CN112444368A - Ground simulation test device for ultrahigh-speed reentry test airflow - Google Patents
Ground simulation test device for ultrahigh-speed reentry test airflow Download PDFInfo
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- CN112444368A CN112444368A CN202011157163.2A CN202011157163A CN112444368A CN 112444368 A CN112444368 A CN 112444368A CN 202011157163 A CN202011157163 A CN 202011157163A CN 112444368 A CN112444368 A CN 112444368A
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- 238000012360 testing method Methods 0.000 title claims abstract description 131
- 238000004088 simulation Methods 0.000 title claims abstract description 22
- 239000007789 gas Substances 0.000 claims abstract description 55
- 230000035939 shock Effects 0.000 claims abstract description 54
- 238000005474 detonation Methods 0.000 claims abstract description 41
- 239000012528 membrane Substances 0.000 claims abstract description 40
- 239000007921 spray Substances 0.000 claims abstract description 29
- 230000001133 acceleration Effects 0.000 claims abstract description 22
- 239000001301 oxygen Substances 0.000 claims abstract description 14
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 14
- 239000000203 mixture Substances 0.000 claims abstract description 8
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 7
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000001257 hydrogen Substances 0.000 claims abstract description 7
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 7
- 230000005540 biological transmission Effects 0.000 claims abstract description 5
- 230000000644 propagated effect Effects 0.000 claims abstract description 3
- 230000000694 effects Effects 0.000 claims description 8
- 239000000523 sample Substances 0.000 claims description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 238000012544 monitoring process Methods 0.000 claims description 5
- 230000001105 regulatory effect Effects 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 238000005259 measurement Methods 0.000 claims description 3
- 230000003287 optical effect Effects 0.000 claims description 3
- 238000005086 pumping Methods 0.000 claims description 3
- 239000000725 suspension Substances 0.000 claims description 3
- 229920006267 polyester film Polymers 0.000 claims 1
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000011160 research Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 239000003570 air Substances 0.000 description 2
- 239000001569 carbon dioxide Substances 0.000 description 2
- 229910002092 carbon dioxide Inorganic materials 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 229920000728 polyester Polymers 0.000 description 2
- 239000000306 component Substances 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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Abstract
The ground simulation test device for the ultrahigh-speed reentry test airflow comprises an air source system, a detonation section and the like; the gas source system fills hydrogen and oxygen into the detonation section through the gas transmission pipeline, the hydrogen-oxygen mixture is detonated to form detonation waves, the detonation waves can break through one membrane, a first main shock wave and a central expansion wave are formed in the shock tube, the test gas in the shock tube is compressed and accelerated by the main shock wave, the main shock wave is propagated to the two membranes downstream in the test gas and breaks through the two membranes, a second incident shock wave and the central expansion wave are formed in the acceleration section, the test gas continues to accelerate to move downstream through the unsteady expansion action of the second central expansion wave, the speed is further accelerated through the unsteady expansion action in the spray pipe, the test gas at the outlet of the spray pipe can reach the reentry speed condition through the triple acceleration action, and the vacuum system integrally pumps the acceleration section to the test and pressure relief section to a high vacuum state. The invention meets the ground simulation requirement of the high enthalpy flow environment when the aircraft flies at the ultrahigh speed again.
Description
Technical Field
The invention relates to an airflow ground simulation test device.
Background
The interests of all countries in the world in space exploration and interstellar travel are increasing day by day, which puts higher and higher requirements on the speed of an aircraft. For example, the speed of a space shuttle in the United states is 7.3km/s when the space shuttle enters the atmosphere again from the earth's near earth orbit, the re-entering speed of the Apollo spacecraft is up to 11.2km/s when the space shuttle returns to the earth's atmosphere after landing a month, and the re-entering speed of the Mars and other distant solar system planet detectors is up to 15km/s when the space shuttle returns. With the continuous increase of the flying speed and the flying height of the aircraft, the surrounding flow environment faced by the aircraft is changed, and the aircraft develops from simple freezing flow to balanced flow and complex unbalanced flow. Due to the existence of the high-temperature real gas effect, the microscopic physical and chemical phenomena of the gas can affect the macroscopic aerodynamic force, the thermal regulation of the aircraft and the aerodynamic physical characteristics of the surrounding flow field through the thermodynamic and shock wave kinetic processes, at the moment, the classical gas dynamics theory is hard to be competent, and the high-temperature real gas effect makes the accurate prediction of the aerodynamic heat and force more difficult.
The complexity of the high enthalpy flow environment of the aircraft during the ultrahigh-speed reentry flight brings great difficulty to the research of the aircraft, the theoretical analysis is greatly limited by the complexity, and meanwhile, the theoretical analysis and the numerical simulation greatly depend on the verification and the correction of the test result. Because the flight test cost is higher, a large amount of pneumatic test research is still finished in ground simulation equipment, and in order to simulate the high-temperature real gas effect encountered during the ultrahigh-speed reentry flight of an aircraft, the ground test research greatly depends on high-enthalpy pneumatic equipment capable of simulating reentry speed test airflow. Therefore, it is necessary to develop a test device capable of simulating an ultrahigh-speed reentry test airflow.
Disclosure of Invention
The technical problem solved by the invention is as follows: the ground simulation test device can simulate the ultrahigh-speed reentry flight airflow environment of the aircraft, accelerates the test airflow to the reentry speed condition through the triple acceleration effect, and meets the ground simulation requirement of the high-enthalpy flow environment during the ultrahigh-speed reentry flight of the aircraft.
The technical scheme adopted by the invention is as follows: the ultrahigh-speed reentry test airflow simulation test device comprises an air source system, a detonation section, a first membrane, a shock tube, a second membrane, an acceleration section, a spray pipe, a test and pressure relief section and a vacuum system;
the gas source system is connected with one end of the detonation section through a gas pipe; the other end of the detonation section is connected with one end of the shock tube, and a membrane is arranged between the detonation section and the shock tube; the other end of the shock tube is connected with one end of the accelerating section, and two membranes are arranged between the accelerating section and the shock tube; the other end of the acceleration section is connected with a spray pipe, the outlet of the spray pipe is arranged in the test and pressure relief section, and the vacuum system is connected with the test and pressure relief section; a test model is arranged in the test and pressure relief section;
the gas source system fills hydrogen and oxygen into the detonation section through the gas transmission pipeline, the hydrogen-oxygen mixture is detonated to form detonation waves, the detonation waves can break through one membrane, a first main shock wave and a central expansion wave are formed in the shock tube, the test gas in the shock tube is compressed and accelerated by the main shock wave, the main shock wave is propagated to the two membranes downstream in the test gas and breaks through the two membranes, a second incident shock wave and the central expansion wave are formed in the acceleration section, the test gas continues to accelerate to move downstream through the unsteady expansion action of the second central expansion wave, the speed is further accelerated through the unsteady expansion action in the spray pipe, the outlet of the spray pipe is arranged in the test and pressure relief section, the test gas at the outlet of the spray pipe can reach the reentry speed condition through the triple acceleration action, and the pressure relief section are integrally pumped to a high vacuum state by the vacuum system.
Furthermore, the air source system consists of a high-pressure hydrogen cylinder and a high-pressure oxygen cylinder, the pressure is adjusted through a pressure regulating valve, and the pneumatic valve is remotely controlled through an electromagnetic valve to inflate.
Furthermore, the detonation section is driven by positive detonation and is provided with an annular expansion cavity structure, a jet mode detonation tube is used for ignition, the hydrogen-oxygen mixture filled into the detonation section is detonated, and in an initial state, the inflation pressure in the detonation section is N1, and N1 is 0.1-2.0 MPa.
Furthermore, the first membrane is a steel membrane, and a cross-shaped groove is milled in the center of the steel membrane to control the fracture form of the steel membrane.
Furthermore, the shock tube needs to be vacuumized and then is filled with required test gas, the inflation pressure is N2, N2 is 100-10000 Pa, different types of test gas can be filled according to the test requirements, and a pressure sensor and an ionization speed measurement probe are arranged along the tube body and used for monitoring the pressure of the shock tube and the speed of the main shock tube.
Furthermore, the second membrane is a polyester membrane, the thickness of the second membrane is 25-90 microns, and the interference of membrane rupture on test airflow can be reduced as far as possible while the test pressure-bearing requirement is met.
Furthermore, the acceleration section needs to be pumped to a high vacuum state, the vacuum degree is N3, N3 equals 1-100 Pa, and a pressure sensor and an ionization speed measurement probe are arranged along the tube body and used for monitoring the pressure of the acceleration section and the speed of the second incident shock wave.
Furthermore, the spray pipe is a conical spray pipe and can also be a profile spray pipe, and the supersonic test gas can be accelerated inside through a steady expansion effect.
Furthermore, optical observation windows are arranged on two sides of the test and pressure relief section, a test model and a model support are installed inside the test and pressure relief section, and after the test, the test gas enters at ultrahigh speed and decelerates at the tail end of the downstream and recovers the pressure.
Furthermore, the vacuum system is composed of two stages of vacuum pumps, the first stage of vacuum pump is a rotary vane mechanical vacuum pump, the whole pressure of the test section is pumped to be less than 1000Pa after the vacuum system is started, the second stage of vacuum pump is a magnetic suspension turbo molecular pump, the maximum rotating speed is 30000r/m, the theoretical pumping speed is 1500L/s, and the whole pressure of the test section can be pumped to be below 10Pa after the vacuum system is started.
Compared with the prior art, the invention has the following advantages:
(1) the invention provides a ground test device for simulating ultrahigh-speed reentry test airflow, which can achieve the speed of a test airflow to be close to or beyond the track speed, so that a high-enthalpy flow environment faced by an aircraft in ultrahigh-speed reentry flight can be simulated, and aerodynamic and thermal tests in the field can be carried out.
(2) The invention provides a detonation drive test technology, which generates detonation waves after detonation of a hydrogen-oxygen mixture, takes high-temperature and high-pressure gas after detonation as drive gas, and has the advantages of strong drive capability, low operation cost, simple structure, easiness in maintenance, good test repeatability and the like.
(3) The invention can provide different test gas components, and air, carbon dioxide, nitrogen and the like are selected as test gases according to the flying environment of the aircraft to simulate the atmospheric environment of stars such as the earth, mars and the like.
(4) The invention can provide different inflation and vacuum pressure conditions, is continuously adjustable, and can simulate test airflow with different speeds in a large range, wherein the speed range of the test airflow is 3.0-10.2 km/s.
Drawings
FIG. 1 is a schematic diagram of the layout of the testing apparatus of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.
Fig. 1 is an ultrahigh-speed reentry test airflow simulation test apparatus according to an embodiment of the present invention, including: the device comprises an air source system 1, a detonation section 2, a first membrane 3, a shock tube 4, a second membrane 5, an acceleration section 6, a spray pipe 7, a test section and pressure relief section 8 and a vacuum system 9;
the gas source system 1 is connected with one end of the detonation section 2 through a gas pipe; the other end of the detonation section 2 is connected with one end of a shock tube 4, and a membrane 3 is arranged between the detonation section 2 and the shock tube 4; the other end of the shock tube 4 is connected with one end of an accelerating section 6, and two membranes 5 are arranged between the accelerating section 6 and the shock tube 4; the other end of the acceleration section 6 is connected with a spray pipe 7, the outlet of the spray pipe 7 is arranged in the test and pressure relief section 8, and a vacuum system 9 is connected with the test and pressure relief section 8; a test model is arranged in the test and pressure relief section 8;
the gas source system 1 is regulated to the required pressure through a pressure regulating valve, the pneumatic valve is remotely controlled through an electromagnetic valve to charge hydrogen and oxygen into the detonation section 2 through a gas transmission pipeline, the oxyhydrogen mixture is detonated through a jet ignition technology, a membrane 3 is broken by a detonation wave formed after detonation, a first main shock wave and a central expansion wave are formed in a shock tube 4, the test gas in the shock tube 4 is compressed and accelerated by the main shock wave, the test gas with different components is selected according to test simulation requirements, the main shock wave is transmitted to a second membrane 5 in the test gas downstream and breaks through the second membrane 5, then a second incident shock wave and the central expansion wave are formed in an acceleration section 6, the test gas continues to accelerate to move downstream through the unsteady expansion action of the second central expansion wave, the speed is further accelerated through the unsteady expansion action in a spray pipe 7, the outlet of the spray pipe 7 is arranged in a test and pressure relief section 8, the test gas at the outlet of the spray pipe 7 can reach the reentry speed condition through the triple acceleration effect, the ultrahigh-speed reentry flow test research is carried out on the model, and the vacuum system 9 integrally pumps the acceleration section 6 to the test and pressure relief section 8 to a high vacuum state.
The gas source system 1 consists of a high-pressure hydrogen cylinder and a high-pressure oxygen cylinder, the pressure is adjusted through a pressure regulating valve, and the pneumatic valve is remotely controlled through an electromagnetic valve to inflate through a gas transmission pipeline.
The detonation section 2 adopts a forward detonation driving technology and is provided with an annular expansion cavity structure, a jet mode detonation tube ignition technology is used for detonating the hydrogen-oxygen mixture charged into the interior, the charging pressure is N1, N1 is 0.1-2.0 MPa, and the main shock wave speed and strength can be adjusted by changing the charging pressure.
One membrane 3 is the steel diaphragm, and the center is milled there is the cross recess control diaphragm form of breaking, avoids the diaphragm rupture in-process to produce the piece, reduces the ability loss that the rupture of membranes process caused simultaneously.
The shock tube 4 is required to be vacuumized and then filled with required test gas, the inflation pressure is N2, N2 is 100-10000 Pa, different types of test gas including air, carbon dioxide, nitrogen and the like can be filled according to test requirements, different star atmospheric environments are simulated, the inflation pressure is changed to adjust the speed and the strength of the main shock wave, and a pressure sensor and an ionization speed measuring probe are arranged along the tube body and used for monitoring the pressure of the shock tube 4 and the speed of the main shock wave.
The second membrane 5 is a polyester membrane, the thickness of the second membrane is 25-90 mu m, and the interference of membrane rupture on test airflow is reduced as far as possible while the test pressure-bearing requirement is met.
The accelerating section 6 needs to be pumped to a high vacuum state, the vacuum degree is N3, N3 is 1-100 Pa, the speed of the test air flow when reaching the test and pressure relief sections can be changed by adjusting the vacuum degree, and a pressure sensor and an ionization speed measuring probe are arranged along the tube body and used for monitoring the pressure of the accelerating section 6 and the speed of the second incident shock wave.
The spray pipe 7 is a conical spray pipe and can also be a profile spray pipe, supersonic test gas can be accelerated inside through a steady expansion effect, the area ratio of an outlet and an inlet of the spray pipe is changed, and the speed of test gas flow reaching a test section and a pressure relief section can be adjusted.
Optical observation windows are arranged on two sides of the test and pressure relief section 8, the state of a flow field can be observed in real time, a test model and a model support are arranged in the test and pressure relief section, and the test airflow is decelerated at the downstream tail end and the pressure is recovered after the test at the ultrahigh speed.
The vacuum system 9 is composed of two stages of vacuum pumps, the first stage of vacuum pump is a rotary vane mechanical vacuum pump, the whole pressure of the test section is pumped to about 1000Pa after the vacuum system is started, the second stage of vacuum pump is a magnetic suspension turbo molecular pump, the maximum rotating speed is 30000r/m, the theoretical pumping speed is 1500L/s, and the whole pressure of the test section can be pumped to below 10Pa after the vacuum system is started.
The invention has not been described in detail in part of the common general knowledge of those skilled in the art.
Claims (10)
1. A ground simulation test device for ultrahigh-speed reentry test airflow is characterized by comprising an air source system (1), a detonation section (2), a first membrane (3), a shock tube (4), a second membrane (5), an acceleration section (6), a spray pipe (7), a test and pressure relief section (8) and a vacuum system (9); the air source system (1) is connected with one end of the detonation section (2) through an air conveying pipe; the other end of the detonation section (2) is connected with one end of the shock tube (4), and a membrane (3) is arranged between the detonation section (2) and the shock tube (4); the other end of the shock tube (4) is connected with one end of an accelerating section (6), and two membranes (5) are arranged between the accelerating section (6) and the shock tube (4); the other end of the acceleration section (6) is connected with a spray pipe (7), the outlet of the spray pipe (7) is arranged in the test and pressure relief section (8), and a vacuum system (9) is connected with the test and pressure relief section (8); a test model is arranged in the test and pressure relief section (8);
the hydrogen and oxygen are filled into the detonation section (2) through the gas transmission pipeline by the gas source system (1), the detonation wave is formed after the hydrogen-oxygen mixture is detonated, the detonation wave breaks through one membrane (3), a first main shock wave and a central expansion wave are formed in the shock tube (4), the test gas in the shock tube (4) is compressed and accelerated by the main shock wave, the main shock wave is propagated to the two membranes (5) downstream in the test gas and breaks through the two membranes, a second incident shock wave and the central expansion wave are formed in the acceleration section (6), the test gas continues to accelerate to move downstream through the unsteady expansion action of the second central expansion wave, the speed is increased through the unsteady expansion action in the spray tube (7), and the test gas at the outlet of the spray tube (7) reaches the reentry speed condition through the acceleration action; the vacuum system (9) pumps the acceleration section (6) to the test and pressure relief section (8) to a vacuum state.
2. An ultra-high speed reentry test airflow ground simulation test device according to claim 1, wherein: the gas source system (1) comprises a hydrogen cylinder and an oxygen cylinder, the pressure is adjusted through a pressure regulating valve, and the pneumatic valve is remotely controlled through an electromagnetic valve to inflate.
3. An ultra-high speed reentry test airflow ground simulation test apparatus according to claim 1 or 2, wherein: the detonation section (2) is driven by positive detonation and is provided with an annular expansion cavity structure, and a jet flow mode detonation tube is used for igniting to detonate the hydrogen-oxygen mixture filled inside; in the initial state, the gas charging pressure of the gas charged in the detonation section (2) is N1, and N1 is 0.1-2.0 MPa.
4. An ultra-high speed reentry test airflow ground simulation test device according to claim 3, wherein: the first membrane (3) is a steel membrane, and a cross-shaped groove is milled in the center.
5. An ultra-high speed reentry test airflow ground simulation test device according to claim 4, wherein: after the interior of the shock tube (4) is vacuumized, required test gas is filled, the filling pressure is N2, N2 is 100-10000 Pa, different types of test gas are filled according to test requirements, and a pressure sensor and an ionization speed measurement probe are arranged along the tube body and used for monitoring the pressure in the shock tube (4) and the speed of the main shock wave.
6. An ultra-high speed reentry test airflow ground simulation test device according to claim 5, wherein: the second film (5) is a polyester film, and the thickness of the second film is 25-90 mu m.
7. An ultra-high speed reentry test airflow ground simulation test device according to claim 6, wherein: the inside vacuum state of taking out to acceleration segment (6), vacuum is N3, and 1 ~ 100Pa is given under N3, arranges pressure sensor and ionization speed probe along the body for monitor acceleration segment (6) pressure and the second way and incide the shock wave speed.
8. An ultra-high speed reentry test airflow ground simulation test device according to claim 7, wherein: the spray pipe (7) is a conical spray pipe or a profile spray pipe, and supersonic test gas is accelerated inside through a steady expansion effect.
9. An ultra-high speed reentry test airflow ground simulation test apparatus according to claim 8, wherein: optical observation windows are arranged on two sides of the test and pressure relief section (8), a test model mounting bracket is arranged in the test and pressure relief section, and after the test, the test gas enters at ultrahigh speed and decelerates at the tail end of the downstream and recovers the pressure.
10. An ultra-high speed reentry test airflow ground simulation test apparatus according to claim 9, wherein: the vacuum system (9) comprises a two-stage vacuum pump, the first-stage vacuum pump is a rotary vane mechanical vacuum pump, the pressure of the test and pressure relief section (8) is pumped to be less than 1000Pa after the vacuum system is started, the second-stage vacuum pump is a magnetic suspension turbo molecular pump, the maximum rotating speed is 30000r/m, the theoretical pumping speed is 1500L/s, and the pressure of the test and pressure relief section (8) is pumped to be below 10Pa after the vacuum system is started.
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Cited By (6)
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| CN113008508A (en) * | 2021-04-30 | 2021-06-22 | 华中科技大学 | Wind tunnel device for prolonging running time of hypersonic velocity temporary impulse type wind tunnel |
| CN113945354A (en) * | 2021-12-14 | 2022-01-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for identifying flow partition characteristics of acceleration section of expansion wind tunnel |
| CN114324221A (en) * | 2021-12-28 | 2022-04-12 | 中国航天空气动力技术研究院 | Absolute radiation intensity measuring device for arc heating test |
| CN114414626A (en) * | 2022-01-21 | 2022-04-29 | 安徽理工大学 | Combustible gas detonation drive generator for high-speed loading |
| CN114563153A (en) * | 2022-04-28 | 2022-05-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ultrahigh-speed pneumatic test device for accelerating gas test through track |
| CN117723261A (en) * | 2024-02-18 | 2024-03-19 | 中国科学技术大学 | Shock driving system, shock driving method and shock tube |
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| CN114563153A (en) * | 2022-04-28 | 2022-05-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ultrahigh-speed pneumatic test device for accelerating gas test through track |
| CN114563153B (en) * | 2022-04-28 | 2022-07-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ultrahigh-speed pneumatic test device for accelerating gas test through track |
| CN117723261A (en) * | 2024-02-18 | 2024-03-19 | 中国科学技术大学 | Shock driving system, shock driving method and shock tube |
| CN117723261B (en) * | 2024-02-18 | 2024-05-03 | 中国科学技术大学 | Shock driving system, shock driving method and shock tube |
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