the technical idea of the present invention in more detail, so the technical idea of the present invention is not limited to the form of the accompanying drawings.

In the above-ground combustion test of a liquid rocket engine, the expansion ratio of the nozzle divided by the nozzle neck and the pressure at the nozzle outlet during combustion are important, and this is directly related to the safety problem during the test. A high altitude nozzle 100 of a liquid rocket engine is provided at the top of a general space launch vehicle, and since there is almost no effect of atmospheric pressure at high altitude, it is highly desirable to make the cross-sectional area of the nozzle outlet large and increase the velocity of the discharged gas. It is advantageous in the environment.

Therefore, the high-altitude nozzle 100 is designed and manufactured to have a large enlargement ratio by increasing the cross-sectional area of the nozzle outlet. Accordingly, when the rocket engine is operated on the ground, the pressure at the nozzle outlet is significantly lower than the atmospheric pressure, resulting in a separate facility. If a combustion test is performed without a combustion test, it may cause a peeling phenomenon inside the high altitude nozzle 100, and vibration caused by a shock wave and high temperature occurs in the corresponding nozzle due to unstable peeling, and in some cases, the high altitude nozzle 100 This can cause damage or destruction problems.

Therefore, the present invention is a device for testing the high altitude nozzle 100 on the ground, without a high altitude environment simulation device such as a supersonic diffuser or a vibration chamber, a nozzle that discharges gas when the high altitude nozzle 100 burns It is a device that enables a combustion test of the high altitude nozzle 100 on the ground by reducing the delamination phenomenon in the high altitude nozzle 100 by reducing the cross-sectional area of the outlet.

Referring to Fig. 1, a liquid rocket engine is provided, and a high altitude liquid rocket engine ground combustion test apparatus for a combustion test of the high altitude nozzle 100 formed in a conical shape gradually widening from the nozzle neck to the nozzle outlet. In this case, a part or the whole of the upper side is formed as a cone, and the conical portion is inserted into the inside of the high altitude nozzle 100 to reduce the nozzle outlet area when the high altitude nozzle 100 is combusted and gas is discharged. It may be configured to include a center body 200 and a cooling water pipe 300 connected to allow external cooling water to flow into the center body 200.

The center body 200 and the cooling water pipe 300 may be formed of metals having good thermal conductivity, such as aluminum, iron, carbon steel, copper, and stainless steel, and the high temperature and high pressure gas discharged by combustion of the high hole nozzle 100 Any material that can withstand against can be used. The coolant moves at high pressure, and the coolant flows into the center body 200 through the coolant pipe 300, and absorbs the heat of the high-temperature and high-pressure gas that is burned and discharged by the high-air nozzle 100. It is possible to prevent deformation of the shape due to a large increase in the temperature of 200.

Figure 2 (a) shows the cross-sectional area of the lowermost end of the high-altitude nozzle 100, Figure 3 (b) is the cone shape of the center body 200 is inserted into the high-altitude nozzle 100 It is shown that the cross section of the lowermost end of the high altitude nozzle 100 is reduced. In the present invention, the center body 200 is inserted into the high-altitude nozzle 100, thereby obtaining an effect of reducing the enlargement ratio of the high-altitude nozzle 100, and the pressure at the end end of the high-altitude nozzle 100 is It has an effect of preventing a situation where a strong shock wave enters the nozzle at an appropriate level, and even if an inclined shock wave by the center body 200 occurs, the level of increase in vibration, pressure and temperature is relatively small compared to the vertical shock wave. There is an effect of enabling a safer combustion test on the ground by using the high altitude nozzle 100.

The specific shape of the center body 200 may be different for each engine, and in each case, a specific shape of the center body 200 may be determined using Computational Fluid Dynamics (CFD) for the shape of the nozzle. In one embodiment of the present invention, the center body 200 may be formed in a conical shape on a part or the entire upper side, which is to minimize shock waves that may occur when inserted into the high altitude nozzle 100, and It is characterized in that only the conical portion of the body 200 is inserted into the high hole nozzle 100. In addition, as shown in FIG. 3, when the center body 200 is formed in a cone only on the upper side, portions of the center body 200 excluding the cone have a shape to which the cooling water pipe 300 can be connected. It does not matter if it is, but has a maximum diameter of the cone of the center body 200 or less, minimizes resistance to the gas discharged from the high altitude nozzle 100, and can stably support the cooling water pipe 300 The phase is most preferred. When the center body 200 is formed entirely in a conical shape, the cooling water pipe may be located at a lower portion where the center body 200 is not inserted into the high hole nozzle 100.

Referring to Figures 3 and 4, the center body 200 may be provided with one or more cooling water pipes 300, and in one embodiment, the cooling water pipe 300 is the high altitude nozzle 100 In order to reduce the resistance to the combustion and exhaust gas, the cross section may be in the form of an airfoil, and it does not matter as long as it is formed so that high-pressure coolant can flow. Since high-pressure cooling water flows into the center body 200 through the cooling water pipe 300, it is appropriate to be provided in a balance of two or more in the center body 200, which is the inflow of high-pressure cooling water. This is to prevent the center body 200 from being shifted to one side. The center body 200 may be provided with three cooling water pipes 300 to allow an appropriate amount of cooling water to flow through each of the cooling water pipes.

As shown in (a) of FIG. 5, the cooling water pipe 300 may be provided with an inclination or vertically in the center body 200, and the cooling water may be introduced into the center body 200. It does not matter if it is formed to be able to. At this time, the center body 200 has a space formed therein so that the cooling water introduced through the cooling water pipe 300 fills the inside of the center body 200 and may have a shape blocked below. A drain pipe may be provided to allow the used cooling water to flow out.

Referring to Figure 5 (b), the cooling water pipe 300, at least one external pipe 310 connecting the outside and the inside of the center body 200 and the inside of the center body 200 It is connected to at least one of the external pipes 310 to be positioned, and may be formed to include an internal transfer pipe 320 formed to eject the cooling water by moving it to the upper end of the center body 200. The center body 200 is formed to include the two outer pipes 310 and one of the inner transfer pipes 320. At this time, the high-pressure cooling water flowing into the external pipe 310 is moved to the upper end of the center body 200 through the internal transfer pipe 320 and is ejected from the upper end of the center body 200, and the center body 200 ), or a space is formed inside the center body 200 excluding the cooling water pipe 300 to fill the center body 200 to cool the center body 200, and have a separate drain pipe so that the used cooling water is It can be configured to flow out.

Referring to (c) of FIG. 5, the center body 200 may include an inner wall 210 formed to be spaced a predetermined distance inward, and the inner wall 210 is an upper portion of the center body 200. It can be opened and formed in. The inner wall 210 may be formed to be open from the upper side of the center body 200 adjacent to the inner transfer pipe 320 at all times, and the inner wall 210 may be formed through the inner transfer pipe 320. When the coolant moved to the upper part of the 200) is ejected, it flows to the lower end of the inner wall 210 and may be induced to cool the center body 200. At this time, the center body 200 has a separate drain pipe to form a space inside the center body 200 excluding the cooling water pipe 300 so that the coolant fills up to cool the center body 200, or The lower part of the center body 200 may be entirely or partially opened to allow the cooling water to flow downward and to be drained.

The present invention is possible regardless of the shape if the center body 200 and the cooling water pipe 300 are included, but as shown in Fig. 5(d) as an optimal embodiment of the present invention, the internal transfer pipe The upper end of 320 and the upper end of the inner wall 210 are connected, so that the high-pressure coolant flowing into the inner transfer pipe 320 moves downwards of the center body 200 by riding the inner wall 210 It may be formed to be, and will be described below based on an embodiment shown in FIG.

6 and 7, the center body 200 may include a center body channel 220 between the center body 200 and the inner wall 210, and the center body channel 220 Is a regeneration cooling channel composed of a plurality of capillaries, and may be provided to regenerate the used cooling water a plurality of times. The center body channel 220 is irrelevant as long as it is provided so that the coolant can move downwards along between the center body 200 and the inner wall 210, and in one embodiment, the capillary tube of the center body channel 220 is The center body 200 may be formed in a longitudinal direction, or the center body channel 220 may be formed in a spiral shape to increase heat transfer efficiency, and FIG. 8 shows a plurality of capillaries of the center body channel 220. It is a perspective view of what is formed in a spiral shape along the inner surface of the center body 200.

9 is a flow chart of cooling water inside the center body 200 when the center body channel 220 is provided in a spiral shape in order to increase the cooling efficiency of the center body 200. Referring to FIG. The high-pressure cooling water flowing into the external pipe 310 moves upwards of the center body 200 along the internal transfer pipe 320 provided in the center of the center body 200. The cooling water flows into the center body channel 220 provided in the inner wall 210 from the upper side of the center body 200, and spirals along the inner surface of the center body 200 downward from the center body 200. Moving to and cooling the center body 200 and discharged to the outside of the center body 200, or the used cooling water is regenerated a plurality of times through a regeneration system provided to cool the center body 200.

As shown in Figure 10, the high-altitude liquid rocket engine ground combustion test apparatus is formed as a cylinder extending in the vertical direction, further comprising a guide 400 formed to accommodate all or part of the center body 200 It may include, and the guide 400 may be formed by being connected to the cooling water pipe 300 connected to the center body 200. When the center body 200 is inserted into the nozzle 100 for high altitude, it accommodates the center body 200 and the cooling water pipe, and is formed to be located at the lower end of the nozzle 100 for high altitude. Can be used without limitation.

Referring to FIG. 11, in an optimal embodiment, the guide 400 is formed to have the same diameter as the lowermost end diameter of the high altitude nozzle 100 so that the guide 400 is connected to the lower end of the high altitude nozzle 100. It is characterized in that it is formed to be able to. At this time, the lowermost end of the nozzle 100 for high altitude and the guide 400 may be connected through a sealing member 440, and the sealing member 440 is formed of the nozzle 100 for high altitude and the guide 400. It is provided along the circumference to fix the high hole nozzle 100 and the guide 400, and maintain airtightness at the end face of the nozzle. Therefore, even if the diameter of the guide 400 is larger or smaller than the diameter of the lowermost end of the high-altitude nozzle 100, or formed in a different shape, the guide 400 can be connected using the sealing member 440 ) Is not limited in shape and size, and is possible regardless of the shape and size, as long as it is formed to be connected to the lowermost end of the high hole nozzle 100. The sealing member 440 may connect the guide 400 and the high altitude nozzle 100 such as silicon, rubber, ceramics, ABS, PLA, etc., and the high temperature and high pressure gas continuously fired from the high altitude nozzle 100 Regardless of what can be endured, it can be used, and the guide 400 and the high altitude nozzle 100 may be welded to each other to connect.

12 is a cross-sectional view of the guide 400 formed while accommodating the center body 200 and the cooling water pipe 300, and will be described with reference to FIGS. 10 to 12, the guide 400 is the cooling water pipe It may be configured to include the guide pipe 410 and the guide pipe 420 so that the coolant flowing into the cooling water pipe 300 can be introduced into the guide 400 by being connected to the 300. As the coolant flows through the guide pipe 410 and the guide pipe 420 to the guide 400, there is an effect of lowering the downstream pressure of the high-altitude nozzle 100 when the high-altitude nozzle 100 is burned. It is possible to form a more stable ground test condition, and the center body 200 inserted into the high altitude nozzle 100 can be further lowered to the rear, and the center body inserted into the high altitude nozzle 100 It is possible to completely exclude the effect of the oblique shock wave that may be caused by (200), so there is an effect that the test can be carried out more safely.

The guide pipe 410 is connected to the cooling water pipe 300 and is formed to move the cooling water to flow the cooling water into the guide 400, and the cooling water is connected to the cooling water pipe 300 to It may be provided regardless of its shape as long as it is formed to flow into the inside of the guide 400. As shown in FIG. 10, in one embodiment, the guide 400 may be extended and formed in an upward direction, and the cooling water introduced into the cooling water pipe 300 may be upwardly formed along the guide 400. It can be configured as a cylinder that can be moved to. The guide pipe 420 is formed so that the cooling water introduced into the guide pipe 410 can flow to the front surface of the guide 400 of the guide 400, and the cooling water can flow along the guide 400. As long as it is formed so that it may be formed regardless of its shape, as shown in FIGS. 11 and 12, it may be formed to be spaced a predetermined distance from the inside of the guide 400 in an embodiment, and the guide pipe 420 is The guide 400 is connected to the guide pipe 410 at the upper end of the guide 400, and the cooling water introduced through the guide pipe 410 flows between the guide 400 and the guide pipe 420 It may be formed to move to the bottom of the. In order to improve the cooling efficiency of the guide 400, a guide pipe 430 may be provided between the guide 400 and the guide pipe 420, and the guide pipe 430 is composed of a plurality of capillaries. It is characterized in that it is a regeneration cooling channel. The guide pipe 430 may be formed in a straight line downward, and may be formed in a spiral shape along the inner surface of the guide 400 in order to further improve cooling efficiency, and the guide pipe 430 may have cooling water downward. It may be provided without limitation as long as it is formed to be movable.

13 is a flow chart of cooling water when the center body 200 is further provided with the guide 400, and when described for reference, the cooling water flowing into the external pipe 310 is inside the center body 200 At the same time as it flows into, it moves to the upper end of the guide 400 along the guide pipe 410. As previously described, the coolant flowing into the center body 200 moves to the top of the center body 200 through the internal transfer pipe 320, and the center body channel formed on the inner wall 210 ( It flows in a spiral through 220 and is discharged to the lower portion of the center body 200. At this time, the cooling water moved to the upper end of the guide 400 along the guide pipe 410 moves to the guide pipe 420 through a connection gap formed at the upper end of the guide pipe 410, and the guide pipe 410 It flows in a spiral through the guide pipe 430 formed in the pipe 420 and is discharged to the lower portion of the guide 400 to cool the guide 400 and the center body 200.

Referring to FIG. 14, each capillary tube forming the guide pipe 430 may further include an ejecting member 450, and the ejecting member 450 cools the guide 400. It has the effect of efficiently lowering the pressure after the nozzle by using the cooling water flowing for the steam ejector. The ejecting member 450 may be formed to eject coolant flowing along each capillary tube of the guide pipe 430 to the outside of the guide 400 at high speed, and the ejecting member 450 is It may be formed to change the direction of the cooling water flowing along each of the capillaries formed as a vertical direction so that it can be ejected to the outside of the guide 400 at high speed. The ejecting member 450 may be provided regardless of its location if it is formed so that it can be used as a steam ejector by ejecting cooling water at high pressure, and in one embodiment, cooling water provided at the rear end of the guide 400 and flowing in a spiral It can be formed by changing the vertical direction, compressing it under high pressure, and ejecting it to the outside. In addition, the ejecting member 450 is provided at the lower end of the center body 200 to compress the coolant flowing through the center body channel 220 at a high pressure at the lower end of the center body 200 and change it to a vertical direction. It ejects to the outside and may be provided to be used as a steam ejector.

As described above, in the present invention, specific matters such as specific components, etc. and limited embodiments have been described, but this is provided only to aid in a more general understanding of the present invention, and the present invention is limited to the above-described embodiment. It is not, and those of ordinary skill in the field to which the present invention belongs can make various modifications and variations from this description.

Therefore, the spirit of the present invention is limited to the described embodiments and should not be determined, and all things equivalent or equivalent to the claims as well as the claims to be described later belong to the scope of the spirit of the present invention. .

1000: High altitude liquid rocket engine ground combustion test device
100: high altitude nozzle
200: center body 210: double wall
220: Center body channel
300: cooling water pipe 310: external pipe
320: internal transfer pipe
400: guide 410: guide piping
420: guide inner wall 430: guide channel
440: sealing member 450: ejecting member

Claims (16)

In the above-ground combustion test apparatus for a high altitude liquid rocket engine for a combustion test of a high altitude nozzle that is provided with a liquid rocket engine and gradually widens from the nozzle neck to the nozzle outlet,
A center body whose upper side is partially or entirely formed into a cone, and a cone portion is inserted into the inside of the nozzle for high altitude to reduce a nozzle outlet area when the nozzle for high altitude burns and discharges gas;
A cooling water pipe connected to allow external cooling water to flow into the center body; And
A guide formed as a cylinder extending in the vertical direction and formed to accommodate the center body;
Including,
The guide,
A guide pipe extending in the vertical direction from the outside of the guide and formed to be connected to the cooling water pipe; And a guide inner wall formed to be spaced apart from the inside of the guide.
High altitude liquid rocket engine ground combustion test apparatus, characterized in that.
The method of claim 1,
The cooling water pipe,
One or more external pipes passing through the center body and connecting the outside and the inside of the center body; And
An internal transfer pipe connected to one or more of the external pipes located inside the center body and formed to move and eject coolant to the upper end of the center body; a high altitude liquid rocket engine ground combustion test comprising: Device.
The method of claim 2,
The center body has an inner wall formed to be spaced a predetermined distance inward, wherein the inner wall is formed to be opened from an upper portion of the center body.
The method of claim 3,
The upper end of the inner transfer pipe and the upper end of the inner wall are connected, and the coolant introduced into the inner transfer pipe moves to the lower part of the center body along the gap between the center body and the inner wall. Liquid rocket engine ground combustion test device.
The method of claim 4,
A high altitude liquid rocket engine ground combustion test apparatus, characterized in that between the center body and the inner wall, a center body channel, which is a regeneration cooling channel composed of a plurality of capillaries, is formed.
The method of claim 5,
The center body channel,
High altitude liquid rocket engine ground combustion test apparatus, characterized in that formed in a spiral along the inner surface of the center body.
The method of claim 1,
The cooling water pipe,
High altitude liquid rocket engine ground combustion test apparatus, characterized in that the cross section is in the form of an airfoil in order to reduce the resistance to the gas discharged from the nozzle.
delete The method of claim 1,
The guide,
High altitude liquid rocket engine ground combustion test apparatus, characterized in that having the same diameter as the lowermost diameter of the nozzle for high altitude.
The method of claim 1,
The guide,
High altitude liquid rocket engine ground combustion test apparatus, characterized in that connected through the lower end of the high altitude nozzle and a sealing member.
delete The method of claim 1,
The guide pipe,
The cooling water introduced into the cooling water pipe is formed as a cylinder that can move upward along the guide,
The guide inner wall,
A liquid rocket engine ground combustion test apparatus for high altitude, characterized in that it is connected to the guide pipe at an upper end of the guide, and coolant moves to a lower portion of the guide along between the guide and the guide inner wall.
The method of claim 1,
A high altitude liquid rocket engine ground combustion test apparatus, characterized in that between the guide and the guide inner wall, a guide channel, which is a regenerative cooling channel composed of a plurality of capillaries, is formed.
The method of claim 13,
The guide channel is a high altitude liquid rocket engine ground combustion test apparatus, characterized in that formed in a spiral along the inner surface of the guide.
The method of claim 13,
Each capillary tube of the guide channel further includes an ejecting member at the lower end of the guide,
The ejecting member is a high altitude liquid rocket engine ground combustion test apparatus, characterized in that the cooling water flowing in a spiral along each capillary of the guide channel is changed in a vertical direction and injected at high speed.
The method of claim 1,
A high altitude liquid rocket engine ground combustion test apparatus, characterized in that a coolant pipe is connected to the center body in which the center body is not inserted into the high altitude nozzle.

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