A superconducting thermal variable body satellite structure based on memory alloy and a processing method thereof

Abstract

The application discloses a superconducting heat variable body satellite structure based on a memory alloy and a processing method, relates to the field of spacecraft structures, and comprises a satellite variable body structure, a compression device and solar wings connected to opposite sides of the satellite variable body structure. The satellite variable body structure is a cylindrical structure with a polygonal cross section, each side of the satellite variable body structure comprises a plurality of arc-shaped plates which are integrally connected in sequence, and the middle part of each arc-shaped plate protrudes away from the center line of the satellite variable body structure. The compression device is used for driving the satellite variable body structure to compress along the direction of the center line of the satellite variable body structure. The spacecraft structure can realize multi-state conversion.

Description

TECHNICAL FIELD

[0001] The application relates to a superconducting heat variable satellite structure based on a memory alloy and a processing method thereof, and belongs to the field of lightweight functional structure design and manufacturing of a spacecraft. BACKGROUND

[0002] The rapid development of the aerospace field makes human beings continuously improve the performance requirements of a spacecraft, and future spacecrafts will have multi-modal functions, that is, when performing a task, a key load with high power intermittently works, a large amount of heat is generated, and the satellite needs to be in an unfolded state to facilitate space radiation heat dissipation; in the on-orbit hibernation or maintenance operation phase, the satellite needs to be in a folded state to reduce the heat radiation area, reduce power consumption and increase the on-orbit service life of the satellite.

[0003] At present, the satellite with a traditional fixed structure is mostly made of honeycomb composite materials or lightweight alloys, has high structural stiffness and does not have deformability, that is, the traditional satellite structure cannot realize shape memory deformation mode conversion, and has been unable to adapt to the complex task requirements of the future aerospace field. SUMMARY

[0004] The application solves the technical problem of overcoming the deficiencies of the prior art and providing a superconducting heat variable satellite structure based on a memory alloy and a processing method thereof, so as to realize multi-state conversion of a spacecraft structure.

[0005] The technical solution of the application is as follows.

[0006] In a first aspect, a superconducting heat variable satellite structure based on a memory alloy is provided, which comprises a satellite variable body structure, a compression device and solar wings connected to opposite sides of the satellite variable body structure; the satellite variable body structure is a cylinder with a polygonal cross section, each side of the satellite variable body structure comprises a plurality of arc-shaped plates which are integrally connected in sequence, and the middle part of each arc-shaped plate protrudes away from the center line of the satellite variable body structure; the compression device is used to drive the satellite variable body structure to compress along the direction of the center line of the satellite variable body structure.

[0007] In some implementations of the first aspect, the included angle between the connection positions of two adjacent arc-shaped plates is an obtuse angle. Preferably, the included angle between the connection positions of the two adjacent arc-shaped plates is 120-160 degrees.

[0008] In some implementations of the first aspect, the arc of the arc-shaped plate is pi / 6-pi / 2 radian, and the radius of the circle on which the arc-shaped plate is located is not less than 5 mm.

[0009] In some implementations of the first aspect, the material of the satellite variable body structure is a nickel-titanium memory alloy material; the satellite variable body structure comprises an outer skin and microstructure cells filled in the skin; the microstructure cells comprise simple cubic, body-centered cubic, face-centered cubic, simple hexagonal, simple tetragonal, body-centered tetragonal, hexagonal, simple orthorhombic, orthorhombic, body-centered orthorhombic, face-centered orthorhombic, simple monoclinic, monoclinic, and simple triclinic, and their deformation body microstructure cells.

[0010] In some implementations of the first aspect, the compression device comprises a plurality of tensioning ropes and a driver group for winding the tensioning ropes, the driver group is connected to the inside of one end of the satellite variable body structure, one end of each of the tensioning ropes is connected to the inside of the other end of the satellite variable body structure, and the other end of each of the tensioning ropes is connected to the driver group.

[0011] In some implementations of the first aspect, the driver group comprises a motor connected to the inside of the satellite variable body structure, a controller, and a winding wheel connected to the output shaft of the motor, the ends of the tensioning ropes are wound around the winding wheel, the controller is used to control the rotation of the motor to complete the winding of the tensioning ropes, and the satellite variable body structure is folded; the motor is enabled to stop, the release of the tensioning ropes is completed, and the memory alloy deformation drive of the satellite variable body structure is implemented to unfold.

[0012] In some implementations of the first aspect, a load plate is connected to the inside of the satellite variable body structure, the load plate is located at the middle of the satellite variable body structure, the driver group is installed on the load plate, and a support rod is connected between the load plate and each inner wall of the satellite variable body structure.

[0013] In some implementations of the first aspect, a polyimide film and a graphene film are sequentially arranged on the inside of the satellite variable body structure.

[0014] In some implementations of the first aspect, a heating device is arranged on the surface of the satellite variable body structure, and the heating device is used to heat to excite the satellite variable body structure to adjust the structural form. Preferably, the heating device is an electrode.

[0015] In the second aspect, a processing method of a superconducting thermal variable body satellite structure based on a memory alloy is provided, according to any one of the above-described superconducting thermal variable body satellite structures based on a memory alloy, comprising:

[0016] S1: a shape memory alloy is used to prepare a satellite variable body structure by laser selective melting integration;

[0017] S2: a polyimide film and a graphene film are pasted on the inner curved surface of the satellite variable body structure;

[0018] S3: install compression device at the bottom of the satellite variable body structure for regulating the double-way deformation of the satellite variable body structure, and install communication and sensing structure on the satellite variable body structure.

[0019] The curved surface with complex three-dimensional folds is manufactured by using nickel-titanium shape memory alloy, the satellite variable body structure with a telescopic ratio of 0.4 is realized, the double-way deformation function is realized by means of the compression device and the heat transfer of the graphene film on the curved surface of the satellite variable body structure; the folding structure (i.e. the satellite variable body structure) has two ends reserved for installing space for loading satellite mechanical, sensing and other components. The statics simulation verifies the structure bearing and the thermodynamics excitation verifies the telescopic performance of the shape memory structure, the modal analysis is carried out, and the first five modes are extracted to check the safety of the structure.

[0020] Based on the additive manufacturing of the nickel-titanium shape memory alloy thin-walled porous superstructure, the macroscopic Young's modulus and Poisson's ratio of the structure can be adjusted through the design of the overall size of the microcell, the rod diameter or the characteristic size of the minimum curved surface, and the periodic arrangement rule, which can improve the carrying capacity of the satellite variable body structure on the basis of light weight and high strength, achieve the ability to resist impact that the traditional honeycomb and foam materials do not have, and have the shape memory function with high accommodation ratio. Based on the integration technology of the additive manufacturing of the nickel-titanium memory alloy material and the superstructure and the film covering technology based on the graphene material, the satellite on-orbit mode conversion is realized.

[0021] In summary, the present application at least has the following beneficial technical effects:

[0022] (1) The additive manufacturing of the nickel-titanium memory alloy satellite structure has the ability of state conversion between the unfolded and the folded states;

[0023] (2) The satellite overall structure composite graphene heat conduction film realizes the rapid diffusion of heat in the load mounting plate and the rapid and efficient thermal deformation driving of the structure;

[0024] (3) The external skin filled with various microstructure cells is adopted, and the mechanical properties such as structure bearing and stiffness have strong designability. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 It is a schematic diagram of the overall structure of the present application;

[0026] Figure 2 It is a schematic diagram of the structure of the compression device;

[0027] Figure 3 It is a local section of the satellite high-thermal-conductivity reciprocating memory deformation structure;

[0028] Figure 4 It is a schematic diagram of the structure of the satellite structure in the unfolded state and the compressed state.

[0029] Explanation of reference numerals in the attached figures: 1. Satellite morphing structure; 2. Solar array; 3. Upper payload plate mounting interface; 4. Lower payload plate; 5. Compression device; 51. Tensioning rope; 52. Driver assembly; 53. Drive motor; 54. Retraction ring; 55. Support structure; 6. Skin lattice structure; 7. Polyimide film; 8. Graphene film. Detailed Implementation

[0030] The present application will now be described in further detail with reference to the accompanying drawings and specific embodiments:

[0031] This application discloses a superconducting thermally variable satellite structure and fabrication method based on shape memory alloys, such as... Figure 1 As shown, the variable satellite structure includes a variable satellite structure 1, a compression device 5, and solar panels 2 connected to opposite sides of the variable satellite structure 1. The compression device 5 is connected to the interior of one end of the variable satellite structure 1 and is used to drive the variable satellite structure 1 to compress along the centerline of the variable satellite structure 1, thereby achieving two-way deformation of the structure.

[0032] The satellite variant structure 1 is a cylindrical shape with a square cross-section. Each side of the structure includes multiple arc-shaped plates that are integrally connected in sequence. The center of each arc-shaped plate protrudes away from the centerline of the satellite variant structure 1. The included angle between the connection points of two adjacent arc-shaped plates is 120° to 160°. The curvature of the arc-shaped plates is π / 6 to π / 2 radians, and the radius of the circle containing the arc-shaped plates is not less than 5 mm.

[0033] The ends of the curved plates on adjacent sides of the satellite's variable structure are connected directly to each other.

[0034] The satellite's morphing structure 1 is made of nickel-titanium shape memory alloy; the satellite's morphing structure 1 is a skin lattice structure 6, such as... Figure 2 As shown, the satellite's variable structure 1 includes an outer skin and microstructure cells filled within the skin; the microstructure cells are body-centered cubic (BCC) cells with an overall size of 7.5 mm × 7.5 mm × 7.5 mm and a characteristic dimension rod diameter of 0.5 mm.

[0035] like Figure 2 As shown, the compression device 5 includes multiple tension ropes 51 and a drive assembly 52 for winding up the tension ropes 51. The drive assembly 52 is connected to the inside of one end of the satellite variable structure 1. A connecting ring is connected to the inside of the other side of the satellite variable structure 1. Four tension ropes 51 are provided. One end of the tension rope 51 is connected to the inside of the other end of the satellite variable structure 1 through the connecting ring. The other end of the tension rope 51 is gathered to the center line of the satellite variable structure 1 and connected to the drive assembly 52.

[0036] The driver group 51 includes a motor connected to the inside of the satellite variable body structure 1, a controller, and a winding wheel connected to the output shaft of the motor, and the ends of the tensioning ropes 51 are wound around the winding wheel. The controller is used to control the rotation of the motor, enable and end enable.

[0037] The upper load plate mounting interface 3 is used to mount the satellite payload or other functional components, and the lower load plate 4 is located at the middle position of the satellite variable body structure 1. The lower load plate 4 is connected to each inner wall of the satellite variable body structure 1 through a support rod. The lower load plate 4 is used to mount the driver group 52 and communication sensing structure, and the driver group 52 is mounted on the lower load plate 4. The surface of the lower load plate 4 is provided with a compression device support structure 55, which includes a support plate mounted on the lower load plate 4, and a bunching ring connected to the support plate. In this embodiment, the support plate is provided with four boxes with openings facing the tensioning ropes 51, and the openings of the boxes are connected to the bunching ring 54. The four tensioning ropes 51 are wound around the driver assembly 52 through the bunching ring 54, and the four tensioning ropes 51 are uniformly wound and released through the driving motor 53, so as to ensure the folding and unfolding of the satellite variable body structure.

[0038] As shown in Figure 3 The inside of the satellite variable body structure 1 is sequentially provided with a polyimide film 6 and a graphene film 8. The polyimide film 7 is used to adhere to the surface of the satellite variable body structure, and ensures high thermal conductivity. The graphene film 8 is used to improve the thermal conductivity, so that the heat generated by the equipment installed inside the satellite variable body structure 1 can be quickly dispersed, so that the satellite variable body structure 1 is uniformly heated, which is beneficial to realize the efficient thermal deformation driving of the satellite variable body structure 1. The surface of the satellite variable body structure 1 is provided with a heating device, which is an electrode adhered to the outer surface of the satellite variable body structure 1 in this embodiment. The heating device is used to heat the satellite variable body structure, so as to stimulate the satellite variable body structure to quickly adjust the structural form.

[0039] The processing method comprises the following steps:

[0040] Step 1: Select a shape memory alloy additive manufacturing material system suitable for space driving, and determine the satellite large-size structure additive manufacturing process parameters;

[0041] Step 2: The fold, vertex and facet definition are used to construct the foldable structure (i.e. the satellite variable body structure), and the arc-shaped large-angle curved surface design is adopted to facilitate additive manufacturing, so as to adjust the satellite form under the premise of ensuring the stiffness of the satellite.

[0042] Step 3: The thermodynamic simulation verifies the shape memory alloy deformation mode and heat transfer characteristics, the statics simulation checks the structure bearing capacity, and the dynamics numerical analysis extracts the characteristic frequency below 100 Hz.

[0043] Step 4: Obtain the satellite variable body structure 1 by laser selective melting integration of shape memory alloy, paste graphene on the outer surface of the satellite variable body structure 1 for heat transfer, and paste electrodes on the surface of the satellite variable body structure 1 for heating to excite the shape memory alloy to adjust the structure morphology; install a driving assembly at the bottom of the satellite variable body structure 1 for regulating the double-way deformation of the structure, and reserve space at the upper and lower ends for installing the mechanical, communication and sensing structures of the satellite,

[0044] The implementation principle of the present application is:

[0045] When the satellite is in the on-orbit dormancy or maintenance operation stage, the controller controls the motor to start, the motor drives the winding wheel to rotate, the tensioning rope 51 is gradually wound on the winding wheel, the satellite variable body structure 1 receives the pulling force of the tensioning rope 51, so that the arc-shaped plate is extruded and deformed along the center line direction of the satellite variable body structure 1, and the satellite is compressed, as shown in the right graph of Figure 4 .

[0046] When the satellite is in on-orbit full-load full-power operation, the controller controls the motor to end, at this time the output shaft of the motor can rotate, the tensioning rope 51 no longer maintains the satellite variable body structure 1 in the contracted state, the heat generated by the equipment installed in the satellite variable body structure 1 and / or the heat provided by the heating device acts on the satellite variable body structure 1, and the satellite variable body structure 1 expands due to its shape memory function, as shown in the left graph of Figure 4 .

[0047] The contents not described in detail in the specification of the present application belong to the known technology of the person skilled in the art.

[0048] Although the present application is disclosed with the preferred embodiments as above, it is not intended to limit the present application, any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present application, therefore, the protection scope of the present application should be limited by the scope defined by the claims of the present application.

Claims

1. A super-insulated morphing satellite structure based on shape memory alloys, characterized by: The satellite variable body structure (1) is a cylindrical body with a polygonal cross section, each side of which comprises a plurality of arc-shaped plates connected in sequence, the middle part of each arc-shaped plate being convex away from the center line of the satellite variable body structure (1); the compression device (6) is used to drive the satellite variable body structure (1) to compress along the center line direction of the satellite variable body structure (1); the compression device (6) comprises a plurality of tensioning ropes (61) and a driver group (62) for winding the tensioning ropes (61), the driver group (62) being connected to the inside of one end of the satellite variable body structure (1), one end of each tensioning rope (61) being connected to the inside of the other end of the satellite variable body structure (1), and the other end of each tensioning rope (61) being connected to the driver group (62); the included angle between the connection positions of two adjacent arc-shaped plates is obtuse; the included angle between the connection positions of two adjacent arc-shaped plates is 120°-160°.

2. A super-insulated morphing satellite structure based on shape memory alloys according to claim 1, characterized in that: The curvature of the arc-shaped plate is π / 6-π / 2 radian, and the radius of the circle on which the arc-shaped plate is located is not less than 5 mm.

3. A super-insulated morphing satellite structure based on shape memory alloys according to claim 1, characterized in that: The material of the satellite variable body structure (1) is shape memory alloy; the satellite variable body structure (1) comprises an outer skin and microstructure cells filled in the skin; the microstructure cells comprise simple cubic, body-centered cubic, face-centered cubic, simple hexagonal, simple tetragonal, body-centered tetragonal, hexagonal, simple orthorhombic, orthorhombic, body-centered orthorhombic, face-centered orthorhombic, simple oblique, orthorhombic, simple triclinic and their deformation body microstructure cells.

4. The super-insulated morphing satellite structure based on shape memory alloys according to claim 1, characterized in that: The driver group (62) comprises a motor connected to the inside of the satellite variable body structure (1), a controller and a winding wheel connected to the output shaft of the motor, the ends of the tensioning ropes (61) being wound on the winding wheel, the controller being used to control the rotation of the motor to complete the winding of the tensioning ropes, so that the satellite variable body structure is folded; the motor is disabled to complete the release of the tensioning ropes, and the shape memory alloy deformation drive of the satellite variable body structure is used to unfold.

5. A super-insulated morphing satellite structure based on shape memory alloys according to claim 1, characterized in that: The inside of the satellite variable body structure (1) is connected with a load plate (5), the load plate (5) being located at the middle part of the satellite variable body structure (1), the driver group (62) being installed on the load plate (5), and a support rod being connected between each inner wall of the satellite variable body structure (1) and the load plate (5).

6. A super-insulated morphing satellite structure based on shape memory alloys according to claim 1, characterized in that: The inside of the satellite variable body structure (1) is sequentially provided with a polyimide film (8) and a graphene film (9).

7. The super-insulated morphing satellite structure based on shape memory alloys according to claim 1, characterized in that: The surface of the satellite variable body structure (1) is provided with a heating device for heating to stimulate the satellite variable body structure (1) to adjust the structural form.

8. A method of processing a superconducting thermal morphing satellite structure based on shape memory alloy, according to any one of claims 1-7, characterized in that: S1: using shape memory alloy to prepare a satellite variable body structure (1) by laser selective melting; S2: pasting a polyimide film (8) and a graphene film (9) on the inner curved surface of the satellite variable body structure (1); S3: installing a compression device (6) at the bottom of the satellite variable body structure (1) to control the double-way deformation of the satellite variable body structure (1), and installing communication and sensing structures on the satellite variable body structure (1).

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