Constant volume combustion bomb test system based on aerostat configuration

Abstract

The invention provides a constant-volume combustion bomb test system based on aerostat configuration. The constant-volume combustion bomb test system comprises an air supply module (100), a constant-volume combustion bomb (200), a schlieren optical module (300) and an ignition module (400), the gas supply module (100) comprises a hydrogen storage device (110) and an air storage device (120); the constant volume combustion bomb (200) comprises a main body part (210), a first end cover (220) provided with a first observation window (240) and a second end cover (230) provided with a second observation window (250); the schlieren optical module (300) comprises a schlieren light source (310), a first plane mirror (320), a first concave mirror (330), a second plane mirror (340), a second concave mirror (350), a knife edge (360) and a high-speed camera (370); the ignition module (400) includes a plurality of ignition devices (420). The constant volume combustion bomb test system based on the aerostat configuration can analyze disaster laws in the aerostat under the danger occurrence condition of different dangerous points.

Description

Technical Field

[0001] This invention relates to the field of airship technology, and in particular to a constant-volume incendiary bomb test system based on an airship configuration. Background Technology

[0002] Airships, relying on buoyancy to ascend, are a branch of the aviation field. Early airships primarily used hydrogen as the lifting gas, but hydrogen easily mixes with air to form a flammable and explosive mixture, posing safety hazards. Therefore, hydrogen was gradually phased out and replaced by helium. Helium is highly safe, but due to its extremely low abundance in the atmosphere, it cannot be synthesized artificially inexpensively, and it almost entirely comes from radioactive gas deposits. Therefore, helium not only has limited reserves and is difficult to extract, resulting in high operating costs, but its widespread use in industrial and scientific fields also limits the amount of helium that can be used in airships.

[0003] In recent years, with the rapid development of the global hydrogen industry, the safe application of hydrogen has become a research focus. Constant-volume incendiary bombs, as a fundamental platform for studying the deflagration characteristics of hydrogen, employ high-strength metallic materials as their main structure and incorporate optical windows in key areas to record the patterns of hydrogen deflagration. Constant-volume incendiary bombs can adjust temperature, pressure, and gas composition to simulate environmental changes and internal / external pressure fluctuations in airships during actual applications. They can also test the effectiveness of safety inhibitors in suppressing hydrogen combustion and deflagration, providing technical support for safe hydrogen application strategies in airships. However, existing constant-volume incendiary bombs cannot meet the requirements for pre-testing combustion characteristics at different risk points, cannot systematically assess the impact of fires at different locations on the overall structural safety, and lack the capability for targeted research on "high-risk points." Summary of the Invention

[0004] This invention provides a constant-volume incendiary bomb test system based on an airship configuration, which addresses the shortcomings of existing constant-volume incendiary bombs that cannot meet the requirements for pre-testing the combustion characteristics at different risk points, cannot systematically assess the impact of fires at different locations on the overall structural safety, and lack the ability to conduct targeted research on "high-risk points".

[0005] This invention provides a constant-volume incendiary bomb test system based on an airship configuration, comprising: a gas supply module, a constant-volume incendiary bomb, a schlieren optical module, and an ignition module.

[0006] The gas supply module includes a hydrogen storage device and an air storage device; the constant-volume incendiary bomb includes a main body, a first end cap, and a second end cap. The longitudinal cross-section of the main body is shaped like an airship. The first and second end caps are positioned opposite each other on both sides of the main body and enclose a sealed cavity. The first end cap has a first observation window, and the second end cap has a second observation window. Both the hydrogen storage device and the air storage device are connected to the sealed cavity; the schlieren optical module includes a schlieren light source, a first plane mirror, a first concave mirror, a second plane mirror, a second concave mirror, a blade, and a high-speed camera. The schlieren light source is positioned toward the first planar reflector, the first planar reflector is positioned toward the first concave mirror, the first concave mirror is positioned toward the first observation window, the second planar reflector is positioned toward the second concave mirror, the second concave mirror is positioned toward the second observation window, the high-speed camera is positioned toward the second planar reflector, and the blade is located between the high-speed camera and the second planar reflector; the ignition module includes multiple ignition devices, which are positioned at different locations on the constant-volume incendiary bomb, and the ignition end of each ignition device is located within the sealed cavity.

[0007] According to the constant-volume incendiary bomb test system based on the airship configuration provided by the present invention, multiple ignition devices are arranged at intervals along the circumference of the main body.

[0008] According to the constant-volume incendiary bomb test system based on the airship configuration provided by the present invention, the gas supply module further includes a gas mixing device, the hydrogen storage device and the air storage device are both connected to the gas mixing device, and the gas mixing device is connected to the sealed cavity.

[0009] According to the constant-volume incendiary bomb test system based on an airship configuration provided by the present invention, the outlet end of the hydrogen storage device is connected to a hydrogen pipe, the outlet end of the air storage device is connected to an air pipe, the inlet end of the gas mixing device is connected to a first air inlet pipe, the outlet end of the gas mixing device is connected to a mixed gas pipe, and the inlet end of the constant-volume incendiary bomb is connected to a second air inlet pipe; both the hydrogen pipe and the air pipe are connected to the first air inlet pipe, both the hydrogen pipe and the air pipe are connected to the second air inlet pipe, and the mixed gas pipe is connected to the second air inlet pipe.

[0010] According to the constant-volume incendiary bomb test system based on an airship configuration provided by the present invention, along the hydrogen flow direction, the hydrogen pipe is sequentially provided with a first pressure reducing valve, a first shut-off valve, a first check valve, and a second shut-off valve; along the air flow direction, the air pipe is sequentially provided with a second pressure reducing valve, a third shut-off valve, a second check valve, and a fourth shut-off valve; the first air inlet pipe is provided with a fifth shut-off valve; along the gas flow direction, the second air inlet pipe is sequentially provided with a sixth shut-off valve, a seventh shut-off valve, and a third check valve; and the mixed gas pipe is provided with an eighth shut-off valve.

[0011] According to the constant-volume incendiary bomb test system based on the airship configuration provided by the present invention, along the gas flow direction, a first pressure gauge and a second pressure gauge are sequentially provided on the second air inlet pipe, a ninth shut-off valve is provided at the inlet end of the first pressure gauge, and both the first pressure gauge and the second pressure gauge are located downstream of the connection position between the mixing gas pipe and the second air inlet pipe.

[0012] The constant-volume incendiary bomb test system based on an airship configuration provided by the present invention further includes: a vacuum pumping module, the vacuum pumping module comprising a vacuum pump, a first vacuum tube, a second vacuum tube, a third vacuum tube, and a fourth vacuum tube; a hydrogen tube connected to the vacuum pump via the first vacuum tube; an air tube connected to the vacuum pump via the second vacuum tube; a gas mixing device connected to the vacuum pump via the third vacuum tube; and a sealed cavity connected to the vacuum pump via the fourth vacuum tube; the first vacuum tube is provided with a tenth shut-off valve along the gas flow direction; the second vacuum tube is provided with an eleventh shut-off valve, a twelfth shut-off valve, and a fourth check valve; the third vacuum tube is provided with a thirteenth shut-off valve along the gas flow direction; and the fourth vacuum tube is provided with a fourteenth shut-off valve and a fifth check valve in sequence.

[0013] According to the constant-volume incendiary bomb test system based on the airship configuration provided by the present invention, the first vacuum tube is connected to the second vacuum tube, the second vacuum tube is provided with a first vacuum pressure gauge, and the third vacuum tube is provided with a second vacuum pressure gauge.

[0014] The constant-volume incendiary bomb test system based on an airship configuration provided by the present invention further includes a first exhaust pipe, a second exhaust pipe, and a third exhaust pipe. The first exhaust pipe is connected to both the hydrogen pipe and the air pipe. The second exhaust pipe is connected to the gas mixing device. The third exhaust pipe is connected to the sealed cavity. The first exhaust pipe is provided with a fifteenth shut-off valve, the second exhaust pipe is provided with a sixteenth shut-off valve, and the third exhaust pipe is provided with a seventeenth shut-off valve.

[0015] The constant-volume incendiary bomb test system based on an airship configuration provided by the present invention further includes: a data acquisition and processing module, wherein the gas supply module, the schlieren optical module and the ignition module are all communicatively connected to the data acquisition and processing module.

[0016] This invention provides a constant-volume incendiary bomb test system based on an airship configuration. By incorporating a gas supply module, a constant-volume incendiary bomb, a schlieren optical module, and an ignition module, the constant-volume incendiary bomb utilizes a sealed cavity mimicking the cross-sectional configuration of an airship. Combined with a multi-point ignition device, and in conjunction with the schlieren optical module and a high-speed camera, it can simultaneously acquire high spatiotemporal resolution images of the entire hydrogen deflagration flame propagation process at the structural scale of a real airship. This allows for the analysis of the disaster patterns inside the airship under different hazard conditions, enabling the observation and analysis of safety hazards arising from replacing helium with hydrogen in airships. The aim is to clarify the occurrence and development patterns of flames when a hydrogen-fuel mixture deflagrates inside an airship, providing technical support for the design of corresponding airship structures. This, in turn, provides a technical foundation for subsequent airship structural design, the formulation of operational safety procedures, and the design of measures to prevent deflagration.

[0017] 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. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of a constant-volume incendiary bomb test system based on an airship configuration provided in an embodiment of the present invention.

[0020] Figure 2 This is one of the schematic diagrams of a constant-volume incendiary bomb in a constant-volume incendiary bomb test system based on an airship configuration provided in an embodiment of the present invention.

[0021] Figure 3 This is the second schematic diagram of a constant-volume incendiary bomb in a constant-volume incendiary bomb test system based on an airship configuration provided in this embodiment of the invention.

[0022] Figure label: 100. Gas supply module; 110. Hydrogen storage device; 120. Air storage device; 130. Gas mixing device; 140. Hydrogen pipe; 141. First pressure reducing valve; 142. First shut-off valve; 143. First check valve; 144. Second shut-off valve; 150. Air pipe; 151. Second pressure reducing valve; 152. Third shut-off valve; 153. Second check valve; 154. Fourth shut-off valve; 160. First air inlet pipe; 161. Fifth shut-off valve; 170. Mixing gas pipe; 171. Eighth shut-off valve; 180. Second air inlet pipe; 181. Sixth shut-off valve; 182. Seventh shut-off valve; 183. Third check valve; 184. First pressure gauge; 185. Second pressure gauge; 186. Ninth shut-off valve.

[0023] 200. Constant volume incendiary bomb; 210. Main body; 220. First end cap; 230. Second end cap; 240. First observation window; 250. Second observation window; 260. Sealing ring.

[0024] 300, Schlieren optical module; 310, Schlieren light source; 320, first plane mirror; 330, first concave mirror; 340, second plane mirror; 350, second concave mirror; 360, blade edge; 370, high-speed camera.

[0025] 400. Ignition module; 410. High-voltage ignition device; 420. Ignition device.

[0026] 500. Data Acquisition and Processing Module.

[0027] 600. Vacuum module; 610. Vacuum pump; 620. First vacuum tube; 621. Tenth shut-off valve; 630. Second vacuum tube; 631. Eleventh shut-off valve; 632. Twelfth shut-off valve; 633. Fourth check valve; 634. First vacuum pressure gauge; 640. Third vacuum tube; 641. Eleventh shut-off valve; 650. Fourth vacuum tube; 651. Fourteenth shut-off valve; 652. Fifth check valve; 653. Second vacuum pressure gauge.

[0028] 700, First exhaust pipe; 710, Fifteenth shut-off valve.

[0029] 800, Second exhaust pipe; 810, Sixteenth shut-off valve.

[0030] 900, Third exhaust pipe; 910, Seventeenth shut-off valve. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0032] The following is combined Figures 1 to 3 This invention describes a constant-volume incendiary bomb test system based on an airship configuration.

[0033] See Figures 1 to 3 As shown, the constant-volume incendiary bomb 200 test system based on the airship configuration provided in this embodiment of the invention includes: a gas supply module 100, a constant-volume incendiary bomb 200, a schlieren optical module 300, and an ignition module 400.

[0034] The gas supply module 100 includes a hydrogen storage device 110 and an air storage device 120; the constant-volume incendiary bomb 200 includes a main body 210, a first end cap 220, and a second end cap 230. The longitudinal section of the main body 210 has a shape similar to an airship. The first end cap 220 and the second end cap 230 are disposed opposite to each other on both sides of the main body 210 and enclose a sealed cavity. The first end cap 220 is provided with a first observation window 240, and the second end cap 230 is provided with a second observation window 250. Both the hydrogen storage device 110 and the air storage device 120 are connected to the sealed cavity; the schlieren optical module 300 includes a schlieren light source 310, a first plane mirror 320, a first concave mirror 330, a second plane mirror 340, and a second concave mirror 350. 0. The blade 360 ​​and the high-speed camera 370 are positioned with the schlieren light source 310 facing the first plane mirror 320, the first plane mirror 320 facing the first concave mirror 330, the first concave mirror 330 facing the first observation window 240, the second plane mirror 340 facing the second concave mirror 350, the second concave mirror 350 facing the second observation window 250, the high-speed camera 370 facing the second plane mirror 340, and the blade 360 ​​being located between the high-speed camera 370 and the second plane mirror 340; the ignition module 400 includes multiple ignition devices 420, which are positioned at different locations on the constant-volume incendiary bomb 200, and the ignition end of the ignition device 420 is located within the sealed cavity.

[0035] The present invention provides a constant-volume incendiary bomb 200 test system based on an airship configuration. By setting up a gas supply module 100, a constant-volume incendiary bomb 200, a schlieren optical module 300, and an ignition module 400, the constant-volume incendiary bomb 200 adopts a sealed cavity with a cross-sectional configuration mimicking an airship. Combined with a multi-point ignition device 420, and with the schlieren optical module 300 and a high-speed camera 370 (with a read frame rate typically exceeding 10,000 frames per second), it can simultaneously acquire high spatiotemporal resolution images of the entire process of hydrogen deflagration flame propagation at the scale of a real airship structure. This allows for the analysis of the disaster patterns inside the airship under different hazard conditions, and the observation and analysis of safety hazards arising from replacing helium with hydrogen in airships. The aim is to clarify the occurrence and development patterns of flames when a hydrogen-mixed gas deflagration occurs inside an airship, providing technical support for the design of corresponding airship structures. This provides a technical foundation for subsequent airship structure design, the formulation of safety regulations, and the design of measures to prevent deflagration.

[0036] Specifically, the gas supply module 100 is used to premix hydrogen and air in a set ratio and then fill the sealed cavity to provide a combustible mixture for the combustion test. The gas supply module 100 includes a hydrogen storage device 110 and an air storage device 120 for storing hydrogen and air respectively. Both the hydrogen storage device 110 and the air storage device 120 can be containers with a certain pressure-bearing capacity, such as bottles or cans.

[0037] It should be noted that the premixed gas used should match the internal and external pressure difference conventionally used in airships in order to accurately reflect the actual situation during internal gas deflagration.

[0038] The constant-volume incendiary bomb 200 is used to create constant-volume conditions within its airship-like sealed cavity, carrying hydrogen-air premixed gas and igniting it to simulate the flame propagation process and pressure changes during deflagration inside a real airship, providing a controllable and observable combustion environment for the experiment. The constant-volume incendiary bomb 200 includes a main body 210 made of high-strength metal materials (such as steel), a first end cap 220, and a second end cap 230, which together form a sealed cavity mimicking the cross-section of an airship. The first end cap 220 and the second end cap 230 are respectively provided with a first observation window 240 and a second observation window 250, used in conjunction with the schlieren optical module 300 to form a convection optical path penetrating the sealed cavity, enabling the high-speed camera 370 to record the entire propagation process of the hydrogen deflagration flame within the airship configuration.

[0039] See Figure 2 As shown in the figure, as an example, in this embodiment, the first end cap 220 and the second end cap 230 are detachably connected to the corresponding side of the main body 210 through threaded connectors (such as screws, bolts, etc.), and a sealing ring 260 is provided between the first end cap 220 and the second end cap 230 and the main body 210 for sealing.

[0040] The schlieren optical module 300 is used to convert the density gradient changes generated by combustion within the sealed cavity into a visible light intensity distribution, which is then recorded in real time by a high-speed camera 370, thereby obtaining a high spatiotemporal resolution image of the hydrogen deflagration flame propagation process. The schlieren optical module 300 includes a schlieren light source 310, a first plane mirror 320, a first concave mirror 330, a second concave mirror 350, a second plane mirror 340, a knife edge 360, and a high-speed camera 370. The components are arranged according to a set optical path. During the experiment, the light beam passes through the first observation window 240 and the second observation window 250 in sequence to visualize the flame density field.

[0041] The ignition module 400 is used to generate electric sparks independently, synchronously, or sequentially at multiple preset locations within the sealed cavity to ignite a mixture of hydrogen and air, simulating real ignition sources at different risk points of the airship and triggering a deflagration test. The ignition module 400 includes a high-voltage ignition device 410 and multiple spark plugs (ignition devices 420). The spark plugs are connected to the high-voltage ignition device 410, which boosts the low-voltage control signal to a set voltage (e.g., 40KV to 50KV) and outputs it to each spark plug in a time-sharing manner, generating high-energy electric sparks at preset locations on the inner wall of the sealed cavity to ignite the hydrogen and air mixture.

[0042] In some embodiments, in order to reflect the actual conditions of the airship under different temperatures on the ground and in the air, a temperature control system can be further added to the outside of the constant volume incendiary bomb 200 to heat or cool the sealed cavity, so that the temperature of the test gas accurately matches the actual operating environment of the airship, and to evaluate the impact of temperature changes on the deflagration characteristics of hydrogen and the effect of inhibitors.

[0043] Furthermore, to investigate the inhibitor's effectiveness in suppressing the deflagration range of hydrogen (4% to 75%) while also considering the net buoyancy loss of the airship, the system can connect nitrogen, argon, or a small amount of propane or other inert / hydrocarbon-based inhibitors to the gas supply module 100. The concentration can be precisely adjusted using a partial pressure method, and deflagration suppression tests can be conducted within a constant-volume incendiary bomb 200. This quantifies the reduction in flame velocity, peak pressure, and deflagration limits caused by different inhibitors, providing data support for selecting the optimal suppression scheme for the hydrogen airship without significantly sacrificing lift. At this point, an inhibitor storage device (not shown in the figure) and control valves can be added, connected to the gas mixing device 130 along with the hydrogen storage device 110 and air storage device 120, to achieve quantitative mixing and precise supply of inert gases or hydrocarbon-based inhibitors.

[0044] In addition, a data acquisition and processing module 500 can be set up to synchronously acquire flame images recorded by the high-speed camera 370 and pressure changes within the cavity measured by the pressure sensor, and to store, process, and analyze the data to obtain combustion characteristic parameters such as flame propagation speed and pressure rise rate. The acquisition and processing module can be configured with a synchronization timing module to facilitate the recording of the ignition point and trigger the recording times of the pressure sensor and the schlieren optical module 300.

[0045] See Figure 3 As shown, according to some embodiments of the present invention, a plurality of ignition devices 420 are circumferentially spaced on the main body 210.

[0046] By arranging multiple ignition devices 420 at intervals on the main body 210, single-point or combined ignition at different locations can be achieved to simulate localized fires at various hazardous sources of the airship, study the interaction of multiple ignition nuclei and flame propagation paths, and provide a basis for assessing the risk of actual deflagration. Furthermore, precise ignition tests can be conducted on high-risk locations such as the air inlet, main gasbag valve, pod, and fan valve during actual airship use, systematically evaluating the flame development characteristics and destructive potential when hydrogen leakage occurs and combustion ensues in each part, providing direct data support for structural protection and safety procedure development.

[0047] As an example, in this embodiment, the ignition module 400 includes four ignition devices 420, which are respectively located at the inflation port, main airbag valve, pod, and fan valve during the actual use of the airship.

[0048] See Figure 1 As shown, according to some embodiments of the present invention, the gas supply module 100 further includes a gas mixing device 130, a hydrogen storage device 110 and an air storage device 120, both of which are connected to the gas mixing device 130, and the gas mixing device 130 is connected to a sealed cavity.

[0049] By setting up a gas mixing device 130, hydrogen and air can be introduced into the device in proportion to be fully mixed statically or dynamically before the mixed gas is filled into the sealed cavity, ensuring that the mixed gas composition is uniform and the concentration is accurate, thereby improving the repeatability of the test and the reliability of the flame propagation data.

[0050] Specifically, in the gas mixing device 130, hydrogen and air are injected simultaneously using the partial pressure method and allowed to stand for more than 30 minutes to make the concentration field uniform. Then, they are quantitatively delivered into the sealed cavity through a shut-off valve and other control mechanisms.

[0051] See Figure 1As shown, according to some embodiments of the present invention, the outlet end of the hydrogen storage device 110 is connected to a hydrogen pipe 140, the outlet end of the air storage device 120 is connected to an air pipe 150, the inlet end of the gas mixing device 130 is connected to a first air inlet pipe 160, the outlet end of the gas mixing device 130 is connected to a mixed gas pipe 170, and the inlet end of the constant volume incendiary bomb 200 is connected to a second air inlet pipe 180; both the hydrogen pipe 140 and the air pipe 150 are connected to the first air inlet pipe 160, both the hydrogen pipe 140 and the air pipe 150 are connected to the second air inlet pipe 180, and the mixed gas pipe 170 is connected to the second air inlet pipe 180.

[0052] By setting up hydrogen pipe 140, air pipe 150, mixing pipe 170, first air inlet pipe 160 and second air inlet pipe 180, it is possible to achieve independent delivery of hydrogen and air, and flexible switching between two modes: premixing or bypass direct charging. It can precisely control the gas flow rate and mixing ratio, prevent gas backflow, and ensure the safety, accuracy and repeatability of experimental gas mixing.

[0053] Specifically, in premixed mode, hydrogen flows sequentially through hydrogen pipe 140 and mixing pipe 170 before entering gas mixing device 130, and air flows sequentially through air pipe 150 and mixing pipe 170 before entering gas mixing device 130. Hydrogen and air enter gas mixing device 130 in a set ratio for premixing, and then finally enter the sealed cavity. In direct charging mode, hydrogen flows sequentially through hydrogen pipe 140 and second inlet pipe 180 before entering the sealed cavity, and air flows sequentially through air pipe 150 and second inlet pipe 180 before entering the sealed cavity, where they are directly mixed.

[0054] See Figure 1 As shown, according to some embodiments of the present invention, along the flow direction of hydrogen, a first pressure reducing valve 141, a first shut-off valve 142, a first check valve 143, and a second shut-off valve 144 are sequentially provided on the hydrogen pipe 140; along the flow direction of air, a second pressure reducing valve 151, a third shut-off valve 152, a second check valve 153, and a fourth shut-off valve 154 are sequentially provided on the air pipe 150; a fifth shut-off valve 161 is provided on the first inlet pipe 160; along the flow direction of gas, a sixth shut-off valve 181, a seventh shut-off valve 182, and a third check valve 183 are sequentially provided on the second inlet pipe 180; and an eighth shut-off valve 171 is provided on the mixed gas pipe 170.

[0055] By equipping the hydrogen pipe 140, air pipe 150, mixing pipe 170, first inlet pipe 160 and second inlet pipe 180 with valve mechanisms such as pressure reducing valves, shut-off valves or check valves, the output pressure of hydrogen and air can be independently adjusted and stabilized, and the airflow of each path can be switched on and off as needed. This enables reliable switching between premixing and direct charging modes, while effectively preventing gas backflow and ensuring that the gas mixing process is safe, the flow rate is controllable, and the test results are repeatable.

[0056] Specifically, in premixed mode, when hydrogen is introduced into the gas mixing device 130, the first pressure reducing valve 141, the first shut-off valve 142, the first check valve 143, and the second shut-off valve 144 on the hydrogen pipe 140, as well as the fifth shut-off valve 161 on the first air inlet pipe 160, are opened, and the bypass valve directly connecting the hydrogen pipe 140 to the second air inlet pipe 180 is closed. When air is introduced into the gas mixing device 130, the second pressure reducing valve 151, the third shut-off valve 152, the second check valve 153, and the fourth shut-off valve 154 on the air pipe 150 are opened, and the fifth shut-off valve 161 on the first air inlet pipe 160 is closed. The fifth shut-off valve 161 on the first air inlet pipe 160 closes the bypass valve that directly connects the air pipe 150 to the second air inlet pipe 180. After premixing, the eighth shut-off valve 171 on the mixed gas pipe 170, the seventh shut-off valve 182 and the third check valve 183 on the second air inlet pipe 180 are opened to fill the sealed cavity with the mixed gas. At the same time, the first shut-off valve 142 and the third shut-off valve 152 on the hydrogen pipe 140 and the air pipe 150 are closed to ensure that the mixed gas in the gas mixing device 130 enters the sealed cavity according to the preset ratio, thereby achieving precise premixing and gas distribution. In direct charging mode, the fifth shut-off valve 161 on the first air inlet pipe 160 and the eighth shut-off valve 171 on the mixing pipe 170 are closed to cut off the gas mixing device 130 passage; the first pressure reducing valve 141, the first shut-off valve 142, the first check valve 143, the second shut-off valve 144 on the hydrogen pipe 140, the sixth shut-off valve 181, the seventh shut-off valve 182, and the third check valve 183 on the second air inlet pipe 180 are opened, and the second pressure reducing valve 151, the third shut-off valve 152, the second check valve 153, and the fourth shut-off valve 154 on the air pipe 150 are opened at the same time. Hydrogen and air flow directly into the second air inlet pipe 180 through their respective pipelines and mix instantly in the sealed cavity to complete the direct charging gas distribution.

[0057] See Figure 1 As shown, according to some embodiments of the present invention, along the gas flow direction, a first pressure gauge 184 and a second pressure gauge 185 are sequentially provided on the second air inlet pipe 180. A ninth shut-off valve 186 is provided at the inlet end of the first pressure gauge 184. The first pressure gauge 184 and the second pressure gauge 185 are both located downstream of the communication position between the mixing pipe 170 and the second air inlet pipe 180.

[0058] By sequentially installing a first pressure gauge 184 and a second pressure gauge 185 on the second air inlet pipe 180, and installing a ninth shut-off valve 186 at the inlet end of the first pressure gauge 184, during inflation, according to Dalton's law of partial pressure, by observing the actual data of the first pressure gauge 184 and the second pressure gauge 185, the moment to stop the introduction of hydrogen or air can be determined, thereby precisely controlling the inflation volume.

[0059] The first pressure gauge 184 can be a pressure gauge with high resolution, while the second pressure gauge 185 can be a pressure gauge with average resolution. Through the cooperation of the first pressure gauge 184 and the second pressure gauge 185, precise mixing of hydrogen and air can be achieved.

[0060] See Figure 1 As shown, according to some embodiments of the present invention, the constant-volume incendiary bomb 200 test system based on an airship configuration further includes: a vacuum module 600, which includes a vacuum pump 610, a first vacuum tube 620, a second vacuum tube 630, a third vacuum tube 640, and a fourth vacuum tube 650. A hydrogen tube 140 is connected to the vacuum pump 610 through the first vacuum tube 620, an air tube 150 is connected to the vacuum pump 610 through the second vacuum tube 630, and a gas mixing device 130 is connected to the third vacuum tube. Vacuum tube 640 is connected to vacuum pump 610, and the sealed cavity is connected to vacuum pump 610 through fourth vacuum tube 650; a tenth shut-off valve 621 is provided on the first vacuum tube 620 along the gas flow direction; an eleventh shut-off valve 631, a twelfth shut-off valve 632 and a fourth check valve 633 are provided in sequence on the second vacuum tube 630; a thirteenth shut-off valve 641 is provided on the third vacuum tube 640 along the gas flow direction; and a fourteenth shut-off valve 651 and a fifth check valve 652 are provided in sequence on the fourth vacuum tube 650.

[0061] By setting up the vacuum module 600, the vacuum pump 610 can be turned on before the test, and the eighth to fourteenth shut-off valves 651 can be opened accordingly to evacuate the hydrogen pipe 140, air pipe 150, gas mixing device 130, and sealed cavity to a vacuum level of less than 0.18 kPa. Furthermore, the independently configured vacuum pipelines and valve arrangement allow for segmented evacuation, avoiding cross-contamination of residual combustible gases, ensuring the purity of the gas mixing starting point, and guaranteeing repeatable test data.

[0062] Specifically, before the test, all gas filling shut-off valves are closed, and the tenth shut-off valve 621, the eleventh shut-off valve 631, the twelfth shut-off valve 632, the thirteenth shut-off valve 641 and the fourteenth shut-off valve 651 are opened. The vacuum pump 610 is started, and the hydrogen pipe 140, the air pipe 150, the gas mixing device 130 and the sealed cavity are evacuated in sections to less than 0.18 kPa. Then, all vacuum shut-off valves are closed and the pump is stopped to complete the system purification and initial vacuum setting.

[0063] See Figure 1 As shown, according to some embodiments of the present invention, the first vacuum tube 620 is connected to the second vacuum tube 630, the second vacuum tube 630 is provided with a first vacuum pressure gauge 634, and the third vacuum tube 640 is provided with a second vacuum pressure gauge 653.

[0064] By installing a first vacuum pressure gauge 634 at the junction of the second vacuum tube 630 and the first vacuum tube 620, and a second vacuum pressure gauge 653 independently installed in the third vacuum tube 640, and simultaneously turning on the vacuum pump 610 and the tenth, eleventh, and twelfth shut-off valves 621, 631, and 632 before the test, the real-time vacuum levels of the hydrogen tube 140 and air tube 150 junction circuit and the gas mixing device 130 can be read respectively. This allows for accurate determination of whether each pipe section has reached less than 0.18 kPa, preventing local vacuum deficiencies caused by differences in pipe length or valve resistance, ensuring thorough system purification and the absence of residual combustible gas, and guaranteeing subsequent gas mixing accuracy and test repeatability.

[0065] See Figure 1 As shown, according to some embodiments of the present invention, the constant-volume incendiary bomb 200 test system based on the airship configuration further includes a first exhaust pipe 700, a second exhaust pipe 800, and a third exhaust pipe 900. The first exhaust pipe 700 is connected to both the hydrogen pipe 140 and the air pipe 150, the second exhaust pipe 800 is connected to the gas mixing device 130, and the third exhaust pipe 900 is connected to the sealed cavity. The first exhaust pipe 700 is provided with a fifteenth shut-off valve 710, the second exhaust pipe 800 is provided with a sixteenth shut-off valve 810, and the third exhaust pipe 900 is provided with a seventeenth shut-off valve 910.

[0066] By setting up a first exhaust pipe 700, a second exhaust pipe 800, and a third exhaust pipe 900, and installing corresponding shut-off valves on the exhaust pipes, the fifteenth shut-off valve 710, the sixteenth shut-off valve 810, or the seventeenth shut-off valve 910 can be selectively opened before or after the test to lead the residual gas in the hydrogen pipe 140, the air pipe 150, the gas mixing device 130, and the sealed cavity to the outside for safe discharge, avoiding cross-contamination of gases from different pipelines, ensuring system cleanliness, and improving gas distribution accuracy.

[0067] The following is a specific example illustrating the test procedure of the constant-volume incendiary bomb 200 test system based on an airship configuration provided by this invention. (See attached image) Figure 1 As shown.

[0068] Before the test, preparatory work is required to confirm the reliability of the technical condition of each component, whether all valves meet the sealing requirements, whether the pipelines are leak-free, and whether the parameters of the high-speed camera 370 are set correctly. The schlieren system should be adjusted so that the observation window glass of the constant-volume incendiary bomb 200 can be clearly projected onto the high-speed camera image.

[0069] During the pre-treatment stage of the experiment, it was confirmed that all valves were in the closed state. The tenth shut-off valve 621 and the fifteenth shut-off valve 710 were opened to allow the gas in the gas passage between the hydrogen storage device 110, the air storage device 120, and the gas mixing device 130 to be naturally vented to the outside atmosphere. After the venting was completed, the tenth shut-off valve 621 and the fifteenth shut-off valve 710 were closed. Then, the tenth shut-off valve 621, the eleventh shut-off valve 631, the twelfth shut-off valve 632, the fourth check valve 633, and the fifteenth shut-off valve 710 were opened, and the vacuum pump 610 was started to evacuate this part of the pipeline. During the evacuation, the reading of the first vacuum pressure gauge 634 was used to judge the vacuum value. When the vacuum value was less than 0.18 kPa, the tenth shut-off valve 621, the eleventh shut-off valve 631, the twelfth shut-off valve 632, the fourth check valve 633, and the fifteenth shut-off valve 710 were closed.

[0070] Open the seventeenth shut-off valve 910 to allow the residual gas in the gas mixing device 130 to naturally vent to atmospheric pressure, and then close the seventeenth shut-off valve 910. Open the eleventh shut-off valve 631, the twelfth shut-off valve 632, the thirteenth shut-off valve 641, and the fourth check valve 633, start the vacuum pump 610, and evacuate the gas mixing device 130. Use the reading of the first vacuum pressure gauge 634 to determine if the vacuum value is less than 0.18 kPa. When the vacuum value is less than 0.18 kPa, close the eleventh shut-off valve 631, the twelfth shut-off valve 632, the thirteenth shut-off valve 641, and the fourth check valve 633.

[0071] Open the seventeenth shut-off valve 910 to allow the residual gas in the sealed cavity to be naturally vented to the outside atmosphere, and then close the seventeenth shut-off valve 910. Open the fourteenth shut-off valve 651 and the fifth check valve 652, start the vacuum pump 610, and evacuate the sealed cavity. Use the reading of the second vacuum pressure gauge 653 to determine the vacuum level. When the vacuum value is less than 0.18 kPa, close the fourteenth shut-off valve 651 and the fifth check valve 652.

[0072] It should be noted that, in the above-mentioned natural venting or vacuuming processes, the residual gas must be discharged outdoors through pipelines to ensure safety during the process.

[0073] During the experiment, the partial pressures of hydrogen and air were calculated according to Dalton's law of partial pressures. Taking the premixing mode with hydrogen introduced first as an example, the first pressure reducing valve 141, the first shut-off valve 142, the first check valve 143, and the second shut-off valve 144 on the hydrogen pipe 140, as well as the fifth shut-off valve 161 on the first inlet pipe 160, were opened. The bypass valve connecting the hydrogen pipe 140 directly to the second inlet pipe 180 was closed, and hydrogen was introduced into the gas mixing device 130. The time to stop introducing hydrogen was determined by observing the data of the first pressure gauge 184 and the second pressure gauge 185. When the data of the first pressure gauge 184 and the second pressure gauge 185 reached the set value, the first pressure reducing valve 141, the first shut-off valve 142, the first check valve 143, the second shut-off valve 144, and the fifth shut-off valve 161 were closed. Based on the calculated air volume, the second pressure reducing valve 151, the third shut-off valve 152, the second check valve 153, and the fourth shut-off valve 154 on the air pipe 150, as well as the fifth shut-off valve 161 on the first air inlet pipe 160, are opened. The bypass valve connecting the air pipe 150 directly to the second air inlet pipe 180 is closed, and air is introduced into the gas mixing device 130. By observing the data of the first pressure gauge 184 and the second pressure gauge 185, the time to stop introducing air is determined. When the data of the first pressure gauge 184 and the second pressure gauge 185 reach the set value, the second pressure reducing valve 151, the third shut-off valve 152, the second check valve 153, the fourth shut-off valve 154, and the fifth shut-off valve 161 are closed.

[0074] After the required gas is introduced into the gas mixing device 130 using the partial pressure method, it is allowed to stand for at least 30 minutes to ensure uniform mixing. Generally, the mixed gas in the gas mixing device 130 should be sufficient to meet the gas requirements of three tests.

[0075] During the first test, the seventh shut-off valve 182, the eighth shut-off valve 171, the ninth shut-off valve 186, and the third check valve 183 were opened to fill the constant-volume incendiary bomb 200 in the shape of an airship with mixed gas. The time to stop filling was determined by observing the data of the first pressure gauge 184 and the second pressure gauge 185. When the data of the first pressure gauge 184 and the second pressure gauge 185 reached the set value, the seventh shut-off valve 182, the eighth shut-off valve 171, the ninth shut-off valve 186, and the third check valve 183 were closed.

[0076] Confirm that the data acquisition and processing module 500 and the high-speed camera 370 are working properly, and confirm that the ignition point is located at ignition position 1 (within). Figure 3Taking the ignition device 420 at the top of the main body 210 as an example, the ignition module 400 is controlled to ignite, and the ignition device 420 at the top of the main body 210 ignites the hydrogen mixture in the constant volume combustion bomb 200. During this process, the flame development process and pressure change curve are recorded synchronously by the data acquisition and processing module 500 and the high-speed camera 370. After the recording is completed, the seventeenth shut-off valve 910 is opened to allow the residual gas in the constant volume combustion bomb 200 to be naturally vented to the outside atmosphere, and then the seventeenth shut-off valve 910 is closed. The fourteenth shut-off valve 651 and the fifth check valve 652 are opened, and the vacuum pump 610 is started to evacuate the constant volume combustion bomb 200. When the reading of the second vacuum pressure gauge 653 is less than 0.18 kPa, the fourteenth shut-off valve 651 and the fifth check valve 652 are closed. Then, the constant volume combustion bomb 200 is purged with clean air.

[0077] The mixed gas stored in the gas mixing device 130 can be used for three tests. After the first test is completed, the second and third tests can be conducted. The above steps can be repeated for both the second and third tests.

[0078] After the third test, open the sixteenth shut-off valve 810 to allow the residual gas in the gas mixing device 130 to be naturally vented to the outside atmosphere, and then close the sixteenth shut-off valve 810. Repeat the above-mentioned vacuuming and gas mixing steps for the pipeline and gas mixing device 130, and conduct three more tests.

[0079] After confirming all tests at ignition point position 1, switch the ignition point to ignition point 2 and repeat the above tests; after confirming all tests at ignition point position 2, switch the ignition point to ignition point 3 and repeat the above tests; after confirming all tests at ignition point position 3, switch the ignition point to ignition point 4 and repeat the above tests.

[0080] The present invention provides a constant-volume incendiary bomb 200 test system based on an airship configuration. The constant-volume incendiary bomb 200, which imitates the shape of an airship, is used as a basis. With the help of a schlieren optical module 300, the flame state of the ignition on the inner wall of the cavity can be recorded. The internal pressure change can be recorded through a pressure sensor to assess the hazards when the flame occurs inside the airship.

[0081] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A constant-volume incendiary bomb test system based on an airship configuration, characterized in that, include: A gas supply module, comprising a hydrogen storage device and an air storage device; A constant-volume incendiary bomb includes a main body, a first end cap, and a second end cap. The longitudinal cross-section of the main body is shaped like an airship. The first end cap and the second end cap are disposed opposite each other on both sides of the main body and enclose a sealed cavity. The first end cap is provided with a first observation window, and the second end cap is provided with a second observation window. The hydrogen storage device and the air storage device are both connected to the sealed cavity. A schlieren optical module includes a schlieren light source, a first plane mirror, a first concave mirror, a second plane mirror, a second concave mirror, a knife edge, and a high-speed camera. The schlieren light source is positioned towards the first plane mirror, the first plane mirror is positioned towards the first concave mirror, the first concave mirror is positioned towards the first observation window, the second plane mirror is positioned towards the second concave mirror, the second concave mirror is positioned towards the second observation window, the high-speed camera is positioned towards the second plane mirror, and the knife edge is located between the high-speed camera and the second plane mirror. The ignition module includes multiple ignition devices, which are disposed at different positions on the constant-volume incendiary bomb, and the ignition end of each ignition device is located within the sealed cavity.

2. The constant-volume incendiary bomb test system based on an airship configuration according to claim 1, characterized in that, Multiple ignition devices are spaced apart circumferentially on the main body.

3. The constant-volume incendiary bomb test system based on an airship configuration according to claim 1, characterized in that, The gas supply module also includes a gas mixing device, and both the hydrogen storage device and the air storage device are connected to the gas mixing device, which is connected to the sealed cavity.

4. The constant-volume incendiary bomb test system based on an airship configuration according to claim 3, characterized in that, The outlet end of the hydrogen storage device is connected to a hydrogen pipe, the outlet end of the air storage device is connected to an air pipe, the inlet end of the gas mixing device is connected to a first air inlet pipe, the outlet end of the gas mixing device is connected to a mixed gas pipe, and the inlet end of the constant volume incendiary bomb is connected to a second air inlet pipe. The hydrogen pipe and the air pipe are both connected to the first air inlet pipe, the hydrogen pipe and the air pipe are both connected to the second air inlet pipe, and the mixed gas pipe is connected to the second air inlet pipe.

5. The constant-volume incendiary bomb test system based on an airship configuration according to claim 4, characterized in that, Along the flow direction of hydrogen, the hydrogen pipe is sequentially equipped with a first pressure reducing valve, a first shut-off valve, a first check valve, and a second shut-off valve; along the flow direction of air, the air pipe is sequentially equipped with a second pressure reducing valve, a third shut-off valve, a second check valve, and a fourth shut-off valve; the first air inlet pipe is equipped with a fifth shut-off valve; along the flow direction of gas, the second air inlet pipe is sequentially equipped with a sixth shut-off valve, a seventh shut-off valve, and a third check valve; and the mixed gas pipe is equipped with an eighth shut-off valve.

6. The constant-volume incendiary bomb test system based on an airship configuration according to claim 5, characterized in that, Along the gas flow direction, a first pressure gauge and a second pressure gauge are sequentially installed on the second air inlet pipe. A ninth shut-off valve is installed at the inlet end of the first pressure gauge. Both the first pressure gauge and the second pressure gauge are located downstream of the connection point between the mixing pipe and the second air inlet pipe.

7. The constant-volume incendiary bomb test system based on an airship configuration according to claim 4, characterized in that, Also includes: The vacuum module includes a vacuum pump, a first vacuum tube, a second vacuum tube, a third vacuum tube, and a fourth vacuum tube. The hydrogen tube is connected to the vacuum pump through the first vacuum tube, the air tube is connected to the vacuum pump through the second vacuum tube, the gas mixing device is connected to the vacuum pump through the third vacuum tube, and the sealed cavity is connected to the vacuum pump through the fourth vacuum tube. The first vacuum tube is equipped with a tenth shut-off valve along the gas flow direction; the second vacuum tube is equipped with an eleventh shut-off valve, a twelfth shut-off valve and a fourth check valve; the third vacuum tube is equipped with a thirteenth shut-off valve along the gas flow direction; and the fourth vacuum tube is equipped with a fourteenth shut-off valve and a fifth check valve in sequence.

8. The constant-volume incendiary bomb test system based on an airship configuration according to claim 7, characterized in that, The first vacuum tube is connected to the second vacuum tube, the second vacuum tube is equipped with a first vacuum pressure gauge, and the third vacuum tube is equipped with a second vacuum pressure gauge.

9. The constant-volume incendiary bomb test system based on an airship configuration according to claim 4, characterized in that, It also includes a first exhaust pipe, a second exhaust pipe and a third exhaust pipe, wherein the first exhaust pipe is connected to both the hydrogen pipe and the air pipe, the second exhaust pipe is connected to the gas mixing device, and the third exhaust pipe is connected to the sealed cavity; The first exhaust pipe is equipped with a fifteenth shut-off valve, the second exhaust pipe is equipped with a sixteenth shut-off valve, and the third exhaust pipe is equipped with a seventeenth shut-off valve.

10. The constant-volume incendiary bomb test system based on an airship configuration according to any one of claims 1 to 9, characterized in that, Also includes: The data acquisition and processing module is communicatively connected to the gas supply module, the schlieren optical module, and the ignition module.

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