CN114413693A - Gas detonation drive ultra-high speed launching test system - Google Patents

Abstract

The invention belongs to the technical field of gas detonation experiments, in particular to a gas detonation drive ultra-high speed launching test system, which comprises a launching body assembly, a target chamber, a gas distribution unit, an ignition unit, a detection unit and a controller, wherein the launching body assembly is arranged in the target chamber; because less data are available, the factors influencing the performance of the fragments in the ultra-high-speed emission state are analyzed; therefore, the invention measures the propagation speed and the propagation pressure change of the detonation shock wave generated after the gas is ignited through the test port arranged on the tube wall of the emitter component, and the pressure sensor and the flame sensor are matched with the laser sensor to record the emission speed of the emitted piece, so that the ultrahigh-speed emission effect of the gas detonation drive test system is verified and improved under different test condition parameters, namely the preparation proportion of oxyhydrogen gas in the ignition gas, the ignition position in the detonation tube section, the length proportional relation between the emitter component and the target chamber, the installation position of a polyethylene film in the emitter component and the like.

Description

A gas detonation-driven ultra-high-speed launch test system

technical field

The invention belongs to the technical field of gas detonation testing, in particular to a gas detonation-driven ultra-high-speed launch testing system.

Background technique

A ballistic target is a test equipment that launches a test projectile to a predetermined speed, measures the aerodynamic parameters during the flight of the projectile, and verifies the impact and damage performance of the projectile on the target plate, such as simulating space debris protection problems, with a mass of grams Space debris with an average speed of 10 km/s has a strong ability to damage on-orbit spacecraft, and it mainly relies on the structural design of the spacecraft itself to resist. In order to study and design corresponding protection technologies, test simulations must be carried out.

Based on the research of related theories, Zhao Feng, Experimental and review research on the high-speed metal flyer driven by the strong detonation of explosives [D], the paper confirms from the experiment and theory that it is feasible to drive the high-speed metal flyer by the strong detonation of explosives, but for detonation The high molecular mass and low speed of sound of ordinary gunpowder gas limit the detonation driving speed that can be generated, and the toxic products of gunpowder will also pollute the test device. The driving energy, but there is little data to analyze the factors that affect the performance of the debris in the ultra-high-speed launch state.

In view of this, in order to verify the ultra-high-speed launch effect of the gas detonation driving test system under different test conditions and parameters, the present invention proposes a gas detonation-driven ultra-high-speed launch test system.

SUMMARY OF THE INVENTION

In order to solve the deficiencies of the prior art, the present invention proposes a gas detonation drive ultra-high-speed launch test system; the solution is to use combustible gas for detonation drive instead of gunpowder as the drive energy, but there are few data on the impact of debris on the The technical problem of analyzing the factors of performance in the ultra-high-speed launch state.

To achieve the above object, the present invention is achieved through the following technical solutions:

A gas detonation-driven ultra-high-speed launch test system according to the present invention includes:

The emitter assembly, the emitter assembly includes a plurality of detachably connected circular tubes, the end of the emitter assembly is sealed with a cover plate, the inside of the emitter assembly is provided with a polyethylene film, and the polyethylene film separates the emitter assembly into combustible gases The detonating tube section and the propagating tube section are two independent cavities, and the center of the propagating tube section is installed with the launched part; the combustible gas is a mixture of hydrogen and oxygen;

The target chamber, the target chamber is connected to one side of the propagation pipe section of the emitter assembly, the target body is fixed in the target chamber, and the back of the target body is provided with a buffer zone;

Gas distribution unit, the gas distribution unit is used to fill the projectile assembly with combustible oxyhydrogen gas, and the gas distribution unit is respectively connected with the round tube of the projectile assembly and the target chamber through pipelines. The gas distribution unit includes a gas cylinder and an air pump. Vacuum pumps, circulating pumps and air compressors;

Ignition unit, the ignition unit is fixedly installed in the circular tube of the detonator section of the launcher assembly, and the ignition unit adopts an electric spark igniter;

a detection unit, the detection unit is installed through a plurality of test ports opened on the pipe wall of the emitter assembly and the target chamber, and the detection unit includes a plurality of pressure sensors, flame sensors, laser detectors, and a measurement and control computer;

Controller, the controller is used to control the operation of the test system.

Preferably, a plug for blocking is also installed on the test port, and the plug is engaged with the test port through threads.

Preferably, a baffle is fixedly connected to the bottom of the plug, and the baffle closes the bottom end of the plug.

Preferably, the surface of the baffle is arranged in an arc shape, and the curvature of the arc shape is the same as the curvature of the round tube of the emitter assembly.

Preferably, a mark is provided on the top surface of the plug, and a mark is also provided on the surface of the circular tube of the emitter assembly in the circumferential direction of the test port.

Preferably, a launch hood is also installed in the launcher assembly, the launch hood is in the shape of a cone, the constricted end of the launch hood cone is facing the target chamber, the part to be fired is placed in the constricted end of the launch hood, and the launch hood passes through Its open end is fixed in the duct of the emitter assembly.

Preferably, the part to be launched is a cylinder, the head of the part to be launched is provided with a chamfered surface, the length of the chamfered surface is more than twice the diameter of the part to be launched, and the tail of the part to be launched is provided with a concave airfoil , the diameter of the airfoil is smaller than the diameter of the part being launched.

Preferably, a rifling is arranged on the inner wall of the constricted end of the launching hood, and the rifling makes the launcher act in a spiral state when it is driven to launch.

Preferably, an electric heating element is further arranged on the propagation pipe section of the emitter assembly, and the electric heating element is attached and fixed on the outer wall of the pipe of the emitter assembly by using an electric heating wire in a serpentine shape.

Preferably, the target chamber is further provided with a plurality of sections of attached tubes, the diameter of the attached tubes is larger than the diameter of the target chamber, and the attached tubes serve as buffer zones of the target chamber.

The beneficial effects of the present invention are as follows:

1. a kind of gas detonation drive ultra-high-speed launch test system of the present invention, by opening the test port on the tube wall of the emitter assembly, the propagation velocity of the detonation shock wave that generates after the gas is ignited by a pressure sensor and a flame sensor measurement and the propagation pressure change, cooperate with the laser sensor to record the launching speed of the emitted part, so that under different test conditions parameters, that is, the preparation ratio of oxyhydrogen gas in the pilot gas, the ignition position in the detonator section, the emitter component and the target Factors such as the length ratio between the chambers, the installation position of the polyethylene film in the emitter assembly, etc., affect the running speed of the emitted parts in the propagation pipe section in the target chamber, so as to verify the ultra-high speed of the boosted gas detonation drive test system. launch effect.

2. A gas detonation-driven ultra-high-speed launch test system of the present invention, through the inner concave arc surface arranged on the surface of the baffle, makes the bottom end of the plug installed on the test port, using the circle with the launcher assembly. The surface of the baffle plate with the same curvature of the tube makes the surface of the inner wall of the round tube tend to be smooth, and maintains the propagation speed of the detonation shock wave generated in the projectile assembly.

3. A kind of gas detonation drive ultra-high-speed launch test system of the present invention, by being arranged on the chamfered surface of the head of the part to be launched, the gas resistance received when being launched at high speed is reduced, and the wings opened on the surface of the part to be launched. The airfoil is used to further stabilize the flying attitude of the fired piece, and the airfoil is opened on the fired piece and formed into a concave shape, which is convenient to maintain the placement state of the fired piece on the constricted end of the launch hood.

Description of drawings

The present invention will be further described below in conjunction with the accompanying drawings.

Fig. 1 is the schematic diagram of the present invention;

Fig. 2 is the perspective view of the present invention;

Fig. 3 is the perspective view of the launch cover part in the present invention;

Fig. 4 is the perspective view of the plug member in the present invention;

Fig. 5 is the partial enlarged view of A place in Fig. 3;

In the figure: 1. Projector assembly; 11. Cover plate; 12. Pipeline; 13. Test port; 2. Launched part; 21. Chamfered surface; 22. Airfoil; 3. Target chamber; unit; 5, plug; 51, baffle; 52, logo; 6, launch cover; 61, rifling; 7, electric heating element; 8, attached pipe.

Detailed ways

In order to make the purpose, technical means and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention are described clearly and completely. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the implementations. example. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

The embodiment of the present invention provides a gas detonation-driven ultra-high-speed launch test system, which solves the problem that the existing use of combustible gas for detonation drive to replace gunpowder as a driving energy source, but there is less data on the impact of debris in the ultra-high-speed launch state. Performance factors to analyze technical issues;

The technical solution in the embodiment of the present invention is to solve the above-mentioned technical problems, and the general idea is as follows: a test port is opened on the pipe wall of the emitter assembly, and the propagation speed and propagation of the detonation shock wave generated after the gas is ignited are measured by a pressure sensor and a flame sensor. The pressure changes, and the laser sensor is used to record the emission speed of the object to be launched. Therefore, under different test conditions and parameters, that is, the preparation ratio of oxyhydrogen gas in the pilot gas, the ignition position in the detonator section, and the distance between the emitter assembly and the target chamber. Factors such as the proportional relationship between the length of the propagating tube and the installation position of the polyethylene film in the projectile assembly have the influence on the running speed of the projectile in the propagation tube section in the target chamber, so as to verify the ultra-high-speed launch effect of the enhanced gas detonation drive test system. ;

In order to better understand the above technical solutions, the above technical solutions will be described in detail below with reference to the accompanying drawings and specific embodiments.

As shown in Figures 1 and 2, a gas detonation-driven ultra-high-speed launch test system according to the present invention includes:

The emitter assembly 1. The emitter assembly 1 includes a plurality of detachably connected circular tubes. The end of the emitter assembly 1 is sealed with a cover plate 11. The inside of the emitter assembly 1 is provided with a polyethylene film. The polyethylene film seals the emitter. The component 1 is divided into two independent cavities, the detonating tube section of the combustible gas and the propagating tube section, the center of the propagating tube section is installed with the launcher 2; the combustible gas adopts the hydrogen-oxygen mixed gas;

The target chamber 3, the target chamber 3 is connected to one side of the propagation pipe section of the emitter assembly 1, the target body is fixed in the target chamber 3, and the back of the target body is provided with a buffer zone;

Gas distribution unit 4, the gas distribution unit 4 is used to fill the launcher assembly 1 with combustible oxyhydrogen gas, and the gas distribution unit 4 is respectively connected with the circular tube of the launcher assembly 1 and the target chamber 3 through the pipeline 12, and the gas distribution unit 4 Including gas cylinder, air pump, vacuum pump, circulating pump and air compressor;

Ignition unit, the ignition unit is fixedly installed in the circular tube of the detonator section of the launcher assembly 1, and the ignition unit adopts an electric spark igniter;

Detection unit, the detection unit is installed through a plurality of test ports 13 provided on the pipe wall of the emitter assembly 1 and the target chamber 3, and the detection unit includes a plurality of pressure sensors, flame sensors and laser detectors and a measurement and control computer;

Controller, the controller is used to control the operation of the test system;

During the test, firstly, according to the test requirements, the round tube is connected and sealed with flanges, rubber gaskets and asbestos gaskets to form the emitter assembly 1, and the air tightness is checked. Ready state; then start the vacuum pump in the gas distribution unit 4 that is connected to the emitter assembly 1 through the pipeline 2 to evacuate the emitter assembly 1 and the target chamber 3, after reaching the vacuum degree required by the test, close the vacuum pump and start The gas pump, fill the hydrogen and oxygen gas in different gas cylinders into the detonating tube section of the emitter assembly 1, so that the amount of hydrogen and oxygen gas filled can meet the volume fraction required for the test; then close the gas pump and start the circulation pump, The mixed gas in the detonating tube section in the emitter assembly 1 is stirred to form a uniform mixed gas, and then the valve on the pipeline 2 is closed to isolate the chamber of the emitter assembly 1 from the gas distribution unit 4; then start the detection unit, set related parameters, so that each sensor and measurement and control computer are in running state; then start the ignition unit, so that the ignited oxyhydrogen gas drives the air pressure in the detonating tube section of the emitter assembly 1 to rise, and breaks through the critical value of the polyethylene film to make it The rupture, the rupture of the polyethylene film causes the high-pressure gas in the detonating tube section in the emitter assembly 1 to quickly rush into the low-pressure propagation tube section, just like an ultrasonic gas "piston", pushing the driven gas in the low-pressure propagation tube section to the direction of the target chamber move, and drive the emitted part 2 to emit at high speed, record the data information collected by the pressure sensors and flame sensors on both sides of the polyethylene film in the emitter assembly 1, and record the emitted part 2 in the target chamber 3 through the laser sensor The speed during flight, and after the test is completed, observe and record the impact damage to the target body in the target chamber 3; after the data collection of the detonation test is completed, start the air compressor to carry out the normal operation of the projectile assembly 1 and the projectile assembly 1. Pressure purging to remove the exhaust gas in the pipeline 12 projectile assembly 1 projectile assembly 1, and replace and reset the fired part 2 and the target body for the next ultra-high-speed launch test;

The present invention utilizes the test port 13 opened on the pipe wall of the emitter assembly 1, measures the propagation speed and propagation pressure change of the detonation shock wave generated after the gas is ignited through the pressure sensor and the flame sensor, and cooperates with the laser sensor to record the emitted component 2. The firing speed, thus under different test conditions and parameters, that is, the preparation ratio of oxyhydrogen gas in the pilot gas, the ignition position in the detonator section, the length proportional relationship between the projectile assembly 1 and the target chamber 3, the projectile assembly 1 Factors such as the installation position of the medium polyethylene film affect the running speed of the ejected component 2 in the propagation pipe section in the target chamber 3, so as to verify the ultra-high-speed launch effect of the enhanced gas detonation drive test system.

As an embodiment of the present invention, as shown in FIGS. 2 and 4 , a plug 5 for blocking is also installed on the test port 13, and the plug 5 is engaged with the test port 13 through threads; at the beginning of the test Before, by installing each sensor or detector in the detection unit into the test port 13, in order to meet the quantitative requirements of the measurement parameters in different test processes and avoid insufficient or excessive measurement data, select an appropriate number of sensors and The detector element is installed on the test port 13 on the pipe wall of the emitter assembly 1 and the target chamber 3 to detect the propagation parameters of the detonation shock wave at the moment of gas ignition, and the remaining test port 13 is blocked by the threaded plug 5 , to maintain the airtightness of the emitter assembly 1 and the target chamber 3 , and conduct the launch test of the object to be launched 2 .

As an embodiment of the present invention, as shown in FIG. 4 , a baffle 51 is fixedly connected to the bottom of the plug 5, and the baffle 51 closes the bottom end of the plug 5; After the body assembly 1 or the point to be measured, and the other test ports 13 are sealed by the plug 5, since the bottom of the plug 5 is open, a local part will be formed on the wall of the round tube of the emitter assembly 1. The cavity, in turn, produces a local wave elimination effect on the detonation shock wave in the emitter assembly 1, which reduces the propagation speed of the detonation shock wave generated after the combustible gas is ignited; It is closed to avoid the formation of a local cavity on the tube wall of the emitter assembly 1, and the propagation speed of the detonation shock wave generated in the emitter assembly 1 is maintained.

As an embodiment of the present invention, as shown in FIG. 4 , the surface of the baffle 51 is arranged in an arc, and the curvature of the arc is the same as the curvature of the circular tube of the emitter assembly 1; the plug 5 is installed in the test port. After 13, the baffle 51 at the bottom of the plug 5 and the arc-shaped wall of the circular tube in the emitter assembly 1 will form an uneven surface on the inner wall of the circular tube, which will affect the propagation speed of the detonation shock wave in the emitter assembly 1. ; By being arranged on the concave arc surface on the surface of the baffle 51, the bottom end of the plug 5 installed on the test port 13 uses the baffle 51 surface with the same curvature arc as the circular tube of the emitter assembly 1 to make the circular The surface of the inner wall of the tube tends to be smooth, maintaining the propagation velocity of the detonation shock wave generated in the emitter assembly 1 .

As an embodiment of the present invention, as shown in FIGS. 2 and 4 , the top surface of the plug 5 is provided with a mark 52 , and the circular tube surface of the emitter assembly 1 in the circumferential direction of the test port 13 is also provided with a mark 52 ; During the test, the disconnected plug 5 is engaged in the test port 13 through threads. In order to maintain the sealing between the plug 5 and the test port 13, the tightening force is often controlled by a torque wrench to prevent insufficient sealing or insufficient sealing due to failure to tighten. Over-tightening damages the contact surface between the plug 5 and the test port 13; by setting the mark 52 on the surface of the plug 5 and the surface of the round tube of the emitter assembly 1, and matching the mark 52 with a common wrench, the plug 5 can be controlled during the test. The tightening state in the port 13 avoids over-tightening when installing the plug 5, protects the thread engaging between the test port 13 and the plug 5, and maintains the sealing between the plug 5 and the test port 13.

As an embodiment of the present invention, as shown in FIGS. 2 and 3 , a launch cover 6 is also installed in the launcher assembly 1 , the launch cover 6 is in the shape of a cone, and the constricted end of the cone of the launch cover 6 faces the target In the chamber 3, the projectile 2 is placed in the constricted end of the launch cover 6, and the launch cover 6 is fixed in the pipeline of the emitter assembly 1 through its open end; during the test, the combustible oxyhydrogen gas is The detonation tube section and the propagation tube section in the generator assembly perform detonation reaction, and the detonation shock wave acts on the emitted part 2 in the constricted end of the launch cover 6, and the energy of the detonation shock wave is used to drive the emitted part 2 to shoot along the target. The chamber 3 moves at a high speed; the launched part 2 is placed by the set launch cover 6, so that the launch part is located in the direction of the central axis of the pipeline of the projectile assembly 1, and the cone shape of the launch cover 6 is used to further increase the propagation of the detonation shock wave. speed, so that the placed projectile 2 can obtain sufficient driving speed of the detonation shock wave.

As an embodiment of the present invention, as shown in FIGS. 3 and 5 , the emitted part 2 is a cylinder, the head of the emitted part 2 is provided with a chamfered surface 21 , and the length of the chamfered surface 21 is greater than that of the emitted part 2 Twice the diameter of the piece 2, a concave airfoil 22 is opened at the tail of the piece to be launched Stability, otherwise it is easy to form an offset in the space of the target chamber 3 and destroy the impact test effect between the target 2 and the target. By setting the chamfered surface 21 on the head of the target 2, the impact of air resistance, the airfoil 22 opened on the surface of the launched part 2 is used to further stabilize the flying attitude of the launched part 2, and the airfoil 22 is opened on the launched part 2 and is concave, which is convenient to maintain the launched part 2 The state of being placed on the shrunken end of the launch hood 6.

As an embodiment of the present invention, as shown in FIG. 5 , a rifling 61 is provided on the inner wall of the constricted end of the launch cover 6 , and the rifling 61 makes the launch piece 2 in a spiral state when it is driven to launch; The slight deviation of the attitude of the launcher 2 will cause the deviation of its flight attitude, which will then affect its ultra-high-speed launch state. By opening the rifling 61 on the inner wall of the constricted end of the launcher 6, the launched part 2 is guided in the launcher 6. Spin is formed during internal movement, and after the launcher 2 is separated from the launch cover 6, the spin is used to stabilize the ballistic trajectory of the gyro to ensure the ultra-high-speed flying state of the launcher 2.

As an embodiment of the present invention, as shown in FIG. 2 , an electric heating element 7 is further provided on the propagation pipe section of the emitter assembly 1 , and the electric heating element 7 is attached and fixed to the pipe of the emitter assembly 1 by means of an electric heating wire serpentine. On the outer wall; during the test, a large amount of heat will be generated when the detonating gas is ignited, and part of the heat will be absorbed by the external environment through the emitter component 1. The electric heating element 7 on the component 1 increases the temperature of the propagation pipe section, slows down the heat loss caused by the energy of the detonation shock wave for heating up, maintains the enthalpy of the detonation shock wave, and ensures the driving speed of the detonation shock wave.

As an embodiment of the present invention, as shown in FIG. 2 , the target chamber 3 is further provided with a plurality of sections of attached tubes 8 . The diameter of the attached tubes 8 is larger than the diameter of the target chamber 3 , and the attached tubes 8 serve as the Buffer zone: During the test process, after the high-speed launch object 2 hits the target body, the detonation shock wave that propagates with it still has a large kinetic energy, which is destructive to the buffer zone of the target chamber 3 to a certain extent. The attached pipe 8, which is larger than its diameter, is arranged in the target chamber 3 to eliminate the propagating detonation shock wave, slow down the propagation energy of the detonation shock wave, and protect the buffer structure of the target chamber 3. The pipe 8 increases the volume of the target chamber 3 , which is convenient to increase the setting volume of the buffer zone and enhance the buffer function of the target chamber 3 .

The specific workflow is as follows:

During the test, firstly, according to the test requirements, the round tube is connected and sealed with flanges, rubber gaskets and asbestos gaskets to form the emitter assembly 1, and the air tightness is checked. Ready state; then start the vacuum pump in the gas distribution unit 4 that is connected to the emitter assembly 1 through the pipeline 2 to evacuate the emitter assembly 1 and the target chamber 3, after reaching the vacuum degree required by the test, close the vacuum pump and start The gas pump, fill the hydrogen and oxygen gas in different gas cylinders into the detonating tube section of the emitter assembly 1, so that the amount of hydrogen and oxygen gas filled can meet the volume fraction required for the test; then close the gas pump and start the circulation pump, The mixed gas in the detonating tube section in the emitter assembly 1 is stirred to form a uniform mixed gas, and then the valve on the pipeline 2 is closed to isolate the chamber of the emitter assembly 1 from the gas distribution unit 4; then start the detection unit, set related parameters, so that each sensor and measurement and control computer are in running state; then start the ignition unit, so that the ignited oxyhydrogen gas drives the air pressure in the detonating tube section of the emitter assembly 1 to rise, and breaks through the critical value of the polyethylene film to make it The rupture, the rupture of the polyethylene film causes the high-pressure gas in the detonating tube section in the emitter assembly 1 to quickly rush into the low-pressure propagation tube section, just like an ultrasonic gas "piston", pushing the driven gas in the low-pressure propagation tube section to the direction of the target chamber move, and drive the emitted part 2 to emit at high speed, record the data information collected by the pressure sensors and flame sensors on both sides of the polyethylene film in the emitter assembly 1, and record the emitted part 2 in the target chamber 3 through the laser sensor The speed during flight, and after the test is completed, observe and record the impact damage to the target body in the target chamber 3; after the data collection of the detonation test is completed, start the air compressor to carry out the normal operation of the projectile assembly 1 and the projectile assembly 1. Pressure purging to remove the exhaust gas in the pipeline 12 projectile assembly 1 projectile assembly 1, and replace and reset the fired part 2 and the target body for the next ultra-high-speed launch test; 1. The test port 13 on the pipe wall is used to measure the propagation speed and propagation pressure of the detonation shock wave generated after the gas is ignited through the pressure sensor and the flame sensor, and record the emission speed of the emitted part 2 with the laser sensor. Under the condition parameters, that is, the preparation ratio of oxyhydrogen gas in the pilot gas, the ignition position in the detonating tube section, the length ratio relationship between the emitter assembly 1 and the target chamber 3, the installation position of the polyethylene film in the emitter assembly 1 and other factors , the effect on the running speed of the emitted part 2 in the propagation tube section in the target chamber 3, so as to verify the ultra-high-speed launch effect of the boosted gas detonation drive test system; The component is located in the direction of the central axis of the pipeline of the projectile assembly 1, and the cone shape of the launch cover 6 is used to further increase the propagation speed of the detonation shock wave, so that the placed component 2 can obtain sufficient driving speed of the detonation shock wave; The chamfered surface 21 of the head of the launched part 2 reduces the gas resistance when it is launched at high speed, and the airfoil opened on the surface of the launched part 2 22, is used to further stabilize the flying attitude of the launched part 2, and the airfoil 22 is opened on the launched part 2 and formed into a concave shape, which is convenient to maintain the placement state of the launched part 2 placed on the constricted end of the launch cover 6.

The foregoing has shown and described the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above-mentioned embodiments. The above-mentioned embodiments and descriptions only illustrate the principle of the present invention. Without departing from the spirit and scope of the present invention, the present invention will also have Various changes and modifications fall within the scope of the claimed invention. The claimed scope of the present invention is defined by the appended claims and their equivalents.

Claims (10)

1. A gas detonation drive ultra-high speed launch test system, comprising:

the device comprises a launching body assembly (1), wherein the launching body assembly (1) comprises a plurality of sections of circular tubes which are detachably connected, a cover plate (11) is hermetically arranged at the end part of the launching body assembly (1), a polyethylene film is arranged in the launching body assembly (1), the launching body assembly (1) is divided into two independent cavities, namely a detonation tube section and a propagation tube section, of combustible gas by the polyethylene film, and a launched part (2) is arranged in the center of the propagation tube section;

the target chamber (3) is connected to one side of the transmission pipe section of the emitter component (1), a target body is fixed in the target chamber (3), and a buffer area is arranged on the back of the target body;

the gas distribution unit (4), the gas distribution unit (4) is used for filling combustible oxyhydrogen gas into the emitter component (1), the gas distribution unit (4) is respectively communicated with the round tube of the emitter component (1) and the target chamber (3) through a pipeline (12), and the gas distribution unit (4) comprises a gas cylinder, a gas transmission pump, a vacuum pump, a circulating pump and an air compressor;

the ignition unit is fixedly arranged in a circular tube of the detonation tube section of the emitter component (1);

the detection unit is installed through a plurality of test ports (13) formed in the pipe walls of the emitter component (1) and the target chamber (3), and comprises a plurality of pressure sensors, a flame sensor, a laser detector and a measurement and control computer;

and the controller is used for controlling the operation of the test system.

2. The gas detonation-driven ultra-high-speed emission testing system as claimed in claim 1, wherein a plug (5) for plugging is further mounted on the testing port (13), and the plug (5) is in threaded engagement with the testing port (13).

3. The gas detonation-driven ultra-high-speed emission testing system according to claim 2, wherein a baffle (51) is fixedly connected to the bottom of the plug (5), and the bottom end of the plug (5) is closed by the baffle (51).

4. The gas detonation-driven ultra-high-speed emission testing system according to claim 3, wherein the surface of the baffle (51) is arc-shaped, and the curvature of the arc is the same as that of the round tube of the emitter assembly (1).

5. A gas detonation drive ultra-high speed emission test system as claimed in claim 3, wherein the top surface of the plug (5) is provided with a mark (52), and the surface of the round tube of the emitter assembly (1) at the circumference of the test port (13) is also provided with a mark (52).

6. The gas detonation-driven ultra-high-speed emission testing system as claimed in claim 1, wherein a launch cap (6) is further installed in the emitter assembly (1), the launch cap (6) is in a cone shape, a reduced end of the cone of the launch cap (6) faces the target chamber (3), a to-be-emitted piece (2) is placed in the reduced end of the launch cap (6), and the launch cap (6) is fixed in a pipeline of the emitter assembly (1) through an open end thereof.

7. The gas detonation-driven ultra-high-speed launching test system as recited in claim 6, wherein the launched element (2) is a cylinder, the head of the launched element (2) is provided with a chamfer surface (21), the length of the chamfer surface (21) is more than twice the diameter of the launched element (2), the tail of the launched element (2) is provided with a concave airfoil surface (22), and the diameter of the airfoil surface (22) is less than the diameter of the launched element (2).

8. The gas detonation-driven ultra-high-speed launching test system as claimed in claim 6, wherein rifling (61) is arranged on the inner wall of the reduced end of the launching shield (6), and the rifling (61) enables the launched member (2) to be in a spiral state when being driven to launch.

9. The gas detonation drive ultra-high-speed emission testing system according to claim 6, characterized in that an electric heating element (7) is further arranged on the propagation pipe section of the emitter assembly (1), and the electric heating element (7) is attached and fixed to the outer wall of the pipeline of the emitter assembly (1) in a snake shape.

10. The gas detonation-driven ultra-high-speed launching test system as claimed in claim 1, wherein a plurality of sections of attached pipes (8) are further arranged in the target chamber (3), the pipe diameters of the attached pipes (8) are larger than the diameter of the target chamber (3), and the attached pipes (8) are used as buffer zones of the target chamber (3).

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