A vacuum chamber for high-altitude simulation testing of liquid rocket engines

Abstract

The present invention relates to a vacuum chamber for high-altitude simulation testing of liquid rocket engines, belonging to the field of aerospace liquid rocket engine testing technology. The chamber solves the technical problems of traditional vacuum chambers, such as single functions, difficult operation, and poor safety. The chamber comprises a chamber body, a hatch, a heat sink system, a fire protection system, a gas displacement system, a reverse-arch blasting device, a sewage system, a mounting platform, an operating platform, a propellant supply pipeline, and measurement and control equipment. The chamber body is cubical, with an internal operating pressure of 0 to 0.1 MPa. The hatch is used for the entry and exit of personnel, small ground equipment, engines, and thrust measurement devices. The heat sink system, fire protection system, gas displacement system, sewage system, mounting platform, and propellant supply pipeline are installed on the chamber body, and the measurement and control equipment serves as a transmission channel for engine control and measurement signals. The vacuum chamber is used for high-altitude simulation testing of liquid rocket engines.

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 testing of liquid rocket engines, the vacuum chambers currently used are mostly cylindrical, with simple structures and limited functions. They only meet the vacuum requirements for high-altitude simulation testing of engines and lack significant functionality. Most vacuum chambers are designed solely to meet testing requirements, resulting in cramped interiors, 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 and placed horizontally, with 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 degrees Celsius.

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

[0008] The heat sink system is a stainless steel tube plate structure. Cooling water is passed into the stainless steel tube to form an interlayer in the cabin, which is used for cabin heat exchange and reduces 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 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 and is used for rapid replacement of gas in the cabin so that the direction of the airflow in the cabin 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 to discharge 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 internal part of the cabin is located around the installation platform, and the external part of the cabin is located in the flange-intensive area of ​​the cabin hatch.

[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 serves as a transmission channel for engine control and measurement signals. It includes a switch cabinet and measurement and control cables. The cables enter the cabin through a through-flange and are routed through the switch cabinet, extending from both sides of the mounting platform to the engine. The switch cabinet and the measurement and control cable 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 windows are installed on the cabin side wall penetration interfaces on both sides of the engine and are used for observing the engine nozzle and non-contact temperature measurement.

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

[0020] In the above-mentioned vacuum chamber, the observation window is made of quartz glass with anti-reflection film 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 vacuum chamber features a DN2200 opening in the center of the bulkhead on the side away from the engine, sealed with a blind plate. Three pneumatic butterfly valves are installed in a triangular pattern on the blind plate, with nozzles installed at the inlets to draw in air during system commissioning to simulate engine fuel gas. During subsequent use of the vacuum chamber, the DN2200 blind plate can be removed, and the DN2200 opening can be fitted with an inflow system for conducting air-breathing engine ignition tests.

[0024] The vacuum chamber is made of S30408 ​​material, with dimensions of 10m x 6m x 6m in length, width, and height. The doors on both sides measure 1.5m x 2.5m in width and height, and the top door measures 3.5m x 6m in width and length.

[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, and one partition is provided at the corresponding position of the hatch on the top of the chamber body. 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 the cabin bottom are laid at an angle of 3° as a whole.

[0027] Each zone is equipped with water pipes at both ends, with one inlet and one outlet. The cooling water enters from a low point and exits from a high point. Each zone is equipped with a drain outlet at the lowest point, which is connected to the main drain pipe, and a drain valve is installed on the main drain pipe.

[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 line includes a main air supply line and branch air supply lines. The main air supply line enters the cabin through the cabin interface and is divided into two lines by a tee, respectively entering two semicircular fire rings from the middle position. The tee is located on the symmetry axis of the two semicircular fire rings, and the two branch air supply lines are arranged symmetrically. The two semicircular fire rings are installed around the diffuser, and two inner and outer rings of air outlet holes are set on the pipe wall facing the engine. The inner ring of air outlet holes is oriented at 45 degrees to the engine axis and is used for fire fighting in the area near the engine; the outer ring of air outlet holes is oriented at 30 degrees to the engine axis and is used for fire fighting in the area near the thrust measurement device behind the engine.

[0030] The firefighting water 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 tilted 20 degrees toward the installation platform inside the cabin and is used for emergency firefighting in the event of a fire inside the cabin.

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

[0032] The vacuum butterfly valve is installed on the through-tank interface of the cabin side wall, with two vacuum butterfly valves 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 outside air into the cabin, and the exhaust fan at the end close to the engine draws air 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 a 3° angle, with the end away 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, and a DN100 drain valve is installed at the filter outlet. The drain valve outlet is led to the sewage 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 used 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 testing of liquid rocket engines features a rectangular cabin design with ample usable space. The cabin baseplate is constructed of S30408 ​​material, which has a low outgassing rate and facilitates the maintenance of a high vacuum level within the cabin. Externally welded crisscross carbon steel reinforcement ribs enhance the cabin's strength and rigidity, ensuring high economic efficiency.

[0039] A vacuum chamber used for high-altitude simulation testing of liquid rocket engines features three sections of the heat sink system, the top and bottom sections, laid out at a 3° angle. This offers two advantages over a flat layout: first, cooling water enters at a low point and exits at a high point, ensuring that the heat sink pipes are filled with liquid for optimal heat exchange. Second, a drain outlet is located at the lowest point of each section. This allows for the complete drainage of accumulated water after the test, preventing freezing and cracking of the cooling water pipes in winter.

[0040] A vacuum chamber for high-altitude simulation testing of liquid rocket engines, designed for ease of commissioning and future expansion, features a DN2200 opening in the center of the bulkhead on the side away from the engine, sealed with a blind plate. Three pneumatic butterfly valves are installed in a triangular pattern on the blind plate, with nozzles installed at the inlets to draw in air and simulate engine combustion during system commissioning. This facilitates full system commissioning of the high-altitude simulation test system after its completion. During subsequent use of the vacuum chamber, the DN2200 blind plate can be removed, and the DN2200 opening can be fitted with an inflow system, enabling ignition tests of air-breathing engines and expanding the functionality of the vacuum chamber.

[0041] A vacuum chamber used for high-altitude simulation testing of liquid rocket engines features a symmetrical layout of nitrogen firefighting ring pipes to ensure uniform air intake and exhaust. The ring pipes are equipped with inner and outer rings of outlet holes. The inner ring's outlet direction is at a 45-degree angle to the engine axis, while the outer ring's outlet direction is at a 30-degree angle to the engine axis. This design ensures that the nitrogen firefighting gas is discharged in a three-dimensional pattern during operation, expanding the firefighting range and improving firefighting effectiveness.

[0042] A vacuum chamber for high-altitude simulation tests of liquid rocket engines is provided with an air intake and exhaust system, which are arranged diagonally, with the air intake away from the engine and the 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 protect the health of the operators. The direction of the airflow in the chamber follows the direction of the engine nozzle, which makes it difficult for excess matter to be blown into the engine cavity. Existing vacuum chambers basically do not have this function. After the test, the air is naturally ventilated by opening the cabin door. When the operator handles the test after the test, there is a lot of residual harmful gas in the chamber.

[0043] A vacuum chamber used for high-altitude simulation testing of liquid rocket engines. Emergency situations involving water firefighting or propellant leaks during testing can cause liquid to accumulate within the chamber. If this accumulated liquid is not promptly drained from the chamber, the vacuum level decreases during the next test, causing the accumulated liquid to evaporate and prolong the vacuum pumping time. 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 drain system is installed on the wall at this lowest point to facilitate the drainage of accumulated liquid from the chamber.

[0044] A vacuum chamber used 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. This can reduce the temperature of the sealing part and avoid O-ring seal failure caused by heat radiation during the test.

[0045] A vacuum chamber used for high-altitude simulation testing of liquid rocket engines features an integrated operating platform and chamber design for operator convenience. The cabin's side door hanging beam serves as both a guide rail for the door and a load-bearing foundation for the operating platform.

[0046] A vacuum chamber designed for high-altitude simulation testing of liquid rocket engines. It features fixed propellant supply lines and measurement and control equipment, facilitating testing of various engine models. The measurement and control adapter cabinet and cable entry points are located at the rear of the chamber, away from the engine, to avoid high-temperature radiation during testing. 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 will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0050] Example 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, various functions are systematically integrated in combination with test requirements, test processes, and test risks. The vacuum chamber is equipped with functions such as 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 post-test cabin gas replacement.

[0052] A vacuum chamber for high-altitude simulation tests of liquid rocket engines consists 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, and a cabin penetration interface.

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

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

[0055] (3) The heat sink system adopts a stainless steel tube plate 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, thereby reducing the ambient temperature in the vacuum cabin. The heat sink system has a total of 7 partitions, 1 partition on each of the 6 sides of the cabin, and a movable partition corresponding to the top door. The 3 partitions on the cabin top and bottom are laid at a 3° angle. A water collecting pipe is set at each end of each partition, one inlet and one outlet. 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, the drain valve is opened to drain all the water inside the heat sink to prevent the cooling water from freezing and bursting the pipe.

[0056] (4) On the bulkhead of the vacuum chamber, a series of process and measurement and control interfaces are set up 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 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 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, air is sucked into the vacuum chamber by opening different combinations of butterfly valves 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 to carry out air-breathing engine ignition tests, thereby expanding the function of the vacuum chamber.

[0057] The process and measurement and control penetration ports on the side walls of the vacuum chamber are used for process fluid and gas supply lines, as well as measurement and control cables. These ports are located at the rear end of the chamber, away from the engine side walls, to prevent high-temperature radiation from the process piping and measurement and control cables during engine operation. The heat sink has corresponding openings.

[0058] (5) A fire-fighting system is installed in the vacuum chamber, including water fire-fighting and nitrogen fire-fighting, which is used to extinguish fires in the event of propellant leakage or fire in the vacuum chamber during testing. The nitrogen fire-fighting system consists of two semicircular DN50 stainless steel fire-fighting rings and a DN50 air supply pipe. The nitrogen fire-fighting main air supply pipe enters the vacuum chamber from the through-chamber interface and is divided into two parts by a tee, which enter the two semicircular fire-fighting rings from the middle position respectively. The tee is located on the symmetrical axis of the two semicircular fire-fighting rings, and the two branch air supply pipes are also arranged symmetrically to ensure uniform air intake and 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 side. The air outlet direction of the inner circle is 45 degrees to the engine axis, mainly for fire-fighting the area near the engine; the air outlet direction of the outer circle is 30 degrees to the engine axis, mainly for fire-fighting the area near the thrust measurement device behind the engine.

[0059] The water fire extinguishing system consists of DN50 stainless steel pipes and nozzles. It is arranged on the top of the cabin and around the cabin door. The axis of all nozzles is tilted 20 degrees toward the installation platform inside the cabin. It is used for emergency fire fighting in case of fire inside the cabin.

[0060] (6) The gas replacement system consists of an air intake and exhaust system on the vacuum chamber, 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 chamber 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 chamber, and the exhaust fan at the end close to the engine draws the air inside the chamber out of the chamber. This design is conducive to the replacement of the gas inside the chamber and realizes the rapid replacement of the gas inside the chamber after the test. The direction of the airflow inside the chamber follows the direction of the engine nozzle, which makes it difficult for excess matter to be blown 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 chamber. When the chamber is over-pressurized, the blasting device is activated to quickly release the pressure inside the chamber.

[0062] (8) The sewage system consists of stainless steel pipes, filters, and sewage valves, and is used to drain 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 wall at the lowest point, 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 installed on the side walls of the cabin, on both sides of the engine. The observation windows are made of 20mm thick quartz glass with anti-reflection coating on both sides. A fluororubber O-ring is used to seal the quartz glass and the through-cabin interface. Since the observation window faces the engine nozzle, the heat radiation is high during the test run. To avoid O-ring seal failure, a water cooling channel is designed inside the through-cabin 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, serving as the installation base for the engine during the test run.

[0065] (11) An operating platform is set up around the installation platform inside the cabin and in the dense area of ​​the cabin flange outside the cabin. It consists 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 cabin side door hanging beam 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 line is arranged in the cabin. It enters the cabin from the top down 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 this interface to the engine is configured on site according to the different types of engines.

[0067] (13) Measurement and control equipment, including a transfer cabinet and measurement and control cables, are arranged in the cabin, serving as a channel for controlling and measuring signals of the engine 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 both arranged at the rear end of the cabin, away from the engine, to avoid high temperature radiation during the test run.

[0068] (14) A vacuum chamber for high-altitude simulation testing of liquid rocket engines. Considering the convenience of debugging and subsequent expansion, 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 and simulate engine combustion during system debugging. This provides convenience for the full system debugging of the entire high-altitude simulation test system after it is completed. 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, allowing for the ignition test of the air-breathing engine, thus expanding the function of the vacuum chamber.

Claims

1. A vacuum chamber for high-altitude simulation testing of liquid rocket engines, characterized in that: Including cabin, hatch, heat sink system, fire protection system, gas replacement system, reverse arch blasting device, sewage system, installation platform, operating platform, propellant supply pipeline, measurement and control equipment; The cabin is in a cubic shape, placed horizontally, and has cross-shaped carbon steel reinforcement ribs welded to 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 body, including two side hatches and a top hatch. The two side hatches are located on both sides of the cabin body, and are used for personnel and small ground equipment to enter and exit. The top hatch is located on the top of the cabin body and is used for the engine and thrust measurement device to enter and exit. The heat sink system is a stainless steel tube plate structure. 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 in the event of propellant leakage or fire in the cabin. The gas replacement system is installed on the through-cabin interfaces on both sides of the cabin and is used to quickly replace the gas in the cabin, so that the airflow direction in the cabin is in 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 mounting 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, with the inner part of the cabin located around the installation platform and the outer part of the cabin located in the flange-intensive area of ​​the cabin hatch; The propellant supply pipeline is fixed on the cabin and enters the cabin from top to bottom through the cabin 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 then extend from both sides of the installation platform to the engine. The transfer cabinet and the measurement and control cable 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 window; The observation windows are installed on the cabin side wall through-cabin interfaces on both sides of the engine and are used for observing the engine nozzle and non-contact temperature measurement; A sealing ring is provided between the observation window and the cabin side wall penetration interface; a water cooling channel is provided at the sealing ring of the cabin side wall penetration interface 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, wherein: 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; 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, wherein: The heat sink system is provided with 7 partitions, one partition is provided on each of the 6 sides of the cabin, and one partition is provided at the position corresponding to the hatch on the top of the cabin. One partition of the hatch on the top of the cabin is a movable partition. The three partitions on the cabin top and cabin bottom are laid at an overall angle of 3°; Water pipes are set at both ends of each partition, with one inlet and one outlet, and the cooling water enters from a low point and exits from a high point; 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 and is divided into two routes through a tee, respectively entering two semicircular fire rings from the middle position; the tee is located on the symmetric axis of the two semicircular fire rings, and the two branch air supply pipelines are arranged symmetrically; the two semicircular fire 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 direction of the inner circle of air outlet holes is 45 degrees to the engine axis and is used for fire fighting in the area near the engine; the direction of the outer circle of air outlet holes is 30 degrees to the engine axis and 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 inside the cabin, and is used for emergency fire fighting when a fire occurs inside 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 a 3° angle, with the end away 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, and a DN100 drain valve is installed at the filter outlet. The drain valve outlet is led to the sewage tank by a stainless steel drain pipe.

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

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