A deployable device for a planar array antenna of a satellite in an overhead configuration

Abstract

The application discloses a top-mounted configuration satellite-borne planar array antenna unfolding device and belongs to the technical field of satellite-borne radars. In a folded state, each antenna plate in a left wing planar antenna and a right wing planar antenna is laminated and fixed to the top of a satellite body through a compression release device. After the compression release device is released from compression, the left wing planar antenna and the right wing planar antenna are unfolded to the two sides of the top of the satellite body through a left wing unfolding mechanism and a right wing unfolding mechanism respectively. The device makes the antenna folded on the top of the satellite body, so that the space in the fairing can be completely used for the envelope of the load antenna. Compared with the load folded on the side of the satellite body, the top-mounted configuration satellite-borne planar array antenna effectively solves the problem that the fairing cannot meet the satellite envelope requirement when the number of antenna plates increases due to the side placement of the traditional satellite-borne planar array antenna.

Description

Technical Field

[0001] This invention belongs to the field of spaceborne radar technology, specifically relating to a top-mounted spaceborne planar array antenna deployment device. Background Technology

[0002] Resolution is the most important performance indicator for spaceborne radar, and the most effective way to improve imaging resolution is to increase the size of the radar antenna array. For example, in the RADARSAT-2 satellite launched by Canada in 2007, the maximum resolution of the radar antenna array can reach 1m, and its deployed size has reached 15m × 1.5m. To meet increasingly higher resolution requirements, radar antenna arrays are becoming larger and larger. However, due to the limited envelope volume of the radome for satellite launch, the need for large antenna deployment technology is becoming increasingly urgent.

[0003] Application No. CN201611118145.7, entitled "An H-configuration Deployable Antenna Mechanism for Spaceborne Satellites," discloses two antenna panels: a left-wing planar antenna and a right-wing planar antenna. These panels, when folded, are located at the top of the satellite. Application No. CN201610556711.6, entitled "A Support Truss for Spaceborne Planar Antennas," discloses an antenna truss capable of folding the planar array antenna to both sides of the satellite. Application No. CN201610556701.2, entitled "A Folding and Deploying Mechanism for Multi-Panel Deployable Antennas on Spacecraft," employs an antenna deployment truss similar to that of the Canadian RADARSAT-1 satellite to deploy the two antenna arrays of a single wing. In 2011, Wang Yan et al. from Harbin Institute of Technology proposed a planar antenna support mechanism configuration that places the two wing antennas in a folded state on both sides of a satellite (see "Comprehensive Design of Deployable Planar Antenna Support Mechanism Configuration," Harbin Institute of Technology, Wang Yan, 2011), which achieves the deployment of four antenna panels on a single wing.

[0004] However, as the number of antenna arrays increases, in order to compress the antenna arrays within a limited fairing envelope, the antenna arrays must be divided into multiple antenna plates. As the number of antenna plates increases, the thickness of the antenna plates in the compressed state continues to increase. If the above-mentioned side-mounted antenna plate method is adopted, the diameter of the fairing of the existing size will eventually need to be increased, otherwise it will not be able to meet the satellite's envelope requirements. Summary of the Invention

[0005] In view of this, the present invention provides a top-mounted configuration spaceborne planar array antenna deployment device, which solves the problem that existing radomes cannot meet the satellite envelope requirements when the number of antenna plates increases due to the side-mounted configuration of traditional spaceborne planar array antennas. It can meet the satellite envelope requirements with existing radomes while having more antenna plates than side-mounted antennas.

[0006] The present invention adopts the following technical solution:

[0007] A top-mounted spaceborne planar array antenna deployment device includes a left-wing deployment mechanism, a left-wing planar antenna, a right-wing deployment mechanism, and a right-wing planar antenna.

[0008] The left wing deployment mechanism is hinged to the star via a rotary joint;

[0009] The left-wing planar antenna includes multiple antenna plates connected in series, and the antenna plates are connected to the left-wing deployment mechanism via a root hinge;

[0010] The right wing deployment mechanism and the left wing deployment mechanism are symmetrical about the celestial body;

[0011] The right-wing planar antenna and the left-wing planar antenna are symmetrical about the star.

[0012] In the retracted state, the antenna plates of the left and right wing planar antennas are stacked and pressed against the top of the star by a pressing and releasing device; after the pressing and releasing device is released, the left and right wing planar antennas are respectively deployed to the top sides of the star by the left and right wing deployment mechanisms.

[0013] Furthermore, the left wing deployment mechanism includes a flip-up plate, a deployable truss, and a support link;

[0014] The flip plate is hinged to the top left side of the star via the rotary joint;

[0015] The deployable truss is connected to the left wing planar antenna;

[0016] One end of the support link is hinged to the deployable truss, and the other end is hinged to the flip plate via a support hinge;

[0017] In the folded state, the deployable truss and the supporting rod are stacked together with each antenna plate in the left wing planar antenna, and the flip plate is close to the left end face of the left wing planar antenna; in the unfolded state, the flip plate is flipped 180° and close to the left end face of the star, and the deployable truss and the supporting rod are unfolded to support the unfolded left wing planar antenna.

[0018] Furthermore, the deployable truss includes a quadrangular pyramidal truss corresponding one-to-one with each of the antenna plates in the left wing planar antenna, and connecting rods connecting each quadrangular pyramidal truss;

[0019] The quadrangular pyramidal truss includes four antenna plate outer frame members, two outer long diagonal members, and two intermediate truss connecting members. The four antenna plate outer frame members are connected end to end to form a rectangular frame and are set on the four sides of the antenna plate. One end of the two outer long diagonal members and the two intermediate truss connecting members are respectively hinged to the four corners of the rectangular frame, and the other end is hinged to each other to form the vertices of the quadrangular pyramidal truss. The vertices of the two quadrangular pyramidal trusses corresponding to each pair of adjacent antenna plates of the left wing planar antenna are hinged through antenna plate joints.

[0020] The connecting rod connects each of the antenna board connectors;

[0021] One end of the support link is hinged to the deployable truss by being hinged to the antenna plate joint closest to the left end of the star.

[0022] Furthermore, the intermediate truss link includes two members hinged together by inter-link hinges;

[0023] The connecting rods include multiple rods that are sequentially hinged end to end by inter-rod hinges.

[0024] The support link comprises two rods hinged together by an inter-rod hinge.

[0025] Furthermore, the inter-bar hinge is provided with a drive source.

[0026] Furthermore, the driving source of the inter-bar hinge is a coil spring.

[0027] Furthermore, the supporting hinge is provided with a drive source.

[0028] Furthermore, the driving source for the supporting hinge is a coil spring.

[0029] Furthermore, the left-wing planar antenna comprises n antenna plates connected in series;

[0030] The antenna plates of the left wing planar antenna are hinged together by inter-plate hinges equipped with a driving source.

[0031] n is an even number.

[0032] Furthermore, the left-wing planar antenna alternately uses a coil spring drive source and a motor drive source as the drive source for the corresponding inter-plate hinge from right to left.

[0033] Beneficial effects:

[0034] 1. The left wing deployment mechanism is hinged to the star via a rotary joint; the left wing planar antenna includes multiple antenna plates connected in series, and the antenna plates are connected to the left wing deployment mechanism via a root hinge; the right wing deployment mechanism is symmetrical to the left wing deployment mechanism about the star; the right wing planar antenna is symmetrical to the left wing planar antenna about the star; in the retracted state, the antenna plates of the left and right wing planar antennas are stacked and fixed to the top of the star via a clamping and releasing device; after the clamping and releasing device is released, the left wing planar antenna and the right wing planar antenna are deployed to the top sides of the star via the left wing deployment mechanism and the right wing deployment mechanism, respectively.

[0035] Thus, when the antenna is folded up at the top of the satellite, the space inside the fairing can be used entirely for the envelope of the payload antenna. Compared with the payload being folded up on the side of the satellite, this top-mounted configuration of the spaceborne planar array antenna effectively solves the problem that the fairing cannot meet the satellite envelope requirements when the number of antenna plates increases due to the side-mounted traditional spaceborne planar array antenna. This top-mounted configuration of the spaceborne planar array antenna can meet the envelope requirements of large-size planar array antennas. Moreover, the height of the satellite structure is reduced after deployment, which can reduce the control requirements for attitude and orbit.

[0036] 2. The quadrangular pyramidal truss includes four antenna panel outer frame members, two outer long diagonal members, and two intermediate truss connecting rods. The four antenna panel outer frame members are connected end to end to form a rectangular frame, which is then set on the four sides of the antenna panel. One end of the two outer long diagonal members and the two intermediate truss connecting rods are respectively hinged to the four corners of the rectangular frame, and the other end is hinged to each other to form the vertices of the quadrangular pyramidal truss. The vertices of the two quadrangular pyramidal trusses corresponding to each pair of adjacent antenna panels of the left wing planar antenna are hinged through antenna panel joints. Connecting rods connect the antenna panel joints. One end of the supporting connecting rod is hinged to the deployable truss by being hinged to the antenna panel joint closest to the left end of the star.

[0037] In this way, the radar's own structural frame can be fully utilized to withstand lateral bending moments and shear forces, resulting in high load-bearing efficiency. This allows for an increase in the number of antenna panels. Furthermore, the modular design of the quadrangular pyramid truss can adapt to different working conditions when the number of antenna panels varies. In addition, the connecting rods connect the joints of each antenna panel, which is equivalent to connecting the quadrangular pyramid trusses corresponding to each antenna panel into a whole structure, thus enhancing the rigidity of the left-wing planar antenna.

[0038] 3. The intermediate truss connecting rod consists of two members hinged together by inter-member hinges; the connecting member consists of multiple members hinged together end to end by inter-member hinges; the supporting connecting rod consists of two members hinged together by inter-member hinges.

[0039] In this way, the number of members in the intermediate truss connecting rods and support connecting rods is reduced, which can reduce the structural complexity. The number of mutually hinged members in the connecting rods can be flexibly adjusted according to the number of antenna plates, so that the truss structure can adapt to different working conditions with different numbers of antenna plates, that is, it can realize the redesign of the antenna plate unfolding length.

[0040] 4. The drive source for the inter-bar hinge is a coil spring, which is more compact and lighter than a motor drive source.

[0041] 5. The drive source supporting the hinge is a coil spring, which is more compact and lighter than a motor drive source.

[0042] 6. The left-wing planar antenna alternately uses spring drive sources and motor drive sources as the drive sources for the corresponding inter-plate hinges from right to left. In this way, compared with using motor drive sources for all inter-plate hinges, the structure is more compact and lighter. Attached Figure Description

[0043] Figure 1 This is a schematic diagram of the structure of a top-mounted spaceborne planar array antenna deployment device in the retracted state, according to an embodiment of the present invention.

[0044] Figure 2 This is a schematic diagram of the structure of a top-mounted spaceborne planar array antenna deployment device in the deployed state, according to an embodiment of the present invention.

[0045] Figure 3 yes Figure 1 Schematic diagram of the connection relationship between the left-side planar antenna and the truss;

[0046] Figure 4 yes Figure 1 Schematic diagram of the structure of the flip-up plate;

[0047] Figure 5 yes Figure 3 Structural diagram of the connecting rod;

[0048] Figure 6 yes Figure 3 A schematic diagram showing the connection relationship between the central support link and the quadrangular pyramid truss;

[0049] Figure 7 A schematic diagram illustrating the principle of deploying the left-wing planar antenna according to an embodiment of the present invention;

[0050] Among them, 1-star body, 2-fixed antenna plate, 3-left wing planar antenna, 301-antenna plate, 302-inter-plate hinge, 4-right wing planar antenna, 501-flip plate, 502-quadrangular pyramidal truss, 502A-antenna plate outer frame member, 502B-outer long diagonal member, 502C-middle truss long member, 502D-middle truss short member, 503-connecting member, 503A-connecting short member, 503B-connecting long member, 504-supporting connecting rod, 504A-supporting short member, 504B-supporting long member, 6-pressing release device, 7-root hinge, 8-rotation joint, 9-inter-rod hinge, 10-connecting rod joint, 11-truss support, 12-antenna plate joint, 13-supporting hinge. Detailed Implementation

[0051] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0052] like Figures 1 to 6 As shown, a top-mounted configuration spaceborne planar array antenna deployment device includes a left-wing deployment mechanism, a left-wing planar antenna 3, a right-wing deployment mechanism, and a right-wing planar antenna 4. Because the right-wing deployment mechanism and the left-wing deployment mechanism are symmetrical about the satellite 1, and the right-wing planar antenna 4 and the left-wing planar antenna 3 are symmetrical about the satellite 1, this embodiment will be described using the left-wing deployment mechanism and the left-wing planar antenna 3 as examples, as detailed below:

[0053] The left wing deployment mechanism is hinged to the star body 1 via a rotary joint; the left wing planar antenna 3 is connected to the left wing deployment mechanism via a root hinge 7; in the retracted state, the left wing planar antenna 3 and the right wing planar antenna 4 are stacked and fixed to the top of the star body 1 via a pressing and releasing device 6; after the pressing and releasing device is released, the pressing and releasing device 6 releases the constraint on the left wing planar antenna 3 and the right wing planar antenna 4, and the left wing planar antenna 3 and the right wing planar antenna 4 are deployed to the left and right sides of the top of the star body 1 via the left wing deployment mechanism and the right wing deployment mechanism, respectively.

[0054] Thus, when the antenna is folded up, it is located at the top of satellite 1, allowing the space inside the fairing to be fully utilized for the envelope of the payload antenna. This makes full use of the upper space of the fairing. Compared with the payload antenna being folded up on the side of satellite 1, this top-mounted configuration of the spaceborne planar array antenna effectively solves the problem that the fairing cannot meet the satellite envelope requirements when the number of antenna plates increases due to the side-mounted traditional spaceborne planar array antenna. This top-mounted configuration of the spaceborne planar array antenna can meet the envelope requirements of large-size planar array antennas. Moreover, the height of the satellite structure is reduced after deployment, which can reduce the control requirements for attitude and orbit.

[0055] Specifically, refer to 1 and Figure 2The left-wing deployment mechanism includes a flip-up plate 501, a deployable truss, and a support rod 504. The flip-up plate 501 is hinged to the top of the satellite 1 via a rotary joint. The deployable truss is connected to the left-wing planar antenna 3. One end of the support rod 504 is hinged to the deployable truss, and the other end is hinged to the flip-up plate 501 via a support hinge 13. In the retracted state, the deployable truss and support rod 504 are folded and stacked together with the antenna plate 301. (Refer to...) Figure 7 (The arrows in the diagram indicate the unfolding direction). This is a schematic diagram of the unfolding principle of the left wing planar antenna 3. Its folding process is the reverse of the unfolding process. The flip plate 501 is pressed against the left end face of the folded left wing planar antenna 3. In the unfolded state, the flip plate 501 is flipped outward by 180° and pressed against the left end face of the star 1. The unfoldable truss and support rod 504 are unfolded to support the unfolded left wing planar antenna 3.

[0056] More specifically, refer to Figure 3 The left-wing planar antenna 3 includes multiple antenna plates 301 connected sequentially in a transverse direction. The deployable truss includes a quadrangular pyramidal truss 502 corresponding one-to-one with each antenna plate 301 in the left-wing planar antenna 3, and connecting rods 503 that connect adjacent quadrangular pyramidal trusses 502; wherein, referring to Figure 6 Each quadrangular pyramidal truss 502 includes four antenna plate outer frame members 502A, two outer long diagonal members 502B, and two intermediate truss connecting members. The four antenna plate outer frame members 502A are connected end to end to form a rectangular frame, which serves as the base of the quadrangular pyramidal truss 502 and is set on the four sides of the antenna plate 301. One end of the two outer long diagonal members 502B and the two intermediate truss connecting members are respectively hinged to the four corners of the rectangular frame, and the other ends are hinged to each other to form the vertices of the quadrangular pyramidal truss 502, and refer to Figure 2 Starting from the end closest to the satellite, the left-wing planar antenna 3 consists of two adjacent antenna panels 301 forming a group. The vertices of the two corresponding quadrangular pyramidal trusses 502 in each group are hinged through antenna panel joints 12. Connecting rods 503 connect the joints of each antenna panel 301. One end of the supporting rod 504 is hinged to the adjacent antenna panel joint 12, thus achieving hinged connection with the deployable truss. In this way, the radar's own structural frame can be fully utilized to withstand lateral bending moments and shear forces, resulting in high load-bearing efficiency. This allows for an increase in the number of antenna panels 301. Moreover, the modular design of the quadrangular pyramidal trusses 502 can adapt to different operating conditions when the number of antenna panels 301 varies. In addition, the connecting rods 503 connect the joints 12 of each antenna panel, which is equivalent to connecting the quadrangular pyramidal trusses 502 corresponding to each antenna panel 301 into a whole structure, enhancing the rigidity of the left-wing planar antenna 3.

[0057] Moreover, referencing Figure 5 and Figure 6The intermediate truss connecting rod includes two members hinged together by inter-rod hinges 9, namely intermediate truss long rod 502C and intermediate truss long rod 502D. The connecting rod 503 includes multiple connecting long rods 503B sequentially hinged together by inter-rod hinges 9, and connecting short rods 503A located at both ends and hinged to the connecting long rods 503B at both ends by inter-rod hinges 9. The supporting connecting rod 504 includes two members hinged together by inter-rod hinges 9, namely supporting short rod 504A and supporting long rod 504B. Thus, the number of members in the intermediate truss connecting rod and the supporting connecting rod 504 is relatively small, reducing structural complexity. The number of mutually hinged members in the connecting rod 503 can be flexibly adjusted according to the number of antenna panels 301, allowing the truss structure to adapt to different numbers of antenna panels 301, i.e., enabling redesign of the unfolded length of 301.

[0058] In this embodiment, the left-wing planar antenna 3 has an even number of antenna plates 301, specifically six antenna plates 301 hinged together by inter-plate hinges 302 with a driving source. Each antenna plate 301 is 4.6m long, 2.9m wide, and 135mm thick. The left-wing planar antenna 3, from right to left, consists of the first antenna plate, the second antenna plate, the third antenna plate, the fourth antenna plate, the fifth antenna plate, and the sixth antenna plate. In this embodiment, starting from the end closest to the star, the left-wing planar antenna 3 is divided into three groups of two adjacent antenna plates 301. That is, the first antenna plate and the second antenna plate form one group, the third antenna plate and the second antenna plate form another group, and so on. Four antenna plates form a group, and the fifth and sixth antenna plates form another group. The end of the first antenna plate facing away from the second antenna plate is hinged to the flip plate 501 via the root hinge 7. Moreover, the left wing planar antenna 3 is alternately equipped with a coil spring drive source (i.e., the hinge is equipped with a coil spring, which accumulates energy in the retracted state and releases energy in the unfolded state) and a motor drive source as the drive source for the corresponding inter-plate hinge 302 from right to left. In this way, compared with all inter-plate hinges 302 being equipped with motor drive sources, the structure is more compact and lighter. Compared with all inter-plate hinges 302 being equipped with coil spring drive sources, the unfolding speed of the antenna plate 301 can be precisely controlled by controlling the motor. Specifically, in this embodiment, the driving source corresponding to the inter-plate hinge 302 between the first antenna plate and the second antenna plate is a coil spring driving source; the driving source corresponding to the inter-plate hinge 302 between the second antenna plate and the third antenna plate is a motor driving source; the driving source corresponding to the inter-plate hinge 302 between the third antenna plate and the fourth antenna plate is a coil spring driving source; the driving source corresponding to the inter-plate hinge 302 between the fourth antenna plate and the fifth antenna plate is a coil spring driving source; and the driving source corresponding to the inter-plate hinge 302 between the fifth antenna plate and the sixth antenna plate is a coil spring driving source.

[0059] Reference Figure 6The inter-plate hinge 302 between the first and second antenna plates is connected to two corners of the rectangular frame formed by the end-to-end connection of the antenna plate outer frame members 502A. The other two corners of the rectangular frame are connected to the antenna plate 301 via truss supports 11. Similarly, the inter-plate hinge 302 between the third and fourth antenna plates is connected to two corners of the rectangular frame, and the inter-plate hinge 302 between the fifth and sixth antenna plates is also connected to two corners of the rectangular frame. Furthermore, in this embodiment, the drive source for both the inter-plate hinge 302 and the support hinge 13 is a coil spring. Compared to a motor drive source, the coil springs provide a more compact structure and lighter weight.

[0060] In addition, this embodiment also includes a fixed antenna plate 2, which is fixedly connected to the top of the satellite 2. In the unfolded state, the left wing planar antenna 3, the right wing planar antenna 4, and the fixed antenna plate 2 are coplanar. Moreover, the aforementioned rotating joint, rod hinge 9, and plate hinge 302 automatically lock when rotated 180°, and the root hinge automatically locks when rotated 90°. In the unfolded state, the distance between the leftmost end of the left wing planar antenna 3 and the rightmost end of the right wing planar antenna 4 is 56m. In the folded state, the overall dimensions of the entire device and the satellite 1 are 4.9m long × 2.9m wide × 2.5m high, which meets the requirements of an ultra-large area antenna array.

[0061] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A top-mounted spaceborne planar array antenna deployment device, characterized in that, It includes a left wing deployment mechanism, a left wing planar antenna, a right wing deployment mechanism, and a right wing planar antenna; The left wing deployment mechanism is hinged to the star via a rotary joint; The left-wing planar antenna includes multiple antenna plates connected in series, and the antenna plates are connected to the left-wing deployment mechanism via a root hinge; The right wing deployment mechanism and the left wing deployment mechanism are symmetrical about the celestial body; The right-wing planar antenna and the left-wing planar antenna are symmetrical about the star. In the retracted state, the antenna plates of the left and right wing planar antennas are stacked and pressed against the top of the star by a pressing and releasing device; after the pressing and releasing device is released, the left and right wing planar antennas are respectively deployed to the top sides of the star by the left and right wing deployment mechanisms. The left-wing deployment mechanism includes a flip-up plate, a deployable truss, and supporting rods. The deployable truss includes a quadrangular pyramidal truss corresponding to each antenna plate in the left-wing planar antenna, and connecting rods connecting each quadrangular pyramidal truss. The quadrangular pyramidal truss includes four antenna plate outer frame rods, two outer long diagonal rods, and two intermediate truss connecting rods. The four antenna plate outer frame rods are connected end to end to form a rectangular frame and are set on the four sides of the antenna plate. One end of the two outer long diagonal rods and the two intermediate truss connecting rods are respectively hinged to the four corners of the rectangular frame, and the other ends are hinged to each other to form the vertices of the quadrangular pyramidal truss. The vertices of the two quadrangular pyramidal trusses corresponding to each pair of adjacent antenna plates of the left-wing planar antenna are hinged through antenna plate joints. The connecting rods connect each antenna plate joint. One end of the supporting rod is hinged to the deployable truss by being hinged to the antenna plate joint closest to the left end of the star.

2. The top-mounted configuration spaceborne planar array antenna deployment device according to claim 1, characterized in that, The flip plate is hinged to the top left side of the star via the rotary joint; The deployable truss is connected to the left wing planar antenna; One end of the support link is hinged to the deployable truss, and the other end is hinged to the flip plate via a support hinge; In the retracted state, the deployable truss and the supporting rod are stacked together with each antenna plate in the left wing planar antenna, and the flip plate is in close contact with the left end face of the left wing planar antenna; In the deployed state, the flip plate rotates 180° and is pressed against the left end face of the star. The deployable truss and the supporting rod unfold to support the deployed left wing planar antenna.

3. The top-mounted configuration spaceborne planar array antenna deployment device according to claim 1, characterized in that, The intermediate truss link consists of two members hinged together by an inter-link hinge. The connecting rods include multiple rods that are sequentially hinged end to end by inter-rod hinges. The support link comprises two rods hinged together by an inter-rod hinge.

4. The top-mounted configuration spaceborne planar array antenna deployment device according to claim 3, characterized in that, The inter-bar hinge is equipped with a drive source.

5. The top-mounted configuration spaceborne planar array antenna deployment device according to claim 4, characterized in that, The drive source for the inter-bar hinge is a coil spring.

6. The top-mounted configuration spaceborne planar array antenna deployment device according to claim 2, characterized in that, The supporting hinge is equipped with a drive source.

7. The top-mounted spaceborne planar array antenna deployment device according to claim 6, characterized in that, The drive source for the supporting hinge is a coil spring.

8. A top-mounted configuration spaceborne planar array antenna deployment device according to any one of claims 1 to 7, characterized in that, The left-wing planar antenna comprises n antenna plates connected in series. The antenna plates of the left wing planar antenna are hinged together by inter-plate hinges equipped with a driving source. n is an even number.

9. A top-mounted spaceborne planar array antenna deployment device according to claim 8, characterized in that, The left wing planar antenna is alternately equipped with a coil spring drive source and a motor drive source from right to left as the drive source for the corresponding inter-plate hinge.

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