30results about How to "High separation reliability" patented technology

The invention discloses a method for separating a satellite and rocket separation electric connector by redundancy backup, which realizes the reliable separation of the separation electric connector from a satellite in a redundancy backup mode and uses an electric separation command as a main separation mode and aramid rope forced separation as a backup separation mode. After the launching of a carrier rocket, the separation electric connector separates from a micro satellite according to an electric signal when receiving an electric connector separation command from the ground; 1.2 seconds later, a carried blasting bolt is unlocked, a separation spring of a connecting bracket base ejects the micro satellite out of the carrier rocket and the connecting bracket stays on the carrier rocket;and if the separation electric connector does not separate successfully, the separation spring of the connecting bracket base ejects the micro satellite out in the flight direction and, at the same time, the loose aramid rope is tightened to pull the separation electric connector out in a direction opposite to the flight direction to separate the separation electric connector. The method of the invention has the characteristics of high reliability, short action time and simplicity and convenience for operation.

The invention relates to a turnover satellite borne antenna locking releasing device which consists of a switchover piece, a rotor shaft, a torsional spring, a pressure plate, a locking lever, a limitcover, a spring cover, a spring, a locknut, a ball pad, a support and a cutter. The invention effectively transforms the impact force applied to the locking lever in cutting to the release power through the limit cover on the pressure plate, and the release power and the torsional force of the torsional spring act together, thereby increasing the separating speed between the pressure plate and the support and increasing the separating reliability. The exposed part of the locking lever under the pressure plate is shorter after the locking lever is cut, the turnover angle of the pressure plateis big, and the pressure plate is kept to be fixed after being in place under the moment action of the torsional spring so as to enable the pressure plate to keep a longer distance from the support, thereby ensuring the rotation reliability of the antenna; meanwhile, the invention has simple structure, therefore facilitating production and manufacture.

The invention discloses a low-impact large-bearing-capacity stack type multi-satellite locking and releasing device and a working method thereof, and particularly relates to the technical field of spacecraft structures. Comprising a satellite bottom plate, a locking and releasing device, a pressing rod, a pre-tightening force mechanism, a pressing rod push rod mechanism and a stackable satellite structure. The satellite bottom plate provides a fixed platform; the locking and releasing device is used for locking the stackable satellites and releasing the pressing rod; the pressing rod is connected with the locking and releasing device, so that the stackable satellites can be tensioned; the pre-tightening force mechanism can provide enough pre-tightening force for pressing and stacking satellites; the pressing rod push rod mechanism pushes the pressing rod to be separated away after the pressing rod is unlocked and released, and the separation safety of the stackable satellites is guaranteed. The non-pyrotechnic locking and releasing device is reasonable in structure and reliable in performance, has the characteristics of small unlocking impact, no pollution, large bearing capacity, safety, reliability and good separation synchronism, is suitable for locking and releasing stacked satellites, and ensures the stability of the stacked satellites in a rocket launching stage.

The invention discloses a plate and diaphragm gripping device and the method thereof, the plate and diaphragm gripping device comprises at least two gripping units, at least one pressing device positioned between the two gripping units, and a driving unit for driving the gripping units and pressing unit; when a plate and a diaphragm are gripped, the driving unit drives the pressing unit to press the inner sides of the plate and the diaphragm, drives the gripping units to grip the circumferences of the plate and the diaphragm and lift the circumferences of the plate and the diaphragm before the pressing unit acts, and then drives the pressing unit to release the plate and the diaphragm. The invention can avoid that a plurality of plates and diaphragms are lifted together, and ensure that users can grip desired plates and diaphragms and solve the problem of position deviation of adjacent plates and diaphragms.

The invention provides a satellite-rocket point type connection and separation module and device. The satellite-rocket point type connection and separation module comprises an upper through connection barrel, a lower through connection barrel, an explosive bolt, a separation spring and a loading nut. The upper through connection barrel and the lower through connection barrel are connected together through the explosive bolt. The free end of the upper through connection barrel is used for being connected with a satellite bottom plate. The portion, connected with the explosive bolt, of the upper through connection barrel is provided with the loading nut. The separation spring is arranged outside the upper through connection barrel and the lower through connection barrel in a sleeving mode and pre-tightened under the effect of the upper through connection barrel and the lower through connection barrel. The satellite-rocket point type connection and separation module and device are good in connection rigidity, low in impact force, high in adaptability, short in research period and low in cost.

The invention relates to a clamping block type stage separation structure of an aircraft, and belongs to the technical field of aircraft separation. The stage separation structure comprises an upper casing, a lower casing, clamping blocks and separation bolts; the upper casing comprises an upper boss located on the outer wall of the upper casing; the top surface of the upper boss is an inclined surface which is inclined downwards; the lower casing comprises a lower boss located on the outer wall of the lower casing; the bottom surface of the lower boss is an inclined surface which is inclinedupwards; grooves fitting the top surface of the upper boss and the bottom surface of the lower boss are formed in the inner sides of the clamping blocks; and the separation bolts sequentially penetrate through the upper casing and the lower casing to be in threaded connection with the clamping blocks. The grooves fitting the top surface of the upper boss and the bottom surface of the lower boss are formed in the inner sides of the clamping blocks of the stage separation structure, the radial force of the separation bolts can be converted into the axial force for connecting the lower casing andthe upper casing through adjustment of the matching angles of the grooves and the top surface of the upper boss and the matching angles of the grooves and the bottom surface of the lower boss, and the radial force can be converted into multiple times of the axial force, so that the bearing capacity of every single separation bolt is improved, the number of the separation bolts can be reduced, theseparation impact can be reduced, and the separation reliability can be improved.

A recording sheet / ink sheet integral type cartridge, includes a recording sheet containing portion that contains recording sheets by stacking the sheets; and an ink sheet containing portion that contains ink sheets, the recording sheet containing portion including two separating pawls disposed to catch corners of a leading edge of the recording sheet in a feeding direction and separating the recording sheet and a first aperture portion formed in one of two side surfaces of said recording sheet containing portion in a direction orthogonal to the recording sheet feeding direction, and urging the recording sheet, wherein one of the two separating pawls, which is closer to the first aperture portion, is larger than the other.

The invention discloses a universal type unmanned aerial vehicle emitting device transfer beam. The universal type unmanned aerial vehicle emitting device transfer beam comprises a transfer beam casing, a guide rail, two wing hangers and two emitting device hangers. The guide rail is a long plate-shaped component and is fixed on the lower side of the transfer beam casing through screws; two parallel sliding grooves are formed in the guide rail in the heading direction; the two emitting device hangers are arranged on the guide rail through two bolts; and the bolts can slide in the guide rail sliding grooves and can be fixed by tightening nuts. The two wing hangers are used for mounting the universal type transfer beam below the wing. Long through grooves are formed in the planes of the lower ends of the emitting device hangers. After the emitting device hangers are arranged on the guide rail, the emitting device hangers are positioned below the guide rail, the center axis of the long through groove and the center axis of the guide rail are vertical to each other, two explosive bolts for hanging the emitting device are placed in the long through grooves, and the two explosive bolts can slide in the long through grooves and can be fixed by tightening the nuts. The universality of transfer beam mounting is realized by a simple and reliable mode.

The method comprises the following steps: preparing a sheet having thickness of 5 mum to a few tens of micrometers, suitable for being etched by a lithographic operation; making a mask on a face of the sheet, the mask presenting etching selectivity S of at least 5; depositing a layer of photosensitive resin on the mask; making through holes in the layer of resin by photolithography; etching through the mask via the pores in the layer of resin; and anisotropically etching through the sheet from the pores in the mask in order to make pores in the sheet having an aspect ratio greater than 5. The invention is applicable to fabricating micron and sub-micron filters.

The invention discloses a universal type unmanned aerial vehicle emitting device transfer beam. The universal type unmanned aerial vehicle emitting device transfer beam comprises a transfer beam casing, a guide rail, two wing hangers and two emitting device hangers. The guide rail is a long plate-shaped component and is fixed on the lower side of the transfer beam casing through screws; two parallel sliding grooves are formed in the guide rail in the heading direction; the two emitting device hangers are arranged on the guide rail through two bolts; and the bolts can slide in the guide rail sliding grooves and can be fixed by tightening nuts. The two wing hangers are used for mounting the universal type transfer beam below the wing. Long through grooves are formed in the planes of the lower ends of the emitting device hangers. After the emitting device hangers are arranged on the guide rail, the emitting device hangers are positioned below the guide rail, the center axis of the long through groove and the center axis of the guide rail are vertical to each other, two explosive bolts for hanging the emitting device are placed in the long through grooves, and the two explosive bolts can slide in the long through grooves and can be fixed by tightening the nuts. The universality of transfer beam mounting is realized by a simple and reliable mode.

The invention relates to a turnover satellite borne antenna locking releasing device which consists of a switchover piece, a rotor shaft, a torsional spring, a pressure plate, a locking lever, a limit cover, a spring cover, a spring, a locknut, a ball pad, a support and a cutter. The invention effectively transforms the impact force applied to the locking lever in cutting to the release power through the limit cover on the pressure plate, and the release power and the torsional force of the torsional spring act together, thereby increasing the separating speed between the pressure plate and the support and increasing the separating reliability. The exposed part of the locking lever under the pressure plate is shorter after the locking lever is cut, the turnover angle of the pressure plateis big, and the pressure plate is kept to be fixed after being in place under the moment action of the torsional spring so as to enable the pressure plate to keep a longer distance from the support, thereby ensuring the rotation reliability of the antenna; meanwhile, the invention has simple structure, therefore facilitating production and manufacture.

A hook type connecting and unlocking device comprises an upper end frame (1), a rotating block (2), a rolling shaft (3), a base (4), an internal supporting ring (5), a lower end frame (6), a motor assembly (7), connecting rods (8) and a roller (9), wherein the upper end frame (1) and the lower end frame (6) are separately fixedly connected to two structures (10 and 11) to be connected and unlocked; a groove is formed in the upper end frame (1); the lower end frame (6) is fixedly connected with the base (4); one end of the rotating block (2) is connected to the base (4) through the rolling shaft (3); a projection is arranged on one side of the other end of the rotating block (2); the shape of the projection is matched with that of the groove; a slot is formed in the other side of the otherend of the rotating block (2); the internal supporting ring (5) is placed in the slot and is connected with the motor assembly (7) through the connecting rods (8); and under the driving effect of themotor assembly (7), the projection on the rotating block (2) rotates around the rolling shaft (3) to enter the groove of the upper end frame (1) or leave away from the groove of the upper end frame (1) through expansion and shrinkage of the internal supporting ring (5), and thus, locking and releasing of the two structures (10 and 11) are realized.

A retaining force on a sewing thread (F) stretching into a suction tube (20) is increased for the duration of a cutting process being undertaken by gripping the thread in the suction tube. Pressure applied to the thread held back by gripping can be increased against a thread cutter (6) through additional movement of the suction tube. An independent claim is also included for a device for servicing an operating point on a textile machine.

The invention discloses a low separation load joint with flexible self-compensation, and relates to a joint of an air supply connector and a liquid supply connector in a carrier rocket (a guided missile) which is more sensitive in rocket-ground separation load requirement, and high in falling separation reliability requirement. The provided joint aims to reduce separation load, has a butting automatic guide positioning function and an automatic flexible compensation function, and is capable of realizing separation without clamping stagnation, and improving butting and separation reliability. The joint comprises cooperatively installed socket and plug. The plug comprises a plug body, a fixing base, a guiding base and a spring. The socket comprises a sealing base and an outer sleeve. The plug body is provided with a hollow cavity structure. The front part of the plug body is a conical surface. The fixing base can be screwed in the plug body and cooperatively installed with the plug body.The guiding base is sheathed at the outer side of the fixing base. The spring is pre-compressed and installed between the plug body and the guiding base. The rear part of the sealing base is providedwith a conical surface structure which has the same inclination angle of the conical surface as the plug body. The rear part of the outer sleeve is sheathed at the outer side of the sealing base.

The invention discloses a penetrator for detecting extraterrestrial celestial bodies with an atmosphere and a solid surface, belonging to the field of terrestrial planet detection. The penetrator comprises a penetrator core mechanism, a protective cover, and a protective cover connection and separation mechanism and the center of mass adjustment mechanism; the penetrator core mechanism includes a penetration structure and a buffer energy-absorbing structure; the shield includes upper and lower shells and front and rear pneumatic rudder surfaces; the shield connection and separation mechanism is driven by a motor to rotate a gear, and the gear The locking rod on the upper part slides in the sliding rail on the active lock piece, so as to realize the connection and separation of the mechanism; the center of mass adjustment mechanism is composed of eight ball-screw electric telescopic rods, and the different telescopic combinations of the rods are used to realize the adjustment. The position of the core of the penetrator is adjusted, so as to realize the transformation of the center of mass of the penetrator as a whole, and create a good initial penetration condition for the penetrator. The invention can realize the integrated detection of entry, deceleration and penetration of Ganymede / Triton and other terrestrial planets.

A connector and a cryogenic rocket system provided by the present invention include: a first connection structure, including a first panel, and a first liquid channel and a plurality of first gas channel channels arranged on the first panel; a second connection structure , including a second panel, the second panel is in contact with the first panel, the second panel is provided with a second liquid channel and a number of second gas channels, the second liquid channel is connected with the first liquid channel, the second The air passage is communicated with the first air passage; the locking piece, passing through the first panel and the second panel, has a locking state for fixing the first panel and the second panel and a separation state for unlocking the first panel and the second panel . This arrangement realizes the effective communication and integration of multiple air passages and liquid passages on a single connector, reduces the number of connectors, realizes the simultaneous communication or isolation of air passages and liquid passages, and improves the performance of the connector. The separation reliability of the system or device is simple in structure and easy to realize.

The invention discloses an automatic control system and method for a cyclone separator. The automatic control system includes a cyclone separator, a motor, a frequency converter, a dust concentration particle size sensor, a controller, an A / D conversion module, a programming device, a display and the like. The input end of the controller is connected with the dust concentration and particle size detection circuit, the output end of the controller is connected with the frequency converter, the motor is connected with the frequency converter, the programming device and the display are connected with the communication interface of PLC, the beneficial effect is high reliability and saving Energy, low maintenance cost, simple wiring, solves the problems of high power consumption and low efficiency of the traditional separator dust removal system, and has a good industrial application prospect.

The invention discloses a plate and diaphragm gripping device and the method thereof, the plate and diaphragm gripping device comprises at least two gripping units, at least one pressing device positioned between the two gripping units, and a driving unit for driving the gripping units and pressing unit; when a plate and a diaphragm are gripped, the driving unit drives the pressing unit to press the inner sides of the plate and the diaphragm, drives the gripping units to grip the circumferences of the plate and the diaphragm and lift the circumferences of the plate and the diaphragm before the pressing unit acts, and then drives the pressing unit to release the plate and the diaphragm. The invention can avoid that a plurality of plates and diaphragms are lifted together, and ensure that users can grip desired plates and diaphragms and solve the problem of position deviation of adjacent plates and diaphragms.