Aircraft ground test device and method driven by solid / gas two-phase explosion wave

Abstract

The present invention relates to an explosion impact test technology, specifically a solid / gas two-phase explosion wave driven aircraft ground test device and method, the solid / gas two-phase explosion wave driven aircraft ground test device comprises an anti-static floor, a gas distribution system, a test system, a solid explosive fixed detonation device and a tunnel system, the tunnel system comprises a fixed bracket, a tunnel, a gas circulation machine, a first gas exchange pipeline and a second gas exchange pipeline, the gas distribution system comprises a high-pressure gas tank, a high-pressure methane gas cylinder and an air exchanger, and the test system comprises an electronic detonator, a pressure sensor and a flame sensor. The present invention can carry out modulation of different overpressures and different durations by controlling the solid charge amount, gas concentration, solid explosive charge amount, solid explosive type and the like, so as to realize the adjustable and controllable overpressure peak value and duration of the explosion shock wave, and meet the requirements of the constantly changing external loads of the aircraft in different flight environments.

Description

Technical Field

[0001] The invention relates to an explosion impact test technology, in particular to an aircraft ground test device and method driven by a solid / gas two-phase explosion wave. Background Art

[0002] In the field of aerospace, as the aerodynamic environment such as the flight altitude and flight speed of the aircraft continues to change, the external loads on the aircraft are constantly changing. Therefore, a large number of tests are required during the aircraft development phase to assess the aerodynamic performance, mechanism movement and strength of the aircraft. At present, the tests that can simulate the aerodynamic environment performance in ground tests mainly include wind tunnel simulation tests, rocket sled slide rail tests, and explosion shock wave tunnel tests.

[0003] Wind tunnel tests can better achieve ground simulation of quasi-static supersonic flow fields by simulating the airflow environment of an object flying or moving at a controllable wind speed in a closed pipe. Wind tunnel simulation tests can well simulate the flow field conditions of hypersonic aircraft flying at high altitudes and have a strong ability to generate high enthalpy test airflows. However, its main disadvantages are long construction periods, high test costs, and high requirements for the radial and technical indicators of the equipment.

[0004] The rocket sled slide test is a test method that uses a high-speed sled system. The rocket thruster provides power to make the sled slide at high speed on a special track, thereby simulating physical phenomena under extreme speed and acceleration conditions. Its advantage is that it can accurately reproduce high-speed motion in a controlled environment, with high accuracy and repeatability. It is an important tool for studying fields such as high-speed impact and thermal effects. However, the test preparation cycle is long, the cost is high, the safety is relatively low, and there are major limitations when testing large or special-sized aircraft.

[0005] The explosive shock tube is a device that uses the shock wave generated by the explosion to conduct ultra-high-speed tests. It overcomes the shortcomings of wind tunnel and rocket sled slide rail tests to a certain extent and is currently a more advanced test technology. It quickly simulates the flow field under hypersonic flight conditions by detonating a small amount of explosives, and has the characteristics of instantly generating high enthalpy, high temperature, and high-speed airflow. The advantages include the ability to quickly achieve near-realistic hypersonic environment simulation, which is suitable for short but critical high-speed mechanics, chemical reactions, and material responses. However, its disadvantage is that the test time is short, only at the millisecond level; at the same time, the damage and safety issues of the test equipment are also challenges.

[0006] At present, in view of the short duration of conventional explosion shock tubes, some researchers have adopted methods such as multi-point detonation and multi-point delayed detonation to overcome this shortcoming. However, since explosion is a process of releasing a large amount of energy instantly, although multi-point explosion prolongs the shock wave action time, its load curve is not smooth enough, and there will be convex points caused by multi-point detonation, which to a certain extent does not conform to the load environment during the flight of the aircraft. Summary of the invention

[0007] In view of the problems pointed out in the background technology, the purpose of the present invention is to provide a solid / gas two-phase explosion wave driven aircraft ground test device and method, which controls the solid charge, gas concentration, solid explosive charge, and solid explosive type to carry out modulation of different overpressures and different durations, thereby realizing the coupled explosion of solid explosion and gas explosion, and realizing the adjustable and controllable overpressure peak and duration of the explosion shock wave, thereby meeting the needs of constantly changing external loads of aircraft in different flight environments.

[0008] To achieve the above object, the present invention adopts the following technical solutions:

[0009] A ground test device for aircraft driven by a solid / gas two-phase explosion wave, comprising an anti-static floor, a gas distribution system, a test system, a solid explosive fixed detonation device and a tunnel system; the tunnel system comprises a fixed bracket, a tunnel, a gas circulation machine, a first gas exchange pipeline and a second gas exchange pipeline; the tunnel as a whole is a tubular structure with one end closed and the other end open, the open end of the tunnel is connected to a sealing flange, a sealing ring and a diaphragm are arranged between the sealing flange and the tunnel, and the closed end of the tunnel cavity is fixedly connected to a gas explosion ignition device; the upper end of the fixed bracket is connected to the lower end of the tunnel outside, and the lower end of the fixed bracket is connected to the anti-static floor; the gas circulation machine is arranged outside the tunnel, one end of the first gas exchange pipeline is connected to the gas circulation machine, and the other end is connected to the open end cavity of the tunnel; one end of the second gas exchange pipeline is connected to the gas circulation machine, and the other end is connected to the closed end cavity of the tunnel;

[0010] The solid explosive fixed detonation device is fixedly connected to the inner wall of the tunnel cavity;

[0011] The gas distribution system includes a high-pressure gas tank, a high-pressure methane gas cylinder and an air exchanger. The high-pressure gas tank is connected to the high-pressure methane gas cylinder through a first air inlet pipe, and the high-pressure gas tank is connected to the air exchanger through a second air inlet pipe; the high-pressure gas tank is connected to the closed end pipe wall of the tunnel through a gas transmission pipe;

[0012] The test system includes an electronic detonator, a pressure sensor and a flame sensor. The electronic detonator is connected to a gas explosion ignition device through a first detonating line, and the electronic detonator is connected to a solid explosive fixed detonating device through a second detonating line; the pressure sensor and the flame sensor are both fixedly connected to the inner wall of the tunnel lumen.

[0013] The gas distribution system also includes a gas distribution system computer, a gas concentration monitor, a first gas flow controller, a second gas flow controller, a third gas flow controller and a fourth gas flow controller; the gas concentration monitor is connected to the high-pressure gas tank, the first gas flow controller is connected to the first air intake pipe, the second gas flow controller is connected to the high-pressure gas tank, the third gas flow controller is connected to the gas pipeline, and the fourth gas flow controller is connected to the second air intake pipe; the gas concentration monitor, the first gas flow controller, the second gas flow controller, the third gas flow controller and the fourth gas flow controller are respectively connected to the gas distribution system computer through data lines.

[0014] The electronic detonator is connected to the solid explosive fixed detonator through the solid explosive ignition device. The solid explosive ignition device is located outside the tunnel, and the solid explosive ignition device is threadedly connected to the solid explosive fixed detonator.

[0015] The test system also includes a fixed table, on which a pressure data collector, a flame data collector, a dynamic data collector and a test system computer are arranged; the pressure sensor is connected to the dynamic data collector via the pressure data collector, and the flame sensor is connected to the dynamic data collector via the flame data collector; the electronic detonator, the pressure data collector, the flame data collector and the dynamic data collector are respectively connected to the test system computer via data lines.

[0016] There are multiple pressure sensors, which are connected to the pressure data collector respectively; there are multiple flame sensors, which are connected to the flame data collector respectively.

[0017] The tunnel system also includes a vacuum pump and a first valve. The first valve is installed on the tunnel. The vacuum pump is fixedly connected to the antistatic floor. The vacuum pump is connected to the first valve through a vacuum pipe.

[0018] The tunnel is also equipped with a second valve, a third valve and a fourth valve. The first gas exchange pipeline is connected to the lumen of the tunnel through the fourth valve, the second gas exchange pipeline is connected to the lumen of the tunnel through the second valve, and the gas transmission pipeline is connected to the lumen of the tunnel through the third valve.

[0019] The gas circulation machine is fixedly connected to the antistatic floor; and the tunnel is connected to the earth through a grounding wire.

[0020] The present invention also provides an aircraft ground test method using the above-mentioned solid / gas two-phase explosion wave driven aircraft ground test test device, comprising the following steps: Step 1, installing a Laval nozzle of appropriate size at the opening end of the tunnel according to the actual requirements of the test load airflow, and fixing the aircraft to be tested at the Laval nozzle;

[0021] Step 2: Determine the type and concentration of the explosive gas according to the test load requirement, start the gas distribution system to configure the corresponding gas concentration, and fill the configured explosive gas into the tunnel;

[0022] Step 3: Determine the type and charge of solid explosives according to the test load requirement, fix the explosives by a solid explosive fixing detonator and connect the detonator;

[0023] Step 4: Calculate the air flow rate according to the volume of the tunnel, and circulate the air in the tunnel to achieve uniform concentration;

[0024] Step 5: setting the detonation time and detonation sequence of the solid explosive ignition device and the gas explosion ignition device according to the test requirements;

[0025] Step 6: Start the test system to begin the test.

[0026] Beneficial effects of the present invention:

[0027] 1) Solid explosive explosion has the characteristics of high explosion heat and fast explosion speed, so the overpressure time history curve shows a high overpressure peak and short duration, such as Fig. 22 As shown in the figure, gas explosion has the characteristics of low explosion heat and slow explosion speed, so the overpressure time history curve shows that the overpressure peak is low and the duration is long, such as Fig.23 As shown; the present invention realizes the coupled explosion of solid explosion and gas explosion, combines the advantages of solid explosion and gas explosion, and realizes the modulation of high peak value and long-lasting load by scientifically and reasonably distributing the explosion energy of solid explosives and gas explosives, such as Fig.25 shown.

[0028] 2) At present, the commonly used multi-point delayed detonation technology can prolong the shock wave action time to a certain extent, but due to the multi-point detonation, there will be multiple peak points, resulting in the curve not being smooth enough, such as Fig.24 As shown in the figure, the energy release of gas explosion is relatively slow and stable, which overcomes the disadvantage of the multi-point delayed detonation technology that there are many convex points in the descending section of the shock wave overpressure time history curve, and realizes the modulation of the smooth descending curve, as shown in the figure. Fig.25 As shown, the external load form is closer to the actual aircraft flight environment.

[0029] 3) Explosion gases of different concentrations have different explosive powers, different types of explosion gases have different properties, different solid explosive charges have different explosive powers, and different types of explosives also have different explosive powers. The present invention controls the solid charge, gas concentration, solid explosive charge, solid explosive type, etc. to carry out modulation of different overpressures and different durations, thereby achieving adjustable and controllable overpressure peak and duration of the explosion shock wave, and meeting the changing needs of external loads in different flight environments of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a stereoscopic diagram of the overall structure of the present invention.

[0031] Figure 2 It is a three-dimensional diagram of the gas distribution system of the present invention.

[0032] Figure 3 It is a top view of the gas distribution system of the present invention.

[0033] Figure 4 It is a three-dimensional diagram of the testing system of the present invention.

[0034] Figure 5 It is a stereoscopic diagram of the solid explosive fixed detonating device of the present invention.

[0035] Figure 6 It is a three-dimensional diagram of the tunnel system of the present invention.

[0036] Figure 7 It is a side view of the tunnel system of the present invention.

[0037] Figure 8 It is a front view of the tunnel system of the present invention.

[0038] Fig. 9 It is a stereoscopic diagram of the overall structure of the present invention from another viewing angle.

[0039] Fig.10 It is a front view of the overall structure of the present invention.

[0040] Fig.11 It is a side view of the overall structure of the present invention.

[0041] Fig.12 It is a top view of the overall structure of the present invention.

[0042] Fig.13 It is a three-dimensional diagram of the gas distribution system of the present invention from another perspective.

[0043] Fig.14 It is a front view of the gas distribution system of the present invention.

[0044] Fig.15 It is a side view of the gas distribution system of the present invention.

[0045] Fig.16 It is a stereoscopic diagram of the testing system of the present invention from another viewing angle.

[0046] Fig.17 It is a front view of the testing system of the present invention.

[0047] Fig.18 It is a side view of the testing system of the present invention.

[0048] Fig.19 FIG. 4 is a top view of the test system of the present invention.

[0049] Fig. 20 It is a stereoscopic view of the tunnel system of the present invention from another viewing angle.

[0050] Fig.21 It is a top view of the tunnel system of the present invention.

[0051] Fig. 22 This is a schematic diagram of the overpressure time history curve of the shock wave of a single-point explosion of solid explosives.

[0052] Fig.23 Schematic diagram of the overpressure time history curve of gas explosion shock wave.

[0053] Fig.24 This is a schematic diagram of the overpressure time history curve of the shock wave caused by multi-point delayed detonation of solid explosives.

[0054] Fig.25 Schematic diagram of the overpressure time history curve of the solid-gas two-phase explosion shock wave.

[0055] In the figure: 1, anti-static floor, 2, gas distribution system, 3, test system, 4, solid explosive fixed detonator, 5, tunnel system, 201, gas distribution system computer, 202, gas concentration monitor, 203, high-pressure gas tank, 204, high-pressure methane gas cylinder, 205, air exchanger, 206, first gas flow controller, 207, second gas flow controller, 208, third gas flow controller, 209, fourth gas flow controller, 301, fixed table, 302, electronic detonator, 303, pressure data collector, 304, fire Flame data collector, 305, dynamic data collector, 306, test system computer, 307, pressure sensor, 308, flame sensor, 401, solid explosive ignition device, 501, fixed bracket, 502, tunnel, 503, gas circulation machine, 504, vacuum pump, 505, sealing flange, 506, grounding wire, 507, first valve, 508, second valve, 509, third valve, 510, fourth valve, 511, gas explosion ignition device, 512, first gas exchange pipeline, 513, second gas exchange pipeline. DETAILED DESCRIPTION

[0056] The technical solution of the present invention will be described clearly and completely below in conjunction with the drawings of this specification. It should be noted that the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0057] like Figure 1-Figure 21 As shown, the present invention first proposes an aircraft ground test device driven by a solid / gas two-phase explosion wave, comprising an anti-static floor 1, a gas distribution system 2, a test system 3, a solid explosive fixed detonating device 4, and a tunnel system 5. The gas distribution system 2, the test system 3, and the tunnel system 5 are all fixedly connected to the anti-static floor 1, and the solid explosive fixed detonating device 4 is connected to the tunnel system 5.

[0058] The tunnel system 5 includes a fixed bracket 501, a tunnel 502, a gas circulation machine 503, a first gas exchange pipeline 512 and a second gas exchange pipeline 513; the tunnel 502 is a tubular structure with one end closed and the other end open, the open end of the tunnel 502 is connected to a sealing flange 505, a sealing ring and a diaphragm are arranged between the sealing flange 505 and the tunnel 502, and the closed end of the tunnel 502 tube cavity is fixedly connected to a gas explosion ignition device 511; the upper end of the fixed bracket 501 is connected to the lower end of the outside of the tunnel 502, and the lower end of the fixed bracket 501 is connected to the anti-static floor 1; the gas circulation machine 503 is arranged outside the tunnel 502, one end of the first gas exchange pipeline 512 is connected to the gas circulation machine 503, and the other end is connected to the open end tube cavity of the tunnel 502; one end of the second gas exchange pipeline 513 is connected to the gas circulation machine 503, and the other end is connected to the closed end tube cavity of the tunnel 502.

[0059] The solid explosive fixed detonating device 4 is fixedly connected to the inner wall of the tube cavity of the tunnel 502 .

[0060] The gas distribution system 2 includes a high-pressure gas cylinder 203, a high-pressure methane gas cylinder 204, an air exchanger 205, a gas distribution system computer 201, a gas concentration monitor 202, a first gas flow controller 206, a second gas flow controller 207, a third gas flow controller 208 and a fourth gas flow controller 209; the high-pressure gas cylinder 203 is connected to the high-pressure methane gas cylinder 204 through a first air inlet pipe, and the high-pressure gas cylinder 203 is connected to the air exchanger 205 through a second air inlet pipe; the high-pressure gas cylinder 203 is connected to the closed end pipe of the tunnel 502 through a gas transmission pipe cavity; the gas concentration monitor 202 is connected to the high-pressure gas tank 203, the first gas flow controller 206 is connected to the first air inlet pipe, the second gas flow controller 207 is connected to the high-pressure gas tank 203, the third gas flow controller 208 is connected to the gas delivery pipe, and the fourth gas flow controller 209 is connected to the second air inlet pipe; the gas concentration monitor 202, the first gas flow controller 206, the second gas flow controller 207, the third gas flow controller 208 and the fourth gas flow controller 209 are respectively connected to the gas distribution system computer 201 through data lines.

[0061] The test system 3 includes an electronic detonator 302, a pressure sensor 307, a flame sensor 308, a pressure data collector 303, a flame data collector 304, a dynamic data collector 305 and a test system computer 306. The electronic detonator 302 is connected to the gas explosion ignition device 511 through a first detonating line, and the electronic detonator 302 is connected to the solid explosive fixed detonation device 4 through a second detonating line; the pressure sensor 307 and the flame sensor 308 are both threadedly connected to the inner wall of the tube cavity of the tunnel 502; the electronic detonator 302 is connected to the gas explosion ignition device 511 through a first detonating line, and the solid explosive fixed detonation device 4 is connected through a second detonating line; the pressure sensor 307 and the flame sensor 308 are both threadedly connected to the inner wall of the tube cavity of the tunnel 502; the electronic detonator 302 is connected to the solid explosive ignition device 511 through a first detonating line. 401 is connected to the solid explosive fixed detonator 4, the solid explosive ignition device 401 is located outside the tunnel 502, and the solid explosive ignition device 401 is threadedly connected to the solid explosive fixed detonator 4; the pressure sensor 307 is connected to the dynamic data collector 305 through the pressure data collector 303, and the flame sensor 308 is connected to the dynamic data collector 305 through the flame data collector 304; the electronic detonator 302, the pressure data collector 303, the flame data collector 304 and the dynamic data collector 305 are respectively connected to the test system computer 306 through data lines. The pressure sensor 307 is in multiple numbers, and the multiple pressure sensors 307 are respectively connected to the pressure data collector 303; the flame sensor 308 is also in multiple numbers, and the multiple flame sensors 308 are respectively connected to the flame data collector 304.

[0062] The tunnel system 5 further comprises a vacuum pump 504 and a first valve 507 . The first valve 507 is installed on the tunnel 502 . The vacuum pump 504 is fixedly connected to the antistatic floor 1 . The vacuum pump 504 is connected to the first valve 507 via a vacuum pipe.

[0063] The tunnel 502 is also equipped with a second valve 508, a third valve 509 and a fourth valve 510. The first gas exchange pipeline 512 is connected to the lumen of the tunnel 502 through the fourth valve 510, the second gas exchange pipeline 513 is connected to the lumen of the tunnel 502 through the second valve 508, and the gas transmission pipeline is connected to the lumen of the tunnel 502 through the third valve 509.

[0064] The gas circulation machine 503 is fixedly connected to the antistatic floor 1 ; the tunnel 502 is connected to the ground via a grounding wire 506 .

[0065] The test system 3 further comprises a fixed table 301 , on which an electronic detonator 302 , a pressure data collector 303 , a flame data collector 304 , a dynamic data collector 305 and a test system computer 306 are all fixed.

[0066] The sealing flange 505 is bolted to one end of the tunnel 502, and the gas explosion ignition device 511 is threadedly fixed to the other end of the tunnel 502. The first valve 507, the second valve 508, the third valve 509 and the fourth valve 510 are respectively threadedly fixed to the tunnel 502.

[0067] In one embodiment of the present invention, the dynamic data collector 305 is a DH5925N type collector, the pressure data collector 303 is a DH5922 (32CH) type collector, the flame data collector 304 is a DH5922 (32CH) collector, the pressure sensor 307 is a CYG402 type sensor, and the flame sensor 308 is a CYG1401F type sensor. The above devices are all prior art and will not be described in detail here. It should be noted that the various sensors used in the present invention can be used as long as they meet the technical indicators and are not limited to specific sensor types.

[0068] The present invention also provides an aircraft ground test method using the test device as described above, comprising the following steps:

[0069] Step 1: Install a Laval nozzle of appropriate size at the opening end of the tunnel 502 according to the actual requirements of the test load airflow, and fix the aircraft to be tested at the Laval nozzle;

[0070] Step 2: Determine the type and concentration of the explosive gas according to the test load requirement, start the gas distribution system 2 to configure the corresponding gas concentration, and fill the configured explosive gas into the tunnel 502;

[0071] Step 3: determine the type and charge of solid explosive according to the test load requirement, fix the explosive by the solid explosive fixing detonator 4 and connect the detonator;

[0072] Step 4: Calculate the air flow rate according to the volume of the tunnel 502, and circulate the air in the tunnel 502 to achieve uniform concentration;

[0073] Step 5: setting the detonation time and detonation sequence of the solid explosive ignition device 401 and the gas explosion ignition device 511 according to the test requirements;

[0074] Step 6: Start the test system 3 to start the test.

[0075] In the step 1, for the gas distribution system 2, firstly, the required amount of explosive gas is calculated by testing the required explosive gas concentration, and the air exchanger 205 is turned on to extract the air in the high-pressure gas tank 203, so that the explosive gas in the high-pressure methane gas cylinder 204 can better enter the high-pressure gas tank 203. The first gas flow controller 206 is controlled to be opened by the gas distribution system computer 201, and its flow rate is monitored. When the flow rate reaches the required flow rate, the first gas flow controller 206 is closed, and the fourth gas flow controller 209 is controlled to be opened by the gas distribution system computer 201, and the air exchanger 205 is started to inject air into the high-pressure gas tank 203. When the flow rate reaches the required flow rate, the fourth gas flow controller 209 is closed, and the gas concentration monitor 202 transmits the concentration data in the high-pressure gas tank 203 to the gas distribution system computer 201 from time to time. The gas distribution system computer 201 controls the opening and closing of the first gas flow controller 206 and the fourth gas flow controller 209 according to the concentration data, so as to keep the set concentration stable at any time.

[0076] In step 2, for the solid explosive fixed detonating device 4, the bolt valve is opened, the TNT explosive with the detonator installed is hung into the tunnel 502 by rope fixing, and the detonator detonating line is connected to the solid explosive ignition device 401 to complete the installation of the solid explosive.

[0077] In step 3, for the test system 3, the test system computer 306, the dynamic data collector 305, the flame data collector 304, and the pressure data collector 303 are turned on, and each device is debugged and is in data monitoring mode.

[0078] In step 4, for the tunnel system 5, the PVC diaphragm is replaced before the test. Two rubber rings are provided between the sealing flange 505 and the tunnel 502. The diaphragm is located between the rubber rings and is tightened by bolts to maintain the sealing performance. All valves of the tunnel system 5 are closed, and the vacuum pump 504 and the first valve 507 are turned on to evacuate the tunnel 502. The data sent back by the pressure sensor 307 of the test system 3 can reflect the vacuum degree. When the vacuum degree is lower than 1×10 -3When the pressure is 0.04 Pa (Pa), it can be considered that the air in a tunnel 502 has been evacuated, the vacuum pump 504 and the first valve 507 are closed, the third gas flow controller 208 is controlled to be opened through the gas distribution system computer 201 of the gas distribution system 2, and the gas flow is monitored, the third valve 509 is opened, and the gas in the high-pressure gas tank 203 will enter the tunnel 502 under the action of pressure. Before the test, the air flow is calculated according to the volume of the tunnel 502. When the calculated flow value is reached, the third gas flow controller 208 is controlled to be closed, and the third valve 509 is closed. The second valve 508, the fourth valve 510 and the gas circulation machine 503 are opened to circulate the air in the tunnel 502 to achieve the purpose of uniform concentration. After the air in the tunnel 502 is circulated for 30 minutes, the second valve 508, the fourth valve 510 and the gas circulation machine 503 are closed to complete the detonation preparation.

[0079] The step 5 is specifically as follows: the dynamic data collector 305, the flame data collector 304, and the pressure data collector 303 are all set to the triggering state, the electronic detonator 302 is turned on to charge the detonator, and the detonation time, detonation sequence, etc. of the solid explosive ignition device 401 and the gas explosion ignition device 511 can be set according to the test requirements.

[0080] The specific steps of step 6 are as follows: after the preparation work is completed, the electronic detonator 302 sends an electrical signal to control the solid explosive ignition device 401 and the gas explosion ignition device 511 to detonate, and the pressure sensor 307 and the flame sensor 308 are used to obtain the shock wave and flame conditions of each part of the tunnel 502. The pressure sensor 307 and the flame sensor 308 at the exit of the tunnel 502 collect the overpressure parameters and flame parameters output by the tunnel 502. The sensors arranged on the aircraft itself can monitor the stress conditions of different parts, thereby completing the simulation of the load conditions of the aircraft flight environment.

[0081] The parts not described in detail in this invention are prior art.

Claims

1. A ground test device for aircraft driven by a solid / gas two-phase explosion wave, comprising an anti-static floor (1), a gas distribution system (2), a test system (3), a solid explosive fixed detonation device (4) and a tunnel system (5); wherein: The tunnel system (5) comprises a fixed support (501), a tunnel (502), a gas circulation machine (503), a first gas exchange pipeline (512) and a second gas exchange pipeline (513); the tunnel (502) is a tubular structure with one end closed and the other end open; the open end of the tunnel (502) is connected to a sealing flange (505); a sealing ring and a diaphragm are provided between the sealing flange (505) and the tunnel (502); the closed end of the tunnel (502) is fixedly connected to a gas explosion ignition device (513); 11); the upper end of the fixed support (501) is connected to the lower end of the outside of the tunnel (502), and the lower end of the fixed support (501) is connected to the antistatic floor (1); the gas circulation machine (503) is arranged outside the tunnel (502), one end of the first gas exchange pipeline (512) is connected to the gas circulation machine (503), and the other end is connected to the open end lumen of the tunnel (502); one end of the second gas exchange pipeline (513) is connected to the gas circulation machine (503), and the other end is connected to the closed end lumen of the tunnel (502); The solid explosive fixed detonation device (4) is fixedly connected to the inner wall of the tube cavity of the tunnel (502); The gas distribution system (2) comprises a high-pressure gas tank (203), a high-pressure methane gas tank (204) and an air exchanger (205); the high-pressure gas tank (203) is connected to the high-pressure methane gas tank (204) via a first air inlet pipe, and the high-pressure gas tank (203) is connected to the air exchanger (205) via a second air inlet pipe; the high-pressure gas tank (203) is connected to the closed end tube cavity of the tunnel (502) via a gas transmission pipe; The test system (3) comprises an electronic detonator (302), a pressure sensor (307) and a flame sensor (308); the electronic detonator (302) is connected to a gas explosion ignition device (511) via a first detonating line, and the electronic detonator (302) is connected to a solid explosive fixed detonation device (4) via a second detonating line; the pressure sensor (307) and the flame sensor (308) are both fixedly connected to the inner wall of the tube cavity of the tunnel (502).

2. The solid / gas two-phase explosion wave driven aircraft ground test device according to claim 1 is characterized in that: The gas distribution system (2) further comprises a gas distribution system computer (201), a gas concentration monitor (202), a first gas flow controller (206), a second gas flow controller (207), a third gas flow controller (208) and a fourth gas flow controller (209); the gas concentration monitor (202) is connected to the high-pressure gas tank (203), the first gas flow controller (206) is connected to the first gas inlet pipe, the second gas flow controller (207) is connected to the high-pressure gas tank (203), the third gas flow controller (208) is connected to the gas transmission pipe, and the fourth gas flow controller (209) is connected to the second gas inlet pipe; the gas concentration monitor (202), the first gas flow controller (206), the second gas flow controller (207), the third gas flow controller (208) and the fourth gas flow controller (209) are respectively connected to the gas distribution system computer (201) via data lines.

3. The solid / gas two-phase explosion wave driven aircraft ground test device according to claim 1 is characterized by: The electronic detonator (302) is connected to the solid explosive fixed detonator (4) via a solid explosive ignition device (401); the solid explosive ignition device (401) is located outside the tunnel (502), and the solid explosive ignition device (401) is threadedly connected to the solid explosive fixed detonator (4).

4. The solid / gas two-phase explosion wave driven aircraft ground test device according to claim 1 is characterized by: The test system (3) further comprises a fixed table (301), on which a pressure data collector (303), a flame data collector (304), a dynamic data collector (305) and a test system computer (306) are arranged; the pressure sensor (307) is connected to the dynamic data collector (305) via the pressure data collector (303), and the flame sensor (308) is connected to the dynamic data collector (305) via the flame data collector (304); and the electronic detonator (302), the pressure data collector (303), the flame data collector (304) and the dynamic data collector (305) are respectively connected to the test system computer (306) via data cables.

5. The solid / gas two-phase explosion wave driven aircraft ground test device according to claim 4 is characterized by: There are multiple pressure sensors (307), and the multiple pressure sensors (307) are respectively connected to the pressure data collector (303); there are multiple flame sensors (308), and the multiple flame sensors (308) are respectively connected to the flame data collector (304).

6. The solid / gas two-phase explosion wave driven aircraft ground test device according to claim 1 is characterized by: The tunnel system (5) further comprises a vacuum pump (504) and a first valve (507), wherein the first valve (507) is installed on the tunnel (502), the vacuum pump (504) is fixedly connected to the antistatic floor (1), and the vacuum pump (504) is connected to the first valve (507) via a vacuum pipe.

7. The solid / gas two-phase explosion wave driven aircraft ground test device according to claim 1 is characterized by: The tunnel (502) is also equipped with a second valve (508), a third valve (509) and a fourth valve (510); the first gas exchange pipeline (512) is connected to the lumen of the tunnel (502) via the fourth valve (510); the second gas exchange pipeline (513) is connected to the lumen of the tunnel (502) via the second valve (508); and the gas transmission pipeline is connected to the lumen of the tunnel (502) via the third valve (509).

8. The solid / gas two-phase explosion wave driven aircraft ground test device according to claim 1 is characterized by: The gas circulation machine (503) is fixedly connected to the antistatic floor (1); and the tunnel (502) is connected to the ground via a grounding wire (506).

9. An aircraft ground test method using the aircraft ground test device driven by the solid / gas two-phase explosion wave according to any one of claims 1 to 8, characterized in that: The following steps are involved: Step 1: Install a Laval nozzle of appropriate size at the opening end of the tunnel (502) according to the actual requirements of the test load airflow, and fix the aircraft to be tested at the Laval nozzle; Step 2: Determine the type and concentration of the explosive gas according to the test load requirement, start the gas distribution system (2) to configure the corresponding gas concentration, and fill the configured explosive gas into the tunnel (502); Step 3: Determine the type and charge of solid explosive according to the test load requirement, fix the explosive by the solid explosive fixing detonator (4) and connect the detonator; Step 4, calculating the air flow rate according to the volume of the tunnel (502), and circulating the air in the tunnel (502) to achieve uniform concentration; Step 5: setting the detonation time and detonation sequence of the solid explosive ignition device (401) and the gas explosion ignition device (511) according to the test requirements; Step 6: Start the test system (3) to start the test.

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