Environmental chamber, test device and method for studying contrail cloud formation and evolution

Abstract

The present invention discloses an environmental chamber, testing device, and method for studying the formation and evolution of contrail clouds. The environmental chamber includes a chamber assembly, an air intake assembly, and an exhaust assembly. A test chamber is formed in the chamber assembly and is provided with an optical observation window panel and a first mounting plate for mounting a sampler. The air intake assembly includes a dilution unit, a first air intake unit, and a second air intake unit. The dilution unit is used to receive and mix the exhaust and dilution gas from an aircraft engine. The first air intake unit is connected to the dilution unit to receive the mixed gas and spray it into the test chamber. The second air intake unit is used to transport low-temperature, high-humidity gas toward the test chamber. The exhaust assembly is used to discharge part of the gas in the test chamber. The environmental chamber for studying the formation and evolution of contrail clouds according to the embodiment of the present invention can not only simulate the formation and evolution of contrail clouds, but also facilitate sampling and research of contrail clouds and optical measurement, thereby achieving effective research on contrail clouds.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft contrail simulation testing, and in particular to an environmental chamber, a testing device and a method for studying contrail generation and evolution. Background Art

[0002] Contrails are linear ice clouds produced by jet aircraft cruising at the top of the troposphere. The persistence of these linear ice clouds in an ice-supersaturated environment will form cirrus clouds, which can exert a huge global radiative forcing effect, become the largest aviation climate forcing factor, and have great potential in reducing aviation climate impacts.

[0003] In order to clearly understand the physical and chemical properties of contrails, their formation, and the transformation process of contrails into cirrus clouds, and to facilitate the subsequent formulation of mitigation measures, it is necessary to study the generation and evolution of aircraft contrails.

[0004] Among them, the formation and evolution of contrails are affected by the coupling of many factors such as aviation carbon soot emissions, plume injection and meteorological environment. It is a multiphase flow process that couples multiple disciplines such as dynamics, thermodynamics, and gas dynamics. At present, there are two main methods for studying the formation and evolution of aircraft contrails. One is to study the formation and evolution process of contrails by combining theoretical deduction with numerical simulation, but this method lacks complete experimental data support; the other method is the "aircraft-to-aircraft" contrails experimental measurement. This experimental method mainly generates contrails by flying an aircraft at a high cruising altitude, and another aircraft equipped with corresponding measurement equipment follows behind to measure the various properties of the contrails. However, this method is not only costly, but also easily affected by environmental factors and the limitations of experimental measurement equipment.

[0005] Therefore, it is necessary to develop a test device that can study the generation and evolution of contrail clouds to support research on the impact of aviation emissions on global climate. Summary of the Invention

[0006] The present invention aims to address at least one of the technical problems existing in the prior art. To this end, the first aspect of the present invention proposes an environmental chamber for studying the formation and evolution of contrail clouds. This chamber not only simulates the formation and evolution of contrail clouds to reduce research costs, but also facilitates contrail cloud sampling and optical measurement, resolving technical issues in prior art contrail cloud research, such as the lack of complete experimental data support and high experimental costs.

[0007] A second aspect of the present invention provides a testing device having the above-mentioned environmental chamber.

[0008] A third aspect of the present invention provides a testing method for the above-mentioned testing device.

[0009] An environmental chamber for studying the formation and evolution of contrails according to an embodiment of the present invention includes: a cabin assembly forming a test cavity, the cabin assembly being provided with an optical observation window panel and a first mounting plate on which a sampler can be mounted; an air intake assembly, the air intake assembly including: a dilution unit, the dilution unit being used to receive exhaust and dilution gas from an aircraft engine and to mix the exhaust and dilution gas; a first air intake unit, the first air intake unit being connected to the dilution unit and being used to receive the mixed gas from the dilution unit and to spray the mixed gas into the test cavity; a second air intake unit, the second air intake unit being used to transport low-temperature and high-humidity gas toward the test cavity; and an exhaust assembly, the exhaust assembly being connected to the test cavity and being used to discharge part of the gas in the test cavity.

[0010] According to an embodiment of the present invention, an environmental chamber for studying the formation and evolution of contrail clouds is provided. By providing a second air intake unit that delivers low-temperature, high-humidity gas toward a test chamber and an exhaust assembly that discharges part of the gas in the test chamber, a low-temperature, low-pressure, and high-humidity environment can be formed in the test chamber, thereby simulating a high-altitude environment. In this way, when the dilution unit injects the aircraft engine exhaust mixed with the dilution gas into the test chamber, the formation and evolution of contrail clouds can be simulated. At the same time, the present application also provides an optical observation window panel and a first mounting plate on which a sampler can be installed on the chamber assembly, so that the contrail clouds in the test chamber can be collected by the sampler and the contrail clouds in the test chamber can be observed and optically measured using the optical observation window panel, so as to realize the study of contrail clouds and reduce research costs. In other words, the environmental chamber of the present application can not only simulate the formation and evolution of contrail clouds, but also facilitate the sampling and optical measurement of contrail clouds, thereby improving the accuracy of research and reducing research costs.

[0011] According to some embodiments of the environmental chamber of the present invention, the optical observation window panels include multiple groups, and the multiple groups of optical observation window panels are arranged along the length direction of the chamber assembly. The optical observation window panels include optical measurement window panels and light source window panels.

[0012] Optionally, the dilution unit includes a mixing tube, which is provided with an air inlet, an air inlet channel and an air outlet connecting the inner and outer sides of the mixing tube, the air inlet and the air outlet are arranged at the axial ends of the mixing tube, the air inlet is connected to the aircraft engine, and the air outlet is connected to the first air intake unit; the air inlet channel is arranged in the circumference of the mixing tube, and is used to transport the dilution gas toward the mixing tube.

[0013] Optionally, the air intake channel includes multiple air intake channels, and the multiple air intake channels are arranged at intervals along the axial and / or circumferential direction of the mixing tube; wherein the axis of the air intake channel extends obliquely relative to the cross-sectional plane of the mixing tube, the cross-sectional plane is parallel to the front-to-back direction and the up-down direction of the mixing tube, and the axes of the multiple air intake channels are inclined in the same clockwise direction.

[0014] Optionally, the dilution unit includes a first air intake pipe and a pressure equalizing pipe with different extension directions. The pressure equalizing pipe is sleeved on the mixing pipe and cooperates with the mixing pipe to define a first pressure equalizing chamber. The first air intake pipe is connected to the first pressure equalizing chamber for transporting the dilution gas toward the first pressure equalizing chamber. The first pressure equalizing chamber is connected to multiple air intake channels.

[0015] Optionally, the air intake assembly includes a connecting plate, which is connected to the end of the cabin assembly, and the first air intake unit and the second air intake unit are both arranged on the connecting plate; wherein, the first air intake unit includes an injection unit, and the injection unit includes a nozzle and an injection pipe, and the nozzle is used to receive the gas mixed by the dilution unit, and the opposite ends of the injection pipe are respectively connected to the nozzle and the test chamber.

[0016] Optionally, a first pressure equalizing plate is provided on the side of the connecting plate close to the test chamber, the first pressure equalizing plate cooperates with the connecting plate to define a second pressure equalizing chamber, and a plurality of first diversion ports connected to the second pressure equalizing chamber are provided on the first pressure equalizing plate, the second air intake unit includes a plurality of second air intake pipes, and the plurality of second air intake pipes are arranged at intervals on the connecting plate and connected to the second pressure equalizing chamber; a second pressure equalizing plate, a third air intake pipe connected to the second pressure equalizing plate and a diversion structure are provided on the connecting plate, the diversion structure includes a plurality of second diversion ports passing through the connecting plate, the second pressure equalizing plate is provided on the side of the connecting plate away from the test chamber and cooperates with the connecting plate to define a third pressure equalizing chamber, the third pressure equalizing chamber covers the diversion structure, and the third air intake pipe is used to transport gas toward the third pressure equalizing chamber.

[0017] Optionally, the cabin assembly is further provided with an air intake pipe mounting plate, the air intake pipe mounting plate is arranged between multiple groups of the optical observation window panels, and a fourth air intake pipe is provided on the air intake pipe mounting plate, and the fourth air intake pipe is used to transport gas toward the test chamber.

[0018] According to an embodiment of the present invention, a test device for studying the formation and evolution of contrail clouds includes: an environmental chamber, which is the aforementioned environmental chamber provided with an optical measurement window panel and a light source window panel; a test system, which includes an air-floating vibration-isolating optical platform, a high-speed camera, a microscope, and a light source, wherein the high-speed camera and the microscope are arranged on the air-floating vibration-isolating optical platform, the microscope is arranged between the high-speed camera and the optical measurement window panel, and the light source is directly opposite the light source window panel; an installation chamber and a first air supply system, wherein an aircraft engine to be tested is arranged in the installation chamber, the aircraft engine and the first air supply system are both connected to the dilution unit, and the first air supply system is used to transport dilution gas toward the dilution unit; a second air supply system, which is connected to the second air inlet unit and is used to transport low-temperature and high-humidity gas toward the second air inlet unit; and an exhaust system, which is connected to the exhaust component and is used to extract gas in the test chamber through the exhaust component.

[0019] According to the testing device of the embodiment of the present invention, by adopting the aforementioned environmental chamber provided with an optical measurement window panel and a light source window panel, it is possible to use the testing device to perform optical measurement of the contrail cloud in the environmental chamber, thereby realizing the study of the contrail cloud and reducing the research cost.

[0020] A testing method for a test device for studying contrail formation and evolution according to an embodiment of the present invention includes the following steps: placing the aircraft engine in the installation chamber; starting the aircraft engine under ground air intake conditions, and determining whether the aircraft engine is in normal condition; if so, executing the next step; if not, performing troubleshooting; and observing the formation and evolution of the contrail of the aircraft engine in the environmental chamber using the test system.

[0021] According to the testing method of the testing device for studying the generation and evolution of contrail clouds in an embodiment of the present invention, by utilizing a test system to observe the generation and evolution of contrail clouds of aircraft engines in an environmental chamber, effective contrail cloud research can be achieved, thereby facilitating the subsequent formulation of mitigation measures for contrail clouds and providing support for research on the impact of aviation emissions on the global climate.

[0022] Additional aspects and advantages of the invention will become apparent from the description which follows, or may be learned by practice of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the following description of the embodiments with reference to the accompanying drawings, in which:

[0024] Figure 1 Schematic diagram of the structure of the environmental chamber of some embodiments of the present invention.

[0025] Figure 2 1 is a front view of an environmental chamber according to some embodiments of the present invention.

[0026] Figure 3 Schematic diagram of the structure of the cabin assembly of some embodiments of the present invention.

[0027] Figure 4 Schematic diagram of the structure of the air intake assembly of some embodiments of the present invention.

[0028] Figure 5 Schematic diagram of the structure of the exhaust assembly of some embodiments of the present invention.

[0029] Figure 6 Schematic diagram of the structure of the dilution unit in some embodiments of the present invention.

[0030] Figure 7 sectional views of dilution units according to some embodiments of the present invention.

[0031] Figure 8 for Figure 7 Cross-sectional view along line BB.

[0032] Figure 9 A side view of an air intake assembly according to some embodiments of the present invention.

[0033] Figure 10 for Figure 9 Sectional view along line AA.

[0034] Figure 11 Schematic diagram of the structure of the injection unit of some embodiments of the present invention.

[0035] Figure 12 sectional views of injection units according to some embodiments of the present invention.

[0036] Figure 13 sectional views of injection units according to other embodiments of the present invention.

[0037] Figure 14 This is a schematic structural diagram of the air intake assembly from another angle according to some embodiments of the present invention.

[0038] Figure 15 Schematic diagram of the coordination of the intake pipe mounting plate and the fourth intake pipe according to some embodiments of the present invention.

[0039] Figure 16 This is a cross-sectional view of the intake pipe mounting plate and the fourth intake pipe when they are matched in some embodiments of the present invention.

[0040] Figure 17 This is a schematic structural diagram of the cabin assembly from another angle according to some embodiments of the present invention.

[0041] Figure 18Schematic diagram of the structure of the bracket assembly of some embodiments of the present invention.

[0042] Figure 19 Schematic diagram of the principle of a test device for studying contrail cloud generation and evolution according to some embodiments of the present invention.

[0043] Figure 20 Schematic diagram of the cooperation between the test system and the cabin assembly according to some embodiments of the present invention.

[0044] Figure 21 Schematic diagram of the principle of the second gas supply system in some embodiments of the present invention.

[0045] Figure 22 Schematic diagram of the principle of the third gas supply system in some embodiments of the present invention.

[0046] Figure 23 This is a schematic diagram of the principles of the cooperation between the installation cabin and the aircraft engine in some embodiments of the present invention.

[0047] Figure 24 This is a flow chart of a testing method for a testing device according to some embodiments of the present invention.

[0048] Figure 25 Flowchart of a testing method of a testing device according to some other embodiments of the present invention.

[0049] Reference numerals:

[0050] 1000. Test device for studying contrail cloud formation and evolution;

[0051] 100. Third gas supply system;

[0052] 110. Mixer;

[0053] 121, third gas supply path; 122, fourth gas supply path; 123, fifth gas supply path;

[0054] 130, air intake tower; 140, second filter; 150, second screw air compressor;

[0055] 160, heating machine; 170, second drying machine; 180, second refrigeration machine;

[0056] 210, installation cabin; 211, air intake cabin; 220, thrust tester; 230, air intake valve;

[0057] 240, first gas supply system;

[0058] 300, Environmental Chamber;

[0059] 310, cabin assembly;

[0060] 311, test chamber;

[0061] 312. Optical observation window panel;

[0062] 3121. Optical measurement window panel; 3122. Light source window panel;

[0063] 313, first mounting plate; 314, air intake pipe mounting plate; 315, bottom mounting plate;

[0064] 316. Guide rail plate; 317. First reinforcing rib;

[0065] 3181, sewage outlet; 3182, sampler interface; 3183, sensor interface;

[0066] 320, air intake assembly;

[0067] 321, dilution unit;

[0068] 3211, mixing tube; 3212, air inlet; 3213, air inlet channel; 3214, air outlet;

[0069] 3215, first air inlet pipe; 3216, pressure equalizing pipe; 3217, first pressure equalizing chamber;

[0070] 322, first air intake unit;

[0071] 3221, spray unit; 3222, nozzle; 3223, spray pipe; 3224, limit pipe;

[0072] 323. Second air intake unit; 3231. Second air intake pipe;

[0073] 324, connecting plate;

[0074] 3241, diversion structure; 3242, second diversion port;

[0075] 3243, first pressure equalizing plate; 3244, first diversion port; 3245, second pressure equalizing chamber;

[0076] 3246, second pressure equalizing plate; 3247, third air inlet pipe; 3248, third pressure equalizing chamber;

[0077] 325, transition pipe; 3261, fourth air inlet pipe; 3262, third pressure equalizing plate;

[0078] 3263, third diversion port; 3264, fourth pressure equalizing chamber;

[0079] 330, exhaust assembly;

[0080] 331, first flange; 332, variable-section transfer tube; 3322, second reinforcement rib;

[0081] 333, second flange;

[0082] 340, connecting flange;

[0083] 350, bracket assembly;

[0084] 3511, bracket body; 3512, support column; 3513, adjustment gasket; 3514, adjustment screw;

[0085] 400, second gas supply system;

[0086] 410, first refrigerator; 421, first gas supply line; 422, second gas supply line;

[0087] 430, first filter; 440, first screw air compressor; 450, transition tank;

[0088] 460, exhaust valve; 470, first dryer;

[0089] 500, exhaust system;

[0090] 510, vacuum pump assembly; 511, first vacuum pump; 512, second vacuum pump;

[0091] 520, heat exchanger; 530, cooler;

[0092] 900, test system;

[0093] 910, floating vibration isolation optical platform; 920, high-speed camera; 930, microscope; 940, light source;

[0094] 2000. Aircraft engines. DETAILED DESCRIPTION

[0095] The following describes embodiments of the present invention in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended only to explain the present invention and are not to be construed as limiting the present invention.

[0096] The following describes an environmental chamber 300 for studying contrail cloud formation and evolution according to an embodiment of the present invention with reference to the accompanying drawings.

[0097] like Figure 1 and Figure 2 As shown, an environmental chamber 300 for studying contrail cloud generation and evolution according to an embodiment of the present invention includes: a chamber assembly 310 , an air intake assembly 320 and an exhaust assembly 330 .

[0098] Among them, such as Figure 3As shown, a test chamber 311 is formed within the chamber assembly 310. The chamber assembly 310 is provided with an optical observation window panel 312 and a first mounting plate 313. The first mounting plate 313 is adapted to accommodate a sampler. The optical observation window panel 312 facilitates direct observation of the environment within the chamber 311, while the first mounting plate 313 provides a mounting location for the sampler, ensuring that the sampler can be mounted on the chamber assembly 310 for convenient sampling of the gas within the chamber 311.

[0099] In some specific examples, the optical observation window panel 312 can facilitate the optical testing system 900 outside the cabin assembly 310 to observe the generation and evolution process of the contrail cloud in the test cavity 311 in real time, so as to achieve the purpose of optically measuring the contrail cloud in the test cavity 311.

[0100] That is, the cabin assembly 310 of the present application provides an optical observation window panel 312 and a first mounting plate 313 on which a sampler can be installed, so as to meet the subsequent research requirements of optical measurement and sampling for the study of contrail cloud formation and evolution.

[0101] like Figure 1 and Figure 4 As shown, air intake assembly 320 includes a dilution unit 321, a first air intake unit 322, and a second air intake unit 323. Dilution unit 321 is used to receive exhaust and dilution gas from aircraft engine 2000 and mix the exhaust and dilution gases. This means that dilution unit 321 receives not only exhaust from aircraft engine 2000 but also dilution gas, and can mix the exhaust and dilution gases to achieve the purpose of diluting and cooling the high-temperature exhaust gas from aircraft engine 2000. This, in turn, simulates plume temperature, facilitating the subsequent simulation of contrail formation and evolution.

[0102] like Figure 4 As shown, the first air intake unit 322 is connected to the dilution unit 321. The first air intake unit 322 is used to receive the mixed gas from the dilution unit 321 and inject the mixed gas into the test chamber 311. Here, the dilution unit 321 can transport the mixed gas to the first air intake unit 322, and the first air intake unit 322 receives the exhaust gas from the dilution unit 321 and injects the exhaust gas into the test chamber 311. This simulates the plume state ejected from the tail nozzle of the aircraft engine 2000 during high-altitude flight, thereby facilitating the subsequent simulation of the formation and evolution of the contrail.

[0103] In some examples, the dilution unit 321 and the first air intake unit 322, as well as the first air intake unit 322 and the cabin assembly 310 are detachably connected via a connecting flange 340. This ensures the relative position stability between the dilution unit 321 and the first air intake unit 322, as well as the first air intake unit 322 and the cabin assembly 310, while also reducing the difficulty of assembling and disassembling the entire environmental chamber 300.

[0104] In summary, it can be understood here that the exhaust gas generated by the aircraft engine 2000 can be transmitted to the dilution unit 321, and the dilution unit 321 is used to receive the exhaust gas of the aircraft engine 2000 and dilute the received exhaust gas. After the dilution is completed, the dilution unit 321 then transmits the diluted exhaust gas to the first air intake unit 322. The first air intake unit 322 is used to receive the diluted exhaust gas and inject the exhaust gas into the test chamber 311, so as to simulate the generation of the aircraft contrail and facilitate the subsequent simulation of the evolution of the contrail cloud in the test chamber 311.

[0105] It should be noted that when high-temperature exhaust gas with a certain temperature and flow rate passes through the dilution unit 321 and into the test chamber 311 through the first air intake unit 322, the first air intake unit 322 can inject the exhaust plume of the real aircraft engine 2000 into the test chamber 311. This can more accurately simulate the real injection state of the aircraft engine 2000 during high-altitude flight and simulate a more realistic contrail cloud growth and evolution form, thereby improving the simulation precision and accuracy.

[0106] The second air inlet unit 323 is used to deliver low-temperature, high-humidity air toward the test chamber 311. This adjusts the temperature and humidity within the test chamber 311, making the environment within the test chamber 311 closer to that of a high-altitude environment. This simulates a high-altitude environment within the test chamber 311, facilitating subsequent simulations of the formation and evolution of aircraft contrails and research on contrails.

[0107] like Figure 1 and Figure 2 As shown, the exhaust assembly 330 is in communication with the test chamber 311 and is used to exhaust some of the gas in the test chamber 311. This creates a low-pressure environment in the test chamber 311, further making the environment in the test chamber 311 closer to a high-altitude environment, improving the accuracy of the generation and evolution of simulated aircraft contrails, and thus facilitating accurate contrails research.

[0108] That is to say, the present application sets up a first air intake unit 322 and an exhaust assembly 330. The first air intake unit 322 and the exhaust assembly 330 cooperate to form a low-temperature, low-pressure, and high-humidity environment in the test chamber 311, that is, the environmental parameters in the test chamber 311 meet the conditions for the generation of contrail clouds, which is convenient for simulating the evolution of persistent contrail clouds and improving the accuracy of the evolution.

[0109] In some specific examples, the environmental chamber 300 of the present application can simulate the temperature, humidity and pressure conditions corresponding to all altitude environmental conditions from sea level conditions to 12 km above sea level.

[0110] As can be seen from the above structure, the environmental chamber 300 for studying the formation and evolution of contrails according to an embodiment of the present invention is provided with a dilution unit 321 and a first air intake unit 322, and the dilution unit 321 is configured to receive the exhaust gas of the aircraft engine 2000. In this way, the exhaust gas generated by the aircraft engine 2000 during operation can enter the dilution unit 321, and the exhaust gas can be diluted by the dilution unit 321, and the diluted exhaust gas can be ejected through the first air intake unit 322 to facilitate the subsequent simulation of the formation and evolution of aircraft contrails.

[0111] By setting up a test chamber 311 in the environmental chamber 300, and setting up a first air intake unit 322 and an exhaust assembly 330 that cooperate with the test chamber 311, a low-temperature, low-pressure, and high-humidity environment can be formed in the test chamber 311. In this way, when the first air intake unit 322 sprays the diluted exhaust gas into the test chamber 311, the generation and evolution of aircraft contrails can be simulated in the test chamber 311, thereby realizing the simulation of the generation and evolution of aircraft contrails using the environmental chamber 300 of the present application.

[0112] In addition, the present application also sets an optical observation window panel 312 and a first mounting plate 313 on the cabin assembly 310 of the environmental cabin 300. The optical observation window panel 312 can facilitate intuitive observation of the contrail cloud in the test chamber 311, thereby facilitating optical measurement of the contrail cloud. The first mounting plate 313 can realize an external sampler, thereby facilitating the use of the sampler to sample the contrail cloud in the test chamber 311, facilitating subsequent research on the contrail cloud, that is, facilitating the subsequent formulation of mitigation measures for the contrail cloud, and providing support for research on the impact of aviation emissions on the global climate.

[0113] That is to say, the environmental chamber 300 of the present application can not only simulate the generation and evolution process of persistent contrail clouds by simulating real high-altitude cruising environmental conditions, but also facilitate sampling research and optical measurement of contrail clouds.

[0114] At the same time, it is also necessary to emphasize that the present application can realize optical measurement and sampling research of contrail clouds by setting up an environmental chamber 300, so as to obtain complete experimental data and improve the accuracy of the research. At the same time, it is not easily affected by environmental factors and limitations of experimental measurement equipment, thereby reducing research difficulty and saving research costs.

[0115] It can be understood that compared with the existing technology, the present application directly establishes an environmental chamber 300, and sets an optical observation window panel 312 and a first mounting plate 313 on which a sampler can be installed on the cabin assembly 310 of the environmental chamber 300, as well as an air intake assembly 320 and an exhaust assembly 330 that cooperate with the test cavity 311 of the cabin assembly 310. While realizing the simulation of the generation and evolution process of the contrail cloud, it is also convenient for sampling and studying the contrail cloud and performing optical measurements, thereby supporting subsequent research on the impact of aviation emissions on the global climate.

[0116] Optionally, the cabin assembly 310 is a square cylindrical structure, including an intermediate cylinder and connecting flanges 340 arranged on the front and rear sides of the intermediate cylinder. A test chamber 311 is formed in the intermediate cylinder, and the connecting flanges 340 on the front and rear sides are respectively connected to the air intake assembly 320 and the exhaust assembly 330 to realize the connection between the cabin assembly 310 and the air intake assembly 320 and the exhaust assembly 330, so as to facilitate the formation of a structurally stable environmental cabin 300. At the same time, it is also convenient to use the air intake assembly 320 to intake air into the cabin assembly 310, and to use the exhaust assembly 330 to extract part of the gas in the cabin assembly 310.

[0117] Alternatively, as Figure 3 As shown, the cabin assembly 310 is provided with a first reinforcing rib 317, which is arranged around the outer periphery of the cabin assembly 310 to ensure that the deformation of the cabin assembly 310 meets the requirements, thereby facilitating the simulation of a high-altitude, low-temperature, low-pressure, and high-humidity environment in the cabin assembly 310.

[0118] In some specific examples, the cabin assembly 310 is made of stainless steel with a wall thickness of 8 mm to further increase the structural strength of the cabin assembly 310 .

[0119] Optionally, the total length of the cabin assembly 310 is 2015 mm, so as to form a test cavity 311 of a certain length in the cabin assembly 310, thereby simulating the generation and evolution of contrail clouds and facilitating the study of contrail clouds.

[0120] It should be noted that the above-mentioned wall thickness of the cabin assembly 310 of 8 mm and the total length of the cabin assembly 310 of 2015 mm are only a specific example of the cabin assembly 310. In some other examples, the wall thickness of the cabin assembly 310 and the length of the cabin assembly 310 can also be set to other values, which are not specifically limited here.

[0121] In some examples, such as Figure 3As shown, a guide plate 316 is provided on the inner bottom wall of the cabin assembly 310. T-slots are machined into the guide plate 316 for mounting test pieces to expand the functionality of the cabin assembly 310. In other words, the cabin assembly 310 of the present application can not only simulate the formation and evolution of contrails, but can also be used to mount other structural components, such as aircraft engines 2000, to simulate the high-altitude environment of an aircraft.

[0122] Specifically, the guide rail plate 316 is an aluminum alloy plate with five T-slots processed along the axial direction of the guide rail plate 316 for installing test equipment. A handle is designed at the rear end of the guide rail plate 316 to facilitate installation and removal of the guide rail plate 316.

[0123] Optionally, a guide groove is provided on the guide rail plate 316, and a limit block cooperating with the guide groove is provided on the inner bottom wall of the cabin assembly 310, and the limit block is limited in the guide groove, so that the guide rail plate 316 can be pushed in from the rear end through the cooperation of the guide groove and the limit block to realize the setting of the guide rail plate 316 in the cabin assembly 310.

[0124] Optionally, the optical observation window panel 312 is formed as a double-layer vacuum glass structure. While ensuring that the contrail in the test cavity 311 can be effectively observed through the optical observation window panel 312, it can also prevent the outer surface of the optical observation window panel 312 from frosting due to the large temperature difference between the inside and the outside, thereby meeting the optical measurement requirements of the study of aircraft contrail formation and evolution.

[0125] In some examples, a first flange plate is provided on the cabin assembly 310 , and the optical observation window panel 312 is connected to the first flange plate by bolts, thereby providing the optical observation window panel 312 on the cabin assembly 310 .

[0126] Optionally, a sensor can also be installed on the first mounting plate 313. That is to say, the first mounting plate 313 of the present application not only provides an installation position for the sampler, but also provides an installation position for the sensor, thereby realizing the installation of the sensor on the cabin assembly 310, so as to facilitate the use of the sensor to detect the environment in the test cavity 311.

[0127] In some examples, the sensor is formed as a temperature, humidity and pressure sensor, which is used to monitor the temperature, humidity and pressure in the test chamber 311, so as to obtain the temperature, humidity and pressure in the test chamber 311 in real time, and facilitate the subsequent control of the temperature, humidity and pressure in the test chamber 311 to ensure that the environment in the test chamber 311 can always be formed into a low-temperature, low-pressure and high-humidity environment.

[0128] Optionally, the material of the first mounting plate 313 can be selected according to actual usage requirements, for example, the first mounting plate 313 can be set to an aluminum plate, an acrylic glass plate or a steel blind plate to ensure the structural strength of the first mounting plate 313.

[0129] Optionally, a second flange plate is provided on the cabin assembly 310, and the first mounting plate 313 is connected to the second flange plate by bolts, thereby setting the first mounting plate 313 on the cabin assembly 310, that is, setting the sampler and sensor on the cabin assembly 310.

[0130] Optionally, the outer dimensions and total thickness of the first mounting plate 313 are consistent with those of the optical observation window panel 312. In this way, the first flange plate and the second flange plate can be formed as the same structural member to reduce the manufacturing difficulty of the cabin assembly 310.

[0131] Alternatively, as Figure 4 As shown, the air intake assembly 320 further includes a transition duct 325, which is connected between the dilution unit 321 and the first air intake unit 322. Thus, after the dilution unit 321 mixes the exhaust gas and dilution gas from the aircraft engine 2000, the mixed gas first flows into the transition duct 325. At this time, the exhaust gas and dilution gas can be further mixed while flowing in the transition duct 325, thereby achieving sufficient dilution of the exhaust gas with the dilution gas. The exhaust gas then enters the first air intake unit 322 through the transition duct 325. Therefore, it can be understood that the provision of the transition duct 325 can better mix the exhaust gas and dilution gas from the aircraft engine 2000.

[0132] At the same time, the transition pipe 325 also provides an installation space for the detection component, which is convenient for the subsequent installation of the detection component between the dilution unit 321 and the first air intake unit 322 to facilitate the detection of the diluted exhaust gas.

[0133] Optionally, the dilution gas mentioned in this application may be nitrogen.

[0134] Alternatively, as Figure 5 As shown, the exhaust assembly 330 includes: a first flange 331, a variable-section transfer tube 332 and a second flange 333. The first flange 331 and the second flange 333 are respectively connected to the two ends of the variable-section transfer tube 332. The first flange 331 is connected to the cabin assembly 310 to connect the exhaust assembly 330 to the cabin assembly 310, so as to facilitate the use of the exhaust assembly 330 to discharge part of the gas in the test chamber 311.

[0135] Alternatively, as Figure 5As shown, the first flange 331 is formed as a square flange and the second flange 333 is formed as a circular flange, so that the shape of the first flange 331 can match the shape of the cabin assembly 310, and the shape of the second flange 333 can match the shape of the pipe connected to the second flange 333, so that the exhaust assembly 330 can be connected to the cabin assembly 310 and the exhaust assembly 330 can be connected to the exhaust system 500 below.

[0136] Optionally, the first flange 331 , the variable-section transfer tube 332 , and the second flange 333 are connected by welding to improve the structural stability of the exhaust assembly 330 .

[0137] Alternatively, as Figure 5 As shown, a second reinforcing rib 3322 is provided on the variable-section adapter tube 332, and the second reinforcing rib 3322 is arranged around the outer circumference of the variable-section adapter tube 332 to increase the structural strength of the variable-section adapter tube 332 and avoid deformation of the variable-section adapter tube 332 during use, thereby facilitating the extension of the service life of the exhaust component 330.

[0138] Specifically, the total length of the exhaust assembly 330 is 470 mm, and the wall thickness of the variable-section transfer tube 332 is 8 mm.

[0139] In some embodiments of the present invention, Figure 3 As shown, the optical observation window panel 312 includes multiple groups, and the multiple groups of optical observation window panels 312 are arranged along the length direction of the cabin assembly 310. The length direction mentioned here can be understood as Figure 1 The front-to-back directions shown in the figure facilitate optical measurement of the contrail clouds at different positions in the test chamber 311 using multiple sets of optical observation window panels 312 to further improve the accuracy of the research.

[0140] In the description of the present invention, unless otherwise specified, "multiple groups" means two or more groups.

[0141] Alternatively, as Figure 3 As shown, the optical observation window panel 312 includes an optical measurement window panel 3121 and a light source window panel 3122. Here, each optical observation window panel 312 includes an optical measurement window panel 3121 and a light source window panel 3122. The light source window panel 3122 facilitates the subsequent light source 940 located outside the cabin assembly 310 to transmit light into the test cavity 311, thereby improving the brightness within the test cavity 311. The optical measurement window panel 3121 facilitates the subsequent high-speed camera 920 located outside the cabin assembly 310 to visually observe the contrail in the test cavity 311, thereby facilitating optical measurement of the contrail.

[0142] That is, the present application sets up an optical observation window panel 312 composed of an optical measurement window panel 3121 and a light source window panel 3122 to improve the brightness in the test cavity 311, thereby facilitating the optical measurement of the contrail cloud in the test cavity 311 using the test system 900.

[0143] In summary, on the premise of realizing the simulation of aircraft contrails, the present application also provides an optical measurement window panel 3121 and a light source window panel 3122, as well as a first mounting plate 313 for mounting samplers and sensors, to meet the research requirements of optical measurement and sampling for the study of contrails generation and evolution.

[0144] In some specific examples, a set of optical observation window panels 312 includes an optical measurement window panel 3121 and two light source window panels 3122, such as Figure 3 As shown, an optical measurement window panel 3121 is arranged on the right side of the cabin assembly 310, and two light source window panels 3122 are respectively arranged on the upper side and the left side of the cabin assembly 310. The two light source window panels 3122 cooperate to maximize the brightness in the test cavity 311, thereby ensuring the clarity of the optical measurement.

[0145] Optionally, combined Figure 6 、 Figure 7 and Figure 8 As shown, the dilution unit 321 includes a mixing tube 3211, which is provided with an air inlet 3212, an air inlet channel 3213 and an air outlet 3214. The air inlet 3212, the air inlet channel 3213 and the air outlet 3214 are all connected to the inner and outer sides of the mixing tube 3211. The air inlet 3212 and the air outlet 3214 are arranged at the axial ends of the mixing tube 3211. The air inlet 3212 is connected to the aircraft engine 2000, and the air outlet 3214 is connected to the first air inlet unit 322. It can be understood here that the air inlet 3212 is used to ensure that the dilution unit 321 can smoothly receive the exhaust gas of the aircraft engine 2000, and ensure that the received exhaust gas of the aircraft engine 2000 can smoothly enter the mixing tube 3211, so as to facilitate the subsequent dilution of the exhaust gas of the aircraft engine 2000, and the air outlet 3214 is used to discharge the gas in the mixing tube 3211, so as to facilitate the subsequent simulation of the formation and evolution of the contrail cloud.

[0146] In some examples, combined Figure 6 and Figure 7 As shown, both ends of the mixing tube 3211 are provided with connecting flanges 340 to facilitate communication between the air inlet 3212 of the dilution unit 321 and the aircraft engine 2000 and communication between the air outlet 3214 of the dilution unit 321 and the first air inlet unit 322 .

[0147] Optionally, the mixing tube 3211 is formed as a steel tube to ensure the structural strength of the mixing tube 3211 and prevent the mixing tube 3211 from being deformed during use.

[0148] In some specific examples, the mixing tube 3211 has a wall thickness of 4 mm and a total length of 200 mm, to further ensure the structural strength of the mixing tube 3211 and to ensure that the mixing tube 3211 has a certain length, thereby facilitating mixing of the exhaust gas of the aircraft engine 2000 and the dilution gas in the mixing tube 3211 .

[0149] Optionally, combined Figure 7 and Figure 8 As shown, the air inlet channel 3213 is provided around the mixing tube 3211 and is used to deliver dilution gas toward the mixing tube 3211. This allows external dilution gas to be introduced into the mixing tube 3211, thereby facilitating dilution of the exhaust gas of the aircraft engine 2000 entering the mixing tube 3211.

[0150] That is to say, the mixing tube 3211 of the present application is respectively provided with an air inlet 3212 and an air inlet channel 3213. The air inlet 3212 is used to ensure that the exhaust gas generated by the aircraft engine 2000 can smoothly enter the mixing tube 3211, and the air inlet channel 3213 is used to ensure that the external dilution gas can smoothly enter the mixing tube 3211, so as to facilitate the dilution of the exhaust gas of the aircraft engine 2000 entering the mixing tube 3211, thereby facilitating the subsequent simulation of the generation and evolution of the contrail cloud.

[0151] Optionally, the air inlet passage 3213 includes multiple air inlet passages 3213, which are spaced apart along the axial direction of the mixing tube 3211. The multiple air inlet passages 3213 can increase the amount of dilution gas entering the mixing tube 3211, thereby diluting the exhaust gas of the aircraft engine 2000 with the dilution gas.

[0152] In some examples, such as Figure 8 As shown, the multiple air inlet channels 3213 are spaced apart along the circumference of the mixing tube 3211. That is, the multiple air inlet channels 3213 are not limited to being spaced apart along the axial direction of the mixing tube 3211, but may also be spaced apart along the circumference of the mixing tube 3211. This arrangement can also increase the amount of dilution gas entering the mixing tube 3211, thereby facilitating the use of the dilution gas to dilute the exhaust gas of the aircraft engine 2000.

[0153] In some other examples, the plurality of air inlet channels 3213 are spaced apart along the axial direction and the circumferential direction of the mixing tube 3211. This means that the plurality of air inlet channels 3213 are spaced apart not only along the axial direction of the mixing tube 3211 but also along the circumferential direction of the mixing tube 3211, so as to maximize the number of air inlet channels 3213, thereby increasing the amount of dilution gas entering the mixing tube 3211.

[0154] Alternatively, as Figure 8 As shown, the axis of the air inlet channel 3213 extends obliquely relative to the cross-sectional plane of the mixing tube 3211, and the cross-sectional plane is parallel to the front-to-back direction and the up-down direction of the mixing tube 3211. Figure 1 In the direction shown in the figure, by tilting and extending the axis of the air intake channel 3213 relative to the cross-sectional plane of the mixing tube 3211, the entire air intake channel 3213 can be tilted and extended, so that when the dilution gas is introduced into the mixing tube 3211 through the air intake channel 3213, the rotational flow of the dilution gas can be achieved, thereby ensuring that the diluted exhaust gas can be discharged in a rotational manner when discharged from the outlet 3214.

[0155] It can also be understood that the high-temperature exhaust gas with a certain temperature and flow rate can be introduced into the test chamber 311 through the first air intake unit 322 in the form of a rotating plume after passing through the mixing pipe 3211. This can more accurately simulate the actual injection state of the aircraft engine 2000 during high-altitude flight and simulate a more realistic contrail cloud growth and evolution form, which is more conducive to simulating the thermal fluid-solid coupling process of carbon soot and simulating the contrail cloud condensation and evolution process.

[0156] Alternatively, as Figure 8 As shown, the axes of the multiple air inlet channels 3213 are tilted in the same clockwise direction. This can be understood as the axes of the multiple air inlet channels 3213 being tilted in the clockwise direction or the axes of the multiple air inlet channels 3213 being tilted in the counterclockwise direction to ensure that the dilution gas entering through the multiple air inlet channels 3213 can rotate in the same direction, thereby simulating the plume rotational inertia.

[0157] Optionally, in some specific examples, the external dilution gas enters the mixing tube 3211 through the air inlet channel 3213 at an angle of 45 degrees, and then mixes with the exhaust gas in the mixing tube 3211 to form a rotating plume.

[0158] In some examples, the diameter of the inlet passage 3213 is 2 mm.

[0159] In summary, the present application utilizes dilution cooling to mix the exhaust gas to reduce the exhaust temperature and achieve a simulated plume temperature; utilizes the first air intake unit 322 to inject the diluted exhaust gas into the test chamber 311 to form an injection velocity; utilizes the inclined extended air intake channel 3213 to introduce the diluted gas into the mixing tube 3211 to achieve a simulated plume rotational inertia, thereby facilitating the subsequent accurate simulation of the formation and evolution process of the contrail cloud.

[0160] Optionally, combined Figure 6 、 Figure 7 and Figure 8 As shown, the dilution unit 321 includes a first air inlet pipe 3215 and a pressure equalizing pipe 3216. The extension directions of the first air inlet pipe 3215 and the pressure equalizing pipe 3216 are different. The pressure equalizing pipe 3216 is arranged on the mixing pipe 3211 and cooperates with the mixing pipe 3211 to define a first pressure equalizing chamber 3217. The first air inlet pipe 3215 is connected to the first pressure equalizing chamber 3217. The first air inlet pipe 3215 is used to transport the dilution gas toward the first pressure equalizing chamber 3217. The first pressure equalizing chamber 3217 is connected to multiple air inlet channels 3213. Through the above-mentioned arrangement, the external dilution gas can be introduced into the first pressure equalizing chamber 3217 between the pressure equalizing tube 3216 and the mixing tube 3211 through the first air inlet pipe 3215, and then the dilution gas can be introduced into the mixing tube 3211 through multiple air inlet channels 3213 connected to the first pressure equalizing chamber 3217, so as to achieve the purpose of transporting the dilution gas toward the mixing tube 3211, so as to facilitate the subsequent use of the dilution gas to cool and dilute the exhaust gas.

[0161] It should be noted that the present application sets a pressure equalizing tube 3216, and defines a first pressure equalizing chamber 3217 in cooperation between the pressure equalizing tube 3216 and the mixing tube 3211. The first pressure equalizing chamber 3217 can buffer and divert the dilution gas introduced from the first air inlet pipe 3215, so that the dilution gas can enter the mixing tube 3211 evenly through multiple air inlet channels 3213.

[0162] In some examples, the pressure equalizing tube 3216 is welded to the mixing tube 3211 to increase the connection strength between the pressure equalizing tube 3216 and the mixing tube 3211 , thereby stabilizing the relative positions of the pressure equalizing tube 3216 and the mixing tube 3211 and facilitating the formation of the first pressure equalizing chamber 3217 .

[0163] Optionally, the wall thickness of the pressure equalizing tube 3216 is 4 mm, ensuring that the pressure equalizing tube 3216 has a certain structural strength.

[0164] Optionally, combined Figure 1 、 Figure 4 and Figure 9As shown, the air intake assembly 320 includes a connecting plate 324, which is connected to the end of the cabin assembly 310. The first air intake unit 322 and the second air intake unit 323 are both provided on the connecting plate 324. It can be understood that the connection plate 324 not only realizes the connection between the air intake assembly 320 and the cabin assembly 310, but also supports the first air intake unit 322 and the second air intake unit 323 to improve the structural stability of the first air intake unit 322 and the second air intake unit 323.

[0165] Alternatively, as Figure 10 and Figure 11 As shown, the first air intake unit 322 includes an injection unit 3221, which includes a nozzle 3222 and an injection pipe 3223. The nozzle 3222 is used to receive the gas mixed by the dilution unit 321, and the opposite ends of the injection pipe 3223 are respectively connected to the nozzle 3222 and the test chamber 311. It can be understood here that the diluted exhaust gas from the dilution unit 321 is discharged into the nozzle 3222, and the nozzle 3222 then sprays the exhaust gas into the injection pipe 3223. The exhaust gas is then transported to the test chamber 311 through the injection pipe 3223. This achieves the purpose of using the first air intake unit 322 to inject the diluted exhaust gas into the test chamber 311, thereby facilitating the simulation of the formation and evolution of contrails in the test chamber 311.

[0166] The nozzle 3222 and the injection pipe 3223 cooperate to achieve a simulated plume injection velocity.

[0167] Alternatively, as Figure 10 and Figure 14 As shown, the injection pipe 3223 extends toward the test chamber 311 and into the test chamber 311 to achieve communication between the injection pipe 3223 and the test chamber 311 , thereby facilitating the delivery of diluted exhaust gas into the test chamber 311 through the injection pipe 3223 .

[0168] It should be noted that the sum of the gas delivery volume of the injection pipe 3223 toward the test chamber 311 and the gas delivery volume of the second air inlet unit 323 toward the test chamber 311 should be close to the total discharge volume of the test chamber 311, and the fluctuation range should not exceed 5%, so that the low pressure and low temperature in the test chamber 311 are stable.

[0169] In a specific example, such as Figure 10 As shown, a limiting tube 3224 is provided on the connecting plate 324 , and the spray unit 3221 is detachably arranged in the limiting tube 3224 , so as to utilize the limiting tube 3224 to support and limit the spray unit 3221 , thereby improving the position stability of the spray unit 3221 .

[0170] Optionally, the limiting tube 3224 is welded to the connecting plate 324 to improve the structural stability of the connecting plate 324 .

[0171] It should be noted that, by detachably arranging the spray unit 3221 in the limiting tube 3224, the difficulty of disassembling the spray unit 3221 can be reduced, thereby facilitating replacement of different types of spray units 3221 to simulate aircraft contrails.

[0172] in, Figure 12 and Figure 13 Two different types of spray units 3221 are shown.

[0173] Specifically, different models of the spray unit 3221 have different corresponding openings of the nozzles 3222 and inner diameters of the spray pipe 3223 . For example, the inner diameter of the spray pipe 3223 can be formed to be 10 mm, 20 mm, 30 mm, 40 mm, etc.

[0174] Optionally, combined Figure 1 、 Figure 5 and Figure 14 As shown, a first pressure equalizing plate 3243 is provided on one side of the connecting plate 324 close to the test chamber 311. The first pressure equalizing plate 3243 cooperates with the connecting plate 324 to define a second pressure equalizing chamber 3245 (the specific structure of the second pressure equalizing chamber 3245 can be found in Figure 10 ), the first pressure equalizing plate 3243 is provided with a plurality of first diversion ports 3244 communicating with the second pressure equalizing chamber 3245, and the second air inlet unit 323 includes a plurality of second air inlet pipes 3231, which are spaced apart on the connecting plate 324 and communicate with the second pressure equalizing chamber 3245. Thus, when the second air inlet unit 323 delivers low-temperature, high-humidity gas toward the test chamber 311, the low-temperature, high-humidity gas can be first delivered to the second pressure equalizing chamber 3245 through the plurality of second air inlet pipes 3231. The second pressure equalizing chamber 3245 is used to collect and buffer the introduced low-temperature, high-humidity gas, and then the buffered low-temperature, high-humidity gas is diverted into the test chamber 311 through the plurality of first diversion ports 3244, thereby reducing the impact of the low-temperature, high-humidity gas on the high-temperature gas flow field, the atmospheric flow field within the test chamber 311, and the growth and evolution of the contrail cloud, while maintaining the low-temperature, high-humidity environment of the test chamber 311.

[0175] Optionally, the first pressure balancing plate 3243 is welded to the connecting plate 324 to improve the position stability of the first pressure balancing plate 3243 .

[0176] In some specific examples, the distance between the first pressure equalizing plate 3243 and the connecting plate 324 is 5 mm, and the diameter of the first diversion port 3244 is 20 mm, so as to improve the uniformity of the low-temperature and high-humidity gas entering the test chamber 311 .

[0177] Optionally, the plurality of second air inlet pipes 3231 are welded to the connecting plate 324 at intervals to improve the position stability of the plurality of second air inlet pipes 3231 .

[0178] Specifically, if Figure 4 As shown, the second air intake unit 323 includes four second air intake pipes 3231 , which are spaced apart at the four corners of the connecting plate 324 . The four second air intake pipes 3231 and the first pressure equalizing plate 3243 cooperate to achieve uniform air intake toward the test chamber 311 .

[0179] Optionally, combined Figure 4 and Figure 14 As shown, the connecting plate 324 is provided with a second pressure balancing plate 3246, a third air inlet pipe 3247 and a diversion structure 3241. The third air inlet pipe 3247 is connected to the second pressure balancing plate 3246. The diversion structure 3241 includes a plurality of second diversion ports 3242. The second diversion ports 3242 pass through the connecting plate 324. The second pressure balancing plate 3246 is provided on the side of the connecting plate 324 away from the test chamber 311 and cooperates with the connecting plate 324 to define a third pressure balancing chamber 3248 (the specific structure of the third pressure balancing chamber 3248 can be seen in FIG. Figure 10 ), the third pressure equalizing chamber 3248 covers the diversion structure 3241, and the third air inlet pipe 3247 is used to transport gas toward the third pressure equalizing chamber 3248.

[0180] It can be understood here that a through second diversion port 3242 is provided on the connecting plate 324 to achieve communication between the two opposite sides of the connecting plate 324, and a second pressure equalizing plate 3246 is provided on one side of the connecting plate 324. Part of the structure of the second pressure equalizing plate 3246 is spaced apart from the connecting plate 324 to define a third pressure equalizing chamber 3248 between the second pressure equalizing plate 3246 and the connecting plate 324, and the third pressure equalizing chamber 3248 covers the diversion structure 3241 to achieve communication between the third pressure equalizing chamber 3248 and the plurality of second diversion ports 3242, so that when the third air inlet pipe 3247 is directed toward the first When the three pressure-equalizing chambers 3248 are delivering gas, the gas entering the third pressure-equalizing chamber 3248 can enter the test chamber 311 through the plurality of second diversion ports 3242, thereby delivering gas toward the test chamber 311. The gas here can act on the surfaces of the optical measurement window panel 3121 and the light source window panel 3122 to form an air film, thereby preventing frost on the optical measurement window panel 3121 and the light source window panel 3122, thereby facilitating optical measurement of the contrail cloud within the test chamber 311 using the optical measurement window panel 3121 and the light source window panel 3122. The gas mentioned here can be understood to be nitrogen.

[0181] Alternatively, as Figure 14As shown, a multi-component flow structure 3241 is provided on the connecting plate 324, and is arranged around the first pressure equalizing plate 3243. It can also be understood that the multi-component flow structure 3241 is disposed near the sidewall of the connecting plate 324. Thus, when nitrogen enters the test chamber 311 through the multi-component flow structure 3241, the nitrogen can act on the surfaces of the optical measurement window panel 3121 and the light source window panel 3122 to form an air film.

[0182] That is to say, the present application not only sets an optical measurement window panel 3121 and a light source window panel 3122 on the cabin assembly 310, but also sets a second pressure equalizing plate 3246, a third air intake pipe 3247 and a diversion structure 3241 that cooperate with the optical measurement window panel 3121 and the light source window panel 3122 to avoid frosting on the optical measurement window panel 3121 and the light source window panel 3122, thereby ensuring the clarity of the optical measurement window panel 3121 and the light source window panel 3122.

[0183] It should be noted that when the connecting plate 324 is provided with a multi-component flow structure 3241, as shown in FIG. Figure 4 As shown, the connecting plate 324 is also provided with a plurality of second pressure equalizing plates 3246 and third air inlet pipes 3247 that cooperate with the multi-component flow structure 3241 to prevent the optical measurement window panel 3121 and the light source window panel 3122 located on different side walls of the cabin assembly 310 from frosting.

[0184] In some specific examples, when the connection plate 324 is provided with three groups of diversion structures 3241, such as Figure 4 As shown, the connecting plate 324 is also provided with three second pressure equalizing plates 3246 and a third air inlet pipe 3247 that cooperate with the multi-component flow structure 3241. The three second pressure equalizing plates 3246 are respectively located at the upper, left and right positions of the connecting plate 324 to enable the introduced nitrogen to act on the optical measurement window panel 3121 and the light source window panel 3122 on different side walls of the cabin assembly 310.

[0185] Alternatively, as Figure 3As shown, the cabin assembly 310 is also provided with an air inlet pipe mounting plate 314, which is arranged between multiple groups of optical observation window panels 312. The air inlet pipe mounting plate 314 is provided with a fourth air inlet pipe 3261, which is used to transport gas toward the test chamber 311. It can be understood that the air inlet pipe mounting plate 314 is provided with a fourth air inlet pipe 3261 that can transport gas toward the test chamber 311, and the air inlet pipe mounting plate 314 is arranged between multiple groups of optical observation window panels 312, that is, the fourth air inlet pipe 3261 is arranged between multiple groups of optical observation window panels 312, so that the fourth air inlet pipe 3261 can be arranged close to the rear end of the cabin assembly 310, so as to utilize the fourth air inlet pipe 3261 to transport gas to the optical measurement window panel 3121 and the light source window panel 3122 near the rear end of the cabin assembly 310, thereby avoiding frosting of the optical measurement window panel 3121 and the light source window panel 3122 at the rear end of the cabin assembly 310, thereby reducing the possibility of frosting of all optical measurement window panels 3121 and light source window panels 3122 on the cabin assembly 310.

[0186] Optionally, the gas mentioned here can also be understood as nitrogen.

[0187] It should be noted that the above-mentioned intake pipe mounting plate 314 is arranged between multiple groups of optical observation window panels 312, which can be understood as, when the optical observation window panels 312 include two groups, one group of optical observation window panels 312 is arranged on both sides of the intake pipe mounting plate 314; when the optical observation window panels 312 include three groups, one group of optical observation window panels 312 is arranged on one side of the intake pipe mounting plate 314, and two groups of optical observation window panels 312 are arranged on the other side of the intake pipe mounting plate 314; when the optical observation window panels 312 include four groups, two groups of optical observation window panels 312 are arranged on both sides of the intake pipe mounting plate 314, and so on.

[0188] In some examples, combined Figure 15 and Figure 16 As shown, a third pressure equalizing plate 3262 is provided on the side of the intake pipe mounting plate 314 away from the fourth intake pipe 3261, and a plurality of third diversion ports 3263 are provided on the third pressure equalizing plate 3262, and a fourth pressure equalizing chamber 3264 is formed between the third pressure equalizing plate 3262 and the intake pipe mounting plate 314 to realize the diversion of the gas entering the rear end of the test chamber 311, so that the gas can enter the test chamber 311 evenly.

[0189] Optionally, multiple third diversion ports 3263 are arranged on the rear side wall of the third pressure equalizing plate 3262, so that when the air intake pipe mounting plate 314 is installed in place, the multiple third diversion ports 3263 can be arranged directly facing the rear end of the test chamber 311, thereby facilitating the delivery of nitrogen to the optical measurement window panel 3121 and the light source window panel 3122 near the rear end of the cabin assembly 310.

[0190] Optionally, the material of the intake pipe mounting plate 314 can also be selected according to actual usage requirements, for example: the intake pipe mounting plate 314 can be set to an aluminum plate, an acrylic glass plate or a steel blind plate, etc. to ensure the structural strength of the intake pipe mounting plate 314.

[0191] It should also be noted that the amount of nitrogen delivered into the test chamber 311 through the third air inlet pipe 3247 and the fourth air inlet pipe 3261 in the present application is negligible compared to the amount of low-temperature and high-humidity gas in the test chamber 311. Therefore, the present application can deliver nitrogen into the test chamber 311 without affecting the environment in the test chamber 311, thereby enabling the test chamber 311 to maintain a low-temperature, low-pressure, and high-humidity environment.

[0192] Alternatively, as Figure 17 As shown, a sampler interface 3182 and a sensor interface 3183 are provided at the bottom of the cabin assembly 310. The sampler interface 3182 is used to connect an external sampler to sample the contrail cloud in the test cavity 311 using the sampler, and the sensor interface 3183 is used to connect an external sensor to detect the environment in the test cavity 311 using the sensor.

[0193] That is to say, the present application not only connects external samplers and sensors to the left and right upper side walls of the cabin assembly 310, but also connects external samplers and sensors to the bottom wall of the cabin assembly 310, so as to achieve sampling of multiple contrails in the test chamber 311 and detection of multiple environments in the test chamber 311.

[0194] Alternatively, as Figure 17 As shown, a sewage outlet 3181 is further provided at the bottom of the cabin assembly 310 , and the sewage outlet 3181 is used to discharge foreign matter in the test cavity 311 when the test cavity 311 is not working.

[0195] Optionally, when the test chamber 311 is working, a blocking piece is provided at the sewage outlet 3181 to block the sewage outlet 3181 , so as to maintain a low temperature, low pressure and high humidity environment in the test chamber 311 .

[0196] It should be noted that when the sampler interface 3182, the sensor interface 3183 and the sewage outlet 3181 are provided at the bottom of the cabin assembly 310, corresponding openings are provided on the guide rail plate 316 so that the sampler interface 3182, the sensor interface 3183 and the sewage outlet 3181 can all achieve communication between the inside and outside of the cabin assembly 310.

[0197] Optionally, combined Figure 1 、 Figure 2 and Figure 18 As shown, the environmental chamber 300 further includes a bracket assembly 350 , which is disposed at the bottom of the chamber assembly 310 to support the chamber assembly 310 , improve the position stability of the chamber assembly 310 , and facilitate adjustment of the position of the chamber assembly 310 .

[0198] In some examples, such as Figure 3 and Figure 17 As shown, a bottom mounting plate 315 is provided at the bottom of the cabin assembly 310, and the cabin assembly 310 is mounted on the bracket assembly 350 through the bottom mounting plate 315 to achieve a fixed connection between the cabin assembly 310 and the bracket assembly 350, making it convenient to use the bracket assembly 350 to support the cabin assembly 310.

[0199] Alternatively, as Figure 17 As shown, a plurality of bottom mounting plates 315 are provided at the bottom of the cabin assembly 310 to increase the contact area between the cabin assembly 310 and the bracket assembly 350, thereby increasing the connection strength between the cabin assembly 310 and the bracket assembly 350, so that the relative positions of the cabin assembly 310 and the bracket assembly 350 are stable.

[0200] Alternatively, as Figure 18 As shown, the bracket assembly 350 includes a bracket body 3511, a support column 3512, an adjustment gasket 3513 and an adjustment screw 3514, wherein the support column 3512 and the adjustment gasket 3513 are used together to adjust the position of the cabin assembly 310 in the up and down directions, and the adjustment screw 3514 is used to adjust the position of the cabin assembly 310 in the left and right directions.

[0201] In a specific example, when it is necessary to adjust the position of the cabin assembly 310 in the up and down directions, the adjustment gasket 3513 is added or removed between the bracket body 3511 and the support column 3512 to achieve the position of the cabin assembly 310 in the up and down directions; when it is necessary to adjust the position of the cabin assembly 310 in the left and right directions, the adjustment screw 3514 is rotated, and the adjustment screw 3514 drives the support column 3512 and the adjustment gasket 3513 to move along the left and right directions to achieve the adjustment of the position of the cabin assembly 310 in the left and right directions.

[0202] Of course, multiple drive motors can also be set on the bracket body 3511. Some drive motors can drive the support column 3512 to move up and down to adjust the position of the cabin assembly 310 in the up and down directions; some drive motors can drive the support column 3512 to move left and right to adjust the position of the cabin assembly 310 in the left and right directions, thereby automatically adjusting the position of the cabin assembly 310 and improving the adjustment accuracy.

[0203] Optionally, a heat insulation plate is provided on the bracket body 3511, and the heat insulation plate is provided between the cabin assembly 310 and the bracket body 3511 to prevent the low temperature in the cabin assembly 310 from being transferred to the bracket body 3511 and causing the bracket body 3511 to freeze, thereby ensuring the service life of the bracket body 3511.

[0204] The following describes a test device 1000 for studying contrail cloud generation and evolution according to an embodiment of the present invention with reference to the accompanying drawings.

[0205] like Figure 19 and Figure 20 As shown, a test device 1000 for studying contrail cloud generation and evolution according to an embodiment of the present invention includes: an environmental chamber 300, a test system 900, an installation chamber 210, a first air supply system 240, a second air supply system 400 and an air extraction system 500.

[0206] The environmental chamber 300 is the aforementioned environmental chamber 300 provided with the optical measurement window panel 3121 and the light source window panel 3122 , and the specific structure of the environmental chamber 300 is not described in detail here.

[0207] like Figure 20 As shown, the testing system 900 includes an air-floating vibration-isolated optical platform 910, a high-speed camera 920, a microscope 930, and a light source 940. The high-speed camera 920 and microscope 930 are located on the air-floating vibration-isolated optical platform 910. The microscope 930 is located between the high-speed camera 920 and the optical measurement window panel 3121. The light source 940 faces the light source window panel 3122. In this way, the light source 940 can enhance the brightness within the test chamber 311 through the light source window panel 3122. The high-speed camera 920 and microscope 930 cooperate to detect contrails within the test chamber 311. The air-floating vibration-isolated optical platform 910 is used to enhance the positional stability of the high-speed camera 920 and microscope 930.

[0208] like Figure 23As shown, an aircraft engine 2000 to be tested is installed in an installation cabin 210. Aircraft engine 2000 and a first air supply system 240 are both connected to a dilution unit 321. First air supply system 240 is used to deliver dilution gas to dilution unit 321. This means that the exhaust gas from aircraft engine 2000 enters dilution unit 321, and the dilution gas also enters dilution unit 321 simultaneously, allowing the dilution gas to mix with the exhaust gas, thereby reducing the exhaust temperature and facilitating subsequent simulation of the formation and evolution of contrails.

[0209] The second gas supply system 400 is connected to the second gas inlet unit 323 and is used to deliver low-temperature, high-humidity gas toward the second gas inlet unit 323. In other words, the low-temperature, high-humidity gas delivered by the second gas inlet unit 323 toward the test chamber 311 is provided by the second gas supply system 400.

[0210] The exhaust system 500 is in communication with the exhaust assembly 330 , and is used to extract gas from the test chamber 311 through the exhaust assembly 330 to achieve a low-pressure environment in the test chamber 311 .

[0211] As can be seen from the above structure, the test device 1000 for studying the formation and evolution of contrail clouds in an embodiment of the present invention, by adopting the aforementioned environmental chamber 300 provided with an optical measurement window panel 3121 and a light source window panel 3122, can realize optical measurement of the contrail clouds in the environmental chamber 300 using the test device 900, thereby realizing the study of the contrail clouds and reducing the research cost.

[0212] Optionally, the natural frequency of the air-floating vibration-isolating optical platform 910 is less than 1.5-2.5 Hz, so as to ensure that the air-floating vibration-isolating optical platform 910 can effectively support the high-speed camera 920 and the microscope 930, improve the stability of the high-speed camera 920 and the microscope 930, and avoid shaking.

[0213] Alternatively, as Figure 21As shown, the second gas supply system 400 includes a first refrigerator 410, a first gas supply path 421 and a second gas supply path 422. The first gas supply path 421 and the second gas supply path 422 are arranged in parallel. The first gas supply path 421 is suitable for conveying low-humidity gas toward the first refrigerator 410, and the second gas supply path 422 is suitable for conveying high-humidity gas toward the first refrigerator 410. The first refrigerator 410 mixes the received gas and reduces the gas temperature. The first refrigerator 410 is used to convey the low-temperature gas to the second air intake unit 323. That is to say, the humidity of the gas transported by the first gas supply path 421 and the second gas supply path 422 is different. In this way, when the first gas supply path 421 and the second gas supply path 422 are used to cooperate to transport gas toward the second air inlet unit 323, the humidity of the gas can be effectively adjusted to achieve the purpose of transporting high-humidity gas toward the second air inlet unit 323 by using the second gas supply system 400, that is, to achieve the purpose of transporting high-humidity gas toward the test chamber 311. At the same time, the first refrigerator 410 is used to cool the mixed gas of the first gas supply path 421 and the second gas supply path 422 to achieve the purpose of cooling the gas. In this way, low-temperature gas can be transported toward the test chamber 311, thereby achieving the purpose of transporting low-temperature and high-humidity gas toward the test chamber 311 by using the second gas supply system 400, which is convenient for simulating the high-altitude environment in the test chamber 311.

[0214] In some examples, such as Figure 21 As shown, a first dryer 470 is provided on the first air supply path 421 and the dew point of the air supply path is low, and a first dryer 470 is provided on the second air supply path 422 and the dew point of the air supply path is higher. The first dryer 470 dries the gas flowing through it to adjust the humidity of the gas, thereby controlling the first air supply path 421 to deliver low-humidity gas toward the first refrigerator 410 and controlling the second air supply path 422 to deliver high-humidity gas toward the first refrigerator 410.

[0215] Alternatively, as Figure 21 As shown, the second air supply system 400 further includes a first filter 430, a first screw air compressor 440, and a transition tank 450. The first filter 430, the first screw air compressor 440, and the transition tank 450 are arranged in sequence along the flow direction of the gas, and the first filter 430 is connected to the external air and the first screw air compressor 440, respectively. In this way, the first filter 430 can lead the external fresh air into the first screw air compressor 440 and filter out impurities in the external fresh air during the introduction process to improve the cleanliness of the introduced air. The first screw air compressor 440 is connected to the transition tank 450 to realize the delivery of the received gas to the transition tank 450. Among them, the first screw air compressor 440 is used to compress the air to increase the amount of gas subsequently entering the transition tank 450. The transition tank 450 is used to store the gas and play a role in stabilizing the pressure to improve the stability of the subsequent gas flow.

[0216] In some examples, the first filter 430 and the first screw air compressor 440 , and the first screw air compressor 440 and the transition tank 450 are both connected through pipelines to ensure that the gas can flow normally.

[0217] Alternatively, as Figure 21 As shown, the transition tank 450 is connected to the first gas supply path 421 and the second gas supply path 422, so that the gas stored in the transition tank 450 can be smoothly transported to the first gas supply path 421 and the second gas supply path 422, so as to facilitate the subsequent use of the first gas supply path 421 and the second gas supply path 422 to adjust the humidity of the gas and the use of the first refrigerator 410 to adjust the temperature of the gas, so as to realize the delivery of low-temperature and high-humidity gas toward the test chamber 311.

[0218] In some examples, such as Figure 21 As shown, an exhaust valve 460 is also provided between the transition tank 450 and the first gas supply line 421 and the second gas supply line 422. The exhaust valve 460 is used to discharge part of the gas that is about to enter the first gas supply line 421 and the second gas supply line 422 to avoid damage to the first gas supply line 421 and the second gas supply line 422 due to excessive gas flow and pressure, as well as damage to the pipelines between the transition tank 450 and the first gas supply line 421 and the second gas supply line 422, thereby extending the service life of the second gas supply system 400.

[0219] In some examples, such as Figure 19 As shown, the test apparatus 1000 for studying contrail formation and evolution further includes a third air supply system 100, which is adapted to deliver cryogenic gas toward the aircraft engine 2000. This system enables the normal operation of the aircraft engine 2000 and simulates the high-altitude operation of the aircraft engine 2000, thereby facilitating subsequent simulation of the formation and evolution of contrail clouds generated by the exhaust of the aircraft engine 2000.

[0220] In some embodiments of the present invention, Figure 22As shown, the third gas supply system 100 includes a mixer 110, a third gas supply line 121, a fourth gas supply line 122, and a fifth gas supply line 123. The third gas supply line 121, the fourth gas supply line 122, and the fifth gas supply line 123 are all in communication with the mixer 110. The third gas supply line 121 is adapted to deliver ambient temperature gas to the mixer 110, the fourth gas supply line 122 is adapted to deliver high temperature gas to the mixer 110, and the fifth gas supply line 123 is adapted to deliver low temperature gas to the mixer 110. The mixer 110 mixes the gases and delivers them to the aircraft engine 2000. In other words, the gases delivered by the third gas supply line 121, the fourth gas supply line 122, and the fifth gas supply line 123 all have different temperatures. The provision of the fifth gas supply line 123, which delivers low temperature gas, allows the fifth gas supply line 123 to deliver low temperature gas to the aircraft engine 2000, thereby achieving the purpose of delivering low temperature gas to the aircraft engine 2000 using the third gas supply system 100.

[0221] In addition, by setting up a third air supply path 121 for conveying normal temperature gas and a fourth air supply path 122 for conveying high temperature gas, the gas temperature in the mixer 110 can be adjusted so that the temperature of the gas entering the aircraft engine 2000 meets the required temperature requirements of the aircraft engine 2000, thereby facilitating high-altitude simulation of the environment in which the aircraft engine 2000 is located; at the same time, the coordinated adjustment of the third air supply path 121, the fourth air supply path 122 and the fifth air supply path 123 can improve the efficiency of temperature regulation.

[0222] Alternatively, as Figure 22As shown, the third air supply path 121 is provided with an air intake tower 130 and a second filter 140 which are sequentially arranged and connected along the flow direction of the gas. The air intake tower 130 is used to introduce external normal temperature gas into the third air supply path 121. When the external normal temperature gas flows along the extension direction of the third air supply path 121, the normal temperature gas first flows to the second filter 140. The second filter 140 is used to filter impurities in the gas to ensure the cleanliness of the gas; the fourth air supply path 122 is provided with an air intake tower 130, a second filter 140, a second screw air compressor 150 and a heater 160 which are sequentially arranged and connected along the flow direction of the gas. The air intake tower 130 is used to introduce external normal temperature gas into the fourth air supply path 122. When the external normal temperature gas flows along the extension direction of the fourth air supply path 122, the normal temperature gas first flows to the second filter 140. The second filter 140 is used to filter impurities in the gas to ensure the cleanliness of the gas, and then The air flows through the second screw air compressor 150 and the heater 160. The heater 160 is used to heat the air to increase the gas temperature and ensure that the fourth air supply path 122 can transport high-temperature gas. The fifth air supply path 123 is provided with an air intake tower 130, a second dryer 170, a second filter 140, a second screw air compressor 150 and a second refrigerator 180, which are arranged in sequence and connected along the flow direction of the gas. The air intake tower 130 is used to introduce external normal-temperature gas into the fifth air supply path 123. When the external normal-temperature gas flows along the extension direction of the fifth air supply path 123, the normal-temperature gas first flows to the second dryer 170. The second dryer 170 is used to remove moisture from the gas to achieve the purpose of drying the gas. Subsequently, the gas flows through the second filter 140, the second screw air compressor 150 and the second refrigerator 180 in sequence. The second refrigerator 180 is used to reduce the air temperature to ensure that the fifth air supply path 123 can transport low-temperature gas.

[0223] Optionally, the heater 160 must meet the temperature requirements of the corresponding flow air of the aircraft engine 2000 at various altitudes and operating conditions, and its maximum heating capacity must be able to keep the maximum intake air temperature at no less than 300K.

[0224] In some examples, the second dryer 170 can remove 99% of the moisture in the gas, preventing the moisture in the air on the fifth air supply path 123 from condensing into water droplets in the second screw air compressor 150 and condensing into ice crystals in the second refrigerator 180, thereby ensuring that the second screw air compressor 150 and the second refrigerator 180 can operate normally.

[0225] Optionally, the second refrigerator 180 must meet the condensation requirements of the corresponding air flow of the aircraft engine 2000 at various altitudes and operating conditions, and its maximum condensation capacity must be able to keep the minimum intake air temperature continuously below 230K.

[0226] Alternatively, as Figure 23As shown, the installation cabin 210 includes an air intake cabin 211, which is connected to the third air supply system 100 and the aircraft engine 2000 at the same time, so that the third air supply system 100 can transport the low-temperature gas to the air intake cabin 211, and then use the air intake cabin 211 to transport the low-temperature gas to the aircraft engine 2000, so as to achieve the purpose of using the third air supply system 100 to transport low-temperature gas to the aircraft engine 2000.

[0227] In some embodiments of the present invention, Figure 23 As shown, the high-altitude simulation system 200 further includes a thrust tester 220 and an air inlet valve 230. The thrust tester 220 is located in the installation cabin 210 and is used to measure the thrust of the aircraft engine 2000. This facilitates subsequent testing during the experiment to determine whether the thrust parameters of the aircraft engine 2000 are normal.

[0228] Alternatively, as Figure 23 As shown, the installation cabin 210 is provided with an air intake valve 230 for intake of air into the installation cabin 210. This ensures that there is always a certain amount of gas in the installation cabin 210 to avoid a vacuum state in the installation cabin 210, thereby maintaining the low temperature environment of the aircraft engine 2000 at high altitude.

[0229] Optionally, the air extraction system 500 is connected to the installation cabin 210 and the aircraft engine 2000, respectively, and is used to extract gas from the installation cabin 210 and the aircraft engine 2000. In other words, the air extraction system 500 is used not only to extract gas from the test chamber 311, but also to extract gas from the installation cabin 210 and exhaust gas from the aircraft engine 2000. When the air extraction system 500 is used to extract gas from the installation cabin 210, part of the gas in the installation cabin 210 can be discharged to form a low-pressure environment in the installation cabin 210, thereby simulating a high-altitude environment. When the air extraction system 500 is used to extract gas from the aircraft engine 2000, part of the exhaust gas generated by the aircraft engine 2000 during operation can be discharged to ensure the normal operation of the aircraft engine 2000.

[0230] Alternatively, as Figure 19As shown, the exhaust system 500 includes a vacuum pump assembly 510, which is respectively connected to the installation cabin 210, the test chamber 311, and the aircraft engine 2000. The vacuum pump assembly 510 includes a first vacuum pump 511 and a second vacuum pump 512 arranged in parallel. It can be understood here that the exhaust system 500 extracts gas from the installation cabin 210, the test chamber 311, and the aircraft engine 2000 mainly through the vacuum pump assembly 510, thereby ensuring that the gas in the third air supply system 100, the installation cabin 210, the test chamber 311, the aircraft engine 2000, and the second air supply system 400 can be smoothly discharged, and realizing the formation of a low-pressure environment in the installation cabin 210 and the test chamber 311.

[0231] In addition, the present application configures the vacuum pump assembly 510 to be composed of a first vacuum pump 511 and a second vacuum pump 512 connected in parallel, so that the first vacuum pump 511 and the second vacuum pump 512 can be used to cooperate with each other to adjust and compensate for the pressure of the exhaust system 500 and improve the exhaust capacity of the exhaust system 500.

[0232] Alternatively, as Figure 19 As shown, the exhaust system 500 further includes a heat exchanger 520 and a cooler 530. The heat exchanger 520 is disposed between the vacuum pump assembly 510 and the test chamber 311, and the cooler 530 is disposed between the vacuum pump assembly 510 and the aircraft engine 2000. The heat exchanger 520 is used to increase the temperature of the gas entering the vacuum pump assembly 510 to prevent the low-temperature gas in the test chamber 311 from damaging the vacuum pump assembly 510. The cooler 530 is used to reduce the temperature of the gas entering the vacuum pump assembly 510 to prevent the high-temperature gas exhausted from the aircraft engine 2000 from damaging the vacuum pump assembly 510, thereby extending the service life of the vacuum pump assembly 510.

[0233] In some examples, the heat exchanger 520 should be able to increase the exhaust temperature entering the vacuum pump assembly 510 to above 25°C at any operating flow rate; the cooler 530 should be able to reduce the exhaust temperature entering the vacuum pump assembly 510 to below 150°C at any operating flow rate.

[0234] The following describes a testing method of the testing device 1000 for studying contrail cloud generation and evolution according to an embodiment of the present invention with reference to the accompanying drawings.

[0235] like Figure 24 As shown, a testing method of a testing device 1000 for studying contrail cloud generation and evolution according to an embodiment of the present invention includes the following steps:

[0236] S1. Place the aircraft engine 2000 in the installation cabin 210.

[0237] S2. Start the aircraft engine 2000 under the ground air intake condition and determine whether the aircraft engine 2000 is in normal condition. If normal, proceed to the next step; if abnormal, perform troubleshooting.

[0238] S3. Observe the generation and evolution of the contrail of the aircraft engine 2000 in the environmental chamber 300 using the test system 900 .

[0239] It can be seen from the above method that the testing method of the testing device 1000 for studying the generation and evolution of contrail clouds in an embodiment of the present invention, after judging that the condition of the aircraft engine 2000 is normal, uses the environmental chamber 300 and the testing system 900 to observe the generation and evolution of the contrail clouds of the aircraft engine 2000, so as to facilitate real-time observation and detection of changes in the contrail clouds, thereby realizing the study of the contrail clouds, that is, facilitating the subsequent formulation of mitigation measures for contrail clouds, and providing support for the study of the impact of aviation emissions on the global climate.

[0240] In some examples, after the aircraft engine 2000 is placed in the installation cabin 210, the thrust tester 220 may be connected first to facilitate subsequent determination of whether the thrust parameters of the aircraft engine 2000 are normal based on the test results of the thrust tester 220.

[0241] Optionally, when starting the aircraft engine 2000 under ground air intake conditions and judging whether the condition of the aircraft engine 2000 is normal, specifically after the aircraft engine 2000 runs to the measured speed and load conditions, observe the various performance indicators and parameters of the aircraft engine 2000 in the ground state, including power (thrust), fuel consumption rate, coolant temperature, lubricating oil pressure and temperature, exhaust temperature, etc., to ensure that the aircraft engine 2000 is in normal condition.

[0242] Optionally, when it is determined that the condition of the aircraft engine 2000 is abnormal and the fault is eliminated, the aircraft engine 2000 can be started again under ground air intake conditions, and it can be determined whether the condition of the aircraft engine 2000 is normal until the exhaust of the aircraft engine 2000 can be tested.

[0243] It should be noted that before using the environmental chamber 300 and the test system 900 to observe the formation and evolution of the contrail of the aircraft engine 2000, Figure 25 As shown, the test system can be installed first, specifically, the microscope 930 is placed between the high-speed camera 920 and the optical measurement window panel 3121, and the high-speed camera 920 and the microscope 930 are placed on the air-floating vibration isolation optical platform 910, and the light source 940 is installed opposite the light source window panel 3122, and the focus of the microscope 930 is adjusted to the expected observation position.

[0244] Then, the simulation altitude is determined, and the second air supply system 400, the third air supply system 100, the environmental chamber 300 and the air extraction system 500 are adjusted according to the simulation altitude to adjust the air intake state of the aircraft engine 2000, the state of the installation cabin 210 and the state of the test chamber 311, so that the installation cabin 210 and the test chamber 311 are both in the working state of contrail cloud generation and evolution, and the dilution unit 321 and the injection unit 3221 are adjusted to adjust the plume state to the expected simulation state, and then the gas diluted by the dilution unit 321 is injected into the test chamber 311.

[0245] During the spraying process, the light source 940 may be turned on, and the high-speed camera 920 may be used to observe the trail cloud generated in the test chamber 311 , and the observation data may be recorded during the observation process.

[0246] It should be noted that the observation content includes but is not limited to the emission of aerosol particles, particle infiltration, water condensation and ice crystal growth, and the continued growth (sublimation) of top (bottom) ice crystals.

[0247] After the recording is completed, determine whether all the required height simulations are completed. When it is determined that they are not completed, adjust the simulation height and observe the contrail clouds generated at different heights. When it is determined that all the required height simulations are completed, determine whether the required plume state simulation is completed. When it is determined that it is not completed, adjust the dilution unit 321 and the injection unit 3221 to adjust the plume state to the expected simulation state. When it is determined that the required plume state simulation is completed, close the installation cabin 210 and the environmental cabin 300 in sequence, and adjust the first air supply system 240, the second air supply system 400, the third air supply system 100 and the exhaust system 500 to gradually restore the intake and exhaust of the aircraft engine 2000 to the ground operation state, and stop the aircraft engine 2000, and the detection is completed.

[0248] Figure 3 Four groups of optical observation window panels 312 are shown for illustrative purposes, but after reading the above technical solution, ordinary technicians can obviously understand that the solution can be applied to two, three, five or more groups of optical observation window panels 312, which also falls within the scope of protection of the present invention.

[0249] The structures and working principles of the environmental chamber 300, the testing device and the method for studying the formation and evolution of contrail clouds according to the embodiments of the present invention, such as the air intake tower 130, the heater 160, the thrust tester 220 and other components, are well known to those skilled in the art and will not be described in detail here.

[0250] Throughout this specification, reference to terms such as "embodiment" or "example" indicates that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0251] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to the embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the claims and their equivalents.

Claims

1. An environmental chamber for studying contrail formation and evolution, characterized in that: include: A cabin assembly is formed with a test cavity, and the cabin assembly is provided with an optical observation window panel and a first mounting plate for mounting a sampler; An air intake assembly, comprising: a dilution unit, the dilution unit being configured to receive exhaust gas and dilution gas from an aircraft engine and to mix the exhaust gas and the dilution gas; a first air intake unit, the first air intake unit being in communication with the dilution unit and configured to receive the mixed gas from the dilution unit and inject the mixed gas into the test chamber; a second air inlet unit, the second air inlet unit being used to deliver low-temperature and high-humidity gas toward the test chamber; An exhaust component is communicated with the test chamber and is used to exhaust part of the gas in the test chamber.

2. The environmental chamber according to claim 1, characterized in that The optical observation window panels include multiple groups, and the multiple groups of optical observation window panels are arranged along the length direction of the cabin assembly. The optical observation window panels include optical measurement window panels and light source window panels.

3. The environmental chamber according to claim 2, characterized in that The dilution unit includes a mixing tube, the mixing tube is provided with an air inlet, an air inlet channel, and an air outlet communicating with the inner and outer sides of the mixing tube, the air inlet and the air outlet being arranged at both axial ends of the mixing tube, the air inlet being communicated with the aircraft engine, and the air outlet being communicated with the first air intake unit; The air inlet passage is arranged in the circumferential direction of the mixing tube and is used for conveying the dilution gas toward the mixing tube.

4. The environmental chamber according to claim 3, characterized in that The air intake passage comprises a plurality of air intake passages, and the plurality of air intake passages are spaced apart along the axial direction and / or circumferential direction of the mixing tube; The axis of the air intake channel extends obliquely relative to the cross-sectional plane of the mixing tube, the cross-sectional plane is parallel to the front-to-back direction and the up-down direction of the mixing tube, and the axes of the multiple air intake channels are inclined in the same clockwise direction.

5. The environmental chamber according to claim 4, characterized in that The dilution unit includes a first air intake pipe and a pressure equalizing pipe with different extension directions. The pressure equalizing pipe is sleeved on the mixing pipe and cooperates with the mixing pipe to define a first pressure equalizing chamber. The first air intake pipe is connected to the first pressure equalizing chamber for transporting the dilution gas toward the first pressure equalizing chamber. The first pressure equalizing chamber is connected to multiple air intake channels.

6. The environmental chamber according to claim 2, characterized in that The air intake assembly includes a connecting plate connected to the end of the cabin assembly, and the first air intake unit and the second air intake unit are both arranged on the connecting plate; The first air intake unit includes an injection unit, which includes a nozzle and an injection pipe. The nozzle is used to receive the gas mixed by the dilution unit, and opposite ends of the injection pipe are respectively connected to the nozzle and the test chamber.

7. The environmental chamber according to claim 6, characterized in that A first pressure equalizing plate is provided on a side of the connecting plate close to the test chamber, and the first pressure equalizing plate cooperates with the connecting plate to define a second pressure equalizing chamber, and the first pressure equalizing plate is provided with a plurality of first diversion ports communicating with the second pressure equalizing chamber, and the second air intake unit includes a plurality of second air intake pipes, and the plurality of second air intake pipes are arranged at intervals on the connecting plate and communicate with the second pressure equalizing chamber; The end of the connecting plate is provided with a second pressure equalizing plate, a third air inlet pipe connected to the second pressure equalizing plate, and a diversion structure. The diversion structure includes a plurality of second diversion ports passing through the connecting plate. The second pressure equalizing plate is arranged on the side of the connecting plate away from the test chamber and cooperates with the connecting plate to define a third pressure equalizing chamber. The third pressure equalizing chamber covers the diversion structure, and the third air inlet pipe is used to transport gas toward the third pressure equalizing chamber.

8. The environmental chamber according to claim 7, characterized in that The cabin assembly is further provided with an air intake pipe mounting plate, which is arranged between the multiple groups of optical observation window panels. The air intake pipe mounting plate is provided with a fourth air intake pipe, which is used to transport gas toward the test chamber.

9. A test device for studying the formation and evolution of contrail clouds, characterized in that: include: An environmental chamber, wherein the environmental chamber is the environmental chamber according to any one of claims 2 to 8; A test system comprising an air-floating vibration-isolating optical platform, a high-speed camera, a microscope, and a light source, wherein the high-speed camera and the microscope are disposed on the air-floating vibration-isolating optical platform, the microscope is disposed between the high-speed camera and the optical measurement window panel, and the light source faces the light source window panel; an installation cabin and a first air supply system, wherein the installation cabin is provided with an aircraft engine to be tested, the aircraft engine and the first air supply system are both in communication with the dilution unit, and the first air supply system is used to deliver dilution gas toward the dilution unit; a second air supply system, the second air supply system being in communication with the second air inlet unit and configured to deliver low-temperature, high-humidity air toward the second air inlet unit; The exhaust system is connected to the exhaust component and is used to extract the gas in the test chamber through the exhaust component.

10. A method for testing a test device for studying contrail cloud generation and evolution according to claim 9, characterized in that: The following steps are involved: Installing the aircraft engine in the installation cabin; Start the aircraft engine under ground air intake conditions and determine whether the aircraft engine is in normal condition. If it is normal, proceed to the next step; if it is not normal, perform troubleshooting. The test system is used to observe the generation and evolution of the contrail of the aircraft engine in the environmental chamber.

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