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

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.

A recording sheet / ink sheet integral type cartridge, comprises 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 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 fairing inclined pushing axial separation device which comprises a spring separation mechanism, a flat ball socket base and a hinge base. The separation spring is in a compressed state, and an included angle exists between the spring separation mechanism and the axis of the fairing. According to the fairing separating device, enough enveloping space can be provided for effective loads, the safety distance between the fairing and the effective loads in the separating process is guaranteed, and the problems that the internal space of the fairing is limited, and a springseparating mechanism cannot be installed sufficiently are solved; in the fairing separation process, the flat ball head rotates in the direction away from the effective load in the middle plane of the flat ball socket, and the sleeve rotates around the hinge base in the direction close to the effective load. The hinge seat, the flat ball head and the flat ball socket are matched to work, so thatthe problem of clamping stagnation in the separation process due to an included angle between the spring separation mechanism and the axis of the fairing is solved, and the device is reliable in work.

The invention relates to a three-dimensional positioning system and a method based on manipulator single-camera multi-view vision, and the system is characterized in that an image collection device inthe system consists of a manipulator and an industrial camera installed on a flange plate at the front end of the manipulator, and is used for controlling the posture of the industrial camera and collecting the image of a measured object; an industrial control computer in the system is used for controlling a manipulator to move and receiving images collected by an industrial camera, synthesizingmulti-angle two-dimensional measured images into a three-dimensional point cloud image, and carrying out three-dimensional positioning on a measured object through a deep learning algorithm. Accordingto the system, a single industrial camera is adopted to form a multi-view hardware system, and the hardware system is simple; the multi-view imaging source is a camera, the internal parameters of thecamera are consistent, and the calibration problem caused by different internal parameters of multiple cameras is avoided; multi-angle shooting is completed by the manipulator, the flexibility is good, and the repeated precision is high.

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 provides a connector and a low-temperature rocket system, and the connector comprises a first connection structure which comprises a first panel, a first liquid path channel and a plurality of first gas path channels arranged on the first panel, a second connecting structure, a locking piece; the second connecting structure comprises a second panel, the second panel abuts against the first panel, the second panel is provided with a second liquid path channel and a plurality of second gas path channels, the second liquid path channel is communicated with the first liquid path channel, and the second gas path channels are communicated with the first gas path channels; and the locking piece penetrates through the first panel and the second panel and has a locking state for fixing the first panel and the second panel and a separating state for unlocking the first panel and the second panel. By means of the arrangement, effective communication and integrated arrangement of the multiple gas path channels and the multiple liquid path channels on the single connector are achieved, the number of the connectors is reduced, simultaneous communication or separation of the gas path channels and the liquid path channels is achieved, the separation reliability of a system or device where the connectors are located is improved, the structure is simple, and implementation is easy.

The invention discloses an eccentric shearing type low-impact expansion pipe double-groove-plate separation device which comprises an explosive cable, filler, a flat pipe, an H-shaped separation plate, an upper end frame, a lower end frame, an upper fastening bolt and a lower fastening bolt. The H-shaped separation plate comprises an upper U-shaped groove, a lower U-shaped groove and a connectingarea; the upper U-shaped groove and the lower U-shaped groove are located in the upper side and the lower side of the connecting area respectively. The upper end frame and the upper U-shaped groove are installed in a butt joint mode and fastened through an upper fastening bolt. The lower end frame and the lower U-shaped groove are installed in a butt joint mode and fastened through a lower fastening bolt. The flat pipe is arranged between the lower end frame and the lower U-shaped groove; the flat pipe is hollow, and the explosive cable is arranged in a hollow cavity of the flat pipe; and thefiller is filled in a cavity between the flat tube and the explosive cable. Impact generated in the action process can be reduced while it is guaranteed that the structure has high separation reliability.

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.

The invention relates to the technical field of blueberry fruit wine production, in particular to a pulping device based on blueberry fruit wine production, which comprises a case, a treatment mechanism for preparing blueberry juice is arranged in the case, a puncture assembly matched with the treatment mechanism to crush blueberries for use is mounted on the case, and a recovery mechanism for recovering fruit residues is arranged on the case; the processing mechanism comprises a processing box arranged in the machine box, a plurality of filtering holes distributed at equal intervals are formed in the bottom wall of the processing box, and the two sides of the processing box are movably installed on the inner wall of the machine box through rotary bases. According to the invention, the purpose of synchronously performing residue and juice separation in the pulping process is achieved, the tedious way of obtaining blueberry juice by mashing and compounding in the past can be replaced, the pulping and liquid extraction process is simplified, the efficiency is remarkably improved, the production cost is greatly reduced, the subsequent filtering and residue removal process is omitted, and the production efficiency is improved. Therefore, the production requirements of the blueberry fruit wine are met.

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.

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 penetrator for detecting an extraterrestrial celestial body with an atmospheric layer and a solid surface, and belongs to the field of terrestrial planet detection. The penetrator comprises a penetrator inner core mechanism, a protective cover, a protective cover connecting and separating mechanism and a centroid adjusting mechanism; the penetrator inner core mechanism comprises a penetrating structure and a buffer energy absorption structure; the protective cover comprises an upper shell, a lower shell, a front pneumatic control surface and a rear pneumatic control surface. According to the protective cover connecting and separating mechanism, a motor drives the gear to rotate, the locking rod on the gear slides in the sliding rail on the driving locking piece, and therefore connection and separation of the mechanism are achieved. The centroid adjusting mechanism is composed of eight ball screw electric telescopic rods, and the position of the inner core of the penetrator is adjusted through different telescopic combinations of the rods, so that centroid transformation of the whole penetrator is achieved, and good initial penetration conditions are created for the penetrator. According to the invention, integrated detection of entry, deceleration and penetration of terrestrial planets such as Ganymede / Triton and the like can be realized.

The embodiment of the invention provides a supporting structure assembly, a transmission and a vehicle, and the supporting structure assembly comprises a first shell provided with a through hole; the first sealing ring is arranged at one end of the through hole; the second sealing ring is arranged at the other end of the through hole; the separation operating shaft penetrates through the first sealing ring, the through hole and the second sealing ring and is provided with an oil duct, the oil duct is provided with at least one first opening and at least one second opening, the second opening is formed in the circumferential side wall of the separation operating shaft, and the second opening is formed between the first sealing ring and the second sealing ring. According to the technical scheme, the two sealing rings are additionally arranged, so that dust and other impurities can be effectively prevented from entering the through hole, and the possibility of grease pollution is reduced. In addition, due to the arrangement of the oil duct, a worker can conveniently carry out later grease adding maintenance on the supporting structure assembly, grease can enter the space between the circumferential side wall of the separation control shaft and the inner wall of the through hole to lubricate the separation control shaft and the through hole, and the separation reliability can be improved.

The invention relates to the field of unmanned helicopter power supply, in particular to a power supply separation plug-off protection device and an unmanned helicopter power supply separation plug-off. The device comprises a protective sleeve, a springback connecting structure, a protective cover and a compensation structure. The opening angle of the springback connecting structure is larger than or equal to 170 degrees, the compensation structure can be pressed tightly, and the protective cover and the protective sleeve can be attached to each other. Through the elastic force of the springback connecting structure and the elastic force of the compensation structure, the unplugging separating force can be enhanced, and the elastic force of the compensation structure is adjusted to be consistent with the opening elastic force of the springback connecting structure. The invention has the following beneficial effects: by adopting the structure of the invention, the separation reliability of unplugging and plugging can be further improved; after the plug-off falling end is separated from the machine body, the covering cap can be tightly covered through the springback of the springback connecting structure, and the plug-off pin is effectively protected; through the flexible protection of the protection sleeve and the protection cover, buffering can be carried out after the plug-out connector falls to the ground, and the plug-out connector is protected from being damaged when falling off.