Vacuum cabin for high-altitude simulation test of liquid rocket engine

Abstract

The invention relates to a vacuum chamber for a high-altitude simulation test of a liquid rocket engine, belongs to the technical field of aerospace liquid rocket engine tests, and solves the technical problems of single function, difficulty in operation and poor safety of a traditional vacuum chamber. The cabin comprises a cabin body, a cabin door, a heat sink system, a fire fighting system, a gas replacement system, an anti-arch blasting device, a blowdown system, a mounting platform, an operation platform, a propellant supply pipeline and measurement and control equipment. The cabin body is cubic, and the working pressure in the cabin body is 0-0.1 MPa. The cabin door is used for entering and exiting of personnel, small ground equipment, an engine and a thrust measuring device. The heat sink system, the fire fighting system, the gas replacement system, the sewage discharge system, the mounting platform and the propellant supply pipeline are mounted on the cabin body, and the measurement and control equipment is a transmission channel for engine control and measurement signals. The vacuum chamber is used for a liquid rocket engine high-altitude simulation test.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace liquid rocket engine testing, and in particular relates to a vacuum chamber used for high-altitude simulation testing of liquid rocket engines. Background Art

[0002] In the field of high-altitude simulation tests of aerospace liquid rocket engines, the vacuum chambers currently used are mostly cylindrical chambers with simple structures and single functions. They only meet the vacuum requirements of high-altitude simulation tests of engines and lack functionality. Most vacuum chambers are only designed to meet the test requirements, with small spaces inside, difficult operation, poor safety, and low system reliability. Summary of the invention

[0003] In order to overcome the shortcomings of traditional vacuum chambers, such as single function, difficult operation and poor safety, the present invention proposes a vacuum chamber for high-altitude simulation tests of liquid rocket engines.

[0004] The technical solution adopted by the present invention to solve the technical problem is:

[0005] A vacuum chamber for high-altitude simulation tests of liquid rocket engines comprises a chamber body, a chamber door, a heat sink system, a fire protection system, a gas replacement system, a reverse arch blasting device, a sewage discharge system, an installation platform, an operating platform, a propellant supply pipeline, and measurement and control equipment.

[0006] The cabin is in a cubic shape, placed horizontally, and has a cross-shaped carbon steel reinforcement rib welded on the outside. The working pressure inside the cabin is 0 to 0.1 MPa, and the working temperature is -20 to 150°C.

[0007] The hatch is rectangular and located on the cabin, including two side hatches and a top hatch. The two side hatches are located on both sides of the cabin, and a total of two are provided for personnel and small ground equipment to enter and exit. The top hatch is located on the top of the cabin and is used for the engine and thrust measurement device to enter and exit.

[0008] The heat sink system is a stainless steel tube sheet structure. Cooling water is passed into the stainless steel tube to form an interlayer in the cabin for heat exchange in the cabin to reduce the ambient temperature in the cabin.

[0009] The fire fighting system includes water fire fighting and nitrogen fire fighting, which are used for fire fighting when the propellant leaks or catches fire in the cabin.

[0010] The gas replacement system is installed on the through-cabin interfaces on both side walls of the cabin body, and is used for rapid replacement of gas in the cabin body so that the direction of the airflow in the cabin body follows the direction of the engine nozzle.

[0011] The reverse arch blasting device is installed on the side wall of the cabin. When the cabin is over-pressurized, the reverse arch blasting device is activated to quickly release the pressure in the cabin.

[0012] The sewage discharge system is used for discharging the accumulated liquid in the cabin.

[0013] The installation platform is located in the cabin and is used to install the thrust measurement device and the engine.

[0014] The operating platform is used for operators to stand and operate. The inner part of the cabin is located around the installation platform, and the outer part of the cabin is located in the flange-dense area of ​​the hatch outside the cabin.

[0015] The propellant supply pipeline is fixed on the cabin, enters the cabin from top to bottom through the cabin penetration flange on the top of the cabin, is laid along the inner side of the cabin top to the rear end of the engine, and is provided with an interface.

[0016] The measurement and control equipment is a transmission channel for engine control and measurement signals, including a transfer cabinet and a measurement and control cable. The measurement and control cable enters the cabin from the cabin flange, is transferred through the transfer cabinet, and is transferred from both sides of the installation platform to the engine. The transfer cabinet and the measurement and control cable cabin interface are located at the rear end of the cabin, away from the engine.

[0017] The above-mentioned vacuum chamber also includes an observation window.

[0018] The observation window is installed on the cabin side wall penetration interface located on both sides of the engine and is used for observing the engine nozzle and non-contact temperature measurement.

[0019] A sealing ring is arranged between the observation window and the through-cabin interface of the side wall of the cabin. A water cooling channel is arranged at the sealing ring of the through-cabin interface of the side wall of the cabin to reduce the temperature of the sealing ring.

[0020] In the above-mentioned vacuum chamber, the observation window is made of quartz glass, and anti-reflection films are coated on both sides.

[0021] The thickness of the observation window is 20mm.

[0022] The sealing ring is a fluororubber O-type sealing ring.

[0023] The above vacuum chamber has a DN2200 opening in the center of the bulkhead on the side away from the engine, which is sealed with a blind plate. Three pneumatic butterfly valves are installed in a triangle on the blind plate, and nozzles are installed at the inlet of the pneumatic butterfly valves to inhale air during system debugging to simulate engine fuel gas. During the subsequent use of the vacuum chamber, the DN2200 blind plate can be removed, and the DN2200 opening can be installed with a flow system, so that the ignition test of the air-breathing engine can be carried out.

[0024] The above vacuum chamber has a chamber body made of S30408 ​​material, and the length×width×height of the chamber body is 10m×6m×6m. The width×height of the doors on both sides is 1.5m×2.5m, and the width×length of the top door is 3.5m×6m.

[0025] In the above-mentioned vacuum chamber, the heat sink system is provided with 7 partitions, one partition is provided on each of the 6 sides of the chamber body, one partition is provided at the corresponding position of the hatch on the top of the chamber body, and one partition of the hatch on the top of the chamber body is a movable partition.

[0026] The three partitions on the cabin top and cabin bottom are laid at an angle of 3° as a whole.

[0027] Water pipes are set at both ends of each partition, with one inlet and one outlet, and cooling water enters from low and exits from high. A drain outlet is set at the lowest point of each partition, and the drain outlets are connected to the main drain pipe, on which a drain valve is installed.

[0028] The above-mentioned vacuum chamber, the nitrogen fire protection includes two semicircular DN50 stainless steel fire protection rings and a DN50 gas supply pipeline.

[0029] The air supply pipeline includes a main air supply pipeline and a branch air supply pipeline. The main air supply pipeline enters the cabin from the cabin penetration interface, is divided into two routes through a tee, and enters two semicircular fire rings from the middle position respectively. The tee is located on the symmetry axis of the two semicircular fire rings, and the two branch air supply pipelines are symmetrically arranged. The two semicircular fire rings are installed around the diffuser, and inner and outer circles of air outlet holes are set on the pipe wall facing the engine side. The direction of the inner circle of air outlet holes is 45° to the engine axis, which is used for fire fighting in the area near the engine; the direction of the outer circle of air outlet holes is 30° to the engine axis, which is used for fire fighting in the area near the thrust measurement device behind the engine.

[0030] The water firefighting system is located around the hatch on the top of the cabin, and includes a DN50 stainless steel pipe and a nozzle. The nozzle axis is inclined 20° toward the installation platform in the cabin, and is used for emergency firefighting when a fire occurs in the cabin.

[0031] The above-mentioned vacuum chamber, the gas replacement system includes 2 exhaust fans and 2 vacuum butterfly valves.

[0032] The vacuum butterfly valve is installed on the through-cabin interface of the side wall of the cabin, and two vacuum butterfly valves are arranged diagonally. An exhaust fan is installed at the outlet of the vacuum butterfly valve. The exhaust fan at the end far from the engine draws the outside air into the cabin, and the exhaust fan at the end close to the engine draws the air in the cabin out of the cabin.

[0033] The above-mentioned vacuum chamber, the sewage discharge system includes a stainless steel sewage discharge pipe, a filter, a sewage discharge valve, and a sewage discharge tank.

[0034] The lower wall of the cabin is arranged at an angle of 3°, with the end farthest from the engine as the lowest point. A DN100 through-cabin interface is set on the cabin wall at the lowest point, an 80-mesh filter is installed on the outside of the through-cabin interface, a DN100 drain valve is installed at the filter outlet, and the drain valve outlet is led to the drain tank by a stainless steel drain pipe.

[0035] The above-mentioned vacuum chamber, the operating platform includes an escalator, a guardrail, a patterned steel plate, and a supporting column.

[0036] The beneficial effects of the present invention are:

[0037] A vacuum chamber for high-altitude simulation tests of liquid rocket engines integrates the functions of a heat sink system, a fire protection system, a gas replacement system, an overpressure relief system, a sewage discharge system, an observation window, an installation platform, an operating platform, a propellant supply pipeline, measurement and control equipment, and a cabin interface. Compared with existing vacuum chambers, its reliability and operational convenience are greatly improved.

[0038] A vacuum chamber for high-altitude simulation tests of liquid rocket engines, with a square chamber design and a large available space inside the chamber. The chamber base plate is made of S30408 ​​material, which has a low outgassing rate and is conducive to maintaining a high vacuum degree inside the chamber. The externally welded cross-shaped carbon steel reinforcement ribs play a role in strengthening the strength and rigidity of the chamber, and are economical.

[0039] A vacuum chamber used for high-altitude simulation tests of liquid rocket engines. The three partitions of the heat sink system cabin top and cabin bottom are laid at an overall 3° angle. Compared with the flat laying method, it has two advantages: first, the cooling water is low-in and high-out, which can make the heat sink pipeline full of liquid and achieve the best heat exchange effect. Second, a drain port is set at the lowest point of each partition. After the test, it is conducive to the complete discharge of the accumulated water in the heat sink to avoid the freezing and cracking of the cooling water pipeline in winter.

[0040] A vacuum chamber for high-altitude simulation tests of liquid rocket engines. Considering the convenience of debugging and later expandability, a DN2200 opening is opened in the center of the bulkhead on the side away from the engine and sealed with a blind plate. Three pneumatic butterfly valves are installed in a triangle on the blind plate, and a nozzle is installed at the inlet of the pneumatic butterfly valve to inhale air during system debugging to simulate engine combustion. This provides convenience for the debugging of the entire system after the completion of the entire high-altitude simulation test system. During the subsequent use of the vacuum chamber, the DN2200 blind plate can be removed, and the DN2200 opening can be installed with an incoming flow system, so that an air-breathing engine ignition test can be carried out, which expands the function of the vacuum chamber.

[0041] A vacuum chamber for high-altitude simulation tests of liquid rocket engines. The nitrogen fire-fighting ring pipe in the vacuum chamber adopts a symmetrical layout to ensure uniform air intake and exhaust. Two inner and outer circles of air outlet holes are set on the nitrogen fire-fighting ring pipe. The inner circle air outlet direction is 45 degrees to the engine axis, and the outer circle air outlet direction is 30 degrees to the engine axis. This design method enables the gas ejected during nitrogen fire-fighting to form a three-dimensional layout, which can expand the fire-fighting range and improve the fire-fighting effect.

[0042] A vacuum chamber used for high-altitude simulation tests of liquid rocket engines is provided with an air intake and exhaust system, which are arranged diagonally, with air intake away from the engine and exhaust close to the engine, which is conducive to the formation of a rapid gas replacement flow field in the vacuum chamber. After the test, the harmful gases in the vacuum chamber can be quickly discharged to ensure the health of the operators. The direction of the airflow in the chamber follows the direction of the engine nozzle, and it is not easy to blow excess matter into the engine cavity. Existing vacuum chambers basically do not have this function. After the test, the cabin door is opened for natural ventilation. When the operator handles the post-test, there is a lot of residual harmful gas in the cabin.

[0043] A vacuum chamber used for high-altitude simulation tests of liquid rocket engines. If water is used for emergency firefighting in the vacuum chamber, or if propellant leaks during the test, liquid will accumulate in the vacuum chamber. If the accumulated liquid is not discharged from the vacuum chamber in time, the vacuum degree in the vacuum chamber will decrease during the next test, and the accumulated liquid will continue to evaporate, which will extend the time for vacuuming. Therefore, the lower wall of the chamber is designed at a 3° angle, with the end away from the engine as the lowest point. A DN100 sewage system is set on the wall at the lowest point, which is conducive to the discharge of accumulated liquid from the vacuum chamber.

[0044] A vacuum chamber for high-altitude simulation tests of liquid rocket engines has a water-cooling channel designed inside the sealing structure between the quartz glass observation window and the through-chamber flange to reduce the temperature of the sealing part and avoid O-ring seal failure caused by heat radiation during the test.

[0045] A vacuum chamber for high-altitude simulation tests of liquid rocket engines is designed with an integrated operating platform and chamber body for the convenience of personnel operation. The hanging beam of the side door of the chamber body serves as both the moving guide rail of the door and the load-bearing foundation of the operating platform.

[0046] A vacuum chamber used for high-altitude simulation tests of liquid rocket engines. The chamber is equipped with fixed propellant supply pipelines and measurement and control equipment, which facilitates the testing of different types of engines. The measurement and control switch cabinet and the measurement and control cable interface are arranged at the rear end of the chamber, away from the engine, to avoid high temperature radiation during the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 This is a front view of a vacuum chamber according to a first embodiment of the present invention;

[0048] Figure 2 Schematic diagram of the internal structure of a vacuum chamber according to an embodiment of the present invention. DETAILED DESCRIPTION

[0049] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0050] Embodiment 1

[0051] A vacuum chamber for high-altitude simulation tests of liquid rocket engines, based on the existing vacuum chamber for high-altitude simulation tests of liquid rocket engines, systematically integrates various functions in combination with test requirements, test procedures, and test risks, so that the vacuum chamber has the functions of engine installation and fixation, cabin temperature control, propellant supply through the cabin, engine control and parameter measurement, emergency fire fighting, overpressure relief, cabin sewage discharge, and gas replacement in the cabin after the test.

[0052] A vacuum chamber for high-altitude simulation tests of liquid rocket engines, consisting of a cabin body, a cabin door, a heat sink system, a fire protection system, a gas replacement system, an overpressure relief system, a sewage discharge system, an observation window, an installation platform, an operating platform, a propellant supply pipeline, measurement and control equipment, a cabin penetration interface, etc.

[0053] (1) The cabin adopts a square cabin, placed horizontally, with an internal space of 10m×6m×6m (length×width×height). The cabin base plate adopts S30408 ​​material with low outgassing rate, which is conducive to maintaining high vacuum degree in the cabin. The external welded cross-shaped carbon steel reinforcement ribs play a role in strengthening the strength and rigidity of the cabin. The working pressure inside the vacuum cabin is 0~0.1MPa, and the working temperature is -20~150℃.

[0054] (2) A 1.5m×2.5m (width×height) hatch is set on each side of the cabin body for personnel and small ground equipment to enter and exit the vacuum cabin. A hatch with a size of 3.5m×6m (width×length) is set on the top of the cabin body, above the installation platform, for the engine, thrust measurement device, etc. to be hoisted in and out of the vacuum cabin. The layout of the hatch takes into account the entry and exit of personnel, small ground equipment, engines, thrust measurement devices, etc. in the vacuum cabin. The engine and thrust measurement device can be directly installed after entering the vacuum cabin from the top of the cabin, simplifying the hoisting process.

[0055] (3) The heat sink system adopts a stainless steel tube sheet structure. Cooling water is passed into the stainless steel tube to form a sandwich in the vacuum cabin. The purpose is to form heat exchange in the vacuum cabin when the engine is ignited to reduce the ambient temperature in the vacuum cabin. The heat sink system is equipped with 7 partitions, 1 partition on each of the 6 sides of the cabin, and a movable partition is set at the corresponding position of the top door. The 3 partitions on the top and bottom of the cabin are laid at an overall angle of 3°. A water collecting pipe is set at both ends of each partition, one in and one out. The cooling water enters from a low position and exits from a high position to ensure full liquid and achieve the best heat exchange effect. A drain outlet is set at the lowest point of each partition, which is collected on the main drain pipe and a drain valve is installed. In winter, after the test, open the drain valve to drain all the water in the heat sink to prevent the cooling water from freezing and bursting the pipeline.

[0056] (4) On the bulkhead of the vacuum chamber, a series of process and measurement and control penetration interfaces are set between the cross-shaped reinforcement ribs as needed. A DN2800 opening is opened at the center of the bulkhead on one side of the engine nozzle to connect the diffuser and guide and extract the gas generated when the engine is ignited. A DN2200 opening is opened at the center of the bulkhead on the side away from the engine and is blocked with a blind plate. Three pneumatic butterfly valves are installed in a triangle on the blind plate, and nozzles are installed at the inlet of the butterfly valves. The nozzle throat diameter is designed according to the debugging needs. During the debugging stage of the liquid rocket engine high-altitude simulation test bench, different combinations of butterfly valves are opened to suck air into the vacuum chamber to simulate engine ignition under different working conditions, thereby verifying the test bench's ability to extract gas. During the subsequent use of the vacuum chamber, the DN2200 blind plate can be removed, and the DN2200 opening can be installed with an inflow system, so that the air-breathing engine ignition test can be carried out, expanding the function of the vacuum chamber.

[0057] The process and measurement and control penetration interfaces on the side wall of the vacuum cabin are used for process liquid supply, gas supply pipelines, measurement and control cables, etc. The process and measurement and control penetration interfaces are arranged at the rear end of the cabin away from the side wall of the cabin body at the engine to avoid high temperature radiation to the process pipelines and measurement and control cables when the engine is working, and the heat sink is set with openings accordingly.

[0058] (5) A fire fighting system is installed in the vacuum chamber, including water fire fighting and nitrogen fire fighting, which are used to extinguish fires when propellant leaks or fires occur in the vacuum chamber during the test. The nitrogen fire fighting system consists of two semicircular DN50 stainless steel fire fighting rings and a DN50 air supply pipeline. The nitrogen fire fighting main air supply pipeline enters the vacuum chamber from the cabin penetration interface and is divided into two routes through a tee, which enter the two semicircular fire fighting rings from the middle position respectively. The tee is located on the symmetric axis of the two semicircular fire fighting rings, and the two branch air supply pipelines are also arranged symmetrically to ensure uniform air intake and air outlet of the nitrogen fire fighting rings. The two semicircular fire fighting rings are installed around the diffuser, and two inner and outer circles of air outlet holes are set on the pipe wall facing the engine. The inner circle air outlet direction is 45° to the engine axis, mainly for fire fighting in the area near the engine; the outer circle air outlet direction is 30° to the engine axis, mainly for fire fighting in the area near the thrust measurement device behind the engine.

[0059] The water fire fighting system consists of DN50 stainless steel pipes, sprinklers, etc. It is arranged on the top of the cabin and around the cabin top door. The axis of all sprinklers is tilted 20° toward the installation platform in the cabin, which is used for emergency fire fighting when a fire occurs in the cabin.

[0060] (6) The gas replacement system consists of an air intake and exhaust system on the vacuum cabin, including two exhaust fans and two vacuum butterfly valves. The vacuum butterfly valves are installed on the side wall interfaces at both ends of the cabin body and are arranged diagonally. An exhaust fan is installed at the outlet of the vacuum butterfly valve. The exhaust fan at the end away from the engine draws the outside air into the vacuum cabin, and the exhaust fan at the end close to the engine draws the air inside the cabin out of the cabin. This design is conducive to the replacement of gas inside the cabin and realizes rapid replacement of gas inside the cabin after the test. The airflow direction in the cabin follows the direction of the engine nozzle, which makes it difficult to blow excess matter into the engine cavity.

[0061] (7) The overpressure relief system consists of an inverted arch blasting device installed on the side wall of the vacuum cabin. When the cabin is over-pressurized, the blasting device is activated to quickly release the pressure inside the cabin.

[0062] (8) The sewage system consists of stainless steel pipes, filters, sewage valves, etc., and is used to discharge the accumulated liquid in the cabin. The lower wall of the cabin is designed at a 3° angle, with the end away from the engine as the lowest point. A DN100 through-cabin interface is set on the lowest point of the cabin wall, and an 80-mesh filter is installed on the outside of the interface. A DN100 sewage valve is installed at the filter outlet, and the valve outlet is led to the sewage tank by a stainless steel pipe.

[0063] (9) Observation windows are set on the side walls of the cabin and on both sides of the engine. The material of the observation windows is 20mm thick quartz glass, and both sides are coated with anti-reflection film. A fluororubber O-ring is used to seal the quartz glass and the penetration interface. Since the observation window faces the engine nozzle, the heat radiation is high during the test run. In order to avoid the failure of the O-ring seal, a water cooling channel is designed inside the penetration flange to reduce the temperature of the sealing part.

[0064] (10) An installation platform is designed inside the cabin for installing the thrust measurement device and the engine, which serves as the installation base for the engine during the test run.

[0065] (11) An operating platform is set up around the installation platform in the cabin and in the dense area of ​​the cabin flange outside the cabin. It is composed of escalators, guardrails, patterned steel plates, support columns, etc., which is convenient for personnel to stand and operate. The operating platform is integrated with the vacuum cabin. The side door hanging beam of the cabin body serves as both the moving guide rail of the cabin door and the load-bearing foundation of the operating platform.

[0066] (12) A fixed propellant supply pipeline is arranged in the cabin, which enters the cabin from top to bottom through the cabin flange at the rear end of the cabin roof, and is laid forward along the cabin roof to the rear end of the engine, leaving an interface. The pipeline from the interface to the engine is configured on site according to different types of engines.

[0067] (13) Measurement and control equipment, including a transfer cabinet and measurement and control cables, are arranged in the cabin as the transmission channel for engine control and measurement signals in the cabin. The measurement and control cables enter the cabin from the cabin flange, and after being transferred through the transfer cabinet, the cables are laid from both sides of the installation platform to the vicinity of the engine. The transfer cabinet and the measurement and control cable cabin interface are arranged at the rear end of the cabin body, away from the engine, to avoid high temperature radiation during the test run.

[0068] (14) A vacuum chamber used for high-altitude simulation tests of liquid rocket engines. Considering the convenience of debugging and subsequent expandability, a DN2200 opening is opened in the center of the bulkhead on the side away from the engine and sealed with a blind plate. Three pneumatic butterfly valves are installed in a triangle on the blind plate, and nozzles are installed at the inlet of the pneumatic butterfly valves to inhale air during system debugging to simulate engine fuel gas. This provides convenience for the debugging of the entire high-altitude simulation test system after it is built. During the subsequent use of the vacuum chamber, the DN2200 blind plate can be removed, and the DN2200 opening can be installed with an inflow system, so that an air-breathing engine ignition test can be carried out, expanding the function of the vacuum chamber.

Claims

1. A vacuum chamber for high-altitude simulation testing of liquid rocket engines, characterized in that: It includes cabin, door, heat sink system, fire protection system, gas replacement system, reverse arch blasting device, sewage system, installation platform, operating platform, propellant supply pipeline, and measurement and control equipment; The cabin is in a cubic shape, placed horizontally, and has cross-shaped carbon steel reinforcement ribs welded on the outside; the working pressure inside the cabin is 0 to 0.1 MPa, and the working temperature is -20 to 150°C; The hatch is rectangular and located on the cabin, including two side hatches and a top hatch. The two side hatches are located on both sides of the cabin, and a total of two are provided for the entry and exit of personnel and small ground equipment; the top hatch is located on the top of the cabin, and is used for the entry and exit of the engine and the thrust measurement device; The heat sink system is a stainless steel tube sheet structure, and cooling water is passed into the stainless steel tube to form a sandwich inside the cabin, which is used for cabin heat exchange and reduces the ambient temperature inside the cabin; The fire fighting system includes water fire fighting and nitrogen fire fighting, which are used to extinguish fires when propellant leaks or catches fire in the cabin; the gas replacement system is installed on the through-cabin interfaces on both side walls of the cabin, which is used to quickly replace the gas in the cabin so that the airflow direction in the cabin follows the direction of the engine nozzle; The reverse arch blasting device is installed on the side wall of the cabin. When the cabin is over-pressurized, the reverse arch blasting device is activated. Rapidly release the pressure in the cabin; The sewage system is used to discharge the accumulated liquid in the cabin; The installation platform is located in the cabin and is used to install the thrust measurement device and the engine; The operating platform is used for operators to stand and operate, the inner part of the cabin is located around the installation platform, and the outer part of the cabin is located in the flange-dense area of ​​the hatch outside the cabin; The propellant supply pipeline is fixed on the cabin and enters the cabin from top to bottom through the cabin penetration flange on the top of the cabin. It is laid along the inner side of the cabin top to the rear end of the engine and is provided with an interface; The measurement and control equipment is a transmission channel for engine control and measurement signals, including a transfer cabinet and measurement and control cables. The measurement and control cables enter the cabin from the cabin flange, are transferred through the transfer cabinet, and are connected from both sides of the installation platform to the engine. The switch cabinet and the measurement and control cable entry interface are located at the rear end of the cabin, away from the engine.

2. The vacuum chamber according to claim 1, characterized in that: Also includes observation windows; The observation window is installed on the cabin side wall through-cabin interface located on both sides of the engine, and is used to observe the engine nozzle and non-contact temperature measurement; A sealing ring is arranged between the observation window and the through-cabin interface of the side wall of the cabin; a water cooling channel is arranged at the sealing ring of the through-cabin interface of the side wall of the cabin to reduce the temperature of the sealing ring part.

3. The vacuum chamber according to claim 2, characterized in that: The observation window is made of quartz glass with anti-reflection coating on both sides; The thickness of the observation window is 20mm; The sealing ring is a fluororubber O-type sealing ring.

4. The vacuum chamber according to claim 1, characterized in that: A DN2200 opening is opened in the center of the bulkhead on the side away from the engine and sealed with a blind plate; three pneumatic butterfly valves are installed in a triangle on the blind plate, and a nozzle is installed at the inlet of the pneumatic butterfly valve to inhale air during system debugging to simulate engine fuel gas; during the subsequent use of the vacuum chamber, the DN2200 blind plate can be removed, and the DN2200 opening can be installed with an incoming flow system to carry out air-breathing engine ignition tests.

5. The vacuum chamber according to claim 1, characterized in that: The cabin is made of S30408 ​​material, and the length × width × height of the cabin is 10m × 6m × 6m; the width × height of the doors on both sides is 1.5m × 2.5m, and the width × length of the top door is 3.5m × 6m.

6. The vacuum chamber according to claim 1, characterized in that: The heat sink system is provided with 7 partitions, one partition is provided on each of the 6 sides of the cabin, one partition is provided at the corresponding position of the hatch on the top of the cabin, and one partition of the hatch on the top of the cabin is a movable partition; The three partitions on the top and bottom of the cabin are laid at an angle of 3° as a whole; Water pipes are set at both ends of each partition, with one inlet and one outlet, and the cooling water enters from low and exits from high; a drain outlet is set at the lowest point of each partition, and the drain outlets are connected to the main drain pipe, and a drain valve is installed on the main drain pipe.

7. The vacuum chamber according to claim 1, characterized in that: The nitrogen firefighting includes two semicircular DN50 stainless steel firefighting rings and a DN50 gas supply pipeline; The air supply pipeline includes a main air supply pipeline and a branch air supply pipeline. The main air supply pipeline enters the cabin from the cabin penetration interface, is divided into two routes through a tee, and enters two semicircular fire rings from the middle position respectively; the tee is located on the symmetry axis of the two semicircular fire rings, and the two branch air supply pipelines are symmetrically arranged; the two semicircular fire rings are installed around the diffuser, and inner and outer circles of air outlet holes are arranged on the pipe wall facing the engine side. The direction of the inner circle of air outlet holes is 45° with the engine axis, which is used for fire fighting in the area near the engine; the direction of the outer circle of air outlet holes is 30° with the engine axis, which is used for fire fighting in the area near the thrust measurement device behind the engine; The water fire fighting is located around the hatch on the top of the cabin, and includes a DN50 stainless steel pipe and a nozzle; the axis of the nozzle is inclined 20° toward the installation platform in the cabin, and is used for emergency fire fighting when a fire occurs in the cabin.

8. The vacuum chamber according to claim 1, characterized in that: The gas replacement system includes 2 exhaust fans and 2 vacuum butterfly valves; The vacuum butterfly valve is installed on the through-cabin interface of the side wall of the cabin, and the two vacuum butterfly valves are arranged diagonally; an exhaust fan is installed at the outlet of the vacuum butterfly valve, the exhaust fan at the end away from the engine draws the outside air into the cabin, and the exhaust fan at the end close to the engine draws the air in the cabin out of the cabin.

9. The vacuum chamber according to claim 1, characterized in that: The sewage system includes a stainless steel sewage pipe, a filter, a sewage valve, and a sewage tank; The lower wall of the cabin is arranged at an angle of 3°, with the end farthest from the engine as the lowest point. A DN100 through-cabin interface is set on the cabin wall at the lowest point, an 80-mesh filter is installed on the outside of the through-cabin interface, a DN100 drain valve is installed at the filter outlet, and the drain valve outlet is led to the drain tank by a stainless steel drain pipe.

10. The vacuum chamber according to claim 1, characterized in that: The operating platform comprises an escalator, a guardrail, a patterned steel plate and a supporting column.

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