CN114497990A

CN114497990A - Satellite-borne expandable antenna and assembly method thereof

Info

Publication number: CN114497990A
Application number: CN202210328785.XA
Authority: CN
Inventors: 董均国; 冯建元; 李�杰; 葛运; 宋振林
Original assignee: APT Mobile Satcom Ltd
Current assignee: APT Mobile Satcom Ltd
Priority date: 2022-03-31
Filing date: 2022-03-31
Publication date: 2022-05-13
Anticipated expiration: 2042-03-31
Also published as: CN114497990B

Abstract

The invention relates to the technical field of antennas, in particular to a satellite-borne expandable antenna and an assembly method thereof, wherein the satellite-borne expandable antenna comprises a satellite platform, a first antenna mechanism and a second antenna mechanism, wherein the first antenna mechanism and the second antenna mechanism can be sequentially expanded or sequentially folded and furled on the satellite platform; according to the invention, the first antenna, the second antenna and the third antenna are folded and folded to the top of the satellite platform in sequence, so that the space on the left side and the space on the right side of the satellite platform are not occupied, the storage rate is high, and more space in the rocket is not occupied.

Description

Satellite-borne expandable antenna and assembly method thereof

Technical Field

The invention relates to the technical field of antennas, in particular to a satellite-borne expandable antenna and an assembly method thereof.

Background

Space-borne antennas are widely used for space-to-ground observation and communication. Due to the limitation of effective carrier space and carrier force of the rocket, the antenna is required to be fixed in a folded 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 action in the space orbit according to the design requirement, and then the spacecraft is locked and kept in a working state. Thus, the antenna's deployable nature becomes a significant feature of modern space antennas.

Space-borne antennas typically include parabolic dish-type and planar antennas. For a planar antenna, such as a planar antenna of a satellite-borne SAR satellite, the configuration makes the antenna in a cantilever state, and therefore, the antenna cannot be fixed with a satellite platform, and the stress manner of the antenna is severe. In order to solve the problem that the fundamental frequency of the plane antenna in a folded state is too low, the invention with the patent number of '201611118145.7' discloses an H-shaped satellite-borne antenna deployable mechanism, which comprises plane antenna components and a deployment mechanism, wherein the plane antenna components and the deployment mechanism are symmetrically arranged on two sides of a satellite platform; the left wing unfolding mechanism comprises a Y-shaped inclined strut type supporting truss, a driving mechanism and a driven strut, and the left wing planar antenna is pressed and folded on the side face of the satellite platform in a folded state; and in the unfolding state, the left wing planar antenna is unfolded at the upper end of the satellite platform. The invention utilizes the supporting truss to improve the furled fundamental frequency of the planar antenna, effectively solves the problem that the fundamental frequency of the antenna is too low due to the overlong cantilever of the H-shaped planar antenna in a furled state, realizes the generalization of a satellite platform, and only locally adds a rod piece.

However, in a folded state of the H-configuration satellite-borne antenna unfolding mechanism, the top ends of the left wing planar antenna and the right wing planar antenna protrude out of the satellite platform, so that in the folded state, the left wing planar antenna and the right wing planar antenna respectively occupy the left space, the right space and the top space of the satellite platform, the storage rate is small, and more rocket inner spaces need to be occupied.

Disclosure of Invention

Solves the technical problem

Aiming at the defects in the prior art, the invention provides a satellite-borne deployable antenna and an assembly method thereof, which can effectively solve the problem that in the folding state of an H-shaped satellite-borne antenna deployable mechanism in the prior art, the top ends of a left wing planar antenna and a right wing planar antenna protrude out of a satellite platform, so that in the folding state, the left wing planar antenna and the right wing planar antenna respectively occupy the left space, the right space and the top space of the satellite platform, the storage rate is small, and more rocket internal spaces need to be occupied.

Technical scheme

In order to achieve the purpose, the invention is realized by the following technical scheme:

a satellite-borne deployable antenna comprises a satellite platform, a first antenna mechanism and a second antenna mechanism, wherein the first antenna mechanism and the second antenna mechanism can be sequentially deployed or folded and furled on the satellite platform, the first antenna mechanism comprises a first antenna, the first antenna is rotatably connected to the satellite platform through a first truss group which is arranged in a rectangular shape, the second antenna mechanism comprises a second antenna, the second antenna is rotatably connected to one side, facing the first antenna, of the satellite platform through a second truss group which is arranged in a rectangular shape, the first truss group comprises a plurality of first outer trusses and a plurality of first inner trusses, the second truss group comprises a plurality of second outer trusses and a plurality of second inner trusses, a plurality of middle hinged seats are fixedly mounted on the satellite platform, a middle shaft is fixedly connected to each middle hinged seat, one end, far away from the first antenna, of the first inner truss and one end, far away from the second antenna, of the first inner truss are rotatably connected and in a limiting fit with one end, far away from the second antenna, one end, far away from the second antenna, of the second inner truss is in rotating connection with the middle shaft and is in limiting fit with the middle shaft, so that the first inner truss and the second inner truss are sequentially unfolded, or the second inner truss and the first inner truss are sequentially folded and furled.

Furthermore, the first outer truss and the first inner truss are respectively connected with the first antenna in a rotating mode through the top hinging seats, the second outer truss and the second inner truss are respectively connected with the second antenna in a rotating mode through the top hinging seats, one end, away from the first antenna, of the first outer truss and one end, away from the second antenna, of the second outer truss are respectively connected with the satellite platform in a rotating mode through the side hinging seats, and limiting blocks used for limiting rotating angles of the first outer truss and the second outer truss are arranged on the side hinging seats.

Furthermore, torsion springs are arranged between one end, away from the first antenna, of the first outer truss and one end, away from the second antenna, of the second outer truss and the side hinge seats.

Furthermore, one end, far away from the first antenna, of the first inner truss is fixedly connected with a shaft sleeve, and one end, far away from the second antenna, of the second inner truss is provided with a first limiting assembly which is in limiting fit with the shaft sleeve and the middle shaft respectively.

Furthermore, the middle part is provided with a limit groove, the inner side wall of the shaft sleeve is provided with a sector groove, the first limit component comprises a shaft collar and a sliding block, the shaft collar is fixedly connected to the second inner truss and far away from one end of the second antenna, the shaft collar is rotatably connected to the shaft sleeve, an inner cavity is formed in the wall of the shaft collar, the sliding block is connected to the inner cavity in a sliding mode, a first spring is arranged between the sliding block and the inner cavity, and the two sides of the sliding block are respectively provided with an outer rod capable of penetrating into the sector groove and an inner rod capable of penetrating into the limit groove.

Furthermore, still include third antenna mechanism, first antenna mechanism and second antenna mechanism with third antenna mechanism can expand in proper order or fold in proper order and draw in on the satellite platform, third antenna mechanism includes third antenna, preceding truss and back truss, expands the back, the third antenna is located between first antenna and the second antenna, folds and draws in the back, the third antenna is located between second antenna and the satellite platform, preceding truss with back truss intercrossing rotates to be connected, preceding truss and back truss both ends respectively with third antenna and satellite platform swing joint, last sliding connection of still having the spacing subassembly of multiunit second of satellite platform, the spacing subassembly of second is used for the second in the truss respectively with preceding truss and the spacing cooperation of back truss.

Furthermore, the second limiting assembly comprises a concave block, one end of the concave block is provided with an L-shaped sliding opening, the other end of the concave block is in transmission fit with the end tooth of the shaft collar, one end of the front truss, away from the third antenna, and one end of the rear truss, away from the third antenna, are both rotatably connected with a lower guide block in sliding connection with the satellite platform, a second spring is arranged between the side wall of the lower guide block and the satellite platform, and a guide rod in sliding fit with the L-shaped sliding opening is further arranged on the side wall of the lower guide block.

Furthermore, a limiting sleeve is fixedly mounted on the satellite platform, a limiting sliding opening is formed in the side wall of the limiting sleeve, the front truss and the rear truss are connected in a cross rotating mode through a cross shaft, and a limiting rod sliding in the limiting sliding opening is fixedly connected to the middle of the cross shaft.

Furthermore, still include the driver that locker and drive locker removed, the locker is used for locking the antenna under the state of expanding or the antenna under the folding folded state, and it includes the jam plate that slides on satellite platform and fixes first locking lever and the second locking lever at jam plate both ends and difference side respectively, one of them seted up on the first inner truss with first locking lever grafting complex lockhole, one of them the guide arm tip is seted up with the second locking lever grafting complex locked groove.

An assembling method of a satellite-borne deployable antenna, the assembling method being according to the above-mentioned one satellite-borne deployable antenna, the assembling method comprising the steps of:

s1, fixedly mounting the side hinge seats, the middle hinge seats and the limiting sleeve on a satellite platform in sequence, fixedly mounting a driver in the satellite platform, and movably mounting a locking device and the concave block on the satellite platform;

s2, sequentially and fixedly installing the top hinged seats on the first antenna and the second antenna respectively;

s3, respectively rotatably mounting the first outer truss, the first inner truss and a top hinged base on the first antenna, respectively rotatably mounting the second outer truss, the second inner truss and a top hinged base on the second antenna, and respectively movably mounting the front truss and the rear truss on a third antenna;

s4, in the unfolded state, movably mounting the other ends of the front truss and the rear truss on the satellite platform respectively, mounting second springs between the end part of the front truss and the satellite platform and between the end part of the rear truss and the satellite platform, movably mounting the transverse shaft between the front truss and the rear truss, and movably mounting the transverse shaft and the limiting sleeve;

s5, in the unfolded state, sleeving one end of a shaft collar into the shaft collar, movably installing the shaft collar on a middle shaft, and respectively installing a first outer truss, a second outer truss and a torsion spring on a side hinge seat to realize the assembly of the first antenna mechanism, the second antenna mechanism and the third antenna mechanism in the unfolded state;

and S6, folding and folding the third antenna mechanism, the second antenna mechanism and the first antenna mechanism in sequence, and controlling the driver to drive the locking device to move so as to realize locking of the folded and folded third antenna mechanism, the folded and folded second antenna mechanism and the folded first antenna mechanism.

Advantageous effects

Compared with the known public technology, the technical scheme provided by the invention has the following beneficial effects:

according to the invention, the first antenna, the second antenna and the third antenna are folded and folded to the top of the satellite platform in sequence, so that the space on the left side and the space on the right side of the satellite platform are not occupied, the storage rate is high, more space in a rocket is not occupied, the first antenna, the second antenna and the third antenna are unfolded in sequence, the mutual interference in the unfolding process of the first antenna, the second antenna and the third antenna is avoided, and the complete unfolding of the first antenna, the second antenna and the third antenna is effectively ensured.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.

FIG. 1 is a flow chart of an assembly method of the present invention;

FIG. 2 is a schematic view of the overall structure of the present invention in a folded and collapsed state;

FIG. 3 is a schematic view of the overall structure of the present invention in the expanded state;

fig. 4 is a first perspective view of the first, second and third antenna mechanisms of the present invention in an unfolded state;

fig. 5 is a second perspective structural view of the first antenna mechanism, the second antenna mechanism structure and the third antenna mechanism in the unfolded state of the present invention;

fig. 6 is a schematic structural view of the first antenna mechanism in the unfolded state of the present invention;

fig. 7 is a schematic diagram of an exploded structure of a first antenna mechanism of the present invention;

FIG. 8 is a structural diagram of a second antenna mechanism in an unfolded state according to the present invention;

FIG. 9 is an exploded view of a second antenna mechanism of the present invention;

FIG. 10 is a schematic structural view of the first inner truss, the second inner truss and the middle hinge base of the present invention;

fig. 11 is a schematic view of an exploded structure of the first inner truss, the second inner truss and the middle hinged base of the present invention;

fig. 12 is a diagram showing sequential changes in the relative positions of the shaft sleeve, the first limiting assembly, and the middle shaft when the first antenna mechanism and the second antenna mechanism of the present invention are sequentially deployed;

FIG. 13 is a schematic view of the connection structure of the third antenna mechanism and the locking device in the unfolded state of the present invention;

FIG. 14 is a schematic diagram of an exploded structure of a third antenna mechanism according to the present invention;

FIG. 15 is a diagram illustrating sequential changes in the relative positions of the guide rod and the L-shaped sliding opening when the second antenna mechanism and the third antenna mechanism of the present invention are sequentially deployed;

the reference numerals in the drawings denote: 1. a satellite platform; 101. a storage groove; 102. a first slide bar; 103. a support; 2. a first antenna mechanism; 201. a first antenna; 202. a first outer truss; 203. a first inner truss; 204. a shaft sleeve; 205. a sector groove; 206. a lock hole; 207. a second shaft pin; 3. a second antenna mechanism; 301. a second antenna; 302. a second outer truss; 303. a second inner truss; 304. a collar; 305. a slider; 306. an inner cavity; 307. a first spring; 308. an outer rod; 309. an inner rod; 310. an outer bore; 311. an inner bore; 312. a ring gear; 313. an end cap; 314. a third shaft pin; 4. the middle part is hinged with a base; 5. a middle shaft; 501. a limiting groove; 6. a top hinge mount; 601. a first shaft pin; 7. a side hinged seat; 701. a limiting block; 8. a torsion spring; 9. a third antenna mechanism; 901. a third antenna; 902. a front truss; 903. a rear truss; 904. a lower guide block; 905. a second spring; 906. a guide bar; 907. locking the groove; 908. an upper guide block; 909. a third shaft pin; 10. a concave block; 1001. an L-shaped sliding port; 1002. a rack; 1003. a first slide hole; 11. a limiting sleeve; 1101. a limiting sliding port; 12. a horizontal axis; 13. a limiting rod; 14. a locking plate; 15. a first lock lever; 16. a second lock lever; 17. a tube cover; 18. a second slide bar; 19. a support rod.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The present invention will be further described with reference to the following examples.

Examples

A satellite-borne deployable antenna according to this embodiment, with reference to fig. 2 to 15: the device comprises a satellite platform 1, a first antenna mechanism 2, a second antenna mechanism 3, a third antenna mechanism 9, a locking device and a driver, wherein the first antenna mechanism 2, the second antenna mechanism 3 and the third antenna mechanism 9 can be sequentially unfolded or sequentially folded on the satellite platform 1, and the locking device is used for locking an antenna in an unfolded state or an antenna in a folded state; wherein, the driver is preferably an electromagnet, and the driver drives the locker to move, so that the locker is unlocked.

Specifically, the first antenna mechanism 2 includes a first antenna 201, the second antenna mechanism 3 includes a second antenna 301, the first antenna 201 is rotatably connected to the top of the satellite platform 1 through a first truss set (using fig. 3 as a reference direction, the same applies below), and the second antenna 301 is rotatably connected to the top of the satellite platform 1 through a second truss set.

The first truss group comprises a plurality of first outer trusses 202 and a plurality of first inner trusses 203, and the second truss group comprises a plurality of second outer trusses 302 and a plurality of second inner trusses 303; in this technical solution, two first outer trusses 202, two first inner trusses 203, two second outer trusses 302, and two second inner trusses 303 are preferable, and the two first outer trusses 202 and the two first inner trusses 203 are rotated between the first antenna 201 and the satellite platform 1 in a rectangular arrangement manner, and the two second outer trusses 302 and the two second inner trusses 303 are rotated between the second antenna 301 and the satellite platform 1 in a rectangular arrangement manner.

Specifically, a top hinge base 6 is fixedly installed at each of the four corners of the bottom side of the first antenna 201 and the four corners of the bottom side of the second antenna 301, a first axis pin 601 is fixedly connected to each of the top hinge bases 6, the top end of the first outer truss 202, the top end of the first inner truss 203, the top end of the second outer truss 302 and the top end of the second inner truss 303 are provided with a first pin hole matched with the first axis pin 601, the first axis pin 601 penetrates through the first pin hole respectively and is fixed to the end portion of the first axis pin 601 through a fixing member (not shown), the first axis pin 601 is limited, the first axis pin 601 is prevented from being separated from the top hinge base 6, the first outer truss 202 and the first inner truss 203 are rotatably installed on the first antenna 201, and meanwhile, the second outer truss 302 and the second inner truss 303 are rotatably installed on the second antenna 301.

Four groups of side hinge seats 7 which are arranged in a rectangular shape are fixedly installed at the top of the satellite platform 1, second pin holes are formed in the side hinge seats 7, a second shaft pin 207 matched with the second pin holes is fixedly connected to the bottom end of the first outer truss 202, a third shaft pin 314 matched with the second pin holes is fixedly connected to the bottom end of the second outer truss 302, and the first outer truss 202 and the second outer truss 302 are rotatably installed with the satellite platform 1 by enabling the second shaft pin 207 and the third shaft pin 314 to respectively penetrate through the second pin holes; wherein the first outer truss 202 and the first inner truss 203 are located on the left side of the satellite platform 1, and the second outer truss 302 and the second inner truss 303 are located on the right side of the satellite platform 1.

The top of the satellite platform 1 is symmetrically and fixedly provided with middle hinged seats 4 in the front and back directions, the middle hinged seats 4 are respectively positioned on the middle points of the front and back groups of side hinged seats 7, the opposite sides of the two groups of middle hinged seats 4 are fixedly connected with middle shafts 5, the bottom ends of the first inner trusses 203 and the second inner trusses 303 are mutually rotatably connected, and the bottom ends of the second inner trusses 303 are rotatably connected with the middle shafts 5, so that the first inner trusses 203 and the second inner trusses 303 are rotatably connected with the satellite platform 1; wherein two second inner trusses 303 are located between two first inner trusses 203.

The first antenna 201 and the second antenna 301 are unfolded or folded through the rotating connection of the first outer truss 202 and the first inner truss 203 which are arranged in a rectangular shape and the first antenna 201, and the rotating connection of the second outer truss 302 and the second inner truss 303 which are arranged in a rectangular shape and the second antenna 301; wherein, second antenna 301 folds to draw in at first antenna 201 downside, and first antenna 201 and second antenna 301's size all is less than 1 top size of satellite platform, then first antenna 201 and second antenna 301 fold to draw in behind 1 top of satellite platform, only occupy 1 headspace of satellite platform, do not occupy 1 left and right sides space of satellite platform, then the storage rate is big, need not occupy the inside more space of rocket.

The side hinged seats 7 are provided with limiting blocks 701 for limiting the rotation angles of the first outer truss 202 and the second outer truss 302, so that the first antenna 201 and the second antenna 301 are coplanar after being unfolded.

Meanwhile, in order to realize the automatic expansion of the first antenna 201 and the second antenna 301, the torsion springs 8 are sleeved on the second axis pin and the third axis pin, two ends of each torsion spring 8 are clamped between the side wall of the side hinge base 7 and the bottom end of the first outer truss 202, and two ends of each torsion spring 8 are clamped between the side wall of the side hinge base 7 and the bottom end of the second outer truss 302.

In order to avoid mutual interference when the first antenna 201 and the second antenna 301 are automatically unfolded, a first limiting component which is in limiting fit with the bottom end of the first inner truss 203 and the middle shaft 5 is arranged at the bottom end of the second inner truss 303 respectively, so that the first inner truss 203 and the second inner truss 303 are sequentially unfolded, or the second inner truss 303 and the first inner truss 203 are sequentially folded and furled.

Specifically, the bottom end of the first inner truss 203 is fixedly connected with a shaft sleeve 204, and the first limiting assembly comprises a shaft ring 304 fixedly connected to the bottom end of the second inner truss 303; wherein, the collar 304 is in clearance fit with the sleeve 204 and is sleeved in the sleeve 204, the collar 304 is in clearance fit with the middle shaft 5 and is sleeved outside the middle shaft 5, thereby realizing the rotary connection of the bottom end of the first inner truss 203 and the bottom end of the second inner truss 303, and the rotary connection of the bottom end of the second inner truss 303 and the middle shaft 5.

Wherein, the side wall of the middle shaft 5 is provided with a limit groove 501, the inner side wall of the shaft sleeve 204 is provided with a fan-shaped groove 205, the ring wall of the shaft collar 304 is internally provided with an inner cavity 306, the inner cavity 306 is respectively communicated with the inside and the outside through an inner hole 311 and an outer hole 310, the inner cavity 306 is internally and slidably connected with a slide block 305, two sides of the slide block 305 are respectively and fixedly connected with an outer rod 308 coaxial with the outer hole 310 and an inner rod 309 coaxial with the inner hole 311, the outer rod 308 can penetrate through the outer hole 310 and penetrate into the fan-shaped groove 205, the inner rod 309 can penetrate through the inner hole 311 and penetrate into the limit groove 501, and meanwhile, a first spring 307 which is sleeved outside the inner rod 309 is arranged between the slide block 305 and the inner wall of the inner cavity 306.

As shown in fig. 12, in a folded state, fig. 12a shows the relative positions of the bushing 204, the collar 304 and the middle shaft 5, at this time, the outer rod 308 is limited by the inner side wall of the bushing 204, so that the inner rod 309 is clamped into the limiting groove 501, so as to limit the collar 304 and the middle shaft 5, that is, to fix the second inner truss 303 and the middle hinge base 4 relatively, and further, when the first antenna 201 is unfolded, that is, when the first inner truss 203 rotates counterclockwise, the rotation of the second inner truss 303 is not caused, and further, during the unfolding of the first antenna 201, the second antenna 301 does not synchronously unfold outward.

When the first antenna 201 is completely unfolded, as shown in fig. 12b, at this time, the sector groove 205 is just rotated to communicate with the outer hole 310, under the action of the first spring 307, the slider 305 is moved radially outward along the collar 304, so that the inner rod 309 is retracted into the inner hole 311, the outer rod 308 is inserted into the sector groove 205, the limit of the collar 304 and the middle shaft 5 is released, as shown in fig. 12c, and then, the second inner truss 303 can be rotated clockwise, that is, the second antenna 301 is unfolded outward, so that the first antenna 201 and the second antenna 301 are successively unfolded.

In order to facilitate the second antenna 301 to fold up, so that the outer rod 308 is pushed into the outer hole 310, the outer rod 308 is configured as a wedge head, and the inner side wall of one end of the sector-shaped slot 205 is configured as a wedge surface matched with the wedge head.

Meanwhile, in order to facilitate the installation of the slider 305 and the first spring 307, an end cap 313 is fixedly installed at one end of the collar 304; the side wall of the end cover 313 is provided with a first half inner cavity groove, a first half outer hole groove and a first half inner hole groove which are respectively communicated with the first half inner cavity groove, and one end of the collar 304 corresponding to the end cover 313 is provided with a second half inner cavity groove, a second half outer hole groove and a second half inner hole groove which are respectively communicated with the second half inner cavity groove.

In the present technical solution, the third antenna mechanism 9 includes a third antenna 901, a front truss 902 and a rear truss 903; after being unfolded, the third antenna 901 is located between the first antenna 201 and the second antenna 301, and after being folded, the third antenna 901 is located between the second antenna 301 and the satellite platform 1.

Specifically, the upper and lower ends of the front truss 902 and the rear truss 903 are respectively and rotatably connected with an upper guide block 908 and a lower guide block 904 through a third shaft pin 909, the bottom side of the third antenna 901 is symmetrically and fixedly connected with an upper guide rail in sliding fit with the upper guide block 908, and the top side of the satellite platform 1 is symmetrically and fixedly connected with a lower guide rail between the two second inner trusses 303, so that the upper and lower ends of the front truss 902 and the rear truss 903 are respectively and rotatably and slidably connected with the third antenna 901 and the satellite platform 1; meanwhile, the front truss 902 and the rear truss 903 are connected in a cross rotation manner through the transverse shaft 12, so that the third antenna 901 can move up and down by controlling the two lower guide blocks 904 to move in the opposite direction or in the opposite direction, that is, the third antenna 901 can be unfolded between the first antenna 201 and the second antenna 301 or folded between the second antenna 301 and the satellite platform 1.

In order to ensure that the third antenna 901 moves along the longitudinal direction of the satellite platform 1, a limiting sleeve 11 is fixedly mounted at the top of the satellite platform 1, a limiting sliding port 1101 is formed in the side wall of the limiting sleeve 11, the axis of the limiting sleeve 11 perpendicularly intersects the middle point of the transverse shaft 12, a supporting rod 19 coaxial with the limiting sleeve 11 is perpendicularly and fixedly connected to the transverse shaft 12, and a limiting rod 13 in sliding fit with the limiting sliding port 1101 is perpendicularly and fixedly connected to the bottom end of the supporting rod 19, so that the transverse shaft 12 can be moved and limited, the transverse shaft 12 can only move up and down, and the third antenna 901 is ensured to move along the longitudinal direction of the satellite platform 1.

Meanwhile, the tube cover 17 is arranged at the end of the limiting sleeve 11, so that the tube cover 17 limits the limiting rod 13, the unfolding distance of the third antenna 901 is limited, and the third antenna 901 is just coplanar with the first antenna 201 and the second antenna 301 after being unfolded.

In order to realize the automatic unfolding of the third antenna 901, a baffle is fixedly connected to one end of the lower guide rail, a third slide bar is fixedly connected to the side wall of the lower guide block 904, the third slide bar is in sliding fit with a slide hole formed in the baffle, and a second spring 905 positioned outside the third slide bar is sleeved between the lower guide block 904 and the baffle.

In order to avoid interference caused by automatic unfolding of the third antenna 901 and unfolding of the first antenna 201 and the second antenna 301, a plurality of groups of second limiting assemblies are further connected to the satellite platform 1 in a sliding manner, and the second limiting assemblies are used for limiting and matching the second inner truss 303 with the front truss 902 and the rear truss 903 respectively.

Specifically, the second limiting component comprises a concave block 10; preferably, two sets of concave type pieces 10 are selected according to the technical scheme, then two sets of accommodating grooves 101 are formed in the top side of the satellite platform 1, a plurality of groups of first slide bars 102 are vertically and fixedly connected in the accommodating grooves 101, and a plurality of groups of first slide holes 1003 slidably connected with the first slide bars 102 are formed in the concave type pieces 10, so that the concave type pieces 10 are slidably connected to the top side of the satellite platform 1, and meanwhile, the concave type pieces 10 can be accommodated in the accommodating grooves 101.

An L-shaped sliding opening 1001 is formed in one end of the concave block 10, racks 1002 are respectively arranged at the other ends of the concave block, a gear ring 312 meshed with the racks 1002 is arranged at one end, away from an end cover 313, of the collar 304, and meanwhile a guide rod 906 in sliding fit with the L-shaped sliding opening 1001 is vertically and fixedly connected to the side wall of the lower guide block 904.

When the second antenna 301 is not deployed, as shown in fig. 15e, the guide rod 906 is located at the top end of the L-shaped sliding opening 1001 to limit the lower guide block 904, and the third antenna 901 cannot be deployed upwards; when the second antenna 301 starts to be unfolded, the second inner truss 303 drives the collar 304 to rotate, and the gear ring 312 is matched with the rack 1002, so that the concave block 10 moves upwards, the guide rod 906 moves to the turning point of the L-shaped sliding opening 1001, as shown in fig. 15f, the limit on the lower guide block 904 is removed, under the action of the second spring 905, the two groups of lower guide blocks 904 move oppositely, the guide rod 906 moves along the transverse section of the L-shaped sliding opening 1001, as shown in fig. 15g, so that the third antenna 901 is unfolded upwards, that is, after the second antenna 301 is unfolded, the third antenna 901 is unfolded upwards, and mutual interference is effectively avoided.

In the technical scheme, the locking device comprises a locking plate 14, and a first locking rod 15 and a second locking rod 16 are fixedly connected to the front side of the top end and the rear side of the bottom end of the locking plate 14 respectively.

Wherein, the front end of the receiving groove 101 is fixedly connected with a support 103, the front side of the bottom end of the lock plate 14 is fixedly connected with a second slide bar 18, the second slide bar 18 is in sliding fit with a slide hole on the support 103, so that the lock plate 14 is in sliding connection with the satellite platform 1.

The first inner truss 203 on the front side is provided with a lock hole 206 in plug-in fit with the first lock rod 15, so that after the first antenna 201, the second antenna 301 and the third antenna 901 are folded and folded, the driver is controlled to move the locking device forward, so that the first lock rod 15 passes through the lock hole 206 to limit the first antenna 201, and meanwhile, the second antenna 301 and the third antenna 901 are limited by the first limiting component and the second limiting component respectively, so that the antenna in the overall folded and folded state is locked, and before an unfolding instruction is not received, the first antenna 201, the second antenna 301 and the third antenna 901 are in the folded and folded state.

A lock groove 907 in inserting fit with the second lock rod 16 is formed in the front end of the guide rod 906 on the front side, so that after an unfolding instruction is received, the driver drives the lock plate 14 to move backwards, the first antenna 201 starts to unfold outwards under the action of the torsion spring 8, the driver is controlled to drive the lock plate 14 to move forwards to reset after the first antenna 201 is unfolded completely, and after the third antenna 901 is unfolded completely, the driver is controlled to drive the lock plate 14 to move backwards, so that the second lock rod 16 is inserted into the lock groove 907, the limiting of the lower guide block 904 is realized, the third antenna 901 cannot move downwards, and the third antenna 901 is kept in an unfolded state; meanwhile, in the unfolded state, the third antenna 901 is coplanar with the first antenna 201 and the second antenna 301, so that the first antenna 201 and the second antenna 301 are limited, the first antenna 201 and the second antenna 301 cannot be folded, and the first antenna 201 and the second antenna 301 are kept in the unfolded state.

This satellite-borne deployable antenna is through folding first antenna 201, second antenna 301 and third antenna 901 in proper order and draw in to satellite platform 1 top, do not occupy satellite platform 1 left and right sides space, then the storage rate is big, need not occupy the inside more space of rocket, realize first antenna 201 simultaneously, second antenna 301 and third antenna 901 and expand in proper order, avoid first antenna 201, second antenna 301 and third antenna 901 mutual interference of unfolding the in-process, then effectively guarantee first antenna 201, the complete expansion of second antenna 301 and third antenna 901.

An assembling method of a satellite-borne expandable antenna, referring to fig. 1, the assembling method is according to the above-mentioned satellite-borne expandable antenna, and the assembling method includes the following steps:

s1, fixedly mounting the side hinge seats 7, the middle hinge seat 4 and the limiting sleeve 11 on the satellite platform 1 in sequence, fixedly mounting the driver in the satellite platform 1, and movably mounting the locking device and the concave block 10 on the satellite platform 1;

s2, sequentially and fixedly installing the top hinge base 6 on the first antenna 201 and the second antenna 301 respectively;

s3, respectively rotatably mounting the first outer truss 202 and the first inner truss 203 with the top hinge base 6 on the first antenna 201, respectively rotatably mounting the second outer truss 302 and the second inner truss 303 with the top hinge base 6 on the second antenna 301, and simultaneously movably mounting the front truss 902 and the rear truss 903 on the third antenna 901;

s4, in an unfolded state, the other ends of the front truss 902 and the rear truss 903 are movably mounted on the satellite platform 1, the second springs 905 are mounted between the end of the front truss 902 and the satellite platform 1 and between the end of the rear truss 903 and the satellite platform 1, the transverse shaft 12 is movably mounted between the front truss 902 and the rear truss 903, and the transverse shaft 12 and the limiting sleeve 11 are movably mounted;

s5, in an unfolded state, sleeving one end of a collar 304 into a shaft sleeve 204, movably mounting the collar 304 on a middle shaft 5, and respectively mounting a first outer truss 202, a second outer truss 302 and a torsion spring 8 on a side hinge base 7 to realize the assembly of a first antenna mechanism 2, a second antenna mechanism 3 and a third antenna mechanism 9 in the unfolded state;

and S6, folding and folding the third antenna mechanism 9, the second antenna mechanism 3 and the first antenna mechanism 2 in sequence, and controlling the driver to drive the locking device to move, so that the third antenna mechanism 9, the second antenna mechanism 3 and the first antenna mechanism 2 are locked after being folded and folded.

Through the assembling mode, the first antenna 201, the second antenna 301 and the third antenna 901 are installed and assembled in an unfolded state, and therefore the first antenna 201, the second antenna 301 and the third antenna 901 are convenient to assemble.

The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the corresponding technical solutions.

Claims

1. A satellite-borne deployable antenna comprising a satellite platform (1), characterized in that: the satellite antenna structure comprises a satellite platform (1), and further comprises a first antenna mechanism (2) and a second antenna mechanism (3) which can be sequentially unfolded or sequentially folded and furled on the satellite platform (1), wherein the first antenna mechanism (2) comprises a first antenna (201), the first antenna (201) is rotatably connected to the satellite platform (1) through a first truss group which is arranged in a rectangular manner, the second antenna mechanism (3) comprises a second antenna (301), the second antenna (301) is rotatably connected to one side, facing the first antenna (201), of the satellite platform (1) through a second truss group which is arranged in a rectangular manner, the first truss group comprises a plurality of first outer trusses (202) and a plurality of first inner trusses (203), the second truss group comprises a plurality of second outer trusses (302) and a plurality of second inner trusses (303), and a plurality of groups of middle hinging seats (4) are fixedly mounted on the satellite platform (1), equal fixedly connected with middle part axle (5) on articulated seat (4) in middle part, first antenna (201) one end is kept away from in first inner truss (203) and second inner truss (303) one end is kept away from second antenna (301) one end and is rotated and be connected and spacing cooperation, second antenna (301) one end is kept away from in second inner truss (303) and is rotated with middle part axle (5) and be connected and spacing cooperation for truss (303) expand in proper order in first inner truss (203) and the second, or truss (303) and first inner truss (203) are folded in proper order in messenger's second.

2. The satellite-borne deployable antenna according to claim 1, wherein the first outer truss (202) and the first inner truss (203) are rotatably connected to the first antenna (201) through a top hinge base (6), the second outer truss (302) and the second inner truss (303) are rotatably connected to the second antenna (301) through a top hinge base (6), one ends of the first outer truss (202) and the second outer truss (302) far away from the first antenna (201) and the second outer truss (302) far away from the second antenna (301) are rotatably connected to the satellite platform (1) through side hinge bases (7), and the side hinge bases (7) are provided with limiting blocks (701) for limiting rotation angles of the first outer truss (202) and the second outer truss (302).

3. The satellite-borne deployable antenna according to claim 2, wherein torsion springs (8) are arranged between the end of the first outer truss (202) far away from the first antenna (201) and the end of the second outer truss (302) far away from the second antenna (301) and the side hinge base (7).

4. The satellite-borne deployable antenna according to claim 1, wherein a shaft sleeve (204) is fixedly connected to one end of the first inner truss (203) far away from the first antenna (201), and a first limiting assembly which is in limiting fit with the shaft sleeve (204) and the middle shaft (5) respectively is arranged at one end of the second inner truss (303) far away from the second antenna (301).

5. The satellite-borne deployable antenna according to claim 4, wherein the middle shaft (5) is provided with a limiting groove (501), the inner side wall of the shaft sleeve (204) is provided with a fan-shaped groove (205), the first limiting assembly comprises a shaft collar (304) and a sliding block (305), the shaft collar (304) is fixedly connected to one end, far away from the second antenna (301), of the second inner truss (303), the shaft collar (304) is rotatably connected into the shaft sleeve (204), an inner cavity (306) is formed in the ring wall of the shaft collar (304), the sliding block (305) is slidably connected into the inner cavity (306), a first spring (307) is arranged between the sliding block and the inner wall of the inner cavity (306), and two sides of the sliding block (305) are respectively provided with an outer rod (308) capable of penetrating into the fan-shaped groove (205) and an inner rod (309) capable of penetrating into the limiting groove (501).

6. The satellite-borne deployable antenna according to claim 5, further comprising a third antenna mechanism (9), wherein the first antenna mechanism (2), the second antenna mechanism (3) and the third antenna mechanism (9) can be sequentially deployed or sequentially folded and furled on the satellite platform (1), the third antenna mechanism (9) comprises a third antenna (901), a front truss (902) and a rear truss (903), after being deployed, the third antenna (901) is located between the first antenna (201) and the second antenna (301), after being folded and furled, the third antenna (901) is located between the second antenna (301) and the satellite platform (1), the front truss (902) and the rear truss (903) are mutually crossed and rotationally connected, and both ends of the front truss (902) and the rear truss (903) are respectively movably connected with the third antenna (901) and the satellite platform (1), the satellite platform (1) is further connected with a plurality of groups of second limiting assemblies in a sliding mode, and the second limiting assemblies are used for limiting and matching the second inner truss (303) with the front truss (902) and the rear truss (903) respectively.

7. The satellite-borne deployable antenna according to claim 6, wherein the second limiting assembly comprises a concave block (10), one end of the concave block (10) is provided with an L-shaped sliding opening (1001), the other end of the concave block (10) is in tooth transmission fit with the end of the shaft collar (304), one end of the front truss (902) away from the third antenna (901) and one end of the rear truss (903) away from the third antenna (901) are both rotatably connected with a lower guide block (904) in sliding connection with the satellite platform (1), a second spring (905) is arranged between the side wall of the lower guide block (904) and the satellite platform (1), and the side wall of the lower guide block (904) is further provided with a guide rod (906) in sliding fit with the L-shaped sliding opening (1001).

8. The satellite-borne deployable antenna according to claim 7, wherein the satellite platform (1) is further fixedly provided with a limiting sleeve (11), a limiting sliding opening (1101) is formed in a side wall of the limiting sleeve (11), the front truss (902) and the rear truss (903) are in cross rotation connection through a transverse shaft (12), and a limiting rod (13) sliding in the limiting sliding opening (1101) is fixedly connected to the middle of the transverse shaft (12).

9. The satellite-borne deployable antenna according to claim 8, further comprising a locker and a driver for driving the locker to move, wherein the locker is used for locking the antenna in the deployed state or the antenna in the folded state, the locker comprises a locking plate (14) sliding on the satellite platform, and a first locking bar (15) and a second locking bar (16) respectively fixed at two ends of the locking plate (14) and at different sides of the locking plate, one of the first inner trusses (203) is provided with a locking hole (206) in plug-in fit with the first locking bar (15), and one of the guide rods (906) is provided with a locking groove (907) in plug-in fit with the second locking bar (16).

10. The method for assembling the deployable antenna on board a satellite according to any one of claims 1 to 9, wherein the method comprises the following steps:

s1, sequentially and fixedly installing the side hinge seat (7), the middle hinge seat (4) and the limiting sleeve (11) on the satellite platform (1), fixedly installing the driver in the satellite platform (1), and movably installing the locking device and the concave block (10) on the satellite platform (1);

s2, sequentially and fixedly installing the top hinged seat (6) on the first antenna (201) and the second antenna (301) respectively;

s3, respectively rotatably mounting a first outer truss (202) and a first inner truss (203) with a top hinged base (6) on a first antenna (201), respectively rotatably mounting a second outer truss (302) and a second inner truss (303) with the top hinged base (6) on a second antenna (301), and simultaneously movably mounting a front truss (902) and a rear truss (903) on a third antenna (901);

s4, in an unfolded state, the other ends of the front truss (902) and the rear truss (903) are movably mounted on the satellite platform (1), the second springs (905) are mounted between the end part of the front truss (902) and the satellite platform (1) and between the end part of the rear truss (903) and the satellite platform (1), the transverse shaft (12) is movably mounted between the front truss (902) and the rear truss (903), and the transverse shaft (12) and the limiting sleeve (11) are movably mounted at the same time;

s5, in the unfolded state, one end of a collar (304) is sleeved into a shaft sleeve (204), the collar (304) is movably mounted on a middle shaft (5), and then a first outer truss (202), a second outer truss (302) and a torsion spring (8) are respectively mounted on a side hinge seat (7), so that the first antenna mechanism (2), the second antenna mechanism (3) and the third antenna mechanism (9) are assembled in the unfolded state;

s6, folding and folding the third antenna mechanism (9), the second antenna mechanism (3) and the first antenna mechanism (2) in sequence, and controlling the driver to drive the locking device to move, so that the third antenna mechanism (9), the second antenna mechanism (3) and the first antenna mechanism (2) are locked after being folded and folded.