CN116573158A - High-low pressure chamber folding wing unmanned aerial vehicle catapulting test device based on gaseous fuel - Google Patents
High-low pressure chamber folding wing unmanned aerial vehicle catapulting test device based on gaseous fuel Download PDFInfo
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- CN116573158A CN116573158A CN202310543294.1A CN202310543294A CN116573158A CN 116573158 A CN116573158 A CN 116573158A CN 202310543294 A CN202310543294 A CN 202310543294A CN 116573158 A CN116573158 A CN 116573158A
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- 238000012360 testing method Methods 0.000 title claims abstract description 47
- 239000000446 fuel Substances 0.000 title claims abstract description 16
- 239000007789 gas Substances 0.000 claims description 67
- 239000002737 fuel gas Substances 0.000 claims description 15
- 230000001133 acceleration Effects 0.000 claims description 13
- 229910052802 copper Inorganic materials 0.000 claims description 9
- 239000010949 copper Substances 0.000 claims description 9
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 8
- 238000006243 chemical reaction Methods 0.000 claims description 7
- 230000008878 coupling Effects 0.000 claims description 7
- 238000010168 coupling process Methods 0.000 claims description 7
- 238000005859 coupling reaction Methods 0.000 claims description 7
- 239000012528 membrane Substances 0.000 claims description 7
- 238000010892 electric spark Methods 0.000 claims description 5
- 230000007246 mechanism Effects 0.000 claims description 5
- 238000003825 pressing Methods 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 5
- 229920001973 fluoroelastomer Polymers 0.000 claims description 4
- 230000009471 action Effects 0.000 claims description 3
- 230000006378 damage Effects 0.000 abstract description 7
- 239000002360 explosive Substances 0.000 abstract description 7
- 230000000977 initiatory effect Effects 0.000 abstract description 7
- 239000003380 propellant Substances 0.000 abstract description 3
- 239000001257 hydrogen Substances 0.000 description 9
- 229910052739 hydrogen Inorganic materials 0.000 description 9
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
- 238000004880 explosion Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 3
- 235000017491 Bambusa tulda Nutrition 0.000 description 3
- 241001330002 Bambuseae Species 0.000 description 3
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 3
- 239000011425 bamboo Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 150000002431 hydrogen Chemical class 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009172 bursting Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 239000003570 air Substances 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 229920003225 polyurethane elastomer Polymers 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/30—Use of alternative fuels, e.g. biofuels
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a high-low pressure chamber folding wing unmanned aerial vehicle ejection test device based on gas fuel. The device comprises a transmitting cylinder outer cylinder, a transmitting cylinder end cover, a high-pressure chamber, a transmitting load assembly, a pneumatic assembly, an ignition assembly, a gas film assembly, a testing assembly and a fixed positioning assembly; the transmitting cylinder end cover is provided with an inner connecting ring and an outer connecting ring, the transmitting cylinder end cover is connected with the transmitting cylinder outer cylinder through the outer connecting ring, one end of the transmitting cylinder outer cylinder is connected with one end of the high-pressure chamber through the inner connecting ring, the other end of the high-pressure chamber is a throat part, the throat part port is provided with an air film component, the inner wall of the transmitting cylinder outer cylinder is provided with a stop block for limiting the bullet holder, and a low-pressure chamber is formed among the high-pressure chamber, the transmitting cylinder outer cylinder and the bullet holder. The invention replaces initiating explosive devices such as propellant with gas fuel, and the application range is wider; the high-temperature and high-pressure gas is reduced to greatly overload, impact damage and high-temperature damage of the unmanned aerial vehicle through the high-pressure chamber and the low-pressure chamber.
Description
Technical Field
The invention belongs to the field of unmanned aerial vehicle emission tests, and particularly relates to a high-low pressure chamber folding wing unmanned aerial vehicle ejection test device based on gas fuel.
Background
For the launching of the folding wing unmanned aerial vehicle, a rocket boosting or ejection mode is adopted. The rocket boosting launching realizes taking off by utilizing a rocket booster carried by an unmanned plane, has good maneuverability and flexibility, but generates signals such as light, sound and the like during launching, has poor concealment and high cost, and meanwhile, the use of the propellant is limited and is difficult to popularize.
Catapulting refers to the conversion of other forms of energy into kinetic energy required for unmanned aerial vehicle take-off. The ejection can be classified into elastic element ejection, electromagnetic ejection, gas/hydraulic ejection, and cannon ejection according to the difference of the energy. The elastic element catapulting converts the energy stored when the element is compressed or stretched into the kinetic energy of the unmanned aerial vehicle by utilizing the elastic potential energy of elastic elements such as rubber bands, springs and the like. The unmanned aerial vehicle has the advantages of simple structure, convenient operation, reusability, no generation of severe emission environments such as high temperature and high pressure and the like, but is limited by the elastic limit of the elastic element, and is only suitable for the emission of a small unmanned aerial vehicle. The pneumatic/hydraulic ejection ejects the unmanned aerial vehicle along the transmitting rail by utilizing the pneumatic/hydraulic cylinder, and compared with the ejection of the elastic element, the device is more complex, but the thrust is larger, so that the pneumatic/hydraulic ejection device is suitable for the unmanned aerial vehicle with larger mass to launch. The basic principle of electromagnetic ejection is similar to that of a linear motor: the magnetic poles are arranged in the form of long straight tracks, the unmanned aerial vehicle or a part of the unmanned aerial vehicle is used as an armature, and the electromagnetic force applied to the unmanned aerial vehicle is utilized to push the unmanned aerial vehicle to accelerate until the unmanned aerial vehicle is launched. The transmitting mode has the advantages of small transmitting load, low cost, good concealment, convenient storage and transportation and the like. Compared with the gas/liquid ejection mode which is controlled by a gas/liquid bottle energy storage and a valve and provided with complex pipeline equipment, the ejection mode is directly controlled by a switch, and has better rapidity, higher control efficiency and higher control accuracy. However, the development of high-power pulse power supply technology, pulse linear motor technology, network control technology, ablation resistance technology and the like in the current electromagnetic track gun field is not particularly perfect, and the load of the order of tens to hundreds of grams can be accelerated to the speed of thousands of meters per second, so that the method is suitable for unmanned aerial vehicle emission with smaller mass.
The gas ejection utilizes a large amount of high-temperature and high-pressure gas generated by the gas generator to push the unmanned aerial vehicle to accelerate in the transmitting cylinder, and finally the unmanned aerial vehicle is transmitted like a projectile. The shooting is actually a kind of gas shooting. Currently, unmanned aerial vehicle gas catapult emission mainly has two forms: the first is that high-pressure gas directly acts on the unmanned aerial vehicle to eject the unmanned aerial vehicle; the second is to take the unmanned aerial vehicle as a warhead to the highest point of the trajectory by a rocket projectile or a shell, and then release the unmanned aerial vehicle. The gas ejection structure is simple and convenient to operate, but the impact and damage of high-temperature high-pressure gas generated in the process of emission to the unmanned aerial vehicle are large; meanwhile, high-pressure fuel gas is generated by utilizing initiating explosive devices and other initiating explosive devices, the use of the initiating explosive devices is limited, and in addition, the initiating explosive devices are high in storage requirement and insufficient in reliability and safety. If the gas fuel is adopted, the gas fuel is matched with a high-low pressure chamber structure, and on the basis of keeping the advantages of the gas ejection device, the limit of initiating explosive devices such as propellant can be effectively avoided, and the impact and damage of high-temperature high-pressure gas to the unmanned aerial vehicle structure are reduced.
In summary, the present folding wing unmanned aerial vehicle is launched by adopting launch modes such as rocket boosting, elastic element ejection, air/hydraulic ejection and the like, and the various launch modes have the defects of more or less device structure, difficult recycling, limited launch initiating explosive device, limited application range and the like.
Disclosure of Invention
The invention aims to provide a high-low pressure chamber folding wing unmanned aerial vehicle ejection test device based on gas fuel.
The technical solution for realizing the purpose of the invention is as follows: the high-low pressure chamber folding wing unmanned aerial vehicle ejection test device based on the gaseous fuel comprises an outer barrel of a transmitting barrel, an end cover of the transmitting barrel, a high-pressure chamber, a transmitting load assembly, a pneumatic assembly, an ignition assembly, an air film assembly, a test assembly and a fixed positioning assembly;
the end cover of the transmitting cylinder is provided with an inner connecting ring and an outer connecting ring, the transmitting cylinder is connected with the outer cylinder of the transmitting cylinder through the outer connecting ring, one end of the transmitting cylinder is connected with one end of a high-pressure chamber through the inner connecting ring, the other end of the high-pressure chamber is a throat part, a gas film component is arranged at a throat port, the inner wall of the outer cylinder of the transmitting cylinder is provided with a stop block for limiting a bullet holder of a transmitting load component, and a low-pressure chamber is formed among the high-pressure chamber, the inner part of the outer cylinder of the transmitting cylinder and the bullet holder;
the pneumatic assembly is used for filling fuel gas into the high-pressure chamber, the ignition assembly is used for igniting the fuel gas in the high-pressure chamber, the test assembly is used for testing the speed and the acceleration of the high-pressure chamber, the low-pressure chamber and the emission load, and the fixed positioning assembly is used for fixing and positioning the test device.
Further, one end of the high-pressure chamber is connected with the inner connecting ring of the transmitting cylinder end cover through threads, and the other end of the high-pressure chamber is connected with the diaphragm assembly through screws, and different high-pressure chambers are replaced according to the requirement of the test volume.
Further, the air film assembly comprises a film pressing piece and a film, one side of the film is provided with a prefabricated cross notch, and films with different thickness and notch depths are selected according to the emission demand pressure.
Further, the end cover of the transmitting cylinder is provided with four threaded holes
The pneumatic assembly comprises two high-pressure gas cylinders, the high-pressure gas cylinders are filled with fuel gas into the high-pressure chamber through copper pipes and guide pipe clamping sleeves respectively, and a pressure reducing valve, an electromagnetic valve and a manual ball valve are sequentially arranged on each copper pipe; one threaded hole of the transmitting cylinder end cover is connected with the catheter clamping sleeve.
Further, the device also comprises a pressure relief electromagnetic valve, and the pressure relief electromagnetic valve is connected with a threaded hole on the end cover of the transmitting cylinder through a high-pressure hose.
Further, the ignition assembly comprises an ignition needle, an igniter, a relay, a battery and a remote control switch;
the battery is connected with the igniter through the relay, and the relay is controlled through the remote control switch; when the circuit is on, the igniter boosts the voltage of the battery from a few volts to kilovolts through the oscillating circuit, and performs tip discharge to generate electric sparks so as to realize ignition.
Further, the launch load assembly further comprises a load body and a load head connected by threads;
the load main body is of a hollow structure, and the balancing weight is filled in the load main body.
Further, the test assembly comprises a high-pressure chamber sensor which is assembled on the end cover of the transmitting cylinder and used for testing the pressure and/or the temperature of the high-pressure chamber, a low-pressure chamber sensor which is assembled on the corresponding side wall of the low-pressure chamber of the outer cylinder of the transmitting cylinder and used for testing the pressure and/or the temperature of the low-pressure chamber, an acceleration sensor which is assembled in the hollow structure of the load main body, and a speed sensor which is assembled at the opening of the transmitting cylinder.
Further, the fixed positioning assembly comprises a force thermal coupling test bed and a supporting frame;
the force thermal coupling test bed realizes three-point clamping of the outer wall of the transmitting cylinder through the chuck screw and the chuck base; the chuck is moved through a bevel gear and a screw rod screw pair;
one end of the supporting frame is connected with the end cover of the transmitting cylinder, the other end of the supporting frame is propped against a wall during operation, and the pretightening force between the supporting frame and the end cover is increased through the spiral guide rod mechanism, so that the transmitting device caused by the reaction force of fuel gas during transmitting is prevented from moving.
Further, the bottom of the bullet support is provided with a skirt edge, and the skirt edge is pressed on the wall of the launching tube under the action of high-pressure gas to realize sealing; the periphery of the spring support is provided with a fluororubber O-shaped ring;
the acceleration sensor adopts piezoelectric type and is arranged on the transmitting load main body in a magnetic attraction mode; the speed sensor measures and calculates the speed of the load transmitting component through infrared signals.
Compared with the prior art, the invention has the remarkable advantages that:
after the experimental device is built, the end cover of the transmitting tube and the high-pressure chamber are screwed down, and a diaphragm requiring bursting pressure is installed on the end face of the high-pressure chamber by using a screw; subsequently, the end cap is rotated back with the high pressure chamber; sequentially loading the bullet holder and the equivalent emission load into the emission cylinder, and installing the bullet holder and the equivalent emission load at a designated position; sequentially opening a high-pressure gas cylinder, a pressure reducing valve and a manual ball valve of an electromagnetic valve, filling gas, observing the filling pressure through signals of a pressure sensor of a high-pressure chamber, closing a pneumatic pipeline when the filling pressure reaches a specified pressure, and filling with another gas; for working conditions such as hydrogen, air, methane, air and the like, in order to reduce possible risks such as leakage of flammable gases such as hydrogen and the like, high-pressure air is filled to a specified pressure, and gas fuels such as hydrogen, methane and the like are filled; after the gas fuel is filled, the relay is controlled by the remote switch, the circuit is conducted, the igniter amplifies the battery voltage through the oscillating circuit, the voltage is boosted to be up to kilovolts, the tip discharge is carried out, electric spark is generated, and the ignition is realized; the gas mixture is subjected to constant volume explosion, the pressure of the high-pressure chamber is continuously increased, when the specified explosion pressure is reached, the membrane is destroyed, the high-pressure gas rushes into the low-pressure chamber, the bullet holder is pushed to accelerate along the launching tube, and when the end of the launching tube is reached, the equivalent launching load has the required launching speed; the bullet holds in the palm and flies out outside the section of thick bamboo along with the transmission load, realizes the release of the inside high-pressure gas of transmission section of thick bamboo.
The invention considers the universality of different emission indexes for different emission loads, designs the high-pressure chamber into a modularized part, and realizes the adjustment of different load masses, different outlet speeds and different maximum overload by changing the volume of the high-pressure chamber and the throat area of the nozzle; meanwhile, the inside of the transmitting equivalent load is of a hollow structure, and simulation of unmanned aerial vehicles with different qualities can be realized by adding the balancing weight.
Considering that the transmitting device has the problems of unsuccessful ignition, unsuccessful membrane rupture after ignition and the like, the transmitting cylinder end cover is connected with the pressure relief electromagnetic valve through the high-pressure hose, the electromagnetic valve is normally closed, and the electromagnetic valve is opened after the power is on, so that the pressure relief of the high-pressure chamber is realized.
Considering that the high-pressure gas is sealed in the low-pressure chamber of the launching tube, the bottom of the bullet support is provided with a skirt edge, and the skirt edge is pressed on the wall of the tube under the action of the high-pressure gas to realize sealing; meanwhile, the periphery of the spring support is provided with a fluororubber O-shaped ring to further prevent gas leakage.
Drawings
Fig. 1 is a schematic structural diagram of an ejection test device of a folding wing unmanned aerial vehicle.
Fig. 2 is a main body portion of the ejection testing device of the present invention.
Fig. 3 is a partial schematic view of a cartridge end cap.
Fig. 4 is a partial cross-sectional view of the high and low pressure chambers.
Fig. 5 is a cross-sectional view of a launch canister of a loading folding wing drone.
Reference numerals illustrate:
the device comprises a 1-force thermal coupling test bed, a 2-support frame, a 3-high-pressure gas cylinder, a 4-pressure reducing valve, a 5-electromagnetic valve, a 6-manual ball valve, a 7-pressure releasing electromagnetic valve, an 8-copper pipe, a 9-sensor, a 10-ignition needle, an 11-backfire-proof valve, a 12-transmitting cylinder end cover, a 13-high-pressure chamber, a 14-transmitting cylinder outer cylinder, a 15-diaphragm pressing piece, a 16-diaphragm, a 17-equivalent transmitting load cover, a 18-equivalent transmitting load main body and a 19-spring holder.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings.
As shown in fig. 1-5, the high-low pressure chamber folding wing unmanned aerial vehicle catapulting experimental device based on the gas fuel comprises a transmitting device, an ignition assembly, a pneumatic assembly, a testing assembly, a transmitting load assembly and a fixed positioning assembly, and is characterized in that the transmitting device consists of a transmitting cylinder outer cylinder 14, a high-pressure chamber 13, a transmitting cylinder end cover 12 and a diaphragm assembly. The left end of the high-pressure chamber 13 is connected with the transmitting cylinder end cover 12 through threads, and the right end of the high-pressure chamber 13 is connected with the diaphragm assembly through screws, so that different high-pressure chambers 13 can be replaced according to the design volume requirement. The pre-emission high-pressure chamber 13 is used for filling the fuel gas mixture; after ignition, the gas mixture undergoes deflagration reaction, when the pressure in the high-pressure chamber reaches the set pressure, the diaphragm is broken, and the high-pressure gas enters the low-pressure chamber. The diaphragm assembly comprises a diaphragm pressing piece 15, a diaphragm 16, an O-ring and a screw. The high pressure chamber 13 is tightly assembled with the diaphragm assembly by screws in the order of the high pressure chamber, the O-ring, the diaphragm, and the diaphragm pressing member. One side of the membrane 16 is provided with a prefabricated cross notch, and the membranes with different thicknesses and notch depths can be selected according to the emission demand pressure. The transmitting cylinder end cover 12 is respectively connected with the high-pressure chamber 13 and the transmitting cylinder outer cylinder 14 through threads, and the transmitting devices are connected into a whole. The transmitting cylinder end cover 12 is provided with four threaded holes for connecting an ignition needle, a catheter clamping sleeve, a pressure relief electromagnetic valve hose and a high-pressure chamber sensor respectively. The launching tube outer cylinder 14 is a main component of the unmanned aerial vehicle launching device. The inner wall of the outer barrel 14 of the launching barrel is provided with a stop block for limiting the movement of the bullet holder, and the launching barrel part on the left side of the stop block forms an ejection low-pressure chamber; the right side is closely adjacent to the bullet support and the unmanned aerial vehicle. While the low pressure chamber portion of the cartridge outer barrel 14 is provided with a threaded bore for mounting a low pressure chamber sensor.
The ignition assembly comprises an ignition needle, an igniter, a relay, a battery and a remote control switch. The battery is connected with the igniter through the relay; the relay is controlled by a remote control switch. The design idea of the ignition component is as follows: when the circuit is on, the igniter boosts the voltage of the battery from a few volts to kilovolts through the oscillating circuit, and performs tip discharge to generate electric sparks so as to realize ignition. The remote control switch realizes remote ignition and avoids the injury to experimental personnel caused by accidents such as the over-high pressure of fuel gas, the destruction of the emission cylinder, the leakage of fuel gas and the like.
The pneumatic assembly comprises a high-pressure gas cylinder 3, a pressure reducing valve 4, an electromagnetic valve 5, a manual ball valve 6, an anti-backfire valve, a pressure releasing electromagnetic valve 7 and a copper pipe 8. The high-pressure gas cylinder 3 is filled with high-pressure gas such as hydrogen, air, oxygen and the like and is used for filling a gas mixture into the high-pressure chamber. The pressure reducing valve 4 is connected with an air outlet of the air bottle and controls the air outlet pressure. The electromagnetic valve 5 controls each air inlet pipeline. When in gas reaction, the explosion caused by gas leakage due to the fact that the ball valve is not closed and the like is prevented. The manual ball valve 6 is responsible for controlling a filling gas pipeline and is closed after filling is finished; and simultaneously forms double-layer safety with the electromagnetic valve 5. The backfire-proof valve 11 can prevent the gas from flowing backwards, and the high-temperature and high-pressure gas ignites the gas in the pipeline during the gas reaction to ignite the high-pressure gas cylinder to explode. The pressure relief electromagnetic valve 7 is connected with the high-pressure chamber 13 on the end cover through a high-pressure hose, and if the membrane cannot be broken normally, the gas in the high-pressure chamber can be discharged through the electromagnetic valve 5. Except the pressure relief electromagnetic valve 7, other pneumatic components are connected through copper pipes, and the copper pipes are good in tightness, firm and reliable.
The testing component comprises a high-pressure chamber pressure sensor, a temperature sensor, a low-pressure chamber pressure sensor, a temperature sensor, an acceleration sensor and a speed sensor. The high-pressure chamber sensor is arranged on the threaded hole of the end cover of the transmitting cylinder. In one aspect, the high pressure chamber sensor acts as a static pressure measurement device, primarily for controlling fuel and oxidant loading. When filling, gas is injected into the transmitting cylinder, the sensor signal is observed, and when the filling pressure is reached, the valve is closed, and the filling is completed. On the other hand, can be used for outputting the pressure change condition of the high-pressure chamber. The low-pressure chamber sensor is radially arranged on the threaded hole of the low-pressure chamber of the outer barrel of the transmitting barrel, so that the pressure sensor can measure the pressure change of the low-pressure chamber in the whole motion process of the transmitting load during test, and can be in direct contact with high-pressure gas to accurately express a high-frequency pressure signal. The acceleration sensor adopts a piezoelectric sensor and is installed on the transmitting load in a magnetic attraction mode, and the signal wire is led out from the cylinder mouth to prevent the influence of the transmitting load on the signal wire. The speed sensor is arranged at the cylinder opening of the transmitting cylinder and measures and calculates the speed of the unmanned aerial vehicle through infrared signals.
The emission load component comprises a bullet holder and an equivalent emission load. The main body of the bullet support is made of hard polyurethane elastomer, the lower part of the bullet support is designed to utilize the high pressure of fuel gas, the bottom of the bullet support is tightly attached to the wall of the emission cylinder, and the fuel gas is prevented from leaking; meanwhile, in order to meet the index of inner trajectory calculation, a space is reserved at the bottom of the bullet holder, and the space of the low-pressure chamber occupied by the wall thickness of the high-pressure chamber is made up. Considering dynamic sealing of fuel gas in a pressure-bearing state, the sealing between the bullet support and the outer cylinder is realized by using a fluororubber O-shaped ring when the bullet support is filled. The equivalent transmitting load consists of a load main body and a load head, and is connected through threads. The load main body is of a hollow structure and can be filled with a balancing weight and an acceleration sensor. The end part of the load head part is of a flat structure, so that the damage of impact to the equivalent emission load is reduced; through holes are formed in the periphery of the acceleration sensor, so that the acceleration sensor can be conveniently connected through cables.
The fixed positioning mechanism comprises a force thermal coupling test bed and a supporting frame. The force thermal coupling test bed realizes three-point clamping of the outer wall of the transmitting cylinder through mechanisms such as a chuck screw rod, a chuck base and the like, and has high clamping stability; the chuck is moved through the bevel gear and the screw rod screw pair, and the position of the transmitting device is adjusted. The support frame, one end is connected with the transmission section of thick bamboo end cover, and one end and wall connection through spiral guide arm mechanism, increase pretightning force between support frame and the end cover, prevent that the emitter that the gas reaction force caused from removing during the transmission.
Examples
Taking the unmanned aerial vehicle with the mass of 12kg, the outlet speed of 30m/s and the maximum overload of not more than 85g as an example, the gas fuel adopts a hydrogen/air mixture. In the experimental preparation stage, a transmitting cylinder outer cylinder, a transmitting cylinder end cover and a high-pressure chamber are sequentially arranged on a force thermal coupling test bed, and then pneumatic pipelines (a high-pressure gas cylinder, a pressure reducing valve, an electromagnetic valve, a manual ball valve and an anti-backfire valve) are sequentially connected with the transmitting cylinder end cover through a high-pressure hose or a copper pipe and are connected with the transmitting cylinder end cover through a clamping sleeve connector; the pressure relief electromagnetic valve is connected with the end cover through a high-pressure hose straight street; the ignition needle in the ignition circuit (battery, relay, igniter and ignition needle) is connected with the end cover through threads, and the relay is controlled through the remote control switch, so that the on-off of the circuit is realized; and then, installing a high-low pressure chamber sensor at the threaded hole of the transmitting cylinder, and completing the construction of the experimental system. In the preparation launching stage, the end cover of the launching tube and the high-pressure chamber are unscrewed, and a diaphragm with required bursting pressure is installed on the end face of the high-pressure chamber by using a screw; subsequently, the end cap is rotated back with the high pressure chamber; sequentially loading the bullet holder and the equivalent emission load into the emission cylinder, mounting the emission cylinder at a specified position, and internally mounting an acceleration sensor in the equivalent emission load for measuring the maximum overload of the unmanned aerial vehicle, wherein a cable is connected with the outside through an upper opening of a load cover; when filling gas, sequentially opening a high-pressure gas cylinder, a pressure reducing valve, an electromagnetic valve and a manual ball valve to fill gas, observing the filling pressure through signals of a pressure sensor of the high-pressure chamber, and when the filling pressure reaches a specified pressure, closing a pneumatic pipeline to replace another gas filling; for the hydrogen/air working condition, in order to reduce the possible risks of hydrogen leakage and the like, high-pressure air is filled to 2.27MPa, and hydrogen is filled to 3.23MPa. In the emission stage, after the gas fuel is filled, a relay is controlled through a remote switch, a circuit is conducted, an igniter amplifies the voltage of a battery through an oscillating circuit, the voltage is boosted to be up to kilovolts, tip discharge is carried out, electric spark is generated, and ignition is realized; the hydrogen mixture is subjected to constant volume explosion, the pressure of the high-pressure chamber is continuously increased, when the specified explosion pressure reaches 25MPa, the membrane is destroyed, high-pressure gas rushes into the low-pressure chamber, and the bomb support is pushed to accelerate along the launching tube; the infrared speed measuring device is arranged at the outlet of the transmitting cylinder and used for measuring the speed of the unmanned aerial vehicle; when the unmanned aerial vehicle reaches the tail end of the transmitting cylinder, the equivalent transmitting load has the required transmitting speed of 32m/s, and the bullet support flies out of the cylinder along with the transmitting load, so that the high-pressure gas in the transmitting cylinder is discharged. At the same time, the maximum overload of the load can be measured by transmitting the internal acceleration sensor of the load, and the maximum overload is not more than 80g.
Claims (10)
1. The high-low pressure chamber folding wing unmanned aerial vehicle ejection test device based on the gas fuel is characterized by comprising an outer barrel (14) of a transmitting barrel, an end cover (12) of the transmitting barrel, a high-pressure chamber (13), a transmitting load component, a pneumatic component, an ignition component, a gas film component, a test component and a fixed positioning component;
an inner connecting ring and an outer connecting ring are arranged on the transmitting cylinder end cover (12), the transmitting cylinder end cover is connected with the transmitting cylinder outer cylinder (14) through the outer connecting ring, one end of the transmitting cylinder outer cylinder (14) is connected with one end of a high-pressure chamber (13) through the inner connecting ring, the other end of the high-pressure chamber is a throat part, an air film component is arranged at a throat port, a stop block for limiting a bullet holder of a transmitting load component is arranged on the inner wall of the transmitting cylinder outer cylinder, and a low-pressure chamber is formed between the outer side of the high-pressure chamber (13), the inner side of the transmitting cylinder outer cylinder (14) and the bullet holder;
the pneumatic assembly is used for filling fuel gas into the high-pressure chamber, the ignition assembly is used for igniting the fuel gas in the high-pressure chamber, the test assembly is used for testing the speed and the acceleration of the high-pressure chamber, the low-pressure chamber and the emission load, and the fixed positioning assembly is used for fixing and positioning the test device.
2. Test device according to claim 1, characterized in that the high pressure chamber (13) is connected at one end by means of a screw thread to the inner connection ring of the cartridge end cap (12) and at the other end by means of a screw to the membrane module, whereby a different high pressure chamber (13) is replaced according to the test volume requirements.
3. The test device according to claim 2, wherein the air film assembly comprises a film pressing piece (15) and a film (16), one side of the film (16) is provided with a prefabricated cross notch, and films with different thicknesses and depths are selected according to the emission demand pressure.
4. A test device according to claim 3, wherein the cartridge end cap (12) is provided with four threaded holes
The pneumatic assembly comprises two high-pressure gas cylinders (3), the high-pressure gas cylinders (3) are respectively filled with fuel gas into a high-pressure chamber (13) through copper pipes (8) and conduit clamping sleeves, and a pressure reducing valve (4), an electromagnetic valve (5) and a manual ball valve (6) are sequentially arranged on each copper pipe (8); one of the threaded holes of the transmitting cylinder end cover (12) is connected with the catheter clamping sleeve.
5. The test device according to claim 4, further comprising a pressure relief solenoid valve (7), the pressure relief solenoid valve (7) being connected to a threaded hole in the cartridge end cap via a high pressure hose.
6. The test device of claim 5, wherein the ignition assembly comprises an ignition pin, an igniter, a relay, a battery, and a remote switch;
the battery is connected with the igniter through the relay, and the relay is controlled through the remote control switch; when the circuit is on, the igniter boosts the voltage of the battery from a few volts to kilovolts through the oscillating circuit, and performs tip discharge to generate electric sparks so as to realize ignition.
7. The test device of claim 6, wherein the launch load assembly further comprises a load body and a load head connected by threads;
the load main body is of a hollow structure, and the balancing weight is filled in the load main body.
8. The test device of claim 7, wherein the test assembly comprises a high pressure chamber sensor mounted on the cartridge end cap (12) for testing the pressure and/or temperature of the high pressure chamber, a low pressure chamber sensor mounted on the corresponding side wall of the low pressure chamber of the cartridge outer barrel (14) for testing the pressure and/or temperature of the low pressure chamber, an acceleration sensor mounted within the hollow structure of the load body, and a speed sensor mounted at the cartridge port.
9. The test device of claim 8, wherein the fixed positioning assembly comprises a force thermally coupled test stand and a support frame;
the force thermal coupling test bed realizes three-point clamping of the outer wall of the transmitting cylinder through the chuck screw and the chuck base; the chuck is moved through a bevel gear and a screw rod screw pair;
one end of the supporting frame is connected with the end cover of the transmitting cylinder, the other end of the supporting frame is propped against a wall during operation, and the pretightening force between the supporting frame and the end cover is increased through the spiral guide rod mechanism, so that the transmitting device caused by the reaction force of fuel gas during transmitting is prevented from moving.
10. The test device according to claim 9, wherein the bottom of the bullet holder is provided with a skirt edge, and the skirt edge is pressed on the wall of the launching tube under the action of high-pressure gas to realize sealing; the periphery of the spring support is provided with a fluororubber O-shaped ring;
the acceleration sensor adopts piezoelectric type and is arranged on the transmitting load main body in a magnetic attraction mode; the speed sensor measures and calculates the speed of the load transmitting component through infrared signals.
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