37 results about "Pyrotechnic fastener" patented technology

A sampling basket throwing device of a manned submarine comprises a spherical hinge support provided with a first groove. A spherical head at one end of a connecting pin is jointed with the first groove, the spherical head and the first groove can be disengaged from each other, the other end of the connecting pin is connected with a second groove, the second groove comprises two split-half grooves I formed in a rotational seat and a fixed seat, the rotational seat is hinged to a connecting frame, the rotational seat rotates to enable the two split-half grooves I to be coupled or uncoupled, a first through hole is formed in the fixed seat, a second through hole is formed in the rotational seat, the first through hole communicates with the second through hole axially to form an integral through hole, a pull rod extends into the integral through hole through one end of the integral through hole, the extension end of the pull rod is provided with an internal threaded hole, an explosive bolt extends into the integral through hole through the other end of the integral through hole, the rotational seat and the fixed seat are fixedly connected through the threaded connection of the explosive bolt and the internal threaded hole, the spherical hinge support and the fixed seat are fixedly connected with the connecting frame, a suspension bracket is connected to the middle pin section of the two ends of the connecting pin in a sleeving way, and the suspension bracket is fixedly connected with a sampling basket. According to the invention, the sampling basket is thrown by adopting electric drive, and the operation is reliable.

The invention provides a wrapping tape type unlocking and separation device driven by explosive bolts, belongs to the technical field of aerospace, and solves the technical problems that the assembly precision is difficult to guarantee, the structure size is large and the impact is great in the prior art. The wrapping tape type unlocking and separation device comprises the explosive bolts, an upper bracket, a lower bracket, a left wrapping tape, a right wrapping tape, wrapping tape connecting springs and explosive bolt detached body collecting devices. The left wrapping tape is in fitting contact with the upper bracket and the lower bracket. The right wrapping tape is in fitting contact with the upper bracket and the lower bracket. The contact parts, on each of the left side and the right side, of the left wrapping tape and the right wrapping tape are fastened together by two parallel explosive bolts. The wrapping tape connecting springs are in threaded connection with the left tape and the right tape. Each of two ends of the right tape is fixedly connected with one explosive bolt detached body collecting device which is used for collecting detached bodies of the explosive bolts. The wrapping tape type unlocking and separation device driven by the explosive bolts has greatly improved bearing capacity is and is simple and compact structure.

The invention relates to the technical field of aerospace, in particular to an explosive bolt buffering device which comprises an installation base, a protection shell cover and an axial buffering device. An installation groove for installing an explosive bolt and the axial buffering device is formed in the installation base. A through hole for the explosive bolt to pass through is formed in the installation base. The protection shell cover is fixedly arranged on the installation base and can cover a groove opening of the installation groove, and the protection shell cover and the installationbase form a closed space together. The axial buffering device is arranged in the closed space. The effective buffering effect on instant large-impact loads is achieved, and the impact degree of the explosive bolt on an upper-stage cabin section in the stage separation test using process is remarkably reduced; the explosive bolt buffering device has the advantages of being small in part number, simple in structure, good in machining process, low in cost, convenient to install, compact in structure, light in weight, high in reliability, good in modularization compatibility and suitable for various aircrafts.

The invention provides an aircraft black box recovery method. A black box is mounted and fixed on an aircraft by explosive bolts, an ignition command of the aircraft is used as the starting timing condition, a timer outputs an explosion signal when the preset time is reached to make a tiny explosive device to explode the explosive bolts, the black box is disengaged from the aircraft, at the same time the timer restarts, and after reaching the preset time, airbags open to decelerate. The invention simultaneously provides an aircraft black box recovery device, which comprises a black box protective shell, the main air bag, the small air bag, an air bag box, the explosive bolts, the timer, a control chip, an igniter, nitrogen solid ions, and the like. The mode that the black box is disengagedfrom a mother body by timing explosion of the explosive bolts and lands through the air bags is adopted, and the problems of limited recovery method and poor recovery effect of the black box in the current aircraft development process can be solved.

The invention discloses an automatically expandable autodyne support for the outer space. The automatically expandable autodyne support for the outer space comprises a fixing device, an electromagnetic locking device and an automatic expanding device, wherein the fixing device comprises a fixing seat, a first fixing rod, a second fixing rod and a third fixing rod; the first fixing rod, the secondfixing rod and the third fixing rod are successively perpendicularly arranged on the fixing seat; the automatic expanding device comprises a first joint, a first movable rod, a second joint, a secondmovable rod and a camera mounting seat; and torsional springs are separately arranged in the first joint and the second joint. The automatically expandable autodyne support for the outer space uses principles of electromagnetic locking and torsional spring driving, under the condition that the electromagnetic locking device is energized and unlocked, the autodyne support is automatically expandedunder the driving effect of the torsional spring, the problem that an existing expanding device driven by a motor is high in cost, large in size and poor in reliability is solved, and meanwhile, the technical problems that an existing locking mechanism using initiator explosive bolts for the outer space is high in cost, and the safety and reliability of an aircraft are affected are also solved.

The invention discloses an ammunition-parachute separation rotating device of a parachute used for ammunition. The ammunition-parachute separation rotating device comprises an upper connector connected with ropes of the parachute, a lower connector connected with the ammunition, and an explosive bolt for enabling the upper connector to be connected with the lower connector. A connection shaft is arranged in the upper connector, quick and relative rotation of the upper connector and the connection shaft can be achieved by arranging a first rolling bearing in the upper connector, the upper connector and the lower connector are quickly and accurately separated through the explosive bolt after the ammunition is put in place, and accordingly, the effect that the ammunition is separated from the parachute is achieved. According to the ammunition-parachute separation rotating device, through the arrangement, the defect that the ropes of the parachutes are twisted in the ammunition delivery process can be effectively overcome, and the speed and accuracy of attitude adjusting of the ammunition are improved; and by means of the explosive bolt, on one hand, the upper connector and the lower connector can be firmly connected in the beginning, on the other hand, the ammunition can be rapidly and accurately separated from the parachute after reaching the specified height, and the ammunition delivery accuracy is effectively improved.

An axial loaded explosive bolt that can repeatedly be used for the purpose of remotely or automatically activating a timely separation of adjoining walls separated by a finite distance by the means of either an explosive charge or activation of a pressurized gas line. The fastener includes two bolts with internal bores that are attached by the means of a two-piece encapsulation connected by an inter-connecting clasp. The fastener assembly employs the use of either a combination of a thermal igniter and a pyrotechnic charge or a pressurized gas line attached to a solenoid valve and pressurized gas storage unit to supply a force sufficient to properly separate the said mechanical fastener assembly.

The invention discloses a cargo-parachute separation mechanism after an airdrop device entering water, and solves the problems of slow separation speed and low separation success rate in a prior separation mechanism. A spring (1) is arranged between a piston (13) and a barrel cover (11), a thermal battery start pin sleeve (16) is arranged in a piston barrel (10) below the piston (13), and a compressed compression spring (18) is arranged on the thermal battery start pin (6), a safety pin (2) is fixed on the bottom surface of the piston (13), the thermal battery (3) is arranged in the piston barrel body (10) below the thermal battery start pin sleeve, and an explosive bolt control circuit board (7) is connected with an adiabatic pad (4), an explosion bolt (9) is fixed on the bottom plate ofthe piston barrel body (10), and the explosion bolt is electrically connected with the explosion bolt control circuit board, and an airdrop device connection seat (5) is fixed on the lower end of theexplosion bolt. The device can be put in place quickly after entering water, and the cargo and the parachute can be separated quickly.

The invention relates to the technical field of aerospace equipment, in particular to a non-pyrotechnic separation device based on an explosive bolt. The non-pyrotechnic separation device comprises atleast one explosive bolt and at least one high-pressure gas cylinder, wherein a gas chamber for accommodating a high-pressure gas is arranged in the explosive bolt; and the high-pressure gas cylinderis communicated with the gas chamber of the explosive bolt through at least one pipeline, is used for conveying the high-pressure gas stored in the high-pressure gas cylinder to the gas chamber of the explosive bolt through the pipeline, and applies an acting force to the explosive bolt to divide the explosive bolt. The non-pyrotechnic separation device based on the explosive bolt, provided by the invention, is reusable and low in cost and does not generate harmful gases.

The invention belongs to an aircraft drag parachute system, and particularly discloses a drag parachute throwing-releasing mechanism with an automatic parachute throwing function after failure. The drag parachute throwing-releasing mechanism is composed of explosive bolts, electric exploders, a pin pushing machine, a non-electric-detonation assembly and a false lock device. The explosive bolts areconnected with an airframe mechanism and a drag parachute cabin rear cover, the false lock device is connected with an airframe support and a drag parachute hanging ring, and the pin pushing end of the pin pushing machine is connected with the false lock device through a thread. The output end of the non-electric-detonation assembly is connected with the explosive bolts and the other end of the pin pushing machine, and the input end of the non-electric-detonation assembly is connected with the electric exploders. One parallel ignition circuit is only needed to add in a traditional non-electric-detonation system, and the ''failure-safety'' function can be realized; and a drag parachute cabin sensor and a related logic judgment system are not needed to be added, the system logic is simple,all functions can be realized only by an initiating explosive device system, and the structure space and weight of the sensor and cable installation thereof are saved.

The invention discloses a large scale solid engine drop test release device which can be applied to large scale engine drop tests. The large scale solid engine drop test release device is strong in transient response capability and good in movement synchronicity. The device comprises a test rack and a release mechanism, wherein the test rack is used for supporting the release mechanism, an engine being tested can be arranged at a specified height on the release mechanism, the release mechanism supports the engine being tested via a baffle plate in a lifting manner, the baffle plate is fixed with a binding tie, and one of the binding tie is connected via an explosive screw bolt assembly. When a downward explosion screw bolt sends an initiation signal, the explosion screw bolt is broken, the binding tie is loosened, the baffle plate is untied without constraint, and the engine being tested falls freely. The engine being tested is supported in a lifted manner, a phenomenon that the engine is damaged due to clamping force of a clamping tool or calipers can be prevented, and the structure of the device is simpler and smaller than the structure of the clamping tool or the calipers; compared with a conventional clamping force unloading mode, the device which employs the explosion screw bolt is strong in transient response capability and good in movement synchronicity, and testing precision control can be improved.

The invention provides a buffer structure, a buffer energy-absorbing recovery device and an aircraft. The buffer structure comprises: a honeycomb core having a plurality of accommodating holes for accommodating residual parts of explosion bolts during the stage separation process of the aircraft, a first panel and a second panel, wherein the honeycomb core is arranged between the first panel and the second panel; cross-sections of the first panel and the second panel and the honeycomb core are designed in shape; and during the stage separation stage of the aircraft, the buffer structure can absorb the energy of the residual parts of the explosion bolts through self moulding and deformation. The technical solution of the buffer structure is applied to solve the technical problem that the prior art cannot safely and reliably recover the separated parts with high hazardness of the explosion bolts.

The invention relates to a pre-splitting warhead comprising a plurality of reduced projectile body sections, wherein each projectile body section is formed by a plurality of shells in an enclosing way; a delay fuse is arranged in a projectile body; the projectile body sections are connected through connectors; a hoop is arranged at the periphery of each projectile body section; the hoops tightly hoop the projectile body; and explosive bolts are mounted on the hoops. Before the warhead gets close to a target, the warhead is detonated through the explosive bolts and the delay fuse, the projectile body is decomposed into a plurality of shells or special-shape projectiles and the target can be attacked on a large scale; and since the quantity of the shells is large, a defense system cannot resist the attack and precise attacks to large warships, airplanes or guided missiles can be realized.

The invention relates to a combined separation parachute opening mechanism, and belongs to the field of civil rocket dispenser bombs. In the separation parachute opening mechanism, the inner wall of an annular connecting table at the middle part of an inner cavity of a separation cylinder is in threaded connection with a stop ring; a separation push plate and a separation bullet are charged on thefront side, where the stop ring is fixed, of the separation cylinder; a stable parachute at the back end of the separation bullet is fixed with a front side plate surface of the separation push platethrough a shearing rope; the separation push plate and the stop ring are synchronously fixed through an explosion bolt and a rupture bolt; the front end of a limiting bolt penetrates through a limiting bolt passing hole in a ring surface of the stop ring, and is in threaded fixation with the separation push plate; the limiting bolt is positioned on the back side of the plate surface of the separation push plate with a mobile margin; a separation explosive box is fixed on the back side plate surface of the separation push plate; the back end of the separation cylinder is in threaded butt jointwith a back end projectile body; and the explosion bolt and a detonation circuit of the separation explosive box are connected with a delay fuse mounted on the back end projectile body through leads.The separation mechanism effectively guarantees the connecting strength in the rocket projectile flight process, and is high in separation reliability and controllable in parachute opening time.