Phased antenna deployment state holding tool and assembly method thereof with satellite

Abstract

The application relates to the field of aerospace technology, in particular to a phased antenna deployment state holding tool and an assembly method thereof with a satellite, which comprises two antenna butt joint frame assemblies and two inclined frame assemblies. The antenna butt joint frame assembly comprises a connecting beam with a first direction as the length direction, two connecting beams are arranged in parallel, two inclined frame assemblies are arranged in the first direction, and the two inclined frame assemblies are arranged in radial symmetry. The inclined frame assembly comprises two connecting inclined beams, the connecting inclined beams are arranged obliquely relative to the first direction, the two connecting inclined beams are fixedly connected with the two connecting beams in a one-to-one correspondence, and the two connecting inclined beams are used for being fixedly connected with a satellite body. The application aims to provide a phased antenna deployment state holding tool and an assembly method thereof with a satellite for at least one technical problem in the prior art.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and more specifically, to a phased array antenna deployment state maintenance fixture and its assembly method with a satellite. Background Technology

[0002] As the most important payload of a SAR satellite, the phased array antenna (SAR antenna) is generally a thin plate-like configuration (the physical size in the azimuth direction is several times that in the range direction). In order to occupy less envelope space in the fairing during launch and to ensure that the SAR antenna has good resistance to mechanical environment, the SAR antenna is usually divided into multiple antenna subarrays along the azimuth direction: the body-mounted subarray and the deployable subarray. The body-mounted subarray is directly fixed on the satellite platform, while the deployable subarray is in a retracted state during launch, either retracted and pressed against the side of the body-mounted subarray or retracted and pressed against other mounting surfaces of the satellite platform. After the satellite is released in orbit, the deployable subarray is deployed through ground remote control commands. The deployable subarray and the body-mounted subarray together form a large-size radiating surface with high flatness.

[0003] The deployment mechanism of a SAR antenna is a key component ensuring high flatness after deployment. This mechanism requires high deployment accuracy and repeatability. During ground-based deployment testing, a zero-gravity deployment truss and suspension system compensate for the gravity of the antenna subarray, simulating the weightlessness of the antenna in space to prevent external forces from affecting the hinge mechanism. Before deployment, the zero-gravity deployment fixture and the satellite's attitude must be adjusted using a theodolite and laser tracker to ensure the antenna's radiating surface is perpendicular to the ground. The adjusted attitude of the zero-gravity deployment fixture and the satellite must not be disrupted during or after deployment. Otherwise, the adjusted zero-gravity state will be lost, causing external forces to damage the antenna hinges and compromising on-orbit deployment accuracy.

[0004] In some situations, it is necessary to move or adjust the attitude of the entire satellite while the SAR antenna is deployed. For example, during thermal testing of the entire satellite, the SAR antenna needs to be kept deployed with its radiating surface facing downwards inside the vacuum chamber. If the gravity unloading is insufficient when moving or adjusting the attitude of the entire satellite, it can easily damage the hinges. There are several ways to solve the problem of gravity-induced hinge stress on the antenna panels. One approach is to use process hinges during the thermal testing phase of the SAR antenna, and then replace them with standard hinges later on the satellite. Another approach is to conduct thermal testing on the SAR antenna without hinges, in which case thermal testing fixtures are needed to assemble multiple antenna pieces into a single array. Both methods can prevent deformation of the standard hinges of the SAR antenna under stress, but the problem is that both require reinstalling the hinges and adjusting the antenna deployment accuracy later, increasing the subsequent satellite assembly steps and time. Summary of the Invention

[0005] The purpose of this application is to provide a phased antenna deployment state maintenance fixture and its assembly method with a satellite, addressing at least one technical problem mentioned in the background art.

[0006] To achieve the above objectives, this application adopts the following technical solution: One aspect of this application provides a fixture for maintaining a phased array antenna in its deployed state, including two antenna docking frame assemblies and two inclined frame assemblies. Each antenna docking frame assembly includes a connecting beam with its length direction in a first direction. The two connecting beams are arranged parallel to each other and aligned in a second direction. Two of the aforementioned oblique frame components are arranged in the first direction and are radially symmetrically positioned. Each oblique frame component includes two connecting oblique beams positioned on the same side of the satellite body in the first direction. The connecting oblique beams are inclined relative to a third direction, the first direction, and the second direction, and the first direction, the second direction, and the third direction are mutually perpendicular. The connecting inclined beam includes a first inclined beam connecting end and a second inclined beam connecting end. The two first inclined beam connecting ends are fixedly connected to the two connecting beams in a one-to-one correspondence, and the two second inclined beam connecting ends are both used to be fixedly connected to the satellite body.

[0007] Optionally, the antenna docking frame assembly further includes two antenna docking frames that are fixed to both ends of the connecting beam in a one-to-one correspondence. In the first direction, each antenna docking frame is located inside the two connecting beams, and in the second direction, the side of the antenna docking frame facing away from the corresponding connecting beam is used for connection with the SAR antenna.

[0008] The beneficial effect of this technical solution is that some SAR antennas have protruding structures. When the phased array antenna is in the unfolded state and the fixture is connected to the SAR antenna, if the SAR antenna is directly fixed to the connecting beam, these protruding structures may interfere with the connecting beam. The side of the antenna docking frame that is away from the corresponding connecting beam in the second direction is used to connect with the SAR antenna, which increases the distance between the SAR antenna and the connecting beam in the second direction, making it less likely for the SAR antenna and the connecting beam to interfere directly.

[0009] Optionally, the antenna docking frame assembly further includes a first heat insulation block, the connecting beam has an L-shaped cross-section, the antenna docking frame is located within the L-shaped structure, one end of the antenna docking frame in the second direction is used to be fixedly connected to the SAR antenna through the first heat insulation block, and the other end of the antenna docking frame is fixed to the connecting beam.

[0010] The beneficial effects of this technical solution are as follows: by making the cross-section of the connecting beam L-shaped, the bending resistance of the connecting beam itself is improved, thereby improving the rigidity and strength of the phased array antenna deployment state maintenance fixture. The first heat insulation block is set to separate the SAR antenna and the antenna docking frame, thereby separating the connecting beam and the SAR antenna, so as to reduce the heat transferred to the connecting beam and other parts of the phased array antenna deployment state maintenance fixture during the thermal experiment. After the phased array antenna deployment state maintenance fixture is connected to the SAR satellite, the SAR antenna, the antenna docking frame and the connecting beam are connected in the vertical direction in sequence, so that the connecting beam can form a direct and effective support for the SAR antenna.

[0011] Optionally, the inclined frame assembly further includes a reinforcing frame, the long side of which is parallel to the second direction, and the wide side of which is parallel to the first direction. The first inclined beam connecting ends of the two connecting inclined beams in the inclined frame assembly are both fixed to the reinforcing frame. In the second direction, one end of the reinforcing frame is connected to the antenna docking frame of one of the antenna docking frame assemblies, and the other end of the reinforcing frame is connected to the antenna docking frame of another of the antenna docking frame assemblies.

[0012] The beneficial effects of this technical solution are as follows: the reinforced frame forms a structure with high rigidity in multiple directions, and by connecting the two antenna docking frames through the reinforced frame, the two antenna docking frame assemblies are connected into a closed structure with high rigidity, thereby improving the overall rigidity of the tooling in the deployed state of the phased antenna.

[0013] Optionally, the reinforcing box and the antenna docking box are arranged in a third-direction orientation.

[0014] The beneficial effect of this technical solution is that it makes the location of the reinforcing box less likely to affect the connection between the antenna docking frame and the SAR antenna.

[0015] Optionally, the inclined frame assembly further includes a connecting rod and two mounting blocks. The second inclined beam connecting ends of the two connecting inclined beams are fixedly connected to the two mounting blocks in a one-to-one correspondence. The two ends of the connecting rod are fixedly connected to the two mounting blocks in a one-to-one correspondence. Both mounting blocks are used to be fixedly installed on the satellite body.

[0016] The beneficial effects of this technical solution are as follows: it facilitates the connection of two connecting oblique beams and corresponding mounting blocks into one unit through connecting rods and reinforcing frames, and then fixes the oblique frame assembly as a whole to the satellite body when connected to the SAR satellite, thereby improving the efficiency of maintaining the connection between the phased antenna deployment fixture and the SAR satellite.

[0017] Optionally, the phased antenna deployment state holding fixture provided in this application further includes a satellite connection reinforcement component fixed to the connecting beam. The satellite connection reinforcement component is disposed near the middle of the connecting beam in the first direction, and the satellite connection reinforcement component is used to fix it to the satellite body.

[0018] The beneficial effects of this technical solution are as follows: by fixing the connecting beam to the satellite body through the satellite connection reinforcement component set in the middle of the connecting beam, the firmness and stability of the connection between the satellite body and the connecting beam can be improved, further enhancing the support capacity of the phased antenna deployment state maintenance fixture, and more reliably maintaining its adjusted attitude when the SAR satellite moves.

[0019] Optionally, each of the connecting beams is equipped with two of the satellite connection reinforcement components, which are symmetrically arranged on both sides of the satellite body in a first direction. Each satellite connection reinforcement component includes a satellite connection block, a plurality of second heat insulation blocks, and a plurality of third heat insulation blocks. The satellite connection block is used to connect to the satellite body through at least one of the second heat insulation blocks, and the satellite connection block is used to be fixedly connected to the connecting beam through at least one of the third heat insulation blocks.

[0020] The beneficial effects of this technical solution are as follows: on the one hand, by providing multiple satellite connection reinforcement components set in different positions, the connection strength and stability between the satellite body and each connecting beam are improved; on the other hand, during the thermal experiment, thermal isolation is achieved through the second and third heat insulation blocks, making it difficult for heat from the SAR satellite to be transferred to the two connecting beams.

[0021] Optionally, the satellite connecting block includes a first connecting plate portion, a second connecting plate portion, and a third connecting plate portion that are perpendicularly connected to each other in pairs. The first connecting plate portion is arranged perpendicular to the first direction, the second connecting plate portion is perpendicular to the third direction, and the third connecting plate portion is perpendicular to the second direction. An L-shaped groove for accommodating the corner of the satellite body is provided between the first connecting plate portion and the second connecting plate portion. The first connecting plate portion and the second connecting plate portion are both used for fixed connection with the satellite body, and the third connecting plate portion is fixedly connected to the connecting beam. The satellite connecting block also includes a first reinforcing plate portion and a second reinforcing plate portion. The first reinforcing plate portion is arranged parallel to the third connecting plate portion. The first connecting plate portion and the second connecting plate portion are both fixedly connected to the first reinforcing plate portion. The second reinforcing plate portion is parallel to the first connecting plate portion. The second connecting plate portion and the third connecting plate portion are both fixedly connected to the second reinforcing plate portion.

[0022] The beneficial effects of this technical solution are as follows: By fixing the star-body connecting block to different sides of the satellite body through the first connecting plate and the second connecting plate respectively, the connection strength between the star-body connecting block and the satellite body is improved. At the same time, by setting the first reinforcing plate and the second reinforcing plate, the rigidity and strength of the star-body connecting block are improved, making the star-body connecting block itself less prone to deformation, providing strong support for the SAR satellite's adjusted attitude, and improving the reliability of the connection between the satellite body, the star-body connection reinforcement components and the connecting beam, further providing reliable support for the SAR satellite's adjusted attitude.

[0023] Another aspect of this application provides a method for assembling a phased array antenna deployment state holding fixture with a satellite, implemented using the phased array antenna deployment state holding fixture provided in this application, wherein the phased array antenna deployment state holding fixture further includes a satellite connection and reinforcement component; the method includes: The SAR satellite is mounted on a support vehicle so that the radiating surface of the SAR antenna is perpendicular to the horizontal plane. The two unfolded subarrays of the SAR antenna are hoisted by a gravity compensation suspension system and the SAR antenna is unfolded under zero gravity. Both deployed subarrays are fixedly connected to the antenna docking frame assembly located below, and the satellite body is fixedly connected to each of the star body connection and reinforcement assemblies located below. Separate the overgravity compensation suspension system from the SAR satellite and fix the two deployable subarrays to the antenna docking frame assembly located above; Both oblique frame components are fixed to the satellite body and the two antenna docking frame components.

[0024] The technical solution provided in this application can achieve at least one of the following beneficial effects: The phased array antenna deployment state maintenance fixture and its assembly method with the satellite provided in this application securely fix the SAR antenna to the satellite body through the phased array antenna deployment state maintenance fixture. Two connecting beams provide firm support for the SAR antenna in the width and length directions of its radiating surface, and connecting inclined beams provide firm support for the SAR antenna in the normal direction of its radiating surface. When the SAR antenna is in the deployed state, the entire satellite can be moved or its attitude adjusted, making it easier for the SAR satellite to maintain the adjusted zero-gravity state and reducing the risk of damage to the hinge. In this way, the hinge does not need to be replaced or disassembled before the entire satellite is moved or its attitude adjusted, nor does it need to be reinstalled, saving assembly steps and time.

[0025] The additional technical features and advantages of this application will become more apparent from the following description or from practical application. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of the specific embodiments of this application, the accompanying drawings used in the description of the specific embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 A three-dimensional structural schematic diagram of one embodiment of the phased antenna deployment state holding fixture provided in this application embodiment; Figure 2 A three-dimensional structural diagram from one angle of one embodiment of the phased antenna deployment state holding fixture, SAR satellite and support vehicle provided in this application embodiment; Figure 3 This is a three-dimensional structural diagram from another angle of one embodiment of the phased antenna deployment state holding fixture, SAR satellite and support vehicle provided in the embodiments of this application; Figure 4 A partial three-dimensional structural schematic diagram of one embodiment of the phased antenna deployment state holding fixture provided in this application; Figure 5 A partial three-dimensional structural schematic diagram of one embodiment of the phased antenna deployment state holding fixture provided in this application; Figure 6 A three-dimensional structural diagram of a partial structure of the phased antenna deployment state holding fixture provided in this application embodiment after being connected to a SAR antenna. Figure 7 A partially exploded structural diagram of one embodiment of the phased antenna deployment state holding fixture provided in this application; Figure 8 A partial three-dimensional structural schematic diagram of one embodiment of the phased antenna deployment state holding fixture provided in this application; Figure 9 A partial three-dimensional structural schematic diagram of one embodiment of the phased antenna deployment state holding fixture provided in this application; Figure 10A A partially exploded structural diagram of one embodiment of the phased antenna deployment state holding fixture provided in this application; Figure 10B A three-dimensional structural schematic diagram of one embodiment of the star-connecting block provided in this application; Figure 11 A partial three-dimensional structural schematic diagram of one embodiment of the phased antenna deployment state holding fixture provided in this application; Figures 12 to 17A schematic diagram of the assembly method of the phased antenna deployment state maintenance fixture and the satellite provided in the embodiments of this application; Figure 18 A flowchart illustrating the assembly method of the phased antenna deployment state maintenance fixture and the satellite provided in this application embodiment; In the exploded diagrams, the dashed lines represent the corresponding positional relationships.

[0028] Figure label: 1. Satellite body; 2. Support vehicle; 3. Fixture for maintaining the deployed state of the phased array antenna; 4. SAR antenna; 5. Gravity-compensated suspension system; 31. Adjustable support rod; 32. Antenna mating frame assembly; 33. Angled frame assembly; 34. Planetary connection reinforcement components; 35. M8 screws; 36. M6 screw; 321. Connecting beam; 322. First heat insulation block; 323. Antenna mating frame; 331. Connecting block; 332. Aluminum square tube; 333. Mounting block; 334. Connecting inclined beam; 335. Connecting rod; 341. Planetary connecting block; 342. Second heat insulation block; 341a. Second connecting plate portion; 341b, First reinforcing plate portion; 341c, First connecting plate portion; 341d, Second reinforcing plate section; 341e, Third connecting plate section. Detailed Implementation

[0029] The technical solutions of this application will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0030] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, 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 this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0031] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; 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; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0032] like Figures 1 to 17 As shown, one aspect of this application provides a phased array antenna deployment state holding fixture 3, including two antenna docking frame assemblies 32 and two inclined frame assemblies 33. The antenna docking frame assembly 32 includes a connecting beam 321 with its length direction in a first direction. The two connecting beams 321 are arranged parallel to each other and aligned in a second direction. Two inclined frame components 33 are arranged in the first direction and are radially symmetrical. Each inclined frame component 33 includes two connecting inclined beams 334 for being disposed on the same side of the satellite body 1 in the first direction. The connecting inclined beams 334 are inclined with respect to the third direction, the first direction, and the second direction. The first direction, the second direction, and the third direction are perpendicular to each other. The connecting inclined beam 334 includes a first inclined beam connecting end and a second inclined beam connecting end. The two first inclined beam connecting ends are fixedly connected to the two connecting beams 321 in a one-to-one correspondence, and the two second inclined beam connecting ends are both used to be fixedly connected to the satellite body 1.

[0033] The phased array antenna deployment state holding fixture 3 provided in this application, during use, is positioned such that the first direction is horizontal, the second direction is vertical, and the third direction is horizontal perpendicular to the first direction. The satellite body 1 is mounted on the support vehicle 2. The SAR antenna 4 is suspended using a gravity compensation suspension system 5, with the radiating surface of the SAR antenna 4 perpendicular to the ground, allowing the SAR antenna 4 to deploy under zero gravity. Then, the middle of the lower connecting beam 321 is fixedly connected to the satellite body 1. The portions of the connecting beam 321 on both sides of the satellite body 1 are fixedly connected to the bottom ends of the two deployed subarrays. The gravity compensation suspension system 5 on the upper part of the SAR antenna 4 is removed to free up space, and the upper connecting beam 321 is installed. The middle of the upper connecting beam 321 is fixedly connected to the satellite body 1. The upper connecting beam 321 is located on the satellite body 1. The two sides of the main body 1 are fixedly connected to the top of the two unfolded subarrays respectively. Then, the two ends of each connecting beam 334 are fixedly connected to the satellite body 1 and the corresponding connecting beam 321 respectively. The SAR antenna 4 is firmly fixed to the satellite body 1 by the phased antenna unfolded state holding fixture 3. The two connecting beams 321 provide firm support for the SAR antenna 4 in the width and length directions of its radiation surface. The connecting beams 334 provide firm support for the SAR antenna 4 in the normal direction of its radiation surface. When the SAR antenna 4 is in the unfolded state, the entire satellite can be moved or its attitude adjusted, making it easier for the SAR satellite to maintain the adjusted zero gravity state and less likely to damage the hinge. In this way, the hinge does not need to be replaced or disassembled before the entire satellite is moved or its attitude adjusted, and the hinge does not need to be reinstalled, saving assembly steps and time.

[0034] Optionally, such as Figure 8 As shown, the antenna docking frame assembly 32 further includes two antenna docking frames 323 fixed to both ends of the connecting beam 321 in a one-to-one correspondence. In the first direction, each antenna docking frame 323 is located inside the two connecting beams 321. In the second direction, the side of the antenna docking frame 323 facing away from the corresponding connecting beam 321 is used for connection with the SAR antenna 4. It can be understood that the side of the antenna docking frame 323 facing away from the corresponding connecting beam 321 refers to the side of the antenna docking frame 323 facing away from the connecting beam 321 connected to the antenna docking frame 323. Some SAR antennas 4 have protruding structures (such as hinges, clamping and releasing mechanisms, etc.). When the phased array antenna is in the unfolded state and the fixture 3 is connected to the SAR antenna 4, if the SAR antenna 4 is directly fixed to the connecting beam 321, these protruding structures may interfere with the connecting beam 321. In this embodiment, the side of the antenna docking frame 323 in the second direction that is away from the corresponding connecting beam 321 is used to connect with the SAR antenna 4, which increases the distance between the SAR antenna 4 and the connecting beam 321 in the second direction, making it less likely for the SAR antenna 4 and the connecting beam 321 to interfere directly.

[0035] Optionally, such as Figure 5 As shown, the antenna docking frame assembly 32 further includes a first heat insulation block 322. The cross-section of the connecting beam 321 is L-shaped, and the antenna docking frame 323 is located within the L-shaped structure. In the second direction, one end of the antenna docking frame 323 is used to fixably connect to the SAR antenna 4 through the first heat insulation block 322, and the other end of the antenna docking frame 323 is fixed to the connecting beam 321. In this embodiment, the connecting beam 321 is preferably integrally machined. By making the cross-section of the connecting beam 321 L-shaped, the bending resistance of the connecting beam 321 itself is improved, thereby improving the stiffness and strength of the phased antenna deployment state maintenance fixture 3. The first heat insulation block 322 is set to separate the SAR antenna 4 and the antenna docking frame 323, thereby separating the connecting beam 321 and the SAR antenna 4, so as to reduce the heat transferred to the connecting beam 321 and other parts of the phased antenna deployment state maintenance fixture 3 during the thermal experiment. After the phased antenna deployment state maintenance fixture 3 is connected to the SAR satellite, the SAR antenna 4, the antenna docking frame 323 and the connecting beam 321 are connected in the vertical direction in sequence, so that the connecting beam 321 can form a direct and effective support for the SAR antenna 4. In this embodiment, preferably, the antenna docking frame 323 and the connecting beam 321 are connected by screws. The hole on the antenna docking frame 323 for connecting with the connecting beam 321 is an oblong hole, and the length direction of the oblong hole is parallel to the first direction. In this way, when the phased array antenna is in the deployed state and the fixture 3 is connected to the SAR satellite, the connection position between the antenna docking frame 323 and the connecting beam 321 can be appropriately adjusted to accommodate the SAR satellite whose attitude has been adjusted. The L-shaped connecting beam 321 is integrally machined, which can provide greater bending stiffness in two directions and ensure that the integral structure has greater resistance to deformation. Preferably, the two surfaces of the connecting beam 321 are evenly distributed with weight-reducing grooves and reinforcing ribs to reduce weight.

[0036] Optionally, such as Figure 4 As shown, the inclined frame assembly 33 further includes a reinforcing frame. The long side of the reinforcing frame is parallel to the second direction, and the wide side of the reinforcing frame is parallel to the first direction. The first inclined beam connecting ends of the two connecting inclined beams 334 in the inclined frame assembly 33 are both fixed to the reinforcing frame. In the second direction, one end of the reinforcing frame is connected to the antenna docking frame 323 of one antenna docking frame assembly 32, and the other end of the reinforcing frame is connected to the antenna docking frame 323 of another antenna docking frame assembly 32. The reinforcing frame forms a structure with high rigidity in multiple directions. By connecting the two antenna docking frames 323 through the reinforcing frame, the two antenna docking frame assemblies 32 are connected into a closed structure with high rigidity, thereby improving the overall rigidity of the phased antenna deployment state maintenance fixture 3.

[0037] Optionally, the reinforcing frame and the antenna docking frame 323 are arranged in a third direction. This makes it less likely that the position of the reinforcing frame will affect the connection between the antenna docking frame 323 and the SAR antenna 4. Of course, the reinforcing frame can also be fixed to the side of the antenna docking frame 323 facing the first direction. In this embodiment, preferably, the reinforcing frame includes two aluminum square tubes 332 and two connecting blocks 331. The two aluminum square tubes 332 serve as the long side of the reinforcing frame, and the two connecting blocks 331 serve as the wide side of the reinforcing frame. The aluminum square tubes 332 and the connecting blocks 331 are connected by screws. The first inclined beam connecting ends of the two connecting inclined beams 334 in the two same inclined frame assemblies 33 are fixedly connected to the two connecting blocks 331 one by one. Preferably, two or three connection points are provided at each connection position to improve the connection strength. Of course, the reinforcing frame can also be integrally formed.

[0038] Optionally, the inclined frame assembly 33 further includes a connecting rod 335 and two mounting blocks 333. The second inclined beam connecting ends of the two connecting inclined beams 334 are fixedly connected to the two mounting blocks 333 one-to-one, and the two ends of the connecting rod 335 are fixedly connected to the two mounting blocks 333 one-to-one. Both mounting blocks 333 are used to be fixedly installed on the satellite body 1. In this way, it is convenient to connect the two connecting inclined beams 334 and the corresponding mounting blocks 333 into a whole through the connecting rod 335 and the reinforcing frame, and then fix the inclined frame assembly 33 as a whole to the satellite body 1 when connected with the SAR satellite, thereby improving the efficiency of maintaining the connection between the phased array antenna deployment fixture 3 and the SAR satellite. In this embodiment, preferably, the components of the inclined frame assembly 33 are detachably connected; the connecting rod 335 is preferably an aluminum square tube; and each connection position is preferably provided with two or three connection points to improve the connection strength.

[0039] Preferably, such as Figure 7 As shown, the inclined frame assembly 33 consists of two connecting blocks 331, three aluminum square tubes 332, two mounting blocks 333, and two connecting inclined beams 334. The assembly is internally assembled using screws. The two connecting blocks 331 are respectively installed on the antenna docking frames 323 on both sides of the antenna using two M8 screws 35; the two mounting blocks 333 are installed at the interfaces reserved on the satellite and connected using two M6 screws 36; the two aluminum square tubes 332 are used to connect the two connecting blocks 331 to form a rigid square integral structure; one aluminum square tube 332 is used to connect the two mounting blocks 333 to ensure the rigidity of the mounting blocks 333; the two connecting inclined beams 334 fix the connecting blocks 331 and the mounting blocks 333 together from two sides.

[0040] Optionally, such as Figure 10A and Figure 10B and Figure 11As shown, the phased-array antenna deployment state maintenance fixture 3 provided in this embodiment further includes a satellite connection reinforcement component 34 fixed to the connecting beam 321. The satellite connection reinforcement component 34 is positioned near the center of the connecting beam 321 in the first direction and is used for fixed connection with the satellite body 1. Thus, by fixing the connecting beam 321 to the satellite body 1 using the satellite connection reinforcement component 34 located in the center of the connecting beam 321, the robustness and stability of the connection between the satellite body 1 and the connecting beam 321 can be improved, further enhancing the support capacity of the phased-array antenna deployment state maintenance fixture 3 and more reliably maintaining its adjusted attitude when the SAR satellite moves. The satellite connection reinforcement component 34 can also fix the center of the antenna docking frame assembly 32 to the satellite body 1, increasing overall rigidity.

[0041] Optionally, such as Figure 10A As shown, each connecting beam 321 is equipped with two satellite connection reinforcement components 34, which are symmetrically arranged on both sides of the satellite body 1 in a first direction. Each satellite connection reinforcement component 34 includes a satellite connection block 341, multiple second heat insulation blocks 342, and multiple third heat insulation blocks 343. The satellite connection block 341 is connected to the satellite body 1 via at least one second heat insulation block 342, and is also fixedly connected to the connecting beam 321 via at least one third heat insulation block 343. In this way, on the one hand, by providing multiple satellite connection reinforcement components 34 arranged in different positions, the connection strength and stability between the satellite body 1 and each connecting beam 321 are improved; on the other hand, during thermal experiments, thermal isolation is achieved through the second heat insulation blocks 342 and the third heat insulation blocks 343, making it difficult for heat from the SAR satellite to be transferred to the two connecting beams 321.

[0042] Optionally, such as Figure 10BAs shown, the satellite connecting block 341 includes a first connecting plate portion 341c, a second connecting plate portion 341a, and a third connecting plate portion 341e that are perpendicularly connected to each other. The first connecting plate portion 341c is arranged perpendicular to the first direction, the second connecting plate portion 341a is perpendicular to the third direction, and the third connecting plate portion 341e is perpendicular to the second direction. An L-shaped groove for accommodating the corner of the satellite body 1 is provided between the first connecting plate portion 341c and the second connecting plate portion 341a. Both the first connecting plate portion 341c and the second connecting plate portion 341a are used to connect with the satellite body 1. The third connecting plate portion 341e is fixedly connected to the connecting beam 321. The celestial connecting block 341 also includes a first reinforcing plate portion 341b and a second reinforcing plate portion 341d. The first reinforcing plate portion 341b is arranged parallel to the third connecting plate portion 341e. The first connecting plate portion 341c and the second connecting plate portion 341a are both fixedly connected to the first reinforcing plate portion 341b. The second reinforcing plate portion 341d is parallel to the first connecting plate portion 341c. The second connecting plate portion 341a and the third connecting plate portion 341e are both fixedly connected to the second reinforcing plate portion 341d. In this way, the first connecting plate portion 341c and the second connecting plate portion 341a respectively fix the star body connecting block 341 to different sides of the satellite body 1, thereby improving the connection strength between the star body connecting block 341 and the satellite body 1. At the same time, by setting the first reinforcing plate portion 341b and the second reinforcing plate portion 341d, the rigidity and strength of the star body connecting block 341 are improved, thereby making the star body connecting block 341 itself less prone to deformation, providing strong support for the SAR satellite's adjusted attitude (the SAR antenna 4 in its fully deployed state), and improving the reliability of the connection between the satellite body 1, the star body connection reinforcement component 34 and the connecting beam 321, further providing reliable support for the SAR satellite's adjusted attitude. In this embodiment of the application, preferably, the phased antenna deployment state holding fixture 3 further includes two adjustable support rods 31. The adjustable support rods 31 are disposed below each connecting beam 321, and the top of the adjustable support rod 31 is fixedly connected to the connecting beam 321 located below. The adjustable support rod 31 is vertically arranged, and the bottom of the adjustable support rod 31 is supported on the ground. The adjustable support rod 31 can be extended and retracted in its length direction. For example, the adjustable support rod 31 includes two sleeves that are fitted together and threadedly connected. The length of the adjustable support rod 31 can be adjusted by selecting the outer sleeve. Alternatively, the adjustable support rod 31 includes a sealed sleeve that is fitted together. The length of the adjustable support rod 31 can be adjusted by inputting air pressure into the adjustable support rod 31 or releasing other pressure.

[0043] Preferably, the satellite connection reinforcement assembly 34 consists of a satellite connection block 341, two second heat insulation blocks 342, and two third heat insulation blocks 343. The satellite connection block 341 has two vertical mounting interfaces with the satellite body 1, and is installed using two M6 screws 36 via the two second heat insulation blocks 342. The satellite connection block 341 is installed with the L-shaped connecting beam 321 via the two third heat insulation blocks 343 using two M6 screws 36. The satellite connection reinforcement assembly 34 can securely connect the middle part of the antenna docking frame assembly 32 to the satellite body 1, increasing overall rigidity. In this embodiment, the heat insulation blocks can also be replaced by heat insulation pads.

[0044] In this embodiment, to ensure that the entire tooling has high rigidity in all three directions, the tooling has a three-dimensional configuration. The connecting beam 321, antenna docking frame 323, connecting block 331, and aluminum square tube 332 form a closed structure to increase the rigidity of the SAR antenna 4 array surface; the oblique frame assembly 33 connects the antenna docking frame 323 and the satellite body 1, increasing the rigidity of the SAR antenna 4 array surface in the normal direction; the satellite connection reinforcement assembly 34 connects the L-shaped connecting beam 321 and the satellite body 1, while increasing the rigidity of the SAR antenna 4 array surface and in the normal direction.

[0045] like Figures 12 to 17 ,as well as Figure 18 As shown, another aspect of this application provides a method for assembling a phased antenna deployment state holding fixture 3 with a satellite, implemented using the phased antenna deployment state holding fixture 3 provided in the embodiments of this application. The phased antenna deployment state holding fixture 3 further includes a satellite connection reinforcement component 34; the method includes: S01: Install the SAR satellite on the support vehicle 2 so that the radiating surface of the SAR antenna 4 is perpendicular to the horizontal plane, hoist the two unfolded subarrays of the SAR antenna 4 through the gravity compensation suspension system 5, and unfold the SAR antenna 4 under zero gravity. S02: Fix both of the two deployable subarrays to the antenna docking frame assembly 32 located below, and fix the satellite body 1 to each of the star body connection and reinforcement assemblies 34 located below; preferably, then install two adjustable support rods 31 on the connecting beam 321 located below, the positions of the two adjustable support rods 31 correspond one-to-one with the positions of the two deployable subarrays; S03: Separate the gravity compensation suspension system 5 from the SAR satellite, and fix the two deployable subarrays to the antenna docking frame assembly 32 located above; S04: Fix both oblique frame components 33 to the satellite body 1 and the two antenna docking frame components 32.

[0046] In this embodiment of the application, the zero-gravity deployment of the SAR antenna 4 means that the hinge between the deployment subarray and the bulk subarray does not need to support the deployment subarray in the vertical direction.

[0047] The assembly method of the phased antenna deployment state holding fixture 3 provided in this application with the satellite adopts the phased antenna deployment state holding fixture 3 provided in this application. The phased antenna deployment state holding fixture 3 securely fixes the SAR antenna 4 to the satellite body 1. The two connecting beams 321 provide firm support for the SAR antenna 4 in the width and length directions of its radiation surface, and the connecting inclined beam 334 provides firm support for the SAR antenna 4 in the normal direction of its radiation surface. When the SAR antenna 4 is in the deployed state, the entire satellite can be moved or its attitude adjusted, making it easier for the SAR satellite to maintain the adjusted zero-gravity state and less likely to damage the hinge. In this way, the hinge does not need to be replaced or disassembled before the entire satellite is moved or its attitude adjusted, and the hinge does not need to be reinstalled, saving assembly steps and time.

[0048] In one application example of the assembly method for maintaining the phased array antenna in its deployed state with the satellite, the method includes: Step 1: The SAR antenna 4 is mounted on the support vehicle 2 with its radiating surface perpendicular to the horizontal plane. The upper part of the antenna is suspended by a gravity compensation system 5, and the SAR antenna 4 is deployed under zero gravity. Step 2: After the SAR antenna 4 is deployed, the antenna docking frame assembly 32 and the satellite connection reinforcement assembly 34 are installed on the lower side, while the upper part is still kept in a state of gravity unloading using the hanging system. Step 3: Because the SAR antenna 4 only has the antenna docking frame assembly 32 installed on the lower side, and its rigidity is relatively poor, two adjustable support rods 31 are installed at the lower part of the L-shaped connecting beam 321 to prevent the whole structure from sagging and deforming. Step 4: Remove the upper suspension system of SAR antenna 4 to make room for the installation of antenna docking frame assembly 32 and satellite connection reinforcement assembly 34; Step 5: Install the reinforcing oblique frame assembly 33 at the rear of the SAR antenna 4, install the mounting block 333 and aluminum square tube 332 at the interface position on the satellite body 1, install the block 333 and aluminum square tube 332 on the antenna docking frame assembly 32, and finally install the connecting oblique beam 334.

[0049] After the SAR antenna 4 is deployed, a fixture with high stiffness in all directions is used to maintain the antenna in its deployed state. This fixture can withstand significant external forces without deformation. Even after the zero-gravity compensation system is removed, the fixture maintains the flatness of the SAR antenna 4 under its own weight and external interference, ensuring the hinge mechanism remains undamaged. Because the fixture has high stiffness in all directions, it prevents deformation of the antenna during movement and rotation.

[0050] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A fixture for maintaining the deployed state of a phased array antenna, characterized in that, It includes two antenna docking frame assemblies and two inclined frame assemblies. Each antenna docking frame assembly includes a connecting beam with its length direction in a first direction. The two connecting beams are arranged parallel to each other and aligned in a second direction. Two of the aforementioned oblique frame components are arranged in the first direction and are radially symmetrically positioned. Each oblique frame component includes two connecting oblique beams positioned on the same side of the satellite body in the first direction. The connecting oblique beams are inclined relative to a third direction, the first direction, and the second direction, and the first direction, the second direction, and the third direction are mutually perpendicular. The connecting beam includes a first inclined beam connecting end and a second inclined beam connecting end. The two first inclined beam connecting ends are fixedly connected to the two connecting beams in a one-to-one correspondence, and the two second inclined beam connecting ends are both used for fixed connection to the satellite body. The antenna docking frame assembly also includes two antenna docking frames that are fixed to both ends of the connecting beam in a one-to-one correspondence. In the first direction, each antenna docking frame is located inside the two connecting beams, and in the second direction, the side of the antenna docking frame facing away from the corresponding connecting beam is used for connection with the SAR antenna.

2. The phased array antenna deployment state holding fixture according to claim 1, characterized in that, The antenna docking frame assembly further includes a first heat insulation block. The cross-section of the connecting beam is L-shaped. The antenna docking frame is located within the L-shaped structure. In the second direction, one end of the antenna docking frame is used to be fixedly connected to the SAR antenna through the first heat insulation block, and the other end of the antenna docking frame is fixed to the connecting beam.

3. The phased array antenna deployment state holding fixture according to claim 1, characterized in that, The inclined frame assembly further includes a reinforcing frame, the long side of which is parallel to the second direction, and the wide side of which is parallel to the first direction. The first inclined beam connecting ends of the two connecting inclined beams in the inclined frame assembly are both fixed to the reinforcing frame. In the second direction, one end of the reinforcing frame is connected to the antenna docking frame of one of the antenna docking frame assemblies, and the other end of the reinforcing frame is connected to the antenna docking frame of another of the antenna docking frame assemblies.

4. The phased array antenna deployment state holding fixture according to claim 3, characterized in that, The reinforcing box and the antenna docking box are arranged in a third-direction upward direction.

5. The phased array antenna deployment state holding fixture according to claim 4, characterized in that, The inclined frame assembly also includes a connecting rod and two mounting blocks. The second inclined beam connecting ends of the two connecting inclined beams are fixedly connected to the two mounting blocks in a one-to-one correspondence. The two ends of the connecting rod are fixedly connected to the two mounting blocks in a one-to-one correspondence. Both mounting blocks are used to fix the satellite body.

6. The phased array antenna deployment state holding fixture according to any one of claims 1 to 5, characterized in that, It also includes a satellite connection reinforcement component fixed to the connecting beam. The satellite connection reinforcement component is disposed near the middle of the connecting beam in the first direction and is used to fix it to the satellite body.

7. The phased array antenna deployment state holding fixture according to claim 6, characterized in that, Two satellite connection reinforcement components are installed on each of the connecting beams. The two satellite connection reinforcement components are symmetrically arranged on both sides of the satellite body in a first direction. Each satellite connection reinforcement component includes a satellite connection block, a plurality of second heat insulation blocks and a plurality of third heat insulation blocks. The satellite connection block is used to connect to the satellite body through at least one second heat insulation block, and the satellite connection block is used to be fixedly connected to the connecting beam through at least one third heat insulation block.

8. The phased array antenna deployment state holding fixture according to claim 7, characterized in that, The satellite connecting block includes a first connecting plate portion, a second connecting plate portion, and a third connecting plate portion that are perpendicularly connected to each other in pairs. The first connecting plate portion is arranged perpendicular to the first direction, the second connecting plate portion is perpendicular to the third direction, and the third connecting plate portion is perpendicular to the second direction. An L-shaped groove for accommodating the corner of the satellite body is provided between the first connecting plate portion and the second connecting plate portion. The first connecting plate portion and the second connecting plate portion are both used for fixed connection with the satellite body, and the third connecting plate portion is fixedly connected to the connecting beam. The satellite connecting block also includes a first reinforcing plate portion and a second reinforcing plate portion. The first reinforcing plate portion is arranged parallel to the third connecting plate portion. The first connecting plate portion and the second connecting plate portion are both fixedly connected to the first reinforcing plate portion. The second reinforcing plate portion is parallel to the first connecting plate portion. The second connecting plate portion and the third connecting plate portion are both fixedly connected to the second reinforcing plate portion.

9. A method for assembling a phased array antenna deployment state maintenance fixture with a satellite, characterized in that, The method is implemented using the phased antenna deployment state holding fixture as described in any one of claims 1 to 8, wherein the phased antenna deployment state holding fixture further includes a satellite connection reinforcement component; the method includes: The SAR satellite is mounted on a support vehicle so that the radiating surface of the SAR antenna is perpendicular to the horizontal plane. The two unfolded subarrays of the SAR antenna are hoisted by a gravity compensation suspension system and the SAR antenna is unfolded under zero gravity. Both deployed subarrays are fixedly connected to the antenna docking frame assembly located below, and the satellite body is fixedly connected to each of the star body connection and reinforcement assemblies located below. Separate the overgravity compensation suspension system from the SAR satellite and fix the two deployable subarrays to the antenna docking frame assembly located above; Both oblique frame components are fixed to the satellite body and the two antenna docking frame components.

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