An apparatus for high-temperature water entry simulation test of an aircraft

Abstract

The present invention discloses a device for simulating high-temperature water entry tests of aircraft, including molybdenum alloy bars, a launching device, a heating furnace, a high-pressure structure for simulating seawater, a wave simulator, a magnetic flaw detection device, a high-speed camera, a seawater pressurizing device, a seabed simulation device, and an observation matrix background board; this application can carry out more realistic sequential environmental tests for different links that an aircraft crash accident may encounter, such as high-temperature and high-speed falling, water entry, and sinking to the seabed; the simulation links are more comprehensive, the simulation scenarios are more realistic, and the connection between different scenarios is closer; this application simulates the ocean state more comprehensively. This patent comprehensively considers various factors such as seawater composition, temperature, sea surface waves, seabed ocean currents, seabed pressure, and seabed ground, and simulates the ocean state more comprehensively. The seabed simulation has the ability to conduct long-term tests.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft simulation tests, and particularly to a device for simulating the high-temperature water entry of an aircraft. Background Art

[0002] During the launch or return process of an aircraft, accidents may occur, causing aircraft components such as radioactive isotope heat sources and fuel tanks to fall into the deep sea at a high-speed flight state.

[0003] When aircraft products such as radioactive isotope heat sources fall into the deep sea at a high speed, it may trigger leakage accidents of radioactive products. Moreover, heat source products generate heat by themselves, combined with the high-speed aerodynamic heat during the fall through the atmosphere, and the complex water entry process, forming a complex high-temperature (product heat) - liquid (falling into the sea) - solid (product) - gas (seawater encountering high temperature) - impact (high-speed impact at the moment of water entry) scenario. This poses a great hidden danger to product safety.

[0004] Currently, domestic and foreign institutions have fully recognized the importance of the high-temperature water entry scenario of aircraft for the safety evaluation of aircraft products. The experimental requirements based on the simulation of the high-temperature water entry scenario of aircraft are also becoming increasingly strong.

[0005] Research Status at Home and Abroad

[0006] The problem of water entry has always been a hot scientific issue that researchers at home and abroad are concerned about, such as the cavitation problem derived from different shapes and surface states of products, and the water entry resistance problem, etc. However, the research on the problem of high-temperature water entry is relatively less. Scholars such as Li Jiachuan from Harbin Institute of Technology carried out experimental research on the characteristics of high-temperature sphere water entry for underwater drag reduction. Using the independently developed test system, the water entry observation below 1000°C can be achieved. However, this system does not evaluate the safety analysis of products, nor does it analyze working conditions such as different ocean states, water entry states, and product states after water entry.

[0007] Existing Technical Solutions

[0008] Doctoral Thesis "Research on Multiphase Flow and Underwater Drag Reduction Characteristics of High-Temperature Sphere Water Entry" - Li Jiachuan, June 2019. The relevant test equipment uses a heating furnace to heat the product to 1000°C. The simulation test piece is designed as a sphere. The high-temperature sphere water entry is realized through an electromagnetic release device. High-speed photography is used to observe the water entry cavitation and the falling speed. The water tank is made of glass.

[0009] The above technical means can reproduce the free water entry state of spherical and small-mass products at a temperature of 1000°C. Through the above technical means, the analysis of the water entry and underwater drag reduction characteristics of high-temperature spheres can be realized, which has certain significance. However, there are also certain limitations, specifically manifested in:

[0010] 1. From the perspective of the safety analysis of aircraft products, the working conditions simulated by this system are insufficient.

[0011] a) This system can simulate the water entry process under high-temperature scenarios for analysis. However, during the water entry process of aircraft products, their attitudes are affected by the sea surface conditions, and their falling situations are affected by the flow of ocean currents at the seabed, etc. Therefore, for the simulation of seawater, the above system is not sufficient.

[0012] b) During the falling process of the product, it is affected by different flight states, and the falling speeds are different, which determine the temperature, speed, etc. of the product when it enters the water. These states affect the safety of the product. The above system cannot simulate this scenario.

[0013] c) After the product enters the water and falls to the seabed, the seabed surface is uneven. And after sinking to the seabed, it is subject to long-term seawater corrosion, wave scouring, seawater pressure, etc., which affect the safety state. The above system cannot simulate this scenario.

[0014] 2. From the analysis of system indicators, the indicators simulated by this system need to be improved.

[0015] a) Traditional technologies use the magnetic attraction method and can only conduct research on small-mass products, and cannot effectively cover the simulation of the high-temperature water entry process of aircraft products and their components.

[0016] b) Traditional technologies can simulate a temperature of 1000°C, but the temperature range is limited. In order to accurately simulate the high-temperature state when relevant aircraft products fall rapidly, the simulation temperature should be increased. At the same time, for the traditional heating method, how to install the product on the magnetic attraction device at high temperature after heating is not clear in technical means, which brings certain difficulties to the operation of the experiment.

[0017] 3. The process detection technology needs to be improved.

[0018] Traditional technologies use high-speed photography technology to observe phenomena such as water entry cavitation at the moment of water entry, but it is not comprehensive. Specifically manifested as:

[0019] a) When the product falls into the deep sea, the landing point is related to the safety of the nearby area, and it is of great significance for salvage, evacuation of nearby residents, safety assessment of the product and subsequent handling, etc. Traditional technologies have not analyzed the relevant landing points.

[0020] b) According to traditional technologies, after the product enters the water and its state stabilizes, the product can be taken out for product state analysis. This belongs to post-detection. Since the temperature of the product is high before water entry and there is a rapid water entry displacement process, it is difficult to install high-temperature sensors inside and outside the product to detect the product state. Therefore, a comprehensive detection ability should be established to analyze the water entry process and detailedly master the product state during the high-temperature water entry process of the aircraft.

[0021] Therefore, it is necessary to develop a device for simulating the high-temperature water entry test of an aircraft to solve the above problems. Summary of the Invention

[0022] The purpose of the present invention is to design a device for simulating the high-temperature water entry test of an aircraft to solve the above problems.

[0023] The present invention realizes the above purpose through the following technical solutions:

[0024] A device for simulating the high-temperature water entry test of an aircraft, comprising:

[0025] A molybdenum alloy rod for simulating the high-temperature heating of a test piece; the molybdenum alloy rod is connected to the test piece;

[0026] A launching device for adjusting the launching attitude of the test piece and launching it; the test piece is installed on the launching device;

[0027] A heating furnace; a retractable sealing cover plate for opening the bottom of the heating furnace is provided at the bottom of the heating furnace; the molybdenum alloy rod, the test piece, and the launching device are all placed in the heating furnace;

[0028] A seawater simulation high-pressure structure; the upper end of the seawater simulation high-pressure structure is connected to the lower end of the heating furnace; simulated seawater is provided in the seawater simulation high-pressure structure;

[0029] A wave simulator, a magnetic flaw detection device, and a high-speed camera; the wave simulator, the magnetic flaw detection device, and the high-speed camera are all placed in the seawater simulation high-pressure structure;

[0030] A seawater pressurizing device for generating a high-pressure effect; the acting end of the seawater pressurizing device is placed in the seawater simulation high-pressure structure;

[0031] A seabed simulation device; the seabed simulation device is placed at the bottom inside the seawater simulation high-pressure structure;

[0032] An observation matrix background board; the observation matrix background board is vertically installed on one side inside the seawater simulation high-pressure structure. The device for simulating the high-temperature water entry test of an aircraft further includes a seawater simulator, and the water outlet of the seawater simulator is communicated with the inside of the seawater simulation high-pressure structure.

[0033] Specifically, the launching device includes:

[0034] A hydraulic device; the hydraulic device is installed on the top of the heating furnace, and the telescopic end of the hydraulic device is connected to the upper end of the molybdenum alloy rod; the lower end of the molybdenum alloy rod is connected to the upper end of the test piece;

[0035] Two adjustable brackets for adjusting the launch attitude of the simulated test piece; the two adjustable brackets are relatively arranged on the two side walls of the heating furnace, and the bottom of the simulated test piece is placed above the opposite ends of the two adjustable brackets.

[0036] Specifically, the adjustable bracket includes a baffle plate and a cylinder. The first end of the baffle plate is hinged to the inner wall of the heating furnace, the fixed end of the cylinder is hinged to the inner wall of the heating furnace, and the piston of the cylinder is hinged below the second end of the baffle plate.

[0037] Further, the adjustable bracket further includes a piston start position detection sensor, a piston end position detection sensor, and a pressure sensor. The piston start position detection sensor is installed on the cylinder near its fixed end, the piston end position detection sensor is installed on the cylinder far from its fixed end, and the pressure sensor is installed at the position where the simulated test piece is placed above the baffle plate.

[0038] Specifically, a chromatograph is installed on the adjustable bracket. Correspondingly, helium is provided in the heating furnace.

[0039] Specifically, the seawater pressurizing device includes a pressure conduit and an air compressor. The outlet of the air compressor is connected to the first end of the pressure conduit, and the second end of the pressure conduit is placed in the upper part of the seawater simulated high-pressure structure.

[0040] Preferably, the seawater simulated high-pressure structure is placed underground.

[0041] Specifically, a dot matrix including coordinates is set on the observation matrix background board.

[0042] The beneficial effects of the present invention are as follows:

[0043] This application can carry out more realistic sequential environmental tests for different links that an aircraft crash accident may encounter, such as high-temperature and high-speed falling, entering water, and sinking to the seabed. Compared with the traditional technology, the simulation links are more comprehensive, the simulation scenarios are more realistic, and the connection between different scenarios is closer.

[0044] This application heats the simulated test piece through molybdenum alloy bars and a heating furnace, providing a technical solution with higher temperature simulation and greater thrust, and having higher operational safety between the heating and launching links.

[0045] This application simulates the ocean state more comprehensively. This patent comprehensively considers various factors such as seawater composition, temperature, sea surface waves, undersea ocean currents, undersea pressure, and seabed ground, and simulates the ocean state more comprehensively. The seabed simulation has the ability to conduct long-term tests.

[0046] This application has more comprehensive testing means. It not only utilizes chromatographs and high-speed cameras, but also adds the design of an observation matrix background board and configures technical means such as magnetic flaw detection. During the detection, not only the leakage state, structural state, and appearance state of the product are concerned, but also the position information of the product is obtained by using the observation matrix background board in cooperation with the high-speed camera, providing technical support for subsequent salvage, accident assessment, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 It is a schematic diagram of typical characteristic links in the process of warm water inlet;

[0048] Figure 2 It is a schematic structural diagram of the present invention;

[0049] Figure 3 It is a schematic structural diagram of the adjustable bracket in the present invention;

[0050] Figure 4 It is a block diagram of the operation principle of the adjustable bracket in the present invention;

[0051] In the figure: 1 - hydraulic device; 2 - molybdenum alloy bar; 3 - heating furnace; 4 - simulation test piece; 5 - adjustable bracket; 51 - cylinder, 52 - piston initial position detection sensor, 53 - piston end position detection sensor, 54 - piston, 55 - hinge, 56 - pressure sensor, 57 - baffle plate; 6 - chromatograph; 7 - pressure conduit; 8 - air compressor; 9 - cover plate; 10 - wave simulator; 11 - observation matrix background board; 12 - high-speed camera; 13 - seawater simulation high-pressure structure; 14 - magnetic flaw detection device; 15 - seawater simulator; 16 - seabed simulation device. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0052] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Usually, the components of the embodiments of the present invention described and illustrated in the accompanying drawings here can be arranged and designed in various different configurations.

[0053] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed present invention, but merely represents selected embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0054] It should be noted that: similar reference numerals and letters denote similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0055] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by terms such as "upper", "lower", "inner", "outer", "left", "right", etc. is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the inventive product is customarily placed during use, or the orientation or positional relationship commonly understood by those skilled in the art. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0056] In addition, terms such as "first", "second", etc. are only used for distinguishing descriptions and should not be construed as indicating or implying relative importance.

[0057] In the description of the present invention, it should also be noted that unless otherwise clearly specified and limited, terms such as "set", "connect" should be understood in a broad sense. For example, "connect" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0058] The following will describe in detail the specific embodiments of the present invention with reference to the drawings.

[0059] During the launch or return process of the aircraft, accidents may occur, causing aircraft components such as radioactive isotope heat sources and fuel tanks to fall into the deep sea at a high-speed flight state. The present invention analyzes the typical characteristic links in this process and conducts state simulations for the falling process, the water entry process, and the seabed state, as Figure 1 shown.

[0060] In the above typical characteristic links of the aircraft, the typical environmental scenarios that need to be experienced include:

[0061] 1. Falling process: During the high-speed flight of the aircraft, it may face aerodynamic heat (some products have self-heating) and a high-speed flight state.

[0062] 2. Water entry process: The aircraft flies at a high temperature and high speed and falls into the sea surface. At this time, the temperature of the sea water, the state of the sea surface (waves), different falling angles of the aircraft cause different sea surface impact forces, the boiling effect of high temperature and sea water, and the superimposed cavitation effect of high-speed water entry, etc.

[0063] 3. Seabed state: The aircraft sinks to the seabed at a certain speed, and the structural state of the seabed ground, the long-term seabed temperature, the sea water composition, the ocean current state, the water pressure, etc. have an impact on the structural safety of the product.

[0064] Typical environmental elements include:

[0065] 1. Falling process: High-temperature and high-speed environmental loading;

[0066] 2. Water entry process: Simulation of incident angle, seawater temperature, and sea surface wave state;

[0067] 3. Seabed state: Simulation of seabed structure state and long-term seabed environment.

[0068] The information that can be verified and obtained through the high-temperature water entry scenario test includes:

[0069] 1. When the product goes through the above typical characteristic links, the safety, structural integrity, etc. of the product during and after the process;

[0070] 2. During the high-temperature water entry process, the high-temperature cavitation phenomenon, the influence of different incident angles, speeds, sea surface states, etc. on the product's landing point and falling attitude, etc.

[0071] As Figure 2 shown, based on the above simulation requirements, the present invention provides a device for high-temperature water entry simulation test of an aircraft, including:

[0072] A molybdenum alloy rod 2 for simulating the high-temperature heating of the test piece 4; the molybdenum alloy rod 2 is connected to the test piece 4;

[0073] A launching device for adjusting the launching attitude of the test piece 4 and launching it; the test piece 4 is installed on the launching device;

[0074] A heating furnace 3; a retractable sealing cover plate 9 for opening the bottom of the heating furnace 3 is provided at the bottom of the heating furnace 3; the molybdenum alloy rod 2, the test piece 4, and the launching device are all placed inside the heating furnace 3;

[0075] A seawater simulation high-pressure structure 13; the seawater simulation high-pressure structure 13 is placed underground; the upper end of the seawater simulation high-pressure structure 13 is connected to the lower end of the heating furnace 3; simulated seawater is provided inside the seawater simulation high-pressure structure 13;

[0076] A wave simulator 10, a magnetic flaw detection device 14, and a high-speed camera 12; the wave simulator 10, the magnetic flaw detection device 14, and the high-speed camera 12 are all placed inside the seawater simulation high-pressure structure 13;

[0077] A seawater pressurizing device for generating a high-pressure effect; the seawater pressurizing device includes a pressure conduit 7 and an air compressor 8, the outlet of the air compressor 8 is connected to the first end of the pressure conduit 7, and the second end of the pressure conduit 7 is placed in the upper part inside the seawater simulation high-pressure structure 13;

[0078] Submarine simulation device 16; the submarine simulation device 16 is placed at the bottom inside the seawater simulation high-pressure structure 13; a dot matrix containing coordinates is set on the observation matrix background board 11;

[0079] Observation matrix background board 11; the observation matrix background board 11 is vertically installed on one side inside the seawater simulation high-pressure structure 13.

[0080] The device for the high-temperature water entry simulation test of the aircraft also includes a seawater simulator 15, and the water outlet of the seawater simulator 15 is communicated with the inside of the seawater simulation high-pressure structure 13.

[0081] The launching device includes:

[0082] Hydraulic device 1; the hydraulic device 1 is installed on the top of the heating furnace 3, and the telescopic end of the hydraulic device 1 is connected to the upper end of the molybdenum alloy bar 2; the lower end of the molybdenum alloy bar 2 is connected to the upper end of the simulation test piece 4;

[0083] Two adjustable brackets 5 for adjusting the launching attitude of the simulation test piece 4; the two adjustable brackets 5 are oppositely arranged on the two side walls of the heating furnace 3, and the bottom of the simulation test piece 4 is placed above the opposite ends of the two adjustable brackets 5. A chromatograph 6 is installed on the adjustable bracket 5. Correspondingly, helium is provided inside the heating furnace 3. Helium with a certain pressure is filled inside the heating furnace 3. When the device is damaged and ruptured, the helium will escape from the gap opening and be captured by the gas chromatograph 6, so as to locate the leakage position, and the minimum leakage rate that can be detected reaches 10^-10 Pa·m³ / s.

[0084] Such as Figure 3 And 4As shown in the figure, the adjustable bracket 5 includes a baffle 57, a cylinder 51, a piston initial position detection sensor 52, a piston end position detection sensor 53, and a pressure sensor 56. The first end of the baffle 57 is hinged to the inner wall of the heating furnace 3, the fixed end of the cylinder 51 is hinged to the inner wall of the heating furnace 3, and the piston 54 of the cylinder 51 is hinged to the lower part of the second end of the baffle 57 through a hinge 55. The piston initial position detection sensor 52 is installed on the cylinder 51 near its fixed end, the piston end position detection sensor 53 is installed on the cylinder 51 far from its fixed end, and the pressure sensor 56 is installed at the position where the simulated test piece 4 is placed above the baffle 57. In some embodiments, a processor is cooperatively provided for signal acquisition and regulation; initially, the piston 54 is in the extended state and the baffle 57 is horizontally placed. A pressure sensor 56 is installed on the baffle 57. When the pressure received by the baffle 57 increases (the hydraulic device 1 acts on the simulated test piece 4 through the molybdenum alloy bar 2 and the pressure reaches the established condition), the cylinder 51 controller issues an instruction, and the piston 54 of the cylinder 51 quickly retracts, driving the baffle 57 to retract. Then, the simulated test piece 4 falls after being separated from the blockage of the lower baffle 57. After a certain time or when the pressure decreases to a certain value, the cylinder 51 controller issues an instruction, and the piston 54 of the cylinder 51 quickly extends, driving the baffle 57 to extend and restoring the initial state. Position sensors installed at other positions of the piston 54 of the cylinder 51 can control the stroke length of the piston 54, thereby controlling the extension angle of the baffle 57.

[0085] The non-working modes of this application include:

[0086] 1. Simulation and observation of typical falling links

[0087] Thermal loading method:

[0088] The heating furnace 3 is used to heat the simulated test piece 4. The heating furnace 3 adopts a sealed structure design (the bottom is sealed by a cover plate 9 and is opened during launch); molybdenum alloy bars 2 (including silicon molybdenum bar materials) are selected as heating elements, and the maximum heating temperature can reach 1600°C. When designing the heating furnace 3, the elongation effect of the heating rods under heating in a large temperature range should be considered, and sufficient distances should be left between the heating rods and the furnace bottom during design.

[0089] Speed and angle simulation:

[0090] A hydraulic device 1 is used to provide thrust to simulate the high-speed falling state of the test piece 4. Compared with traditional forms such as air cannons, it can provide greater thrust. For the force transmission device, the present invention proposes to select molybdenum alloy bars 2 (TZM alloy). According to the data (Research Status of High Temperature Properties of TZM Alloy, Tan Jiangfei et al., Materials Review), the tensile strength and yield strength of TZM alloy both exceed 100 MPa at 1400 °C, and both exceed 50 MPa at 1600 °C. When designing the thrust according to the molybdenum alloy bar 2 with φ = 100 mm, the transmitted thrust can exceed 20 tons. At the same time, by adjusting the contact position and angle with the test piece, etc., and cooperating with the adjustable bracket 5, the simulation of the test piece launch at different speeds and angles can be realized.

[0091] Product state detection in typical falling links:

[0092] It is designed to use detection means such as a chromatograph 6 to detect the product state at high temperatures, such as the sealing state. A certain component of gas (helium) is filled into the sealed product. When the product is heated to the target temperature, detection instruments such as the chromatograph 6 arranged at the mouth of the heating furnace 3 can detect the leakage state of the product.

[0093] 2. Simulation and observation of typical water entry links

[0094] Simulation of sea surface state:

[0095] The seawater simulation high-pressure structure 13 is buried deep underground, and such a design is more conducive to safety under high-pressure ocean conditions. The sea surface state is realized through a wave simulator 10, which is a multi-group loop design. Different components (including chemical substances such as CL and Mg), seawater with simulated temperature and pressure are added to the seawater simulator 15 in advance. Through devices such as an air compressor 8, the circulating simulated seawater is injected into the seawater simulation high-pressure structure 13 through the wave simulator 10, and the flow rate of the seawater is adjusted by pressure to form simulated waves.

[0096] Product state detection in typical water entry links:

[0097] When the test piece at high temperature and high speed shoots into the sea surface, the high-speed object will form cavities with the seawater, inducing the cavity effect and affecting the water entry attitude of the test piece. Superimposed with the strong boiling effect of high temperature encountering water, it constitutes its unique high-temperature water entry link, which has a great impact on the product structure, attitude, incident speed, etc. In order to observe the relevant states, the relevant detection links and means are optimized; a high-speed camera 12 is selected to perform real-time imaging observation on the product state under cavity and boiling phenomena. When designing, the observation elements are clarified and the observation technology is optimized.

[0098] An observation matrix background board 11 is designed. The background board is composed of a dot matrix with coordinates. By analyzing the state of the product during the water entry process, after high-temperature water entry, the product experiences the high-temperature boiling effect and the cavitation effect, and the surface temperature of the product drops rapidly. The product enters a relatively stable sinking state. Therefore, by arranging the observation matrix background board 11, the change in the falling attitude of the product and the change in position during the falling process can be observed, providing technical support for the state process detection of the product and the judgment of the deep-sea falling position.

[0099] 3. Simulation and Observation of Typical Seabed Conditions

[0100] Simulation of seabed conditions:

[0101] The simulation design of seabed conditions includes the temperature, ocean current, and composition of seawater at the seabed; the simulation of deep-sea pressure and the simulation of the seabed ground.

[0102] The simulation of the temperature, ocean current, and composition of seawater at the seabed is similar to the simulation of ocean waves and is achieved by using a seawater simulator 15. The difference is that the present invention provides a long-term seabed simulation environment, and the state of the test piece 4 sinking into the seabed for a long time can be simulated through cyclic tests.

[0103] The process of simulating deep-sea pressure is as follows: When the product enters the water, the cover plate is sealed. At the same time, an air compressor 8 is used to input pressure to the water surface through a pressure conduit 7 and transfer the pressure to the seawater to achieve the purpose of simulating deep-sea pressure.

[0104] For the simulation of the seabed ground, the present invention provides different materials, such as different seabed simulation designs of sand, rock, soft sea surface, etc., for selection according to different requirements during the test.

[0105] Detection of products under typical seabed conditions:

[0106] In order to observe the state of the test piece on the seabed for a long time, the present invention designs and adopts a variety of technical means such as image detection, a chromatograph 6, and a pre-embedded magnetic flaw detection device 14 to observe the state of the product in real time.

[0107] The above is only the preferred embodiment of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the technical principle of the present invention, several improvements and retouches can be made, and these improvements and retouches should also be regarded as the protection scope of the present invention.

Claims

1. An apparatus for simulating the high-temperature water entry test of an aircraft, characterized in that Comprising: A molybdenum alloy rod for high-temperature heating of the simulated test piece; The molybdenum alloy rod is connected to the simulated test piece; A launching device for adjusting the launching attitude of the simulated test piece and launching it; the simulated test piece is installed on the launching device; A heating furnace; a retractable sealing cover plate for opening the bottom of the heating furnace is provided at the bottom of the heating furnace; the molybdenum alloy rod, the simulated test piece, and the launching device are all placed inside the heating furnace; A seawater simulation high-pressure structure; the upper end of the seawater simulation high-pressure structure is connected to the lower end of the heating furnace; simulated seawater is provided inside the seawater simulation high-pressure structure; A wave simulator, a magnetic flaw detection device, and a high-speed camera; the wave simulator, the magnetic flaw detection device, and the high-speed camera are all placed inside the seawater simulation high-pressure structure; A seawater pressurizing device for generating a high-pressure effect; the acting end of the seawater pressurizing device is placed inside the seawater simulation high-pressure structure; A seabed simulation device; the seabed simulation device is placed at the bottom inside the seawater simulation high-pressure structure; An observation matrix background board; the observation matrix background board is vertically installed on one side inside the seawater simulation high-pressure structure.

2. The device for simulating high-temperature water entry test of an aircraft according to claim 1, wherein, The device for the high-temperature water entry simulation test of the aircraft further includes a seawater simulator, and the water outlet of the seawater simulator is communicated with the inside of the seawater simulation high-pressure structure.

3. The device for simulating high-temperature water entry test of an aircraft according to claim 1, wherein, The launching device includes: A hydraulic device; the hydraulic device is installed on the top of the heating furnace, and the telescopic end of the hydraulic device is connected to the upper end of the molybdenum alloy rod; the lower end of the molybdenum alloy rod is connected to the upper end of the simulated test piece; Two adjustable brackets for adjusting the launching attitude of the simulated test piece; the two adjustable brackets are oppositely arranged on the two side walls of the heating furnace, and the bottom of the simulated test piece is placed above the opposite ends of the two adjustable brackets.

4. The device for simulating high-temperature water entry test of an aircraft according to claim 3, wherein, The adjustable bracket includes a blocking plate and a cylinder. The first end of the blocking plate is hinged to the inner wall of the heating furnace, the fixed end of the cylinder is hinged to the inner wall of the heating furnace, and the piston of the cylinder is hinged below the second end of the blocking plate.

5. The device for simulating the high-temperature water entry test of an aircraft according to claim 4, characterized in that, The adjustable bracket further includes a piston start position detection sensor, a piston end position detection sensor, and a pressure sensor. The piston start position detection sensor is installed on the cylinder near its fixed end, the piston end position detection sensor is installed on the cylinder far from its fixed end, and the pressure sensor is installed at the position where the simulated test piece is placed above the blocking plate.

6. The device for simulating the high-temperature water entry test of an aircraft according to claim 3, characterized in that, A chromatograph is installed on the adjustable bracket. Correspondingly, helium is provided inside the heating furnace.

7. The device for simulating high-temperature water entry test of an aircraft according to claim 1, characterized in that, The seawater pressurizing device includes a pressure conduit and an air compressor. The outlet of the air compressor is connected to the first end of the pressure conduit, and the second end of the pressure conduit is placed in the upper part inside the seawater simulation high-pressure structure.

8. A device for simulating the high-temperature water entry test of an aircraft, as claimed in claim 1, wherein The seawater simulation high-pressure structure is placed underground.

9. The device for simulating high-temperature water entry test of an aircraft according to claim 1, characterized in that, The observation matrix background board is provided with a dot matrix including coordinates.

Images