A ground flight test system for hypersonic vehicle design verification

Abstract

The application discloses a ground flight test system for hypersonic vehicle design verification, which is used for hypersonic vehicle design verification and comprises a test piece platform, a vacuum electromagnetic ejection section, a vacuum electromagnetic acceleration section, a hypersonic flight test section and an electromagnetic aerodynamic deceleration section. The hypersonic vehicle to be tested is installed on the test piece platform. The first end of the vacuum electromagnetic acceleration section, the first end of the hypersonic flight test section and the first end of the electromagnetic aerodynamic deceleration section are respectively provided with a diaphragm. The application can continuously, stably and accurately simulate the high-altitude environmental conditions of the actual flight corridor, has a large adjustment range of total temperature, total pressure and Mach number, and can keep the environmental conditions of each functional section of the ground flight test system for hypersonic vehicle design verification independent of each other and not affect the test.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aerospace, and particularly relates to a ground flight test system for hypersonic vehicle design verification. BACKGROUND

[0002] Hypersonic vehicle is a kind of vehicle such as aircraft, missile, etc. with flight speed exceeding 5 times the speed of sound, which has the characteristics of rapid penetration and precise attack, and has huge military value and potential economic benefits. At present, the wide-range hypersonic vehicle, hypersonic vehicle integration device, hypersonic ramjet engine, and core components such as inlet and combustion chamber in hypersonic vehicle have rapidly become the research focus in the field of hypersonic technology.

[0003] Hypersonic flight test is a key technical means to carry out the design feasibility and performance verification of hypersonic vehicles and their key components in actual high-altitude environment, which requires that the test equipment can meet the following requirements: it can simulate a high-altitude environment with good uniformity and purity; it can accurately simulate the flight conditions of the test piece under actual high-altitude environment, with total pressure higher than 17 MPa and total temperature higher than 2700K; and it can obtain the pressure and temperature of the vehicle and its external flow field structure under real flight conditions.

[0004] At present, there are two ways to carry out verification tests of hypersonic vehicles and their key components at home and abroad. One is to use external power boost to push the test piece to the predetermined height and speed; the other is to use a free jet ground test system to simulate high-altitude environment of hypersonic air inflow. The hypersonic flight test by boost type has high cost and limited research and measurement means, so the effective test data are limited. The core equipment of free jet verification test is a pulse shock tunnel. The pulse shock tunnel has conventional driving modes such as detonation driving, free piston driving and heated light gas driving, and its inherent defect is that the high total temperature and high total pressure of the driven section of the test gas will cause dissociation reaction, resulting in a decrease in oxygen content of the test gas flow, and the existence of nitrogen oxide and oxygen atom pollutants, which cannot simulate the pure air of actual high-altitude environment. At the same time, the von Neumann high pressure point of the detonation wave head limits the total pressure of the test gas formed by the reflection of the detonation wave, which reduces the total pressure of the hypersonic inflow. In general, the free jet tunnel test with flight Mach number greater than 8 cannot meet the requirements of high total enthalpy and high total pressure of the test gas flow at the same time, and cannot balance the test time and component pollution problems. Therefore, in order to avoid the shortcomings in the prior art, it is necessary to improve the prior art. SUMMARY

[0005] The application aims to provide a ground flight test system for hypersonic vehicle design verification, which can continuously and stably simulate the high-altitude environment conditions of the actual flight corridor, has a large adjustment range of total temperature, total pressure and Mach number, and can keep the environment of each functional section of the ground flight test system for hypersonic vehicle design verification independent of each other without affecting the test.

[0006] To solve the above technical problems, the technical scheme adopted by the application is as follows:

[0007] The application discloses a ground flight test system for hypersonic vehicle design verification, which comprises a test piece platform, a vacuum electromagnetic ejection section, a vacuum electromagnetic acceleration section, a hypersonic flight test section and an electromagnetic aerodynamic deceleration section.

[0008] In some embodiments, the electromagnetic aerodynamic deceleration section is provided with a normal-conductivity magnetic levitation track, and the electromagnetic aerodynamic deceleration section is connected with a second high-pressure gas storage tank.

[0009] In some embodiments, the vacuum electromagnetic ejection section is provided with a first power supply device, the vacuum electromagnetic acceleration section is provided with a second power supply device, and the electromagnetic aerodynamic deceleration section is provided with a third power supply device.

[0010] In some embodiments, the vacuum electromagnetic ejection section is provided with a first measuring device, the vacuum electromagnetic acceleration section is provided with a second measuring device, and the electromagnetic aerodynamic deceleration section is provided with a third measuring device.

[0011] In some embodiments, the electromagnetic aerodynamic deceleration section is connected with a vacuum exhaust system.

[0012] In some embodiments, the first end of the vacuum electromagnetic catapult section is connected with a general control room, and the general control room is electrically connected with the vacuum electromagnetic catapult section, the vacuum electromagnetic acceleration section, the hypersonic flight test section and the electromagnetic aerodynamic deceleration section respectively.

[0013] In some embodiments, the hypersonic flight test section is provided with cooling pipes in the pipe wall.

[0014] In some embodiments, the cooling pipes are arranged in a meandering manner in the pipe wall of the hypersonic flight test section.

[0015] In some embodiments, the test piece platform comprises a suspension channel and a guide channel.

[0016] In some embodiments, the test piece platform is provided with electromagnetic devices for fixing the hypersonic aircraft for experiment.

[0017] The ground flight test system for hypersonic aircraft design verification provided by the present application has the beneficial effects compared with the prior art:

[0018] The application can continuously, stably and accurately simulate the high-altitude environment condition of the actual flight corridor, the total temperature, total pressure and Mach number adjustment range of the test simulation is large, the test gas types are various and the components, temperature and pressure are stable, the diaphragm is installed between the vacuum electromagnetic ejection section, the vacuum electromagnetic acceleration section, the hypersonic flight test section and the electromagnetic aerodynamic deceleration section to separate the test system, the environment of each function section of the ground flight test system for the hypersonic vehicle design verification can be kept independent from each other without affecting the test, the first vacuum pump is used to maintain the vacuum environment of the vacuum electromagnetic ejection section, the second vacuum pump is used to maintain the vacuum environment of the vacuum electromagnetic acceleration section, the vacuum environment is maintained to prevent the gas from affecting the stability of the test piece platform and the hypersonic vehicle acceleration, the vacuum environment is maintained to enable the hypersonic vehicle to accelerate in the vacuum environment without resistance, and the high temperature burning of the vehicle caused by the high speed in the non-vacuum environment is avoided; the first high-pressure gas tank is used to store the test gas, the second high-pressure gas tank is used to store the inert high-density high-pressure gas, the test gas stored in the first high-pressure gas tank is filled into the hypersonic flight test section after reaching the actual high-altitude condition or the pressure and temperature of the actual inlet of the supersonic combustion chamber through the aerodynamic pressure reducer and the heat exchange device, and the air or premixed gas meeting the hypersonic flight test research is obtained. The inert high-density high-pressure gas stored in the second high-pressure gas tank is filled into the electromagnetic aerodynamic deceleration section to decelerate the test piece platform. The hypersonic vehicle needing to be tested in the vacuum electromagnetic ejection section is fixed on the test piece platform, the test piece platform with the hypersonic vehicle needing to be tested is accelerated, the friction resistance of the test piece platform is reduced by using the normal-conducting magnetic suspension technology, and after a larger initial speed is obtained by electromagnetic ejection, the test piece platform enters the vacuum electromagnetic acceleration section along the electromagnetic ejection track, and the diaphragm at the first end of the vacuum electromagnetic acceleration section is broken. The acceleration mode of the test piece platform in the vacuum electromagnetic acceleration section is changed to superconducting magnetic suspension propulsion acceleration, after the corresponding speed of the flight Mach number greater than 8 under the actual high-altitude condition is obtained, the diaphragm between the vacuum electromagnetic acceleration section and the hypersonic flight test section is broken, the test piece platform enters the hypersonic flight test section, the test piece platform realizes the movement with force guiding or without force guiding under the action of the electromagnetic device, and the test data is obtained by using the contact type and non-contact type measurement mode. After the hypersonic flight test research is completed, the diaphragm between the electromagnetic aerodynamic deceleration section and the hypersonic flight test section is broken, the hypersonic vehicle needing to be tested is fixed on the test piece platform again by the electromagnetic device, and the test piece platform enters the electromagnetic aerodynamic deceleration section to complete the deceleration under the action of the electromagnetic brake and the gas resistance. After the test is completed, the gas in the closed rectangular pipeline test system is exhausted by using the vacuum exhaust system, so that the next ground hypersonic flight test can be carried out.The present application realizes the required test gas type and state of the continuous, stable and accurate simulation of the hypersonic flight test by the cooperation of the vacuum electromagnetic ejection section, the vacuum electromagnetic acceleration section, the hypersonic flight test section, the electromagnetic pneumatic deceleration section, the control communication facilities and the power supply and energy storage facilities, and the hypersonic ground flight test with the total pressure higher than 17MPa and the total temperature higher than 2700K can be carried out. The present application is a ground test system which can meet the flight test research requirements of the hypersonic aircraft and key components in the full speed domain and large airspace from subsonic speed to the flight Mach number higher than 8. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings of the embodiments will be briefly introduced below.

[0020] Figure 1 is a schematic diagram of the ground flight test system for the hypersonic aircraft design verification of the present application;

[0021] Figure 2 is a structural schematic diagram of the vacuum electromagnetic ejection section of the present application;

[0022] Figure 3 is a structural schematic diagram of the vacuum electromagnetic acceleration section of the present application;

[0023] Figure 4 is a structural schematic diagram of the hypersonic flight test section of the present application;

[0024] Figure 5 is a cooling pipeline schematic diagram of the hypersonic flight test section of the present application;

[0025] Figure 6 is a structural schematic diagram of the electromagnetic pneumatic deceleration section of the present application;

[0026] Figure 7 is a structural schematic diagram of the test piece platform of the present application.

[0027] Markings in the figure:

[0028] 1, control room; 2, vacuum electromagnetic catapult section; 3, vacuum electromagnetic acceleration section; 4, hypersonic flight test section; 5, electromagnetic pneumatic deceleration section; 6, first power supply device; 7, electromagnetic catapult track; 8, first vacuum pump; 9, first measuring device; 10, second power supply device; 11, second measuring device; 12, second vacuum pump; 13, superconducting magnetic levitation acceleration track; 14, diaphragm; 15, heat exchange device; 16, pneumatic pressure reducer; 17, first high-pressure gas tank; 18, superconducting magnetic levitation track; 19, test piece platform; 20, third power supply device; 21, normal-conducting magnetic levitation track; 22, third measuring device; 23, vacuum exhaust system; 24, second high-pressure gas tank; 25, electromagnetic device; 26, guide channel; 27, levitation channel; 28, cooling pipeline. DETAILED DESCRIPTION

[0029] The embodiments of the present application are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary only, for the purpose of explaining the present application, and should not be understood as a limitation of the present application.

[0030] In the description of the present application, it should be understood that the orientation description, such as the orientation or position relationship indicated by up, down, front, back, left, right, etc. is based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be understood as a limitation of the present application.

[0031] In the description of the present application, the meaning of several is one or more, and the meaning of multiple is more than two. Greater than, less than, more than, etc. are understood as not including the number, and above, below, etc. are understood as including the number. If it is described as first, second, it is only for the purpose of distinguishing technical features, and should not be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features or the order of indicated technical features.

[0032] In the description of the present application, unless otherwise explicitly limited, the words such as setting, installing, connecting, etc. should be broadly understood, and those skilled in the art can reasonably determine the specific meaning of the above words in the present application in combination with the specific content of the technical solution.

[0033] Please refer to Figures 1 to 7 , now the ground flight test system for hypersonic vehicle design verification provided by the embodiments of the present application will be described.

[0034] As Figures 1 to 7As shown, the ground flight test system for hypersonic vehicle design verification of the embodiment of the present application is used for hypersonic vehicle design verification, comprising a test piece platform 19, a vacuum electromagnetic ejection section 2, a vacuum electromagnetic acceleration section 3, a hypersonic flight test section 4 and an electromagnetic aerodynamic deceleration section 5, the hypersonic vehicle needing to be tested is installed on the test piece platform 19, an electromagnetic ejection track 7 is arranged in the vacuum electromagnetic ejection section 2, the test piece platform 19 is installed on the electromagnetic ejection track 7, a first vacuum pump 8 is installed on the vacuum electromagnetic ejection section 2, the first end of the vacuum electromagnetic acceleration section 3 is connected with the last end of the vacuum electromagnetic ejection section 2, a superconducting magnetic suspension acceleration track 13 is arranged on the vacuum electromagnetic acceleration section 3, a second vacuum pump 12 is installed on the vacuum electromagnetic acceleration section 3, the first end of the hypersonic flight test section 4 is connected with the last end of the vacuum electromagnetic acceleration section 3, a superconducting magnetic suspension track 18 is arranged on the hypersonic flight test section 4, the first high-pressure gas storage tank 17, the heat exchange device 15 and the aerodynamic pressure reducer 16 are connected in the hypersonic flight test section 4, and the first end of the electromagnetic aerodynamic deceleration section 5 is connected with the last end of the hypersonic flight test section 4, wherein the first end of the vacuum electromagnetic acceleration section 3, the first end of the hypersonic flight test section 4 and the first end of the electromagnetic aerodynamic deceleration section 5 are respectively provided with a diaphragm 14.

[0035] The test piece platform 19 can also be installed with the test piece such as an engine needing to be tested.

[0036] The vacuum electromagnetic ejection section 2 and the vacuum electromagnetic acceleration section 3 adopt a straight-section tubular structure, so that the test piece platform 19 moves along the vacuum electromagnetic ejection section 2 and the vacuum electromagnetic acceleration section 3, and after a certain initial speed is obtained in the vacuum electromagnetic ejection section 2, the test piece platform 19 is further accelerated in the vacuum electromagnetic acceleration section 3, so that the test piece platform 19 reaches a specified speed to enter the hypersonic flight test section 4. The acceleration through the straight-section tubular structure can reduce the requirement on the material strength of the pipeline. If the rotating acceleration mode is adopted, because the hypersonic vehicle needs a larger speed, the material connected with the test piece platform 19 needs to bear a larger centripetal force during acceleration, and the requirement on the material strength is relatively high. The straight-section tubular structure can reduce the requirement on the material strength of the vacuum electromagnetic ejection section 2 and the vacuum electromagnetic acceleration section 3 to reduce the cost and technical difficulty.

[0037] Figure 1is a schematic diagram of a hypersonic flight ground test system structure designed by the present application. The test system adopts electromagnetic ejection, superconducting magnetic suspension and acceleration as the acceleration scheme of the test piece platform 19. In the vacuum electromagnetic ejection section 2 and the vacuum electromagnetic acceleration section 3, electromagnetic ejection and superconducting magnetic suspension are used to accelerate to the corresponding speed of subsonic speed to flight Mach number greater than 8 under actual high altitude conditions respectively; the test piece meeting the flight test speed requirement enters the hypersonic flight test section 4, and completes the flight test here to obtain the flight test data of the hypersonic aircraft and its key components; after the flight test is completed, the electromagnetic pneumatic deceleration section 5 is used for deceleration, and the vacuum exhaust system 23 is used to extract the gas inside the closed pipeline of the test system. The ground flight test system control for the design verification of the hypersonic aircraft and the test data receiving and processing are realized through the general control room 1.

[0038] Figure 2 is the vacuum electromagnetic ejection section 2 designed by the present application, which is composed of a first power supply device 6, an electromagnetic ejection track 7, a first vacuum pump 8 and a first measuring device 9. The test piece platform 19 is installed on the electromagnetic ejection track 7 to reduce the frictional resistance in the movement process of the test piece platform 19. The first power supply device 6 supplies energy to accelerate the test piece platform 19 and obtain a larger initial speed, and then the test piece platform 19 enters the vacuum electromagnetic acceleration section 3.

[0039] Figure 3 is the vacuum electromagnetic acceleration section 3 designed by the present application, which is composed of a second power supply device 10, a second measuring device 11, a second vacuum pump 12 and a superconducting magnetic suspension acceleration track 13. The vacuum electromagnetic acceleration section 3 forms a closed environment under the joint action of the diaphragm 14 and the rectangular pipeline of the vacuum electromagnetic acceleration section 3. The closed environment generates and maintains vacuum under the action of the second vacuum pump 12. The test piece platform 19 is installed on the superconducting magnetic suspension track 18 to reduce the frictional resistance in the movement process of the test piece platform 19. Under the action of the propulsion provided by the superconducting magnetic suspension track 18, the test piece platform 19 is further accelerated to obtain the corresponding speed greater than flight Mach number 8 under actual high altitude conditions. Finally, the diaphragm 14 is broken, and the test piece platform 19 enters the hypersonic flight test section 4.

[0040] Figure 4is the hypersonic flight test section 4 designed by the present application, which is composed of superconducting magnetic levitation track 18, first high-pressure gas tank 17, heat exchange device 15, aerodynamic pressure reducer 16, contact and non-contact measurement system and diaphragm 14. The diaphragm 14 is installed at the front and rear ends of the hypersonic flight test section 4, which on the one hand prevents the test gas from entering the vacuum electromagnetic acceleration section 3 to destroy the vacuum environment, and on the other hand avoids the interference of inert high-density high-pressure gas in the electromagnetic aerodynamic deceleration section 5 to the flight test. According to the requirements of hypersonic flight test research, the type of test gas is selected, and the test gas is stored in the first high-pressure gas tank 17 distributed on both sides of the hypersonic flight test section 4. The hypersonic flight test section 4 can use the heat exchange device 15 to cool the test gas to accurately simulate the temperature of the airflow under actual high-altitude conditions, and heat the test gas to simulate the temperature of the airflow at the inlet of the hypersonic vehicle combustion chamber, so as to realize the temperature conditions of the simulated hypersonic flight test. The aerodynamic pressure reducer 16 is used to adjust the pressure of the test gas to realize the pressure conditions of the simulated hypersonic flight test. The test piece moves under the action of the test piece platform 19 to realize force-guided or force-free guided motion, and the contact and non-contact measurement system is used to measure the parameters such as pressure and temperature of the external flow field of the hypersonic vehicle during the hypersonic flight test. The energy supply of the normal-conducting magnetic levitation system and auxiliary system is realized by the energy storage power supply facility. As shown in Figure 5 The inner wall of the closed pipe of the hypersonic flight test section 4 is equipped with a cooling pipe 28 to avoid damage to the test system by the high-temperature and high-pressure plume of the hypersonic vehicle engine, and finally the tail diaphragm 14 is broken and the test piece platform 19 enters the electromagnetic aerodynamic deceleration section 5.

[0041] Figure 6 is the electromagnetic aerodynamic deceleration section 5 designed by the present application, which is composed of second high-pressure gas tank 24, third measurement device 22, normal-conducting magnetic levitation track 21, third power supply equipment 20 and vacuum exhaust system 23. The inert high-density high-pressure gas from the second high-pressure gas tank 24 is filled in the closed rectangular pipe interval. The third power supply equipment 20 supplies energy to brake the test piece platform 19 on the normal-conducting magnetic levitation track 21, and at the same time uses the high-pressure gas to generate a reaction force to reduce the speed of the test piece platform 19. Finally, the vacuum exhaust system 23 is opened to exhaust the gas in the test system closed rectangular pipe, so as to carry out the next hypersonic flight test.

[0042] Figure 7The test piece platform 19 is designed by the present application, which is composed of the electromagnetic device 25, the suspension channel 27 and the guide channel 26. The suspension channel 27 is mainly used for passing current to generate upward force to realize the suspension of the test piece platform 19, and the guide channel 26 is used for passing current to generate forward guiding force to realize the acceleration of the test piece platform 19. The electromagnetic device 25 is used for fixing the hypersonic aircraft which needs to be experimented in the vacuum electromagnetic ejection section 2, the vacuum electromagnetic acceleration section 3 and the electromagnetic pneumatic deceleration section 5, and realizing the powerful guiding or non-powerful guiding movement of the aircraft in the hypersonic flight test section 4.

[0043] As shown in Figure 6 , the electromagnetic pneumatic deceleration section 5 is provided with the normal magnetic suspension track 21, and the second high-pressure gas tank 24 is connected to the electromagnetic pneumatic deceleration section 5. The second high-pressure gas tank 24 is used for storing inert high-density high-pressure gas, and the second high-pressure gas tank 24 fills the inert high-density high-pressure gas into the electromagnetic pneumatic deceleration section 5 to generate reaction force to reduce the speed of the test piece platform 19.

[0044] As shown in Figure 2 , Figure 3 , Figure 6 , the vacuum electromagnetic ejection section 2 is provided with the first power supply equipment 6, the vacuum electromagnetic acceleration section 3 is provided with the second power supply equipment 10, and the electromagnetic pneumatic deceleration section 5 is provided with the third power supply equipment 20. The first power supply equipment 6 is used for supplying power to the electromagnetic ejection track 7 of the vacuum electromagnetic ejection section 2 to generate electromagnetic force to accelerate and eject the test piece platform 19, the second power supply equipment 10 is used for supplying power to the superconducting magnetic suspension acceleration track 13 of the vacuum electromagnetic acceleration section 3 to generate electromagnetic force to accelerate the test piece platform 19 in the same direction, and the third power supply equipment 20 is used for supplying power to the normal magnetic suspension track 21 of the electromagnetic pneumatic deceleration section 5 to generate electromagnetic force to decelerate the test piece platform 19 in the opposite direction.

[0045] The vacuum electromagnetic ejection section 2 is provided with the first measuring device 9, the vacuum electromagnetic acceleration section 3 is provided with the second measuring device 11, and the electromagnetic pneumatic deceleration section 5 is provided with the third measuring device 22. The first measuring device 9, the second measuring device 11 and the third measuring device 22 respectively measure the speed and other data of the test piece platform 19 in the vacuum electromagnetic ejection section 2, the vacuum electromagnetic acceleration section 3 and the electromagnetic pneumatic deceleration section 5.

[0046] The electromagnetic pneumatic deceleration section 5 is connected with the vacuum exhaust system 23, which is used for exhausting the gas in the electromagnetic pneumatic deceleration section 5 after the test to carry out the next hypersonic flight test.

[0047] As shown in Figure 1As shown, the first end of the vacuum electromagnetic ejection section 2 is connected with the general control room 1, the general control room 1 is respectively electrically connected with the vacuum electromagnetic ejection section 2, the vacuum electromagnetic acceleration section 3, the hypersonic flight test section 4 and the electromagnetic pneumatic deceleration section 5, and the ground flight test system control for hypersonic aircraft design verification and test data receiving and processing are realized through the general control room 11.

[0048] As shown in Figure 4 , Figure 5 As shown, the pipe wall of the hypersonic flight test section 4 is provided with cooling pipes 28, liquid water is introduced into the cooling pipes 28 to cool the pipe wall of the hypersonic flight test section 4, the hypersonic flight test section 4 will produce high-temperature gas during the test, and the high-temperature gas will heat and warm the pipe wall. By cooling the pipe wall of the hypersonic flight test section 4 through the cooling pipes 28, it can ensure that the test is successfully carried out.

[0049] The cooling pipes 28 are arranged in the pipe wall of the hypersonic flight test section 4 in a winding manner, which prolongs the total length of the cooling pipes 28 and also makes the cooling pipes 28 spread in the pipe wall of the hypersonic flight test section 4, uniformly cooling and cooling the entire pipe wall, and the cooling effect is good.

[0050] As shown in Figure 7 As shown, the test piece platform 19 includes a suspension channel 27 and a guide channel 26. The suspension channel 27 generates electromagnetic force after the current is introduced, so that the test piece platform 19 and the electromagnetic ejection track 7, the superconducting magnetic suspension acceleration track 13, the superconducting magnetic suspension track 18 and the normal conductive magnetic suspension track 21 generate mutual interaction force, so that the test piece platform 19 is in a suspended state. The guide channel 26 introduces current to make the test piece platform 19 and the electromagnetic ejection track 7, the superconducting magnetic suspension acceleration track 13, the superconducting magnetic suspension track 18 and the normal conductive magnetic suspension track 21 generate mutual interaction force to realize the acceleration of the test piece platform 19.

[0051] The electromagnetic device 25 is arranged on the test piece platform 19 for fixing the hypersonic aircraft to be tested, and generates electromagnetic force to fix the hypersonic aircraft to be tested on the electromagnetic device 25. After the test piece platform 19 is accelerated in the vacuum electromagnetic acceleration section 3 and obtains the corresponding speed under the actual high-altitude condition with the flight Mach number greater than 8, the diaphragm 14 between the vacuum electromagnetic acceleration section 3 and the hypersonic flight test section 4 is broken, the test piece platform 19 enters the hypersonic flight test section 4, and the test piece platform 19 moves under the action of the electromagnetic device 25 to realize force-guided or non-force-guided movement. The test data are obtained by using the contact type and non-contact type measurement methods, that is, in the hypersonic flight test section 4, the electromagnetic device 25 can fix the hypersonic aircraft to be tested or not, so that the aircraft flies at the accelerated speed, and the test data are collected. After the hypersonic flight test research is completed, the diaphragm 14 between the electromagnetic aerodynamic deceleration section 5 and the hypersonic flight test section 4 is broken, and the hypersonic aircraft to be tested is fixed on the test piece platform 19 by the electromagnetic device 25 again.

[0052] Compared with the prior art, the ground flight test system for hypersonic aircraft design verification provided by the application has the beneficial effects that:

[0053] The application can continuously, stably and accurately simulate the high-altitude environment condition of the actual flight corridor, the total temperature, total pressure and Mach number adjustment range of the test simulation is large, the test gas type is various and the composition, temperature and pressure are stable, the diaphragm 14 between the vacuum electromagnetic ejection section 2, the vacuum electromagnetic acceleration section 3, the hypersonic flight test section 4 and the electromagnetic aerodynamic deceleration section 5 is installed to separate the test system, the ground flight test system for the hypersonic vehicle design verification can keep the environment of each function section independent of each other, does not affect the test, the first vacuum pump 8 is used to maintain the vacuum environment of the vacuum electromagnetic ejection section 2, the second vacuum pump 12 is used to maintain the vacuum environment of the vacuum electromagnetic acceleration section 3, the vacuum environment is maintained to prevent the gas from affecting the stability of the test piece platform 19 and the hypersonic vehicle acceleration, the vacuum environment can make the hypersonic vehicle accelerate in the vacuum environment without resistance, avoid high temperature burning of the vehicle due to high speed in the non-vacuum environment; the first high-pressure gas tank 17 is used for storing test gas, the second high-pressure gas tank 24 is used for storing inert high-density high-pressure gas, the test gas stored in the first high-pressure gas tank 17 is filled into the hypersonic flight test section 4 after reaching the actual high-altitude condition or the pressure and temperature of the actual inlet of the supersonic combustion chamber through the aerodynamic pressure reducer 16 and the heat exchange device 15, and the air or premixed gas meeting the hypersonic flight test research is obtained. The inert high-density high-pressure gas stored in the second high-pressure gas tank 24 is filled into the electromagnetic aerodynamic deceleration section 5 to decelerate the test piece platform 19. The hypersonic vehicle needing to be tested in the vacuum electromagnetic ejection section 2 is fixed on the test piece platform 19, and the test piece platform 19 with the hypersonic vehicle needing to be tested is accelerated, the friction resistance of the test piece platform 19 is reduced by using the normal-conducting magnetic suspension technology, and after a larger initial speed is obtained by electromagnetic ejection, the test piece platform 19 enters the vacuum electromagnetic acceleration section 3 along the electromagnetic ejection track 7, at this time, the diaphragm 14 at the head of the vacuum electromagnetic acceleration section 3 is broken. The acceleration mode of the test piece platform 19 in the vacuum electromagnetic acceleration section 3 is changed to superconducting magnetic suspension propulsion acceleration, after the corresponding speed of the flight Mach number greater than 8 under the actual high-altitude condition is obtained, the diaphragm 14 between the vacuum electromagnetic acceleration section 3 and the hypersonic flight test section 4 is broken, the test piece platform 19 enters the hypersonic flight test section 4, the test piece platform 19 realizes the movement of force guiding or non-force guiding under the action of the electromagnetic device 25, and the test data is obtained by using the contact type and non-contact type measurement mode. After the hypersonic flight test research is completed, the diaphragm 14 between the electromagnetic aerodynamic deceleration section 5 and the hypersonic flight test section 4 is broken, the hypersonic vehicle needing to be tested is fixed on the test piece platform 19 again by the electromagnetic device 25, and the test piece platform 19 enters the electromagnetic aerodynamic deceleration section 5 to complete the deceleration under the action of electromagnetic braking and gas resistance.The present application realizes the required test gas type and state of the continuous, stable and accurate simulation of the hypersonic flight test by the cooperation of the vacuum electromagnetic catapult section 2, the vacuum electromagnetic acceleration section 3, the hypersonic flight test section 4, the electromagnetic pneumatic deceleration section 5, the control communication facilities and the power supply equipment, and the hypersonic ground flight test with the total pressure higher than 17MPa and the total temperature higher than 2700K can be carried out. The present application is a ground test system which can meet the flight test research requirements of the hypersonic aircraft and key components thereof in the full speed domain and large airspace from the subsonic speed to the flight Mach number higher than 8.

[0054] The above only describes the preferred embodiments of the present application, and it should be noted that those skilled in the art can make several improvements and replacements without departing from the technical principles of the present application, and these improvements and replacements should also be considered as the protection scope of the present application.

Claims

1. A ground-based flight test system for hypersonic vehicle design verification, characterized in that, include: A test platform is provided, on which a hypersonic vehicle to be tested is mounted. The test platform includes a suspension channel and a guide channel. An electromagnetic device for fixing the hypersonic vehicle to be tested is provided on the test platform. The vacuum electromagnetic catapult section is equipped with an electromagnetic catapult track, the test piece platform is installed on the electromagnetic catapult track, and a first vacuum pump is installed on the vacuum electromagnetic catapult section. The vacuum electromagnetic acceleration section is connected at its beginning to the end of the vacuum electromagnetic catapult section. A superconducting magnetic levitation acceleration track is provided on the vacuum electromagnetic acceleration section, and a second vacuum pump is installed on the vacuum electromagnetic acceleration section. The hypersonic flight test section is connected at its head to the end of the vacuum electromagnetic acceleration section. A superconducting magnetic levitation track is installed on the hypersonic flight test section. A first high-pressure gas storage tank, a heat exchange device, and a pneumatic pressure reducer are connected inside the hypersonic flight test section. An electromagnetic aerodynamic deceleration section, the first end of which is connected to the end of the hypersonic flight test section; Diaphragms are respectively provided at the beginning of the vacuum electromagnetic acceleration section, the beginning of the hypersonic flight test section, and the beginning of the electromagnetic aerodynamic deceleration section. The electromagnetic device generates electromagnetic force to attract and fix the hypersonic vehicle to be tested onto the device. After the test platform gains a large initial velocity in the vacuum electromagnetic catapult section, the diaphragm between the vacuum electromagnetic catapult section and the vacuum electromagnetic acceleration section breaks, and the test platform enters the vacuum electromagnetic acceleration section. After the test platform obtains the speed corresponding to the Mach number of flight under actual high-altitude conditions, the diaphragm between the vacuum electromagnetic acceleration section and the hypersonic flight test section breaks, and the test platform enters the hypersonic flight test section. Under the action of the electromagnetic device, the test platform achieves force-guided or non-force-guided motion, and test data is obtained using contact and non-contact measurement methods. After the hypersonic flight test is completed, the diaphragm between the electromagnetic aerodynamic deceleration section and the hypersonic flight test section breaks, and the hypersonic vehicle that has completed the test is re-fixed to the test platform by the electromagnetic device and completes deceleration.

2. The ground flight test system for hypersonic vehicle design verification according to claim 1, characterized in that, The electromagnetic pneumatic deceleration section is equipped with a normally conductive magnetic levitation track, and the electromagnetic pneumatic deceleration section is connected to a second high-pressure gas storage tank.

3. The ground flight test system for hypersonic vehicle design verification according to claim 2, characterized in that, The vacuum electromagnetic catapult section is equipped with a first power supply device, the vacuum electromagnetic acceleration section is equipped with a second power supply device, and the electromagnetic pneumatic deceleration section is equipped with a third power supply device.

4. The ground flight test system for hypersonic vehicle design verification according to claim 3, characterized in that, The vacuum electromagnetic catapult section is equipped with a first measuring device, the vacuum electromagnetic acceleration section is equipped with a second measuring device, and the electromagnetic pneumatic deceleration section is equipped with a third measuring device.

5. The ground flight test system for hypersonic vehicle design verification according to claim 4, characterized in that, The electromagnetic pneumatic deceleration section is connected to a vacuum exhaust system.

6. The ground flight test system for hypersonic vehicle design verification according to claim 5, characterized in that, The beginning of the vacuum electromagnetic catapult section is connected to a central control room, which is electrically connected to the vacuum electromagnetic catapult section, the vacuum electromagnetic acceleration section, the hypersonic flight test section, and the electromagnetic aerodynamic deceleration section.

7. The ground flight test system for hypersonic vehicle design verification according to any one of claims 1 to 6, characterized in that, Cooling pipes are installed inside the pipe wall of the hypersonic flight test section.

8. The ground flight test system for hypersonic vehicle design verification according to claim 7, characterized in that, The cooling pipes are arranged in a circuitous manner within the pipe wall of the hypersonic flight test section.

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