7results about How to "High separation reliability" patented technology

The invention discloses a carrier rocket fairing and a design method, and belongs to the field of carrier rocket design, and the carrier rocket fairing comprises a fairing body connected with an effective load adapter; a protruding limiting body is arranged on the outer side wall of the effective load adapter. The bottom of the inner side wall of the fairing body is provided with a groove body surrounding the protruding limiting body. The groove body and the protruding limiting body are matched in an inserted mode. The fairing body comprises at least two cover petals; the adjacent cover petals are fixedly connected through a longitudinal separation unlocking device in the longitudinal direction. Through the design of the protruding limiting body and the groove body, the arrangement of a transverse separation unlocking device is omitted, the manufacturing cost of the fairing is increased, and the separation reliability of the fairing is improved.

This invention belongs to the field of aircraft separation structure design technology, specifically relating to an explosive bolt collection device and its design method suitable for compact axial space. The method includes: Step 1, determining the initial velocity and initial kinetic energy of the explosive bolt remnant; Step 2, selecting buffer structure connecting fasteners based on the initial kinetic energy of the explosive bolt remnant calculated in Step 1; Step 3, designing the collection structure based on the initial kinetic energy of the explosive bolt remnant calculated in Step 1 and the buffer structure connecting fasteners selected in Step 2; Step 4, conducting numerical simulation analysis and ground tests on the bolt collection device designed in Steps 2 and 3 to verify the feasibility of the design method for an explosive bolt collection device suitable for compact axial space. This invention can solve the problems of complex structure, high axial space requirements, and the risk of rebound in explosive bolt collection devices.

A large-diameter tension-compression decoupling fusion type linear separation device is composed of a separation ring, an inner support protective cover, a detonator seat, an energy-gathering cutting cable assembly, a connecting fastener and a detonator, the protective cover is internally provided with the energy-gathering cutting cable, after the detonation energy is transmitted to the main charge of the cutting cable through the transmission assembly of the detonator, the shaped charge is driven by the detonation wave to form a metal jet to cut and separate the separation ring, the high-level load transmitted by the projectile body is tension-compression decoupled through the tolerance control of the separation ring and the inner support protective cover, and a large-diameter tension-compression decoupling fusion type linear separation device is given, which has the advantages of simple structure, reliable separation performance, high bearing capacity, large connection stiffness, light weight, convenient installation and the like.

The utility model relates to the technical field of labeling and coding all-in-one machines, and discloses a labeling and coding all-in-one machine convenient to adjust, which comprises a winding bracket and a transmission belt, the key point is that stable separation of a label layer and a backing paper layer is realized through a cooperative structure of a turning roller and a rough roller; a backing paper layer of a label roll is wound on the turning roller in a U shape, the thick roller is driven by a servo motor, and the outer wall of the thick roller adsorbs the label layer through negative pressure, so that the label layer is separated from the backing paper layer and turns to one side of the transmission belt. Two pressing rollers on the other side of the transmission belt are connected with a double-rod air cylinder through a movable frame, the round bottles can be extruded to the outer wall of a rough roller, and label layers are precisely attached to the peripheries of the round bottles through glue; the label height adjusting platform arranged below the material rolling support comprises a fixing plate, a lifting plate and a rhombic lifting frame, a distance adjusting screw rod is driven by a double-head motor to achieve electric adjustment of the height of the material rolling support, and the label height adjusting platform can be rapidly matched with round bottles of different heights.

The present invention proposes a separation and retraction type compression release device, which can realize separation and retraction while unlocking the unlocking device. It includes: a bracket, an end cover, a support, a bottom plate, a spring A, a spring B, an adapter plate A, an adapter plate B, a screw cap, an anti-drop cap, an unlocker A and an unlocker B; the upper support leg of the bracket passes through the through hole of the support and contacts the support, and the bottom of the support leg of the bracket is connected to the end surface of the bottom plate; one side of the end cover is connected to the adapter plate A, and the other side is connected to the support, and the end cover and the support constitute the main structure; the unlocker A, unlocker B, bracket and spring B are installed inside the main structure; the bottom plate is used to connect the bracket and the adapter plate B; the bottom plate is connected to the four support legs of the bracket; the unlocker A and unlocker B are installed on the inner side of the end cover and the inner side of the bracket respectively, and are used for unlocking and separating the separation and retraction type compression release device.

The invention provides a space propulsion system device based on automatic module separation and a design method thereof. The space propulsion system device is characterized in that one end of a propellant storage and supply module is connected with an orbit control engine module through a first separation interface, and the other end of the propellant storage and supply module is connected with an attitude control engine module through a second separation interface; the storage and supply module is used for providing propellants for the orbit control engine module and the attitude control engine module, the orbit control engine module is used for providing thrust torque required by orbit transfer, and the attitude control engine module is used for providing thrust torque required by attitude control; the first separation interface and the second separation interface provide a module separation function for the storage and supply module, the orbit control engine module and the attitude control engine module. Separation of the propulsion system can be achieved, part of the propulsion system is removed, the total size and mass of extraterrestrial landing aircrafts such as lunar surfaces and Mars are reduced, the operation efficiency of the propulsion system can be improved, and energy consumption can be reduced.