CN114413693A - Gas detonation drive ultra-high speed launching test system - Google Patents
Gas detonation drive ultra-high speed launching test system Download PDFInfo
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- CN114413693A CN114413693A CN202210079526.8A CN202210079526A CN114413693A CN 114413693 A CN114413693 A CN 114413693A CN 202210079526 A CN202210079526 A CN 202210079526A CN 114413693 A CN114413693 A CN 114413693A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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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
Technical Field
The invention belongs to the technical field of gas detonation testing, and particularly relates to a gas detonation-driven ultra-high-speed launching testing system.
Background
The ballistic target is a test device which emits a test projectile to a preset speed, measures aerodynamic parameters of the projectile in the flying process, and verifies the impact and damage performance of the projectile on a target plate, such as simulating the problem of space fragment protection, the space fragment with the mass of gram level and the average speed of 10km/s has extremely strong damage capability to an in-orbit spacecraft, is mainly resisted by the structural design of the spacecraft, and needs to be subjected to test simulation in order to research and design a corresponding protection technology.
Based on the research of relevant theory, Zhao Feng, the test and comment research [ D ] of the high-speed metal flying piece driven by the strong detonation of explosive, in this article, the experiment and theory prove that the high-speed metal flying piece driven by the strong detonation of explosive is feasible, but the gas molecules of the common gunpowder used for detonation are large in mass and low in sound velocity, the detonation driving speed capable of being generated is limited, and the toxic product of the gunpowder can also pollute the test testing device, therefore, the combustible gas is adopted for detonation driving to replace the gunpowder as the driving energy source, but few data are used for analyzing the factors influencing the performance of the fragments in the ultra-high-speed launching state.
In view of this, in order to verify that the ultra-high-speed launching effect of the gas detonation drive test system is improved under different test condition parameters, the invention provides a gas detonation drive ultra-high-speed launching test system.
Disclosure of Invention
In order to solve the defects of the prior art, the invention provides a gas detonation drive ultra-high speed launching test system; the technical problem that the factors influencing the performance of fragments in an ultra-high-speed launching state are analyzed by less data is solved by adopting combustible gas to carry out detonation driving to replace gunpowder as driving energy.
In order to achieve the above purpose, the invention is realized by the following technical scheme:
the invention relates to a gas detonation drive ultra-high speed launching test system, which comprises:
the device comprises a launching body assembly, a gas-liquid separation assembly and a gas-liquid separation assembly, wherein the launching body assembly comprises a plurality of sections of circular tubes which are detachably connected, a cover plate is hermetically arranged at the end part of the launching body assembly, a polyethylene film is arranged in the launching body assembly, the polyethylene film divides the launching body assembly into two independent cavities, namely an initiation pipe section and a propagation pipe section, of combustible gas, and a launched piece is arranged in the center of the propagation pipe section; wherein the combustible gas adopts mixed gas of hydrogen and oxygen;
the target chamber is connected to one side of the transmission pipe section of the emitter assembly, a target body is fixed in the target chamber, and the back of the target body is provided with a buffer area;
the gas distribution unit is used for filling combustible oxyhydrogen gas into the emitter assembly, is respectively communicated with the circular tube and the target chamber of the emitter assembly through pipelines, and 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 and adopts an electric spark igniter;
the detection unit is installed through a plurality of test ports formed in the pipe walls of the emitter assembly and the target chamber 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.
Preferably, a plug for plugging is further installed on the test port, and the plug is meshed with the test port through threads.
Preferably, the bottom of the plug is fixedly connected with a baffle, and the bottom end of the plug is closed by the baffle.
Preferably, the surface of the blocking piece is arc-shaped, and the curvature of the arc is the same as that of a circular tube of the emitter assembly.
Preferably, the top surface of the plug is provided with a mark, and the surface of the round tube of the emitter component in the circumferential direction of the test port is also provided with a mark.
Preferably, still install the launching shield in the emitter subassembly, the launching shield is the awl tube-shape, and the throat end of launching shield awl tube is towards the target chamber, has placed in the throat end of launching shield and has been launched the piece, and the launching shield is fixed in the pipeline of emitter subassembly through its open end.
Preferably, the launched part adopts a cylinder, the head of the launched part is provided with a chamfer surface, the length of the chamfer surface is more than twice of the diameter of the launched part, the tail of the launched part is provided with a concave wing surface, and the diameter of the wing surface is less than the diameter of the launched part.
Preferably, the inner wall of the reducing end of the launching shield is provided with rifling, and the rifling enables the launching piece to be in a spiral state when being driven to launch.
Preferably, an electric heating element is further arranged on the transmission pipe section of the emitter component, and the electric heating element is fixed on the outer wall of the pipeline of the emitter component in a snake-shaped attaching mode through a heating wire.
Preferably, the target chamber is also provided with a plurality of sections of auxiliary pipes, the pipe diameter of each auxiliary pipe is larger than that of the target chamber, and the auxiliary pipes are used as buffer areas of the target chamber.
The invention has the following beneficial effects:
1. the gas detonation drive ultra-high speed launching test system measures the propagation speed and the propagation pressure change of detonation shock waves generated after gas is ignited through the test port arranged on the pipe wall of the launching body assembly through the pressure sensor and the flame sensor, records the launching speed of a launched piece in cooperation with the laser sensor, and accordingly influences the running speed of the launched piece in the target chamber in the propagation pipe section on the factors of different test condition parameters, namely the preparation proportion of oxyhydrogen gas in ignition gas, the ignition position in the initiation pipe section, the length proportional relation between the launching body assembly and the target chamber, the installation position of a polyethylene film in the launching body assembly and the like, and accordingly verifies and improves the ultra-high speed launching effect of the gas detonation drive test system.
2. According to the gas detonation-driven ultra-high-speed launching test system, the inner concave cambered surface is arranged on the surface of the baffle, so that the bottom end of the plug installed on the test port is smooth on the surface of the baffle with the same curvature and arc shape as the circular pipe of the launching body assembly, and the propagation speed of detonation shock waves generated in the launching body assembly is maintained.
3. According to the gas detonation-driven ultra-high-speed launching test system, the gas resistance borne by the launched piece during high-speed launching is reduced through the chamfer surface arranged at the head of the launched piece, the wing surface arranged on the surface of the launched piece is used for further stabilizing the flying posture of the launched piece, and the wing surface is arranged on the launched piece and is concave, so that the placing state of the launched piece at the necking end of the launching shield is maintained conveniently.
Drawings
The invention will be further explained with reference to the drawings.
FIG. 1 is a schematic view of the present invention;
FIG. 2 is a perspective view of the present invention;
FIG. 3 is a perspective view of the discharge cap assembly of the present invention;
FIG. 4 is a perspective view of a plug assembly of the present invention;
FIG. 5 is an enlarged view of a portion of FIG. 3 at A;
in the figure: 1. an emitter assembly; 11. a cover plate; 12. a pipeline; 13. a test port; 2. a launched member; 21. chamfering; 22. an airfoil; 3. a target chamber; 4. a gas distribution unit; 5. a plug; 51. a baffle plate; 52. identifying; 6. a transmitting cover; 61. rifling; 7. an electric heating element; 8. and (4) attaching a pipe.
Detailed Description
In order to make the objects, technical means and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention are clearly and completely described, and it is obvious that the described embodiments are a part of the embodiments of the present invention, but not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention provides a gas detonation-driven ultra-high-speed launching test system, which solves the technical problem that the existing combustible gas is adopted for detonation driving to replace gunpowder as driving energy, but few data are used for analyzing the factors influencing the performance of fragments in an ultra-high-speed launching state;
in order to solve the technical problems, the technical scheme in the embodiment of the invention has the following general idea: the testing port is formed in the pipe wall of the emitter component, the propagation speed and the propagation pressure change of detonation shock waves generated after gas ignition are measured through the pressure sensor and the flame sensor, and the laser sensor is matched to record the emission speed of an emitted piece, so that under different test condition parameters, namely the preparation proportion of oxyhydrogen gas in ignition gas, the ignition position in a detonation pipe section, the length proportional relation between the emitter component and a target chamber, the installation position of a polyethylene film in the emitter component and other factors, the influence on the running speed of the emitted piece in the propagation pipe section in the target chamber is realized, and the ultrahigh-speed emission effect of the gas detonation drive testing system is verified and improved;
in order to better understand the technical solution, the technical solution will be described in detail with reference to the drawings and the specific embodiments.
As shown in fig. 1 and 2, the system for testing ultra-high speed emission driven by gas detonation comprises:
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 and divides the launching body assembly 1 into two independent cavities, namely an initiation pipe section and a propagation pipe section, of combustible gas, and a launched part 2 is arranged in the center of the propagation pipe section; wherein the combustible gas adopts mixed gas of hydrogen and oxygen;
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 is used for filling combustible oxyhydrogen gas into the emitter component 1, the gas distribution unit 4 is respectively communicated with the circular 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 and adopts an electric spark igniter;
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;
the controller is used for controlling the operation of the test system;
during testing, firstly, connecting and sealing a circular pipe by adopting a flange plate, a rubber gasket and an asbestos gasket through bolts according to the testing requirement to form an emitter assembly 1, checking the air tightness, and debugging all instrument equipment and keeping the instrument equipment in a working preparation state; then starting a vacuum pump in the gas distribution unit 4, which is communicated to the emitter assembly 1 through the pipeline 2, vacuumizing the emitter assembly 1 and the target chamber 3, after the vacuum degree required by the test is achieved, closing the vacuum pump and starting a gas transmission pump, and filling hydrogen and oxygen in different gas cylinders into a detonation pipe section of the emitter assembly 1 so that the amount of filled hydrogen and oxygen meets the volume fraction required by the test; then, the gas transmission pump is closed and the circulating pump is started, the mixed gas in the detonation pipe section in the emitter component 1 is stirred to form uniform mixed gas, and then the valve on the pipeline 2 is closed, so that the cavity of the emitter component 1 is isolated from the gas distribution unit 4; then starting a detection unit, setting relevant parameters and enabling each sensor and the measurement and control computer to be in an operating state; starting an ignition unit, so that ignited oxyhydrogen gas drives the air pressure in an initiation pipe section of the emitter assembly 1 to rise, and breaks through the critical value of a polyethylene film to break the polyethylene film, the polyethylene film breaks to enable high-pressure gas in the initiation pipe section in the emitter assembly 1 to rapidly rush into a low-pressure propagation pipe section, the low-pressure propagation pipe section is just like an ultrasonic gas piston, driven gas in the low-pressure propagation pipe section is pushed to move towards a target chamber direction, the emitted piece 2 is driven to be emitted at a high speed, data information collected by pressure sensors and flame sensors on two sides of the polyethylene film in the emitter assembly 1 is recorded, the flying speed of the emitted piece 2 in the target chamber 3 is recorded through a laser sensor, and after a test is finished, the impact damage condition of the target body in the target chamber 3 is observed and recorded; after data collection of detonation test is finished, starting an air compressor to perform positive pressure purging on the emitter component 1 of the emitter component 1, removing waste gas in the emitter component 1 of the pipeline 12, and replacing and resetting the emitted piece 2 and the target body to perform next test of ultra-high-speed emission;
the invention utilizes the test port 13 arranged on the tube wall of the emitter component 1, measures the propagation speed and the propagation pressure change of detonation shock waves generated after gas ignition through the pressure sensor and the flame sensor, and records the emission speed of the emitted piece 2 by matching with the laser sensor, so that under different test condition parameters, namely the preparation proportion of oxyhydrogen gas in ignition gas, the ignition position in a detonation tube section, the length proportional relation between the emitter component 1 and a target chamber 3, the installation position of a polyethylene film in the emitter component 1 and other factors, the invention has influence on the running speed of the emitted piece 2 in the target chamber 3 in the propagation tube section, thereby verifying and improving the ultra-high speed emission effect of the gas detonation drive test system.
As an embodiment of the invention, as shown in fig. 2 and 4, a plug 5 for plugging is further installed on the test port 13, and the plug 5 is engaged with the test port 13 through threads; before the test is started, all sensors or detectors in the detection unit are respectively installed in the test ports 13, in order to meet the quantity requirements of measurement parameters in different test processes and avoid insufficient or excessive measurement data quantity, proper quantity of sensors and detector elements are selected to be installed on the test ports 13 on the pipe walls of the emitter assembly 1 and the target chamber 3, the propagation parameters of gas ignition instant detonation shock waves are detected, the rest test ports 13 are plugged through the plugs 5 which are meshed with threads, the sealing performance of the emitter assembly 1 and the target chamber 3 is maintained, and the emission test of the emitted piece 2 is carried out.
As an embodiment of the present invention, as shown in fig. 4, a blocking piece 51 is fixedly connected to the bottom of the plug 5, and the blocking piece 51 closes the bottom end of the plug 5; before the test is started, the emitter assembly 1 or the point position to be measured is selected, and after other test ports 13 are sealed by the plugs 5, local cavities are formed on the pipe walls of the circular pipes of the emitter assembly 1 due to the fact that the bottoms of the plugs 5 are open, so that local wave absorption is generated on detonation shock waves in the emitter assembly 1, and the propagation speed of the detonation shock waves generated after combustible gas is ignited is reduced; the bottom end of the baffle 51 arranged at the bottom of the plug 5 is closed, so that a local cavity is prevented from being formed on the pipe wall of the round pipe of the emitter component 1, and the propagation speed of detonation shock waves generated in the emitter component 1 is maintained.
As an embodiment of the present invention, as shown in fig. 4, the surface of the blocking plate 51 is arc-shaped, and the curvature of the arc is the same as the curvature of the circular tube of the projectile assembly 1; after the plug 5 is installed in the test port 13, the baffle 51 at the bottom end of the plug 5 and the arc-shaped wall of the circular tube in the emitter assembly 1 form an uneven surface on the inner wall of the circular tube, so that the propagation speed of detonation shock waves in the emitter assembly 1 is influenced; the bottom end of the plug 5 installed on the test port 13 is made to approach the surface of the circular tube inner wall to be smooth by the concave arc surface arranged on the surface of the baffle 51 and utilizing the surface of the baffle 51 with the same curvature and arc shape as the circular tube of the projectile assembly 1, thereby maintaining the propagation speed of the detonation shock wave generated in the projectile assembly 1.
As an embodiment of the present invention, as shown in fig. 2 and 4, 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 around the test port 13 is also provided with a mark 52; in the testing process, the plug 5 which is detachably connected is meshed in the testing port 13 through threads, and in order to keep the sealing performance between the plug 5 and the testing port 13, the screwing force is controlled through a torque wrench usually, so that the contact surface between the plug 5 and the testing port 13 is prevented from being damaged due to insufficient sealing or excessive screwing caused by unthreading; through setting up sign 52 on the surface of end cap 5 and emitter subassembly 1 pipe surface, through ordinary spanner cooperation sign 52, can control the state of screwing of end cap 5 in test port 13, the condition of excessively screwing when avoiding installing end cap 5 protects the screw thread of meshing between test port 13 and end cap 5, maintains the leakproofness between end cap 5 and test port 13.
As an embodiment of the invention, as shown in fig. 2 and 3, a launching shield 6 is further installed in the projectile body assembly 1, the launching shield 6 is in a cone shape, a reduced end of the cone of the launching shield 6 faces the target chamber 3, a launched piece 2 is placed in the reduced end of the launching shield 6, and the launching shield 6 is fixed in a pipeline of the projectile body assembly 1 through an open end thereof; in the testing process, after being ignited, combustible oxyhydrogen gas carries out detonation reaction along a detonating tube section and a propagation tube section in a generator assembly, detonation shock waves act on the to-be-launched piece 2 in the necking end of the launching shield 6, and the energy of the detonation shock waves is utilized to drive the to-be-launched piece 2 to be launched out to move at a high speed along the target chamber 3; the launched element 2 is placed through the arranged launching shield 6, the launched element is positioned in the central shaft direction of the pipeline of the launcher assembly 1, the propagation speed of the detonation shock wave in the launched element is further increased by utilizing the conical cylinder shape of the launching shield 6, and the placed launched element 2 obtains sufficient driving speed of the detonation shock wave.
As an embodiment of the present invention, as shown in fig. 3 and 5, the launched part 2 is a cylinder, the head of the launched part 2 is provided with a chamfer 21, the length of the chamfer 21 is greater than twice the diameter of the launched part 2, the tail of the launched part 2 is provided with a concave airfoil 22, and the diameter of the airfoil 22 is smaller than the diameter of the launched part 2; in the testing process, the high-speed launched piece 2 needs to keep the stability of flight, otherwise, the space of the target chamber 3 is easy to form deviation to destroy the collision testing effect between the launched piece 2 and the target body, the gas resistance received when the launched piece is launched at high speed is reduced through the chamfer surface 21 arranged at the head of the launched piece 2, the wing surface 22 arranged on the surface of the launched piece 2 is used for further stabilizing the flight attitude of the launched piece 2, and the wing surface 22 is arranged on the launched piece 2 and is concave, so that the placing state of the launched piece 2 at the necking end of the launching shield 6 is maintained.
As an embodiment of the present invention, as shown in fig. 5, the inner wall of the reducing end of the launching shield 6 is provided with rifling 61, and the rifling 61 makes the launching member 2 in a spiral state when being driven to launch; in the test process, the deviation of the flying posture of the launched element 2 can be caused by the slight deviation of the posture, the ultra-high speed launching state of the launched element is further influenced, the rifling 61 is arranged on the inner wall of the necking end of the launching shield 6 to guide the launched element 2 to form spin when moving in the launching shield 6, and the stable trajectory which plays a role in gyro stability by utilizing the spin after the launched element 2 is separated from the launching shield 6 is used for ensuring the ultra-high speed flying state of the launched element 2.
As an embodiment of the present invention, as shown in fig. 2, an electric heating element 7 is further disposed on the propagation pipe section of the emitter assembly 1, and the electric heating element 7 is fixed on the outer wall of the pipe of the emitter assembly 1 by serpentine attachment of an electric heating wire; in the test process, a large amount of heat can be generated while igniting the detonation gas, and part of the heat is absorbed by the external environment through the emitter assembly 1, and due to the high enthalpy energy of the detonation shock wave, the electric heating element 7 attached to the emitter assembly 1 improves the temperature of the propagation pipe section, slows down the heat loss caused by the temperature rise due to the energy of the detonation shock wave, maintains the enthalpy value 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, a plurality of sections of attached pipes 8 are further disposed in the target chamber 3, the pipe diameter of the attached pipe 8 is larger than the diameter of the target chamber 3, and the attached pipe 8 serves as a buffer zone of the target chamber 3; in the test process, by the high-speed launch by launcher 2 behind the impact target body, still have great kinetic energy along with the detonation shock wave of propagation, buffer to target chamber 3 has certain destructiveness, through setting up the accessory tube 8 that is greater than its pipe diameter in target chamber 3, a wave elimination effect is played to the detonation shock wave of propagation, slow down the propagation energy of detonation shock wave, protect the buffer structure of target chamber 3, and the accessory tube 8 that sets up has increased the 3 volumes of target chamber, be convenient for improve the volume that sets up of buffer, strengthen the buffer function of target chamber 3.
The specific working process is as follows:
during testing, firstly, connecting and sealing a circular pipe by adopting a flange plate, a rubber gasket and an asbestos gasket through bolts according to the testing requirement to form an emitter assembly 1, checking the air tightness, and debugging all instrument equipment and keeping the instrument equipment in a working preparation state; then starting a vacuum pump in the gas distribution unit 4, which is communicated to the emitter assembly 1 through the pipeline 2, vacuumizing the emitter assembly 1 and the target chamber 3, after the vacuum degree required by the test is achieved, closing the vacuum pump and starting a gas transmission pump, and filling hydrogen and oxygen in different gas cylinders into a detonation pipe section of the emitter assembly 1 so that the amount of filled hydrogen and oxygen meets the volume fraction required by the test; then, the gas transmission pump is closed and the circulating pump is started, the mixed gas in the detonation pipe section in the emitter component 1 is stirred to form uniform mixed gas, and then the valve on the pipeline 2 is closed, so that the cavity of the emitter component 1 is isolated from the gas distribution unit 4; then starting a detection unit, setting relevant parameters and enabling each sensor and the measurement and control computer to be in an operating state; starting an ignition unit, so that ignited oxyhydrogen gas drives the air pressure in an initiation pipe section of the emitter assembly 1 to rise, and breaks through the critical value of a polyethylene film to break the polyethylene film, the polyethylene film breaks to enable high-pressure gas in the initiation pipe section in the emitter assembly 1 to rapidly rush into a low-pressure propagation pipe section, the low-pressure propagation pipe section is just like an ultrasonic gas piston, driven gas in the low-pressure propagation pipe section is pushed to move towards a target chamber direction, the emitted piece 2 is driven to be emitted at a high speed, data information collected by pressure sensors and flame sensors on two sides of the polyethylene film in the emitter assembly 1 is recorded, the flying speed of the emitted piece 2 in the target chamber 3 is recorded through a laser sensor, and after a test is finished, the impact damage condition of the target body in the target chamber 3 is observed and recorded; after data collection of detonation test is finished, starting an air compressor to perform positive pressure purging on the emitter component 1 of the emitter component 1, removing waste gas in the emitter component 1 of the pipeline 12, and replacing and resetting the emitted piece 2 and the target body to perform next test of ultra-high-speed emission; the method comprises the steps that a test port 13 formed in the pipe wall of an emitter component 1 is utilized, the propagation speed and the propagation pressure change of detonation shock waves generated after gas ignition are measured through a pressure sensor and a flame sensor, and the laser sensor is matched to record the emission speed of an emitted piece 2, so that under different test condition parameters, namely the preparation proportion of oxyhydrogen in ignition gas, the ignition position in a detonation pipe section, the length proportional relation between the emitter component 1 and a target chamber 3, the installation position of a polyethylene film in the emitter component 1 and other factors, the influence on the running speed of the emitted piece 2 in the propagation pipe section in the target chamber 3 is realized, and the ultrahigh-speed emission effect of the gas detonation drive test system is verified and improved; the launching shield 6 is arranged to place the launched element 2, so that the launched element is positioned in the central axis direction of the pipeline of the launcher assembly 1, and the conical cylinder shape of the launching shield 6 is utilized to further increase the propagation speed of the detonation shock wave therein, so that the placed launched element 2 obtains sufficient driving speed of the detonation shock wave; the chamfer surface 21 arranged at the head of the launched part 2 reduces the gas resistance received when the launched part is launched at high speed, the wing surface 22 arranged on the surface of the launched part 2 is used for further stabilizing the flying posture of the launched part 2, and the wing surface 22 is arranged on the launched part 2 and is concave, so that the placing state of the launched part 2 placed at the necking end of the launching shield 6 is maintained.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
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).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210079526.8A CN114413693B (en) | 2022-01-24 | 2022-01-24 | Gas detonation driving ultra-high-speed emission testing system |
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|---|---|---|---|
| CN202210079526.8A CN114413693B (en) | 2022-01-24 | 2022-01-24 | Gas detonation driving ultra-high-speed emission testing system |
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| CN118067951A (en) * | 2024-04-10 | 2024-05-24 | 吉林大学 | Ultrasonic energetic material detonating device and ultrasonic energetic material detonating method |
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