Ground zero-gravity deployment test equipment for two-dimensional deployable planar antenna

Abstract

The invention discloses ground zero-gravity deployment test equipment for a two-dimensional deployable planar antenna, and relates to the technical field of satellite ground tests. The first follow-up assembly and the second follow-up assembly are movably installed on the supporting truss in the horizontal direction and used for passively following unfolding and folding movement of the panel antenna; the at least two unloading assemblies are detachably connected with the first follow-up assembly or the second follow-up assembly and used for hanging and gravity unloading of the panel antenna; the satellite overturning vehicle is used for changing the attitude of the panel antenna; and the switching assembly is mounted on the satellite turnover vehicle and is used for connecting the panel antenna. The device combines the unfolding principle of the two-dimensional deployable planar antenna and the precise unloading requirements of gravity and gravitational torque in the unfolding process, provides powerful technical support and engineering practice guarantee for smooth unfolding and stability keeping of the planar antenna after a satellite is in orbit, and has important significance for guaranteeing normal operation of a satellite system.

Description

Technical Field

[0001] The present application relates to the technical field of satellite ground tests, and in particular to a ground zero-gravity deployment test device for a two-dimensional deployable flat-panel antenna. Background Art

[0002] Satellites operate in a state of weightlessness while in orbit, a stark contrast to the conditions on Earth where they are subject to gravity. As a key component of satellite systems, the smooth deployment and stability of large, deployable flat-panel antennas onboard are crucial for their operation. To ensure this, ground-based zero-gravity deployment testing of flat-panel antennas is essential. Therefore, developing a set of high-precision zero-gravity deployment test equipment for two-dimensional deployable flat-panel antennas is crucial for ensuring the normal operation of satellite systems. Summary of the Invention

[0003] In view of this, the purpose of this application is to provide a ground zero-gravity deployment test equipment for a two-dimensional deployable flat-panel antenna to solve the above technical problems.

[0004] The present application provides a ground-based zero-gravity deployment test device for a two-dimensional deployable flat-panel antenna, comprising: a support truss; a first follower assembly and a second follower assembly, both movably mounted on the support truss in a horizontal direction, for passively following the deployment and retraction movements of the flat-panel antenna; at least two unloading assemblies, detachably connected to the first follower assembly or the second follower assembly, for suspending and gravity unloading the flat-panel antenna; a satellite flip vehicle, for changing the posture of the flat-panel antenna; and a adapter assembly, mounted on the satellite flip vehicle, for connecting the flat-panel antenna.

[0005] In some optional embodiments, the supporting truss includes a truss, a plurality of slide rails, and a plurality of movable bases, wherein the plurality of slide rails are installed in parallel on a horizontal plane at the top of the truss for installation and horizontal sliding of a first follower assembly and a second follower assembly, and the plurality of movable bases are installed at the bottom of the truss for movement of the truss.

[0006] In some optional embodiments, each movable base includes a base body, multiple rollers with brakes, and multiple adjustable supports, the multiple rollers with brakes are installed at the bottom of the base body, the multiple adjustable supports are installed on the base body, and each adjustable support can be raised and lowered.

[0007] In some optional embodiments, each adjustable support includes a screw, a handle and a support, the screw has a self-locking thread and is threadedly connected to the base body in a vertically liftable manner, the handle is installed at the upper end of the screw, and the support is installed at the lower end of the screw.

[0008] In some optional embodiments, the first follower assembly includes a first support frame, a plurality of first sliders, and a plurality of follower arms. The first support frame is slidably mounted on a plurality of slide rails through the plurality of first sliders. The plurality of follower arms are mounted on the side of the first support frame, and each follower arm is rotatable in a horizontal direction.

[0009] In some optional embodiments, the first support frame includes a first upper frame and a first lower frame connected up and down, the first upper frame spans across multiple slide rails along the width direction of the slide rails, and multiple first sliders are installed at each end of the first upper frame in the width direction of the corresponding slide rails, and the first lower frame is a rectangular frame structure; the multiple follower arms include a first follower arm, a second follower arm, a third follower arm, and a fourth follower arm, the first follower arm and the second follower arm are symmetrically installed on two opposite side surfaces of the first lower frame in the length direction of the corresponding slide rail, and the third follower arm and the fourth follower arm are both installed on a side surface of the first lower frame in the width direction of the corresponding slide rail and are respectively located on the left and right sides of the side surface.

[0010] In some optional embodiments, the second follower assembly includes a second support frame, a plurality of second sliders, and a plurality of follower arms. The second support frame is slidably mounted on a plurality of slide rails through the plurality of second sliders. The plurality of follower arms are mounted on the side and bottom of the second support frame, and each follower arm is rotatable in the horizontal direction.

[0011] In some optional embodiments, the second support frame includes a second upper frame, a middle frame, and a second lower frame connected in sequence from top to bottom, the second upper frame spans across multiple slide rails along the width direction of the slide rails, and multiple second sliders are installed at each end of the second upper frame in the corresponding width direction of the slide rails, the middle frame is a rectangular frame structure and the bottom surface is two-stepped along the length direction of the slide rails, divided into an upper bottom surface and a lower bottom surface, the second lower frame is a rectangular frame structure and is connected to the lower bottom surface, and is located in the middle position of the middle frame in the length direction of the slide rails; the multiple follower arms include a fifth follower arm, a sixth follower arm, a seventh follower arm, an eighth follower arm, and a ninth follower arm, the fifth follower arm and the sixth follower arm are distributedly installed on the upper bottom surface along the width direction of the slide rails, the seventh follower arm and the eighth follower arm are both installed on a side surface of the second lower frame in the corresponding width direction of the slide rails and are respectively located on the left and right sides of the side surface, and the ninth follower arm is installed on the side surface of the middle frame in the corresponding length direction of the slide rails and adjacent to the lower bottom surface.

[0012] In some optional embodiments, each unloading component includes a lifting ring, a force-adjusting forward and reverse buckle, a force gauge, a tension sensor, and a plurality of inelastic unloading ropes. The lifting ring, the force-adjusting forward and reverse buckle, the force gauge, and the tension sensor are connected from top to bottom in sequence through the inelastic unloading rope. The lifting ring is used to connect with the first follow-up component or the second follow-up component. The force-adjusting forward and reverse port is used to adjust the pulling force of the unloading component on the flat-panel antenna. The lower end of the tension sensor is also connected to an inelastic unloading rope, and the inelastic unloading rope is used to connect to the flat-panel antenna to realize the hanging of the flat-panel antenna.

[0013] In some optional embodiments, the adapter assembly includes an adapter flange, multiple legs, and a satellite body. The adapter flange is installed on the satellite flip vehicle and connected to the satellite body through the multiple legs. The satellite body is used to connect and support the flat panel antenna.

[0014] Based on the above technical solution, the ground zero-gravity deployment test equipment for a two-dimensional deployable flat-panel antenna provided in this application, the first follower assembly and the second follower assembly can passively follow the deployment and retraction movement of the flat-panel antenna, the unloading assembly can hang the flat-panel antenna on the first follower assembly or the second follower assembly, and can offset the gravity of the flat-panel antenna by adjusting the pulling force, thereby realizing the ground zero-gravity deployment test of the flat-panel antenna. This equipment combines the deployment principle of the two-dimensional deployable flat-panel antenna and the precise unloading requirements of gravity and gravitational torque during the deployment process, providing strong technical support and engineering practice guarantees for the smooth deployment and stability of the flat-panel antenna after the satellite is in orbit, which is of great significance for ensuring the normal operation of the satellite system. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0016] Figure 1 A schematic diagram of the antenna in the folded state of a ground zero-gravity deployment test device for a two-dimensional deployable flat-panel antenna provided in an embodiment of the present application.

[0017] Figure 2 A schematic diagram of the antenna deployment state of a ground zero-gravity deployment test device for a two-dimensional deployable flat-panel antenna provided in an embodiment of the present application.

[0018] Figure 3 A schematic structural diagram of a support truss provided in an embodiment of the present application with a movable base hidden.

[0019] Figure 4A schematic structural diagram of a truss unit provided in an embodiment of the present application.

[0020] Figure 5 A schematic structural diagram of a movable base provided in an embodiment of the present application.

[0021] Figure 6 A schematic structural diagram of a first follower assembly and a second follower assembly on a support truss provided in an embodiment of the present application.

[0022] Figure 7 A schematic structural diagram of a first follower assembly provided in an embodiment of the present application.

[0023] Figure 8 A schematic structural diagram of a second follower assembly provided in an embodiment of the present application.

[0024] Figure 9 A schematic diagram of the structure of an uninstall component provided in an embodiment of the present application.

[0025] Figure 10 A schematic structural diagram of a switching assembly provided in an embodiment of the present application.

[0026] Figures 11 to 24 They are schematic diagrams of various steps of a ground zero-gravity deployment test method for a two-dimensional deployable flat-panel antenna provided in an embodiment of the present application.

[0027] Figure numerals: 100, ground zero-gravity deployment test equipment; 10, supporting truss; 11, truss; 111, column; 112, first crossbeam; 113, second crossbeam; 114, truss unit; 1141, connecting rod; 1142, ball joint pair; 1143, diagonal brace; 12, slide rail; 13, movable base; 131, base body; 132, roller with brake; 133, adjustable support; 1331, screw; 1332, handle; 1333, support; 20, first follower assembly; 21, first support frame; 211, first upper frame; 212, first lower frame; 22, first slider; 23, first follower arm; 24, second follower arm; 25, third follower arm; 26, fourth follower arm; 30, second follower assembly; 31, second support frame; 311, second upper frame ;312, middle frame;313, second lower frame;32, second slider;33, fifth follower arm;34, sixth follower arm;35, seventh follower arm;36, eighth follower arm;37, ninth follower arm;40, unloading assembly;41, lifting ring;42, force adjustment positive and negative buckle;43, tension meter;44, tension sensor;45, inelastic unloading rope;50, satellite flip car;60, adapter assembly;61, adapter flange;62, support leg;63, satellite body;A, flat antenna;A1, four-panel assembly;A2, four-panel assembly;A3, three-panel assembly;A4, four-panel assembly;A5, four-panel assembly;A6, three-panel assembly;A7, four-panel assembly;A8, four-panel assembly;A9, three-panel assembly;A10, three-panel assembly;A11, four-panel assembly;A12, three-panel assembly. DETAILED DESCRIPTION

[0028] Specific embodiments of the present application will be described in detail below with reference to the accompanying drawings. It is apparent that the described embodiments are only a portion of the embodiments of the present application, and not all of the embodiments. All other embodiments derived by persons of ordinary skill in the art based on the description of this application without inventive effort are intended to fall within the scope of protection of this application.

[0029] In the description of this application, unless otherwise specified or limited, the terms "connect," "dispose," and "install" should be understood broadly. For example, "connect" can mean a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can mean that two components are internally connected. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0030] The terms "upper", "lower", "left", "right", "front", "back", "center", "top", "bottom", "inside", "outside", "vertical", "horizontal", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, or the orientation or position relationship in which the product of the application is usually placed when used. They are only for the convenience of description and simplification of description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, they should not be understood as limiting the present application.

[0031] The terms "first," "second," "third," etc. are merely used to distinguish elements of similar nature, and do not indicate or imply relative importance or a particular order, unless expressly specified and limited otherwise.

[0032] The terms "comprises," "includes," "has," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not expressly listed or inherent to such process, method, article, or apparatus. In the absence of more limitations, an element defined by the phrase "comprising a ..." does not preclude the presence of additional identical elements in the process, method, article, or apparatus that includes the element.

[0033] The term "plurality" means two or more (including two).

[0034] The term "and / or" is a description of the association relationship of associated objects, indicating that three relationships can exist. For example, A and / or B can mean: A exists alone, A and B exist at the same time, and B exists alone.

[0035] The terms "one embodiment," "as an example," "in one implementation," and the like mean that the specific features, structures, materials, or characteristics described in conjunction with the embodiment or example may be included in at least one embodiment or example of the present application. The schematic representations of such terms do not necessarily refer to the same embodiment, nor are they mutually exclusive independent or alternative embodiments. The embodiments and features within the embodiments of the present application may be combined in appropriate ways unless there is a conflict.

[0036] Figure 1 This is a schematic diagram of the antenna folded state of a ground zero-gravity deployment test device 100 of a two-dimensional deployable flat-panel antenna provided in an embodiment of the present application. Figure 2 Schematic diagram of the antenna deployment state of a ground zero-gravity deployment test device 100 of a two-dimensional deployable flat-panel antenna provided in an embodiment of the present application.

[0037] like Figure 1 and Figure 2 As shown, an embodiment of the present application provides a ground-based zero-gravity deployment test apparatus 100 for a two-dimensional deployable flat panel antenna. The apparatus comprises a support truss 10, a first follower assembly 20, a second follower assembly 30, at least two unloading assemblies 40 (not shown), a satellite tumbler 50, and an adapter assembly 60. The support truss 10 serves as a load-bearing carrier, carrying the first and second follower assemblies 20, 30, and the loads thereon. The first and second follower assemblies 20, 30 serve as passive tracking devices, both horizontally movably mounted on the support truss 10 to passively follow the deployment and retraction of the flat panel antenna A. The unloading assembly 40 is detachably connected to the first or second follower assembly to facilitate the suspension and gravity unloading of the flat panel antenna A. The satellite tumbler 50 is used to adjust the posture of the flat panel antenna A. The adapter assembly 60 is mounted on the satellite tumbler 50 and is connected to the flat panel antenna A. Each component is described in detail below.

[0038] like Figure 3 As shown, the support truss 10 includes a truss 11, a slide rail 12, and a movable base 13 ( Figure 3 Not shown, see Figure 1 and Figure 2 Truss 11 serves as a load-bearing structure and is comprised of multiple detachable truss units 114. Slide rails 12 are horizontally mounted on the top of truss 11, supporting the installation and horizontal sliding of first and second follower assemblies 20 and 30. A movable base 13 is mounted on the bottom of truss 11 to facilitate its movement.

[0039] Regarding the truss 11, as an example, the truss 11 includes four columns 111, two first cross beams 112, and two second cross beams 113. The four columns 111 are arranged in a rectangular array, and the two first cross beams 112 and two second cross beams 113 are arranged in a rectangular array and connected between the tops of the four columns 111. Specifically, the columns 111 are composed of nine truss units 114, the first cross beams 112 are composed of three truss units 114, and the second cross beams 113 are composed of eight truss units 114. The three-dimensional dimensions of a single truss unit 114 are 692mm*692mm*692mm, and the three-dimensional dimensions of the truss 11 are 3460mm*6920mm*6228mm.

[0040] Regarding the slide rails 12 , as an example, there are two slide rails 12 , which are arranged on the same horizontal plane and parallel to the second beams 113 of the truss 11 , and the two slide rails 12 are connected to the two second beams 113 via connectors, respectively.

[0041] Regarding the truss unit 114, as an example, Figure 4 As shown, each truss unit 114 is a cubic frame structure, including twelve connecting rods 1141 and eight ball-jointed connection pairs 1142. The twelve connecting rods 1141 are distributed along the twelve edges of the cube, and the eight ball-jointed connection pairs 1142 are distributed corresponding to the eight vertices of the cube. Each ball-jointed connection pair 1142 connects the ends of adjacent connecting rods 1141. Two adjacent truss units 114 are connected by sharing four connecting rods 141 and four ball-jointed connection pairs 1142. In order to enhance structural strength, each truss unit 114 may further include four diagonal braces 1143, which are arranged along a diagonal line of the four sides of the cube, and one end of the diagonal braces 1143 on two adjacent sides is connected to the same ball-jointed connection pair 1142.

[0042] Regarding the movable base 13, as an example, Figure 1 、 Figure 2 and Figure 5 As shown, there are four movable bases 13, each mounted at the bottom of four columns 111. Each movable base 13 comprises a base body 131, four braked rollers 132, and four adjustable supports 133. The base body 131 is a square frame structure, with its four corners connected to ball joints 1142 at the four corners of the base of the column 111 via bolts. The braked rollers 132 are universal wheels, mounted in the middle of the bottom of each of the four sides of the base body 131. Four adjustable supports 133 are arranged in a rectangular array on two diagonal lines of the base body 131. Each adjustable support 133 includes a screw 1331, a handle 1332, and a support 1333. The screw 1331 uses a self-locking thread and is vertically threadedly connected to the base body 131 so that it can be raised and lowered. The handle 1332 is mounted at the upper end of the screw 1331, and the support 1333 is mounted at the lower end of the screw 1331. When the support truss 10 needs to be moved, the handle 1332 of each adjustable support 133 is operated to raise the screw 1331 and the support 1333, which can then be moved via the braked roller 132. When the support truss 10 needs to be fixed, the handle 1332 of each adjustable support 133 is operated to lower the screw 1331 and the support 1333 to the ground. The support 1333 contacts the ground and applies pressure, thereby ensuring that the support truss 10 is firmly positioned.

[0043] Figure 6 A schematic structural diagram of a first follower assembly 20 and a second follower assembly 30 on a support truss 10 is provided in an embodiment of the present application. Figure 6 As shown, the first follower assembly 20 and the second follower assembly 30 are both movably mounted on the slide rail 12 of the support truss 10 along the horizontal direction.

[0044] like Figure 7 As shown, the first follower assembly 20 includes a first support frame 21, a plurality of first sliders 22, and a plurality of follower arms. The first support frame 21 is slidably mounted on the slide rail 12 of the support truss 10 via the plurality of first sliders 22. The plurality of follower arms are mounted on the sides of the first support frame 21, and each follower arm is rotatable in the horizontal direction.

[0045] Regarding the first support frame 21, as an example, it comprises a first upper frame 211 and a first lower frame 212 connected vertically. The first upper frame 211 spans the two slide rails 12 along their width direction (i.e., the direction perpendicular to the slide rails 12), and two first sliders 22 are mounted on each end of the first upper frame 211 corresponding to the width of the slide rails 12. The first lower frame 212 is a rectangular parallelepiped frame structure.

[0046] Regarding the multiple follower arms of the first follower assembly 20, as an example, the multiple follower arms include a first follower arm 23, a second follower arm 24, a third follower arm 25, and a fourth follower arm 26. The first follower arm 23 and the second follower arm 24 are symmetrically mounted on two opposite side surfaces of the first lower frame 212 in the length direction of the corresponding slide rail 12, and the third follower arm 25 and the fourth follower arm 26 are both mounted on a side surface of the first lower frame 212 in the width direction of the corresponding slide rail 12 and are respectively located on the left and right sides of the side surface.

[0047] like Figure 8 As shown, the second follower assembly 30 includes a second support frame 31, a plurality of second sliders 32, and a plurality of follower arms. The second support frame 31 is slidably mounted on the slide rail 12 of the support truss 10 via the plurality of second sliders 32. The plurality of follower arms are distributed and mounted on the sides and bottom of the second support frame 31, and each follower arm is rotatable in the horizontal direction.

[0048] Regarding the second support frame 31, as an example, the second support frame 31 includes a second upper frame 311, a middle frame 312, and a second lower frame 313 connected in sequence from top to bottom. Among them, the second upper frame 311 spans across the two slide rails 12 along the width direction of the slide rails 12, and three second sliders 32 are installed at each end of the corresponding slide rails 12 in the width direction. The middle frame 312 is a rectangular parallelepiped frame structure, and its bottom surface is in a two-step shape along the length direction of the slide rail 12, divided into an upper bottom surface and a lower bottom surface. The second lower frame 313 is a rectangular parallelepiped frame structure, connected to the lower bottom surface of the middle frame 312, and is located in the middle position of the middle frame 312 in the length direction of the slide rail 12.

[0049] Regarding the multiple follower arms of the second follower assembly 30, as an example, the multiple follower arms include a fifth follower arm 33, a sixth follower arm 34, a seventh follower arm 35, an eighth follower arm 36, and a ninth follower arm 37. The fifth follower arm 33 and the sixth follower arm 34 are installed on the upper bottom surface of the middle frame 312 in a distributed manner along the width direction of the slide rail 12. The seventh follower arm 35 and the eighth follower arm 36 are both installed on a side surface of the second lower frame 313 corresponding to the width direction of the slide rail 12 and are respectively located on the left and right sides of the side surface. The ninth follower arm 37 is installed on a side surface of the middle frame 312 corresponding to the length direction of the slide rail 12 and adjacent to the lower bottom surface.

[0050] Regarding the structure of the follower arm, as an example, each follower arm mainly includes a follower arm body, a rotating shaft, and multiple hanging buckles. The follower arm body is arranged in a horizontal direction, with one end of the follower arm body mounted on the supporting frame via the rotating shaft, and the other end of the follower arm body suspended in the air, so that the follower arm body can rotate in the horizontal direction. Multiple hanging buckles are mounted on the follower arm body, each of which is movable along the follower arm body to adjust its position, and the hanging buckles are used to hang the unloading assembly 40. To enhance structural strength, the follower arm body can be designed as a right-angled triangle structure, with multiple hanging buckles mounted on the horizontal right-angled sides of the right-angled triangle.

[0051] The unloading assembly 40 is used for hanging and gravity unloading of the flat antenna A on the first follower assembly 20 or the second follower assembly 30 to achieve a zero gravity environment for the flat antenna A. As an example, Figure 9As shown, the unloading assembly 40 includes a lifting ring 41, a force-adjusting buckle 42, a tension gauge 43, a tension sensor 44, and multiple inelastic unloading ropes 45. The lifting ring 41, force-adjusting buckle 42, tension gauge 43, and tension sensor 44 are sequentially connected via the inelastic unloading ropes 45. The lifting ring 41 is mounted on the lifting ring of the follower arm. The force-adjusting buckle 42 is used to adjust the tension applied by the unloading assembly 40 to the flat panel antenna A. The tension gauge 43 is used to measure tension for quick adjustment. The tension sensor 44 is used to accurately measure tension. Specifically, the tension gauge 43 is a spring tension gauge. The tension sensor 44 is an S-shaped tension sensor with a digital display. The digital display is connected to the S-shaped tension sensor via a data cable. One end of the S-shaped tension sensor is connected to the tension gauge 43 via the inelastic unloading rope 45. The other end of the S-shaped tension sensor is connected to another inelastic unloading rope 45. This inelastic unloading rope 45 is used to connect to the flat panel antenna A to suspend the flat panel antenna A. During the test, at least two unloading assemblies 40 are configured. The lifting ring 41, the force-adjusting front and back buckle 42, the tension meter 43, and the tension sensor 44 of each unloading assembly 40 are arranged in sequence from top to bottom. The lifting ring 41 is installed on the lifting buckle of the follower arm, and the inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the flat antenna A. By adjusting the force-adjusting front and back buckle 42 and coordinating the tension measurement of the tension meter 43 and the tension sensor 44, the tension of the inelastic unloading rope 45 on the flat antenna A can be quickly and accurately adjusted, thereby offsetting the gravity of the flat antenna A and making the flat antenna A in a zero-gravity state during the test.

[0052] The satellite flipping vehicle 50 is used to drive the flat panel antenna A to flip, so as to meet the requirements of the flat panel antenna A for different postures during the zero-gravity deployment test on the ground. The satellite flipping vehicle 50 can adopt existing technology. As an example, the satellite flipping vehicle 50 can drive the flat panel antenna A to flip on a vertical plane.

[0053] The adapter assembly 60 is mounted on the satellite flip car 50 and is used to connect the flat panel antenna A. As an example, Figure 10 As shown, the adapter assembly 60 includes an adapter flange 61, a plurality of legs 62, and a satellite body 63. The adapter flange 61 is mounted on the satellite flip vehicle 50 and is connected to the satellite body 63 via a plurality of parallel legs 62. The satellite body 63 is a rectangular parallelepiped structure used to connect and support the flat panel antenna A.

[0054] The specific steps of performing a ground zero gravity deployment test on a two-dimensional inn flat panel antenna using the ground zero gravity deployment test equipment 100 are as follows: Before the test begins, the flat antenna A to be tested is mounted on the star body 63 of the adapter assembly 60 .

[0055] S1: If Figure 11As shown, first, move the first follower assembly 20 to the middle position of the slide rail 12, move the satellite flip car 50 to the bottom of the first follower assembly 20, and adjust the rotation axis of the four-panel assembly A1 of the flat antenna A in the vertical direction with the first follower arm 23 (see Figure 7 ) are aligned with the rotating shaft of the first follower arm 23. Then, install two unloading assemblies 40. The lifting ring 41 of each unloading assembly 40 is installed on the lifting buckle of the first follower arm 23. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the four-panel assembly A1. Adjust the force-adjusting positive and negative buckles 42 so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the four-panel assembly A1. Next, manually unfold the four-panel assembly A1. After confirming that the unfolding is normal, automatically unfold the four-panel assembly A1. After the automatic unfolding is in place, first rigidly fix the four-panel assembly A1 to the star body 63, then remove the two unloading assemblies 40, and reset the first follower arm 23.

[0056] S2: If Figure 12 As shown, first, adjust the rotation axis of the four-panel assembly A2 in the vertical direction with the second follower arm 24 (see Figure 7 ) are aligned with the rotating shaft of the second follower arm 24. Next, install two unloading assemblies 40. The lifting ring 41 of each unloading assembly 40 is mounted on the lifting buckle of the second follower arm 24. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the four-panel assembly A2. Adjust the force-adjusting positive and negative buckles 42 so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the four-panel assembly A2. Next, manually unfold the four-panel assembly A2. After confirming that the unfolding is normal, automatically unfold the four-panel assembly A2. After the automatic unfolding is in place, first rigidly fix the four-panel assembly A2 to the star body 63, then remove the two unloading assemblies 40 and reset the second follower arm 24.

[0057] S3: If Figure 13 As shown, the satellite flipping vehicle 50 drives the current flat panel antenna A to rotate 90° clockwise.

[0058] S4: As Figure 14 As shown, first, adjust the rotation axis of the three-panel assembly A3 in the vertical direction with the first follower arm 23 (see Figure 7) are aligned with the rotating shaft of the first follower arm 23. Next, install two unloading assemblies 40. The lifting ring 41 of each unloading assembly 40 is mounted on the lifting buckle of the first follower arm 23. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the three-panel assembly A3. Adjust the force-adjusting positive and negative buckle 42 so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the three-panel assembly A3. Next, manually unfold the three-panel assembly A3. After confirming that the unfolding is normal, automatically unfold the three-panel assembly A3. After the automatic unfolding is in place, first rigidly secure the three-panel assembly A3 to the star body 63, then remove the two unloading assemblies 40 and reset the first follower arm 23.

[0059] S5: If Figure 15 As shown, first, adjust the rotation axis of the four-panel assembly A4 in the vertical direction with the third follower arm 25 (see Figure 7 ) are aligned with the rotating shaft of the third follower arm 25. Next, install two unloading assemblies 40, with the lifting ring 41 of each unloading assembly 40 mounted on the lifting hook of the third follower arm 25. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the four-panel assembly A4. Adjust the force-adjusting positive and negative hooks 42 so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 counteracts the gravity of the four-panel assembly A4. Next, manually unfold the four-panel assembly A4. After confirming that the unfolding is normal, automatically unfold the four-panel assembly A4. Once the automatic unfolding is in place, first rigidly secure the four-panel assembly A4 to the star body 63, then remove the two unloading assemblies 40 and reset the third follower arm 25.

[0060] S6: As Figure 16 As shown, first, adjust the rotation axis of the four-panel assembly A5 in the vertical direction with the fourth follower arm 26 (see Figure 7 ) are aligned with the rotating shaft of the fourth follower arm 26. Then, two unloading assemblies 40 are installed. The lifting ring 41 of each unloading assembly 40 is mounted on the lifting buckle of the fourth follower arm 26. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the four-panel assembly A5. The force-adjusting positive and negative buckles 42 are adjusted so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the four-panel assembly A5. Next, the four-panel assembly A5 is manually unfolded. After confirming that the unfolding is normal, the four-panel assembly A5 is automatically unfolded. After the automatic unfolding is in place, the four-panel assembly A5 is first rigidly fixed to the star body 63, and then the two unloading assemblies 40 are removed and the fourth follower arm 26 is reset.

[0061] S7: As Figure 17 As shown, first, adjust the rotation axis of the three-panel assembly A6 in the vertical direction with the second follower arm 24 (see Figure 7) are aligned with the rotating shaft of the second follower arm 24. Next, install two unloading assemblies 40. The lifting ring 41 of each unloading assembly 40 is mounted on the lifting hook of the second follower arm 24. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the three-panel assembly A6. Adjust the force-adjusting positive and negative buckles 42 so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 offsets the gravity of the three-panel assembly A6. Next, manually unfold the three-panel assembly A6. After confirming that the unfolding is normal, automatically unfold the three-panel assembly A6. After automatic unfolding, first rigidly secure the three-panel assembly A6 to the star body 63, then remove the two unloading assemblies 40 and reset the second follower arm 24.

[0062] S8: Figure 18 As shown, the satellite flip car 50 drives the current flat-panel antenna A to rotate counterclockwise 90°, moves the first follower assembly 20 to a safe position (as shown in the figure, near the end of the slide rail), and moves the second follower assembly 30 to directly above the satellite flip car 50.

[0063] S9: As Figure 19 As shown, first, adjust the rotation axis of the four-panel assembly A7 in the vertical direction with the fifth follower arm 33 (see Figure 8 ) are aligned with the rotating shaft of the fifth follower arm 33. Then, install two unloading assemblies 40. The lifting ring 41 of each unloading assembly 40 is installed on the lifting buckle of the fifth follower arm 33. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the four-panel assembly A7. Adjust the force-adjusting positive and negative buckles 42 so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the four-panel assembly A7. Next, manually unfold the four-panel assembly A7. After confirming that the unfolding is normal, automatically unfold the four-panel assembly A7. After the automatic unfolding is in place, first rigidly fix the four-panel assembly A7 to the star body 63, then remove the two unloading assemblies 40, and reset the fifth follower arm 33.

[0064] S10: Figure 20 As shown, first, adjust the rotation axis of the four-panel assembly A8 in the vertical direction with the seventh follower arm 35 (see Figure 8 ) are aligned with the rotating shaft of the seventh follower arm 35. Then, two unloading assemblies 40 are installed. The lifting ring 41 of each unloading assembly 40 is installed on the lifting buckle of the seventh follower arm 35. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the four-panel assembly A8. The force-adjusting positive and negative buckles 42 are adjusted so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the four-panel assembly A8. Next, the four-panel assembly A8 is manually unfolded. After confirming that the unfolding is normal, the four-panel assembly A8 is automatically unfolded. After the automatic unfolding is in place, the four-panel assembly A8 is first rigidly fixed to the star body 63, and then the two unloading assemblies 40 are removed and the seventh follower arm 35 is reset.

[0065] S11: If Figure 21 As shown, first, move the second follower assembly 30 to a safe position (as shown in the figure, near the end of the slide rail), and move the first follower assembly 20 to the top of the satellite flip car 50. Then, adjust the rotation axis of the three-panel assembly A9 in the vertical direction with the third follower arm 25 (see Figure 7 ) are aligned with the rotating shaft of the third follower arm 25. Next, install two unloading assemblies 40. The lifting ring 41 of each unloading assembly 40 is mounted on the lifting buckle of the third follower arm 25. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the three-panel assembly A9. Adjust the force-adjusting positive and negative buckles 42 so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the three-panel assembly A9. Next, manually unfold the three-panel assembly A9. After confirming that the unfolding is normal, automatically unfold the three-panel assembly A9. After the automatic unfolding is in place, first rigidly fix the three-panel assembly A9 to the star body 63, then remove the two unloading assemblies 40 and reset the third follower arm 25.

[0066] S12: Figure 22 As shown, first, move the first follower assembly 20 to a safe position (as shown in the figure, near the end of the slide rail), and move the second follower assembly 30 to the top of the satellite flip car 50. Then, adjust the rotation axis of the three-panel assembly A10 in the vertical direction and the eighth follower arm 36 (see Figure 8 ) are aligned with the rotating shaft of the third panel assembly A10. Afterwards, two unloading assemblies 40 are installed. The lifting ring 41 of each unloading assembly 40 is installed on the lifting buckle of the eighth follower arm 36. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the three-panel assembly A10. The force-adjusting positive and negative buckles 42 are adjusted so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the three-panel assembly A10. Next, the three-panel assembly A10 is manually unfolded. After confirming that the unfolding is normal, the three-panel assembly A10 is automatically unfolded. After the automatic unfolding is in place, the three-panel assembly A10 is first rigidly fixed to the star body 63, and then the two unloading assemblies 40 are removed and the eighth follower arm 36 is reset.

[0067] S13: If Figure 23 As shown, first, adjust the rotation axis of the four-panel assembly A11 in the vertical direction with the ninth follower arm 37 (see Figure 8) are aligned with the rotating shaft of the fourth panel assembly A11. Then, two unloading assemblies 40 are installed. The lifting ring 41 of each unloading assembly 40 is installed on the lifting buckle of the ninth follower arm 37. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the four-panel assembly A11. The force-adjusting positive and negative buckles 42 are adjusted so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the four-panel assembly A11. Next, the four-panel assembly A11 is manually unfolded first. After confirming that the unfolding is normal, the four-panel assembly A11 is automatically unfolded. After the automatic unfolding is in place, the four-panel assembly A11 is first rigidly fixed to the star body 63, and then the two unloading assemblies 40 are removed and the ninth follower arm 37 is reset.

[0068] S14: Figure 24 As shown, first, adjust the rotation axis of the three-panel assembly A12 in the vertical direction with the sixth follower arm 34 (see Figure 8 ) are aligned with the rotating shaft of the sixth follower arm 34. Next, install two unloading assemblies 40. The lifting ring 41 of each unloading assembly 40 is mounted on the lifting buckle of the sixth follower arm 34. The inelastic unloading rope 45 at the lower end of the tension sensor 44 is connected to the three-panel assembly A12. Adjust the force-adjusting positive and negative buckles 42 so that the tension of the inelastic unloading ropes 45 of the two unloading assemblies 40 can offset the gravity of the three-panel assembly A12. Next, manually unfold the three-panel assembly A12. After confirming that the unfolding is normal, automatically unfold the three-panel assembly A12. After the automatic unfolding is in place, first rigidly fix the three-panel assembly A12 to the star body 63, then remove the two unloading assemblies 40 and reset the sixth follower arm 34.

[0069] In summary, the ground zero-gravity deployment test equipment for a two-dimensional deployable flat-panel antenna provided in the embodiment of the present application, the first follower component and the second follower component can passively follow the deployment and retraction movement of the flat-panel antenna, the unloading component can hang the flat-panel antenna on the first follower component or the second follower component, and can offset the gravity of the flat-panel antenna by adjusting the pulling force, thereby realizing the ground zero-gravity deployment test of the flat-panel antenna. This equipment combines the deployment principle of the two-dimensional deployable flat-panel antenna and the precise unloading requirements of gravity and gravitational torque during the deployment process, and provides strong technical support and engineering practice guarantees for the smooth deployment and stability of the flat-panel antenna after the satellite is in orbit, which is of great significance for ensuring the normal operation of the satellite system.

[0070] The above is only a specific implementation method of the present application, but the scope of protection of the present application is not limited thereto. Any technician familiar with the field can easily think of various changes or replacements within the technical scope disclosed in the present application, which should all be included in the scope of protection of the present application.

Claims

1. A ground zero gravity deployment test equipment for a two-dimensional deployable flat panel antenna, characterized in that: include: Support trusses; The first follower assembly and the second follower assembly are both movably mounted on the support truss in the horizontal direction and are used to passively follow the expansion and retraction movement of the flat panel antenna; At least two unloading assemblies, detachably connected to the first follower assembly or the second follower assembly, for hanging and gravity unloading the flat panel antenna; Satellite flip car, used to change the attitude of flat-panel antenna; as well as The adapter assembly is installed on the satellite flip vehicle and is used to connect the flat panel antenna.

2. The ground zero gravity deployment test equipment according to claim 1, characterized in that: The supporting truss includes a truss, multiple slide rails, and multiple movable bases. The multiple slide rails are installed in parallel on the horizontal plane at the top of the truss for the installation and horizontal sliding of the first follower assembly and the second follower assembly. The multiple movable bases are installed at the bottom of the truss for the movement of the truss.

3. The ground zero gravity deployment test equipment according to claim 2, characterized in that: Each of the movable bases includes a base body, a plurality of rollers with brakes, and a plurality of adjustable supports. The plurality of rollers with brakes are installed at the bottom of the base body, the plurality of adjustable supports are installed on the base body, and each of the adjustable supports can be raised and lowered.

4. The ground zero gravity deployment test equipment according to claim 3, characterized in that: Each adjustable support includes a screw, a handle and a support. The screw has a self-locking thread and is threadedly connected to the base body in a vertically liftable manner. The handle is installed at the upper end of the screw, and the support is installed at the lower end of the screw.

5. The ground zero gravity deployment test equipment according to claim 2, characterized in that: The first follower assembly includes a first support frame, multiple first sliders, and multiple follower arms. The first support frame is slidably mounted on multiple slide rails through multiple first sliders. Multiple follower arms are mounted on the side of the first support frame, and each follower arm is rotatable in the horizontal direction.

6. The ground zero gravity deployment test equipment according to claim 5, characterized in that: The first support frame includes a first upper frame and a first lower frame connected to each other in an upper and lower direction, the first upper frame spans over the plurality of slide rails along the width direction of the slide rails, a plurality of first sliding blocks are respectively installed at both ends of the first upper frame corresponding to the width direction of the slide rails, and the first lower frame is a rectangular parallelepiped frame structure; The multiple follower arms include a first follower arm, a second follower arm, a third follower arm, and a fourth follower arm. The first follower arm and the second follower arm are symmetrically installed on two opposite side surfaces of the first lower frame corresponding to the length direction of the slide rail. The third follower arm and the fourth follower arm are both installed on a side surface of the first lower frame corresponding to the width direction of the slide rail and are respectively located on the left and right sides of the side surface.

7. The ground zero gravity deployment test equipment according to claim 2, characterized in that: The second follower assembly includes a second support frame, multiple second sliders, and multiple follower arms. The second support frame is slidably mounted on the multiple slide rails through the multiple second sliders. The multiple follower arms are mounted on the side and bottom of the second support frame, and each follower arm is rotatable in the horizontal direction.

8. The ground zero gravity deployment test equipment according to claim 7, characterized in that: The second support frame includes a second upper frame, a middle frame, and a second lower frame connected in sequence from top to bottom, the second upper frame spanning over the plurality of slide rails along the width direction of the slide rails, a plurality of second sliders are respectively installed at both ends of the second upper frame corresponding to the width direction of the slide rails, the middle frame is a rectangular parallelepiped frame structure and the bottom surface is in a two-step shape along the length direction of the slide rails, divided into an upper bottom surface and a lower bottom surface, the second lower frame is a rectangular parallelepiped frame structure and is connected to the lower bottom surface and is located in the middle position of the middle frame in the length direction of the slide rails; The multiple follower arms include a fifth follower arm, a sixth follower arm, a seventh follower arm, an eighth follower arm, and a ninth follower arm. The fifth follower arm and the sixth follower arm are distributedly installed on the upper bottom surface along the width direction of the slide rail. The seventh follower arm and the eighth follower arm are both installed on a side surface of the second lower frame corresponding to the width direction of the slide rail and are respectively located on the left and right sides of the side surface. The ninth follower arm is installed on a side surface of the middle frame corresponding to the length direction of the slide rail and adjacent to the lower bottom surface.

9. The ground zero gravity deployment test equipment according to claim 1, characterized in that: Each of the unloading components includes a lifting ring, a force-adjusting forward and reverse buckle, a force gauge, a force sensor, and a plurality of inelastic unloading ropes. The lifting ring, the force-adjusting forward and reverse buckle, the force gauge, and the force sensor are connected in sequence from top to bottom through the inelastic unloading rope. The lifting ring is used to be connected to the first follower component or the second follower component. The force-adjusting forward and reverse buckle is used to adjust the pulling force of the unloading component on the flat antenna. The lower end of the force sensor is further connected to an inelastic unloading rope, and the inelastic unloading rope is used to connect to the flat antenna to realize the hanging of the flat antenna.

10. The ground zero gravity deployment test equipment according to claim 1, characterized in that: The adapter assembly includes an adapter flange, a plurality of legs, and a satellite body. The adapter flange is installed on the satellite flip vehicle and is connected to the satellite body through the plurality of legs. The satellite body is used to connect and support the flat panel antenna.

Images