CN113675615A - Aerospace folded antenna reflector and satellite system provided with same - Google Patents
Aerospace folded antenna reflector and satellite system provided with same Download PDFInfo
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- CN113675615A CN113675615A CN202110982802.7A CN202110982802A CN113675615A CN 113675615 A CN113675615 A CN 113675615A CN 202110982802 A CN202110982802 A CN 202110982802A CN 113675615 A CN113675615 A CN 113675615A
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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
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
Abstract
The invention belongs to the technical field of space navigation, and particularly provides an aerospace folding and unfolding antenna reflector and a satellite system provided with the same. The aerospace folding and unfolding antenna reflector and the satellite system provided with the same have the advantages of high storage rate, high unfolding rigidity, good stability, high shape surface precision and the like.
Description
Technical Field
The invention belongs to the technical field of space navigation space, and particularly provides an aerospace folding and unfolding antenna reflector and a satellite system with the reflector.
Background
The space navigation folding antenna reflector is an important component of a satellite system, and is important space navigation equipment which is essential for people to carry out communication and scientific research such as satellite communication, deep space exploration, space science, radio astronomy and the like. The folded and unfolded antenna reflector has the folding and unfolding functions, and when the rocket is launched, the folded reflector is arranged on the side surface of the satellite system; when the satellite enters a preset orbit, the folded antenna reflector executes a series of operations such as unlocking, unfolding, locking and the like according to the instruction requirement, and finally starts to work. Since such reflectors have a large storage ratio, they are widely used in space vehicles such as satellite systems, space vehicles, and space stations. With the continuous development of aerospace technology, the structure and function of an aerospace vehicle are more and more complex and diversified, and thus urgent needs are brought to the folding and unfolding antenna reflector with the characteristics of large caliber, high precision and light weight. The folding and unfolding antenna reflector can be divided into three types, namely a solid surface type, an inflatable type and a net surface type according to the structural form of a working surface, wherein the net surface type folding and unfolding antenna reflector is most widely applied, the structural composition of the folding and unfolding antenna reflector is that a flexible metal reflecting net surface structure is usually laid on a rigid supporting structure with a folding and unfolding function, and the supporting structure plays roles of unfolding, supporting, shape keeping and the like on the net surface. The existing net surface type folding and unfolding antenna reflector represented by an annular truss type has the advantage that the structural mass is not multiplied along with the increase of the aperture of an antenna, but the structure of the reflector has the problems of poor stability, insufficient rigidity, difficult guarantee of shape surface precision and the like along with the further increase of the aperture of the antenna; meanwhile, as the annular truss type folding antenna reflector is installed on the satellite system, the disadvantages of low stability and low rigidity can also have adverse effects on the stability and safety of the whole satellite system.
Disclosure of Invention
The invention provides an aerospace folding and unfolding antenna reflector and a satellite system with the same, and aims to solve the problems that the existing net surface type folding and unfolding antenna reflector is low in rigidity, poor in structural stability and low in shape surface precision along with the increase of an unfolding caliber, and the stability and safety of the satellite system are affected.
The invention is realized in such a way, and provides an aerospace folded and unfolded antenna reflector which comprises a central rod assembly and a plurality of rib units, wherein the central rod assembly comprises a central rod, the plurality of rib units are radially and uniformly distributed by taking the central rod as the center, each rib unit comprises an expandable unit and a Y-shaped mechanism, one end of the expandable unit is rotatably connected with the central rod, the other end of the expandable unit is rotatably connected with the Y-shaped mechanism, and the edge of a cable net is connected with each Y-shaped mechanism.
Preferably, the center rod subassembly still includes connecting block and connecting block under the center rod on the well core rod, connecting block fixed connection is in on the well core rod the upper end of well core rod, connecting block fixed connection is at well core rod's lower extreme under well core rod, and connecting block are petal column structure under well core rod is gone up the outside and each of connecting block on well core rod but the upper end one side of expansion unit is rotated and is connected, and the outside of connecting block is rotated with lower extreme one side of each expansion unit under well core rod.
Further preferably, the expandable unit comprises an upper chord, a lower chord, a vertical rod, a large diagonal web member and a small diagonal web member, wherein two sides of the upper end of the vertical rod are respectively rotatably connected with an upper chord, two small diagonal web members are respectively rotatably connected with the vertical rod on the lower side of the two upper chord, two sides of the lower end of the vertical rod are respectively rotatably connected with two lower chord, a vertical rod slider and a vertical rod spring are sleeved on the vertical rod, two ends of the vertical rod spring respectively prop against the lower ends of the vertical rod slider and the vertical rod, two ends of the vertical rod slider are respectively rotatably connected with a support rod, the other ends of the two support rods are respectively rotatably connected with the small diagonal web members on the same side, one ends of the two small diagonal web members, which are far away from the vertical rod, are respectively rotatably connected with the large diagonal web members on the same side, one ends of the two large diagonal web members, which are far away from the vertical rod, are respectively rotatably connected with the upper end of the central rod, one end of the other upper chord far away from the vertical rod is rotatably connected with one side of the upper end of the Y-shaped mechanism, one end of one lower chord far away from the vertical rod is rotatably connected with the lower end of the central rod, and one end of the other lower chord far away from the vertical rod is rotatably connected with one side of the lower end of the Y-shaped mechanism.
Further preferably, the deployable unit still includes connecting block on the montant and connecting block under the montant, connecting block fixed connection on the montant in the upper end of montant, connecting block fixed connection is at the lower extreme of montant under the montant, and the connecting block is the I shape structure on the montant, on the montant the upper end both sides of connecting block respectively with last chord member rotates to be connected, on the montant the lower extreme both sides of connecting block respectively with little oblique web member rotates to be connected, under the montant the connecting block keep away from the montant both ends respectively with lower chord member rotates to be connected.
Further preferably, the Y-shaped mechanism comprises a Y-shaped mechanism center rod, Y-shaped mechanism upper chords, Y-shaped mechanism large diagonal web members and Y-shaped mechanism small diagonal web members, the upper end of the Y-shaped mechanism center rod is rotatably connected with the two Y-shaped mechanism upper chords, the lower end of the Y-shaped mechanism center rod is rotatably connected with the two Y-shaped mechanism large diagonal web members, the other ends of the two Y-shaped mechanism large diagonal web members are respectively rotatably connected with one Y-shaped mechanism small diagonal web member, the other ends of the two Y-shaped mechanism small diagonal web members are respectively rotatably connected to the Y-shaped mechanism upper chords on the corresponding side, the Y-shaped mechanism is characterized in that a Y-shaped mechanism sliding block and a Y-shaped mechanism spring are sleeved on a center rod of the Y-shaped mechanism, two ends of the Y-shaped mechanism spring respectively abut against the upper end of the center rod of the Y-shaped mechanism and the Y-shaped mechanism sliding block, the side face of the Y-shaped mechanism sliding block is rotatably connected with two Y-shaped mechanism supporting rods, and the other ends of the two Y-shaped mechanism supporting rods are respectively rotatably connected to two Y-shaped mechanism large inclined web members on the corresponding side.
Further preferably, the Y-shaped mechanism further comprises an upper Y-shaped mechanism connecting block and a lower Y-shaped mechanism connecting block, the upper Y-shaped mechanism connecting block is fixedly connected to the upper end of the center rod of the Y-shaped mechanism and is rotationally connected with the upper chord of the Y-shaped mechanism through the upper Y-shaped mechanism connecting block, the lower Y-shaped mechanism connecting block is fixedly connected to the lower end of the center rod of the Y-shaped mechanism and is rotationally connected with the large diagonal web member of the Y-shaped mechanism through the lower Y-shaped mechanism connecting block, and the lower Y-shaped mechanism connecting block is rotationally connected with the deployable unit through the upper Y-shaped mechanism connecting block and the lower Y-shaped mechanism connecting block.
Preferably, the two upper chords of the Y-shaped mechanism are connected with the small diagonal web members of the Y-shaped mechanism through connecting members, the connecting members are provided with long holes, and the small diagonal web members of the Y-shaped mechanism are rotatably connected in the long holes of the connecting members.
Further preferably, there are 6 rib units.
The invention also provides a satellite system provided with the space navigation folding and unfolding antenna reflector, which comprises a satellite body, wherein the space navigation folding and unfolding antenna reflector is connected to the satellite body through a mechanical arm assembly, the mechanical arm assembly is an open type multi-link mechanism, one end of the mechanical arm assembly is rotatably connected to the satellite body, the other end of the mechanical arm assembly is fixedly connected with the space navigation folding and unfolding antenna reflector, and one end of the mechanical arm assembly, which is connected with the space navigation folding and unfolding antenna reflector, is also provided with a locking and releasing device.
Preferably, two solar wings are symmetrically arranged on the side surface of the satellite body.
Compared with the prior art, the invention has the advantages that:
the aerospace folding and unfolding antenna reflector provided by the invention consists of a plurality of unfolding units with modular structural characteristics and a Y-shaped mechanism, reduces the types and the number of parts, and has great advantages in the aspects of interchangeability, development period, processing cost and the like;
after the aerospace folding and unfolding antenna reflector is completely unfolded, the radial deployable units and the circumferential Y-shaped mechanism are used for ensuring that the radial and circumferential structures support the reflecting net surface, so that the rigidity, the stability and the shape surface precision of the structure are improved;
the aerospace folding and unfolding antenna reflector provided by the invention adopts a passive driving mode, is unfolded by an elastic potential energy driving mechanism stored by a compression spring, and has the advantages of light weight, high reliability, small occupied space for installation and the like;
the aerospace folding and unfolding antenna reflector provided by the invention is not only suitable for the technical field of aerospace space, but also has higher reference and reference values in the related fields of ground vehicle-mounted antennas, sunshade umbrellas, sunshade pavilions, rescue tents and the like;
the satellite system provided with the reflector can realize the quick installation of the reflector mechanism and the satellite body, and has the advantages of simple structure, convenience in installation and good stability.
Drawings
FIG. 1 is a schematic diagram of an aerospace folded antenna reflector provided by the present invention in a fully unfolded state;
FIG. 2 is a top view of an aerospace folded antenna reflector provided by the present invention in a fully unfolded state;
fig. 3 is a schematic diagram of an aerospace folded antenna reflector according to the present invention in a fully folded state;
FIG. 4 is a schematic view of a center rod assembly;
FIG. 5 is a schematic view of a rib unit structure;
FIG. 6 is a schematic view of a deployable cell structure;
FIG. 7 is a schematic view of the Y-mechanism in an expanded state;
FIG. 8 is a schematic view of the Y-mechanism in a collapsed state;
FIG. 9 is a schematic view of the upper chord assembly;
FIG. 10 is a schematic view of the lower chord assembly;
FIG. 11 is a schematic view of the installation of the large diagonal web members;
FIG. 12 is a schematic view of the assembly of the upper chord of the Y-mechanism;
FIG. 13 is a schematic view of the Y-mechanism web member assembly;
fig. 14 is a schematic view of an aerospace folded antenna reflector provided by the present invention in a folded state connected to a satellite body;
FIG. 15 is a schematic view of an aerospace folded antenna reflector of the present invention shown in an unfolded state with a robotic arm attached to a satellite body;
fig. 16 is a schematic view of an aerospace folded antenna reflector according to the present invention in a fully unfolded state when it is attached to a satellite body.
In the drawings: 1-central rod component, 2-rib unit, 3-central rod upper connecting block, 4-upper chord, 5-large diagonal web member, 6-small diagonal web member, 7-vertical rod upper connecting block, 8-first straight rod, 9-Y-shaped mechanism upper connecting block, 10-Y-shaped mechanism large diagonal web member, 11-Y-shaped mechanism small diagonal web member, 12-connecting component, 13-Y-shaped mechanism upper chord member, 14-first joint, 15-Y-shaped mechanism lower connecting block, 16-Y-shaped mechanism sliding block, 17-Y-shaped mechanism central rod, 18-lower chord member, 19-vertical rod lower connecting block, 20-vertical rod, 21-vertical rod sliding block, 22-supporting rod, 23-central rod lower connecting block, 24-central rod, 25-vertical rod spring, 26-Y-shaped mechanism spring, 27-seventh joint, 28-eighth joint, 29-fourth joint, 30-fifth joint, 31-second joint, 32-third joint, 33-Y-shaped mechanism supporting rod, 34-deployable unit, 35-Y-shaped mechanism, 36-first fixing hole, 37-first through hole, 38-second straight rod, 39-second fixing hole, 40-fourth through hole, 41-third straight rod, 42-third fixing hole, 43-fifth through hole, 44-fifth straight rod, 45-fourth straight rod, 46-sixth joint, 47-end face, 48-sixth straight rod, 49-fifth fixing hole, 50-third through hole, 51-satellite body, 52-aerospace folded antenna reflector, 53-mechanical arm assembly, 54-solar wing, 55-lock release, 56-fourth fixing hole, 57-second through hole.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Examples 1,
Referring to fig. 1, 2 and 3, the present embodiment provides an aerospace folded antenna reflector, including a central rod assembly 1 and a plurality of rib units 2, where the central rod assembly 1 includes a central rod 24, the plurality of rib units 2 are radially and uniformly distributed around the central rod 24, each rib unit 2 includes an expandable unit 34 and a Y-shaped mechanism 35, one end of the expandable unit 34 is rotatably connected to the central rod 24, and the other end is rotatably connected to the Y-shaped mechanism 35, so as to connect the edge of a cable net to each Y-shaped mechanism 35.
During deployment, the deployable cell 34 and the Y-mechanism 35 are deployed radially outward centered on the central rod 24, such that the cable net is supported by the deployable cell 34 and the Y-mechanism 35.
Referring to fig. 4, the center pole subassembly still includes connecting block 3 and connecting block 23 under the center pole on well core rod, and connecting block 3 fixed connection is in on well core rod the upper end of well core rod 24, connecting block 23 fixed connection is at the lower extreme of well core rod 24 under well core rod, and connecting block 3 and connecting block 23 are petal column structure under well core rod on well core rod, and the outside of connecting block 3 is equipped with a plurality of preformed holes on well core rod, through preformed hole and each the upper end one side of deployable unit 34 is rotated and is connected, and the outside of connecting block 23 also is equipped with a plurality of preformed holes under well core rod, rotates through preformed hole and each lower extreme one side of deployable unit 34 and is connected.
Specifically, the upper connecting block 3 of the central rod is connected with the upper end of the central rod 24 in an interference fit manner, and the lower connecting block 23 of the central rod is connected with the lower end of the central rod 24 in a bolt connection manner.
Referring to fig. 5 and 6, the expandable unit 34 includes an upper chord 4, a lower chord 18, a vertical rod 20, a large diagonal web member 5 and a small diagonal web member 6, two upper sides of the upper end of the vertical rod 20 are respectively rotatably connected with the upper chord 4, two small diagonal web members 6 are respectively rotatably connected to the vertical rod 20 at the lower side of the two upper chord 4, two lower sides of the lower end of the vertical rod 20 are respectively rotatably connected with the two lower chords 18, a vertical rod slider 21 and a vertical rod spring 25 are sleeved on the vertical rod 20, two ends of the vertical rod spring 25 respectively prop against the lower ends of the vertical rod slider 21 and the vertical rod 20, two ends of the vertical rod slider 21 are respectively rotatably connected with a support rod 22, the other ends of the two support rods 22 are respectively rotatably connected to the small diagonal web member 6 at the same side, one ends of the two small diagonal web members 6 far away from the vertical rod 20 are respectively rotatably connected with the large diagonal web member 5 at the same side, one ends of the two large diagonal web members 5 far away from the small diagonal web members 6 are respectively rotatably connected with one end of the lower web members 18 far away from the vertical rod 20 at the same side, one end of one upper chord 4 far away from the vertical rod 20 is rotatably connected with the upper end of the central rod 24, one end of the other upper chord 4 far away from the vertical rod 20 is rotatably connected with one side of the upper end of the Y-shaped mechanism 35, one end of one lower chord 18 far away from the vertical rod 20 is rotatably connected with the lower end of the central rod 24, and one end of the other lower chord 18 far away from the vertical rod 20 is rotatably connected with one side of the lower end of the Y-shaped mechanism 35.
When the folded state, montant spring 25 is compression state, expand the in-process, montant spring 25 extends, promote montant slider 21 to the upper end removal of montant 20, montant slider 21 promotes two little oblique web members 6 through two bracing pieces 22 and opens, two little oblique web members 6 give the effect of two 5 power of big oblique web members, make two lower chords 18 of the other both ends traction of big oblique web member 5 be straight state, thereby it is straight state to drive two upper chords 4, to this end, the unit that can expand realizes from drawing in to expanding.
Referring to fig. 9, the upper chord 4 is an assembly mainly composed of a first straight rod 8 and a first joint 14, the first straight rod 8 is a hollow round rod, two ends of the hollow round rod are respectively inserted with the first joint 14, and the hollow round rod is fixed by a pin. According to the principle of mechanics, in order to ensure that the components in the mechanism can be accurately connected and have a certain motion rule, the distance between the kinematic pairs of each component is kept constant, and in the case of the upper chord 4 of the present invention, the distance between the first through holes 37 at the two ends of the first strut 8 is required to be constant. Therefore, in the actual process of manufacturing, necessary tooling needs to be designed to perform combined processing on the upper chord member 4 assembly, that is, after the first joint 14 is inserted into the first straight rod 8, the first fixing hole 36 is drilled on the tooling, and then the pin is driven in, so that the accuracy of mounting the upper chord member 4 assembly can be ensured.
Referring to fig. 10, the lower chord 18 is an assembly mainly composed of a second joint 31, a third joint 32 and a second straight rod 38, and the second straight rod 38 is a hollow round rod, and two ends of the hollow round rod are respectively inserted into the second joint 31 and the third joint 32 and are fixed at a second fixing hole 39 by using a pin. Due to the design, the accuracy of the structural size of the lower chord 18 is guaranteed, and the distance between the two fourth through holes 40 is guaranteed to be unchanged.
Referring to fig. 11, the large diagonal web member 5 is an assembly mainly composed of a fourth joint 29, a fifth joint 30 and a third straight rod 41, the third straight rod 41 is a hollow round rod, two ends of which are respectively inserted into the fourth joint 29 and the fifth joint 30, and are fixed in a third fixing hole 42 by using a pin. By the design, the accuracy of the structural size of the large diagonal web member 5 is guaranteed, and the distance between the two fifth through holes 43 is guaranteed to be unchanged.
In order to facilitate connection, as an improvement, the deployable unit 34 further includes an upper vertical rod connecting block 7 and a lower vertical rod connecting block 19, the upper vertical rod connecting block 7 is fixedly connected to the upper end of the vertical rod 20, the lower vertical rod connecting block 19 is fixedly connected to the lower end of the vertical rod 20, the upper vertical rod connecting block 7 is of an i-shaped structure, two sides of the upper end of the upper vertical rod connecting block 7 are rotatably connected to the upper chord 4, two sides of the lower end of the upper vertical rod connecting block 7 are rotatably connected to the small diagonal web member 6, and two ends of the lower vertical rod connecting block 19, which are far away from the vertical rod 20, are rotatably connected to the lower chord member 18.
Specifically, the upper connecting block 7 of the vertical rod and the upper end of the vertical rod 20 form a fixed connection through interference fit, and the lower connecting block 19 of the vertical rod is fixedly connected with the lower end of the vertical rod 20 through two bolts.
Referring to fig. 5, 7 and 8, the Y-shaped mechanism 35 includes a Y-shaped mechanism center rod 17, a Y-shaped mechanism top chord 13, a Y-shaped mechanism large diagonal web member 10 and a Y-shaped mechanism small diagonal web member 11, the upper end of the Y-shaped mechanism center rod 17 is rotatably connected with the two Y-shaped mechanism top chord 13, the lower end of the Y-shaped mechanism center rod 17 is rotatably connected with the two Y-shaped mechanism large diagonal web members 10, the other ends of the two Y-shaped mechanism large diagonal web members 10 are respectively rotatably connected with one Y-shaped mechanism small diagonal web member 11, the other ends of the two Y-shaped mechanism small diagonal web members 11 are respectively rotatably connected with the Y-shaped mechanism top chord 13 on the corresponding side, a Y-shaped mechanism slider 16 and a Y-shaped mechanism spring 26 are sleeved on the Y-shaped mechanism center rod 17, the two ends of the Y-shaped mechanism spring 26 are respectively abutted against the upper end of the Y-shaped mechanism center rod 17 and the Y-shaped mechanism slider 16, the side of the Y-shaped mechanism slider 16 is rotatably connected with two Y-shaped mechanism support rods 33, the other ends of the two Y-shaped mechanism support rods 33 are respectively and rotatably connected to the two Y-shaped mechanism large diagonal web members 10 on the corresponding sides.
When the Y-shaped mechanism 35 is in a folded state, the Y-shaped mechanism spring 26 is in a compressed state, and in an unfolding process, the Y-shaped mechanism spring 26 extends to push the Y-shaped mechanism slider 16 to move towards the lower end of the center rod 17 of the Y-shaped mechanism, push the two Y-shaped mechanism support rods 33 to unfold outwards, push the two Y-shaped mechanism large diagonal web members 10 to unfold outwards, push the two Y-shaped mechanism small diagonal web members 11 to unfold outwards through the action of the connecting structural force of the Y-shaped mechanism large diagonal web members 10, and push the two Y-shaped mechanism upper chords 13 to unfold outwards through the Y-shaped mechanism small diagonal web members 11 to form a Y-shaped opening structure.
Referring to fig. 12, the upper chord 13 of the Y-shaped mechanism is an assembly mainly composed of a sixth joint 46, a fourth straight rod 45, a connecting member 12, and a fifth straight rod 44, and for the upper chord 13, the distance between the center of the second through hole 57 on the sixth joint 46 and the end face 47 of the fifth straight rod 44 is mainly ensured, and the structure is assembled and processed at the fourth fixing hole 56. By the design, the accuracy of the structural size of the upper chord 13 of the Y-shaped mechanism is guaranteed. The connecting member 12 is provided with a long hole, and the small diagonal web member 11 of the Y-shaped mechanism is rotatably connected in the long hole of the connecting member 12.
Referring to fig. 13, the Y-shaped mechanism small diagonal web member 11 is an assembly mainly composed of a seventh joint 27, an eighth joint 28 and a sixth straight rod 48. The sixth straight rod 48 is a hollow round rod, and the seventh joint 27 and the eighth joint 28 are respectively inserted into two ends of the sixth straight rod, and for the Y-shaped mechanism small diagonal web member 11, the distance between the centers of the two third through holes 50 on the seventh joint 27 and the eighth joint 28 is mainly ensured, and the structure is combined and processed at the fifth fixing hole 49. By the design, the accuracy of the structural size of the small inclined web member 11 of the Y-shaped mechanism is guaranteed.
For convenience of connection, the Y-shaped mechanism 35 further includes an upper Y-shaped mechanism connecting block 9 and a lower Y-shaped mechanism connecting block 15, the upper Y-shaped mechanism connecting block 9 is fixedly connected to the upper end of the center rod 17 of the Y-shaped mechanism and is rotatably connected to the two upper Y-shaped mechanism chords 13 through the upper Y-shaped mechanism connecting block 9, the lower Y-shaped mechanism connecting block 15 is fixedly connected to the lower end of the center rod 17 of the Y-shaped mechanism, is rotatably connected to the two large diagonal web members 10 of the Y-shaped mechanism through the lower Y-shaped mechanism connecting block 15, and is rotatably connected to the deployable unit 34 through the upper Y-shaped mechanism connecting block 9 and the lower Y-shaped mechanism connecting block 15.
Specifically, the upper connecting block 9 of the Y-shaped mechanism is fixedly connected with the upper end of a center rod 17 of the Y-shaped mechanism through interference fit, and the lower connecting block 15 of the Y-shaped mechanism is connected with the lower end of the center rod 17 of the Y-shaped mechanism through a bolt.
Preferably, there are 6 rib elements 2.
The aerospace satellite-borne folding and unfolding antenna reflector is stored in a payload cabin of a rocket when the rocket is launched, the rib units 2 are in a completely folded state, the vertical rod springs 25 and the Y-shaped mechanism springs 26 are compressed and store certain elastic potential energy, and the overall volume of the mechanism is the minimum at the moment; after the satellite enters the orbit, the satellite-borne folding and unfolding antenna reflector performs unlocking according to a task instruction, and then the vertical rod spring 25 and the Y-shaped mechanism spring 26 simultaneously push the vertical rod sliding block 21 and the Y-shaped mechanism sliding block 16 to move along the vertical rod 20 and the Y-shaped mechanism central rod 17 respectively, so that the basic extensible unit 34 and the Y-shaped mechanism 35 are driven to be unfolded; the mechanism is provided with a limit structure at the joint of the small inclined web member 6 and the large inclined web member 5 and at the joint of the Y-shaped mechanism large inclined web member 10 and the Y-shaped mechanism small inclined web member 11, and when the small inclined web member 6 and the large inclined web member 5, the Y-shaped mechanism large inclined web member 10 and the Y-shaped mechanism small inclined web member 11 are respectively unfolded into a straight line, the mechanism reaches a limit position and is locked, so that the mechanism is converted into a stable structure.
In the embodiment, on the basis of adopting the deployable unit 34 as a radial extending structure, the aerospace satellite-borne folding and unfolding antenna reflector introduces another structural form, namely a Y-shaped mechanism 35; the purpose of this design is mainly to consider that for this radiation type deployable antenna reflector, if only the deployable unit 34 is adopted singly, the effective structure at the edge of the antenna becomes relatively sparse with the increase of the aperture of the antenna, which is further unfavorable for the connection and tensioning of the reflective net, and the shape accuracy of the antenna is difficult to guarantee; after the Y-shaped mechanism 35 is arranged on the outer side of the deployable unit 34, the covering surface of the structure can be greatly improved, and the weight of the structure can be effectively reduced. In addition, in order to meet the requirement for a larger-aperture antenna, the number of branches may be increased on the basis of the Y-shaped mechanism 35, or the number of circumferential directions of the basic deployable units 34 may be increased, or a combination of the two may be adopted, which may better meet the requirement.
In this embodiment, the rib unit 2 is a key structure for unfolding the folded antenna reflector, and mainly comprises two assemblies, namely an extensible unit 34 and a Y-shaped mechanism 35, wherein each assembly is relatively independent and has an unfolding function, so that the extensible unit 34 and the Y-shaped mechanism 35 respectively need 1 power source to drive the extensible unit to unfold; in consideration of the harsh requirements of space navigation tasks on the quality of the structure, the passive driving mode of the compression spring is adopted in the invention to reduce the quality of the structure as much as possible, and meanwhile, the driving mode avoids the complex structure of the traditional motor combined with the lead screw driving, and has the advantages of high reliability, good unfolding synchronism and the like.
In the embodiment, the central rod assembly 1 and the six rib units 2 are made of titanium alloy, magnesium alloy or carbon fiber in terms of material selection, so that the weight of the antenna reflector mechanism is reduced, and the requirement of an actual satellite task is met.
In this embodiment, each Y-mechanism 35 is comprised of two Y-mechanism top chords 13, and is configured to meet the needs of most mission scenarios. On the basis, the number of the upper chords 13 of the Y-shaped mechanism can be adjusted to be adaptively increased or decreased according to the change of tasks, so that a wider using effect is achieved.
Examples 2,
Referring to fig. 14, 15 and 16, the present embodiment provides a satellite system provided with an aerospace folded and unfolded antenna reflector according to embodiment 1, including a satellite body 51, the aerospace folded and unfolded antenna reflector 52 is connected to the satellite body 51 through a mechanical arm assembly 53, the mechanical arm assembly 53 is an open type multi-link mechanism, one end of the mechanical arm assembly 53 is rotatably connected to the satellite body 51, the other end of the mechanical arm assembly 53 is fixedly connected to the aerospace folded and unfolded antenna reflector 52, and a locking and releasing device 55 is further disposed at one end of the mechanical arm assembly 53 connected to the aerospace folded and unfolded antenna reflector 52. On the side of the satellite body 51, two sun wings 54 are also symmetrically arranged.
The outer contour of the satellite body 51 is cuboid, one side surface of the satellite body is connected with one end of a mechanical arm component 53, and the other two side surfaces of the satellite body are respectively connected with a solar wing 54; the mechanical arm assembly 53 is an open type multi-link mechanism, one end of the mechanical arm assembly is connected with the satellite body 51, and a rotating pair is formed; the other end is connected with the folded and unfolded antenna reflector mechanism 52 and is fixedly connected with the same; the lock release device 55 binds and unlocks the folded antenna reflector mechanism 52.
The unfolding process of the folded antenna reflector mechanism 52 in an aerospace space can be divided into two stages:
in the first stage: when the satellite system enters the orbit, under the driving of the motor, the mechanical arm assembly 53 sequentially opens each component of the mechanical arm assembly 53, and supports the folded and unfolded antenna reflector mechanism 52 in the folded state to the working position;
the second stage is as follows: the locking and releasing device 55 works to release the folded and unfolded antenna reflector mechanism 52 which is bound and locked and in a folded state, the folded and unfolded antenna reflector mechanism 52 is unfolded under the action of the driving force of the spring, and after the folded and unfolded antenna reflector mechanism is completely unfolded, the mechanism realizes rigid locking and is converted into a stable structure.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. Aerospace folded antenna reflector, characterized by, including central pole subassembly (1) and a plurality of rib unit (2), central pole subassembly (1) is including central pole (24), a plurality of rib unit (2) use central pole (24) as the center, be radial evenly distributed, every rib unit (2) are including deployable unit (34) and Y shape mechanism (35), deployable unit (34) one end is rotated with central pole (24) and is connected, the other end rotates with Y shape mechanism (35) and is connected, the border and each Y shape mechanism (35) of rope net are connected.
2. The aerospace folded antenna reflector according to claim 1, wherein the center rod assembly further includes a center rod upper connection block (3) and a center rod lower connection block (23), the center rod upper connection block (3) is fixedly connected to an upper end of the center rod (24), the center rod lower connection block (23) is fixedly connected to a lower end of the center rod (24), the center rod upper connection block (3) and the center rod lower connection block (23) are both petal-shaped structures, an outer side of the center rod upper connection block (3) is rotatably connected to one side of an upper end of each of the deployable units (34), and an outer side of the center rod lower connection block (23) is rotatably connected to one side of a lower end of each of the deployable units (34).
3. The aerospace folded and unfolded antenna reflector according to claim 1, wherein the deployable unit (34) comprises an upper chord (4), a lower chord (18), a vertical rod (20), a large diagonal web member (5) and a small diagonal web member (6), both sides of the upper end of the vertical rod (20) are respectively and rotatably connected with the upper chord (4), both sides of the lower end of the vertical rod (20) are respectively and rotatably connected with the two small diagonal web members (6), both sides of the lower end of the vertical rod (20) are respectively and rotatably connected with the two lower chord members (18), the vertical rod (20) is sleeved with a vertical rod slider (21) and a vertical rod spring (25), both ends of the vertical rod spring (25) respectively prop against the lower ends of the vertical rod slider (21) and the vertical rod (20), both ends of the vertical rod slider (21) are respectively and rotatably connected with a support rod (22), and the other ends of the two support rods (22) are respectively and rotatably connected with the small diagonal web members (6) at the same side, the one end that montant (20) were kept away from in two little oblique web members (6) rotates with big oblique web member (5) of homonymy respectively to be connected, and the one end that little oblique web member (6) were kept away from in two big oblique web members (5) rotates with the one end that montant (20) were kept away from in lower chord (18) of homonymy respectively to be connected, and the one end that montant (20) were kept away from in last chord (4) with the upper end of well core rod (24) rotates to be connected, another one end that montant (20) were kept away from in last chord (4) with the upper end one side of Y shape mechanism (35) rotates to be connected, and the one end that montant (20) were kept away from in one lower chord (18) rotates with the lower extreme of well core rod (24) to be connected, and the one end that montant (20) were kept away from in another lower chord (18) rotates with lower extreme one side of Y shape mechanism (35) to be connected.
4. The aerospace folded and unfolded antenna reflector according to claim 3, wherein the deployable unit (34) further comprises an upper vertical rod connecting block (7) and a lower vertical rod connecting block (19), the upper vertical rod connecting block (7) is fixedly connected to the upper end of the vertical rod (20), the lower vertical rod connecting block (19) is fixedly connected to the lower end of the vertical rod (20), the upper vertical rod connecting block (7) is of an I-shaped structure, two sides of the upper end of the upper vertical rod connecting block (7) are rotatably connected with the upper chord (4), two sides of the lower end of the upper vertical rod connecting block (7) are rotatably connected with the small diagonal web member (6), and two ends of the lower vertical rod connecting block (19) far away from the vertical rod (20) are rotatably connected with the lower chord (18) respectively.
5. The aerospace folded antenna reflector according to claim 1, wherein the Y-shaped mechanism (35) comprises a Y-shaped mechanism center rod (17), a Y-shaped mechanism upper chord (13), a Y-shaped mechanism large diagonal web member (10) and a Y-shaped mechanism small diagonal web member (11), the upper end of the Y-shaped mechanism center rod (17) is rotatably connected with two Y-shaped mechanism upper chord members (13), the lower end of the Y-shaped mechanism center rod (17) is rotatably connected with two Y-shaped mechanism large diagonal web members (10), the other ends of the two Y-shaped mechanism large diagonal web members (10) are respectively rotatably connected with one Y-shaped mechanism small diagonal web member (11), the other ends of the two Y-shaped mechanism small diagonal web members (11) are respectively rotatably connected with the Y-shaped mechanism upper chord member (13) on the corresponding side, a Y-shaped mechanism slider (16) and a Y-shaped mechanism spring (26) are sleeved on the Y-shaped mechanism center rod (17), two ends of a Y-shaped mechanism spring (26) are respectively propped against the upper end of a Y-shaped mechanism center rod (17) and a Y-shaped mechanism sliding block (16), the side surface of the Y-shaped mechanism sliding block (16) is rotatably connected with two Y-shaped mechanism supporting rods (33), and the other ends of the two Y-shaped mechanism supporting rods (33) are respectively rotatably connected to two Y-shaped mechanism large inclined web members (10) on the corresponding side.
6. The aerospace folded antenna reflector of claim 5, wherein the Y-mechanism (35) further comprises an upper Y-mechanism connecting block (9) and a lower Y-mechanism connecting block (15), the upper Y-mechanism connecting block (9) is fixedly connected to the upper end of the center Y-mechanism rod (17) and rotatably connected to the two upper Y-mechanism chords (13) through the upper Y-mechanism connecting block (9), the lower Y-mechanism connecting block (15) is fixedly connected to the lower end of the center Y-mechanism rod (17), and rotatably connected to the two large Y-mechanism diagonal web members (10) through the lower Y-mechanism connecting block (15), and rotatably connected to the deployable unit (34) through the upper Y-mechanism connecting block (9) and the lower Y-mechanism connecting block (15).
7. The aerospace folded antenna reflector of claim 5, wherein a connecting member (12) is provided at a position where the two Y-shaped mechanism upper chords (13) are connected to the Y-shaped mechanism small diagonal web members (11), respectively, and a long hole is provided in the connecting member (12), and the Y-shaped mechanism small diagonal web members (11) are rotatably connected in the long hole of the connecting member (12).
8. Aerospace folded antenna reflector according to claim 1, characterised in that there are 6 rib elements (2).
9. The satellite system provided with the astronomical folding antenna reflector according to claim 1 or 2 or 3 or 4 or 5 or 6 or 7, comprising a satellite body (51), wherein the astronomical folding antenna reflector (52) is connected to the satellite body (51) through a mechanical arm assembly (53), the mechanical arm assembly (53) is an open type multi-link mechanism, one end of the mechanical arm assembly (53) is rotatably connected to the satellite body (51), the other end of the mechanical arm assembly (53) is fixedly connected with the astronomical folding antenna reflector (52), and a locking release device (55) is further arranged at the end of the mechanical arm assembly (53) connected with the astronomical folding antenna reflector (52).
10. Aerospace folding antenna reflector according to claim 9, characterised in that on the side of the satellite body (51) there are also symmetrically arranged two sun wings (54).
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005048765A1 (en) * | 2003-11-18 | 2005-06-02 | Gb Design Limited | Umbrella |
| CN201328444Y (en) * | 2007-10-31 | 2009-10-21 | 奇贝设计有限公司 | Umbrella |
| US20110187627A1 (en) * | 2010-02-01 | 2011-08-04 | Harris Corporation | Extendable rib reflector |
| CN102458179A (en) * | 2009-04-07 | 2012-05-16 | 休伯特·塞缪尔·弗罗斯特 | Umbrella, umbrella frame and rib therefor |
| CN105160051A (en) * | 2015-06-30 | 2015-12-16 | 中国空间技术研究院 | Truss antenna reflector deployment dynamics modeling method based on multi-body analysis test |
| JP2017069921A (en) * | 2015-10-02 | 2017-04-06 | 株式会社テクノソルバ | Development type reflector and development structure for the same |
| CN112259949A (en) * | 2020-09-16 | 2021-01-22 | 航天东方红卫星有限公司 | High storage ratio modularization folding and unfolding support truss |
| CN112713379A (en) * | 2020-12-08 | 2021-04-27 | 西安电子科技大学 | Deployable antenna adopting Y-shaped rib cable net parabolic cylinder, control method and application |
-
2021
- 2021-08-25 CN CN202110982802.7A patent/CN113675615B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005048765A1 (en) * | 2003-11-18 | 2005-06-02 | Gb Design Limited | Umbrella |
| CN201328444Y (en) * | 2007-10-31 | 2009-10-21 | 奇贝设计有限公司 | Umbrella |
| CN102458179A (en) * | 2009-04-07 | 2012-05-16 | 休伯特·塞缪尔·弗罗斯特 | Umbrella, umbrella frame and rib therefor |
| US20110187627A1 (en) * | 2010-02-01 | 2011-08-04 | Harris Corporation | Extendable rib reflector |
| CN105160051A (en) * | 2015-06-30 | 2015-12-16 | 中国空间技术研究院 | Truss antenna reflector deployment dynamics modeling method based on multi-body analysis test |
| JP2017069921A (en) * | 2015-10-02 | 2017-04-06 | 株式会社テクノソルバ | Development type reflector and development structure for the same |
| CN112259949A (en) * | 2020-09-16 | 2021-01-22 | 航天东方红卫星有限公司 | High storage ratio modularization folding and unfolding support truss |
| CN112713379A (en) * | 2020-12-08 | 2021-04-27 | 西安电子科技大学 | Deployable antenna adopting Y-shaped rib cable net parabolic cylinder, control method and application |
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