Power metasurface antenna pressing device for stacked satellites

Abstract

The invention provides a power metasurface antenna pressing device for stacked satellites, which relates to the field of satellite antenna pressing, and comprises an antenna reflecting surface, an auxiliary reflecting surface, a frame, an antenna frame unfolding mechanism and an antenna frame pressing mechanism, one end of the frame is folded and pressed on one side face of the stacked satellite body through the antenna frame unfolding mechanism, an antenna frame pressing mechanism is arranged on the periphery of the frame, and the frame is pressed on the surface of the stacked satellite body through the antenna frame pressing mechanism. According to the method, the strict size enveloping requirement of the stacked satellite on the load is met; the antenna feed source is positioned near the antenna pressing rod, so that the antenna efficiency is improved; the antenna metasurface unit, the feed source and the antenna subreflector are all located in the same frame and are integrally unfolded, the antenna unfolding precision is well guaranteed, and the application range of the antenna is expanded.

Description

Technical Field

[0001] The present invention relates to the field of satellite antenna compression, and in particular to a power metasurface antenna compression device for stacked satellites, and in particular to a large-caliber power metasurface antenna compression device suitable for stacked, flat satellites. Background Art

[0002] The traditional "multiple satellites in one rocket" launch mode relies on satellite adapters with large mass and volume, which makes insufficient use of the precious space in the fairing and limits the number of satellites that can be launched at one time. Stacked satellite launch is a new "multiple satellites in one rocket" launch mode. Stacked satellites no longer require special satellite adapters, which saves carrying capacity while making full use of the available space in the fairing of the launch vehicle. Through reasonable design, the number of satellites that can be launched at one time can be exceeded, and the launch efficiency can be improved.

[0003] Stacked satellites have strong constraints on satellite height due to their configuration and layout design. Satellites are generally flat in configuration. When carrying large-aperture high-power metasurface antennas, the antenna payload is required to be reasonably gathered and compacted, with a lower antenna height, to facilitate multi-satellite stacking. Therefore, it is required to invent a compaction strategy for carrying large-aperture high-power metasurface antennas that meets the requirements of low antenna folding height, high-precision antenna installation, and simple and reliable installation process.

[0004] The closest existing technical achievements are:

[0005] (1) "Spaceborne deployable antenna clamping device", patent application number: CN201710877190.9, publication number: CN107808991A. This patent discloses a spaceborne deployable antenna clamping device, which includes a satellite antenna mounting bracket assembly, a clamping seat, and a clamping rod; one side of the antenna mounting bracket assembly is fixed to the clamping seat by a clamping rod, and a pyrotechnic cutter is located on the side of the clamping seat; the other side of the antenna mounting bracket assembly is fixed to an antenna deployment device. The present invention provides a high-rigidity clamping device for a columnar antenna; the present invention requires the least number of power supply circuits, is light in weight, and has high reliability. The patent does not involve stacked satellites, nor does it involve secondary deployment of a sub-reflector.

[0006] (2) "A flexible clamping mechanism and its clamping method", patent application number: CN201810682946.9, publication number: CN108890548A. This patent discloses a flexible clamping mechanism and its clamping method, the flexible clamping mechanism is composed of a plurality of flexible clamping units, the flexible clamping unit includes a shell, a rubber wheel, a spring, and a connecting mechanism; the flexible clamping units are connected to each other by pins and can rotate around the pins; the angles between adjacent flexible clamping units are adjusted according to the skin shape and then locked; pull rings are provided at both ends of the flexible clamping mechanism, and the flexible clamping mechanism is fixed to the frame as a whole by a tightening clamp fixed on the tooling frame, and the clamping of the skin with different curvatures is achieved by combining a plurality of flexible clamping units at different angles. This patent is applicable to aviation flexible clamping mechanisms, not to stacked satellites.

[0007] (3) "Peripheral clamping and locking device for large-scale space deployment structure and clamping method thereof", patent application number: CN201611046403.5, publication number: CN106379557A. The patent discloses that the present invention provides a peripheral clamping and locking device for large-scale space deployment structure, comprising: a housing; a worm fixed on one side of the housing; a worm wheel meshing with the worm and connected to the housing through the worm wheel rotating shaft; a clamping lock hook, one end of which is connected to the housing so that the clamping lock hook rotates in the housing, and the other end is provided with a slide groove, and the end of the clamping lock hook acts on the clamping point; a swing rod, one end of which is fixedly connected to the worm wheel rotating shaft and the other end is slidably connected to the slide groove of the clamping lock hook. The present invention also provides a clamping method for a peripheral clamping and locking device for large-scale space deployment structure. The peripheral clamping and locking device provided by the present invention is installed and fixed on the periphery of the folding array surface, so that the deployment mechanism has a compact and reliable structure during the launch stage, and can avoid the effective working surface of the array surface, and has a simple mechanical structure and is easy to operate. This patent is applicable to large space deployment structures and peripheral clamping and locking devices, but is not applicable to stacked satellites and antenna loads with strict restrictions on the clamping height.

[0008] (4) "A flexible clamping mechanism and its clamping method", patent application number: CN201810682946.9, publication number: CN108890548A. This patent discloses a flexible clamping mechanism and its clamping method, the flexible clamping mechanism is composed of a plurality of flexible clamping units, the flexible clamping unit includes a shell, a rubber wheel, a spring, and a connecting mechanism; the flexible clamping units are connected to each other by pins and can rotate around the pins; the angles between adjacent flexible clamping units are adjusted according to the skin shape and then locked; pull rings are provided at both ends of the flexible clamping mechanism, and the flexible clamping mechanism is fixed to the frame as a whole by a tightening clamp fixed on the tooling frame, and the clamping of the skin with different curvatures is achieved by combining a plurality of flexible clamping units at different angles. This patent is applicable to aviation flexible clamping mechanisms, not to stacked satellites.

[0009] (5) "An integrated device for NFC antenna compression and conductivity testing", patent application number: CN201820439248.1, publication number: CN208076643U. This utility model discloses an integrated device for NFC antenna compression and conductivity testing, including an air press, a first bracket, a switch, a test probe, an upper mold device, a second bracket, a product fixing seat and a silicone pressing plate; the air press is installed on the first bracket; the first bracket is fixed on the second bracket; the upper mold device is installed below the air press; the test probe and the silicone pressing plate are installed on the bottom surface of the upper mold device; the product fixing seat is installed on the second bracket and corresponds to the installation position of the silicone pressing plate. Compared with the prior art, the beneficial effect of the integrated device for NFC antenna compression and conductivity testing of this utility model is that the two processes of NFC antenna compression and conductivity testing are combined into one, which can reduce the number of operators, effectively improve production efficiency, and the equipment manufacturing cost is much lower than the price of existing conductivity testing equipment. This patent is applicable to ground operation equipment.

[0010] (6) The paper "A limited clamping and releasing method for large satellite-borne radar antennas" (Spacecraft Engineering) (Issue 5, 2022) explores a limited clamping and releasing method based on the characteristics of large satellite-borne phased array radar antennas with a large number of sub-boards, large size and heavy mass. Based on the idea of ​​integrated design of the clamping and releasing mechanism and the satellite structure, the system scheme design and principle prototype development were carried out. A series of performance tests were carried out around the prototype. The test results show that the system base frequency meets the requirements of the carrier and can withstand a large number of vibrations during launch. It can provide a good dynamic environment for the radar antenna and achieve reliable clamping of the antenna. Kinematic simulation analysis shows that after entering orbit, the satellite truss can be smoothly unfolded and the radar antenna can be released smoothly. It has been verified that the limited clamping and releasing system scheme is reasonable and feasible, and the functional performance meets the requirements, which can effectively support the development of satellite models. This paper is mainly aimed at large radar antennas, and the object is not large-caliber antennas with high requirements. Summary of the invention

[0011] In view of the defects in the prior art, an object of the present invention is to provide a power metasurface antenna compression device for stacked satellites.

[0012] According to the present invention, a power metasurface antenna pressing device for a stacked satellite comprises: an antenna reflector, a sub-reflector, a frame, an antenna frame deployment mechanism and an antenna frame pressing mechanism. The antenna reflector and the sub-reflector are both mounted on the frame. One end of the frame is folded and pressed against a side surface of a stacked satellite body by the antenna frame deployment mechanism. An antenna frame pressing mechanism is provided around the frame. The frame is pressed against the surface of the stacked satellite body by the antenna frame pressing mechanism.

[0013] The sub-reflector is switched between an extended state and a retracted state by a sub-reflector pressing and unfolding device. When the sub-reflector is in the extended state, the sub-reflector is located on the upper side of the antenna reflector; when the sub-reflector is in the retracted state, the sub-reflector is located on the other side of the stacked satellite body.

[0014] Preferably, the antenna reflector comprises a metasurface unit, an antenna feed, a bellows amplifier and an antenna transmitter, the antenna feed is fixedly connected to the upper surface of the metasurface unit, the lower surface of the metasurface unit is connected to the front surface of the mounting frame, the antenna transmitter and the bellows amplifier are installed on the back surface of the mounting frame, and the antenna transmitter is connected to the antenna feed waveguide;

[0015] When the antenna is in transmitting state, the traveling wave tube amplifier amplifies the excitation signal and transmits it through the antenna transmitter. After the antenna feed source synthesizes the polarization, it is irradiated to the sub-reflector through space and then reflected to the antenna reflector, and the antenna reflector forms a transmitting beam in the specified direction.

[0016] Preferably, the sub-reflector surface pressing and unfolding device comprises a sub-reflector surface unfolding mechanism and a sub-reflector surface pressing mechanism, the sub-reflector surface is fixedly connected to the sub-reflector surface unfolding mechanism, the sub-reflector surface unfolding mechanism is connected to both sides of the frame, and the sub-reflector surface pressing mechanism is installed at the other end of the frame;

[0017] The secondary reflective surface is switched between an extended state and a retracted state by a secondary reflective surface extending mechanism and a secondary reflective surface pressing mechanism respectively.

[0018] Preferably, the antenna reflector, the sub-reflector and the frame are integrally unfolded;

[0019] The sub-reflecting surface is unfolded once by the antenna frame unfolding mechanism, and the sub-reflecting surface is unfolded twice by the sub-reflecting surface unfolding mechanism.

[0020] Preferably, the deployment angle of the antenna reflective surface and the antenna frame deployment mechanism is 0-180°.

[0021] Preferably, the deployment angle of the secondary reflector deployment mechanism is 0-130°.

[0022] Preferably, both the antenna frame deployment mechanism and the sub-reflector deployment mechanism are equipped with in-place deployment sensors, and the antenna reflector and the sub-reflector respectively feed back antenna deployment in-place information through corresponding in-place deployment sensors.

[0023] Preferably, the antenna frame clamping mechanism is distributed on the frame circumferentially around the antenna feed source.

[0024] Preferably, the secondary reflector deployment mechanism adopts a constant force spring passive deployment locking device, and the secondary reflector clamping mechanism adopts a flexible clamping release device;

[0025] During the launch phase, the sub-reflector is gathered and pressed against the surface of the satellite through the sub-reflector pressing mechanism;

[0026] After the satellite enters orbit, the sub-reflector is rotated through the sub-reflector deployment mechanism and locked in a predetermined position.

[0027] Preferably, the antenna reflecting surface is a Cassegrain-style planar reflector array, and the metasurface unit is composed of 42,000 array elements. Each array element obtains a different reflection phase (0°, ±90°, ±180°, ±270°) when two diodes are combined in different on-off states, thereby forming different beam direction switching for the entire antenna.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] (1) This application adopts a stacked satellite large-aperture power metasurface antenna folding and pressing device to achieve a relatively low satellite folding height, meet the stacked satellite's entire satellite's relatively low altitude bearing requirements, and greatly expand the application of large-aperture power metasurface antennas in stacked satellites;

[0030] (2) In the present application, the super surface unit, antenna feed, and antenna sub-reflector are all located on the same frame and deployed using a passive mechanism; the antenna sub-reflector adopts a secondary deployment scheme with a flexible unlocking release and a constant force spring passive deployment locking design. The deployment device has a small impact and high deployment reliability, which reduces the impact during the deployment of the sub-reflector and ensures the high-precision and reliable deployment of the sub-reflector mechanism;

[0031] (3) The power metasurface antenna clamping device for stacked satellites proposed in this application meets the requirements for carrying large-aperture power metasurface antennas on inclined orbit stacked satellites, and expands the application of stacked satellite platforms. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0033] Figure 1 This is a schematic diagram of the overall compressed state of the power metasurface antenna;

[0034] Figure 2 It is a schematic diagram of the reflective surface of the power metasurface antenna being unfolded and the secondary anti-deployment mechanism being compressed;

[0035] Figure 3 It is a schematic diagram of the unfolded state of the reflective surface of the power metasurface antenna and the unfolded state of the secondary anti-deployment mechanism.

[0036] The figure shows: an antenna reflector 1, a sub-reflector 2, a sub-reflector deployment mechanism 21, a sub-reflector clamping mechanism 22, a frame 3, an antenna frame deployment mechanism 4, and an antenna frame clamping mechanism 5. DETAILED DESCRIPTION

[0037] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0038] Example

[0039] The present invention provides a power super-surface antenna pressing device for stacking satellites, such as Figure 1 As shown, it is suitable for antennas with larger diameters. The diameter of the antenna is not less than The stacked satellite payload has a low compression height, the height of the antenna in the folded state is not more than 350mm, and there are strict restrictions on the load height. It includes an antenna reflector 1, a sub-reflector 2, a frame 3, an antenna frame deployment mechanism 4 and an antenna frame clamping mechanism 5. The antenna reflector 1 and the sub-reflector 2 are both installed on the frame 3 to reduce the installation error caused by the installation of different parts of the antenna in different components. The antenna reflector 1, the sub-reflector 2 and the frame 3 are unfolded as a whole. One end of the frame 3 is folded and pressed against one side of the stacked satellite body by the antenna frame deployment mechanism 4. The antenna frame deployment mechanism 4 adopts a passive deployment mechanism, which is a constant force spring. While ensuring the deployment accuracy of each component of the antenna, it also has high reliability. An antenna frame clamping mechanism 5 is arranged around the frame 3 to ensure that the deployment and locking device has high reliability. The frame 3 is pressed against the surface of the stacked satellite body by the antenna frame clamping mechanism 5. The sub-reflector 2 is switched between an extended state and a retracted state by a sub-reflector pressing and unfolding device. When the sub-reflector 2 is in the extended state, the sub-reflector 2 is located on the upper side of the antenna reflector 1; when the sub-reflector 2 is in the retracted state, the sub-reflector 2 is located on the other side of the stacked satellite body.

[0040] like Figure 2 As shown, the antenna reflector 1 includes a metasurface unit, an antenna feed, a traveling wave tube amplifier and an antenna transmitter. The metasurface unit, the antenna feed and the sub-reflector 2 mounting frame are mounted on the side of the star. The deployment angle of the antenna reflector 1 and the antenna frame deployment mechanism 4 is 180°, which effectively reduces the overall folding height of the antenna. The antenna feed is fixedly connected to the upper surface of the metasurface unit. In order to improve the antenna efficiency, the antenna frame clamping mechanism 5 is located near the antenna feed. Through this clamping method, the array element of the antenna reflector 1 is less damaged, and the antenna efficiency is also improved. The lower surface of the metasurface unit is connected to the front of the mounting frame. In order to effectively reduce the loss between the antenna transmitter and the antenna feed, the antenna transmitter and the traveling wave tube amplifier are installed on the back of the mounting frame. The frame 3 provides an antenna transmitter installation interface. The antenna transmitter is connected to the antenna feed waveguide, which effectively reduces the connection loss between the antenna transmitter and the antenna feed. The antenna transmitter is installed outside the cabin to meet the heat dissipation requirements of the on-orbit transmitter for long-term operation. The antenna adopts the Cassegrain form to illuminate the plane reflective array. When the antenna is in the transmitting state, the traveling wave tube amplifier amplifies the excitation signal and transmits it through the ring antenna transmitter. After the feed horn antenna synthesizes the polarization, it is irradiated to the sub-reflector 2 through space and then reflected to the plane reflective array surface, and the array surface forms a transmitting beam in the specified direction; the metasurface unit is composed of 42,000 array elements, and each array element obtains a different reflection phase (0°, ±90°, ±180°, ±270°) when the two diodes are combined in different on-off states, thereby forming different beam direction switching of the entire antenna.

[0041] like Figure 3As shown, the antenna sub-reflector adopts a secondary deployment scheme, and the sub-reflector pressing and deploying device includes a sub-reflector deployment mechanism 21 and a sub-reflector pressing mechanism 22. The sub-reflector 2 is fixedly connected to the sub-reflector deployment mechanism 21 and no longer deployed with each other; the solar array is a single wing and is installed on the satellite-Y side. The sub-reflector deployment mechanism 21 is connected to the frame 3, and the sub-reflector pressing mechanism 22 is installed at the other end of the frame 3; the sub-reflector 2 is in a deployed state through the sub-reflector deployment mechanism 21, and the sub-reflector 2 is deployed once through the antenna frame deployment mechanism 4, and the sub-reflector 2 is deployed twice through the sub-reflector deployment mechanism 21. The sub-reflector 2 is in a retracted state through the sub-reflector pressing mechanism 22. The deployment angle of the sub-reflector deployment mechanism 21 is 130°. In order to ensure the deployment accuracy of the sub-reflector, the sub-reflector and the frame are in a fixed connection state. The antenna frame deployment mechanism 4 and the sub-reflector deployment mechanism 21 are both equipped with in-place deployment sensors, and the antenna reflector 1 and the sub-reflector 2 respectively feedback the antenna deployment in-place information through the corresponding in-place deployment sensors.

[0042] The sub-reflector deployment mechanism 21 adopts a constant force spring passive deployment locking device, and the locking device uses a cutter or a separation nut pyrotechnic locking device; the sub-reflector clamping mechanism 22 adopts a flexible clamping release device. During the launch phase, the sub-reflector 2 is gathered and pressed on the surface of the satellite through the sub-reflector clamping mechanism 22 to ensure that the stiffness requirements are met; after the satellite enters orbit, the clamping point fuse cutter cuts off the tension rope in the clamping device, and the deployment hinge drives the deployment rod to rotate 130° and lock it in a predetermined position to meet the use requirements of the sub-reflector antenna; the root of the deployment mechanism is set to a deployment sensor to feedback the antenna deployment information; in order to ensure the deployment accuracy of the sub-reflector 2, the sub-reflector 2 and the frame 3 are in a fixed connection state.

[0043] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A power metasurface antenna pressing device for stacked satellites, characterized in that: include: An antenna reflector (1), a sub-reflector (2), a frame (3), an antenna frame deployment mechanism (4) and an antenna frame pressing mechanism (5), wherein the antenna reflector (1) and the sub-reflector (2) are both mounted on the frame (3), one end of the frame (3) is folded and pressed against a side surface of a stacked satellite body by the antenna frame deployment mechanism (4), the antenna frame pressing mechanism (5) is arranged around the frame (3), and the frame (3) is pressed against the surface of the stacked satellite body by the antenna frame pressing mechanism (5), The sub-reflecting surface (2) is switched between an extended state and a retracted state by means of a sub-reflecting surface pressing and unfolding device; when the sub-reflecting surface (2) is in the extended state, the sub-reflecting surface (2) is located on the upper side of the antenna reflecting surface (1); when the sub-reflecting surface (2) is in the retracted state, the sub-reflecting surface (2) is located on the other side of the stacked satellite body.

2. The power metasurface antenna pressing device for stacked satellites according to claim 1 is characterized in that: The antenna reflector (1) comprises a metasurface unit, an antenna feed, a bellows amplifier and an antenna transmitter, wherein the antenna feed is fixedly connected to the upper surface of the metasurface unit, the lower surface of the metasurface unit is connected to the front surface of the mounting frame, the antenna transmitter and the bellows amplifier are mounted on the back surface of the mounting frame, and the antenna transmitter is waveguide-connected to the antenna feed; When the antenna is in a transmitting state, the traveling wave tube amplifier amplifies the excitation signal and transmits it through the antenna transmitter. After the antenna feed source synthesizes polarization, the signal is irradiated to the sub-reflection surface (2) through space and then reflected to the antenna reflection surface (1). The antenna reflection surface (1) forms a transmission beam in a specified direction.

3. The power metasurface antenna pressing device for stacked satellites according to claim 1 is characterized in that: The secondary reflector surface pressing and unfolding device comprises a secondary reflector surface unfolding mechanism (21) and a secondary reflector surface pressing mechanism (22); the secondary reflector surface (2) is fixedly connected to the secondary reflector surface unfolding mechanism (21); the secondary reflector surface unfolding mechanism (21) is connected to both sides of the frame (3); and the secondary reflector surface pressing mechanism (22) is installed at the other end of the frame (3); The secondary reflective surface (2) is switched between an extended state and a retracted state by means of the secondary reflective surface extension mechanism (21) and the secondary reflective surface clamping mechanism (22).

4. The power metasurface antenna pressing device for stacked satellites according to claim 3 is characterized in that: The antenna reflecting surface (1), the sub-reflecting surface (2) and the frame (3) are unfolded as a whole; Furthermore, the secondary reflector (2) is unfolded once by the antenna frame unfolding mechanism (4), and the secondary reflector (2) is unfolded twice by the secondary reflector unfolding mechanism (21).

5. The power metasurface antenna pressing device for stacked satellites according to claim 4 is characterized in that: The unfolding angles of the antenna reflection surface (1) and the antenna frame unfolding mechanism (4) are 0-180°.

6. The power metasurface antenna pressing device for stacked satellites according to claim 3 is characterized in that: The deployment angle of the secondary reflective surface deployment mechanism (21) is 0-130°.

7. The power metasurface antenna pressing device for stacked satellites according to claim 3 is characterized in that: The antenna frame deployment mechanism (4) and the sub-reflecting surface deployment mechanism (21) are both equipped with in-place deployment sensors, and the antenna reflecting surface (1) and the sub-reflecting surface (2) respectively feed back antenna deployment in-place information through the corresponding in-place deployment sensors.

8. The power metasurface antenna pressing device for stacked satellites according to claim 2 is characterized in that: The antenna frame clamping mechanism (5) is distributed on the frame (3) circumferentially around the antenna feed source.

9. The power metasurface antenna pressing device for stacked satellites according to claim 3 is characterized in that: The secondary reflector surface deployment mechanism (21) adopts a constant force spring passive deployment locking device, and the secondary reflector surface pressing mechanism (22) adopts a flexible pressing release device; During the launch phase, the secondary reflector (2) is folded and pressed onto the surface of the star by the secondary reflector pressing mechanism (22); After the satellite enters orbit, the sub-reflector (2) is rotated by the sub-reflector deployment mechanism (21) and locked at a predetermined position.

10. The power metasurface antenna pressing device for stacked satellites according to claim 2, characterized in that: The antenna reflection surface (1) is a Cassegrain-type irradiation plane reflection array, and the metasurface unit is composed of 42,000 array elements. Each array element obtains a different reflection phase (0°, ±90°, ±180°, ±270°) when two diodes are combined in different on-off states, thereby forming different beam direction switching of the entire antenna.

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