High space utilization bracket / mast for space structures

Abstract

The invention discloses a high-space-utilization-rate support / mast for a space structure, and belongs to the technical field of aerospace. The stent / mast is of a tubular structure in which material portions of higher strength are arranged on opposite sides of the tubular structure; the thermoplastic resin material part is connected with the edge part of the material part with high specific strength to form a pipe main body structure with a tubular structure; the slotted hole gaps are formed in the positions, opposite to each other, of the material parts with the high specific strength on the two opposite sides. During storage, pipe section parts, located outside the two ends of the slotted hole gap, of the tubular structure are flattened oppositely, flattening creases occur at the thermoplastic resin material parts, the two flattened pipe section parts are wound on the core material, and the wound flattened pipe section parts are restrained through binding belts; and the two coiled and restrained pipe section parts realize the turning direction orthogonal to the flattening direction through the slotted hole gap. The folding folding bed has the advantages of being convenient to store, small in occupied space after being stored and high in structural rigidity after being unfolded.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, and in particular to a high space utilization support / mast for space structures. BACKGROUND

[0002] There are three main technical routes for existing space deployable structures: (1) mechanical hinge structures relying on complex transmission mechanisms, resulting in a high mass ratio; (2) inflatable deployable structures that require continuous pressure to maintain and are vulnerable to space debris penetration; (3) thin-walled multi-stable deployable structures. Currently, the last type of structure is widely researched and applied. On the one hand, it can use high-strength carbon fiber composite materials, titanium alloys, etc., to meet the requirements of satellite support systems and lunar base structures for weight and strength. On the other hand, it can be folded and automatically deployed, greatly reducing the demand for transportation space.

[0003] However, due to the limited fracture strain of the resin matrix of the composite material, the minimum folding radius of the deployable structure is generally large, the transportation storage space is large, and transportation is not convenient. In addition, the stiffness of the structure after deployment is generally low, which may not be able to effectively withstand the impact of micro-meteoroids / space debris, the driving force of solar panels, the gravity of the lunar gravity field, etc. SUMMARY

[0004] The present application aims to at least partially solve one of the problems in the related art. To this end, one object of the present application is to provide a high space utilization support / mast for space structures, which is convenient to store and occupies a small space after storage, has high structural stiffness after deployment, and is suitable for satellite antenna or solar panel support systems, lunar surface base communication towers, and rapid deployment supports for solar energy stations, etc.

[0005] The high space utilization support / mast for space structures according to an embodiment of the present application is a tubular structure, comprising: a high-strength material portion arranged on opposite sides of the tubular structure a thermoplastic resin material portion connecting the edge portions of the high-strength material portions on opposite sides to form a tube main structure of the tubular structure together with the high-strength material portions; an oblong hole gap arranged at positions opposite each other on the high-strength material portions on opposite sides When the high space utilization support / mast for space structure of the embodiment of the present application needs to be stored, the tubular structure is heated, and the tubular structure is pressed in opposite directions by external force to form two layers of flat plates with a gap in the middle (with large internal stress) and with the flat fold occurring at the thermoplastic resin material part. The two pressed tubular segments are wound on two core materials respectively to form two winding structures. Compared with the winding structure formed by winding the same high space utilization support / mast for space structure on the same core material, the diameter of the winding structure is much smaller, so the height and width of the storage space are greatly reduced. Since the tubular segments wound on the two core materials have large internal stress, the tubular segments are constrained by the binding belt after winding to achieve stable storage. The two constrained tubular segments pass through the long circular hole gap 3 to achieve a turn in the direction perpendicular to the pressing direction, which further greatly reduces the length of the storage space. In other words, the high space utilization support / mast for space structure of the embodiment of the present application is easy to store and occupies a small space after storage, which is convenient for transportation from the earth to space.

[0006] When the high space utilization support / mast for space structure of the embodiment of the present application needs to be stored, the tubular structure is heated, and the tubular structure is pressed in opposite directions by external force to form two layers of flat plates with a gap in the middle (with large internal stress) and with the flat fold occurring at the thermoplastic resin material part. The two pressed tubular segments are wound on two core materials respectively to form two winding structures. Compared with the winding structure formed by winding the same high space utilization support / mast for space structure on the same core material, the diameter of the winding structure is much smaller, so the height and width of the storage space are greatly reduced. Since the tubular segments wound on the two core materials have large internal stress, the tubular segments are constrained by the binding belt after winding to achieve stable storage. The two constrained tubular segments pass through the long circular hole gap 3 to achieve a turn in the direction perpendicular to the pressing direction, which further greatly reduces the length of the storage space. In other words, the high space utilization support / mast for space structure of the embodiment of the present application is easy to store and occupies a small space after storage, which is convenient for transportation from the earth to space.

[0007] When the high space utilization support / mast for space structure of the embodiment of the present application needs to be stored, the tubular structure is heated, and the tubular structure is pressed in opposite directions by external force to form two layers of flat plates with a gap in the middle (with large internal stress) and with the flat fold occurring at the thermoplastic resin material part. The two pressed tubular segments are wound on two core materials respectively to form two winding structures. Compared with the winding structure formed by winding the same high space utilization support / mast for space structure on the same core material, the diameter of the winding structure is much smaller, so the height and width of the storage space are greatly reduced. Since the tubular segments wound on the two core materials have large internal stress, the tubular segments are constrained by the binding belt after winding to achieve stable storage. The two constrained tubular segments pass through the long circular hole gap 3 to achieve a turn in the direction perpendicular to the pressing direction, which further greatly reduces the length of the storage space. In other words, the high space utilization support / mast for space structure of the embodiment of the present application is easy to store and occupies a small space after storage, which is convenient for transportation from the earth to space.

[0008] The high space utilization support / mast for space structure has the following advantages: first, the bending radius is small. The high space utilization support / mast for space structure is designed with the thermoplastic resin material part on both sides, which can effectively reduce the minimum bending radius. Second, the space occupied by the high space utilization support / mast for space structure is small. The flattened tube structure is flattened at the thermoplastic resin material part, and the flattened tube segments are wound on the core material respectively, and the flattened tube segments are constrained by the binding belt. The two constrained tube segments are turned through the long circular slot, which is perpendicular to the flattened direction. Thus, the high space utilization support / mast for space structure occupies a small space after being stored. Third, the structural stiffness is better. The upper and lower perforations cause great damage to the stiffness of the component itself. The high space utilization support / mast for space structure only needs to punch a pair of long circular slot holes on the two material parts with high specific strength, which can reduce the loss of structural stiffness of the high space utilization support / mast for space structure.

[0009] In some embodiments, the elastic modulus of the material of the material part with high specific strength is 100-200 GPa, and the tensile strength is 600-3700 MPa.

[0010] In some embodiments, the material of the material part with high specific strength is a fiber composite material or a titanium alloy.

[0011] In some embodiments, the fiber composite material is a carbon fiber composite material, a basalt fiber composite material, or an aramid fiber composite material.

[0012] In some embodiments, the material of the thermoplastic resin material part is a thermoplastic polyurethane, a thermoplastic elastomer, a modified polyethylene, or a nylon elastomer.

[0013] In some embodiments, a shape memory material layer is further included, which is arranged on the inner wall and the outer wall of the tube main body structure.

[0014] In some embodiments, the material of the shape memory material layer is an epoxy-based SMP, a polyurethane-based SMP, or a liquid crystal elastomer.

[0015] In some embodiments, the material, quantity, and shape of the binding belt can effectively constrain the stored tubular structure with a large internal stress.

[0016] In some embodiments, the material and shape of the core material can effectively support the stored tubular structure.

[0017] In some embodiments, the core material is a cylinder.

[0018] Additional aspects and advantages of the present application will be set forth in part in the description which follows, and in part will be obvious from the description, or can be learned by practice of the application. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 is a schematic view of a deployed state of a high space utilization support / mast structure for a space structure according to an embodiment of the present application; Figure 2 is a schematic view of a stowed state of a high space utilization support / mast structure for a space structure according to an embodiment of the present application; Figure 3 is a schematic view of a cross section of Figure 1 .

[0020] REFERENCE NUMERALS high space utilization support / mast 1000 for a space structure; high-strength material portion 1; thermoplastic resin material portion 2; long circular hole slit 3; shape memory material layer 4; binding tape 5; core material 6. DETAILED DESCRIPTION

[0021] Embodiments of the present application are described in detail below with reference to the attached drawings. The embodiments of the present application are examples and do not limit the present application. Throughout the drawings, same or similar components are designated by the same reference numerals.

[0022] Embodiments of the present application are described below in detail with reference to the attached drawings. Figures 1 to 3 A high space utilization support / mast 1000 for a space structure according to an embodiment of the present application is described below.

[0023] As shown in Figure 1 , the high space utilization support / mast 1000 for a space structure according to an embodiment of the present application is a tubular structure, which can be understood as a hollow straight tubular structure in a deployed state, and is used for a support system for a satellite antenna or a solar panel in space, a communication tower for a lunar surface base, and a rapid deployment support for a solar energy station.

[0024] Specifically, the high space utilization support / mast 1000 for a space structure according to an embodiment of the present application includes a high-strength material portion 1, a thermoplastic resin material portion 2, and a long circular hole slit 3.

[0025] The material part 1 with high specific strength is arranged on opposite sides of the tubular structure, the radial section of the material part 1 with high specific strength in the unfolded state is in the shape of a circular arc, and has high strength and rigidity, so the material part 1 with high specific strength is the main force-bearing part of the satellite antenna or solar sail. Meanwhile, the material part 1 with high specific strength can be flattened and has a large internal stress to facilitate storage, and can restore to the unfolded state after the internal stress is released. The material part 1 with high specific strength can be understood as having an elastic modulus of 100-200 GPa and a tensile strength of 600-3700 MPa.

[0026] The thermoplastic resin material part 2 connects the edge parts of the material parts 1 with high specific strength on the opposite sides to form a tubular main body structure together with the material parts 1 with high specific strength, and forms a flattening fold when the tubular structure is flattened in the diameter direction after being softened by heating, and is a fold part after the high-space-utilization support / mast 1000 for space structures is coiled; therefore, the thermoplastic resin material part 2 is conducive to the storage of the high-space-utilization support / mast 1000 for space structures.

[0027] The long circular hole slits 3 are arranged at positions opposite to each other on the material parts 1 with high specific strength on the opposite sides, are orthogonal to the thermoplastic resin material part 2, and can be located at an intermediate position in the length direction of the tubular structure, and the specific position can be determined as required. Since the support / mast is transported from the earth to the space, there are specific requirements for the length, width and height of the storage space of the support / mast, and for the long mast parts used in the scene of a solar sail, if coiled on a single core material 6, the diameter can exceed the space requirement. In order to meet the requirements of transportation and storage, the long circular hole slits 3 are arranged to realize the bending and folding of the tubular structure in the length direction, and the bending fold of the bending and folding is orthogonal to the fold of the thermoplastic resin material part 2, that is, the flattening fold, so that after the tubular structure is coiled on two core materials, the bending and folding at the long circular hole slits 3 can further reduce the storage space occupied by the tubular structure before unfolding. The length of the long circular hole slits can meet the requirement of being bent orthogonally to the thermoplastic resin material part 2, and the width is recommended to be 1 / 5-1 / 3 of the diameter of the tubular structure to minimize the damage to the overall rigidity of the tubular structure.

[0028] During storage, the tubular structure is flattened in opposite directions to form flattening folds at the thermoplastic resin material part 2, and the flattened tubular segments are coiled on the core material 6, and the flattened tubular segments after coiling are constrained by the binding belt 5; the two coiled and constrained tubular segments are turned through the long circular hole slits 3 to be orthogonal to the flattening direction; in this way, the high-space-utilization support / mast 1000 for space structures of the embodiment of the application occupies a small space after storage.

[0029] When the high space utilization support / mast 1000 for space structure of the embodiment of the present application needs to be stored (as shown in Figure 2 the tubular structure is heated, the two flattened tube sections are wound on the two core materials 6 respectively, forming two winding structures, which have much smaller diameter than the winding structure formed by winding the same high space utilization support / mast 1000 for space structure on the same core material 6, thus greatly reducing the size of the storage space in the height and width directions; since the flattened tube sections wound on the two core materials 6 have large internal stress, the flattened tube sections are restrained by the binding belts 5 to keep the tubular structure in stable storage state; the two restrained flattened tube sections, i.e. the two winding structures, are turned through the long circular hole gap 3 to be perpendicular to the flattening direction, thus further greatly reducing the size of the storage space in the length direction. That is, the high space utilization support / mast 1000 for space structure of the embodiment of the present application is convenient to store and occupies small space after storage, and is convenient to transport from the earth to space.

[0030] When the high space utilization support / mast 1000 for space structure of the embodiment of the present application needs to be deployed after being transported to space or the lunar surface environment, the binding belts 5 are sequentially untied; due to the decrease of the temperature of the outer space environment, the high space utilization support / mast 1000 for space structure of the embodiment of the present application with large internal stress will automatically deploy under the release of the internal stress, and the bending stiffness of the whole deployed tubular structure is first borne by the material part 1 with high specific strength. That is, the high space utilization support / mast 1000 for space structure of the embodiment of the present application has high stiffness after deployment, and can be applied to the support system of satellite antenna or solar panel, the rapid deployment support of communication tower and solar energy station for lunar surface base, etc.

[0031] The high space utilization support / mast 1000 for space structure has the following advantages: first, the bending radius is small. The high space utilization support / mast 1000 for space structure is designed with the thermoplastic resin material part 2 on both sides, which can effectively reduce the minimum bending radius. Second, the space occupied by the support / mast 1000 for space structure is small. By flattening the tubular structure at the pipe segment part outside the long circular hole gap 3 at both ends, the flattening fold is generated at the thermoplastic resin material part 2, and the flattened two pipe segment parts are wound on the core material 6 respectively, and the flattened pipe segment parts after winding are constrained by the binding belt 5; the two wound and constrained pipe segment parts are turned through the long circular hole gap 3 to be perpendicular to the flattening direction; in this way, the high space utilization support / mast 1000 for space structure of the embodiment of the present application occupies a small space after being stored. Third, the structural stiffness is better. The perforation causes great damage to the stiffness of the component itself, and the high space utilization support / mast 1000 for space structure of the embodiment of the present application only needs to punch a pair of long circular gap holes on the two high-strength material parts 1, which can reduce the loss of structural stiffness of the high space utilization support / mast 1000 for space structure.

[0032] In some embodiments, the elastic modulus of the material of the high-strength material part 1 is 100-200 GPa, and the tensile strength is 600-3700 MPa. Within this parameter range, the high space utilization support / mast 1000 for space structure of the embodiment of the present application meets the mechanical performance requirements of supporting satellite antennas or solar panels.

[0033] In some embodiments, the material of the high-strength material part 1 is a fiber composite material or a titanium alloy. The fiber composite material or the titanium alloy can meet the requirements of weight and strength of satellite support systems and lunar base structures.

[0034] In some embodiments, the fiber composite material is a carbon fiber composite material, a basalt fiber composite material, or an aramid fiber composite material. The carbon fiber composite material has higher stiffness and strength, the basalt fiber composite material has higher temperature resistance, and the aramid fiber composite material has higher toughness and impact resistance.

[0035] In some embodiments, the material of the thermoplastic resin material part 2 is a thermoplastic polyurethane, a thermoplastic elastomer, a modified polyethylene, or a nylon elastomer. These materials have good thermoplasticity, fatigue life, and toughness, which ensures that the initial shape can be restored to the maximum extent after deployment.

[0036] In some embodiments, a shape memory material layer 4 is further included, which is arranged on the inner wall and outer wall of the tubular body structure. The shape memory material layer 4 can be hardened or softened by adjusting the temperature, and the shape memory material layer 4 is coated on the inner wall or outer wall of the high specific strength material part 1. For example, the shape memory material layer 4 can be softened by increasing the temperature, and at this time, the shape memory material layer 4 is adjusted to be arranged on the inner wall or outer wall of the high specific strength material part 1. After reaching space, the ambient temperature decreases, and the shape memory material layer 4 gradually hardens, and after the binding belt 5 is released, it can be automatically unfolded and attached to the inner wall or outer wall of the high specific strength material part 1, which can further improve the overall stiffness of the high space utilization support / mast 1000 for space structures.

[0037] Specifically, the high space utilization support / mast 1000 for space structures of the embodiment is heated when it needs to be stored, and the tubular structure is pressed by an external force towards each other at the part of the tube segment outside the long circular hole gap 3 on both ends, so that the pressed tube segment part forms two layers of flat plates with a gap in the middle (there is a large internal stress) and the pressing fold occurs at the thermoplastic resin material part 2, and the two pressed tube segment parts are wound on two core materials 6 respectively to form two winding structures. Compared with the same winding structure of the high space utilization support / mast 1000 for space structures wound on the same one core material 6, the diameter of the winding structure is much smaller, so the size of the transportation storage space in the height and width directions is greatly reduced. Since the tube segment part wound on the two core materials 6 has a large internal stress, the tubular structure is stably stored by restraining the pressed tube segment part after winding with the binding belt 5. The two winding restrained tube segment parts, i.e. the two winding structures mentioned above, are turned through the long circular hole gap 3 to be perpendicular to the pressing direction, which further greatly reduces the size of the transportation storage space in the length direction. That is, the high space utilization support / mast 1000 for space structures of the embodiment is convenient to store and occupies a small space after storage, which is convenient for transportation from the earth to space.

[0038] When the high space utilization support / mast 1000 for space structure of the present application needs to be deployed after being transported to the space or the lunar surface environment, the shape memory material layer 4 is heated to enable plastic deformation, and then the binding belts 5 are sequentially untied; due to the decrease of the temperature in the space environment, the high space utilization support / mast 1000 for space structure of the present application with a large internal stress will automatically deploy under the release of the internal stress, and the shape memory material layer 4 will also deploy, and in the process of temperature decrease, the shape memory material layer 4 attached to the inner wall or the outer wall of the high specific strength material part 1 gradually hardens, which can effectively further improve the overall rigidity of the high space utilization support / mast 1000 for space structure. That is, the high space utilization support / mast 1000 for space structure of the present application has high rigidity after deployment, and can be applied to the support system of a satellite antenna or a solar panel, a communication tower for a lunar surface base, and a rapid deployment support of a solar energy station, etc.

[0039] In some embodiments, the material of the shape memory material layer 4 is epoxy-based SMPs, polyurethane-based SMPs or liquid crystal elastomers. These materials have high recovery stress.

[0040] In some embodiments, the material, number and shape of the binding belts 5 can effectively constrain the stored tubular structure with a large internal stress. The setting of the binding belts 5 ensures that the tubular structure will not be loosened during the transportation process after being stored.

[0041] In some embodiments, the material and shape of the core material 6 can effectively support the stored tubular structure. The material of the core material 6 is based on the density parameter of minimizing the launch mass, rigidity and strength to meet the radial winding pressure of the mast without being crushed. Therefore, the recommended material is a polymer foam, such as polymethacrylimide foam (density of 30-75 kg / m 3 ), aluminum alloy honeycomb material (density can be controlled at 30-100 kg / m 3 ).

[0042] In some embodiments, the core material 6 is a cylinder. The tubular body is formed by winding around the cylindrical core material 6, and the cylindrical shape can maximize the utilization of space.

[0043] Although the embodiments of the present application have been shown and described above, it should be understood that the above embodiments are exemplary and should not be construed as limiting the present application, and those of ordinary skill in the art can make changes, modifications, replacements and variations to the above embodiments within the scope of the present application.

Claims

1. A support / mast with high space utilization for space structures, characterized in that, It is a tubular structure, including: A high-strength material portion is arranged on opposite sides of the tubular structure; A thermoplastic resin material portion, wherein the thermoplastic resin material portion is connected to the edges of the high-specific-strength material portions on opposite sides, so as to form the tube body structure of the tubular structure together with the high-specific-strength material portions; Elongated oval slits are arranged on opposite sides of the high-strength material portions at positions directly opposite each other. During storage, the tubular structure sections located outside the two ends of the elongated hole are flattened facing each other, so that the flattening creases occur at the thermoplastic resin material. The two flattened tubular sections are then coiled around the core material, and the coiled flattened tubular sections are secured with binding straps. The two coiled and secured tubular sections are then rotated orthogonally to the flattening direction through the elongated hole.

2. The high space utilization support / mast for space structures according to claim 1, characterized in that, The material with high specific strength has an elastic modulus of 100~200GPa and a tensile strength of 600~3700MPa.

3. The high space utilization support / mast for space structures according to claim 1, characterized in that, The high-strength material is made of fiber composite material or titanium alloy.

4. The high space utilization support / mast for space structures according to claim 3, characterized in that, The fiber composite material is carbon fiber composite material, basalt fiber composite material, or aramid fiber composite material.

5. The high space utilization support / mast for space structures according to claim 1, characterized in that, The thermoplastic resin material is made of thermoplastic polyurethane, thermoplastic elastomer, modified polyethylene, or nylon elastomer.

6. The high space utilization support / mast for space structures according to claim 1, characterized in that, It also includes a shape memory material layer, which is disposed on the inner and outer walls of the tube body structure.

7. The high space utilization support / mast for space structures according to claim 6, characterized in that, The shape memory material layer is made of epoxy-based SMPs, polyurethane-based SMPs, or liquid crystal elastomers.

8. The high space utilization support / mast for space structures according to claim 1, characterized in that, The material, quantity, and shape of the binding straps can effectively constrain and fix the tubular structure after it has been stored, which has a large internal stress.

9. The high space utilization support / mast for space structures according to claim 1, characterized in that, The material and shape of the core material are sufficient to effectively support the tubular structure after it has been stored.

10. The high space utilization support / mast for space structures according to claim 1, characterized in that, The core material is cylindrical.

Images