241 results about "Explosive device" patented technology

An explosive downhole tool includes a housing having an upper housing part on one side of a window section and a lower housing part on an opposite side of the window section. An explosive charge is provided within the housing for cutting or expanding the wall of the tubular. The majority of outer surface of at least one of the upper and lower housing part in cross-section is rounded so as to be devoid of corners. The rounded surface eliminates the presence of sharp corners that may catch on restrictions or protrusions in a wellbore so that the downhole tool is more easily conveyable within a wellbore. Another explosive downhole tool includes fins extending from the housing. The fins have a height that decreases in a direction away from the housing. The shape of the fins enables the downhole tool to be more easily conveyable within the wellbore.

The invention discloses an intelligent fuse, which comprises a conductor pre-fracture, an explosion device, a cutting device and an amplitude limiter, and is characterized in that the amplitude limiter is connected in series between the explosion device and a conductor at the front end of the conductor pre-fracture and is used for transmitting a generated voltage drop signal to the explosion device when an external circuit is short-circuited; the explosion device comprises two external signal input ports, one external signal input port is connected with the amplitude limiter, and the other external signal input port is connected with the external signal receiver; and the energy generated by the explosion device cuts off the conductor pre-fracture. Based on a transformer-free circuit structure, intelligent control of a circuit trigger signal and an external trigger signal on the fuse is realized, high and low voltage isolation is realized, the current can be automatically cut off at the moment when an external control signal is received or the current exceeds a detection threshold, and finally the purpose of improving the safety of an electrical system is achieved.

The invention belongs to the technical field of aircraft recovery, and provides an aircraft controllable parachute recovery device which comprises a parachute opening motor (1), a motor support (2), a motor rocker arm (3), a connecting rod (4), a recovery parachute cabin (5), a parachute cabin cover (6), a parachute cabin locking block torsional spring (9), a locking block rotating shaft (10), a driving rod (11), an unlocking hook (12), a spring guide rod (13), an initial locking rod (14), a parachute opening shaft (21), a parachute opening compression spring (18), a parachute hanging screw (17), a recovery parachute (19), a tower spring (20) and a tower spring pressing plate (15). According to the technical scheme, the motor drives the connecting rod mechanism to unlock, the tower spring and the pressure spring are combined to open the parachute, and the problems that an initiating explosive device is low in safety, poor in testability, unrepeatable in recovery and the like are solved.

The invention provides a test system and method for a general integrated electrical system of a carrier rocket, and relates to the technical field of test launch of carrier rockets, and a single test device is used for testing initiating explosive devices and cables on the carrier rocket; the single test equipment comprises a low-voltage high-precision power supply and a wide-voltage high-precision power supply; the wide-voltage high-precision power supply comprises a high-voltage module and a low-voltage module; when a single test device is used for testing the sequential access resistance of the initiating explosive device on the carrier rocket, a low-voltage high-precision power supply is selected; when a single test device is used for testing the on-rocket cable of the carrier rocket and testing conduction of the on-rocket cable of the carrier rocket, a low-voltage module in a wide-voltage high-precision power supply is selected; when insulation of a cable on a carrier rocket is tested, a high-voltage module in a wide-voltage high-precision power supply is selected. According to the invention, a single ground test device can test a time sequence access resistance value of a launch vehicle initiating explosive device and a cable conduction insulation test.

The invention relates to the technical field of initiating explosive device induction, and discloses an initiating explosive device induction system matched with a mixed loading explosive truck, which comprises a visual detection camera, a visual controller and a trip computer which are arranged on the mixed loading explosive truck, the visual detection camera collects initiating explosive device information on the road condition around the mixed loading explosive truck, the visual detection camera transmits collected data to the visual controller through a data transmission protocol defined by the visual controller, the visual controller carries out algorithm processing, and an early warning signal for the initiating explosive device is obtained. The visual controller transmits an early warning signal to the trip computer through the CAN bus, the trip computer processes the early warning signal and instructs the emergency stop system of the mixed loading explosive truck to start the emergency stop function, so that the mixed loading explosive truck stops rapidly, and the mixed loading explosive truck is prevented from rolling the initiating explosive device. The technical problem that the explosive device is rolled by the vehicle due to site limitation, visual angle blind areas, personnel command errors, driver operation errors and the like of the mixed loading explosive vehicle on the blasting operation site is solved.

The invention relates to a low-cost parachute landing recovery system for a microgravity load return capsule, and aims to realize an efficient, reliable and economical recovery scheme through modular design, all modules are connected through standard interfaces, and assembly, maintenance and upgrading are facilitated. The structure module is used for assembling the parachute module and providing necessary shock resistance; the parachute module is used for pneumatic deceleration and attitude stabilization of the system and adopts a multi-stage unfolding structure; and the initiating explosive device module is used for bouncing the brake parachute, releasing the brake parachute and releasing a parachute closing opening. According to the system, the production and maintenance cost is remarkably reduced through modular design, meanwhile, the reliability and adaptability of the system are improved, and the system is suitable for various microgravity load return scenes and has wide market application prospects.

The utility model relates to the technical field of initiating explosive devices, in particular to a medicine strip cutting-off system which comprises a medicine strip cutting-off device, the medicine strip cutting-off device comprises a frame body, a cutter structure, a power piece and a transmission mechanism, and the power piece and the transmission mechanism are both arranged on the frame body. The medicine strip cutting-off process adopting the medicine strip cutting-off system comprises the steps that firstly, the power piece is controlled to work, the upper cutting blade and the lower cutting blade are moved and separated, and a cutting edge is formed between the two cutting edges which are closest to each other; then the medicine strip is conveyed to the shearing knife edge from top to bottom, and the lower end of the medicine strip penetrates through the shearing knife edge and is held by a worker; and finally, the power piece is controlled to work again, the upper cutting blade and the lower cutting blade move to be close to each other, the medicine strip is cut off under the action of the cutting edges of the upper cutting blade and the lower cutting blade, and therefore the cutting work of a section of medicine strip is completed. Compared with the prior art that the medicine strips are cut off manually, the labor intensity is remarkably reduced, the requirement for personnel is lowered, the cutting-off efficiency is improved, and automatic production is facilitated.

An explosive downhole tool includes a housing having an upper housing part on one side of a window section and a lower housing part on an opposite side of the window section. An explosive charge is provided within the housing for at least one of cutting and expanding the wall of the tubular. The outer surface of at least one of the upper and lower housing part is rounded so as to be devoid of corners. The rounded surface eliminates the presence of sharp corners that may catch on restrictions or protrusions in a wellbore so that the downhole tool is more easily conveyable within a wellbore. Another explosive downhole tool includes fins extending from the housing. The fins have a height that decreases in a direction away from the housing. The shape of the fins enables the downhole tool to be more easily conveyable within the wellbore.

The invention relates to the technical field of image recognition, and particularly provides a YOLOv11 blasting site initiating explosive device real-time detection method fused with multi-scale feature enhancement. A multi-scale attention module is introduced into a backbone network, and a cross-level feature aggregation module is used in a neck network, so that the parameter quantity and the calculation quantity are remarkably reduced, and the detection accuracy is improved. The detection precision and the real-time performance are improved, and the identification degree of shielded targets and small targets in a complex environment is enhanced; the lightweight model is suitable for efficient operation on terminal equipment with limited resources, easy to deploy and high in adaptability, the intelligent level of safety monitoring and management can be remarkably improved, safety accidents are effectively prevented and reduced, and the safety of workers is guaranteed.

The header of an EED is redesigned to increase stiction forces to better hold the main charge throughout deflagration. The header includes a main charge holder, integrally formed or as a discrete component, that has internal structure that is press fit to a complementary outer surface of the main charge. The contact area between the internal structure and the main charge being greater than the contact area between a cylinder that circumscribes the internal structure (the uniform cylindrical shape of a typical EED contact area of π*D*L) to increase stiction forces between the main charge holder and the main charge. For a given diameter and length, the inclusion of the internal structure will reduce the mass of the main charge.

The invention relates to the technical field of aerospace, and discloses a low-impact structure of an aerospace point type separation initiating explosive device, which comprises a shell, one end of the shell is in threaded plug-in connection with a connector, a fixed seat is arranged in the shell, two screws are in threaded plug-in connection between the bottom end of the fixed seat and one end of the shell, and the outer wall of the fixed seat is slidably sleeved with a constraint piston. The outer wall of the restraining piston is sleeved with a positioning spring, a bolt is inserted into one end of the fixing base in a sliding mode, an ejection spring is arranged at one end of the fixing base and one end of the bolt, a groove is formed in the outer wall of the bolt, and a plurality of steel balls are connected into the groove in a rolling mode. High-temperature and high-pressure gas generated by the igniter enters the inner cavity and then flows into the constraint piston through the ejection cavity, so that the constraint piston is pushed to move, constraint of the constraint piston on the steel ball is relieved, the steel ball moves outwards in the radial hole, meanwhile, the ejection spring plays a role to push the bolt to be separated, and the bolt is released and unlocked.

A system for delivering and activating a two-part explosive may include an unmanned vehicle and / or an elevated structure, and a two-part explosive device. The device may include a container that is attached to, and releasable from, the unmanned vehicle or elevated structure. The container may contain an unsensitized explosive enclosed in a casing and and a sensitizing agent adjacent to the casing. The device may include an opening mechanism positioned at least partially within the container and adjacent to the casing. The opening mechanism may open the casing and expose the unsensitized explosive to the sensitizing agent, forming the two-part explosive in response to the container being released from the unmanned vehicle or elevated structure. The device may include a detonator inside or attached to the container. The detonator may trigger ignition of the two-part explosive after the unsensitized explosive is exposed to the sensitizing agent.

A ballistically-safe wellbore tool may include an explosive device, an initiator including an initiating charge, and a bias member. A relative configuration of the explosive device and the initiator may be switchable between a first configuration, in which the initiating charge is at a ballistically safe distance from the explosive device, and a second configuration, in which the initiating charge is within a ballistically operable distance from the explosive device. The bias member is configured to bias the explosive device and the initiator to the first configuration.

The invention discloses a controlled environment monitoring system for an initiating explosive device storage space, and relates to the technical field of environment monitoring of the initiating explosive device storage space, the controlled environment monitoring system comprises an equipment main body, an environment monitoring module I, an environment monitoring module II, a display module and a moving module, the environment monitoring module I is arranged at the top of the interior of the equipment main body, and the environment monitoring module II is arranged at the top of the interior of the equipment main body; and one side of the first environment monitoring module is electrically connected with a second environment monitoring module, the display module is embedded in the middle of the front side of the equipment body, and a moving module is installed at the bottom of the equipment body. According to the controlled environment monitoring system for the initiating explosive device storage space, through rotation of a driving wheel and cooperation of a conveying belt, a transmission roller and a built-in shaft can rotate in a follow-up mode, so that a cleaning brush plate connected with the built-in shaft can synchronously rotate when an equipment body moves, a dustproof plate in a first side plate can be conveniently cleaned in a follow-up mode, and the cleaning efficiency is improved. And influence on subsequent environmental data monitoring and heat dissipation of the interior of the equipment main body is avoided.

The invention relates to a driving protection circuit for an initiating explosive device, belongs to the technical field of initiating explosive devices, and solves the problem of insufficient safety of an ignition driving circuit in the prior art. The driving protection circuit comprises a power supply power-on protection circuit, a capacitor charging protection circuit and an ignition control protection circuit; the power supply power-on protection circuit is connected with a power supply and is used for providing power-on protection when the power supply is powered on and providing charging energy for the capacitor charging protection circuit; the capacitor charging protection circuit is used for receiving the charging energy of the power supply power-on protection circuit under the control of the charging control signal and charging an internal energy storage capacitor; and the ignition control protection circuit is used for releasing the energy of the energy storage capacitor under the control of the ignition control signal to ignite the initiating explosive device load. And safe ignition of the initiating explosive device is realized.

Described herein, according to various aspects, are unmanned aerial systems (UAS) that can carry multiple layered modules on a mission. An exemplary UAS may include layered modules that contain functional components such as communication relay modules, armor, batteries, charging modules, propulsion modules, GPS modules, sensor modules, processors, databases, lights, explosive devices, electronic attack devices, payloads, flotation and / or buoyancy control devices, etc. The layered modules can be easily added and / or removed, which allows the UAS to be reconfigured to perform different missions without significantly modifying the structure of the UAS. The layered modules can be deployed at specific locations along a flight path of the UAS to perform location-dependent functionalities (e.g., surveillance of a target region). Multiple layered modules can be coupled to expand upon the payload capacity and the functionality of the UAS. Such an UAS can thus provide a versatile, multifunctional vessel for performing different autonomous missions for military and commercial applications.

A strong electromagnetic protective cover is a cover body with a closed space defined by a specified shell, the specified shell is formed by overlapping at least seven layers of metal materials, and the metal materials sequentially comprise an outer layer of copper, an outer second layer of 1J22, an outer third layer of copper, an outer fourth layer of 1J22, an outer fifth layer of copper, an inner second layer of 1J22 and an inner layer of 1J22 from outside to inside. According to the invention, through computer analogue simulation and sample field actual test, full-frequency-domain protection with the electromagnetic field intensity reaching 6T can be met, and the shielding percentage reaches and exceeds 95%. Reliable theoretical and practical protection is provided for protection of initiating explosive devices and electronic products, and theoretical and practical basis is provided for further deep electromagnetic field protection analysis.

The invention discloses a collision test method and test system for an energy storage element of an electronic detonator, and belongs to the technical field of initiating explosive device test. The method comprises the following steps: blocking an electronic detonator sample with a first rotating speed by adopting a blocking mechanism on a collision test system, so that the electronic detonator sample collides with the blocking mechanism; capturing a voltage curve image at the collision moment T through a voltage curve monitoring and processing unit, and calculating to obtain a first drop amplitude value under the maximum voltage at the collision moment T according to the captured voltage curve image; capturing a voltage curve image from the collision moment T to the first collision duration T + T1 through a voltage curve monitoring processing unit, and calculating to obtain a voltage drop rate from the collision moment T to the first collision duration T + T1 according to the captured voltage curve image; and evaluating the impact resistance of the energy storage element according to the obtained first drop amplitude under the maximum voltage and the voltage drop rate. The collision test method provided by the invention is beneficial to improving the accuracy of a collision test result.

The invention discloses a preparation method of a [Ag2BNOD] n energetic film, the [Ag2BNOD] n energetic film obtained through the preparation method and application of the [Ag2BNOD] n energetic film in an MEMS initiating explosive device, and relates to the technical field of energetic materials.The preparation method of the [Ag2BNOD] n energetic film specifically comprises the following steps that S1, a quartz glass substrate is ultrasonically cleaned with absolute ethyl alcohol, washed with water and air-dried, the quartz glass substrate is put into a sodium hydroxide solution to be soaked, washed with water and air-dried, and the [Ag2BNOD] n energetic film is obtained; soaking the quartz glass substrate in a mixed solution of ethanol, water and triaminopropyltriethoxysilane, washing the quartz glass substrate with water, and curing the quartz glass substrate at 90-110 DEG C for 0.5-2 hours to obtain a quartz glass substrate modified layer; s2, washing the quartz glass substrate modified layer obtained in the S1 with deionized water, soaking the quartz glass substrate modified layer in a silver nitrate solution, taking out the quartz glass substrate modified layer, washing the quartz glass substrate modified layer with deionized water, soaking the quartz glass substrate modified layer in a BNOD aqueous solution, and repeating the steps for 10-30 times to obtain a [Ag2BNOD] n energetic film; the preparation method is very suitable for automation, and the obtained energetic film can improve the energy output characteristic of the MEMS device and improve the ignition capability of the MEMS device.

The invention discloses a damping fluid outflow coefficient rapid testing device capable of simulating driving force of an initiating explosive device. The air cylinder piston can amplify the airflow pressure and transmit the airflow pressure to the donor piston within millisecond, so that the main characteristics of the driving force on the donor piston are basically consistent with those of the driving force of the initiating explosive device, and the effect of simulating the driving force of the initiating explosive device is achieved; the donor piston pushes the damping liquid to pass through the oil passing sheet to simulate the damping effect process, and the change of the length-diameter ratio of the central oil passing hole can be realized by replacing the oil passing sheet, so that the damping effect of the oil passing holes with different length-diameter ratios can be simulated and tested at the initial stage of development; the movement speed of the acceptor piston is consistent with the flow speed of the damping fluid after passing through the oil passing sheet, and the movement speed of the acceptor piston is indirectly obtained based on a photoelectric target signal. Therefore, the outflow coefficients under different temperatures, different damping fluid types, different overflowing hole structure sizes and different driving forces can be obtained, and the damping effect under different working conditions can be rapidly evaluated.

The invention discloses a circulating ventilation and airing system for painting parts, relates to the technical field of ventilation and drying, and ensures continuous production of a production line by utilizing seamless joint of a boxing buffer unit and the painting production line. A large number of painting part turnover boxes are stored through the multi-layer temporary storage roller line, and large-scale airing can be achieved. And a connection unit is designed at an outlet of the three-dimensional warehouse, so that the painted component turnover box automatically completes warehouse-out and pours the painted component into a designated position of the next procedure, and automatic discharging of the painted component and butt joint of rear-end equipment are achieved. And automatic production of airing of the painting component can be realized on a production line with higher and higher automation degree. The system can be in seamless butt joint with a coating production line, automatic conveying, airing and discharging of painted parts are achieved, and the automation level of production is improved. The problem of low airing efficiency under natural wind can be solved, the danger caused by drying and heating in the initiating explosive device industry can be solved, and the situation of large-scale continuous production of painting parts can be achieved.

The invention relates to an underwater platform releasing and cable cutting mechanism which comprises a releasing base, a shell, a push shaft, a releasing hook, an initiating explosive device, a watertight connector and a cable limiting structure. The shell is fixed to underwater equipment through the release base and provided with a closed pneumatic cavity, the push shaft is slidably connected to the pneumatic cavity, and the two ends of the push shaft extend out of the two ends of the shell. One extending end of the push shaft is matched with the release hook so as to limit the underwater platform to the underwater equipment; the other extending end of the push shaft is a cutting knife; the cable limiting structure limits the cable to one end corresponding to the cutting knife, and the position of the cable corresponds to the position of the cutting knife. The initiating explosive device is electrically connected with the underwater equipment through the watertight connector and used for receiving signals of the underwater equipment and releasing high-pressure gas to the pneumatic cavity, the high-pressure gas pushes the push shaft to move towards the cable, the push shaft is made to be disengaged from the release hook to relieve limiting of the underwater platform, and meanwhile the cutting knife moves to cut off the cable. According to the invention, the release of the test platform and the cutting of the cable can be synchronously completed, the full-water-pressure balance is realized, and the adaptability is high.

The invention provides a high-pressure gas membrane rupture pressure measuring device and a measuring method thereof, and belongs to the technical field of pressure measurement. The measuring device comprises a pressure generation system, a gas compression system, a gas injection system, a pressure measuring system and a diaphragm clamping system. The piston divides the cavity into a hydraulic cavity and a gas compression cavity, and the piston is hydraulically driven to compress the pre-filled gas, so that the diaphragm is broken. The pressure measurement system records pressure-time data in real time, and a sliding window average algorithm is adopted to extract a membrane rupture pressure peak value. According to the technical scheme, inert gas is used, initiating explosive devices are not used, membrane rupture energy is only gas expansion, the protection box can absorb fragments, and explosion-proof transformation is not needed in a laboratory. And the smoothed unique membrane rupture pressure value is output through a sliding window averaging algorithm, and manual reading errors are eliminated. According to the technical scheme, the device is compact in structure, safe to operate, rapid in testing and suitable for accurately measuring the diaphragm rupture pressure of the gas gun diaphragm in a conventional laboratory.

The utility model discloses a single foot twist break type transducing element. Including electrode plug, shell, fixed glue, solder and bridge silk. The utility model has designed single foot twist break type initiating explosive device structure in the country first, is a novel structure's transducing element for missile gyro, has higher firing reliability, twist break reliability and security, can be applicable to various gyro ignition, provides new train of thought for gyro design and structure optimization. Product adopts single foot structure electrode plug, double bridge parallel firing design, constitutes firing unit after filling detonating agent, integrates firing and working function, realizes product 700ma firing, 35MPa output pressure bearing, foot line 3.92N the twist break of cm, 59kPa vacuum ignition, damp heat, medium withstand voltage, electromagnetic compatibility, firing reliability 0.999 etc. technical index requirement. The utility model product reliability, security, versatility are high, and environmental adaptability is strong, and the technology reaches the leading level in the country, and the application prospect is wide, and military, economic benefit is remarkable.

The invention discloses an initiating explosive device production line safety risk assessment method based on digital twinning and risk field theory fusion, and the method comprises the steps: building an initiating explosive device production line twinning model based on the field data of an initiating explosive device production line, and importing the model into a digital twinning platform; based on a risk field theory, an initiating explosive device production line safety risk mathematical model is constructed, and safety risk attribute definition is mathematically performed on each part of the initiating explosive device production line twin model through the mathematical model in a digital twin platform. According to the method, the three-dimensional risk field models of the kinetic energy field, the potential energy field and the behavior field are constructed, various risk sources in the initiating explosive device production line are comprehensively described, and compared with a traditional single fault diagnosis method, the multi-dimensional risk modeling method can more comprehensively and accurately reflect potential safety hazards in the production process; meanwhile, risk assessment is more accurate through risk quantification.

Safe addressable firing controls positioned within a reusable housing that only allows voltage and current from the shooting panel to reach the explosive device by addressing the switch to open allowing electricity to pass through it and setting off the chain reaction during detonation, wherein the safe addressable firing controls positioned within a cartridge that creates a safety barrier between the surface equipment and a downhole tool, such as an explosive device.

The explosive injection shaping cutter for the initiating explosive device comprises a cutter mounting body, a plurality of shaping blades are fixedly mounted at the bottom of the cutter mounting body, and asymmetric double-angle blades are arranged on the two sides of each shaping blade. The medicine injection shaping cutter is simple in structure, has the characteristics that the weight of the cutter is suitable for manual operation, safety is guaranteed, the cutter is provided with multiple blades and the asymmetric double-angle blade structure is adopted, the cutter can better adapt to medicine surface appearances under different complex conditions, shaping precision is high, medicine surface slicking work is easily completed, production quality and efficiency are both improved, and the cutter conforms to the lean production principle.

The invention discloses a method and a system for measuring the resistance value of an initiating explosive device of a carrier rocket, and the system for measuring the resistance value of the initiating explosive device of the carrier rocket comprises a central controller, a constant current source detection device, a safety protection device, a measurement control signal output device and a resistance detection result output device. The method has the technical effects of high measurement accuracy and high measurement safety.

The utility model relates to the technical field of army teacher training auxiliary tools, and discloses a weapon launching bidirectional acousto-optic smoke effect simulation device, which comprises a device main body, and a bidirectional initiating explosive device is fixedly connected in the device main body. According to the weapon launching bidirectional acousto-optic smoke effect simulation device, through cooperative arrangement of the device main body, a limiting groove, a reset spring and a fixed suction cup, the device main body is rotationally clamped into a 40mm rocket barrel during training use, and then the reset spring is driven to be compressed; when the device main body is rotated and clamped to a proper position, the fixed sucking disc stops moving and is adsorbed on the inner wall of a 40mm rocket barrel for anti-skid fixation, and when the device main body needs to be separated, the device main body can be pulled out by rotating and loosening the fixed sucking disc, so that the anti-skid adsorption and fixation effects on the weapon launching two-way acousto-optic smoke effect simulation device and the 40mm rocket barrel are achieved; the operation is simple, and the possibility of loosening and falling off is low.

The utility model discloses a circuit substrate structure as well as an electronic detonator control module and an electronic detonator comprising the circuit substrate structure, and belongs to the technical field of initiating explosive devices. The circuit substrate structure comprises a body, the body is of a long-plate-shaped structure, the body is provided with a containing through groove used for containing an energy storage capacitor, the containing through groove extends in the length direction of the body, the body forms a wide-edge bridge on one side of the containing through groove in the width direction, and the body forms a narrow-edge bridge on the other side of the containing through groove in the width direction. The narrow-side bridge is arranged right opposite to the wide-side bridge, the width size of the wide-side bridge is larger than that of the narrow-side bridge, and when the energy storage capacitor is placed in the placing through groove, the energy storage capacitor is located on the inner side of the placing through groove in the horizontal direction; and the narrow-side strength enhancing structure is arranged on the narrow-side bridge and is used for enhancing the strength of the narrow-side bridge. The circuit substrate structure provided by the utility model is beneficial to reducing the size of the protruding body of the energy storage capacitor and improving the reliability and stability of the energy storage capacitor.