A heat shield and a rocket engine high altitude simulation test device having the same

Abstract

The present invention relates to the technical field of rocket engine high-altitude simulation test, and discloses a heat insulation screen and a rocket engine high-altitude simulation test device having the same. The heat insulation screen includes a plurality of heat insulation units, and the heat insulation units include: a heat insulation side plate, on which a cooling pipe is fixedly installed; a heat insulation top plate, fixedly installed on the top of the heat insulation side plate, the heat insulation top plate is arranged vertically with the heat insulation side plate and extends toward the inner side surface of the heat insulation side plate; a heat insulation bottom plate, fixedly installed on the bottom of the heat insulation side plate, the heat insulation bottom plate extends toward the inner side surface of the heat insulation side plate, and / or the heat insulation bottom plate extends toward the outer side surface of the heat insulation side plate. By setting a heat insulation screen and continuously passing a cooling medium into the cooling pipe of the heat insulation screen, a cold wall barrier is formed at the heat insulation screen. At the same time, the cooling medium can continuously bring the high temperature generated by the engine nozzle out of the vacuum chamber, which can greatly improve the cooling efficiency of the vacuum chamber, thereby reducing the ambient temperature of the space outside the heat insulation screen in the vacuum chamber.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engine high-altitude simulation test, and in particular to a heat insulation screen and a rocket engine high-altitude simulation test device having the heat insulation screen. Background Art

[0002] The high-altitude simulation test of rocket engines is a ground test that must be carried out on rocket engines. The high-altitude simulation test creates an environment similar to high-altitude conditions in ground test equipment, allowing the rocket engine to work in this environment and conduct various tests on its performance, reliability, service life, etc.

[0003] During the high-altitude simulation test of rocket engines, single-wall nozzles are often used for large-area ratio engine nozzles. The nozzles adopt a radiation cooling structure, and the maximum surface temperature during the test can reach over 1000°C. When this type of engine is hot-tested for a long time in a vacuum chamber, the heat radiation effect of the engine nozzle in the vacuum chamber will continue to heat up. In order to ensure that the equipment in the vacuum chamber can operate normally in a high-temperature environment, measures need to be taken to protect the vacuum chamber and key components such as cables and sensors in the vacuum chamber. In the prior art, water injection cooling is usually used to cool the engine nozzle. However, the efficiency of water injection cooling is extremely low in a high-temperature environment far above the boiling point of water, which affects the test efficiency of the high-altitude simulation test of rocket engines. Summary of the invention

[0004] In view of this, the present invention provides a heat shield and a rocket engine high-altitude simulation test device having the same, so as to solve the problem of low test efficiency of the engine high-altitude simulation test in the prior art.

[0005] In a first aspect, the present invention provides a heat shield for a rocket engine high-altitude simulation test device, the heat shield is suitable for being installed outside the engine nozzle, the heat shield comprises a plurality of heat insulation units, and the plurality of heat insulation units are enclosed to form a cylindrical structure;

[0006] The insulation unit consists of:

[0007] A heat-insulating side plate on which a cooling pipe is fixedly mounted, the cooling pipe being used to circulate a cooling medium;

[0008] The heat-insulating top plate is fixedly mounted on the top of the heat-insulating side plate, and the heat-insulating top plate is arranged vertically with the heat-insulating side plate and extends toward the inner side surface of the heat-insulating side plate;

[0009] The heat-insulating bottom plate is fixedly mounted on the bottom of the heat-insulating side plate, and the heat-insulating bottom plate extends toward the inner side surface of the heat-insulating side plate, and / or the heat-insulating bottom plate extends toward the outer side surface of the heat-insulating side plate.

[0010] The heat shield is installed in the vacuum chamber of the rocket engine high-altitude simulation test device. When the rocket engine is conducting a high-altitude simulation test in the vacuum chamber, the engine nozzle at the tail of the rocket engine extends into the inner cavity of the heat shield. By continuously introducing cooling medium into the cooling pipe, a cold wall barrier is formed at the heat shield. When the rocket engine is conducting a high-altitude simulation test, the heat radiation released by the engine nozzle to the outside will be blocked by the cold wall barrier at the heat shield inside the heat shield, and the high temperature generated by the engine nozzle during the simulation test will be taken away by the cooling medium in the cooling pipe, and the inside of the vacuum chamber will be cooled simultaneously, thereby protecting the equipment in the vacuum chamber from the high temperature. By setting up a heat shield and continuously introducing cooling medium into the cooling pipe of the heat shield, a cold wall barrier is formed at the heat shield. At the same time, the cooling medium can continuously bring the high temperature generated by the engine nozzle out of the vacuum chamber, which can greatly improve the cooling efficiency of the vacuum chamber, thereby reducing the ambient temperature of the space outside the heat shield in the vacuum chamber, and protecting the working equipment in the vacuum chamber from the high temperature.

[0011] In an optional embodiment, the cooling pipe extends to the heat-insulating bottom plate and continues to extend along the extension direction of the heat-insulating bottom plate, and the cooling pipe is fixedly connected to the heat-insulating bottom plate. By extending the cooling pipe to the heat-insulating bottom plate, a heat-insulating barrier can also be formed at the heat-insulating bottom plate, thereby blocking the heat flow inside the heat-insulating screen at the bottom, preventing the heat flow from overflowing from the bottom of the heat-insulating screen to the rest of the space in the vacuum chamber, and ensuring that the space near the heat-insulating screen inside the vacuum chamber can maintain a relatively low temperature.

[0012] In an optional embodiment, a reinforcing plate is fixedly mounted on the heat-insulating bottom plate, the reinforcing plate is vertically arranged with the heat-insulating bottom plate, and the cooling pipe is fixedly connected to the reinforcing plate. The reinforcing plate is arranged to position and fix the cooling pipe on the heat-insulating bottom plate, so that the coldness of the cooling medium in the cooling pipe can be better transferred to the heat-insulating bottom plate through the fins, ensuring that the heat-insulating bottom plate maintains a relatively low temperature.

[0013] In an optional embodiment, the cooling pipe extends to the insulating top plate and continues to extend along the extension direction of the insulating top plate, a positioning piece is fixedly installed on the cooling pipe, a positioning hole is provided on the insulating top plate, and the positioning piece is plugged into the positioning hole.

[0014] In an optional embodiment, a plurality of air holes are arranged at intervals on the heat-insulating top plate, and the heat-insulating top plate and the cooling pipe are detachably mounted, and the amount of high-temperature radiation passing through the heat-insulating top plate is adjusted by blocking a predetermined number of air holes or installing heat-insulating top plates with different numbers of air holes. By arranging air holes on the heat-insulating top plate, the flow of airflow during the start-up and shutdown of the rocket engine can be achieved, and the high-temperature radiation generated at the engine nozzle can be transmitted upward through the air holes, thereby achieving thermal assessment of other engine components.

[0015] In an optional embodiment, two insulation top plates in adjacent insulation units are fixedly connected via a connecting piece;

[0016] And / or, two insulation bottom plates in adjacent insulation units are fixedly connected by a connector. Multiple groups of insulation units are connected by the connector to form an insulation screen, thereby improving the integrity of the insulation screen.

[0017] In an optional embodiment, the heat insulation side plate is composed of a plurality of fins arranged in sequence, and the angle between two adjacent fins is 120° to 150°, which plays a role in gas diversion when the engine is started, thereby reducing the aerodynamic load on the heat insulation screen and extending the service life of the heat insulation screen.

[0018] In a second aspect, the present invention further provides a rocket engine high altitude simulation test device, which has the heat shield of the present invention. Because the rocket engine high altitude simulation test device includes a heat shield, it has the same effect as the heat shield, and will not be described in detail here.

[0019] In an optional embodiment, a vacuum chamber is further included, the bottom of which is provided with an air extraction port, and a diffuser is installed on the air extraction port, and the diffuser is used to extract air from the inner cavity of the vacuum chamber to make the air pressure in the vacuum chamber lower than the ambient air pressure. By setting the diffuser to achieve suction of the vacuum chamber, the pressure in the vacuum chamber is lower than the atmospheric pressure, meeting the conditions of high-altitude simulation.

[0020] In an optional embodiment, the heat shield is installed in the vacuum chamber, and the heat shield cover is installed on the exhaust port;

[0021] When conducting high-altitude simulation tests of rocket engines, the rocket engine body is placed in a vacuum chamber, the engine nozzle of the rocket engine body extends into the heat shield, and the top of the heat shield is flush with the top of the nozzle hot wall of the engine nozzle. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 It is a schematic structural diagram of a rocket engine high altitude simulation test device provided in an embodiment of the present invention.

[0024] Figure 2 It is a schematic structural diagram of the heat insulation screen provided in an embodiment of the present invention.

[0025] Figure 3It is a schematic structural diagram of the cooperative connection between the heat insulating side panels and the heat insulating bottom panel provided in an embodiment of the present invention.

[0026] Explanation of the reference numerals: 1. Vacuum chamber; 2. Rocket engine; 3. Nozzle cold wall; 4. Insulation side panel; 5. Insulation top panel; 6. Nozzle hot wall; 7. Insulation bottom panel; 8. Diffuser; 9. Connecting steel belt; 10. Stud; 11. Air vent; 12. Bolt hole; 13. Water inlet; 14. Water outlet; 15. Fin; 16. Reinforcement plate; 17. Cooling pipe. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0028] Combine the following Figures 1 to 3 , describing an embodiment of the present invention.

[0029] According to an embodiment of the present invention, on the one hand, a high-altitude simulation test device for a rocket engine 2 is provided, comprising a vacuum chamber 1 and a heat shield, wherein an exhaust port is arranged at the bottom of the vacuum chamber 1, and the heat shield is installed inside the vacuum chamber 1. The heat shield is cylindrical, and a cover is arranged and installed above the exhaust port.

[0030] The heat insulation screen includes multiple groups of heat insulation units, and the multiple groups of heat insulation units are enclosed to form a cylindrical structure. Specifically, the heat insulation screen is divided into four fan-shaped heat insulation units, which are convenient for installation after the rocket engine 2 is installed, while reducing the weight of a single heat insulation unit, and facilitating transportation and installation. Among them, the heat insulation unit includes a heat insulation side panel 4, a heat insulation top panel 5 and a heat insulation bottom panel 7. A cooling pipe 17 is fixedly installed on the heat insulation side panel 4, and the cooling pipe 17 is used to circulate the cooling medium. The heat insulation top panel 5 is fixedly installed on the top of the heat insulation side panel 4, and the heat insulation top panel 5 is arranged vertically with the heat insulation side panel 4 and extends toward the inner side surface of the heat insulation side panel 4. The heat insulation bottom panel 7 is fixedly installed at the bottom of the heat insulation side panel 4, and the heat insulation bottom panel 7 extends toward the inner side surface and the outer side surface of the heat insulation side panel 4, so that the heat insulation bottom panel 7 is supported and installed on the heat insulation side panel 4, and the heat insulation side surface is arranged at a position close to the middle of the plane of the heat insulation bottom panel 7. The cooling pipe 17 can be fixedly connected to the inner side of the heat-insulating side plate 4 or the outer side of the heat-insulating side plate 4. In this embodiment, a matching pipe for installing the cooling pipe 17 is formed on the heat-insulating side plate 4, and the cooling pipe 17 is directly expanded and matched with the matching pipe. The cooling pipe 17 is arranged in an array on the heat-insulating side plate 4 vertically. A water inlet 13 and a water outlet 14 are set on the cooling pipe 17 of each fan-shaped heat-insulating unit. The cooling pipes 17 on multiple groups of heat-insulating units can be independently operated in parallel or can be arranged in series. In the vacuum chamber 1, the heat shield is fixedly connected to the bottom of the vacuum chamber 1 by bolts passing through the bolt holes 12 of the heat-insulating bottom plate 7. In this embodiment, the cooling pipe 17 as the heat shield skeleton is selected as a water pipe according to a specific trajectory, and cooling water is passed inside to take away the radiant heat generated by the nozzle hot wall 6 when the rocket engine 2 is running in the vacuum chamber 1. The four heat-insulating top plates 5 can be installed with respect to the heat-insulating side plates 4 by rotating the axis at a certain angle, and staggered at a certain angle, such as 45°, with the heat-insulating side plates 4, so as to strengthen the overall structure of the heat-insulating screen.

[0031] The heat shield is installed in the vacuum chamber 1 of the high-altitude simulation test device of the rocket engine 2. When the rocket engine 2 is conducting a high-altitude simulation test in the vacuum chamber 1, the engine nozzle at the tail of the rocket engine 2 extends into the inner cavity of the heat shield, and a cooling medium is continuously introduced into the cooling pipe 17 to form a cold wall barrier at the heat shield. When the rocket engine 2 is conducting a high-altitude simulation test, the heat radiation released by the engine nozzle to the outside will be blocked by the cold wall barrier at the heat shield inside the heat shield, and the high temperature generated by the engine nozzle during the simulation test will be taken away by the cooling medium in the cooling pipe 17, and the inside of the vacuum chamber 1 will be cooled simultaneously, thereby protecting the equipment in the vacuum chamber 1 from the high temperature. By setting a heat shield and continuously introducing a cooling medium into the cooling pipe 17 of the heat shield, a cold wall barrier is formed at the heat shield, and at the same time, the cooling medium can continuously bring the high temperature generated by the engine nozzle out to the outside of the vacuum chamber 1, which can greatly improve the cooling efficiency of the vacuum chamber 1, thereby reducing the ambient temperature of the space outside the heat shield in the vacuum chamber 1, and protecting the working equipment in the vacuum chamber 1 from the high temperature.

[0032] In one embodiment, the cooling pipe 17 extends onto the insulation bottom plate 7 and continues to extend along the extension direction of the insulation bottom plate 7, and the cooling pipe 17 is fixedly connected to the insulation bottom plate 7. By extending the cooling pipe 17 onto the insulation bottom plate 7, an insulation barrier can also be formed at the insulation bottom plate 7, thereby blocking the heat flow inside the insulation screen at the bottom, preventing the heat flow from overflowing from the bottom of the insulation screen to the rest of the space in the vacuum chamber 1, and ensuring that the space near the insulation screen inside the vacuum chamber 1 can maintain a relatively low temperature. The cooling pipe 17 on the insulation bottom plate 7 is U-shaped, and the insulation bottom plate 7 and the bottom U-shaped cooling pipe 17 are connected by welding.

[0033] Specifically, a reinforcing plate 16 is fixedly mounted on the heat-insulating bottom plate 7, the reinforcing plate 16 is arranged vertically with the heat-insulating bottom plate 7, the cooling pipe 17 is fixedly connected to the reinforcing plate 16, and the sides of the heat-insulating bottom plate 7 and the bottom U-shaped cooling pipe 17 are welded and reinforced by the triangular reinforcing plate 16. By arranging the reinforcing plate 16, the cooling pipe 17 on the heat-insulating bottom plate 7 is positioned and fixed, and while the connection strength between the cooling pipe 17 and the heat-insulating bottom plate 7 is improved, the coldness of the cooling medium in the cooling pipe 17 can be better transferred to the heat-insulating bottom plate 7 through the fins 15, ensuring that the heat-insulating bottom plate 7 maintains a relatively low temperature.

[0034] In one embodiment, the cooling pipe 17 extends to the insulation top plate 5 and continues to extend along the extension direction of the insulation top plate 5. A positioning piece is fixedly installed on the cooling pipe 17. A positioning hole is provided on the insulation top plate 5. The positioning piece is plugged into the positioning hole. Specifically, the cooling pipe 17 on the insulation top plate 5 is U-shaped. A stud 10 as a positioning piece is welded on the pipe wall of the top U-shaped cooling pipe 17. The stud 10 passes through the positioning hole on the insulation top plate 5 and is tightened with a nut to fix the insulation top plate 5. The insulation top plate 5 and the pipe wall of the top U-shaped cooling pipe 17 are fully in contact to achieve heat dissipation.

[0035] Furthermore, a plurality of air holes 11 are arranged at intervals on the heat-insulating top plate 5, and the heat-insulating top plate 5 and the cooling pipe 17 are detachably mounted. A predetermined number of air holes 11 are blocked by fasteners, or heat-insulating top plates 5 with different numbers of air holes are installed to adjust the amount of high-temperature radiation passing through the heat-insulating top plate 5. By arranging the air holes 11 on the heat-insulating top plate 5, the flow of airflow during the start-up and shutdown process of the rocket engine 2 can be achieved, and at the same time, the high-temperature radiation generated at the engine nozzle can be transmitted upward through the air holes 11 to achieve thermal assessment of other engine components. Specifically, the heat-insulating top plate 5 is a ring plate structure with a circular hole in the middle as a whole, and the gap between the heat-insulating top plate 5 and the nozzle hot wall 6 of the engine nozzle is set to 5cm~10cm to prevent vibration and collision of the heat shield when the rocket engine 2 is working. By replacing different heat-insulating top plates 5, the number of air holes 11 evenly distributed on different heat-insulating top plates 5 is different, and the radiation intensity can be adjusted during the thermal assessment of the engine components.

[0036] In one embodiment, two heat insulation top plates 5 in adjacent heat insulation units are fixedly connected by a plurality of connecting steel strips 9 as connecting members; and two heat insulation bottom plates 7 in adjacent heat insulation units are fixedly connected by a plurality of connecting steel strips 9 as connecting members. Multiple groups of heat insulation units are connected by connecting members to form a heat insulation screen, thereby improving the integrity of the heat insulation screen.

[0037] In one embodiment, the heat-insulating side plate 4 is composed of a plurality of fins 15 arranged in sequence, and the angle between two adjacent fins 15 is 120° to 150°, which plays a role in gas diversion when the engine is started, thereby reducing the aerodynamic load on the heat shield. Extend the service life of the heat shield. Specifically, the heat-insulating side plate 4 is composed of a plurality of cooling tubes 17 with fins 15, and two fins 15 are arranged on each cooling tube 17. The cooling tube 17 is made of 304 stainless steel, which has high strength and plays a role in supporting the heat shield body and preventing water leakage. The fin 15 is made of aluminum alloy, which has a high thermal conductivity and can conduct heat to the cooling tube 17 as quickly as possible. The fixing method between the fin 15 and the water pipe adopts an expansion method to ensure sufficient contact and good heat conduction. The side of the fin 15 facing the rocket engine 2 is blackened to increase the heat absorption. The side of the fin 15 facing the vacuum chamber 1 adopts the original color of aluminum alloy to reduce the heat release.

[0038] In one embodiment, a vacuum port is provided at the bottom of the vacuum chamber 1 of the high-altitude simulation test device of the rocket engine 2, and a diffuser 8 is installed on the vacuum port. The diffuser 8 is used to evacuate the inner cavity of the vacuum chamber 1 so that the air pressure in the vacuum chamber 1 is lower than the ambient air pressure. The combustion gas discharged from the engine nozzle of the rocket engine 2 enters the diffuser 8 to achieve suction of the vacuum chamber 1, so that the pressure in the vacuum chamber 1 is lower than the atmospheric pressure, meeting the conditions of high-altitude simulation.

[0039] In one embodiment, the heat shield is installed in the vacuum chamber 1, and the heat shield cover is installed on the exhaust port. When conducting a high-altitude simulation test of the rocket engine 2, the rocket engine 2 body is placed in the vacuum chamber 1, and the engine nozzle of the rocket engine 2 body extends into the heat shield. The engine nozzle includes a nozzle cold wall 3 on the upper side and a nozzle hot wall 6 on the lower side. The heat shield is arranged on the outside of the rocket engine 2 to isolate the heat radiation between the nozzle hot wall 6 and the vacuum chamber 1. The nozzle of the rocket engine 2 is divided into two parts: the nozzle cold wall 3 and the nozzle hot wall 6. The height of the heat insulation side panel 4 is consistent with the height of the nozzle hot wall 6, that is, the top of the heat shield is flush with the top of the nozzle hot wall 6 of the engine nozzle.

[0040] The heat shield provided in this embodiment is designed to take into account the need to set up a heat insulation device between the vacuum cabin 1 and the engine to avoid affecting the heat dissipation of the engine nozzle. The heat shield needs to be light enough to facilitate installation in the restricted environment of the vacuum cabin 1; the heat shield needs to have sufficient air permeability to meet the flow requirements of the airflow in the cabin during the engine startup and shutdown process; the heat shield needs to have sufficient strength to withstand the impact of the airflow in the cabin during the engine startup and shutdown process; the heat shield has the function of heat flow regulation to achieve the test of the heat radiation of the engine structure itself. By setting up a heat shield and continuously passing a cooling medium through the cooling pipe 17 of the heat shield, a cold wall barrier is formed at the heat shield. At the same time, the cooling medium can continuously bring the high temperature generated by the engine nozzle out to the outside of the vacuum cabin 1, which can greatly improve the cooling efficiency of the vacuum cabin 1, thereby reducing the ambient temperature of the space outside the heat shield in the vacuum cabin 1 and protecting the working equipment in the vacuum cabin 1 from the influence of high temperature.

[0041] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A rocket engine high altitude simulation test device, characterized in that: It comprises a heat shield and a vacuum chamber (1), wherein the heat shield is installed in the vacuum chamber (1), and the heat shield cover is installed on an air extraction port provided at the bottom of the vacuum chamber (1); when performing a rocket engine high-altitude simulation test, the rocket engine body is placed in the vacuum chamber (1), the engine nozzle of the rocket engine body extends into the heat shield, and the top of the heat shield is flush with the top of the nozzle hot wall (6) of the engine nozzle; The heat insulation screen comprises a plurality of groups of heat insulation units, and the plurality of groups of heat insulation units are enclosed to form a cylindrical structure; The heat insulation unit comprises a heat insulation side plate (4), a heat insulation top plate (5) and a heat insulation bottom plate (7); a cooling pipe (17) is fixedly mounted on the heat insulation side plate (4); the cooling pipe (17) is used to circulate a cooling medium; the heat insulation top plate (5) is fixedly mounted on the top of the heat insulation side plate (4); the heat insulation top plate (5) is arranged perpendicularly to the heat insulation side plate (4) and extends towards the inner side surface of the heat insulation side plate (4); a plurality of air holes (11) are arranged at intervals on the heat insulation top plate (5); the heat insulation top plate and the cooling pipe are detachably mounted; the amount of high-temperature radiation passing through the heat insulation top plate is adjusted by blocking a predetermined number of the air holes or installing the heat insulation top plate with different numbers of air holes; the heat insulation bottom plate (7) is fixedly mounted on the bottom of the heat insulation side plate (4); the heat insulation bottom plate (7) extends towards the inner side surface of the heat insulation side plate (4), and / or the heat insulation bottom plate (7) extends towards the outer side surface of the heat insulation side plate (4).

2. The rocket engine high altitude simulation test device according to claim 1, characterized in that: The cooling pipe (17) extends onto the heat-insulating bottom plate (7) and continues to extend along the extension direction of the heat-insulating bottom plate (7); the cooling pipe (17) is fixedly connected to the heat-insulating bottom plate (7).

3. The rocket engine high altitude simulation test device according to claim 2, characterized in that: A reinforcing plate (16) is fixedly mounted on the heat-insulating bottom plate (7), the reinforcing plate (16) being arranged vertically to the heat-insulating bottom plate (7), and the cooling pipe (17) is fixedly connected to the reinforcing plate (16).

4. The rocket engine high altitude simulation test device according to any one of claims 1 to 3, characterized in that: The cooling pipe (17) extends onto the heat-insulating top plate (5) and continues to extend along the extension direction of the heat-insulating top plate (5); a positioning piece is fixedly mounted on the cooling pipe (17); a positioning hole is provided on the heat-insulating top plate (5); the positioning piece is plugged into and fitted with the positioning hole.

5. The rocket engine high altitude simulation test device according to any one of claims 1 to 3, characterized in that: Two of the thermal insulation top plates (5) in adjacent thermal insulation units are fixedly connected via a connecting piece; And / or, two of the heat insulating bottom plates (7) in adjacent heat insulating units are fixedly connected via a connecting piece.

6. The rocket engine high altitude simulation test device according to any one of claims 1 to 3, characterized in that: The heat-insulating side plate (4) is composed of a plurality of fins (15) arranged in sequence, and the angle between two adjacent fins (15) is 120° to 150°.

7. The rocket engine high altitude simulation test device according to any one of claims 1 to 3, characterized in that: The vacuum chamber (1) is provided with an air extraction port at the bottom thereof, and a diffuser (8) is installed on the air extraction port. The diffuser (8) is used to extract air from the inner cavity of the vacuum chamber (1) so that the air pressure in the vacuum chamber (1) is lower than the ambient air pressure.

Images