31results about How to "Short power path" patented technology

The invention provides a hollow high-bearing high-maneuverability spacecraft configuration. The hollow high-bearing high-maneuverability spacecraft configuration includes a payload cabin, a propulsioncabin and an instrument cabin. The payload cabin is located at the central axis of a spacecraft. The payload cabin passes through the central axes of the propulsion cabin and the instrument cabin. The interior of the payload cabin is a cylindrical space which is open at the front and back, and the payload cabin runs through the whole of the spacecraft, and is used for carrying a large space loadwhich needs to be arranged in the middle of the spacecraft. The propulsion cabin is located at the exterior of the payload cabin. The instrument cabin is positioned above the propulsion cabin. According to the hollow high-bearing high-maneuverability spacecraft configuration, the large space is reserved in the central axis of the spacecraft and used for installing a large-size and high-mass load system with a slender shape, the overall height and centroid height of the spacecraft can be effectively reduced, centroid lateral deviation of the spacecraft is reduced, and a better mechanical environment is provided for both the load and the spacecraft.

The invention relates to a geostationary orbit satellite with a thermal deformation isolation function of a load and platform. The geostationary orbit satellite comprises a satellite platform, a loadcabin and the load, the load cabin is composed of three side plates and an antenna main reflecting surface support truss, the antenna main reflecting surface support truss is arranged on a top plate of the satellite platform, the load comprises an antenna main reflecting surface, an antenna main reflecting surface back frame, antenna secondary and main reflecting surface expansion arms, an antennalarge secondary and main reflecting surface, an antenna small secondary and main reflecting surface and a quasi-optics system, the antenna large secondary and main reflecting surface and the antennasmall secondary and main reflecting surface are arranged on the antenna secondary and main reflecting surface expansion arms, the antenna main reflecting surface is arranged on the top plate of the satellite platform through an unlocking separation device on the antenna main reflecting surface support truss, and the quasi-optics system is connected with the antenna main reflecting surface back frame by adopting a titanium alloy lug piece. The geostationary orbit satellite solves the technical problems that an existing satellite cannot meet the high resolution requirement of load detection, andthe thermal deformation between the in-orbit satellite platform and the load is intercoupled.

The invention discloses a microsatellite structure suitable for an optical load. The structure comprises a bottom board, an intermediate board, a top board, side boards, supports, separation frames, abottom board reinforcing embedded part, a docking ring and the load. The bottom board, the intermediate board, the top board and the side boards are each of a rectangular board structure. The bottomboard reinforcing embedded part used for reinforcing the structure is pre-buried in the bottom board. The supports used for supporting the load are installed on the upper surface of the bottom board.The docking ring is installed on the lower surface of the bottom board. Through holes allowing the load to penetrate through are formed in the intermediate board and the top board. The bottom board, the intermediate board and the top board are parallel, and the edges of the bottom board, the intermediate board and the top board are perpendicularly and fixedly connected with the four side boards toform a box-type structure. The multiple separation frames used for reinforcing the rigidity are installed between the bottom board and the intermediate board. Through cooperation of the bottom board,the intermediate board, the top board, the side boards, the supports, the separation frames, the bottom board reinforcing embedded part, the docking ring and the load, the force transferring path ofthe optical load is shortened, the structural layout of a whole microsatellite is optimized, and the defects that parts of a traditional microsatellite truss structure are concentrated, and the mass is large are overcome.

The invention discloses a shear wall mold board external corner counter-pulling device which comprises a horizontal back strip and a counter-pulling screw device. The L-shaped horizontal back strip includes two strip bodies vertical to each other. The two strip bodies are fixed on the mold boards on two sides of an external angle. A steel plate seat is fixed at one end, close to the external angle, of each of the two strip body. The counter-pulling screw device comprises a screw and circular gasket type hexagonal nuts. The screw sequentially penetrates the two steep plate seats to connect the same. The circular gasket type hexagonal nuts for locking the mold boards on two sides of the external angle are disposed at two ends of the screw. By the shear wall mold board external corner counter-pulling device, mold expansion and mud leakage can be avoided, the shear wall concrete external corner is enabled to be angular, smooth and free of mold expansion, and concrete waste during construction is reduced greatly.

The invention relates to an oilfield skid block hoisting structure comprising a skid block and having the innovative characteristics as follows: a plurality of lifting eyes are formed on two edges of the skid block symmetrically; a hoisting system connected with the lifting eyes is arranged above the skid block; the hoisting system at least comprises a lifting beam and a plurality of branch slings; the lifting beam is arranged right above the skid block horizontally; the axes of the lifting beam is perpendicular to the two edges of the skid block, on which the lifting eyes are formed; the number of the branch slings corresponds to the number of the lifting eyes; and the lifting eyes on the same edge of the skid block are respectively connected with one end of the lifting beam close to the same edge through the branch slings. When the oilfield skid block hoisting structure is used, the lifting beam of the hoisting system is connected with a lifting hook of a loop wheel machine directly or indirectly, and the branch slings of the hoisting system are connected with the lifting eyes of the skid block so as to achieve hoisting. When the branch slings are connected with the lifting eyes, the lifting eyes on the same edge of the skid block are respectively connected with one end of the lifting beam close to the same edge through the branch slings, so that the branch slings are far away from a mounting plane of the skid block, the occupation of useful installation space on the upper end surface of the skid block can be reduced, and application range of the oilfield skid block hoisting structure can be widened.

Disclosed is a beam end controllable energy dissipation plastic hinge. The beam end controllable energy dissipation plastic hinge comprises a mechanical hinge; disc spring self-resetting devices are arranged on the inner sides of the upper end and the lower end of the mechanical hinge; and friction energy dissipation devices are arranged on the front end face and the rear end face of the mechanical hinge. The structure can be induced to form a reasonable damage mechanism under the earthquake action, the anti-seismic performance of a fabricated concrete frame structure is improved, passive control over the structure under the earthquake action is achieved, the purpose that the structure function can be recovered is achieved, and rapid development of the fabricated concrete frame structure is promoted.

A shed forming device (1) for a power loom has a plurality of heddle shafts, to which a drive mechanism with a plurality of servo motor groups (13, 14) is assigned. The servo motor groups are located below each of the heddle shafts (3 through 8), in each case as a cluster, and they are located with their pivot axes (27 through 32) on a circle, an ellipse, or a similar figure. They are also axially offset from one another. Each servo motor (15 through 20) is provided with a driven lever (21 through 26). The free ends of all the levers are located approximately at the center of the circle or ellipse or other figure of revolution. They are connected to the heddle shafts (3 through 8) via connecting rods (34 through 39) and form various angles with the connecting rods (34 through 39). The result is a drive mechanism with little inertia, low resilience, and little play. Very fast shaft motions can be attained in a controlled way.

The invention provides a repeated locking and unlocking mechanism for a master-slave non-contact double-super-satellite platform. The repeated locking and unlocking mechanism for the master-slave non-contact double-super-satellite platform comprises a first installation body, a second installation body, electromagnetic locking mechanisms, an electric driving bolt and an emergency unlocking mechanism, wherein one electromagnetic locking mechanism and the electric driving bolt are arranged on the first installation body; the other electromagnetic locking mechanism and the emergency unlocking mechanism are arranged on the second installation body; the first installation body and the second installation body can be attracted for locking after being powered on through the two electromagnetic locking mechanisms and can be powered off for unlocking through the two electromagnetic locking mechanisms; the emergency unlocking mechanism is provided with a butt joint nut matched with the electric driving bolt; and after the first installation body and the second installation body are locked through the two electromagnetic locking mechanisms, the electric driving bolt is unscrewed to be connected with the butt joint nut. According to the repeated locking and unlocking mechanism for the master-slave non-contact double-super-satellite platform, the electromagnetic locking mechanisms are arranged, and thus repeated locking and separating functions can be achieved through on-off of electromagnetic induction coils.

A shed forming device (1) for a power loom has a plurality of heddle shafts, to which a drive mechanism with a plurality of servo motor groups (13, 14) is assigned. The servo motor groups are located below each of the heddle shafts (3 through 8), in each case as a cluster, and they are located with their pivot axes (27 through 32) on a circle, an ellipse, or a similar figure. They are also axially offset from one another. Each servo motor (15 through 20) is provided with a driven lever (21 through 26). The free ends of all the levers are located approximately at the center of the circle or ellipse or other figure of revolution. They are connected to the heddle shafts (3 through 8) via connecting rods (34 through 39) and form various angles with the connecting rods (34 through 39). The result is a drive mechanism with little inertia, low resilience, and little play. Very fast shaft motions can be attained in a controlled way.

The invention discloses a truss type satellite structure suitable for a point type satellite-rocket separation mode, and the structure comprises a composite truss and a honeycomb sandwich structure plate, and is provided with a platform cabin and a load cabin; the composite truss comprises platform cabin truss vertical rods, load cabin truss vertical rods, truss transverse rods, lifting connectors, satellite-rocket separation connectors and inter-cabin butt joints. The load cabin truss vertical rods are in one-to-one correspondence with the platform cabin truss vertical rods; the bottom ends of the platform cabin truss vertical rods are fixedly connected with satellite-rocket separation joints, and the top ends of the platform cabin truss vertical rods are fixedly connected with the bottom ends of the load cabin truss vertical rods through inter-cabin butt joints; the top end of the load cabin truss vertical rod is fixedly connected with a lifting connector. The satellite structure can meet the requirements of a satellite on strength, rigidity, precision and various interfaces, is easy to process and assemble, and can meet the requirements of batch production and modular subdivision operation of products.

The invention relates to the technical field of aerospace, and in particular relates to a satellite support and a carrier rocket. The satellite support comprises a first force bearing structure on which a satellite is arranged, a second force bearing structure which is arranged on the outer side of the first force bearing structure and is suitable for being connected with a control cabin of the carrier rocket, and a connecting structure which is arranged between the first force bearing structure and the second force bearing structure, and the two ends of the connecting structure are connected with the first force bearing structure and the second force bearing structure respectively; the first force bearing structure, the second force bearing structure and the connecting structure are integrally formed. The first force bearing structure, the second force bearing structure and the connecting structure of the satellite support are integrally formed, so that the satellite support only comprises a necessary main body structure, other connecting structures for connecting the main body structure do not need to be additionally arranged, the number of parts is reduced as much as possible, the overall size of the satellite support is reduced, and overall assembling procedures are reduced; the assembly is simple, the weight of the satellite support is reduced, and the overall carrying capacity of the carrier rocket is improved.

A two-section thin shell type high-stability integrated structure comprises shell section sheets, strengthening ribs, strengthening cover plates, upper strengthening corner boxes, lower strengtheningcorner boxes, a honeycomb bottom plate, a star sensor support, a camera connecting piece and an upper end face. The shell section sheets are symmetrically arranged relative to the symmetry axis of thehoneycomb bottom plate. The upper portions of the shell section sheets are connected with the upper end face, and the lower portions of the shell section sheets are connected with the honeycomb bottom plate. The strengthening ribs are arranged on the two sides of the shell section sheets. The upper strengthening corner boxes are distributed at the included angle position between the upper end face and the surfaces of the shell section sheets in the circumferential direction, and the lower strengthening corner boxes are distributed at the included angle position between the surfaces of the shell section sheets and the honeycomb bottom plate in the circumferential direction. The star sensor support and the camera connecting piece are arranged on the upper end face, and the strengthening cover plates are arranged in the included angles between the side faces of the strengthening ribs and the upper end face. Through the two-section thin shell type structure, sufficient layout space is provided for an optical camera, meanwhile, an integrated installing plane is provided for the optical camera and the star sensor support, and the requirements for rigidity, strength and micron-order heatstability design are met.

The invention relates to a half hidden type elevating rudder rocker arm, and belongs to the technical field of control surface structures of airplane tail wings. A rocker arm main body is positioned between a right control surface and a left control surface, the rocker arm main body is connected with an ear piece of a left joint in the left control surface through an ear piece of a right joint in the right control surface; the rocker arm main body is 'S'-shaped; the rocker arm main body is connected to a horizontal tail joint through a horizontal tail joint bolt; the rocker arm main body is connected with a control operating rod through a control connecting bolt. The structural style of the rocker arm has the advantages that aiming at the characteristic that the structure space of a light aeroplane is small, the structural style of the elevating rudder control rocker arm is improved, a traditional torque tube structure is cancelled, the conventional structure is fully used, the left control surface and the right control surface are integrally and directly connected with the rocker arm through the two symmetrical joints. The elevating rudder adopting the structural style is good in integrality, the rocker arm is half hidden type, only part of the control ear pieces is exposed, the force transmission path is short, the crossbeam directly participates in load carrying, the assembly parts are reduced, and the joint bolts of the left control surface and the right control surface are simplified as two.

The invention discloses an inverted cup-type cradle for use in a drop test of a landing chassis, which is an important component for use in the simulation of the normal weight of an aircraft and the lThe invention discloses an inverted cup-type cradle for use in a drop test of a landing chassis, which is an important component for use in the simulation of the normal weight of an aircraft and the lional rigidity, short power transmission route, large rigidity, and capacity for simulating the normal weight of a miniature aircraft.ional rigidity, short power transmission route, large rigidity, and capacity for simulating the normal weight of a miniature aircraft.oading of the landing chassis of a landing chassis drop test bed and for forming a drop system with the landing chassis drop test bed. The cradle comprises a box body, a cradle top plate and a guide doading of the landing chassis of a landing chassis drop test bed and for forming a drop system with the landing chassis drop test bed. The cradle comprises a box body, a cradle top plate and a guide device using the inverted cup-type cradle to do linear motion vertical to the ground, wherein the guide device is fixed on two opposite sides of the box body; and the lower surface of the cradle top plevice using the inverted cup-type cradle to do linear motion vertical to the ground, wherein the guide device is fixed on two opposite sides of the box body; and the lower surface of the cradle top plate is provided with a fixing device for mounting the landing chassis to form a inverted cup-type structure, and the inside of the inverted cup-type structure is provided with a rigidity adjusting devate is provided with a fixing device for mounting the landing chassis to form a inverted cup-type structure, and the inside of the inverted cup-type structure is provided with a rigidity adjusting device. Compared with the conventional cradle, the inverted cup-type cradle has the advantages of saving the space and height and construction cost of the drop test bed, along with adjustable multidirectice. Compared with the conventional cradle, the inverted cup-type cradle has the advantages of saving the space and height and construction cost of the drop test bed, along with adjustable multidirect

The invention relates to a mixed supporting system for steel structure integral lifting construction. The mixed supporting system involves the following steps of 1, determining the arrangement positions of lifting points; 2, determining the lifting points arranged on an original structure and the lifting points independent of the original structure, and determining the number of the lifting points arranged on the original structure and the number of the lifting points independent of the original structure; 3, determining the type and form of a lifting supporting structure; 4, determining the specification of a lifting support at the lifting supporting structure, and determining the specification of a lifting tower of the lifting supporting structure; 5, determining the reinforcing form of the lifting support at the lifting supporting structure, adding lifting support rear pull rods, and improving the stability in the plane of the lifting support; and 6, adding a connecting structure at the top of the lifting tower of the lifting supporting structure for reinforcement, improving the stability in a lifting process, and forming the mixed lifting supporting system by different types of lifting supporting structures.

A two-section thin shell type high-stability integrated structure comprises shell section sheets, strengthening ribs, strengthening cover plates, upper strengthening corner boxes, lower strengtheningcorner boxes, a honeycomb bottom plate, a star sensor support, a camera connecting piece and an upper end face. The shell section sheets are symmetrically arranged relative to the symmetry axis of thehoneycomb bottom plate. The upper portions of the shell section sheets are connected with the upper end face, and the lower portions of the shell section sheets are connected with the honeycomb bottom plate. The strengthening ribs are arranged on the two sides of the shell section sheets. The upper strengthening corner boxes are distributed at the included angle position between the upper end face and the surfaces of the shell section sheets in the circumferential direction, and the lower strengthening corner boxes are distributed at the included angle position between the surfaces of the shell section sheets and the honeycomb bottom plate in the circumferential direction. The star sensor support and the camera connecting piece are arranged on the upper end face, and the strengthening cover plates are arranged in the included angles between the side faces of the strengthening ribs and the upper end face. Through the two-section thin shell type structure, sufficient layout space is provided for an optical camera, meanwhile, an integrated installing plane is provided for the optical camera and the star sensor support, and the requirements for rigidity, strength and micron-order heatstability design are met.

An asymmetrical V-groove, two-point unlocking type rigid tape for inter-stage line separation device, its features include rigid tape, tape end, asymmetrical V-groove, bolt holes; rigid tape The inner surface is processed into an asymmetric V-shaped groove; the tape ends are provided with bolt holes; the wedge-shaped flange on the lower end of the upper separation body and the wedge-shaped flange on the upper end of the lower separation body are butted to form an asymmetric V-shaped flange embedded in the rigid The asymmetric V-shaped groove on the inner surface of the tape realizes the connection function. Compared with the existing technology at home and abroad, the rigid tape of the present invention has the advantages of high reliability, simple and convenient installation, good connection stiffness of the butt joint surface, uniform distribution of contact stress and pretightening force at the end frame interface, and strong ultimate bearing capacity. The rigid tape has large openings on both sides in the free state. After the pre-tightening force is applied, the four free ends of the rigid tape are tightened, and a large elastic deformation occurs in the radial direction. The elastic deformation of the rigid tape itself is used to realize The quick release function after unlocking can meet the needs of large-scale launch missions with large payloads and large diameters in the future.

The invention discloses a rotation starting separation mechanism which comprises a shell, a rotary drum, spiral sliding grooves, a roller assembly, a cable drum, a bearing, a rotation starting spring and a pressing assembly. The cable drum is fixed in the shell and is sleeved outside an electric connector on a main detector; at the beginning, a rotation starting load is connected with the electric connector in an inserted mode. The rotary drum is a double-layer sleeve, the inner layer is located outside the cable drum, and the outer layer is located in the shell; the three spiral sliding grooves are evenly fixed to the outer surface of the outer layer of the rotary drum in the circumferential direction, and the roller assembly is fixed to the upper end of the shell and is in rolling fit with the spiral sliding grooves. The shell and the rotation starting load are locked or unlocked through a pressing assembly, and when the rotation starting load and the shell are locked, the rotation starting load limits the upward movement of the rotary drum; the bearing is coaxially fixed on the outer surface of the inner layer of the rotary drum, the rotation starting spring is pressed between the bearing and the inner bottom surface of the shell, when the rotation starting load and the shell are unlocked, the rotation starting spring releases elastic potential energy, and the bearing converts the translation of the rotation starting spring in the axial direction of the cable drum into the spiral motion of the rotary drum.

The invention relates to a half hidden type elevating rudder rocker arm, and belongs to the technical field of control surface structures of airplane tail wings. A rocker arm main body is positioned between a right control surface and a left control surface, the rocker arm main body is connected with an ear piece of a left joint in the left control surface through an ear piece of a right joint in the right control surface; the rocker arm main body is 'S'-shaped; the rocker arm main body is connected to a horizontal tail joint through a horizontal tail joint bolt; the rocker arm main body is connected with a control operating rod through a control connecting bolt. The structural style of the rocker arm has the advantages that aiming at the characteristic that the structure space of a light aeroplane is small, the structural style of the elevating rudder control rocker arm is improved, a traditional torque tube structure is cancelled, the conventional structure is fully used, the left control surface and the right control surface are integrally and directly connected with the rocker arm through the two symmetrical joints. The elevating rudder adopting the structural style is good in integrality, the rocker arm is half hidden type, only part of the control ear pieces is exposed, the force transmission path is short, the crossbeam directly participates in load carrying, the assembly parts are reduced, and the joint bolts of the left control surface and the right control surface are simplified as two.

A dragging unfolding type high-rigidity stretching arm with high spatial folding-unfolding ratio comprises a folding and unfolding unit set, an axial force bearing cable, unfolding jet engines and an end face force bearing plate. The two unfolding jet engines are fixed to the two end face force bearing plates respectively, a foldable unit set is arranged between the two end face force bearing plates, the foldable unit set comprises N foldable units hinged in series, and the two foldable units on the outermost side are fixedly connected with the two end face force bearing plates respectively. Each foldable unit is a triangular prism after being unfolded, a telescopic rod is hinged to the opposite angle of each side face of the triangular prism, the telescopic rods stretch out along with unfolding of the foldable units and retract along with folding, and the three axial force bearing cables stretch across the corresponding side faces of the N foldable units respectively and are limited in the radial direction. The two ends of each axial force bearing cable are fixed to the two end face force bearing plates respectively. According to the stretching arm, the rigidity and the tensile capacity are improved, and the dragging and unfolding driving mode is high in efficiency and can adapt to unfolding of the large-scale stretching arm.

The invention discloses a lattice type large antenna azimuth seat frame with a tower footing, and relates to an antenna technology in the fields of communication, measurement and control, radar, radio astronomy and the like. The invention discloses a seat frame, and aims to provide a seat frame which is high in rigidity, strong in overturning resistance, large in equipment operation space and not easy to destabilize. The device comprises a main supporting truss, a side supporting beam, a radial oblique beam, a lower edge beam, an inner oblique beam, a central tower footing, a central pivot, a bearing seat, a roller mechanism and a track. The main supporting truss is of a lattice structure and is composed of a plurality of triangular grids. The central tower footing is located in the center of the seat frame, the upper portion of the central tower footing is a central pivot, and the side supporting beams and the radial oblique beams intersect on the central pivot. The rolling wheel mechanism is composed of four sets, each set of rolling wheel mechanism comprises eight rolling wheels, and the rolling wheels are arranged in a one-to-two mode, a two-to-four mode and an eight-to-four mode. According to the invention, the overall rigidity and wind load resistance of the seat frame structure are effectively improved, and the seat frame structure is particularly suitable for design and manufacturing of azimuth seat frames of large and ultra-large antennas.

The invention relates to a spacecraft parking mechanism, and belongs to the field of space station cargo transportation. The spacecraft parking mechanism comprises an active end and a passive end. Theactive end comprises a three-jaw connecting mechanism, a spring push rod separation mechanism, a ball screw transmission mechanism, a worm and gear self-locking mechanism, an active end shell, an active end electric interface, a push disc and a fixed disc; the passive end comprises a passive end shell, a passive end disc spring assembly, a passive end electric interface and a passive end guide directional hole; after the active end is aligned with the active end under the driving of the space mechanical arm, the three-jaw connecting mechanism is rotated outwards to be opened; the active end continues to move towards the driven end until the active end electric interface is inserted into the passive end electric interface and is inserted in place; three clamping jaws of the three-jaw connecting mechanism rotate inwards to be closed, and locking and fixing are achieved. Mechanical connection between carried goods and a space station can be achieved under the assistance of the space mechanical arm, the goods can be parked in the space station, and stable parking can be kept for a long time. When separation is needed, low-impact reliable separation is realized.

The invention discloses a multichannel device for the rear end of a front vehicle body. The multichannel device comprises a front girder welded part, a front surrounding plate and a front floor; the front surrounding plate and the front floor are fixedly connected to the front girder welded part, the front surrounding plate and the front floor are fixedly connected, front floor reinforcing platesare fixedly connected to the inner sides of the middles of the two sides of the front girder welded part correspondingly, the longitudinal sections of the front floor reinforcing plates are in U shapes, the upper parts of the front floor reinforcing plates are fixedly connected with the front surrounding plate, the middles of the front floor reinforcing plates are fixedly connected with the frontfloor, the right ends of the front floor reinforcing plates are fixedly connected with front floor center channel reinforcing plates, and the front floor center channel reinforcing plates are fixedlyconnected to the front floor. According to the multichannel device for the rear end of the front vehicle body, the local rigidity of an overlapped area of the front girder welded part, the front surrounding plate and the front floor is improved, meanwhile, the force transferring path is increased, collision energy is dispersed into all main bearing parts as much as possible, and thus the force transferring path is more multidirectional, shorter and more stable.

The invention discloses an asymmetric V-shaped groove and double-point unlocking type rigid wrapping tape for an interstage line type separation device. The asymmetric V-shaped groove and double-pointunlocking type rigid wrapping tape for the interstage line type separation device is characterized by comprising a rigid wrapping tape, wrapping tape ends, an asymmetric V-shaped groove and bolt holes; the inner surface of the rigid wrapping tape is processed into the asymmetric V-shaped groove; the bolt holes are formed in the end heads of the wrapping tape ends; and the lower end surface wedge-shaped flange of an upper separating body is in butt joint with the upper end surface wedge-shaped flange of a lower separating body to form an asymmetric V-shaped flange which is embedded into the asymmetric V-shaped groove on the inner surface of the rigid wrapping tape, so that a connecting function is realized. Compared with the prior art at home and abroad, the rigid wrapping tape has the advantages of being high in reliability, simple and convenient to install, good in butt joint surface connection rigidity, uniform in distribution of end frame interface contact stress and pre-tighteningforce, high in ultimate bearing capacity and the like. Openings at the two sides of the rigid wrapping tape are large in a free state, after the pre-tightening force is applied, four free ends of therigid wrapping tape are tensioned, large elastic deformation occurs in the radial direction, quick separation function after unlocking is realized by utilizing the elastic deformation of the rigid wrapping tape, and the requirement of large-load large-diameter large-scale launching tasks in the future is met.

The invention discloses a pressing device for a planar antenna and a layout method. The pressing device comprises a first sleeve, a pressing rod, an embedded part, a second sleeve, a third sleeve, a force application sleeve, an outer sleeve, a honeycomb pad, a pressing nut, a spherical pad, a spring top sleeve, a compression spring, a spring bottom sleeve and a separation nut. The pressing device takes two antenna plates as a group and is respectively connected with a satellite platform, so that 'layered pressing' between a plurality of plates and a satellite body is realized. According to the invention, the release stroke of the pressing device is not influenced by the number of the antenna plates, and the connection of a plurality of plates and a star body is converted into a connection structure form of two plates and the star body, so that the reliability of unlocking is improved; the shell and the star platform are positioned and reset through the separation nut, and compared with a pin positioning mode, the problems that the machining difficulty of a star mounting surface is large, and the precision is difficult to guarantee are solved; and compression among a plurality of antenna plates is transmitted through the embedded parts, and compared with a traditional sleeve for transmitting force, the compression effect of the antenna is better.