Satellite-borne deployable antenna

Abstract

The invention belongs to the technical field of spaceborne antennas, and discloses a spaceborne deployable antenna, which comprises a base, a locking and releasing mechanism, an X-axis pointing mechanism, a Y-axis pointing mechanism and a reflecting surface assembly, and is characterized in that the base and the locking and releasing mechanism are arranged on an antenna mounting platform at an interval, and the X-axis pointing mechanism is rotationally arranged on the base; the Y-axis pointing mechanism is rotationally arranged at the end, away from the base, of the X-axis pointing mechanism, and in the locking state, the end, away from the X-axis pointing mechanism, of the Y-axis pointing mechanism is connected to the locking and releasing mechanism; in a release state, the Y-axis pointing mechanism is separated from the locking and releasing mechanism; the reflecting surface assembly is arranged on the Y-axis pointing mechanism, and an included angle A is formed between a main reflecting surface of the reflecting surface assembly and the antenna installation platform and is larger than 0 degree and smaller than 90 degrees. The main reflecting surface of the reflecting surface assembly is obliquely mounted on the antenna mounting platform, the requirement for the size of the antenna mounting platform is reduced, the overall weight is reduced, and the rotation angle range of the Y-axis pointing mechanism is increased.

Description

Technical Field

[0001] This invention relates to the field of spaceborne antenna technology, and more particularly to a spaceborne deployable antenna. Background Technology

[0002] In the field of spaceborne antenna technology, a spaceborne antenna typically consists of a base, an X-axis pointing mechanism, a Y-axis steering mechanism, a locking and releasing assembly, an antenna reflector, a waveguide, and a rotary joint. The base and locking and releasing assembly are fixed to the satellite module. The base is sequentially connected to the Y-axis pointing mechanism, the X-axis pointing mechanism, and the antenna reflector. The locking and releasing assembly is fixedly connected to the X-axis pointing mechanism for locking and securing. In the locked state, the central axis of the antenna reflector is perpendicular to the satellite module. Therefore, the size of the satellite module is generally not smaller than the outer diameter of the antenna reflector. Since the outer diameter of the antenna reflector is relatively large, when the size of the satellite module is limited, there are issues with the spaceborne antenna not being able to be installed, or a larger satellite module needs to be designed, resulting in a larger overall weight. Summary of the Invention

[0003] The purpose of this invention is to provide a spaceborne deployable antenna to reduce the installation size of the spaceborne antenna in the locked state and reduce the overall weight.

[0004] To achieve this objective, the present invention adopts the following technical solution: A spaceborne deployable antenna includes: The base is fixedly mounted on the antenna mounting platform; A locking and releasing mechanism is fixedly installed on the antenna mounting platform, and the locking and releasing mechanism is spaced apart from the base; X-axis pointing mechanism, the X-axis pointing mechanism is rotatably mounted on the base; The Y-axis pointing mechanism is rotatably located at the end of the X-axis pointing mechanism away from the base. In the locked state, the end of the Y-axis pointing mechanism away from the X-axis pointing mechanism is connected to the locking release mechanism; in the released state, the Y-axis pointing mechanism is separated from the locking release mechanism. A reflector assembly is mounted on the Y-axis pointing mechanism, and the main reflector of the reflector assembly has an included angle A with the antenna mounting platform, where 0° < A < 90°.

[0005] In some embodiments, the Y-axis pointing mechanism includes a Y-axis bracket, the Y-axis bracket comprising: The locking part is connected to the locking release mechanism in the locked state and separated from the locking release mechanism in the released state. A support portion, wherein the reflective surface assembly is disposed on the support portion, and the support portion is connected to the X-axis pointing mechanism; The connecting part has two ends connected to the locking part and the supporting part, respectively. The included angle B between the connecting part and the locking part and the included angle C between the connecting part and the supporting part are both obtuse angles.

[0006] In some embodiments, the rotation angle range of the Y-axis pointing mechanism is greater than 170°, and the rotation angle range of the X-axis pointing mechanism is greater than 150°.

[0007] In some embodiments, the wall thickness of the main reflective surface is 1~1.5mm.

[0008] In some embodiments, the spaceborne deployable antenna further includes a waveguide comprising a first segment, a second segment, and a third segment connected in sequence. The first segment and the second segment are rotatably connected via a Y-axis rotary joint, and the second segment and the third segment are rotatably connected via an X-axis rotary joint. The first segment extends from the vertex of the main reflector and is arranged vertically along the main reflector. The second segment is arranged along the X-axis pointing mechanism, and the third segment extends along the base.

[0009] In some embodiments, the locking release mechanism includes: A separation base, the bottom end of which is located on the antenna mounting platform, and the top end of which is provided with a slotted bolt; A locking screw, the tail of which passes through the Y-axis pointing mechanism and is threaded to the slotted bolt; A first self-locking washer is fitted onto the locking screw, and a first nut is threaded onto the locking screw and locks the first self-locking washer above the slotted bolt. A spring top block is sleeved on the locking screw. A second nut is threadedly connected to the locking screw and locks the spring top block above the Y-axis pointing mechanism, thereby locking the Y-axis pointing mechanism onto the separation seat.

[0010] In some embodiments, the locking release mechanism further includes a second self-locking washer, which is sleeved on the locking screw and located between the spring top block and the second nut.

[0011] In some embodiments, the locking release mechanism further includes a third self-locking washer, which is sleeved on the locking screw and located between the Y-axis pointing mechanism and the spring top block.

[0012] In some embodiments, the top of the separating seat is provided with a first boss, and a mounting groove is coaxially provided on the first boss. The Y-axis pointing mechanism is provided with a groove, and a second boss is protruding in the groove. The second boss is provided with a through hole. In the locked state, the first boss is inserted into the groove, and the groove wall of the mounting groove is connected to the outer conical surface of the second boss. The locking screw passes through the through hole.

[0013] In some embodiments, the mounting groove includes a tapered hole section and a circular hole section. The circular hole section is located at the small hole end of the tapered hole section, and the diameter of the small hole end is equal to the diameter of the circular hole section. The large hole end of the tapered hole section is oriented towards the Y-axis pointing mechanism, and the axial length of the tapered hole section is greater than the axial length of the circular hole section.

[0014] In some embodiments, the inner wall of the through hole is provided with a relief groove. When the slotted bolt is released and separated, the first nut can rise along the through hole to the relief groove and abut against the bottom of the relief groove to drive the Y-axis pointing mechanism to separate from the separation seat.

[0015] The beneficial effects of this invention are: The spaceborne deployable antenna provided by this invention, by setting the reflector assembly on the Y-axis pointing mechanism, has an angle A between the main reflector of the reflector assembly and the antenna mounting platform in the locked state, where 0° < A < 90°. This allows for the tilted installation of the main reflector of the reflector assembly on the antenna mounting platform. Compared with the prior art where the main reflector and the antenna mounting platform are parallel, the spaceborne deployable antenna provided by this invention has a smaller installation dimension in the longitudinal direction and an increased height on the antenna mounting platform, reducing the size requirements of the antenna mounting platform and helping to reduce the overall weight. Furthermore, the reflector assembly is set on the Y-axis pointing mechanism, which also forms an angle A with the antenna mounting platform in the locked state, thereby increasing the rotation range of the Y-axis pointing mechanism. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of the spaceborne deployable antenna in the locked state provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of the spaceborne deployable antenna in the locked state along its length direction provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of the first angle structure of the spaceborne deployable antenna in the deployed state provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of the second angle structure of the spaceborne deployable antenna in the deployed state provided in an embodiment of the present invention; Figure 5This is a cross-sectional view of the locking and releasing mechanism in the locked state of the spaceborne deployable antenna provided in an embodiment of the present invention; Figure 6 This is a cross-sectional view of the locking and releasing mechanism in the released state of the spaceborne deployable antenna provided in an embodiment of the present invention.

[0017] In the picture: 100. Antenna mounting platform; 1. Base; 2. Locking and releasing mechanism; 21. Separating seat; 211. Grooved bolt; 212. First boss; 213. Mounting groove; 2131. Tapered hole section; 2132. Round hole section; 22. Locking screw; 23. First self-locking washer; 24. First nut; 25. Spring top block; 26. Second nut; 27. Second self-locking washer; 28. Third self-locking washer; 3. X-axis pointing mechanism; 31. X-axis support; 32. X-axis drive mechanism; 4. Y-axis pointing mechanism; 41. Y-axis bracket; 411. Locking part; 4111. Groove; 4112. Second boss; 4113. Through hole; 4114. Clearance groove; 412. Support part; 413. Connecting part; 42. Y-axis drive mechanism; 5. Reflector assembly; 51. Main reflector; 6. Waveguide; 61. Y-axis rotary joint; 62. X-axis rotary joint. Detailed Implementation

[0018] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0019] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0020] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0021] In the description of this embodiment, the terms "upper," "lower," "left," and "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0022] like Figures 1-6 As shown, this embodiment of the invention provides a spaceborne deployable antenna, including a base 1, a locking and releasing mechanism 2, an X-axis pointing mechanism 3, a Y-axis pointing mechanism 4, and a reflector assembly 5. The base 1 is fixedly mounted on an antenna mounting platform 100; the locking and releasing mechanism 2 is fixedly mounted on the antenna mounting platform 100, spaced apart from the base 1; the X-axis pointing mechanism 3 is rotatably mounted on the base 1; the Y-axis pointing mechanism 4 is rotatably mounted at the end of the X-axis pointing mechanism 3 away from the base 1. In the locked state, the end of the Y-axis pointing mechanism 4 away from the X-axis pointing mechanism 3 is connected to the locking and releasing mechanism 2; in the released state, the Y-axis pointing mechanism 4 is separated from the locking and releasing mechanism 2; the reflector assembly 5 is mounted on the Y-axis pointing mechanism 4, and the main reflector 51 of the reflector assembly 5 has an included angle A with the antenna mounting platform 100, where 0° < A < 90°.

[0023] The spaceborne deployable antenna provided by the present invention sets the reflector assembly 5 on the Y-axis pointing mechanism 4. Typically, the main reflector 51 of the reflector assembly 5 is parallel to the Y-axis, that is, the line connecting the vertex of the main reflector 51 and the feed is perpendicular to the Y-axis. When the Y-axis pointing mechanism 4 and the X-axis pointing mechanism 3 are fully overlapped and locked, the main reflector 51 faces away from the base 1. Therefore, its installation size on the antenna mounting platform 100 is mainly limited by the maximum outer diameter of the main reflector 51. The spaceborne deployable antenna provided by this invention, in the locked state, has its main reflector 51 fixed by the locking and releasing mechanism 2 via the Y-axis pointing mechanism 4. The main reflector 51 and the antenna mounting platform 100 have an included angle A, where 0° < A < 90°, thus achieving an inclined installation of the main reflector 51 on the antenna mounting platform 100. In the prior art, the X-axis pointing mechanism 3 and the Y-axis pointing mechanism 4 are completely folded in the locked state to reduce the overall installation height, and the main reflector 51 is parallel to the antenna mounting platform 100. Due to the large area of ​​the main reflector 51, this installation method results in a large projected area of ​​the spaceborne deployable antenna on the antenna mounting platform 100. The traditional method involves a large overall length dimension of the spaceborne deployable antenna, requiring a large antenna mounting platform 100, resulting in a large total weight of the entire satellite. The spaceborne deployable antenna provided by this invention has a smaller length dimension and increased height on the antenna mounting platform 100. Specifically, the main reflector 51 is inclined relative to the antenna mounting platform 100, which reduces the size requirements of the antenna mounting platform 100, thereby reducing the overall weight of the antenna mounting platform 100 and increasing its applicability. Furthermore, the reflector assembly 5 is mounted on the Y-axis pointing mechanism 4, which forms an angle A with the antenna mounting platform 100 when locked, thus increasing the rotation range of the Y-axis pointing mechanism 4. Since the Y-axis pointing mechanism 4 has an elevation angle with the antenna mounting platform 100 when it is locked, the X-axis pointing mechanism 3 will also form a certain angle with the antenna mounting platform 100. Compared with the prior art, which completely overlaps the X-axis pointing mechanism 3 and the Y-axis pointing mechanism 4 on the antenna mounting platform 100, the spaceborne deployable antenna provided by the present invention is more conducive to rapid deployment after the locking release mechanism 2 is released and separated, thus improving the deployment efficiency.

[0024] In some embodiments, the Y-axis pointing mechanism 4 includes a Y-axis support 41, which includes a locking part 411, a support part 412, and a connecting part 413 connected between the locking part 411 and the support part 412. In the locked state, the locking part 411 is connected to the locking release mechanism 2; in the released state, the locking part 411 is separated from the locking release mechanism 2. The reflective surface assembly 5 is disposed on the support part 412, which is connected to the X-axis pointing mechanism 3. The two ends of the connecting part 413 are respectively connected to the locking part 411 and the support part 412. The included angle B between the connecting part 413 and the locking part 411 and the included angle C between the connecting part 413 and the support part 412 are both obtuse angles.

[0025] like Figure 1 and Figure 2 As shown, the X-axis pointing mechanism 3 includes an X-axis bracket 31 and an X-axis drive mechanism 32. The X-axis drive mechanism 32 is fixed on the base 1 and is used to drive the X-axis bracket 31 to rotate around the X-axis. The Y-axis pointing mechanism 4 includes a Y-axis bracket 41 and a Y-axis drive mechanism 42. The Y-axis drive mechanism 42 is fixed at the end of the X-axis bracket 31 away from the base 1 and is used to drive the Y-axis bracket 41 to rotate around the Y-axis. One end of the Y-axis bracket 41 is connected to the Y-axis drive mechanism 42, and the other end is connected to the locking and releasing mechanism 2, such as... Figure 2 The Y-axis bracket 41 is an integral structure. The locking part 411 is connected to the top of the locking and releasing mechanism 2. In the locked state, the locking part 411 is connected and fixed to the locking and releasing mechanism 2. When released, the locking part 411 is separated from the locking and releasing mechanism 2 first, and the rotating mechanism (including the Y-axis pointing mechanism 4 and the X-axis pointing mechanism 3) is unlocked, and the rotating and unfolding action can be performed. The support portion 412 is used to mount the reflective surface assembly 5. Typically, the opening direction of the main reflective surface 51 is vertically upward relative to the Y-axis. In this embodiment, a connecting portion 413 and a locking portion 411 are sequentially mounted at the end of the support portion 412 away from the Y-axis drive mechanism 42. An angle C is formed between the connecting portion 413 and the support portion 412, and an angle B is formed between the connecting portion 413 and the locking portion 411. Therefore, when the locking portion 411 is fixed to the locking and releasing mechanism 2, the top end of the connecting portion 413 is inclined upward to connect to the support portion 412, increasing the distance between the main reflective surface 51 and the locking portion 411. This allows the main reflective surface 51 to be installed at an angle and provides sufficient assembly space for the locking and releasing mechanism 2, facilitating assembly and enabling modular assembly, thus saving assembly time. Figure 6 The angle B should be set to facilitate the connection and assembly of the locking part 411 and the locking release mechanism 2. By setting the angle C to be greater than the angle B, the support part 412 is tilted upwards to support and fix the main reflective surface 51. This tilts the main reflective surface 51. In the locked state, the height of one end of the support part 412 connected to the Y-axis drive mechanism 42 is higher than the height of the other end. Consequently, the height of the top end of the X-axis bracket 31 is higher than the height of the bottom end. The X-axis bracket 31 is tilted at a certain angle. When it needs to be released and unfolded, after the locking part 411 separates from the locking release mechanism 2, the X-axis pointing mechanism 3 and the Y-axis pointing mechanism 4 can be rotated to adjust the unfolding angle. This increases the angle adjustment range and improves the unfolding efficiency.

[0026] With the above structural configuration, the rotation angle range of the Y-axis pointing mechanism 4 is greater than 170°, and the rotation angle range of the X-axis pointing mechanism 3 is greater than 150°. The rotation angle range of the Y-axis pointing mechanism 4 is -85° to +85°. Figure 3 and Figure 4As shown, the X-axis pointing mechanism 3 rotates 150° from the locked state to the deployed state, and the Y-axis pointing mechanism 4 rotates 85° or -85°. The rotation range of the main reflector 51 is increased, thereby reducing the overall rotation of the satellite for attitude adjustment and saving a lot of propellant energy.

[0027] In some embodiments, the wall thickness of the main reflector 51 is 1~1.5mm. Further, taking a wall thickness of 1.2mm for the main reflector 51 as an example, by rationally arranging the reinforcing ribs of the reflector assembly 5, the total weight of the reflector assembly 5 can be further reduced, thereby reducing the total weight of the spaceborne deployable antenna. It can be understood that the inclined arrangement of the main reflector 51 reduces the pressure on the Y-axis support 41, thus facilitating a reduction in the weight of the Y-axis support 41 while ensuring its structural strength. After the main reflector 51 is thinned, the number of reinforcing ribs on the main reflector 51 can also be reduced accordingly, further reducing the total weight of the reflector assembly 5.

[0028] In some embodiments, the spaceborne deployable antenna further includes a waveguide 6, which includes a first segment, a second segment, and a third segment connected in sequence. The first segment and the second segment are rotatably connected by a Y-axis rotation joint 61, and the second segment and the third segment are rotatably connected by an X-axis rotation joint 62. The first segment extends from the apex of the main reflector 51 and is arranged vertically along the main reflector 51. The second segment is arranged along the X-axis pointing mechanism 3, and the third segment extends along the base 1.

[0029] like Figure 1 As shown, the Y-axis rotary joint 61 is coaxially arranged with the Y-axis pointing mechanism 4, and the X-axis rotary joint 62 is coaxially arranged with the X-axis pointing mechanism 3. When the Y-axis support 41 rotates around the Y-axis, the first and second segments of the waveguide 6 rotate relative to each other. When the X-axis support 31 rotates around the X-axis, the second and third segments of the waveguide 6 rotate relative to each other. The first and second segments are respectively arranged close to the Y-axis support 41 and the X-axis support 31. Through the three-segment layout of the waveguide 6, the waveguide 6 can minimize the impact on the rotation range of the Y-axis pointing mechanism 4, which is beneficial for designing a larger rotation range for the Y-axis pointing mechanism 4.

[0030] During the deployment of the satellite-borne antenna in a locked state while it moves with the satellite, the clamping force between the Y-axis pointing mechanism 4 and the locking and releasing mechanism 2 can loosen due to mechanical vibrations during the movement. Furthermore, as the vibration level increases, the contact surfaces between the Y-axis pointing mechanism 4 and the locking and releasing mechanism 2 may not fully adhere, resulting in a significant drop in the fundamental frequency and failing to meet specified requirements. To address this loosening issue caused by vibration, such as... Figure 5 and Figure 6As shown, the locking and releasing mechanism 2 provided in this embodiment of the invention includes a separating seat 21, a locking screw 22, a first self-locking washer 23, and a spring top block 25. The bottom end of the separating seat 21 is provided on the antenna mounting platform 100, and the top end of the separating seat 21 is provided with a slotted bolt 211. The tail end of the locking screw 22 is provided with a Y-axis pointing mechanism 4 and threadedly connected to the slotted bolt 211. The first self-locking washer 23 is sleeved on the locking screw 22, and the first nut 24 is threadedly connected to the locking screw 22 and locks the first self-locking washer 23 above the slotted bolt 211. The spring top block 25 is sleeved on the locking screw 22, and the second nut 26 is threadedly connected to the locking screw 22 and locks the spring top block 25 above the Y-axis pointing mechanism 4, thereby locking the Y-axis pointing mechanism 4 onto the separating seat 21.

[0031] The locking and releasing mechanism 2 provided in this embodiment of the invention overcomes the problem of limited screw length by replacing the screw in the prior art with a locking screw 22. The locking screw 22 has sufficient length to connect the first self-locking washer 23 and the first nut 24. The top of the locking screw 22 locks the spring top block 25 through the second nut 26, thereby pressing and fixing the locking part 411 onto the separation seat 21. By setting a first self-locking washer 23 and a first nut 24 on the locking screw 22, with the first self-locking washer 23 located above the head of the slotted bolt 211, the locking screw 22 and the head of the slotted bolt 211 can be locked together by the first nut 24, preventing the locking screw 22 from loosening under vibration. A spring top block 25 is set to elastically press the Y-axis pointing mechanism 4 onto the separation seat 21. When the slotted bolt 211 is unlocked, the locking screw 22 causes the head of the slotted bolt 211 to elastically rise at the moment of unlocking, achieving rapid separation of the Y-axis pointing mechanism 4 from the separation seat 21. The spring top block 25 helps the locking screw 22 remain in the unlocked position, avoiding positional interference with subsequent movements of the rotating mechanism. The spaceborne deployable antenna only needs one locking and releasing mechanism 2 connected to the Y-axis bracket 41 to achieve overall locking and releasing, which helps reduce the overall weight.

[0032] In some embodiments, the locking release mechanism 2 further includes a second self-locking washer 27, which is sleeved on the locking screw 22 and located between the spring top block 25 and the second nut 26. The second self-locking washer 27 can prevent the contact surfaces between the second nut 26 and the spring top block 25 from loosening and separating, ensuring that the locking screw 22 locks the Y-axis bracket 41.

[0033] In some embodiments, the locking release mechanism 2 further includes a third self-locking washer 28, which is sleeved on the locking screw 22 and located between the Y-axis pointing mechanism 4 and the spring top block 25. The third self-locking washer 28 and the contact surface between the spring top block 25 and the Y-axis pointing mechanism 4 prevent loosening due to vibration. The arrangement of the first self-locking washer 23, the second self-locking washer 27, and the third self-locking washer 28 can effectively prevent loosening between the contact surfaces and improve the locking effect. It should be noted that the first self-locking washer 23, the second self-locking washer 27, and the third self-locking washer 28 can be existing self-locking washer products. The self-locking washer consists of two washers with radial ridges on the outer side and helical teeth on the inner side. Under vibration, the tension and the difference in the angle of the helical teeth generate a lifting force to achieve self-locking.

[0034] In some embodiments, the top of the separating seat 21 is provided with a first boss 212, and a mounting groove 213 is coaxially provided on the first boss 212. The Y-axis pointing mechanism 4 is provided with a groove 4111, and a second boss 4112 is protruding in the groove 4111. The second boss 4112 is provided with a through hole 4113. In the locked state, the first boss 212 and the groove 4111 are inserted and engaged. The groove wall of the mounting groove 213 and the outer conical surface of the second boss 4112 are connected by a conical engagement. The locking screw 22 passes through the through hole 4113.

[0035] Combination Figure 5 and Figure 6 As shown, the first boss 212, the mounting groove 213 and the slotted bolt 211 are coaxially arranged, and the groove 4111, the second boss 4112 and the through hole 4113 are coaxially arranged. The first boss 212 and the groove 4111 both adopt a rectangular cross section to facilitate positioning during installation. During installation, the tail of the locking screw 22 passes through the mounting groove 213 and is threaded to the slotted bolt 211. Then, the first self-locking washer 23 and the first nut 24 are fitted onto the locking screw 22. The first nut 24 locks the first self-locking washer 23 to the top of the slotted bolt 211. Then, the locking part 411, the third self-locking washer 28, the spring top block 25, the second self-locking washer 27, and the second nut 26 are sequentially fitted onto the locking screw 22. After the second nut 26 is tightened, the locking part 411 is fixed on the separating seat 21. At the same time, the second boss 4112 is inserted into the mounting groove 213, and the first boss 212 is inserted into the groove 4111, realizing a double insertion fit. The conical fit increases the contact area, thereby improving the friction and load-bearing capacity, which is conducive to improving the connection stability. Multiple self-locking washers achieve the anti-loosening function.

[0036] In some embodiments, the mounting groove 213 includes a tapered hole section 2131 and a circular hole section 2132. The circular hole section 2132 is disposed at the small hole end of the tapered hole section 2131, and the diameter of the small hole end is equal to the diameter of the circular hole section 2132. The large hole end of the tapered hole section 2131 is disposed toward the Y-axis pointing mechanism 4, and the axial length of the tapered hole section 2131 is greater than the axial length of the circular hole section 2132.

[0037] Combination Figure 5 and Figure 6 Corresponding to the tapered hole section 2131, the second boss 4112 has an outer tapered surface. During connection, the outer tapered surface and the inner tapered surface of the tapered hole section 2131 are inserted to form a tapered surface contact. The inner and outer tapered surfaces are set to have the same taper. The tapered surface connection can convert axial pressure into radial extrusion force. The contact area increases exponentially with the insertion depth. Under the condition that the axial pressure remains unchanged, the contact area increases after pressing, and the friction is significantly improved. It can effectively resist external forces such as cutting force and vibration. At the same time, the larger contact area can distribute the load more evenly and enhance the resistance to deformation.

[0038] In some embodiments, the inner sidewall of the through hole 4113 is provided with a relief groove 4114. When the slotted bolt 211 is released and separated, the first nut 24 can rise along the through hole 4113 to the relief groove 4114 and abut against the bottom of the relief groove 4114 to drive the Y-axis pointing mechanism 4 to separate from the separation seat 21.

[0039] like Figure 6 To facilitate the separation and release of the Y-axis pointing mechanism 4, the through hole 4113 is designed as a tapered hole. In this embodiment, a clearance groove 4114 is provided on the inner wall of the through hole 4113 to facilitate the installation of the first self-locking washer 23 and the first nut 24. The clearance groove 4114 can provide a sufficient upward channel for the separation and release of the first nut 24, so that the head of the slotted bolt 211 separates and the first nut 24 abuts against the bottom of the clearance groove 4114, thereby driving the Y-axis pointing mechanism 4 to separate quickly, which is easy to control.

[0040] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A spaceborne deployable antenna, characterized in that, include: The base (1) is fixedly mounted on the antenna mounting platform (100); A locking and releasing mechanism (2) is fixedly installed on the antenna mounting platform (100), and the locking and releasing mechanism (2) is spaced apart from the base (1); X-axis pointing mechanism (3), which is rotatably mounted on the base (1); The Y-axis pointing mechanism (4) is rotatably located at the end of the X-axis pointing mechanism (3) away from the base (1). In the locked state, the end of the Y-axis pointing mechanism (4) away from the X-axis pointing mechanism (3) is connected to the locking release mechanism (2); in the released state, the Y-axis pointing mechanism (4) is separated from the locking release mechanism (2). A reflector assembly (5) is disposed on the Y-axis pointing mechanism (4), and the main reflector (51) of the reflector assembly (5) has an included angle A with the antenna mounting platform (100), where 0° < A < 90°.

2. The spaceborne deployable antenna according to claim 1, characterized in that, The Y-axis pointing mechanism (4) includes a Y-axis bracket (41), the Y-axis bracket (41) comprising: The locking part (411) is connected to the locking release mechanism (2) in the locked state; and is separated from the locking release mechanism (2) in the released state. Support part (412), the reflective surface assembly (5) is disposed on the support part (412), and the support part (412) is connected to the X-axis pointing mechanism (3); The connecting part (413) is connected to the locking part (411) and the supporting part (412) at its two ends respectively. The included angle B between the connecting part (413) and the locking part (411) and the included angle C between the connecting part (413) and the supporting part (412) are both obtuse angles.

3. The spaceborne deployable antenna according to claim 1, characterized in that, The rotation angle range of the Y-axis pointing mechanism (4) is greater than 170°, and the rotation angle range of the X-axis pointing mechanism (3) is greater than 150°.

4. The spaceborne deployable antenna according to claim 1, characterized in that, The wall thickness of the main reflective surface (51) is 1~1.5mm.

5. The spaceborne deployable antenna according to any one of claims 1-4, characterized in that, It also includes a waveguide (6), which includes a first segment, a second segment and a third segment connected in sequence. The first segment and the second segment are rotatably connected by a Y-axis rotary joint (61), and the second segment and the third segment are rotatably connected by an X-axis rotary joint (62). The first segment extends from the vertex of the main reflector (51) and is arranged vertically along the main reflector (51). The second segment is arranged along the X-axis pointing mechanism (3), and the third segment extends along the base (1).

6. The spaceborne deployable antenna according to claim 1, characterized in that, The locking and releasing mechanism (2) includes: A separation base (21) is provided at its bottom end on the antenna mounting platform (100), and a slotted bolt (211) is provided at its top end. A locking screw (22) is provided with the tail end of which is threaded through the Y-axis pointing mechanism (4) and connected to the slotted bolt (211); The first self-locking washer (23) is sleeved on the locking screw (22), and the first nut (24) is threaded to the locking screw (22) and locks the first self-locking washer (23) above the slotted bolt (211); A spring top block (25) is sleeved on the locking screw (22). A second nut (26) is threaded to the locking screw (22) and locks the spring top block (25) above the Y-axis pointing mechanism (4), thereby locking the Y-axis pointing mechanism (4) on the separation seat (21).

7. The spaceborne deployable antenna according to claim 6, characterized in that, The locking release mechanism (2) further includes a second self-locking washer (27), which is sleeved on the locking screw (22) and located between the spring top block (25) and the second nut (26).

8. The spaceborne deployable antenna according to claim 7, characterized in that, The locking release mechanism (2) further includes a third self-locking washer (28), which is sleeved on the locking screw (22) and located between the Y-axis pointing mechanism (4) and the spring top block (25).

9. The spaceborne deployable antenna according to claim 8, characterized in that, The top of the separating seat (21) is provided with a first boss (212), and a mounting groove (213) is coaxially provided on the first boss (212). The Y-axis pointing mechanism (4) is provided with a groove (4111), and a second boss (4112) is protruding in the groove (4111). The second boss (4112) is provided with a through hole (4113). In the locked state, the first boss (212) is inserted into the groove (4111), and the groove wall of the mounting groove (213) is connected to the outer conical surface of the second boss (4112) with a conical surface engagement. The locking screw (22) passes through the through hole (4113).

10. The spaceborne deployable antenna according to claim 9, characterized in that, The mounting groove (213) includes a tapered hole section (2131) and a circular hole section (2132). The circular hole section (2132) is located at the small hole end of the tapered hole section (2131). The diameter of the small hole end is equal to the diameter of the circular hole section (2132). The large hole end of the tapered hole section (2131) is oriented towards the Y-axis pointing mechanism (4). The axial length of the tapered hole section (2131) is greater than the axial length of the circular hole section (2132).

11. The spaceborne deployable antenna according to claim 9, characterized in that, The inner wall of the through hole (4113) is provided with a relief groove (4114). When the slotted bolt (211) is released and separated, the first nut (24) can rise along the through hole (4113) to the relief groove (4114) and abut against the bottom of the relief groove (4114) to drive the Y-axis pointing mechanism (4) to separate from the separation seat (21).

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