47results about How to "High storage ratio" patented technology

The invention discloses a large spatial assembly type antenna reflector modular unit and an assembly method thereof. The modular unit comprises a hexagonal extensible truss, a reflecting rope net and a rope connecting device, wherein the hexagonal extensible truss comprises top hinges, a synchronous power hinge, annular rods, and middle slanting poles; two annular rods with the same length form asynchronous folding rod through the synchronous power hinge, and the synchronous power hinge is connected with two middle slanting poles through three top hinges to form a planar triangle structural unit; 12 planar triangle structural units are connected with one another by sharing the middle slanting poles and the top hinges to form a ring, namely the truss of the antenna reflector modular unit;during connection, synchronous folding rods of two adjacent triangle structural units are spatially staggered with each other, and two layers of hexagons with different sizes and staggered vertexes are formed spatially; the reflecting rope net comprises a metal net for reflecting electromagnetic waves and an adjusting rope for adjusting the shape surface of the metal net; the metal net is sewed on the adjusting rope which is fixed with the truss of the modular unit through the top hinges; and the rope connecting device is mainly used for connecting and fixing the reflecting rope net and the hexagonal extensible truss.

The invention discloses a controlled-unfolding coiled stretching arm for unfolding a satellite load. The stretching arm mainly comprises a stretching arm main body, a bottom storage tube, a Y-shaped top plate and an unfolding control assembly, wherein one end of the stretching arm main body is connected with the storage tube, the other end of the stretching arm main body is connected with the Y-shaped top plate, a driving unit in the unfolding control assembly is mounted at the bottom of the storage tube, and an unfolding control cable is connected to the Y-shaped top plate. The stretching arm has the characteristics of high storage ratio, light weight, high reliability and the like, can realize the linear-direction short-distance or middle/far-distance unfolding, is applicable to the unfolding of satellite loads, such as magnetometers, antennae and gravity gradient counterweights and has wide application adaptability.

The invention discloses a retractable spatial stretching arm for a satellite. The retractable spatial stretching arm mainly comprises a mounting bracket, an elastic stretching arm, a storage device and an unfolding control component, wherein the mounting bracket is mounted at the top end of the elastic stretching arm, the bottom of the elastic stretching arm is mounted on the storage device, and the unfolding control component is mounted on the storage device and is connected with the mounting bracket through a rope system. The retractable spatial stretching arm can realize the linear-direction controlled movement of the unfolding accessories and various load instruments of the satellite and is applicable to satellite loads, such as magnetometers, antennae and gravity gradient counterweights, and working statuses of the retractable spatial stretching arm comprise a folded lock status, an unfolding process and a fully-unfolded status, so that the application adaptability is wide.

The invention provides a manufacturing method of a solar sail capable of being unfolded controllably and orderly based on shape memory polymers, and relates to the manufacturing method of the solar sail, in particular to the manufacturing method of the solar sail for a spacecraft. The invention aims to solve the problems that a driving mechanism is complex, an unfolding process is instable, a structure is easy to damage and air leakage occurs existing in the conventional solar sail with an inflatable type structure, and solve the problems that the structure is complex, the unfolding reliability is poor, the total weight is large, the folding efficiency is low and the emitting volume is large existing in the solar sail with a mechanical unfolded and supported structure. The manufacturing method disclosed by the invention comprises the following steps of firstly synthesizing shape memory polymeric materials into shape memory thin polymer films, and covering electrothermal films on the shape memory thin polymer films; and fixing flexible material light reflecting films on the shape memory thin polymer films covered with the electrothermal films, then energizing for heating the electrothermal films until the shape memory thin polymer films are softened, orderly folding the sail surface of the solar sail, and after power cut, cooling the electrothermal films so as to obtain the solar sail which is folded. The manufacturing method disclosed by the invention is suitable for manufacturing the solar sail.

The present invention provides a circular cross cable antenna which comprises an annular truss and a front cable net and a back cable net which are interlaced by cables. The annular truss comprises aplurality of vertical rods and inclined rods with the equal number. Nodes on the circumference of the front cable net are correspondingly connected to connection parts of the vertical rods and the inclined rods at the top of the annular truss, the front cable net and the back cable net are paraboloids and are in symmetrical arrangement, nodes corresponding to non-intersecting parts of the front cable net and the back cable net are connected by flexible ropes, and nodes corresponding to intersecting parts of the front cable net and the back cable net are connected by support rods. According tothe circular cross cable antenna, a ring-shaped expandable structure is adopted, so the weight is small, the profile precision is good, the storage ratio is high, the excessive arch height is avoided,the overlarge antenna folding size is avoided, the weight of the antenna is reduced, symmetrical cable net structures are used by front and back cable net surfaces, and the good structural stabilityis provided.

The invention discloses a space deployable mechanism designed on the basis of a posterior wing deployable mechanism of dermaptera insect earwigs. The space deployable mechanism is applied to a reflector of a satellite antenna and structurally comprises a first-grade rod set, a second-grade rod set, a third-grade rod set, a supporting rod set, a push-pull rod set, a combined hinge mechanism and a polyester film. End portions of rods in the first-grade rod set are sequentially connected through hinges. The second-grade rod set comprises rods and gears, and the gears are connected with the second-grade rods and then connected with the first-grade rods. Rods in the third-grade rod set are connected with the rods in the second-grade rod set through supporting rods. The rods in the first-grade rod set are driven so that the whole mechanism can be deployed. By the adoption of the space deployable mechanism, controllable folding and deployment of the satellite antenna of a spacecraft can be achieved, and the space deployable mechanism has the beneficial effects that the containing ratio is relatively large, and meanwhile a carbon fiber material is selected and used, so that the whole space deployable mechanism is small in weight, high in strength, good in stability and the like.

The invention provides a reflecting surface folding and unfolding structure of a foldable and deployable antenna of space-based radar, belongs to the technical field of the space-based radar and solves the problems of existing foldable and deployable antennas. The reflecting surface folding and unfolding structure comprises a reflecting surface, transverse ribs, bistable composite foldable and deployable cylindrical shells and auxiliary unfolding inflatable arms, wherein the reflecting surface is rectangular, the multiple transverse ribs arranged in the width direction of the reflecting surface are mounted on the surface of one side of the reflecting surface, are bonded with the reflecting surface and adopt a hollow tubular structure, the surface, bonded with the reflecting surface, of each transverse rib is a plane, and the surface, opposite to the surface bonded with the reflecting surface, of each transverse rib is an indent arc surface; at least two bistable composite foldable and deployable cylindrical shells are arranged between every two adjacent transverse ribs, and two ends of each bistable composite foldable and deployable cylindrical shell are contacted with the adjacent transverse ribs respectively; the two transverse ribs located on the outmost side of all the transverse ribs are connected through the at least two auxiliary unfolding inflatable arms. The reflecting surface folding and unfolding structure is applied to the space-based radar.

The invention relates to an expandable double-layer hybrid space planar antenna in the technical field of spacecrafts, and the antenna comprises: a planar film antenna frame, which comprises expansion rods and cross rods, and the expansion rods and the cross rods are connected to form a rectangular structure; multiple groups of three-dimensional metal net antenna frame assemblies, which comprises metal net supporting rods and rotating seats, and are installed on the planar film antenna frame; a pressing and releasing device, which comprises a first pressing and releasing apparatus and a second pressing and releasing apparatus; two planar film antenna frames are connected through flexible hinges and folded to form a double-layer frame, a pressing base is connected with an upper cross rod and a lower cross rod in the double-layer frame, the first pressing and releasing apparatus is connected with an upper expansion rod and a lower expansion rod in the double-layer frame, and the metal net supporting rods are locked on the side faces of the expansion rods through the second pressing and releasing apparatus and are kept parallel. Folding of the planar film antenna and a metal net cavity is realized, and a higher storage ratio is realized through resultant force layout of an unfolding mechanism.

The embodiment of the present invention provides a truss type extensible antenna reflector, and belongs to the technical field of antennas. A cable-net structure of the reflector includes an upper layer of cable net, a lower layer of cable net, a tension array and multiple flower disc connecting columns; the flower disc connecting columns extend along a vertical direction; the upper layer of cablenet and the lower layer of cable net are fixedly stacked via the flower disc connecting columns on a net surface formed by folding rods; the upper layer of cable net is spliced by multiple first triangular lattice units; the lower layer of cable net is spliced by multiple second triangular lattice units; an exterior outline of each triangular lattice unit is matched with a triangle; at least onefirst node is provided at an edge of each first triangular lattice unit; a second node matched with the first node in one-to-one correspondence is provided at an edge of each second triangular latticeunit; and corresponding first nodes and second nodes are fixed by corresponding tension array ropes. The truss type extensible antenna reflector can increase the number of nodes without adding a truss unit, can reduce the weight of the reflector obviously, and improves the storage ratio.

The invention provides a light flexible inflatable deployable dipole antenna structure. The light flexible inflatable deployable dipole antenna structure comprises an inflatable frame main body, a feed assembly and a reflection cavity. According to the invention, the weight of the dipole antenna is limited by adopting an inflatable unfolding mode; an antenna inflation frame is made of a flexible composite material, the reflection cavity is made of a metal net in a stretched mode, a feeder line does not need to be supported by a medium, the super-flexible cable is straightened by means of the tensile force of inflation and unfolding of the frame, the weight of the antenna is greatly reduced, and the advantages of the antenna form are brought into play to the maximum extent. Along with the increase of the number of arrays, the antenna can be folded, the storage ratio is small, and along with the increase of the number of arrays, the storage ratio is also reduced, so that the antenna is suitable for large-scale antennas and structures, platforms with loading weight and volume requirements, and the application prospect is wide.

A high-storage-ratio unfolding and supporting mechanism comprises scissor-type driving mechanisms and supporting parts; the two scissor-type driving mechanisms which are arranged in parallel are installed at two ends of each ninth rod piece (9), and the supporting parts are connected with the scissor-type driving mechanisms through the ninth rod pieces (9). When the unfolding and supporting mechanism is unfolded, a space triangular-prism-shaped frame structure is formed under the drive of the scissor-type driving mechanisms. According to the unfolding and supporting mechanism, the problem thatan existing hinged type foldable supporting mechanism is low in storage ratio is solved, the structure is simple, the manufacturing is easy, the cost is low, and the storage ratio is remarkably increased.

The invention discloses a high-rigidity and high-storage-ratio unfolding antenna mechanism. The high-rigidity and high-storage-ratio unfolding antenna mechanism comprises a compression antenna windingdrum and a guiding limiting mechanism; an antenna is arranged in the compression antenna winding drum; and a compressing releasing mechanism is arranged on the outer side of the guiding limiting mechanism. The high-rigidity and high-storage-ratio unfolding antenna mechanism has the characteristics of high storage ratio, light weight, repeatable expansion and the like; and the extended antenna diameter and length can be adjusted, and the unfolding speed of the mechanism can be controlled, thereby reducing impact after the antenna is in the proper position.

The invention relates to a loading plate unfolding component of a spacecraft. The loading plate unfolding component of the spacecraft comprises a loading single wing; the loading single wing comprisesat least four loading plate groups hinged to each other; the loading plate groups comprise two hinged loading plates and supporting rods I, wherein the supporting rods I are hinged to the left and right ends of the loading plate groups; at least one active interplate hinge is arranged between the adjacent loading plates of the loading single wing; one ends of the supporting rods I are hinged to the end parts of the loading plates; the other ends of the supporting rods I are hinged to the other supporting rod of the same loading plate groups; middle supporting rod groups are arranged between the adjacent loading plate groups of the loading single wing; and moreover, the middle supporting rod group in the midst is a first middle supporting rod group; the other middle supporting rod groups are second middle supporting rod groups; the first middle supporting rod group comprise two symmetrically arranged connecting rod groups; each connecting rod group comprises a supporting rod IV and a supporting rod V; and the second middle supporting rod groups comprise two supporting rods II. The loading plate unfolding component of the spacecraft is used for unfolding the multiple loading platesand possesses high storage ratio.

The invention discloses a foldable tent. The foldable tent comprises a foldable bracket which is composed of more than two horizontal shear type mechanisms and more than two longitudinal chain-shapedshear mode mechanisms. Each horizontal shear type mechanism is composed of an upper chord arch, supports and an inhaul cable, wherein the upper chord arch is composed of a plurality of first shear type hinge units connected end to end. Each support is composed of a plurality of second shear type hinge units, telescopic bars and flexible cables. The upper ends of the supports are arranged on crosshinged joints of the upper chord arch and the shear type hinge units. The telescopic bars are arranged at the end portions of the second shear type hinge units, and the end portions of every two adjacent second shear type hinge units are connected through the flexible cables. Compared with the prior art, the foldable tent is simple in unfolding and folding type, convenient to drive and good in stress performance, the foldable tent has the advantages of convenient installation and manufacturing and the like, so as to well meet the requirements for the rapid unfolding and folding function of temporary, semi-permanent or special structures, meanwhile, transportation space is saved and the cost is reduced.