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47results about How to "High storage ratio" patented technology
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Large spatial assembly type antenna reflector modular unit and assembly method thereof
ActiveCN102173312AImprove reliabilityHigh storage ratioCosmonautic vehiclesCosmonautic partsModular unitComputer module
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.
Owner:XIAN INSTITUE OF SPACE RADIO TECH
Expandable mechanism of space plane thin film antenna
ActiveCN107453017AHigh storage ratioGuaranteed synchronicityPivotable antennasClosed loopEngineering
The invention discloses an expandable mechanism of a space plane thin film antenna. The expandable mechanism comprises the expandable mechanism, and a plane thin film connected with the expandable mechanism through a connecting rope; rigid frames which are hinged end to end, a pair of short synchronous rods connected with the rigid frames, a pair of connecting rods and a pair of hinged long synchronous rods are arranged on the expandable mechanism to form an expandable mechanism framework; the pair of the rigid frames, the pair of short synchronous rods and the pair of long synchronous rods are hinged through annular connectors; the long synchronous rods are hinged with the rigid frames, the short synchronous rods and the rigid frames through radial connectors; the annular connectors and the radial connectors are provided with pulleys; a pulling rope winds the pulleys on the annular connectors and the radial connectors in sequence to form a closed loop; the head and tail ends of the pulling rope are connected with a motor shaft of a satellite; and the expandable mechanism can be expanded under driving of a motor winding-unwinding pulling rope on the satellite. The expandable mechanism can be folded by adopting an out-of-plane two-dimensional folding mode, so that the storage ratio and the expanded caliber area are greatly improved, and therefore, the expandable mechanism can be more suitable for application of large-scale and even super-large-scale plane thin films.
Owner:XIDIAN UNIV
Controlled-unfolding coiled stretching arm for unfolding satellite load
InactiveCN103693212AHigh storage ratioMeet the installation requirementsCosmonautic vehiclesCosmonautic partsFar distanceShortest distance
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.
Owner:SHANGHAI SATELLITE ENG INST
Retractable spatial stretching arm for satellite
InactiveCN103693217ASimple structureImprove reliabilityCosmonautic vehiclesCosmonautic partsEngineeringWork status
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.
Owner:SHANGHAI SATELLITE ENG INST
Manufacturing method of solar sail capable of being unfolded controllably and orderly based on shape memory polymers
ActiveCN105480436ALightweight materialLight in massCosmonautic power supply systemsSolar sailPolymer thin films
Owner:HARBIN INST OF TECH
Circular cross cable antenna
ActiveCN108306100AAvoid collapsing dimensionsLight in massAntenna supports/mountingsRadiating elements structural formsCable netEngineering
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.
Owner:XIDIAN UNIV
Space deployable mechanism designed on basis of posterior wing deployable mechanism of dermaptera insect earwigs
ActiveCN106364700AReduce weightImprove controllabilityCosmonautic vehiclesCosmonautic partsFiberPolyester
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.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Reflecting surface folding and unfolding structure of foldable and deployable antenna of space-based radar
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.
Owner:HARBIN INST OF TECH
Expandable double-layer hybrid space planar antenna
ActiveCN112736403ARealize folding and collapsingHigh storage ratioCollapsable antennas meansBi layerStructural engineering
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.
Owner:SHANGHAI SATELLITE ENG INST
Parabolic cylindrical surface deployable antenna adopting Y-shaped rib cable net, control method and application
The invention belongs to the technical field of satellite-borne deployable antennas, and discloses a Y-shaped rib cable net parabolic cylinder deployable antenna, a control method and application, which are composed of a Y-shaped rib support truss, a cable net and a metal wire net. The Y-shaped rib supporting truss is composed of a Y-shaped rib deployable unit in the parabola direction and a shear type deployable unit in the baseline direction, and the Y-shaped rib deployable unit and the shear type deployable unit are connected through a fixed hinge joint and a sliding hinge joint at the tail end of the shear type deployable unit. End points on the two sides of the cable net and nodes on the lower side of the cable net are connected with the Y-shaped rib deployable units, and a needed parabolic cylinder shape is formed through pretension design. The metal wire mesh is laid on the cable mesh to receive and reflect electromagnetic waves. The Y-shaped rib supporting truss serves as a supporting and unfolding mechanism of the cable net parabolic cylinder deployable antenna, and smooth unfolding of the antenna in the parabola direction and the baseline direction is achieved under combined driving of the torsional spring and the inhaul cable. The folding mechanism is large in unfolding caliber, high in storage ratio, high in unfolding reliability and high in structural expansibility.
Owner:XIDIAN UNIV
Multi-beam satellite-borne AIS signal receiving system and method based on time modulation metasurface
ActiveCN112688770ASimple structureEasy Bias ControlMulti-frequency code systemsSignal channelsLow noiseTelecommunications
The invention provides a multi-beam satellite-borne AIS signal receiving system and method based on a time modulation metasurface. The multi-beam satellite-borne AIS signal receiving system comprises the time modulation metasurface and a 1-bit coding unit on the surface; a feed source, a low-noise amplifier, a mixer and a local oscillator connected in sequence, used for carrying out low-noise amplification and down-conversion on a received AIS signal and converting the AIS signal into a digital domain; and a low-pass filter and an analog-to-digital converter, sequentially connected, and the mixer. The low-pass filter and the analog-to-digital converter are used for controlling and periodically modulating the phase of the one-bit coding unit on the time modulation metasurface and filtering and demodulating the received AIS signal, so that simultaneous multi-beam detection of the AIS signal is realized. According to the system, the implementation difficulty of the satellite-borne large-aperture antenna is reduced, and the AIS cells covered by the independent beams are isolated through space / frequency, so that the time slot conflict probability of satellite-borne AIS signal interception is reduced, and the high interception probability is realized.
Owner:SHANGHAI SATELLITE ENG INST
Truss type extensible antenna reflector
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.
Owner:XIAN INSTITUE OF SPACE RADIO TECH
Light flexible inflatable deployable dipole antenna structure
ActiveCN111146557AReduce weightHigh storage ratioInflatable antennasAntenna adaptation in movable bodiesMetal meshDipole antenna
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.
Owner:CHINA ELECTRONICS TECH GRP NO 39 RES INST
A Modular Planar Antenna
ActiveCN106654504BSolving Series Reliability IssuesSolve the problem of low base frequencyInflatable antennasPivotable antennasComputer moduleModularity
The invention discloses a modular planar antenna, belongs to the technical field of a space-borne antenna, and solves the problems existing in the current Z-shaped foldable strip-shaped planar antenna. The modular planar antenna comprises a Z-shaped foldable antenna panel which is formed by a plurality of planar signal transceiving modules hinged in an end-to-end manner in sequence; a supporting arm is arranged on each of the two side edges, perpendicular to corresponding connecting seams, of the antenna panel separately; the supporting arms adopt flexible gas filled tubes; each supporting arm is glued with the antenna panel through a piece of connecting cloth for coating the supporting arm; end covers are arranged at one ends of the same side of the two supporting arms; a truss, which is formed by a plurality of flexible gas filled tubes in a gluing manner, is arranged on the back surface of the antenna panel; a flexible baffle is arranged in a position, corresponding to each connecting seam of the antenna panel, in each supporting arm; and the diameter of a through hole in each flexible baffle is gradually reduced from one side of the end cover. The modular planar antenna is used for a space-borne platform.
Owner:HARBIN INST OF TECH
High-storage-ratio unfolding and supporting mechanism
ActiveCN107618679ASimple structureEasy to manufactureCosmonautic power supply systemsEngineeringTriangular prism
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.
Owner:CHINA ACADEMY OF SPACE TECHNOLOGY
High-storage-ratio modular folding and unfolding supporting truss
ActiveCN112259949AControllable expansion arcLight in massPivotable antennasAntenna supports/mountingsFlight vehicleIndustrial engineering
The invention discloses a high-storage-ratio modular folding and unfolding supporting truss, which relates to the technical field of aerospace machinery, in particular to a high-storage-ratio modularfolding and unfolding supporting truss of a framework type antenna and a space dust detector of an aircraft. In the changing process from the folded state to the unfolded state, on one hand, the central rod compression spring drives the central rod sliding block to drive the inclined web member to be unfolded, on the other hand, the outer rod compression spring drives the crank sliding block mechanism to drive the inclined web member to be unfolded, and the leaf spring drives the lower chord member to assist in unfolding. Due to the design of locking mechanisms in the chassis and the outer rodconnector, the unfolding radian of the supporting truss is controllable, and the supporting truss can be unfolded into a plane or a curved surface. The grooves in the inclined web member are matchedwith the elastic positioning pins to limit the relative positions of the telescopic rods of the inclined web member, and the maximum unfolding length of the inclined web member is limited. Due to thedesign of the crank sliding block mechanism, the unfolding synchronism of the two adjacent upper chords or the two adjacent inclined web members in the unfolding process of the folding and unfolding supporting truss is guaranteed.
Owner:AEROSPACE DONGFANGHONG SATELLITE
A deployment mechanism of a parabolic cylindrical antenna reflector with high accommodation ratio
A deployment mechanism of a parabolic cylindrical antenna reflector with a high accommodation ratio comprises a plurality of groups of M-shaped antenna reflector deployment mechanisms (1); Each groupof M-shaped antenna reflector deployment mechanism (1) is installed on the support truss; The M-shaped antenna reflector deployment mechanism (1) is of a symmetrical structure and comprises a power source (3), a middle fixed mandrel (10) and a linkage mechanism; A sliding pair is established between the power source (3) and the intermediate fixed mandrel (10), A linkage mechanism is connected withthat central fixed mandrel (10) and the power source (3) through a rotating pair, the linkage mechanism is symmetrical about the central fixed mandrel (10), and under the driving action of the powersource (3), the power source (3) slides along the central fixed mandrel (10), thereby driving the linkage mechanism to expand in a plane. The invention solves the parabolic cylindrical surface application problem that 50m or longer size is difficult to realize in the current space mission, and provides a solution for a space large parabolic cylindrical deployable antenna.
Owner:XIAN INSTITUE OF SPACE RADIO TECH
High-storage ratio on-orbit semiautonomous stretching-contracting spatial rollable metal surface antenna and method
ActiveCN106252826ASimple designEasy to processAntenna supports/mountingsAntenna adaptation in movable bodiesHigh stiffnessOrbit
The invention provides a high-storage ratio on-orbit semiautonomous stretching-contracting spatial rollable metal surface antenna and a method. The high-storage ratio on-orbit semiautonomous stretching-contracting spatial rollable metal surface antenna is mainly composed of a hinge-type stretching arm, a rollable metal surface antenna, a storage tube, a stretching control assembly and the like, wherein the hinge-type stretching arm is fixedly connected with the rollable metal surface; the whole metal surface is driven to stretch outwardly through rotation of the storage tube and stretching and locking of the hinge-type stretching arm and reaches the working state; and the deformation energy of the metal surface can also provide partial power for the stretching process. Contracting and stretching of a satellite large-area antenna array surface can be realized; the metal antenna array surface is curled and contracted in a transmission process and is attached to the storage tube; after the satellite enters the orbit, according to a driving control instruction, an antenna surface required by a working state is formed through semiautonomous stretching; and the technique of the invention has the advantages of high storage ratio, light weight, high stiffness, high reliability, wide adaptability and the like.
Owner:SHANGHAI SATELLITE ENG INST
High-rigidity and high-storage-ratio unfolding antenna mechanism
ActiveCN107994313AHigh storage ratioControl the unfolding speedRadiating elements structural formsFlexible aerialsEngineeringConductor Coil
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.
Owner:银河航天(北京)科技有限公司
Loading plate unfolding component of spacecraft
PendingCN109515753AHigh storage ratioDegree of freedom contractionCosmonautic vehiclesCosmonautic partsEngineeringMechanical engineering
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.
Owner:SHANGHAI AEROSPACE SYST ENG INST
Large spatial assembly type antenna reflector modular unit and assembly method thereof
ActiveCN102173312BImprove reliabilityHigh storage ratioCosmonautic vehiclesCosmonautic partsModular unitComputer module
Owner:XIAN INSTITUE OF SPACE RADIO TECH
A deployment antenna mechanism with high stiffness and high storage ratio
ActiveCN107994313BHigh storage ratioControl the unfolding speedRadiating elements structural formsFlexible aerialsStructural engineeringMechanical engineering
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.
Owner:银河航天(北京)科技有限公司
Folding and unfolding large-diameter optical mirror with high storage ratio
Owner:SHANGHAI SATELLITE ENG INST
Controllable deployment truss device with high storage ratio applied to spacecraft
ActiveCN107804484BHigh storage ratioAchieve lightweightCosmonautic partsArtificial satellitesEngineeringControl theory
The invention provides a high-storage-ratio controllable truss spreading device for a spacecraft. The high-storage-ratio controllable truss spreading device includes a triangular-prism truss and a controllable spreading device; the triangular-prism truss comprises an upper triangular frame, upper support rods, hinges, lower support rods, a lower triangular frame, limit bolts and tensile bolts; thecontrollable spreading device comprises tensile arms, a trapezoidal lead screw, limit arms, a lead screw nut, a support frame, a guide rod and the like; the upper triangular frame is located on the upper support rods, the hinges are located between the upper support rods and the lower support rods, the lower triangular frame is located between the lower support rods and the limit bolts, the tensile bolts are located below the limit bolts, the lower triangular frame is located under the upper support rods, the upper triangular frame is located above the tensile bolts, and the tensile arms arelocated on the trapezoidal lead screw. According to the high-storage-ratio controllable truss spreading device for the spacecraft, by adopting the single lead screw and a television, controllable spreading of the triangular-prism truss is achieved; compared with a method using three lead screws, weight reduction of products is achieved, the reliability of a system is improved, and at the same time, the radical size of the system is reduced.
Owner:SHANGHAI SATELLITE ENG INST
Semi-rigid mechanical deployment into deceleration landing gear
InactiveCN105584645BImprove deceleration effectReduced Envelope RequirementsCosmonautic thermal protectionSystems for re-entry to earthSpacecraftLanding gear
The invention discloses a semi-rigid mechanically-unfolded deceleration entering landing device and belongs to the field of spacecraft entrance and return. The semi-rigid mechanically-unfolded entering decelerated landing device comprises a body, a control ring, a rigid head cone, a semi-rigid heat insulation cover, a semi-rigid heat insulation cover control mechanism and a flexible heat insulation cover mechanism. The body is fixedly connected with the control ring. A drive mechanism is connected between the control ring and the rigid head cone and controls the control ring and the rigid head cone to move relatively. The semi-rigid heat insulation cover control mechanism is covered with the semi-rigid heat insulation cover and hinged to the body and the rigid head cone and controls the semi-rigid heat insulation cover to be unfolded or folded. The flexible heat insulation cover mechanism capable of being unfolded outwards secondarily is arranged on the outer side of the semi-rigid heat insulation cover. The total area of the unfolded device is larger than the primarily-unfolded area, the size is kept small in a folded transmission state, the storage ratio of the device is increased, the deceleration effect of a pneumatic face is improved, the system complexity is lowered, and two-stage deceleration and landing buffering are organically unified.
Owner:BEIJING SPACE TECH RES & TEST CENT +1
High storage ratio winding rib type deployable antenna structure
ActiveCN108767418BRelease the constraintsHigh rigidity of reflective surfaceAntenna supports/mountingsTelescopic elementsState of artConductor Coil
The invention relates to a high-storage-ratio winding rib type expandable antenna structure which comprises a mounting base, a center body which is hollow inside and arranged on the mounting base; a telescopic feed source arranged in the center body; a plurality of elastic winding ribs arranged surrounding the outside of the bottom of the center body; a metal mesh surface tensioned and laid on theelastic winding rib and matched with the unfolded elastic winding ribs to form a parabolic reflection surface; a locking assembly comprising a bottom groove which is arranged on the mounting base around the center body, a locking hoop used for restraining the elastic winding ribs to be unfolded and having the bottom in the bottom groove, an upper top plate arranged at the top end of the telescopic feed source and pressing the upper end of the locking hoop, and a locking rope; a release assembly comprising a round rod hot cutter in contact with the locking rope and an external power supply. Compared with the prior art, the elastic winding ribs are used for tensioning the metal mesh surface to form the parabolic reflection surface, ultra-high storage ratio and unfolding reliability can be provided, and enough surface precision is achieved.
Owner:TONGJI UNIV
Circular Cross Cable Net Antenna
ActiveCN108306100BAvoid collapsing dimensionsLight in massAntenna supports/mountingsRadiating elements structural formsCable netControl theory
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.
Owner:XIDIAN UNIV
Space rollable metal surface antenna and method for semi-autonomous deployment and retraction on orbit with high storage ratio
ActiveCN106252826BSimple designEasy to processAntenna supports/mountingsAntenna adaptation in movable bodiesNatural satelliteHigh stiffness
The invention provides a high-storage ratio on-orbit semiautonomous stretching-contracting spatial rollable metal surface antenna and a method. The high-storage ratio on-orbit semiautonomous stretching-contracting spatial rollable metal surface antenna is mainly composed of a hinge-type stretching arm, a rollable metal surface antenna, a storage tube, a stretching control assembly and the like, wherein the hinge-type stretching arm is fixedly connected with the rollable metal surface; the whole metal surface is driven to stretch outwardly through rotation of the storage tube and stretching and locking of the hinge-type stretching arm and reaches the working state; and the deformation energy of the metal surface can also provide partial power for the stretching process. Contracting and stretching of a satellite large-area antenna array surface can be realized; the metal antenna array surface is curled and contracted in a transmission process and is attached to the storage tube; after the satellite enters the orbit, according to a driving control instruction, an antenna surface required by a working state is formed through semiautonomous stretching; and the technique of the invention has the advantages of high storage ratio, light weight, high stiffness, high reliability, wide adaptability and the like.
Owner:SHANGHAI SATELLITE ENG INST
A method for making a controllable and orderly unfolding solar sail based on shape memory polymer
ActiveCN105480436BLightweight materialLight in massCosmonautic power supply systemsSolar sailEngineering
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.
Owner:HARBIN INST OF TECH
Foldable tent
ActiveCN108798201AHigh storage ratioHigh Storage Ratio Super Large Storage RatioTents/canopiesStructural engineeringHorizontal shear
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.
Owner:CHANGSHA UNIVERSITY OF SCIENCE AND TECHNOLOGY +1
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