Integrated foldable truss structure with length of hundreds of kilometers

Abstract

The application discloses a length-hundred-kilometer integrated foldable truss structure, which is folded in multiple directions and finally one-dimensionally unfolded in the length direction, and the length after unfolding can reach 100 kilometers; the length-hundred-kilometer integrated foldable truss structure comprises multiple truss units, multiple connecting mechanisms and multiple locking and damping mechanisms; the multiple foldable truss units are arranged in a stacked manner in multiple rows and multiple columns in the radial direction and the circumferential direction in the rocket fairing; each truss unit is composed of multiple truss sub-units which can be unfolded in the length direction; the application has higher folding efficiency in the radial direction perpendicular to the rocket fairing, can fully utilize the smaller space of the rocket fairing to realize a higher folding ratio, and can quickly reach the length-hundred-kilometer integrated foldable truss structure and the ideal working state after being unfolded along the radial direction of the rocket.

Description

Technical Field

[0001] This invention belongs to the field of aerospace equipment technology, and in particular relates to an integrated foldable truss structure with a length of hundreds of kilometers. Background Technology

[0002] In modern aerospace engineering, truss structures are widely used in important components such as spacecraft support systems, antenna brackets, and solar panels due to their excellent load-bearing capacity, stiffness, and lightweight design. With the increasing demands of aerospace missions, especially in the design of space stations, satellites, and other spacecraft, truss structures not only need to possess high strength and stability but also compact folding capabilities to accommodate limited launch module volume and unfold after entering orbit, maintaining structural stability and efficient operation.

[0003] In existing technologies, folding and unfolding techniques for truss structures have seen some basic applications, especially in axial folding. Traditional axially folding truss structures typically fold and unfold along the long axis of the rocket fairing, which is often circular along its axis. While this design can compress the structural volume to some extent and achieve an excellent folding-to-unfold ratio, it neglects the radial space of the rocket fairing, resulting in low utilization of this radial space. This leads to limitations on the unfolded length of the truss structure and requires complex mechanical operations to ensure structural stability and precision during unfolding. Summary of the Invention

[0004] To address the problems existing in the prior art, this invention proposes an integrated foldable truss structure with a length of hundreds of kilometers. The purpose is to solve the problem that existing truss structures in the aerospace field are usually folded along the long axis of the rocket fairing, but the radial space of the rocket fairing is ignored, resulting in low utilization of the radial space of the rocket fairing and limited length of the truss structure after unfolding.

[0005] To solve its technical problem, the present invention proposes the following technical solution:

[0006] A foldable truss structure with a length of hundreds of kilometers is characterized by the following: This foldable truss structure achieves one-dimensional unfolding along its length through multiple directional flips, reaching a length of hundreds of kilometers after unfolding; the foldable truss structure includes multiple truss units, multiple connecting mechanisms, and multiple locking and damping mechanisms; the multiple foldable truss units are arranged in multiple rows and columns, either neatly or irregularly, in a stacked manner along the radial and circumferential directions within the rocket fairing, with the height of the neatly or irregularly arranged truss units aligned with the axial direction of the rocket fairing; when the length reaches hundreds of kilometers... After the kilometer-level integrated foldable truss structure is unfolded, the height of each truss unit is part of the total unfolded length; the connecting mechanism consists of revolute joints and slid joints, or the connecting mechanism consists of revolute joints; the locking and damping mechanisms and revolute joints are used together and arranged in the assembly gaps between adjacent truss units; each truss unit consists of multiple truss sub-units that can be unfolded along the length direction, which is the length direction of the hundred-kilometer-level integrated foldable truss structure; on each truss unit, according to its length and width, multiple revolute joints and multiple locking and damping mechanisms are set; the revolute joints are fixed to the truss unit by pins.

[0007] Furthermore, the multiple connecting mechanisms are arranged with rotating and sliding pairs between rows and columns within the rocket fairing.

[0008] Furthermore, in the rocket fairing, the non-uniformly arranged truss units are: multiple sets of truss units of varying lengths arranged in rows or columns within the fairing.

[0009] Furthermore, the locating pair is used to move along a linear guide to a target position during the deployment of truss units that are not neatly arranged in rows or columns, and to align with the truss unit at the target position.

[0010] Furthermore, the rotating joint is used to rotate to the target position in a counterclockwise or clockwise direction during the deployment of the truss structure, so as to be arranged in a straight line with the truss unit at the target position.

[0011] Furthermore, during the unfolding of the truss structure, for the neatly arranged truss units, they rotate around the revolute joint, so that the adjacent two rows or two columns of truss units are arranged in a straight line.

[0012] Furthermore, during the deployment of the truss structure, for non-uniformly arranged truss units, the sliding joint is first used to move along the slide rail to the predetermined position and align with the target truss unit, and then rotates around the rotating joint to arrange the adjacent two rows or two columns of truss units into a straight line.

[0013] Furthermore, during the deployment of the truss structure, the revolute joint is arranged on the upper or lower surface near the junction of two adjacent truss units; when the revolute joint is arranged between the lower surfaces near the junction of two adjacent truss units, the two adjacent truss units fold towards the lower surface where the revolute joint is installed; when the revolute joint is arranged between the upper surfaces near the junction of two adjacent truss units, the two adjacent truss units fold towards the upper surface where the revolute joint is installed.

[0014] Furthermore, the locking and damping mechanism and the rotating joint, which are connected to adjacent truss units, lock and damping mechanism simultaneously lock when the rotating joint connecting the adjacent truss units rotates to the target position.

[0015] Advantages and effects of the invention

[0016] 1. This invention proposes an integrated, deployable truss structure with a length of hundreds of kilometers. This radially folding truss structure is arranged in multiple rows and columns along the radial direction of the rocket fairing. These rows and columns include both neatly and irregularly arranged sections, connected by revolute and slid joints. This structure exhibits high folding efficiency in the radial direction perpendicular to the rocket fairing. This design can fully utilize the limited space of the rocket fairing to achieve a higher folding ratio, and after radial deployment along the rocket, it can quickly reach the integrated, deployable truss structure with a length of hundreds of kilometers and achieve an ideal working state. Specifically, radial folding not only improves space utilization and saves launch volume, but also reduces the complexity and instability during deployment through an innovative folding path design.

[0017] 2. The radial folding truss structure of this invention has significant advantages in terms of folding-to-spread ratio, deployment reliability, deployment stability, and locking mechanism, and can overcome the shortcomings of traditional axial folding truss structures. This invention is particularly suitable for spacecraft design, featuring high space utilization and high reliability, and can effectively improve the overall performance of spacecraft. Attached Figure Description

[0018] Figure 1a is a top view of the folding mechanism of Scheme 1 of the present invention, viewed from the entrance of the rocket fairing;

[0019] Figure 1b is a top view of the radial unfolding process of Scheme 1 of the present invention from a first perspective;

[0020] Figure 1c is a top view of the radial unfolding process of Scheme 1 of the present invention from a second perspective;

[0021] Figure 1d is a top view (third perspective) of the radial unfolding process of Scheme 1 of the present invention;

[0022] Figure 2a is a top view of the folding mechanism of Scheme 2 of the present invention, viewed from the entrance of the rocket fairing;

[0023] Figure 2b shows the first perspective of the radial unfolding process of Scheme 2 of the present invention. Figure 2a Side view;

[0024] Figure 2c is a right view of the radial unfolding process of Scheme 2 of the present invention, taken from the second perspective of Figure 2b, and a schematic diagram of the unfolding process from the middle collinear position to both sides;

[0025] Figure 2d is a schematic diagram of the final effect of radial expansion of Scheme 2 of the present invention, viewed from the third perspective as shown in Figure 2c, along the collinear expansion to both sides;

[0026] Figure 3a is a top view of the folding mechanism of Scheme 3 of the present invention, viewed from the entrance of the rocket fairing;

[0027] Figure 3b is a top view of the radial unfolding process of Scheme 3 of the present invention from a first perspective;

[0028] Figure 3c is a top view of the radial unfolding process of Scheme 3 of the present invention from a second perspective;

[0029] Figure 3d shows the top view (left) and fourth view (right) of the radial unfolding process of Scheme 3 of the present invention.

[0030] Figure 4 is a schematic diagram of the cooperation between the rotating pair and the locking mechanism of the present invention.

[0031] In the diagram, 1: Rocket fairing; 2: Truss unit; 2-1: Truss unit; 2-2: Truss unit; 2-3: Truss unit; 2-4: Truss unit; 2-5: Truss unit; 2-6: Truss unit; 2-7: Truss unit; 2-8: Truss unit; 3: Revolute joint; 3-1: Revolute joint; 3-2: Revolute joint; 3-3: Revolute joint; 3-4: Revolute joint; 3-5: Revolute joint; 3-6: Revolute joint; 4: Locking and damping mechanism; 4-1: Locking and damping mechanism; 4-2: Locking and damping mechanism; 4-3: Locking and damping mechanism; 4-4: Locking and damping mechanism; 4-5: Locking and damping mechanism; 4-6: Locking and damping mechanism. Detailed Implementation

[0032] Innovation of this invention

[0033] 1. Radial Folding Design: This invention introduces a radial folding truss structure, which is a folding mechanism that unfolds along the radius of the rocket launcher. Compared with the traditional axial folding truss structure, it can more effectively utilize the radial space of the rocket, improve space utilization, further reduce structural volume, and increase the folding ratio. It solves the limitations of traditional designs in terms of space compactness.

[0034] 2. Highly efficient and reliable deployment process: This structure is more stable and simpler during deployment, reducing the complexity of mechanical devices compared to traditional designs and ensuring symmetry and precision during deployment. Simplifying the deployment process not only improves deployment efficiency but also enhances system reliability, providing higher reliability, especially in complex launch missions.

[0035] 3. Multiple Deployment Path Planning: This invention can plan multiple deployment paths based on the needs of different launch missions, the size and shape of the rocket fairing, and limitations under launch conditions. This improves the flexibility of launch missions, meets diverse payload requirements, and allows for flexible configuration according to different missions, thereby improving the spacecraft's loading efficiency.

[0036] The invention will be further explained below with reference to the accompanying drawings:

[0037] A type of integrated, foldable truss structure with a length of hundreds of kilometers, such as Figures 1a to 4 As shown, its characteristics are: this integrated foldable truss structure with a length of hundreds of kilometers achieves one-dimensional unfolding along its length through multiple directional flips, reaching a length of hundreds of kilometers after unfolding; this integrated foldable truss structure with a length of hundreds of kilometers includes multiple truss units 2, multiple connecting mechanisms, and multiple locking and damping mechanisms 4; the multiple foldable truss units 2 are arranged in multiple rows and columns in a neat or non-neat stacked manner along the radial and circumferential directions in the rocket fairing 1, and the height direction of the multiple rows and columns of neat or non-neatly arranged truss units 2 is the same as the axis of the rocket fairing 1; when the integrated foldable truss structure with a length of hundreds of kilometers... After the folding truss structure is unfolded, the height of each truss unit 2 is part of the total unfolded length; the connecting mechanism consists of a revolute joint 3 and a sliding joint 4, or the connecting mechanism consists of a revolute joint 3; the locking and damping structure 4 and the revolute joint 3 are used together and are arranged in the assembly gap between adjacent truss units 2; each truss unit 2 consists of multiple truss sub-units that can be unfolded along the length direction, which is a length direction on the order of hundreds of kilometers; on each truss unit 2, multiple revolute joints 3 and multiple locking and damping mechanisms 4 are set according to their length and width; the revolute joint 3 is fixed to the truss unit 2 by a pin.

[0038] like Figure 1a , 2a As shown in 3a, the multiple connecting mechanisms 2 are arranged with rotating pairs 3 and sliding pairs 4 between rows and columns inside the rocket fairing 1.

[0039] like Figure 1a , 2a As shown in 3a, in the rocket fairing 1, the non-uniformly arranged truss units are: multiple sets of truss units 2 with different lengths arranged in rows or columns inside the fairing.

[0040] like Figure 1a , 1b As shown, the locating pair is used to move along a linear guide rail to a target position and align with the truss unit 2 at the target position during the unfolding process of truss units 2 that are not neatly arranged in rows or columns.

[0041] like Figure 1c , Figure 2c As shown, the rotating joint is used to rotate to the target position in a counterclockwise or clockwise direction during the unfolding of the truss structure, and to be arranged in a straight line with the truss unit 2 at the target position.

[0042] like Figure 2a , Figure 2b As shown, during the unfolding of the truss structure, the neatly arranged truss units 2 rotate around the swivel joint 3, so that the adjacent two rows or two columns of truss units 2 are arranged in a straight line.

[0043] like Figure 1a , Figure 1b , Figure 1c , Figure 1d As shown, during the deployment of the truss structure, for non-uniformly arranged truss units 2, the sliding joint is first used to move along the slide rail to the predetermined position and align with the target truss unit 2, and then rotates around the rotating joint 3 to arrange the adjacent two rows or two columns of truss units 2 into a straight line.

[0044] like Figure 2a As shown, during the unfolding of the truss structure, the rotating joint is arranged on the upper or lower surface near the junction of two adjacent truss units 2; when the rotating joint is arranged between the lower surfaces near the junction of two adjacent truss units 2, the two adjacent truss units 2 fold towards the lower surface where the rotating joint 2 is installed; when the rotating joint 2 is arranged between the upper surfaces near the junction of two adjacent truss units 2, the two adjacent truss units fold towards the upper surface where the rotating joint 3 is installed.

[0045] like Figure 4 As shown, the locking and damping mechanism 4 and the rotating joint 3 are connected to the adjacent truss unit 2. When the rotating joint 3 connecting the adjacent truss unit 2 rotates to the target position, the locking and damping mechanism 4 locks simultaneously. Example 1

[0046] Figures 1a to 1d This is a top view of Scheme 1 in its folded state. The outer circle is the rocket fairing, and the interior is a stacked foldable truss structure with multiple rows and columns arranged in a non-organic manner. Each small rectangle in the figure represents a truss unit, and the semicircles 3-1, 3-2, 3-3, and 3-4 are the rotating joints connecting the adjacent trusses 2.

[0047] The first step in the unfolding process, such as Figure 1bAs shown, when unfolded, the two trusses on the left move downwards to align truss unit 2-1 with truss unit 2-3 and truss unit 2-2 with truss unit 2-4, while the two trusses on the right move upwards to align truss unit 2-5 with truss unit 2-7 and truss unit 2-6 with truss unit 2-8.

[0048] The second step of the unfolding process, such as Figure 1c As shown, truss unit 2-1 then rotates around revolute joint 3-1 to laterally align with truss unit 2-2 and is locked by locking and damping mechanism 4-1. Truss unit 2-6 rotates around revolute joint 3-3 to laterally align with truss unit 2-5; and is locked by locking and damping mechanism 4-3.

[0049] The third step of the unfolding process, such as Figure 1d As shown, while the aforementioned revolute joint completes its rotation, the first row of trusses is locked by locking and damping mechanism 4-3, rotates counterclockwise around revolute joint 3-2, and simultaneously aligns laterally with the second row of trusses and is locked by locking and damping mechanism 4-2. The third row of trusses rotates counterclockwise around revolute joint 3-4, and simultaneously aligns laterally with the second row of trusses and is locked by locking and damping mechanism 4-4. The locking is completed simultaneously with the rotation, as... Figure 4 As shown, because the rotating joint and the locking mechanism are connected to the common truss unit on both sides, the locking is completed when the rotation is completed.

[0050] The fourth step in the unfolding process is that the truss sub-units of each truss unit are unfolded along the length of hundreds of kilometers, thereby realizing an integrated foldable truss structure with a length of hundreds of kilometers. Example 2

[0051] Figures 2a to 2d Scheme 2 is shown in the top and side views during the unfolding process. The outer circle is the rocket fairing 1, and the interior is a stacked, foldable truss structure with multiple rows and columns. Each small rectangle in the figure represents a truss unit 2. 3-1, 3-2, 3-3, and 3-4 are the revolute joints connecting adjacent truss units 2. Dashed lines indicate that the revolute joints are arranged at the bottom, and solid lines indicate that the revolute joints are arranged at the top.

[0052] The first step in the unfolding process, such as Figure 2aAs shown, the first row of truss units 2 first rotates from top to bottom around the rotating joints 3-1 and 3-2 toward the surface where the rotating joints are installed, until it aligns with the second row of trusses. This is then locked by locking and damping mechanisms 4-1 and 4-2. At this point, truss units 2-3 and 2-4 are on top, and truss units 2-1 and 2-2 are on the bottom. Then, the second row of trusses rotates from bottom to top around the rotating joints 3-3 and 3-4 toward the surface where the rotating joints are installed, until it aligns with the third row of trusses. This is also locked by locking and damping mechanisms 4-3 and 4-4. At this point, truss units 2-1 and 2-2 are on the top layer, truss units 2-3 and 2-4 are in the middle, and truss units 2-5 and 2-6 are on the bottom layer. The result after flipping is as follows: Figure 2b As shown, this is a flipped side view. Truss units 2-2, 2-4, and 2-6 (within brackets) are in the back row, while truss units 2-1, 2-3, and 2-5 (outside brackets) are in the front row.

[0053] The second step of the unfolding process, as follows: Figure 2c As shown, truss elements 2-1, 2-3, 2-5 and truss elements 2-2, 2-4, 2-6 rotate from their collinear positions around revolute joint 3-5 to both sides, and after rotation, they appear as follows: Figure 2d They are arranged in a straight line as shown, and locking is achieved through locking and damping mechanisms 4-5.

[0054] In the third step of the unfolding process, the truss sub-units of each truss unit are unfolded along a length of hundreds of kilometers, thereby realizing an integrated foldable truss structure with a length of hundreds of kilometers. Example 3

[0055] Figures 3a to 3d This diagram illustrates the unfolding process of Scheme 3. The outer circle represents the rocket fairing 1, and the interior consists of a non-uniformly arranged, stacked, foldable truss structure. Each small rectangular truss unit 2-1, truss unit 2-2, truss unit 2-3, truss unit 2-4, truss unit 2-5, truss unit 2-6, and truss unit 2-7 represents a truss unit. 3-1, 3-2, 3-3, and 3-4 are revolute joints connecting adjacent truss units. Dashed lines between two adjacent trusses indicate that the revolute joint is located below, while solid lines indicate that it is located above.

[0056] The first step in the unfolding process, such as Figure 3a , 3bAs shown, during deployment, truss unit 2-1 and truss unit 2-2 are first aligned with truss unit 2-3 and truss unit 2-4 via sliding joints (sliding joints are tracks, not shown in the figure), and truss unit 2-6 and truss unit 2-7 are aligned with truss unit 2-4 and truss unit 2-5 via sliding joints (sliding joints are tracks, not shown in the figure).

[0057] The second step of the unfolding process, as follows: Figure 3b , 3c As shown, truss unit 2-2 then rotates counterclockwise around revolute joint 3-1 to align with truss unit 2-1, and is locked by locking and damping mechanism 4-1; truss unit 2-6 rotates counterclockwise around revolute joint 3-3 to align with truss unit 2-7, and is locked by locking and damping mechanism 4-3.

[0058] The third step of the unfolding process, as follows: Figure 3c , 3d As shown in the left figure, truss unit 2-1 rotates from top to bottom around revolute joint 3-2 to align with truss unit 2-3, and is locked by locking and damping mechanism 4-2. At this time, from the top view, truss unit 2-3 is at the top, truss unit 2-1 is in the middle, and truss unit 2-2 is at the bottom. Truss unit 2-6 rotates from bottom to top around revolute joint 3-4 to align with truss unit 2-5 and is locked by locking and damping mechanism 4-4. At this time, from the top view, truss unit 2-7 is at the top, truss unit 2-6 is in the middle, and truss unit 2-5 is at the bottom. The result after the above flipping is as follows. Figure 3d As shown in the left figure;

[0059] The fourth step in the unfolding process, as follows: Figure 3d As shown in the right figure, the truss unit 2-3 rotates around the revolute joint 3-5 to align with the truss unit 2-4 and is locked by the locking and damping mechanism 4-5. The truss unit 2-5 rotates around the revolute joint 3-6 to align with the truss unit 2-4 and is locked by the locking and damping mechanism 4-6, thus finally unfolding into a longitudinal straight line.

[0060] The fifth step in the unfolding process is that the truss sub-units of each truss unit are unfolded along the length of hundreds of kilometers, thereby realizing an integrated foldable truss structure with a length of hundreds of kilometers.

[0061] It should be emphasized that the above specific embodiments are merely explanations of the present invention and are not intended to limit the present invention. After reading this specification, those skilled in the art can make modifications to the above embodiments without contributing any inventive step, but as long as they are within the scope of the claims of the present invention, they are protected by patent law.

Claims

1. A length of 100 kilometers integrated deployable truss structure, characterized in that: The length hundred-kilometer integrated foldable truss structure is folded and unfolded through multiple directions, and finally realizes one-dimensional unfolding in the length direction, and the length after unfolding can reach hundreds of kilometers; the length hundred-kilometer integrated foldable truss structure comprises multiple truss units (2), multiple connecting mechanisms, and multiple locking and damping mechanisms (4); the multiple foldable truss units (2) are arranged in multiple rows and multiple columns in a neat or non-neat stacking manner along the radial direction and the circumferential direction in the rocket fairing (1), and the height direction of the multiple rows and multiple columns of truss units (2) is the same as the axial direction of the rocket fairing (1); when the length hundred-kilometer integrated foldable truss structure is unfolded, the height of each truss unit (2) is a part of the total length after unfolding; the connecting mechanism is composed of a rotating pair (3) and a moving pair, or the connecting mechanism is composed of a rotating pair (3); the locking and damping mechanism (4) and the rotating pair (3) are used together, and are arranged in the assembly gap between adjacent truss units (2); each truss unit (2) is composed of multiple truss sub-units which can be unfolded along the length direction, and the length direction is the length direction of the length hundred-kilometer integrated foldable truss structure; on each truss unit (2), multiple rotating pairs (3) and multiple locking and damping mechanisms (4) are arranged according to the different lengths and widths; the rotating pair (3) and the truss unit (2) are fixed by a pin shaft.

2. The integrated deployable truss structure of claim 1, wherein the length is in the order of 100 kilometers. The multiple connecting mechanisms are arranged with rotating pairs (3) and moving pairs between rows and between columns in the rocket fairing (1).

3. The integrated deployable truss structure of claim 2, wherein the length is in the order of 100 kilometers. In the rocket fairing (1), the non-neatly arranged truss units are multiple groups of truss units (2) with different lengths of rows or columns arranged in the fairing.

4. The integrated deployable truss structure of claim 1, wherein the length is in the order of 100 kilometers. The moving pair is used to move to a target position along a linear guide rail during the unfolding process of the non-neatly arranged truss units (2), and aligns with the truss unit (2) at the target position.

5. The integrated deployable truss structure of claim 1, wherein the length is in the order of 100 kilometers. The rotating pair is used to rotate to a target position in a counterclockwise or clockwise direction during the unfolding process of the truss structure, and forms a linear arrangement with the truss unit (2) at the target position.

6. The integrated deployable truss structure of claim 1, wherein the length is in the order of 100 kilometers. During the unfolding process of the truss structure, for the neatly arranged truss units (2), the adjacent two rows or two columns of truss units (2) are arranged in a linear arrangement by rotating around the rotating pair (3).

7. The integrated deployable truss structure of claim 2, wherein the length is in the order of 100 kilometers. During the unfolding process of the truss structure, for the non-neatly arranged truss units (2), the moving pair is first used to move to a predetermined position and align with the target truss unit (2) along the slide rail, and then the adjacent two rows or two columns of truss units (2) are arranged in a linear arrangement by rotating around the rotating pair (3).

8. The integrated deployable truss structure of claim 1, wherein the length is in the order of 100 kilometers. During the unfolding process of the truss structure, the rotating pair is arranged on the upper surface or the lower surface near the junction of the adjacent two truss units (2); when the rotating pair is arranged between the lower surfaces near the junction of the adjacent two truss units (2), the adjacent two truss units (2) are folded towards the lower surface where the rotating pair (3) is installed; when the rotating pair (3) is arranged between the upper surfaces near the junction of the adjacent two truss units (2), the adjacent two truss units are folded towards the upper surface where the rotating pair (3) is installed.

9. The integrated deployable truss structure of claim 1, wherein the length is in the order of 100 kilometers. The locking and damping mechanism (4) and the rotary pair (3) are connected to adjacent truss units (2) together, and when the rotary pair (3) connecting adjacent truss units (2) rotates to the target position, the locking and damping mechanism (4) simultaneously completes locking.

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