CN111681520A - Simulation experiment device for external fire of airplane - Google Patents
Simulation experiment device for external fire of airplane Download PDFInfo
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- CN111681520A CN111681520A CN202010529827.7A CN202010529827A CN111681520A CN 111681520 A CN111681520 A CN 111681520A CN 202010529827 A CN202010529827 A CN 202010529827A CN 111681520 A CN111681520 A CN 111681520A
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
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Abstract
The invention discloses a simulation experiment device for an external fire of an airplane, which comprises an experiment table main body, a fire source system and a data measurement system, wherein a cylindrical cabin of the experiment table main body is used for simulating a middle cabin section of the actual airplane, and the upper end of a supporting frame of the experiment table main body supports the cylindrical cabin and is adjustable in height; the fire source system is used for simulating fire sources with different powers, which are applied to various areas outside the aircraft body; the data measuring system comprises a temperature distribution measuring system, a thermal radiation flux measuring system and a fire plume and jet flow measuring system which are respectively used for measuring the surface temperature distribution condition of the outside of the cylindrical cabin, the thermal radiation flux change condition of different positions outside the cylindrical cabin and the flame shape, the fire plume and the jet flow characteristics of the outside of the cylindrical cabin in the experimental process. The invention can comprehensively research the temperature distribution of the outer surface of the airplane, the change rule of the thermal radiation flux, the fire plume and the jet flow characteristic thereof when different parts of the outer part of the airplane body are acted by fire sources with different powers in a laboratory, and has the advantages of low cost, accurate measurement and the like.
Description
Technical Field
The invention relates to the technical field of safety of external fires of airplanes, in particular to a simulation experiment device for the external fires of airplanes.
Background
The airplane is a high integration of modern high and new technologies, and the common civil airplane is very expensive. However, with the continuous development of the aviation industry, external fire accidents of parked airplanes occur at the same time, and the problem of the external fire of airplanes attracts extensive attention and profound thinking. When the airplane is parked and is dragged, overhauled, refueled, loaded and unloaded, the external environment is relatively complex, and fire accidents can be avoided. The thermal radiation and the thermal convection of the flame of an external fire can cause damage to the surface of the airplane in different degrees, influence the integrity, the structural support, the corrosion resistance and the like of the outer surface of the airplane, and more possibly influence the thermal influence of the internal equipment of the airplane, so that the damage which is difficult to estimate is generated.
The high temperature heat radiation and heat convection of the flame generated by the fire when the load around the airplane occurs cause losses of different degrees to the inside and the outside of the airplane body. The fire load around the aircraft is from various sources, station building bridge fire around the airport, construction sites around the airport, relevant devices externally hung on the aircraft, traction vehicles, leaked aircraft fuel and the like. The fire source power, the fire source form, the fire plumes and the jet flow of different load combustion are different, and meanwhile, the influence on the airplane caused by different relative positions of the inflamed objects and the airplane is different, so that the most serious area of the surface damage of the airplane is difficult to judge, and the loss condition of the fire to the internal equipment of the airplane cannot be determined.
In the case of fire combustion in an open environment, such as solid fire, liquid fire, gas fire, and the like, a great deal of intensive research on combustion characteristics, flame shapes, fire plumes, jet flows, and the like has been conducted by using fuels such as wood, cardboard boxes, n-heptane, aviation kerosene, methane, propane, and the like as experimental subjects, but research is mainly focused on some characteristics of the fire itself. Especially, NIST in the united states and the fire focus laboratory at the university of chinese science and technology have conducted a great deal of research, in which Hamins et al of NIST analyzed the heat transfer pattern in the combustion process using the heat transfer principle and the law of conservation of energy, and established a model for calculating the average combustion rate in the steady-state combustion process. Fuugh proposes a model for predicting flame radiation based on flame morphology characteristics. There are also a lot of experimental studies on the interaction of fire with ceilings, side walls and the like, but all are based on the limited conditions of building fire, tunnel fire and the like. Hasemii researches the relation between the fire source expansion length and the fire source power when the fire source impacts the plane ceiling without the limitation of a side wall through experiments, and establishes a dimensionless prediction model. Ji et al studied the influence of the distance between the fire source and the side wall on the maximum flue gas temperature of the tunnel ceiling in the tunnel laboratory, and found that the maximum temperature rise under the ceiling is increased compared with the case of an unlimited space and the case of a fire on the longitudinal centerline. However, the aircraft itself is in an open environment, and the aircraft fuselage is cylindrical, and the fuselage surface is a cambered surface, and what kind of influence that different relative positions and different power fire sources caused the aircraft is fresh research. The influence on the cambered surface ceiling and the side wall cannot be well predicted by the conventional experimental data and the combustion model.
Because a large amount of manpower and material resources are required to be mobilized in a full-size fire experiment, the economic consumption is high, the influence of various factors is large, the conditions are difficult to control, and the repeatability is poor, so that the full-size fire experiment is difficult to develop.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art. Therefore, one objective of the present invention is to provide an experimental apparatus for simulating an external fire of an aircraft, which can be used for studying the external surface temperature distribution and the thermal radiation flux change rule of the aircraft, and the evolution rule of interaction between fire plumes and jet flows thereof when different parts of the external part of the aircraft body are affected by fire sources with different powers in a laboratory, and has the advantages of simple operation and control, low cost, good reproducibility, high reliability of measurement results, and strong repeatability, and provides scientific basis and data support for airport aircraft parking design, airport fire-fighting and rescue tactics, aircraft structure protection, and the like.
The simulation experiment device for the external fire of the airplane comprises the following components:
the experiment table comprises an experiment table main body and a supporting frame, wherein the experiment table main body comprises a cylindrical cabin and the supporting frame, the cylindrical cabin is used for simulating a middle cabin section of an actual airplane, the whole volume of the cylindrical cabin is smaller than that of the middle cabin section of the actual airplane, the cylindrical cabin is supported by the upper end of the supporting frame, and the height of the supporting frame is adjustable, so that the cylindrical cabin is in a horizontal state or an inclined state according to experiment requirements, and the state of the actual airplane is simulated;
the fire source system can move horizontally and is arranged near the experiment table main body in a height-adjustable manner, and is used for providing a solid fuel fire source, a liquid fuel fire source or a gas combustion fire source according to experiment requirements so as to simulate the action of fire sources with different powers on various regions outside the airplane body;
a data measurement system comprising a temperature distribution measurement system, a thermal radiation flux measurement system, and a fire plume and jet measurement system; the temperature distribution measuring system is used for measuring the temperature distribution condition of the outer surface of the cylindrical cabin in the experimental process; the thermal radiation flux measurement system is used for measuring the thermal radiation flux change conditions of different positions outside the cylindrical cabin in the experimental process; the fire plume and jet measurement system is used to measure the flame morphology, fire plume and jet characteristics outside the cylindrical chamber.
According to the simulation experiment device for the external fire of the airplane, disclosed by the embodiment of the invention, the actual middle cabin section of the airplane is simulated through the cylindrical cabin, the whole volume of the simulation experiment device is smaller than that of the actual middle cabin section of the airplane, the inclination angle of the cylindrical cabin is adjusted through the supporting frame to simulate the actual airplane state, the external fire of the airplane is simulated really by igniting different combustion fire sources such as a solid fuel fire source, a liquid fuel fire source or a gas combustion fire source, the temperature distribution condition of the outer surface of the cylindrical cabin in the experiment process is measured through the temperature distribution measuring system, the change condition of the thermal radiation flux at different positions outside the cylindrical cabin in the experiment process is measured through the thermal radiation flux measuring system, and the flame form, the fire plume and the jet flow characteristics outside the cylindrical cabin are measured through the fire plume and jet flow measuring system, so that the experiment data of the simulation experiment device for the external fire of the airplane disclosed by the embodiment of the invention can be utilized in a laboratory to measure the different The method has the advantages that the change rule of the temperature distribution and the heat radiation flux of the outer surface of the airplane and the evolution rule of the interaction of the fire plumes and the jet flows thereof are comprehensively researched under the action of the power fire source, the operation and the control are simple, the cost is low, the reproducibility is good, the reliability of the measuring result is high, and the repeatability is strong. In addition, the fire source system can move horizontally and is adjustable in height, so that fire scenes of different positions outside the airplane body can be effectively simulated, the change rule of the temperature distribution and the heat radiation flux of the outer surface of the airplane and the evolution rule of the interaction of fire plumes and jet flows of the fire plumes can be researched when different parts outside the airplane body are affected by fire sources with different powers in a laboratory, and scientific basis and data support are provided for airport airplane parking design, airport fire extinguishing and rescue tactics, airplane structure protection and the like.
According to one embodiment of the invention, the cylindrical cabin comprises a structural support inner layer, a heat insulation interlayer and a high-temperature-resistant fireproof outer layer from inside to outside, wherein the heat insulation interlayer is arranged on the outer surface of the structural support inner layer, and the high-temperature-resistant fireproof outer layer is arranged on the outer surface of the heat insulation interlayer.
According to a further embodiment of the invention, the inner layer of the structural support is a steel cylinder inner layer, the heat insulation interlayer is made of ceramic fibers, and the outer layer of the high-temperature-resistant fireproof plate is made of skin and is wrapped on the outer surface of the heat insulation interlayer.
According to one embodiment of the invention, the cylindrical bin can be continuously varied between a range of inclination angles of 0-15 °.
According to one embodiment of the invention, the support frame is provided with scales.
According to one embodiment of the invention, the support frame is provided with a hydraulic lifting device, so that the support frame is height-adjustable.
According to one embodiment of the invention, the lower end of the support frame is provided with a first pulley.
According to one embodiment of the present invention, the ignition source system includes a main body frame, an oil pan, a gas burner, and an igniter; the lower end of the main body frame is provided with a second pulley, and the height of the main body frame is adjustable; the oil pan, the gas burner, and the igniter are disposed on the main body frame, and the igniter is used to ignite the solid fuel placed on the main body frame, the fuel oil in the oil pan, and the gas fuel in the gas burner.
According to a further embodiment of the invention, the fire source system further comprises an electronic balance, the electronic balance is arranged on the main body frame, the oil pan is arranged on the electronic balance, the electronic balance measures the combustion loss mass of the liquid fuel and feeds the measured electric signal of the balance back to a data measuring device connected with the electronic balance, so as to record and process the electric signal of the balance through the data measuring device connected with the electronic balance and dynamically present the combustion loss mass condition of the liquid fuel in real time.
According to a further embodiment of the invention the solid fuel is a wood stack or a carton, the liquid fuel is jet fuel or n-heptane and the gaseous fuel is methane or propane.
According to one embodiment of the invention, the temperature distribution measuring system comprises a thermocouple array arranged on the outer surface of the cylindrical cabin, and the thermocouple array is used for measuring the temperature of the outer surface of the cylindrical cabin in the experimental process and feeding back a measured outer surface temperature signal to a data measuring device connected with the thermocouple array so as to record and process the measured outer surface temperature signal through the data measuring device connected with the thermocouple array and dynamically present the outer surface temperature distribution condition of the cylindrical cabin in real time.
According to a further embodiment of the invention, the temperature distribution measuring system further comprises an infrared camera for recording the temperature change condition of the external surface of the cylindrical cabin in an image mode during the experiment.
According to one embodiment of the invention, the bolometer is a plurality of bolometers, the plurality of bolometers are arranged outside the cartridge type cabin at intervals, and the plurality of bolometers are used for measuring the thermal radiation flux at different positions outside the cartridge type cabin in the experimental process and feeding back the measured thermal radiation flux signals to the data measuring device connected with the plurality of bolometers so as to record and process the thermal radiation flux signals and dynamically present the thermal radiation flux change at different positions outside the cartridge type cabin in real time through the data measuring device connected with the plurality of bolometers.
According to one embodiment of the invention, the fire plume and jet flow measuring system comprises a first high-speed camera and a second high-speed camera, and the first high-speed camera and the second high-speed camera are used for measuring and recording the flame form, the fire plume and the jet flow characteristics outside the cylindrical cabin in real time in a camera mode.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic structural diagram of a simulation experiment device for an aircraft external fire according to an embodiment of the invention.
Fig. 2 is a structural layout view of a thermocouple array and a bolometer of a simulation experiment apparatus for an aircraft external fire according to an embodiment of the present invention.
Fig. 3 is a schematic structural diagram of a fire source system of the aircraft external fire simulation experiment device according to the embodiment of the invention.
Reference numerals:
Experiment table main body 1
Thermocouple array 31 infrared camera 32 bolometer 33 first high speed camera 34
Second high-speed camera 35
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
A simulation experiment apparatus 1000 for an aircraft external fire according to an embodiment of the present invention is described below with reference to fig. 1 to 3.
As shown in fig. 1 to 3, a simulation experiment device 1000 for an aircraft external fire according to an embodiment of the present invention includes an experiment table main body 1, a fire source system 2 and a data measurement system 3, wherein the experiment table main body 1 includes a cylindrical cabin 11 and a support frame 12, the cylindrical cabin 11 is used for simulating a middle cabin section of an actual aircraft, and has an overall volume smaller than that of the middle cabin section of the actual aircraft, the upper end of the support frame 12 supports the cylindrical cabin 11, and the height of the support frame 12 is adjustable, so that the cylindrical cabin 11 is in a horizontal state or an inclined state according to experiment requirements, so as to simulate a state where the actual aircraft is located; the fire source system 2 can move horizontally and is arranged near the experiment table main body 1 in a height-adjustable manner, and is used for providing a solid fuel fire source, a liquid fuel fire source or a gas combustion fire source according to experiment requirements so as to simulate the action of various regions outside the airplane body on fire sources with different powers; the data measuring system 3 comprises a temperature distribution measuring system, a thermal radiation flux measuring system and a fire plume and jet flow measuring system; the temperature distribution measuring system is used for measuring the temperature distribution condition of the outer surface of the cylindrical cabin 11 in the experimental process; the thermal radiation flux measuring system is used for measuring the thermal radiation flux change conditions of different positions outside the cylindrical cabin 11 in the experimental process; the fire plume and jet measurement system is used to measure the flame morphology, fire plume and jet characteristics outside the cylindrical chamber 11.
Specifically, the experiment table main body 1 comprises a cylindrical cabin 11 and a support frame 12, the cylindrical cabin 11 is used for simulating an actual airplane middle cabin section, the whole volume of the cylindrical cabin 11 is smaller than that of the actual airplane middle cabin section, the upper end of the support frame 12 supports the cylindrical cabin 11, the height of the support frame 12 is adjustable, and therefore the cylindrical cabin 11 is in a horizontal state or an inclined state according to experiment needs to simulate the actual airplane state. It can be understood that the cylindrical cabin 11 is used for simulating an actual middle cabin section of an airplane, the whole volume of the cylindrical cabin 11 is smaller than that of the actual middle cabin section of the airplane, and the cylindrical cabin 11 can be constructed according to a ratio of the actual middle cabin section of the airplane to 2, for example, the inner diameter of the cylindrical cabin 11 can be 2045mm, the outer diameter can be 2100mm, and the length can be 4000mm, so that the cylindrical cabin 11 is suitable in size and low in cost, can be placed in a laboratory, and can simulate the effect of a fire source on each part outside an airplane body in the laboratory, and meanwhile, the cylindrical cabin 11 with the medium size is convenient to operate and control, good in reproducibility, high in reliability of a measurement result and strong in repeatability; the height of the support frame 12 is adjusted to adjust the trunk type cabin 11 to a horizontal state or an inclined state so as to simulate the state of a real airplane.
It should be noted that the height of the cylindrical cabin 11 from the ground can be adjusted to continuously change between 400mm and 800mm by adjusting the height of the support frame 12; the height of the fire source system 2 from the ground varies between 500mm and 1000 mm.
The fire source system 2 can move horizontally and is arranged near the experiment table main body 1 in a height-adjustable manner, and is used for providing a solid fuel fire source, a liquid fuel fire source or a gas combustion fire source according to experiment requirements, and changing flame power so as to more truly simulate the action of different power fire sources on each region outside the airplane body; it can be understood that the fire scene at different positions can be effectively simulated by moving the position of the fire source system 2 and adjusting the height of the fire source system 2; by igniting different kinds of burning fire sources, such as a solid fuel fire source, a liquid fuel fire source or a gas burning fire source, the external fire of the airplane can be simulated more truly.
The data measurement system 3 includes a temperature distribution measurement system, a thermal radiation flux measurement system, and a fire plume and jet measurement system. It can be understood that the temperature distribution measuring system is used for measuring the temperature distribution of the outer surface of the cylindrical cabin 11 during the experiment; the thermal radiation flux measuring system is used for measuring the thermal radiation flux change conditions of different positions outside the cylindrical cabin 11 in the experimental process; the fire plume and jet flow measuring system is used for measuring the flame form, the fire plume and the jet flow characteristics outside the cylindrical cabin 11, so that the data measuring system 3 can carry out systematic and comprehensive research on the surface temperature distribution and the thermal radiation flux change rule of the cylindrical cabin 11 and the evolution rule of the interaction of the fire plume and the jet flow thereof by external fire disasters at different positions and different fire source powers.
According to the simulation experiment device 1000 of the external fire of the airplane of the embodiment of the invention, the actual middle cabin section of the airplane is simulated through the cylindrical cabin 11, the whole volume of the simulation experiment device is smaller than that of the actual middle cabin section of the airplane, the inclination angle of the cylindrical cabin 11 is adjusted through the support frame 12 to truly simulate the state of the actual airplane, the actual external fire of the airplane is truly simulated through igniting different combustion fire sources such as a solid fuel fire source, a liquid fuel fire source or a gas combustion fire source, the temperature distribution condition of the outer surface of the cylindrical cabin 11 in the experiment process is measured through the temperature distribution measuring system, the thermal radiation flux change conditions of different positions outside the cylindrical cabin 11 in the experiment process are measured through the thermal radiation flux measuring system, and the flame form, the flame plume and the jet flow characteristics outside the cylindrical cabin 11 are measured through the plume and the jet flow measuring system, so that the experiment data of the simulation experiment device 1000 of the external fire of the airplane of the embodiment of the invention can be utilized in a laboratory The method has the advantages that the method comprehensively researches the change rule of the temperature distribution and the heat radiation flux of the outer surface of the airplane and the evolution rule of the interaction of the fire plumes and the jet flows thereof when the outer part of the airplane body is acted by fire sources with different powers, and is simple in operation and control, low in cost, good in reproducibility, high in reliability of the measuring result and strong in repeatability. In addition, the fire source system 2 can be horizontally moved and is adjustable in height, so that fire scenes at different positions outside the airplane body can be effectively simulated, the change rule of the temperature distribution and the thermal radiation flux of the outer surface of the airplane and the evolution rule of the interaction of fire plumes and jet flows thereof can be comprehensively researched when different parts outside the airplane body are acted by fire sources with different powers in a laboratory, and scientific basis and data support are provided for airport airplane parking design, airport fire-fighting and rescue tactics, airplane structure protection and the like.
According to one embodiment of the invention, the cylindrical cabin 11 comprises, from inside to outside, a structural support inner layer, a thermal insulation interlayer arranged on the outer surface of the structural support inner layer, and a high temperature fire-resistant outer layer arranged on the outer surface of the thermal insulation interlayer. It can be understood that the structural support inner layer, the heat insulation interlayer and the high-temperature-resistant fireproof outer layer are sequentially arranged from inside to outside to form the cylindrical cabin 11, so that the shape of the cylindrical cabin 11 is close to the shape of an airplane, the measurement result is reliable and accurate, and the structural strength is high and the integrity is good.
According to a further embodiment of the invention, the inner layer of the structural support is a steel cylinder inner layer, the heat insulation interlayer is made of ceramic fibers, and the high-temperature-resistant fireproof outer layer is formed by covering a skin made of high-temperature-resistant fireproof plates on the outer surface of the heat insulation interlayer. It can be understood that the inner layer of the structural support is used for providing support for the cylindrical cabin 11, and the inner layer of the steel cylinder can be made of carbon steel, for example, the steel cylinder can be 5mm thick carbon steel, so that the strength is high and the support effect is good; the heat insulation interlayer is used for insulating heat inside the cylindrical cabin 11, can be ceramic fiber with the thickness of 40mm, and has good heat insulation effect; the outer fire-resistant layer of high temperature resistant fire prevention is as the flame retardant coating of aircraft shell, and the outer fire-resistant layer of high temperature resistant fire prevention can be the arc covering that the high temperature resistant PLASTIC LAMINATED of 10mm thickness made, like this, guarantees effectively that the shape of shell type cabin 11 is close to the aircraft shape more, and measuring result is reliable accurate, and structural strength is high and the integrality is good.
According to one embodiment of the invention, the cylindrical bin 11 can be continuously varied between a range of inclination angles of 0-15 °. In particular, the angle of inclination of the cabin 11 can be 0 °, 5 °, 10 ° or 15 ° in order to simulate the conditions of a real aircraft.
According to one embodiment of the present invention, the support 12 is provided with a scale. It will be appreciated that the angle of inclination of the capsule 11 can be conveniently controlled by means of a scale.
According to one embodiment of the present invention, the support frame 12 is configured with a hydraulic lift device to make the support frame 12 height adjustable. It can be understood that the cartridge type cabin 11 has a heavy weight, the height of the support frame 12 can be conveniently adjusted by arranging the hydraulic lifting system on the support frame 12, and the structure is simple and reasonable.
According to one embodiment of the invention, the lower end of the support frame 12 is provided with a first pulley 13. Thus, the position of the experiment table main body 1 can be easily moved.
According to one embodiment of the present invention, the ignition source system 2 includes a main body frame 21, an oil pan 22, a gas burner 23, and an igniter 24; the lower end of the main body frame 21 is provided with a second pulley 211, and the height of the main body frame 21 is adjustable; an oil pan 22, a gas burner 23, and an igniter 24 are provided on the main body frame 21, and the igniter 24 is used to ignite the solid fuel placed on the main body frame 21, the fuel oil in the oil pan 22, and the gas fuel in the gas burner 23. It can be understood that the second pulley 211 is provided at the lower end of the main body frame 21 and the height of the main body frame 21 is adjustable, so that the fire source system 2 can be conveniently moved according to experimental requirements, the relative position of the fire source system 2 and the cylindrical cabin 11 is changed, the height of the fire source system 2 is adjusted, so as to simulate real fire scenes in different positions, the ignition position of the igniter 24 is adjustable, when the liquid fuel needs to be ignited, the igniter 24 is moved to the periphery of the oil pan 22 to ignite the liquid fuel, when the solid fuel needs to be ignited, the igniter 24 is moved to the periphery of the solid fuel to ignite the solid fuel, when the gas fuel needs to be ignited, the igniter 24 is moved to the periphery of the gas burner 23 to ignite the gas fuel, the operation is convenient, and the structure is simple.
It should be noted that a hydraulic lifting device may be disposed on the main body frame 21 to facilitate the height adjustment of the main body frame 21; the oil pan 22 may vary in size and shape.
According to a further embodiment of the present invention, the fire source system 2 further comprises an electronic balance 25, the electronic balance 25 is disposed on the main body frame 21, the oil pan 22 is disposed on the electronic balance 25, the electronic balance 25 measures the combustion loss mass of the liquid fuel and feeds the measured balance electrical signal back to the data measuring device connected to the electronic balance 25, so as to record and process the balance electrical signal through the data measuring device connected to the electronic balance 25 and dynamically present the combustion loss mass of the liquid fuel in real time. Therefore, the combustion loss mass of the liquid fuel is measured by the electronic balance 25, the influence of different combustion loss masses on the external surface temperature distribution and the thermal radiation flux change rule of the barrel-shaped cabin 11 and the evolution rule of interaction of the fire plume and the jet flow is judged, and the accuracy of the experiment is improved.
According to a further embodiment of the invention the solid fuel is a wood stack or a carton, the liquid fuel is jet fuel or n-heptane and the gaseous fuel is methane or propane. Therefore, different types of fuels can be selected according to experimental needs, flame power is changed, and different types of external fires can be simulated more truly.
It should be noted that the solid fuel is a standard piece of wood crib or a standard piece of carton.
According to an embodiment of the present invention, the temperature distribution measuring system includes a thermocouple array 31 disposed on the outer surface of the cylindrical chamber 11, the thermocouple array 31 is used for measuring the temperature of the outer surface of the cylindrical chamber 11 during the experiment and feeding back the measured outer surface temperature signal to the data measuring device connected to the thermocouple array 31, so as to record and process the measured outer surface temperature signal through the data measuring device connected to the thermocouple array 31 and dynamically present the outer surface temperature distribution of the cylindrical chamber 11 in real time. It can be understood that the distribution of the temperature of the outer surface of the can type chamber 11 can be conveniently and accurately studied by disposing the thermocouple array 31 on the outer surface of the can type chamber 11 and feeding back the outer surface temperature signal measured by the thermocouple array 31 to the data measuring device connected to the thermocouple array 31.
According to a further embodiment of the invention, the temperature distribution measuring system further comprises an infrared camera 32, the infrared camera 32 being adapted to graphically record the temperature variations on the outer surface of the capsule 11 during the experiment. Specifically, the infrared camera 32 is disposed between the cylindrical chamber 11 and the fire source system 2, and photographs the cylindrical chamber 11, and changes in the temperature of the outer surface of the cylindrical chamber 11 during the experiment are recorded in the form of images, so that the distribution of the temperature of the outer surface of the cylindrical chamber 11 can be further accurately studied.
According to an embodiment of the present invention, the bolometer 33 is a plurality of bolometers 33, the plurality of bolometers 33 are arranged outside the cartridge type chamber 11 in a spaced apart relationship, the plurality of bolometers 33 are configured to measure the bolometers at different positions outside the cartridge type chamber 11 during the experiment and to feed back the measured bolometer flux signals to the data measuring device connected to the plurality of bolometers 33, so as to record and process the bolometer flux signals through the data measuring device connected to the plurality of bolometers 33 and dynamically present the bolometer flux variation at different positions outside the cartridge type chamber 11 in real time. Specifically, the plurality of bolometers 33 are distributed at intervals in the vertical direction and the horizontal direction outside the cylindrical cabin 11, the bolometers 33 measure the thermal radiation fluxes at different positions outside the cylindrical cabin 11 in the experimental process and feed the measured thermal radiation flux signals back to the data measuring device connected with the plurality of bolometers 33, and the data measuring device records and processes the thermal radiation flux signals and dynamically presents the thermal radiation flux change conditions at different positions outside the cylindrical cabin 11 in real time, so that the thermal radiation flux change rules of each region outside the cylindrical cabin 11 under the action of the fire sources with different powers can be conveniently researched.
According to one embodiment of the present invention, the fire plume and jet measurement system includes a first high speed camera 34 and a second high speed camera 35, the first high speed camera 34 and the second high speed camera being used to photographically measure in real time the flame morphology, the fire plume and the jet characteristics outside the recording cylinder type chamber 11. Specifically, the fire source system 2 is arranged near one side of the cylindrical chamber 11, and the first high-speed camera 34 and the second high-speed camera are arranged near the experiment table main body 1, wherein the first high-speed camera 34 is opposite to one end of the cylindrical chamber 11, so that one end face of the cylindrical chamber 11 is in the middle of the shooting range of the first high-speed camera 34; the second high-speed camera deviates from the other end of the cylindrical cabin 11 and is positioned at one side of the cylindrical cabin 11, so that one side surface and the other end surface of the cylindrical cabin 11 are positioned in the shooting range of the second high-speed camera, the first high-speed camera 34 and the second high-speed camera are used for carrying out image acquisition on the flame outside the cylindrical cabin 11, and the flame form, the fire plume and the jet flow characteristic outside the cylindrical cabin 11 are measured and recorded in real time, so that the change rule of the flame form, the fire plume and the jet flow characteristic of the flame outside the cylindrical cabin 11 under the action of fire sources with different powers can be conveniently researched.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (14)
1. A simulation experiment device for an aircraft external fire is characterized by comprising:
the experiment table comprises an experiment table main body and a supporting frame, wherein the experiment table main body comprises a cylindrical cabin and the supporting frame, the cylindrical cabin is used for simulating a middle cabin section of an actual airplane, the whole volume of the cylindrical cabin is smaller than that of the middle cabin section of the actual airplane, the cylindrical cabin is supported by the upper end of the supporting frame, and the height of the supporting frame is adjustable, so that the cylindrical cabin is in a horizontal state or an inclined state according to experiment requirements, and the state of the actual airplane is simulated;
the fire source system can move horizontally and is arranged near the experiment table main body in a height-adjustable manner, and is used for providing a solid fuel fire source, a liquid fuel fire source or a gas combustion fire source according to experiment requirements so as to simulate the action of fire sources with different powers on various regions outside the airplane body;
a data measurement system comprising a temperature distribution measurement system, a thermal radiation flux measurement system, and a fire plume and jet measurement system; the temperature distribution measuring system is used for measuring the temperature distribution condition of the outer surface of the cylindrical cabin in the experimental process; the thermal radiation flux measurement system is used for measuring the thermal radiation flux change conditions of different positions outside the cylindrical cabin in the experimental process; the fire plume and jet measurement system is used to measure the flame morphology, fire plume and jet characteristics outside the cylindrical chamber.
2. An aircraft external fire simulation experiment device according to claim 1, wherein the cylindrical cabin comprises a structural support inner layer, a heat insulation interlayer and a high-temperature-resistant fireproof outer layer from inside to outside in sequence, the heat insulation interlayer is arranged on the outer surface of the structural support inner layer, and the high-temperature-resistant fireproof outer layer is arranged on the outer surface of the heat insulation interlayer.
3. The aircraft external fire simulation experiment device according to claim 2, wherein the structural support inner layer is a steel cylinder inner layer, the heat insulation interlayer is made of ceramic fibers, and the high-temperature-resistant fireproof outer layer is formed by covering a skin made of a high-temperature-resistant fireproof plate on the outer surface of the heat insulation interlayer.
4. An aircraft external fire simulation experiment device according to claim 1, wherein the canister type chamber is continuously variable between tilt angles of 0-15 °.
5. An aircraft external fire simulation experiment device according to claim 1, wherein the support frame is provided with graduations.
6. An aircraft external fire simulation experiment device according to claim 1, wherein the support frame is provided with a hydraulic lifting device to make the support frame height adjustable.
7. An aircraft external fire simulation experiment device according to claim 1, wherein the lower end of the support frame is provided with a first pulley.
8. A simulation experiment device for an aircraft external fire according to claim 1, wherein the ignition source system includes a main body frame, an oil pan, a gas burner, and an igniter; the lower end of the main body frame is provided with a second pulley, and the height of the main body frame is adjustable; the oil pan, the gas burner, and the igniter are disposed on the main body frame, and the igniter is used to ignite the solid fuel placed on the main body frame, the fuel oil in the oil pan, and the gas fuel in the gas burner.
9. The aircraft external fire simulation experiment device according to claim 8, wherein the fire source system further comprises an electronic balance, the electronic balance is arranged on the main body frame, the oil pan is arranged on the electronic balance, the electronic balance measures the burning loss mass of the liquid fuel and feeds back the measured balance electric signal to a data measuring device connected with the electronic balance, so that the balance electric signal is recorded and processed by the data measuring device connected with the electronic balance, and the burning loss mass condition of the liquid fuel is dynamically presented in real time.
10. An aircraft external fire simulation experiment device according to claim 8, wherein the solid fuel is wood stacks or cartons, the liquid fuel is aviation kerosene or n-heptane, and the gas fuel is methane or propane.
11. The aircraft external fire simulation experiment device according to claim 1, wherein the temperature distribution measurement system comprises a thermocouple array arranged on the external surface of the cylindrical cabin, and the thermocouple array is used for measuring the external surface temperature of the cylindrical cabin during the experiment and feeding back a measured external surface temperature signal to a data measurement device connected with the thermocouple array so as to record and process the measured external surface temperature signal through the data measurement device connected with the thermocouple array and dynamically present the external surface temperature distribution of the cylindrical cabin in real time.
12. An aircraft external fire simulation experiment device according to claim 11, wherein the temperature distribution measurement system further comprises an infrared camera for recording temperature changes of the external surface of the cylindrical cabin during the experiment in an image mode.
13. A simulation experiment apparatus for an aircraft external fire according to claim 1, wherein the bolometer system is a plurality of bolometers arranged outside the canister type cabin in a spaced apart relationship with each other, the plurality of bolometers being adapted to measure thermal radiation flux at different positions outside the canister type cabin during the experiment and to feed measured thermal radiation flux signals back to the data measurement apparatus connected to the plurality of bolometers, so as to record and process the thermal radiation flux signals and dynamically present the thermal radiation flux variation at different positions outside the canister type cabin in real time by the data measurement apparatus connected to the plurality of bolometers.
14. The simulated experiment device of the aircraft external fire as claimed in claim 1, wherein the fire plume and jet flow measuring system comprises a first high speed camera and a second high speed camera, and the first high speed camera and the second high speed camera are used for measuring and recording the flame shape, the fire plume and the jet flow characteristic outside the cylindrical cabin in real time in a camera mode.
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