CN107768797B - Satellite-borne solid surface deployable antenna - Google Patents
Satellite-borne solid surface deployable antenna Download PDFInfo
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- CN107768797B CN107768797B CN201710973786.9A CN201710973786A CN107768797B CN 107768797 B CN107768797 B CN 107768797B CN 201710973786 A CN201710973786 A CN 201710973786A CN 107768797 B CN107768797 B CN 107768797B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/08—Means for collapsing antennas or parts thereof
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
- H01Q15/161—Collapsible reflectors
- H01Q15/162—Collapsible reflectors composed of a plurality of rigid panels
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Abstract
The invention discloses a satellite-borne fixed surface deployable antenna which comprises a fixed surface reflector, a deployable mechanism and a driving assembly. The extensible mechanism is formed by combining a plurality of synchronous three-rod extensible units and a synchronous two-rod extensible unit array; the fixed surface reflector consists of a plurality of rigid thin plates; the driving assembly comprises a driving motor and an elastic energy storage element. The fixed surface reflector is connected with the deployable mechanism through a universal hinge, and under the action of the driving motor, the fixed surface reflector realizes primary space synchronous deployment through the deployable mechanism and realizes secondary space synchronous deployment under the action of the elastic energy storage element and the compression spring; after the antenna is unfolded, any two adjacent panels in the fixed surface reflector are hinged and locked through the locking mechanism, and the whole antenna is stabilized in a completely unfolded state. The satellite-borne solid surface expandable antenna has the characteristics of large expansion caliber, strong expansion and support rigidity and high molded surface precision; the antenna can also be used in space or on the ground as a reflector or concentrator.
Description
Technical Field
The invention relates to the technical field of satellite antenna structure design, in particular to a satellite-borne fixed surface deployable antenna.
Background
The antenna is used as a wireless communication device and plays a great role in the fields of aerospace, meteorology, communication and military affairs. At present, the satellite-borne antenna is widely applied to various satellite systems, and with the continuous development of the aerospace technology and the continuous expansion of aerospace application, the development of the satellite-borne antenna with large caliber, high precision and light weight becomes a development trend. However, due to the limitation of the effective accommodation space and the carrying capacity of the carrier rocket, the antenna is required to be fixed in a furled state in a carrier payload cabin in the launching stage, after the spacecraft enters the orbit, the ground control center instructs the spacecraft to gradually complete the unfolding process in the space orbit according to the design requirement, and then the spacecraft is locked and kept in a working state, so that the antenna can be unfolded to form a remarkable characteristic of a large-scale satellite-borne antenna, and the comprehensive characteristics of the satellite-borne antenna can be measured from the aspects of the accommodation rate, the profile precision, the profile holding capacity, the unfolding and the supporting rigidity.
Among various types of space-borne antennas, the research on parabolic deployable antennas has been a major issue. Parabolic antennas can be classified into mesh parabolic antennas and solid parabolic antennas according to the form of the reflecting surface. Although the reflecting surface forms are different, in order to seek a higher receiving rate as much as possible, the deployable parabolic antenna generally adopts a structural form similar to an umbrella. The existing antenna generally has the defects of small unfolded caliber, low unfolded precision, poor supporting rigidity, low precision of a reflecting surface, sensitive impact response and the like, directly influences the service life and the working performance of a satellite, and is difficult to meet the requirement of a large satellite-borne antenna system.
The invention patent CN 105896020 a discloses an expandable fixed surface antenna, which is characterized in that the storage rate and the reflecting surface accuracy are high, but the expansion aperture is limited by the structure of the fixed surface antenna, so that the antenna cannot be applied to a large expandable antenna, the support rigidity and the expansion accuracy are poor, and it is difficult to ensure that each panel of the antenna can be expanded smoothly.
The invention patent CN 103872422A proposes an umbrella-shaped deployable antenna system, which has high storage rate, light weight and smaller deployment caliber and is suitable for small deployable antennas; when the unfolding aperture is increased, the unfolding process of the antenna reflector has greater difficulty in actual operation; under the severe high and low temperature environment in space, the profile of the antenna reflector is easy to change, the stability of a profile system is not high, and the antenna reflector does not have higher profile precision and profile holding capacity, so that the performance of the antenna reflector is influenced.
Disclosure of Invention
In order to avoid the defects of the prior art, the invention provides a satellite-borne solid surface deployable antenna; the supporting and unfolding mechanism of the antenna is arranged on the back of the antenna, can realize secondary space unfolding, and has the characteristics of large unfolding caliber, strong unfolding supporting rigidity, high profile precision and strong profile holding capacity.
The invention solves the technical problem by adopting the technical scheme that the device comprises a fixed surface reflector, an extensible mechanism, a driving assembly and a bottom panel, wherein the extensible mechanism and the fixed surface reflector are formed by combining basic unit arrays; in the surface fixing reflector, 12 fan-shaped panels and 12 annular panels are respectively arranged, 6 upper panels and 6 lower panels are respectively arranged, a first fan-shaped panel, a second fan-shaped panel, a first annular panel, a second annular panel and an upper panel and a lower panel form a surface fixing reflector basic unit, a plurality of basic units are sequentially adjacent and distributed around a bottom panel to form the surface fixing reflector, wherein the surface fixing reflector is composed of a plurality of rigid thin plates, rectangular planes are arranged at the hinged positions of the rigid thin plates, and the rectangular planes at the hinged positions are positioned in the same plane; the bottom panel is hinged with the lower panel through a hinge, the hinge is arranged on the inner surface of the panel, one side of the lower panel is hinged with the first sector panel through the hinge, the other side of the lower panel is hinged with the second sector panel through the hinge, the hinge is arranged on the inner surface of the panel, the first sector panel and the second sector panel are respectively hinged with the sector panels in the adjacent basic units of the fixed surface reflector through elastic energy storage elements, the elastic energy storage elements are arranged on the outer surface of the panel, the lower panel is hinged with the upper panel through the elastic energy storage elements, the elastic energy storage elements are arranged on the outer surface of the panel, one side of the upper panel is hinged with the first annular panel through the elastic energy storage elements, the other side of the upper panel is hinged with the second annular; two adjacent panels in the fixed surface reflector are locked by a locking mechanism;
the deployable mechanism is formed by combining a plurality of synchronous three-rod deployable units, a plurality of synchronous two-rod deployable units, a plurality of connecting rods and a plurality of supporting rod arrays, the synchronous three-rod extensible unit comprises a first bevel gear pair, a second bevel gear pair, a third bevel gear pair, a large graphite bearing, a first T-shaped rotating shaft, a second T-shaped rotating shaft, a third T-shaped rotating shaft and a connecting node main body, wherein the first bevel gear pair, the second bevel gear pair and the third bevel gear pair respectively consist of two bevel gears with the same structure, the bevel gears are meshed with each other, the crossed axes angle is 60 degrees, the first bevel gear pair and the second bevel gear pair, the second bevel gear pair and the third bevel gear pair, the third bevel gear pair and the first bevel gear pair are respectively fixedly connected through the first T-shaped rotating shaft, the second T-shaped rotating shaft and the third T-shaped rotating shaft, the large graphite bearings are arranged between the two ends of the T-shaped rotating shaft and the connecting node main body; the three pairs of bevel gear pairs are distributed in the same plane in a regular triangle mode according to the axis center, the other end of each T-shaped rotating shaft is provided with threads, and the joint of each T-shaped rotating shaft is connected with a corresponding connecting rod or a corresponding supporting rod respectively;
the synchronous two-rod deployable unit comprises an incomplete gear pair, a small graphite bearing, a connecting plate, a first synchronous rod joint and a second synchronous rod joint, wherein the first synchronous rod joint and the second synchronous rod joint are symmetrically arranged in the connecting plate through a rotating shaft and the small graphite bearing, the incomplete gear pair is positioned on the outer side surface of the connecting plate and coaxially arranged with the first synchronous rod joint and the second synchronous rod joint, the synchronous rod joints are provided with threads, each synchronous two-rod deployable unit is respectively connected with two synchronous three-rod deployable units through connecting rods, the first synchronous rod joint is in threaded connection with the second connecting rod of one synchronous three-rod deployable unit, the second synchronous rod joint is in threaded connection with the first connecting rod of the other adjacent synchronous three-rod deployable unit, a limit baffle is arranged on the side end surface of the connecting plate, when the synchronous two-rod deployable units are deployed, the first synchronous rod joint and the second synchronous rod joint are positioned on the limit baffle, and the included angle between the first synchronous rod joint and the second synchronous rod joint is 180 degrees; the supporting rod and the connecting rod are hollow cylindrical rods, threads are arranged at two ends of the supporting rod and the connecting rod, the connecting rod is used for connecting the synchronous three-rod extensible unit and the synchronous two-rod extensible unit, and the supporting rod is used for connecting the synchronous three-rod extensible unit and the lower panel to realize the connection of the extensible mechanism and the fixed surface reflector;
the connecting joint main body comprises V-shaped plates, a joint base, a lower baffle and an upper baffle, the V-shaped plates are formed by connecting a plurality of rectangular plates with the same structure in pairs, an included angle theta between every two rectangular plates is 120 degrees, the rectangular plates are respectively provided with a shaft hole, the centers of the shaft holes are positioned in the same plane, the V-shaped plates are fixed on the joint base, the lower baffle and the upper baffle are arranged on the joint base between every two pairs of V-shaped plates, and the lower baffle and the upper baffle are used for limiting the rotating angle of the T-shaped rotating shaft to be 0-90 degrees;
the back of the lower panel is provided with a slide rail along the axial direction, a slide block of the universal hinge is arranged on the slide rail, and slide block baffles are arranged at two ends of the slide rail and used for limiting the movement of the slide block; the universal hinge comprises a universal joint and a sliding block, the universal joint is positioned below the sliding block and is connected through a rotating shaft, and the universal joint is in threaded connection with the supporting rod;
the driving assembly comprises a driving motor and an elastic energy storage element, and the driving motor is connected with the synchronous three-rod extensible unit; the elastic energy storage element comprises an elastic flexible part, a rotating part, a pressing plate, a pin shaft, a spring and a locking pin, wherein the upper surface of the pressing plate is a plane, bosses are arranged at the four corners of the lower surface of the pressing plate and the middle parts of the side edges of the pressing plate, and the pressing plate is fixedly connected with the rotating part through screws to form a cavity for mounting the elastic flexible part; the rotating piece is two parts with the same structure, a shaft hole is formed in the middle of a convex block of the rotating piece, locking holes are formed in the position close to the shaft hole according to the unfolding angle, the two rotating pieces are installed through pin shafts, the locking holes in the same positions of the contact surfaces of the two rotating pieces are blind holes with different depths and the same diameters, the deep holes are used for installing springs and locking pins, and the shallow holes are used for wedging the locking pins when locking.
And the hinged part of any two adjacent panels in the fixed surface reflector is provided with a locking mechanism.
The rigid thin plate formed by the fixed surface reflector is made of carbon fiber reinforced composite materials.
The universal hinge, the T-shaped rotating shaft, the connecting rod, the supporting rod, the locking mechanism and the connecting node main body are all formed by processing titanium alloy materials.
Advantageous effects
Compared with the prior art, the satellite-borne solid surface deployable antenna of the invention has the advantages that:
1. the synchronous three-rod extensible unit of the invention provides a three-rod extensible unit node capable of ensuring synchronous motion of three rod pieces based on the closed transmission principle of bevel gears, and a regular hexagonal unit synchronous multi-rod symmetrical extensible mechanism is formed by combining a double-gear transmission planar synchronous two-rod extensible unit node. The unfolding mode belongs to multi-node synchronous unfolding, the rod pieces connected with the rotating shafts move accurately and synchronously, and then the synchronous three-rod extensible units stably pass through a motion singular point in a geometric configuration; the advantages of single-degree-of-freedom movability, no motion singular point, high storage rate and high unfolding precision of the synchronous multi-rod unfolding mechanism are fully exerted, the synchronous multi-rod unfolding mechanism can be applied to novel symmetrical unfolding mechanisms, and the synchronous multi-rod unfolding mechanism is particularly suitable for a foldable over-constraint system formed by a revolute pair and a scissor hinge unit.
2. According to the invention, a large-span three-dimensional closed-loop expandable system can be formed according to the combination mode of the synchronous expandable units of the expandable mechanism, namely, the synchronous multi-rod array symmetrical expandable system based on the regular hexagon units has wide application prospect in the engineering fields of large expandable antennas, solar sailboards, retractable roof structures and the like.
3. When the panel of the solid reflector is partitioned, the structure is optimally designed, so that the interference of the antenna in the unfolding and folding processes is avoided; under the action of an electric signal and a driving assembly, the solid reflector is unfolded from an initial folded state through the extensible mechanism and the elastic energy storage element, after the fixed reflector is unfolded, any two adjacent panels in the fixed reflector are hinged and locked through the locking mechanism, meanwhile, the extensible mechanism is also locked, and the whole antenna is stabilized in a completely unfolded state.
4. The support and the deployable mechanism of the satellite-borne solid-surface deployable antenna are arranged on the back surface of the antenna; the extensible mechanism can not only realize the operation and the extension of the extensible part, but also can not influence the effective area of the reflecting surface, and greatly improves the reflecting effect of the antenna reflector.
5. The deployable antenna has the characteristics of large deployed caliber, high profile precision, strong profile holding capacity, high stability, high storage rate and high deployment and support rigidity, and can be used as a reflector or a concentrator in space or on the ground.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings and embodiments.
Fig. 1 is a schematic view of a deployable antenna structure of a satellite-borne solid plane according to the present invention.
Fig. 2 is a schematic view of a foldable antenna of the satellite-borne fixing surface according to the present invention.
Fig. 3 is a bottom view of the deployable antenna of the satellite mount surface of the present invention in an expanded state.
Fig. 4 is a schematic structural view of the deployable antenna on the satellite-borne mounting surface according to the present invention.
Fig. 5 is a schematic structural view of the foldable mechanism of the present invention in a folded state.
Fig. 6 is a schematic structural diagram of a connection node according to the present invention.
FIG. 7 is a schematic view of a T-shaped shaft according to the present invention.
Fig. 8 is a schematic view of a connecting rod of the present invention.
Fig. 9 is a schematic structural diagram of a node base according to the present invention.
FIG. 10 is a schematic view of a synchronization rod joint of the present invention.
Fig. 11 is a schematic view of a synchronous two-rod deployable unit according to the present invention.
FIG. 12 is a schematic view of the installation positions of the lower panel, the slider and the slide rail according to the present invention.
FIG. 13 is a schematic view of the universal hinge structure of the present invention.
Fig. 14 is a schematic structural diagram of an elastic energy storage element according to the present invention.
FIG. 15 is a schematic view of a rotating member according to the present invention.
Fig. 16 is a schematic view of the deployment process of the deployable mechanism of the present invention.
Fig. 17 is a schematic view of the deployable mechanism of the present invention in a deployed state.
FIG. 18 is an expanded schematic view of the regular hexagonal cell-based synchronous multi-rod array deployable system of the present invention.
In the figure:
1. the synchronous three-rod extensible unit 2, the synchronous two-rod extensible unit 3, the bottom panel 4, the lower panel 5, the upper panel 6, the first sector panel 6a, the second sector panel 6b, the third sector panel 7, the first annular panel 7a, the second annular panel 7b, the third annular panel 8, the universal hinge 9, the elastic energy storage element 10, the hinge 11, the locking mechanism 12, the first bevel gear pair 12a, the second bevel gear pair 12b, the third bevel gear pair 13, the large graphite bearing 14, the first T-shaped rotating shaft 14a, the second T-shaped rotating shaft 14b, the third T-shaped rotating shaft 15, the connecting node main body 16, the first connecting rod 16a, the second connecting rod 16b, the third connecting rod 17, the supporting rod 18, the incomplete gear pair 19, the small graphite bearing 20, the connecting plate 21, the sliding rail 22, the sliding block baffle 23, the universal joint 24, the sliding block 25, the elastic flexible pressing plate 26, the rotating piece 28, the spring 30, the incomplete gear pair 16, the sliding block 19, the sliding block Locking pin 31, V-shaped plate 32, node base 33, lower baffle plate 34, deployable mechanism 35, fixed surface reflector 36, driving motor 37, upper baffle plate 38, first synchronizing rod joint 38a, second synchronizing rod joint 39 and limit baffle plate
Detailed Description
The embodiment is a satellite-borne solid-surface deployable antenna.
Referring to fig. 1 to 15, in the present embodiment, the satellite-borne fixed surface deployable antenna has a deployment aperture of 12 m; the device comprises a fixed surface reflector 35 consisting of a plurality of rigid thin plates, a deployable mechanism 34 for supporting and controlling the switching of the unfolding and folding states of the fixed surface antenna and a driving component for a power device. The driving assembly comprises a driving motor 36 and an elastic energy storage element 9; the fixed surface reflector 35 is connected with the deployable mechanism 34 through a universal hinge 8, and the driving motor 36 is connected with the synchronous three-rod deployable unit 1; under the action of an electric signal and a driving assembly, the fixed surface reflector 35 is unfolded from an initial folded state through the extensible mechanism 34 and the elastic energy storage element 9, and the whole antenna is stabilized in a completely unfolded state under the action of the locking mechanism 11.
In this embodiment, the fixed surface reflector 35 is a parabolic antenna panel composed of 37 rigid sheets in sheet form, and is symmetrically installed. The fixed surface reflector 35 comprises a hexagonal bottom panel 3, 6 lower panels 4, 6 upper panels 5, 12 sector panels and 12 annular panels, wherein the sector panels comprise a first sector panel 6, a second sector panel 6a and a third sector panel 6b, and the annular panels comprise a first annular panel 7, a second annular panel 7a and a third annular panel 7 b; at the hinge joint of each sheet-shaped rigid thin plate, the paraboloid is filled into a plane under the condition of not influencing the profile precision, so that the hinge is conveniently installed at the hinge joint plane, the panels are hinged, and the interference of the antenna panels in the unfolding and folding processes is avoided. A rectangular plane is arranged at the hinge joint of each panel, and the rectangular planes at the hinge joints are positioned in the same plane; the bottom panel 3 is hinged with the lower panel 4 through a hinge 10, and the hinge 10 is arranged on the inner surface of the panel and is arranged at three positions along the hinge axis. One side of the lower panel 4 is hinged with the first sector panel 6 through a hinge 10, the other side of the lower panel 4 is hinged with the second sector panel 6a through a hinge 10, and the hinge 10 is arranged on the inner surface of the panel and is arranged at three positions along the hinge axis. The first sector-shaped panel 6 and the third sector-shaped panel 6b are hinged through an elastic energy storage element 9, and the elastic energy storage element 9 is installed on the outer surface of the panels and is arranged at two positions along the hinge axis. The lower panel 4 is hinged with the upper panel 5 through an elastic energy storage element 9, and the elastic energy storage element 9 is arranged on the outer surface of the panel and is arranged at two positions along the hinge axis. One side of the upper panel 5 is hinged with the first annular panel 7 through an elastic energy storage element 9, the other side of the upper panel is hinged with the second annular panel 7a through the elastic energy storage element 9, and the elastic energy storage element 9 is arranged on the inner surface of the panel and is arranged at two positions along the hinge axis. The locking mechanism 11 is arranged at the hinged position of any two adjacent panels in the fixed surface reflector 35; in the folded state and the unfolded process of the antenna, the first annular panel 7 and the third annular panel 7b and the first sector panel 6 and the first annular panel 7 are separated, and after the antenna is unfolded, any two adjacent panels in the fixed surface reflector 35 are hinged and locked through the locking mechanism 11.
The fixed surface reflector 35 is formed by combining and connecting panel unit arrays in different shapes. Each panel unit is hinged along a straight line in the folding and unfolding processes, and when the parabolic antenna panel is partitioned, the partition surfaces among the other panel units are all planes except the partition surfaces between the sector panel and the annular panel.
In this embodiment, the deployable mechanism 34 is a three-dimensional closed-loop regular hexagonal unit synchronous multi-rod symmetric deployable mechanism formed by combining 6 synchronous three-rod deployable units 1, 6 synchronous two-rod deployable units 2, 12 connecting rods and 6 supporting rods 17 in an array; the synchronous three-rod extensible unit 1 comprises a first bevel gear pair 12, a second bevel gear pair 12a, a third bevel gear pair 12b, a large graphite bearing 13, a first T-shaped rotating shaft 14, a second T-shaped rotating shaft 14a, a third T-shaped rotating shaft 14b and a connecting node main body 15, wherein the first connecting rod 16, the second connecting rod 16a and the third connecting rod 16b are meshed with one another; the mutually meshed bevel gear pair comprises two bevel gears with the same structure, and the shaft intersection angle of the bevel gears is 60 degrees. First bevel gear pair 12 and second bevel gear pair 12a, second bevel gear pair 12a and third bevel gear pair 12b, third bevel gear pair 12b and first bevel gear pair 12 are respectively through first T type pivot 14, second T type pivot 14a, third T type pivot 14b fixed connection, and install on connected node main part 15, have big graphite bearing between T type pivot both ends and connected node main part 15. The three pairs of bevel gear pairs are distributed in the same plane in a regular triangle shape according to the axis center.
During assembly, when the synchronous three-rod extensible unit 1 is completely extended, the first T-shaped rotating shaft 14, the second T-shaped rotating shaft 14a and the third T-shaped rotating shaft 14b are located in the same plane; the joint of the T-shaped rotating shaft is provided with threads, the joint of the first T-shaped rotating shaft 14 is connected with the first connecting rod 16, the joint of the second T-shaped rotating shaft 14a is connected with the second connecting rod 16a, and the joint of the third T-shaped rotating shaft 14b is connected with the supporting rod 17. The synchronous two-rod deployable unit 2 comprises an incomplete gear pair 18, a small graphite bearing 19, a connecting plate 20, a first synchronous rod joint 38, a second synchronous rod joint 38a and a limit baffle 39, wherein the first synchronous rod joint 38 and the second synchronous rod joint 38a are symmetrically installed in the connecting plate 20 through a rotating shaft and the small graphite bearing 19, the incomplete gear pair 18 is located on the outer side of the connecting plate 20 and coaxially installed with the first synchronous rod joint 38 and the second synchronous rod joint 38a, the synchronous rod joints are provided with threads, the first synchronous rod joint 38 is in threaded connection with a second connecting rod 16a, and the second synchronous rod joint 38a is in threaded connection with a third connecting rod 16b. The end face of the side of the connecting plate 20 is provided with a limit baffle 39, when the synchronous two-rod deployable unit 2 is deployed, the first synchronous rod joint 38 and the second synchronous rod joint 38a are positioned on the limit baffle 39, and an included angle between the first synchronous rod joint 38 and the second synchronous rod joint 38a is 180 degrees. The supporting rod 17 and the connecting rod are hollow cylindrical rods, threads are arranged at two ends of the supporting rod 17 and the connecting rod, the connecting rod is used for connecting the synchronous three-rod extensible unit 1 and the synchronous two-rod extensible unit 2, the supporting rod 17 is used for connecting the synchronous three-rod extensible unit 1 with the lower panel 4, and the connection of the extensible mechanism 34 and the solid reflector 35 is achieved.
In order to ensure that the rotation angle of the second connecting rod 16a and the third connecting rod 16b is 0-90 degrees, and the incomplete gear pair 18 is completely meshed in the rotation process, 1/3 of which the incomplete gear is a circular gear is taken in the embodiment. The synchronous three-rod extensible unit 1, the synchronous two-rod extensible unit 2, the first connecting rod 16, the second connecting rod 16a and the supporting rod 17 are connected and combined into a basic unit of the extensible mechanism 34.
The connecting joint main body 15 comprises a V-shaped plate 31, a joint base 32, a lower baffle 33 and an upper baffle 37, the V-shaped plate 31 is formed by connecting a plurality of rectangular plates with the same structure in pairs, the included angle theta between every two rectangular plates is 120 degrees, the rectangular plates are respectively provided with shaft holes, the shaft holes are positioned in the same plane, and the shaft holes are used for installing the large graphite bearing 13; the V-shaped plates are fixed on the node base 32, and a lower baffle 33 and an upper baffle 37 are arranged on the node base 32 between every two pairs of V-shaped plates and used for limiting the rotation angle of the T-shaped rotating shaft to be 0-90 degrees.
The unfolding mode of the unfolding mechanism 34 belongs to multi-node synchronous unfolding, and the movable degree of freedom is 1, so that only one power source is needed for driving. The regular hexagon unit synchronous multi-rod symmetrical deployable mechanism has larger coverage area in a fully deployed state, and has higher rigidity and storage rate; under the driving action of the driving motor 36, the connecting rods and the supporting rods 17 are synchronously unfolded along with the synchronous three-rod extensible unit 1 and the synchronous two-rod extensible unit 2 by the extensible mechanism 34, and the device can stably move from a compact round bundle folded state to a completely unfolded state, and the process is reversible. In the unfolding process, the synchronous nodes at the two ends of the connecting rod unit are respectively positioned on the two motion planes and are parallel to each other, all the synchronous nodes are synchronously unfolded along the radial direction of the regular hexagon, and all the synchronous nodes are positioned on the same plane until the synchronous nodes are completely unfolded.
The back of the lower panel 4 is provided with a slide rail 21 along the axial direction, a slide block 24 of the universal hinge is arranged on the slide rail, and two ends of the slide rail 21 are provided with slide block baffles 22 for limiting the movement of the slide block 24. The universal hinge 8 comprises a universal joint 23 and a sliding block 24, the universal joint 23 is positioned below the sliding block 24 and is connected with the sliding block through a rotating shaft, and the universal joint 23 is in threaded connection with the supporting rod 17; the universal hinge 8 is used for connecting the slide rail 21 and the support rod 17, so that the lower panel 4 and the support rod 17 are prevented from interfering in the movement process; the universal hinge 8 is driven by the deployable mechanism 34, and the lower panel 4 is deployed under the traction of the universal hinge 8, so that the first-time space synchronous deployment of the fixed-surface reflector 35 is realized.
In this embodiment, the driving assembly includes a driving motor 36 and an elastic energy storage element 9, and the driving motor 36 is connected to the synchronous three-rod deployable unit 1. The elastic energy storage element 9 comprises an elastic flexible part 25, a rotating part 26, a pressing plate 27, a pin shaft 28, a spring 29 and a locking pin 30, wherein the upper surface of the pressing plate 27 is a plane, bosses are respectively arranged at the four corners and the middle of the side edge of the lower surface of the pressing plate 27, the pressing plate 27 and the rotating part 26 are fixedly connected through screws to form a cavity for mounting the elastic flexible part 25, and the elastic flexible part 25 slides in the cavity in a micro-gap manner. The rotor 26 is two parts with the same structure, the rotor 26 has a shaft hole in the middle of its boss and is mounted by a pin 28, and the two rotors 26 have locking holes at the vicinity of the shaft hole according to the spreading angle. The same positions of the contact surfaces of the two rotating parts 26 are respectively provided with blind holes with the same depth and different diameters, the deep holes are used for installing the spring 29 and the locking pin 30, and the shallow holes are used for wedging the locking pin 30 during locking. When the included angle between the two rotating members 26 is 180 °, the elastic flexible members are all located in the cavity formed by the pressing plate 27 and the rotating members 26, and the elastic flexible members are not elastically deformed. When torque is applied to the elastic energy storage element 9, the included angle between the two rotating parts 26 is changed, at the moment, one part of the elastic flexible part 25 is pulled out from the cavity, the elastic flexible part 25 of the pulled-out part participates in working deformation, and the elastic flexible part in the cavity does not elastically deform; when the external force is removed, the rotating member returns to the initial state under the restoring elastic force of the elastic flexible member 25. When the antenna is in a folded state and is unfolded for the first time, the elastic flexible part 25 of the elastic energy storage element 9 is in a working deformation state; the antenna panel is controlled by an electric signal, and the second time of space expansion is realized through the restoring elastic force action of the elastic energy storage element 9; after the antenna panel is unfolded, the antenna panel is hinged and locked through the elastic energy storage element 9.
The elastic energy storage element 9 is used as a power source for the second time space expansion of a part of the antenna panel, and is also a constant-torque flexible hinge with a locking function, so that the elastic energy storage element plays a dual role of driving and hinging; different driving torques can be realized by changing the requirements of the material, the length, the width and the thickness of the elastic flexible piece 25.
In this embodiment, the regular hexagon unit synchronous multi-rod symmetrical deployable mechanism 34 is composed of a synchronous n1Lever extensible mechanism and synchronization n2The rod-extensible mechanisms are combined in an array, wherein n1＝2、n 23. For n1、n2The description is as follows:
according to the coordination condition of the geometric displacement of the structure in the completely folded and unfolded states, the following conditions can be known:
in the formula, the left side of the inequality is n1The included angle formed by adjacent units at the joint of the rod and the right side of the inequality is positive n2The internal angle of the polygon. Due to the integer n1≥2、n2Not less than 3, and considering the symmetry requirement at the node, solving the limited feasible solutions satisfying the formula (1) as follows:
considering that the antenna panel needs a multi-node six-rod mechanism to be unfolded synchronously, n is taken out in the embodiment1＝2、n2And 3, namely, a regular hexagon unit synchronous multi-rod symmetrical deployable mechanism formed by combining the synchronous three-rod deployable unit 1 and the synchronous two-rod deployable unit 2 in an array manner is adopted.
In this embodiment, the fixed-surface reflector 35 is a rigid thin plate and made of a carbon fiber reinforced composite material, so that the mass of the antenna can be reduced. The universal hinge 8, the hinge 10, the locking mechanism 11, the T-shaped rotating shaft, the connecting node main body 15, the connecting rod, the supporting rod 17 and the connecting plate 20 are all formed by titanium alloy processing, and therefore the quality of the antenna is reduced on the premise that the strength of parts is guaranteed.
The deployable mechanism 34 and the fixed surface reflector 35 in this embodiment are formed by combining basic unit arrays; the first sector-shaped panel 6, the second sector-shaped panel 6a, and the third sector-shaped panel 6b are members having the same structure, the first annular panel 7, the second annular panel 7a, and the third annular panel 7b are members having the same structure, the first bevel gear pair 12, the second bevel gear pair 12a, and the third bevel gear pair 12b are members having the same structure, the first T-shaped rotating shaft 14, the second T-shaped rotating shaft 14a, and the third T-shaped rotating shaft 14b are members having the same structure, the first connecting rod 16 and the second connecting rod 16a are members having the same structure, the first synchronizing rod joint 38 and the second synchronizing rod joint 38a are members having the same structure, and the mounting positions and the connection relationships of the respective members are different.
In the normal unfolding of the antenna, the driving mode is that the satellite-borne surface-fixing deployable antenna unlocks the locking rope through an electric signal, and under the action of the driving motor 36, the lower panel 4 of the surface-fixing reflector 35 is unfolded along with the deployable mechanism 34 through the universal hinge 8; meanwhile, the sector panel is unfolded under the action of the elastic energy storage element 9 and the hinge 10; and finishing the first time of space synchronous unfolding of the antenna. The bottom plate 3 and the lower plate 4, the lower plate 4 and the first sector-shaped panel 6, the lower plate 4 and the second sector-shaped panel 6a, and the first sector-shaped panel 6 and the third sector-shaped panel 6b are locked by the locking mechanism 11, and the deployable mechanism 34 is locked. After the first unfolding is finished, the elastic energy storage element 9 is unlocked; the upper panel 5 and the annular panel of the fixed surface reflector 35 realize second space expansion under the action of the elastic energy storage element 9 and the compression spring; after the antenna is unfolded, any two adjacent panels in the fixed surface reflector 35 are hinged and locked through the locking mechanism 11, and the whole antenna is stabilized in a completely unfolded state.
The present embodiment can form a large-span three-dimensional closed-loop expandable system according to the synchronous expandable unit combination manner of the expandable mechanism 34. Fig. 18 is a fully expanded state of the regular-hexagon-cell-based synchronous multi-bar array symmetric expandable system, which is derived from a plurality of regular-hexagon-cell synchronous multi-bar symmetric expandable mechanisms 34 along a plane direction of nodes, and has a more significant space group symmetry; the movable freedom degree is always 1, and the whole extensible system only needs one power source to be extended, and is irrelevant to the number of module units. The synchronous multi-rod array symmetrical expandable system based on the regular hexagon units meets the requirements of small occupied space in a folded state, large coverage area in an expanded state, no motion singular point, synchronous folding-expansion of single degree of freedom and high expansion precision, and has wide application prospect in the field of large expandable antennas, solar sailboards and retractable roof structure engineering.
Claims (4)
1. A satellite-borne fixed surface deployable antenna is characterized by comprising a fixed surface reflector, a deployable mechanism, a driving assembly and a bottom panel, wherein the deployable mechanism and the fixed surface reflector are formed by combining basic unit arrays; in the surface fixing reflector, 12 fan-shaped panels and 12 annular panels are respectively arranged, 6 upper panels and 6 lower panels are respectively arranged, a first fan-shaped panel, a second fan-shaped panel, a first annular panel, a second annular panel and an upper panel and a lower panel form a surface fixing reflector basic unit, a plurality of basic units are sequentially adjacent and distributed around a bottom panel to form the surface fixing reflector, wherein the surface fixing reflector is composed of a plurality of rigid thin plates, rectangular planes are arranged at the hinged positions of the rigid thin plates, and the rectangular planes at the hinged positions are positioned in the same plane; the bottom panel is hinged with the lower panel through a hinge, the hinge is arranged on the inner surface of the panel, one side of the lower panel is hinged with the first sector panel through the hinge, the other side of the lower panel is hinged with the second sector panel through the hinge, the hinge is arranged on the inner surface of the panel, the first sector panel and the second sector panel are respectively hinged with the sector panels in the adjacent basic units of the fixed surface reflector through elastic energy storage elements, the elastic energy storage elements are arranged on the outer surface of the panel, the lower panel is hinged with the upper panel through the elastic energy storage elements, the elastic energy storage elements are arranged on the outer surface of the panel, one side of the upper panel is hinged with the first annular panel through the elastic energy storage elements, the other side of the upper panel is hinged with the second annular; two adjacent panels in the fixed surface reflector are locked by a locking mechanism;
the deployable mechanism is formed by combining a plurality of synchronous three-rod deployable units, a plurality of synchronous two-rod deployable units, a plurality of connecting rods and a plurality of supporting rod arrays, the synchronous three-rod extensible unit comprises a first bevel gear pair, a second bevel gear pair, a third bevel gear pair, a large graphite bearing, a first T-shaped rotating shaft, a second T-shaped rotating shaft, a third T-shaped rotating shaft and a connecting node main body, wherein the first bevel gear pair, the second bevel gear pair and the third bevel gear pair respectively consist of two bevel gears with the same structure, the bevel gears are meshed with each other, the crossed axes angle is 60 degrees, the first bevel gear pair and the second bevel gear pair, the second bevel gear pair and the third bevel gear pair, the third bevel gear pair and the first bevel gear pair are respectively fixedly connected through the first T-shaped rotating shaft, the second T-shaped rotating shaft and the third T-shaped rotating shaft, the large graphite bearings are arranged between the two ends of the T-shaped rotating shaft and the connecting node main body; the three pairs of bevel gear pairs are distributed in the same plane in a regular triangle mode according to the axis center, the other end of each T-shaped rotating shaft is provided with threads, and the joint of each T-shaped rotating shaft is connected with a corresponding connecting rod or a corresponding supporting rod respectively;
the synchronous two-rod deployable unit comprises an incomplete gear pair, a small graphite bearing, a connecting plate, a first synchronous rod joint and a second synchronous rod joint, wherein the first synchronous rod joint and the second synchronous rod joint are symmetrically arranged in the connecting plate through a rotating shaft and the small graphite bearing, the incomplete gear pair is positioned on the outer side surface of the connecting plate and coaxially arranged with the first synchronous rod joint and the second synchronous rod joint, the synchronous rod joints are provided with threads, each synchronous two-rod deployable unit is respectively connected with two synchronous three-rod deployable units through connecting rods, the first synchronous rod joint is in threaded connection with the second connecting rod of one synchronous three-rod deployable unit, the second synchronous rod joint is in threaded connection with the first connecting rod of the other adjacent synchronous three-rod deployable unit, a limit baffle is arranged on the side end surface of the connecting plate, when the synchronous two-rod deployable units are deployed, the first synchronous rod joint and the second synchronous rod joint are positioned on the limit baffle, and the included angle between the first synchronous rod joint and the second synchronous rod joint is 180 degrees; the supporting rod and the connecting rod are hollow cylindrical rods, threads are arranged at two ends of the supporting rod and the connecting rod, the connecting rod is used for connecting the synchronous three-rod extensible unit and the synchronous two-rod extensible unit, and the supporting rod is used for connecting the synchronous three-rod extensible unit and the lower panel to realize the connection of the extensible mechanism and the fixed surface reflector;
the connecting joint main body comprises V-shaped plates, a joint base, a lower baffle and an upper baffle, the V-shaped plates are formed by connecting a plurality of rectangular plates with the same structure in pairs, an included angle theta between every two rectangular plates is 120 degrees, the rectangular plates are respectively provided with a shaft hole, the centers of the shaft holes are positioned in the same plane, the V-shaped plates are fixed on the joint base, the lower baffle and the upper baffle are arranged on the joint base between every two pairs of V-shaped plates, and the lower baffle and the upper baffle are used for limiting the rotating angle of the T-shaped rotating shaft to be 0-90 degrees;
the back of the lower panel is provided with a slide rail along the axial direction, a slide block of the universal hinge is arranged on the slide rail, and slide block baffles are arranged at two ends of the slide rail and used for limiting the movement of the slide block; the universal hinge comprises a universal joint and a sliding block, the universal joint is positioned below the sliding block and is connected through a rotating shaft, and the universal joint is in threaded connection with the supporting rod;
the driving assembly comprises a driving motor and an elastic energy storage element, and the driving motor is connected with the synchronous three-rod extensible unit; the elastic energy storage element comprises an elastic flexible part, a rotating part, a pressing plate, a pin shaft, a spring and a locking pin, wherein the upper surface of the pressing plate is a plane, bosses are arranged at the four corners of the lower surface of the pressing plate and the middle parts of the side edges of the pressing plate, and the pressing plate is fixedly connected with the rotating part through screws to form a cavity for mounting the elastic flexible part; the rotating piece is two parts with the same structure, a shaft hole is formed in the middle of a convex block of the rotating piece, locking holes are formed in the position close to the shaft hole according to the unfolding angle, the two rotating pieces are installed through pin shafts, the locking holes in the same positions of the contact surfaces of the two rotating pieces are blind holes with different depths and the same diameters, the deep holes are used for installing springs and locking pins, and the shallow holes are used for wedging the locking pins when locking.
2. The space-borne solid-surface deployable antenna according to claim 1, wherein a locking mechanism is arranged at the hinged joint of any two adjacent panels in the solid-surface reflector.
3. The spaceborne solid-surface deployable antenna according to claim 1, wherein the rigid sheet composed of the solid-surface reflector is made of carbon fiber reinforced composite material.
4. The space-borne solid surface deployable antenna according to claim 1, wherein the universal hinge, the T-shaped rotating shaft, the connecting rod, the supporting rod, the locking mechanism and the connecting node main body are all formed by processing titanium alloy materials.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109586000B (en) * | 2018-11-23 | 2020-07-14 | 哈尔滨工程大学 | Central-driven annular tensioning integral expandable structure |
| CN109659701B (en) * | 2018-12-17 | 2021-07-30 | 西北工业大学 | Truss type synchronous deployable antenna |
| CN109742504B (en) * | 2019-01-28 | 2020-10-13 | 中国电子科技集团公司第三十八研究所 | Radar antenna array face unfolding and folding mechanism |
| US11942687B2 (en) * | 2019-02-25 | 2024-03-26 | Eagle Technology, Llc | Deployable reflectors |
| CN110444901B (en) * | 2019-08-23 | 2021-04-09 | 广东曼克维通信科技有限公司 | Reflector antenna |
| CN112490616B (en) * | 2020-11-06 | 2022-11-04 | 东南大学 | Novel solid surface expandable antenna structure |
| CN112407335B (en) * | 2020-12-10 | 2022-06-03 | 长春工业大学 | Extensible mechanism based on integral tensioning structure |
| CN114430100B (en) * | 2022-02-15 | 2023-10-13 | 长沙天仪空间科技研究院有限公司 | Satellite-borne antenna unfolding control system |
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