Truss installation scaffold and method for constructing large space truss

Abstract

Provided are a truss mounting outer frame for mounting truss units and a method for constructing a large space truss, the outer frame comprising a sleeve, a catching member, and an end plate, the method comprising the following steps: placing a truss unit in a stowed state in a cavity of the truss mounting outer frame; fixing a catching hand on a satellite or a truss unit, extending a telescopic arm, and pushing the mounting outer frame to move outward; unfolding the truss unit; changing the catching position of the catching hand, gradually pushing the mounting outer frame outward until the truss unit is completely unfolded; placing a next truss unit from an opening into the cavity, adjusting the attitude of the next truss unit using the end plate, and abutting the next truss unit with an adjacent truss unit, and repeating the foregoing mounting process to complete the unfolding of the next truss unit. The method realizes efficient on-orbit installation of modular truss units, thereby enabling construction of a large space truss structure of hundreds of meters to thousands of meters.

Description

Technical Field

[0001] This invention relates to the field of spacecraft, and more specifically to the field of truss structures. Background Technology

[0002] Space deployable truss structures are a new type of foldable structure that has emerged in the last thirty years along with the development of aerospace technology. They are folded and collapsed during ground launch and unfolded and locked into a working state after entering orbit. Due to the limitations of rocket payload volume and mass, the harsh mechanical conditions during launch, and the high cost of launch, the size of space trusses is currently limited and cannot meet the needs of large and super-large spacecraft in the hundreds or even thousands of meters range. Summary of the Invention

[0003] One object of the present invention is to provide a truss mounting frame that can efficiently assist in the deployment and installation of truss units.

[0004] To achieve the above objectives, a truss mounting frame is used to install truss units. Each truss unit includes multiple frame bodies and telescopic sections connecting the frame bodies. These telescopic sections allow the frame bodies to move closer or further apart, enabling the truss unit to be in a retracted or extended state. The mounting frame includes a sleeve, a catcher, and an end plate. The sleeve includes a cavity for accommodating the truss unit. The catcher, located at a first end of the sleeve, includes a telescopic arm and a catcher hand located at the end of the telescopic arm. The catcher hand is used to connect to a fixed point. The catcher provides a driving force to move the sleeve by means of the length change of the telescopic arm. The end plate, located at a second end of the sleeve, is used to connect to the end of the truss unit and includes a three-degree-of-freedom adjustment mechanism to adjust the attitude of the truss unit.

[0005] In one or more embodiments, the sleeve includes a plurality of side frames and a telescopic member connecting the side frames to enable the sleeve to be telescopic.

[0006] In one or more embodiments, the top of the sleeve forms an opening in the cavity.

[0007] In one or more embodiments, the truss unit includes a mating interface, and adjacent truss units are mated to each other through the mating interface to form a truss structure.

[0008] Another objective of this invention is to provide a method for constructing large-scale space trusses, which can efficiently and conveniently construct space truss structures hundreds or thousands of kilometers long in orbit.

[0009] To achieve the above objectives, a method for constructing large-scale space trusses uses the aforementioned truss mounting frame to install truss units. This method includes the following steps: S1. Placing the truss unit in its retracted state within the cavity of the truss mounting frame; S2. Fixing the grabber to a satellite or truss unit, extending the telescopic arm, and pushing the mounting frame outwards; S3. Deploying the truss unit; S4. Changing the grabber's position, gradually pushing the mounting frame outwards until the truss unit is fully deployed; S5. Inserting the next truss unit into the cavity through the opening, adjusting the attitude of the next truss unit using an end plate, aligning the next truss unit with the adjacent truss unit, and repeating S2-S4 to complete the deployment of the next truss unit.

[0010] In one or more embodiments, the truss unit in its retracted state is located within the cavity of the truss mounting frame in its retracted state, and the truss unit and the truss mounting frame are jointly installed on the same satellite and launched together with the satellite.

[0011] In one or more embodiments, in step S5, a new satellite carrying a truss unit is launched to supplement the truss unit.

[0012] In one or more embodiments, in step S5, the next truss unit is first moved downward into the cavity using a three-degree-of-freedom adjustment mechanism, and then the left-right and front-back positions of the next truss unit are adjusted.

[0013] In one or more embodiments, in step S4, the telescopic arm is shortened to change the grabbing position of the grabber.

[0014] In one or more embodiments, in step S5, before placing the next truss unit into the cavity from the opening, the end plate is separated from the truss unit, and the first end of the sleeve is moved to the end of the truss unit so that the empty portion of the cavity can accommodate the next truss unit.

[0015] The above installation method breaks down the large-scale truss structure into multiple standard foldable truss units, and relies on the efficient auxiliary installation of the truss installation frame to simplify the on-orbit assembly process of the truss units and reduce the research and development and construction costs of ultra-large space truss structures. Attached Figure Description

[0016] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein: Figure 1 This is a schematic diagram of a single truss unit in its stowed-away state; Figure 2 This is a schematic diagram of a single truss unit in its deployed state; Figures 3A-3B This is a schematic diagram of the interface between truss units; Figure 4 This is a schematic diagram of the truss unit connecting to the satellite; Figure 5 This is a schematic diagram of the truss installation frame in the open state; Figure 6 This is a schematic diagram showing the truss installation frame in its retracted state and the truss unit in its stowed state connected to the satellite. Figure 7 This is a schematic diagram of the unfolding process; Figure 8 This is a diagram illustrating the change of fixed locations by the arresting officers; Figure 9 This is a schematic diagram showing the extension of the telescopic arm causing the sleeve to move outward. Figure 10 This is a schematic diagram showing the installation of the external frame in preparation for docking with the next truss unit; Figure 11 This is a schematic diagram of the next truss unit being placed into the cavity. Detailed Implementation

[0017] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0018] It should be noted that these and other accompanying drawings are merely examples and are not drawn to scale, and should not be construed as limiting the scope of protection of the present invention.

[0019] Space deployable structures are a new type of foldable structure that has emerged in the last thirty years alongside the development of aerospace technology. They are folded and stowed during ground launch, and unfold and lock into operational mode after entering orbit. The development of foldable and deployable structures has expanded the scale of spacecraft, making large and even super-large spacecraft possible. Space trusses, as an important type of space component, have become a crucial part of spacecraft structures and are widely used in space missions such as deep space exploration base construction, space station functional expansion, and high-resolution Earth observation.

[0020] Due to limitations in launch capacity, spacecraft with foldable truss structures based on existing technology typically have an on-orbit unfolded size in the range of 10 to 100 meters. However, for large or ultra-large spacecraft exceeding 100 meters in size, existing truss structures are insufficient to meet the requirements due to limitations in rocket payload volume and mass, stringent mechanical conditions during launch, and high launch costs. For example, using a space truss as a support platform cannot support equipment with a mass exceeding 10,000 tons, such as ultra-large area antennas, large-scale space solar power station systems, large on-orbit service platforms, and large high-orbit service stations.

[0021] To address the aforementioned issues, this invention provides a truss installation framework and a method for constructing large-scale space trusses, which possesses strong scalability and can efficiently extend the spacecraft baseline to the kilometer level, enabling the construction of ultra-large-scale spacecraft.

[0022] The truss mounting frame 20 is used to mount the truss unit 10. Each truss unit 10 serves as a mounting module; its specific structure is described in [reference needed]. Figures 1 to 4 As shown, it includes multiple frame bodies 11 and telescopic portions 12 connecting the frame bodies 11. The telescopic portions 12 allow the frame bodies 11 to move closer or further apart, so that truss units are formed. Figure 1 The storage status shown and Figure 2 The diagram shows the unfolded state. In some embodiments, the telescopic section 12 is configured to automatically extend and retract, for example, by including a plurality of connecting rods 15 and hinges 14 connecting the connecting rods, with the hinges 14 enabling the folding and unfolding of adjacent connecting rod sections 15. The frame body 11 is a quadrilateral frame, and after the truss unit is unfolded, the connecting rods 15 are perpendicular to the frame body 11. In addition, the truss unit may also include cable stays 16.

[0023] Truss unit 10 also includes interface 13. For example... Figures 3A-3B As shown, the truss is equipped with standardized interfaces at both ends. One side is the passive end 131, designed to be concave; the other side is the active end 132, designed to be convex. This enables on-orbit docking and mechanical locking. The standardized interfaces facilitate the free assembly of truss units. Adjacent truss units connect with each other through the interfaces to form a truss structure, thereby extending the truss. By docking a certain number of truss units, the large-scale truss is disassembled into several standard foldable truss units. The truss units are folded up during launch, with a small outer envelope, low requirements for transportation, and reduced manufacturing difficulty of the truss structure. After entering orbit, they can be unlocked by their own unlocking device and deployed in orbit.

[0024] Reference for scaffolding installation 20 Figure 5 and Figure 6 As shown, it includes a sleeve 21, a capture component 22, and an end plate 23.

[0025] Sleeve 21 includes a cavity 210 for accommodating truss units. The cavity 210 includes an opening 211, for example, a C-frame at the top of sleeve 21 forming the opening 211 of the cavity 210. The C-frame has a cross-sectional dimension slightly larger than the truss unit 10 to facilitate placement of the truss unit 10. Sleeve 21 includes multiple side frames 212 and telescopic members 213 connecting the side frames 212, allowing the sleeve's length to be telescopic, such as a telescopic sleeve or threaded assembly where the telescopic member 213 extends or shortens in the X direction, allowing the sleeve to be in a telescopic position. Figure 5 The contraction state shown or Figure 6 The sleeve 21 is shown in its unfolded state. In some embodiments, the sleeve 21 also includes a diagonal cable 214 connecting the adjacent frame 212.

[0026] The grabbing component 22 is located at the first end A of the sleeve 21 and includes a grabbing hand 228 and a telescopic arm 229. The telescopic arm 229 can be a telescopic sleeve, and the grabbing hand 228 can be a clamping mechanism to connect to fixed points such as satellites and frame bodies 11. Preferably, the grabbing hand 228 is equipped with a vision device to identify standard docking positions on satellites and quadrilateral frame bodies 11 of the truss. After the grabbing hand 228 grabs the fixed point, it serves as a support end to provide a fixed point for the installation of the scaffold. After the grabbing hand is in place, it locks the sleeve and the grabbing hand to complete the fixation of the left side of the scaffold. The grabbing component 22 provides the driving force to move the sleeve 21 by means of the length change of the telescopic arm 229. The grabbing component 22 located at the end of the scaffold forms a constantly changing force-bearing fixed point through a locking-unlocking-relocking process with multiple fixed points on the satellite and truss unit, and then uses the telescopic extension of the sleeve structure to realize the left and right movement of the scaffold on the truss unit.

[0027] End plate 23 is located at the second end B of sleeve 21 and is used to connect to the end of truss unit 10. It includes a three-degree-of-freedom adjustment mechanism to adjust the attitude of truss unit in the X, Y, and Z directions. In some embodiments, end plate 23 is designed with the same standardized active end interface as truss unit to dock with truss unit 10, realizing functions such as truss unit transportation and docking between auxiliary truss units.

[0028] In some embodiments, such as Figure 11 As shown, the three-degree-of-freedom adjustment mechanism includes three sliding structures: the innermost is a translation plate 231 with a standard interface, the middle is a three-degree-of-freedom adjustment plate 232, and the outermost is a fixed plate 233. The right side of the truss unit mates with the standard interface on the translation plate 231. Relying on the opening 211 of the outer frame, the translation plate 231 moves downward along direction P, causing the next truss unit 10' to translate downward until the left interface of the truss unit 10' is roughly aligned with the left interface of the unfolded truss unit 10. Then, the position of the truss unit is finely adjusted by the three-degree-of-freedom adjustment plate 232. After calibration, it is pushed to the left to assist the new truss unit 10' in mates with the unfolded truss unit 10.

[0029] After docking is completed, the grabber at the first end A of the outer frame unlocks, and the truss unit 10 automatically unfolds, pushing the entire truss mounting frame 20 to the right. When the truss unit is fully unfolded, the outer frame grabber 228 re-identifies the unfolded frame body 11, and uses the telescopic arm 229 to retract and extend, and the grabber 228 to lock again, to achieve the rightward shift of the grabbing position and the overall rightward movement of the outer frame, until the top opening 211 of the outer frame is once again completely located on the right side of the unfolded truss unit, so that the empty part of the cavity 210 can accommodate the next new truss unit.

[0030] Figure 6 The initial configuration of the spacecraft is shown, which includes a satellite 100, a truss structure 10 in a retracted state, and a truss mounting frame 20 in a retracted state. One end of the truss unit is fixed to the satellite and is located within the cavity 210 of the sleeve in the retracted state.

[0031] The initial launch status of the spacecraft is as follows Figure 6 As shown, the main satellite carries a truss unit as the basic truss and is launched together with the mounting frame. Before launch, a sleeve is placed over the outside of the truss unit, so that the truss unit in the retracted state is located inside the cavity of the truss mounting frame in the retracted state. The grabbing member 22 at the first end A of the sleeve is locked in the satellite's parking position, thereby achieving sleeve position locking.

[0032] After the satellite is launched into orbit, the basic truss and the outer frame are unlocked and deployed simultaneously, with the basic truss forming a large-scale truss foundation configuration. The outer frame assembles multiple truss units together to form a large-scale truss system.

[0033] Using this truss to install the external frame simplifies the on-orbit assembly process, making operation simple and assembly highly efficient.

[0034] Based on the above description of the truss installation frame, we can also understand a method for constructing large-scale spatial trusses.

[0035] The method includes the following steps: S1. Placing the truss unit in its retracted state into the cavity of the truss mounting frame; S2. Fixing the grabber to the satellite or truss unit, extending the telescopic arm, and pushing the mounting frame outward; S3. Deploying the truss unit; S4. Changing the grabber's position, gradually pushing the mounting frame outward until the truss unit is fully deployed; S5. Inserting the next truss unit into the cavity through the opening, using the end plate to adjust the attitude of the next truss unit, so that the next truss unit aligns with the adjacent truss unit, and repeating S2-S4 to complete the deployment of the next truss unit.

[0036] It should be noted that the step numbers above are only for illustrating the installation process and do not necessarily limit the order of installation.

[0037] Reference Figures 6 to 11 Understanding. For example... Figure 6 As shown, in the early stages of on-orbit installation, the truss unit in its retracted state is placed within the cavity of the truss mounting frame in its retracted state, allowing the truss unit and the truss mounting frame to be installed together on the same satellite 100 and launched together with the satellite. The truss unit directly connected to the satellite serves as the basic truss and is the first truss unit of the truss structure.

[0038] After the satellite is launched into orbit, the basic truss and the external frame are unlocked and deployed simultaneously. For example... Figure 7 As shown, the sleeve of the outer frame extends, and the grabber 228 initially grabs the fixed point on the first frame body 11. The telescopic arm 229 extends, pushing the sleeve 21 to move outward in the X direction. At the same time, the deployment of the truss unit 10 also provides driving force for the deployment of the outer frame. That is, the deployment of the base truss provides driving force for the deployment of the outer frame, and the grabber achieves the displacement of the outer frame on the base truss by the retraction and extension of the telescopic arm and the change of the fixed point.

[0039] Reference Figure 8 As shown, the catcher 228 unlocks from the fixed point on the first frame body 11, and the telescopic arm 229 retracts until the catcher 228 moves to the second truss body 11'. The catcher quickly identifies the fixed point and locks it in place.

[0040] Reference Figure 9 As shown, the telescopic arm 229 extends again, and the grabber 228 is fixed on the second truss body 11'. Then, with the extension of the telescopic arm 229, the outer frame continues to move outward in the X direction, so that the outer frame 20 moves outward relative to the truss unit 10.

[0041] Repeat the above process until the outer frame 20 is located at the outer end of the truss unit 10, so that the remaining portion of the cavity 210 can accommodate the next truss unit, such as... Figure 10 As shown.

[0042] Continue to refer to Figure 11 As shown, the next truss unit 10' is placed into the cavity 210 through the opening 211, and the attitude of the next truss unit is adjusted using the three-degree-of-freedom adjustment mechanism of the end plate. For example, first, the translation plate 231 of the three-degree-of-freedom adjustment mechanism is used to move the next truss unit downward along the Z direction into the cavity 210, and then the three-degree-of-freedom adjustment plate 232 is used to adjust the truss unit's front-to-back position along the X direction and its left-to-right position along the Y direction until the next truss unit is accurately aligned with the adjacent deployed truss unit. Repeat. Figures 7 to 10 The process of truss deployment and external frame movement, as shown, is used to assemble the next set of truss units. This process is repeated multiple times to achieve on-orbit construction of large-scale trusses.

[0043] In some embodiments, a new satellite carrying truss units is launched to supplement the existing truss units. In other embodiments, a number of truss units may also be stored inside the satellite to supplement the truss units already in orbit.

[0044] The above method uses independent truss units to assemble large-scale truss structures in orbit, giving the truss structure strong scalability. It can effectively extend the spacecraft baseline to the kilometer level, realize the construction of ultra-large-scale spacecraft, break through the carrying capacity of existing launch vehicles, and solve the problem of spacecraft efficiency limitation caused by a single launch.

[0045] It should be noted that the use of terms such as "first" and "second" to define the components in the above content is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this application.

[0046] Furthermore, this application uses specific terms to describe embodiments of the application. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0047] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A truss mounting frame for mounting truss units, the truss unit comprising a plurality of frame bodies and telescopic portions connecting the frame bodies, the telescopic portions allowing the frame bodies to move closer or further apart to position the truss unit in a retracted or extended state, characterized in that... The mounting frame includes: A sleeve includes a cavity for receiving the truss unit, the top of the sleeve forming an opening in the cavity, the sleeve including a plurality of side frames and a telescopic member connecting the side frames to make the sleeve retractable; The grabbing element, located at the first end of the sleeve, includes a telescopic arm and a grabbing hand located at the end of the telescopic arm. The grabbing hand is used to connect to a fixed point. The grabbing element provides a driving force to move the sleeve by means of the change in the length of the telescopic arm. An end plate, located at the second end of the sleeve, is used to connect to the end of the truss unit. It includes a three-degree-of-freedom adjustment mechanism to adjust the attitude of the truss unit. The three-degree-of-freedom adjustment mechanism includes three sliding structures: the innermost is a translation plate with a standard interface, the middle is a three-degree-of-freedom adjustment plate, and the outermost is a fixed plate.

2. The truss mounting frame as described in claim 1, characterized in that, The truss unit includes a mating interface, and adjacent truss units are connected to each other through the mating interface to form a truss structure.

3. A method for constructing large spatial trusses, characterized in that, Using the truss mounting frame truss unit as described in any one of claims 1-2, the method includes the following steps: S1. Place the truss unit in its stowed state into the cavity of the truss mounting frame; S2. Secure the capture arm to the satellite or truss unit, extend the telescopic arm, and push the mounting frame outward; S3. Deploy the truss unit; S4. Change the grabbing position of the grabber and gradually push the installation frame outward until the truss unit is fully deployed; S5. Insert the next truss unit into the cavity through the opening, and use the end plate to adjust the posture of the next truss unit so that the next truss unit docks with the adjacent truss unit. Repeat S2-S4 to complete the deployment of the next truss unit.

4. The method for constructing a large spatial truss as described in claim 3, characterized in that, The truss unit in its retracted state is located within the cavity of the truss mounting frame in its retracted state, so that the truss unit and the truss mounting frame are jointly installed on the same satellite and launched together with the satellite.

5. The method for constructing a large spatial truss as described in claim 3, characterized in that, In step S5, a new satellite carrying truss units is launched to supplement the truss units.

6. The method for constructing a large spatial truss as described in claim 3, characterized in that, In step S5, the three-degree-of-freedom adjustment mechanism is first used to move the next truss unit downward into the cavity, and then the left-right and front-back positions of the next truss unit are adjusted.

7. The method for constructing a large spatial truss as described in claim 3, characterized in that, In step S4, the telescopic arm is shortened to change the capture position of the capture hand.

8. The method for constructing a large spatial truss as described in claim 7, characterized in that, In step S5, before placing the next truss unit into the cavity from the opening, the end plate is separated from the truss unit, and the first end of the sleeve is moved to the end of the truss unit so that the empty portion of the cavity can accommodate the next truss unit.

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