Spacecraft self-opening and closing light shielding mechanism based on shape memory alloy and manufacturing method thereof

Abstract

The application relates to a spacecraft self-opening and closing light shielding mechanism based on a shape memory alloy and a manufacturing method, which comprises a fixing frame, a driving shaft rotatingly arranged on the fixing frame, a driving ring slidingly sleeved on the driving shaft, a light shielding plate fixedly arranged on the driving shaft, and an extension driving mechanism arranged between the fixing frame and the driving ring; wherein the extension driving mechanism comprises a sliding sleeve and an extension screw; the two ends of the sliding sleeve are connected with the fixing frame and the driving ring respectively; the extension screw is a shape memory alloy screw; the driving shaft is in the shape of a twisted prism, and the driving ring is adaptively sleeved on the driving shaft, so that the extension screw can be extended and contracted and drive the driving ring to slide along the driving shaft when the extension screw is heated or cooled, thereby driving the driving shaft to rotate and driving the light shielding plate to synchronously overturn. Compared with the prior art, the application effectively solves the technical problems of the existing porthole light shielding mechanism, such as response lag, complex structure and easy damage, improves the intelligence and reliability of the spacecraft, and has a wide engineering application prospect.

Description

Technical Field

[0001] This invention belongs to the field of additive manufacturing and smart materials technology, and relates to a spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy and its manufacturing method. Background Technology

[0002] Shape memory alloys are a class of smart materials composed of specific metallic elements in a certain proportion. Their core characteristic is that they undergo martensitic phase transformation and inverse transformation under thermal excitation, thereby generating a shape memory effect. In recent years, shape memory alloys have become a research hotspot in the field of smart materials and have demonstrated key application value in the manufacturing of core equipment in the aerospace field.

[0003] Spacecraft need to perform missions in the vacuum environment of space for a long time, and the observation and scientific instruments they carry are extremely sensitive to the working environment: the temperature of the sunlit side rises sharply due to strong light, while the temperature of the shaded side drops sharply due to insufficient light. In order to ensure the operational stability of the instrument components and the accuracy of data acquisition, a shading mechanism must be equipped to avoid the influence of extreme thermal environment. However, the current shading mechanism of spacecraft mostly adopts a complex mechanical structure driven by motor, which has obvious limitations in practical applications: (1) The equipment structure is complex. The existing mechanism uses a motor as the power source and needs to be matched with a multi-stage transmission mechanism, which increases the number of assembly connection points and directly reduces the overall operational reliability of the equipment; at the same time, the motor needs to be wired separately, which further increases the complexity of the structural design; (2) The maintenance is difficult. The mechanism is easily damaged by the impact of space debris, and due to the complexity of the structure, if an on-orbit failure occurs, extravehicular maintenance is not only extremely difficult, but also increases the safety risk of astronauts; (3) The intelligence is insufficient. The response is lagging and it cannot automatically adjust the state according to the solar irradiation under different attitudes of the spacecraft. It lacks intelligent functions that adapt to changes in thermal environment.

[0004] In contrast, shape memory alloys can autonomously recover their pre-set shape, providing a core material foundation for constructing intelligent opening and closing structures that do not require electrical control. Furthermore, the development of additive manufacturing (3D printing) and 4D printing (functional structure self-evolution) technologies has broken through the manufacturing limitations of shape memory alloys in complex aerospace structures. Against this backdrop, how to develop self-opening and closing light-shielding mechanisms for spacecraft based on shape memory alloys and their manufacturing methods has become one of the key issues in promoting the practical application of this technology in the field of aerospace components. Summary of the Invention

[0005] The purpose of this invention is to provide a spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy and its manufacturing method. This invention utilizes temperature changes under illumination and backlighting conditions to alter the length of a telescopic helical component made of shape memory alloy, thereby generating thrust and tension on a drive ring. This, in turn, drives a drive shaft, which is conformally slidably fitted to the drive ring, to twist in both directions. The twisting of the drive shaft causes the light-shielding plate to rotate synchronously, thus opening and closing the light-shielding mechanism. This achieves automatic switching of the light-shielding function's open / closed state according to illumination conditions, effectively solving the technical problems of existing window light-shielding mechanisms, such as slow response, complex structure, and susceptibility to damage.

[0006] The objective of this invention can be achieved through the following technical solutions:

[0007] The first aspect of the present invention provides a spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy, including a fixed frame, a drive shaft rotatably mounted on the fixed frame, a drive ring slidably mounted on the drive shaft, a light-shielding plate fixedly mounted on the drive shaft, and a telescopic drive mechanism disposed between the fixed frame and the drive ring.

[0008] The telescopic drive mechanism includes a sliding sleeve and a telescopic spiral component disposed inside the sliding sleeve; both ends of the sliding sleeve are respectively connected to a fixed frame and a drive ring; the telescopic spiral component is a shape memory alloy spiral component, and both ends are respectively connected to both ends of the sliding sleeve.

[0009] The drive shaft is in the shape of a torsion prism, and the inner hole shape of the drive ring matches the cross-sectional shape of the drive shaft. It is conformally slidably sleeved on the drive shaft to achieve a limiting sliding fit, so that the telescopic spiral can extend and retract when heated or cooled and drive the drive ring to slide along the drive shaft, thereby driving the drive shaft to rotate and driving the light shield to rotate synchronously.

[0010] In some specific embodiments, the drive shaft has rotating shafts at both ends; the fixed frame has rotating shaft seats that rotatably support the rotating shafts.

[0011] In some specific embodiments, a torsion helical component is sleeved on the rotating shaft. The torsion helical component is a shape memory alloy component used to apply torque to assist the rotation of the drive shaft when heated, thereby forming a dual drive mode with the telescopic helical component.

[0012] In some specific embodiments, a torsion helical component is sleeved on the rotating shaft. The torsion helical component is a shape memory alloy helical component, one end of which is fixed to the rotating shaft, preferably fixed to the blind hole of the rotating shaft; the other end is fixedly connected to the rotating shaft seat and fixed to the through hole of the rotating shaft seat.

[0013] In some specific embodiments, the drive shaft is provided with support frames arranged in parallel, and a driven shaft is provided between the support frames; one side of the light shield is fixedly connected to the driven shaft.

[0014] In some specific embodiments, the drive shaft is a quadrangular prism that twists about the axis of rotation, and the drive ring is correspondingly a conformal square shape.

[0015] In some specific embodiments, the shape memory alloy spiral component is a shape memory alloy component with Ni and Ti as the main elements.

[0016] In some specific embodiments, the pivot seat includes a housing for accommodating the pivot and having an opening, and a cover provided at the opening.

[0017] In some specific embodiments, the fixing frame includes bases arranged side by side, and the rotating shaft seat is disposed on the corresponding base;

[0018] Positioning rods and slide rails are arranged side by side between the bases;

[0019] One end of the sliding sleeve is provided with a positioning ring, which is detachably fixed on the positioning rod; the other end is provided with a sliding block, which is slidably disposed on the slide rail.

[0020] A second aspect of the present invention provides a method for preparing a spacecraft self-opening and closing light-shielding mechanism based on the above-described method, comprising the following steps:

[0021] S1: Plan the linkage deformation path of the light shield, telescopic screw, and torsion screw, and verify the deformation coordination under different temperature ranges through experiments to ensure that the structure can achieve precise opening and closing actions within the preset temperature range.

[0022] S2: Based on the linkage deformation path planning, construct a three-dimensional linkage model of the light shield and the telescopic drive mechanism. The model includes the size parameters, connection methods and shape memory effect trigger points of each component.

[0023] S3: Using metal 3D printing technology, based on the three-dimensional linkage model constructed in step S2, shape memory alloy powder is integrated into a structural component with thermal response function to ensure the mechanical properties and phase transformation consistency of the structure.

[0024] S4: Perform stepped heat treatment on the printed overall structure to eliminate internal stress generated during printing; at the same time, through shape constraint and release at heating temperature, set the initial memory shape, target recovery shape and response temperature threshold of the structure to ensure stable shape transformation under preset temperature excitation.

[0025] S5: The molded structure processed in step S4 is precisely assembled into the spacecraft window system to simulate the extreme temperature difference environment of alternating high temperature on the sun-facing side and low temperature on the shaded side in space. The opening and closing response speed, repeated operation stability and extreme working condition tolerance of the shading mechanism are tested to verify the actual application performance of the device.

[0026] In some specific implementations, the self-opening and closing light-blocking mechanism is integrated with the spacecraft's observation window.

[0027] This invention utilizes a shape memory alloy to create a telescopic drive mechanism. By leveraging the thermal deformation characteristics of the shape memory alloy, and the heating and cooling effects under illumination and backlighting conditions, the telescopic drive mechanism achieves telescopic movement, driving the drive ring to reciprocate on the drive shaft. Simultaneously, the torsional prismatic structure of the drive shaft and the conformal fitting between the drive ring and the drive shaft allow the drive ring to rotate the drive shaft in either the forward or reverse direction during its reciprocating motion, thereby achieving the flipping of the light-shielding plate. Ultimately, this achieves the effect of opening the light-shielding plate under illumination and closing it under backlighting. It boasts advantages such as simple and robust structure, rapid response under illumination conditions, and high degree of automation. It effectively solves the technical problems of existing window light-shielding mechanisms, such as slow response, complex structure, and susceptibility to damage, improving the intelligence and reliability of spacecraft and possessing broad engineering application prospects.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] (1) No additional driving force required. Thanks to the thermal response characteristics of shape memory alloys, the device can achieve self-opening and closing function when the ambient temperature changes, eliminating the dependence on driving components such as motors and improving the stability and reliability of operation.

[0030] (2) The structure is simple and the economy is excellent. The overall structure of the device is simple, reducing the number of multi-stage transmission mechanisms and wiring components, thus reducing the overall weight to meet the lightweight requirements of spacecraft. At the same time, the reduction in the number of parts reduces manufacturing costs and assembly difficulty, improving the economic efficiency of equipment operation.

[0031] (3) It can realize the integration of "material-structure-function". With the help of 4D printing technology to precisely form shape memory alloys, the initial shape and target shape of the components can be flexibly designed according to the task requirements, so as to realize the integration of material properties, structural shape and light-shielding function.

[0032] (4) Flexible and controllable functional applications. Based on the unique phase transformation properties of shape memory alloys, while keeping the structural body unchanged, the functions such as shading angle and opening and closing rate can be flexibly controlled by preset temperature thresholds or adjusting shape memory parameters, which can adapt to the diverse working needs of spacecraft in complex space environments. Attached Figure Description

[0033] Figure 1 This is a three-dimensional structural diagram of a spacecraft self-opening and closing light-shielding mechanism based on the above-mentioned invention.

[0034] Figure 2 This is a schematic diagram of a partial disassembly of the drive shaft and fixing frame of a spacecraft self-opening and closing light-shielding mechanism based on the above-mentioned invention.

[0035] Figure 3 This is a schematic diagram of the deployment structure of a spacecraft self-opening and closing light-shielding mechanism based on the above-mentioned embodiment.

[0036] Figure 4 This is a schematic diagram of the telescopic drive mechanism based on the above-mentioned spacecraft self-opening and closing light-shielding mechanism in one embodiment.

[0037] Figure 5 This is a schematic diagram of the assembly of the telescopic drive mechanism and the drive ring.

[0038] Figure 6 This is a schematic diagram of a partial disassembly of the positioning ring based on the above-described spacecraft self-opening and closing light-shielding mechanism in an embodiment.

[0039] Figure 7 This is a schematic diagram of the pin structure.

[0040] Figure 8 This is a schematic diagram of the assembly structure of the telescopic drive mechanism and the positioning ring.

[0041] Explanation of markings in the diagram:

[0042] 1-Drive shaft; 101-Support frame; 102-Rotating shaft; 103-Rotating shaft blind hole; 2-Driven shaft; 3-Light shield; 4-Fixed frame; 401-Fixed frame housing; 402-Base; 403-Rotating shaft seat through hole; 5-Positioning rod; 6-Drive ring; 601-Drive hole; 602-Sliding hole; 603-Connecting hole; 7-Slide rail; 8-Telescopic drive mechanism; 801-Sliding sleeve; 802-Telescopic spiral component; 803-Torsion ring buckle; 9-Positioning ring; 901-Rotating hook; 902-Positioning pin; 903-Positioning ring housing; 10-Pin; 11-Torsion spiral component; 12-Cap. Detailed Implementation

[0043] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. The following embodiments are based on the above-described technical solutions of the present invention, providing detailed implementation methods and specific operating procedures. However, the scope of protection of the present invention is not limited to the following embodiments.

[0044] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention. Furthermore, the terms "first," "second," "third," etc., used to describe a common object only indicate different instances of the same object, and do not imply that the objects described in this way must be in a given order, whether temporally, spatially, sequentially, or in any other way.

[0045] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0046] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0047] The following detailed description of some embodiments of the present invention is provided in conjunction with the accompanying drawings. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0048] Example:

[0049] like Figure 1 and Figure 2 The spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy shown includes a fixed frame 4, a drive shaft 1 rotatably mounted on the fixed frame 4, a drive ring 6 slidably mounted on the drive shaft 1, a light-shielding plate 3 fixedly mounted on the drive shaft 1, and a telescopic drive mechanism 8 disposed between the fixed frame 4 and the drive ring 6.

[0050] The drive shaft 1 is in the shape of a torsion prism, and the inner hole shape of the drive ring 6 matches the cross-sectional shape of the drive shaft 1. It is conformally slidably sleeved on the drive shaft 1 to achieve a limiting sliding fit, so that when the telescopic spiral 802 is heated or cooled, it can extend and retract and drive the drive ring 6 to slide along the drive shaft 1, thereby driving the drive shaft 1 to rotate and driving the light shield 3 to rotate synchronously.

[0051] The device is installed on the outside of the porthole of a spacecraft or capsule. By responding to temperature changes, the light-shielding plate 3 automatically closes when exposed to sunlight and automatically opens when in shadow or no light. Normally, it remains in a semi-open state to balance the needs of shading and observation. Specifically, the telescopic spiral component 802 is a spiral component made of shape memory alloy. When the spiral component is heated by light, it returns to its original shape and elongates axially, thereby pushing the sliding sleeve 801 to elongate. This causes the drive ring 6 to move forward along the drive shaft 1. Since the drive shaft 1 is a torsion prism, the drive ring 6 is conformally fitted onto the drive shaft 1, so that while the drive shaft 1 moves, the drive ring 6 pushes the drive shaft 1 to rotate in the torsional direction, thereby pushing the light shield 3 to flip forward, changing from an open state to a closed state. When the spiral component is cooled, it contracts axially, thereby pulling the sliding sleeve 801 to contract, causing the drive ring 6 to move in the opposite direction along the drive shaft 1. Under the conformal limiting action of the drive ring 6, the drive shaft 1 rotates in the opposite direction, thereby causing the light shield 3 to flip in the opposite direction, changing from a closed state to an open state.

[0052] Therefore, this embodiment uses a shape memory alloy to make the telescopic drive mechanism 8. By utilizing the thermal deformation characteristics of the shape memory alloy, as well as the heating and cooling effects of the shape memory alloy under illumination and backlighting conditions, the telescopic drive mechanism 8 can achieve telescopic movement, driving the drive ring 6 to reciprocate on the drive shaft 1. At the same time, by utilizing the torsional prism structure of the drive shaft 1 and the conformal fitting between the drive ring 6 and the drive shaft 1, the drive ring 6 can drive the drive shaft 1 to rotate in the forward or reverse direction while reciprocating, thereby realizing the flipping of the light shield 3. Ultimately, it achieves the effect of opening the light shield 3 under illumination and closing the light shield 3 under backlighting conditions. It has the advantages of simple and reliable structure, rapid response under illumination conditions, and high degree of automation. It effectively solves the technical problems of existing window light shielding mechanisms such as slow response, complex structure, and easy damage, improves the intelligence and reliability of spacecraft, and has broad engineering application prospects.

[0053] In some specific embodiments, the two ends of the sliding sleeve 801 are hinged to the fixed frame 4 and the driving ring 6, respectively. For example... Figure 4 As shown, the telescopic drive mechanism 8 includes a sliding sleeve 801 and torsion rings 803 at both ends of the sliding sleeve 801, and a telescopic spiral member 802 disposed inside the sliding sleeve 801. Both ends of the sliding sleeve 801 are fixed to the bottom surface of the torsion rings 803, as shown. Figure 5 As shown, the torsion rings 803 at both ends of the sliding sleeve 801 are hinged to the fixing frame 4 and the driving ring 6 respectively; the telescopic spiral 802 is a shape memory alloy spiral, and its two ends are connected to the bottom surface of the torsion rings 803 at both ends of the sliding sleeve 801 respectively. Specifically, a hook structure can be used for connection, that is, hooks are provided at both ends of the telescopic spiral 802 and the bottom surface of the torsion rings 803 respectively, and they are connected through the hooks.

[0054] The torsion ring 803 is rotatably disposed at the end of the sliding sleeve 801. Specifically, the torsion ring 803 includes a disc-shaped base and a connecting plate arranged in parallel on the base. A connecting hole is provided through the connecting plate. A protruding ridge is provided around the outer edge of the disc-shaped base. An annular groove corresponding to the protruding ridge is provided on the inner wall of the end of the sliding sleeve 801. The protruding ridge is slidably disposed in the annular groove to realize the rotatable connection between the torsion ring 803 and the end of the sliding sleeve 801.

[0055] The drive ring 6 is provided with an insert plate inserted between the connecting plates. The insert plate has a socket adapted to the connecting hole. The drive ring 6 and the torsion ring 803 at one end of the sliding sleeve 801 are hinged by a pin 10 passing through the connecting hole and the socket. The structure of the pin 10 is as follows: Figure 7 As shown.

[0056] In some specific embodiments, a support frame 101 is arranged in parallel on the drive shaft 1, and a driven shaft 2 is arranged between the support frames 101; one side of the light shield 3 is fixedly connected to the driven shaft 2.

[0057] In some specific embodiments, the support frame 101 has a square hole, and the two ends of the driven shaft 2 are fitted into the square hole.

[0058] In some specific embodiments, the driven shaft 2 and the light shield 3 are mortise and tenon connected to facilitate installation, disassembly, maintenance and replacement.

[0059] In some specific embodiments, the drive shaft 1 is provided with rotating shafts 102 at both ends; the fixed frame 4 is provided with rotating shaft seats that support the rotating shafts.

[0060] In some specific embodiments, the drive shaft 1 is a quadrangular prism that twists about the axis of the rotating shaft 102, and the drive ring 6 is correspondingly a conformal square shape.

[0061] In some specific embodiments, the cross-section of the quadrangular prism is a square, that is, any cross-section perpendicular to the central axis is a square with equal side length.

[0062] In some specific embodiments, the drive shaft 1 is provided with multiple drive rings 6, and the fixed frame 4 is provided with multiple sets of sliding sleeves 801 and telescopic spiral components 802. Under the action of the contraction tension and extension thrust of the multiple sets of telescopic spiral components 802, the drive rings 6 are translated along the drive shaft 1, and the torsion prism in the middle of the drive shaft 1 is driven to twist, providing torque for the flipping of the light shield 3.

[0063] In some specific embodiments, a torsion spiral component 11 is sleeved on the rotating shaft 102. The torsion spiral component 11 is a shape memory alloy spiral component, with one end fixed to the rotating shaft and the other end fixedly connected to the rotating shaft seat.

[0064] The torsion spiral component 11 is made of shape memory alloy. When heated, it unfolds in the reverse spiral direction. Since one end of the spiral component is connected to a fixed rotating shaft seat and the other end is connected to a movable rotating shaft, it can drive the rotating shaft 102 to rotate together while unfolding, thus assisting the forward rotation of the light shield 3. Similarly, when cooling down, it retracts in the spiral direction to assist the reverse rotation of the light shield 3.

[0065] That is, under the same temperature change conditions (heating due to light exposure or cooling due to backlighting / shading), the torsion screw 11 and the telescopic screw 801 drive the mechanism to provide torque in the same direction to the drive shaft 1, forming a dual drive mode, and jointly control the opening and closing of the light shield 3.

[0066] In some specific embodiments, the shape memory alloy spiral component is a shape memory alloy with Ni, Ti, Cu, Zn, Al, and Fe as the main constituent elements, preferably a shape memory alloy component with Ni and Ti as the main constituent elements.

[0067] In some specific implementations, shape memory alloy powder is used as raw material, and additive manufacturing (3D printing) and 4D printing (functional structure self-evolution) technologies are used to manufacture the light shield 3, torsion spring and telescopic spring, so as to achieve precise control of the preset size of the parts.

[0068] In some specific embodiments, a temperature control device is also included, which is disposed in the sliding sleeve 801 or the housing 401, for heating or cooling the shape memory alloy spiral component.

[0069] In some specific embodiments, except for the light-shielding plate 3, the torsion screw 11 and the telescopic screw 802, the other components are all made of high-temperature resistant metal materials such as iron-based, nickel-based and cobalt-based materials with low coefficient of thermal expansion and stable microstructure without solid-state phase change.

[0070] In some specific embodiments, the pivot seat includes a housing 401 for accommodating the pivot and having an opening, and a cover 12 provided at the opening.

[0071] In some specific embodiments, the fixing frame 4 includes bases 402 arranged side by side, and the rotating shaft seat is disposed on the corresponding base 402;

[0072] The base 402 is provided with a positioning rod 5 and a slide rail 7 arranged side by side.

[0073] One end of the sliding sleeve 801 is hinged to a positioning ring 9, which is detachably fixed to the positioning rod 5; the other end is hinged to a sliding block, which is slidably mounted on the slide rail 7 and connected to the drive ring 6.

[0074] In some specific embodiments, the positioning ring 9 includes a rotating hook 901, a positioning pin 902, and a positioning ring housing 903. The positioning ring housing 903 is rectangular and is fitted onto the positioning rod 5. The positioning rod 5 has a positioning hole. The positioning ring housing 903 has a positioning through hole on one side and an installation hole on the opposite side. The positioning pin 902 passes through the positioning through hole and is inserted into the positioning hole to position the positioning ring 9 on the positioning rod 5. An annular groove is formed on the inner edge of the installation hole. The rotating hook 901 includes a hook disc seat and an insert plate on the hook disc seat. The outer edge of the hook disc seat has a protruding rib, which slides in the annular groove to achieve a rotatable connection between the rotating hook 901 and the positioning ring housing 903. A through hole is formed on the insert plate. The torsion ring 803 and the torsion ring 803 at one end of the sliding sleeve 801 are hinged together by a pin 10 passing through a connecting hole and the through hole.

[0075] The telescopic drive mechanism 8 is connected to the rotating hook 901. The telescopic spiral 802 passes through the sliding sleeve 801, limiting and protecting the telescopic spiral 802. The telescopic drive mechanism 8 limits the telescopic spiral 802, which is then fixed by the torsion ring 901 located on the edge of the sliding sleeve 801. After the components are assembled, they form one component of the self-opening and closing light-shielding mechanism. Multiple component units can be assembled according to the light-shielding requirements.

[0076] In some specific embodiments, the number of drive rings 6 is set to 1-5 according to the light-shielding area, and they are placed at equal intervals. Each drive ring 6 has a drive hole 601, a sliding hole 602, and a connecting hole 603. The sliding hole 602 is opened on the sliding block and fits into the slide rail 7. The square drive hole 601 of each drive ring 6 has the same rotation angle as the square cross section of the drive shaft rotating cylinder at the corresponding installation position, so as to ensure that the drive ring 6 can move smoothly on the slide rail 7 after being fitted into the drive shaft 1 and drive the drive shaft 1 to rotate. The connecting hole 603 is connected to the telescopic drive mechanism 8. The slide rail 7 ensures that the drive ring 6 slides smoothly back and forth on the slide rail 7. The number of positioning rings 9 is set to 1-5. The positioning rings 9 are installed on the positioning rod 5 and locked and fixed by the positioning pin 902. Specifically, positioning holes are opened on the side wall of the positioning ring 9 and the positioning rod 5. The positioning pin 902 passes through the positioning holes on the positioning ring 9 and the positioning rod 5 to fix the position of the positioning ring 9.

[0077] In some specific embodiments, the end face of the housing 401 is parallel to the end face of the base 402.

[0078] In some specific implementation methods, such as Figure 2As shown, the rotating shaft 102 is provided with a blind hole 103, and the housing 401 is provided with a through hole 403 for the rotating shaft seat. The rotating shaft 102 of the drive shaft 1 is installed at the through hole of the housing 401. The pin hole on the housing 401 is used to install the torsion screw 11. The inner diameter of the torsion screw 11 is larger than the cross-sectional diameter of the rotating shaft of the drive shaft 1. One end of the torsion screw 11 is bent outward and the other end is bent inward. During installation, the torsion screw 11 is fitted into the rotating shaft 102, the inwardly bent end of the torsion screw 11 is inserted into the blind hole 103 of the rotating shaft 102, and the outwardly bent end is inserted into the through hole 403 of the rotating shaft seat of the housing 401. A cover 12 is installed on the outside of the housing 401 for sealing and dust prevention. The base 402 locks and fixes the positioning rod 5 and the slide rail 7.

[0079] In some specific implementations, the spacecraft's self-opening and closing sunshade mechanisms are arranged side by side.

[0080] This embodiment utilizes the thermally induced phase transformation properties of NiTi50 shape memory alloy and combines additive manufacturing technology to achieve the integrated fabrication of the aforementioned spacecraft self-opening and closing light-shielding mechanism, including the following steps:

[0081] S1: Temperature-controlled response structure design. Based on the thermal phase change mechanism of shape memory alloys and combined with the environmental temperature change characteristics of spacecraft in orbit, the linkage deformation path planning is carried out for core components such as the light-shielding plate 3, telescopic screw 802, and torsion screw 11 of the light-shielding mechanism. The deformation coordination under different temperature ranges is verified by experiments to ensure that the structure can achieve precise opening and closing actions within the preset temperature range.

[0082] S2: 3D Model Construction. Using computer-aided design (CAD) software, based on the determined linkage deformation scheme, a refined three-dimensional linkage model of the light-shielding plate 3 and the stretching and contraction mechanism is constructed. The model needs to include the dimensional parameters of each component, the connection method, and the trigger point of the shape memory effect, so as to provide accurate data support for subsequent additive manufacturing.

[0083] S3: Additive manufacturing. Using metal 3D printing technology, based on the 3D model constructed in step S2, shape memory alloy powder is integrally printed into a structural component with intelligent response function, ensuring the consistency of the structure's mechanical properties and phase transformation.

[0084] S4: Heat treatment and shape memory setting. The printed overall structure undergoes stepped heat treatment (including solution treatment, aging treatment, etc.) to eliminate internal stress generated during printing; at the same time, through shape constraint and release at a specific heating temperature, the initial memory shape, target recovery shape and response temperature threshold of the structure are set to ensure stable shape transformation under preset temperature excitation;

[0085] S5: Integrated Assembly and Functional Verification. The molded structure processed in step S4 is precisely assembled into the spacecraft window system. The extreme temperature difference environment of alternating high temperature on the sun-facing side and low temperature on the shaded side in space is simulated to test the opening and closing response speed, repeated operation stability, and extreme condition tolerance of the shading mechanism, thus verifying the actual application performance of the device.

[0086] In some specific implementations, the self-opening and closing shading mechanism is installed in a modular assembly to meet the shading area requirements and is integrated with the spacecraft observation window to form a shading mechanism that automatically responds to changes in the direction of solar illumination.

[0087] Among them, the light-shielding plate 3, the torsion spiral component 11, and the telescopic spiral component 801 are made of NiTi50 spherical powder with a particle size of 15-53μm, and are printed by selective laser melting (SLM) technology.

[0088] In some specific embodiments, the light-shielding plate 3 is designed as a square hollow structure (thickness 0.8mm, diameter 300mm), the laser power is 200W, the scanning speed is 800mm / s, and the layer thickness is 30μm. After printing, it undergoes solution treatment at 800℃ for 1h + aging treatment at 400℃ for 2h. The initial memory shape is set to a fully unfolded state (0° angle with the horizontal plane), and the target restored shape is a closed state (90° angle with the horizontal plane).

[0089] In some specific embodiments, the drive shaft 1 is formed into a left-handed helical structure. The two ends of the torsion helical component 11 are respectively machined with inward and outward folds, and are subjected to a setting treatment at 600°C for 30 minutes to ensure that a torsional force of 0.5 N·m is generated when the temperature exceeds 80°C.

[0090] In some specific embodiments, the telescopic spiral component 802 is designed as a cylindrical compression spring (free length 50mm, diameter 12mm). Through temperature gradient aging treatment (300-500℃ step temperature increase), it is set to extend to 65mm at -10℃ and contract to 35mm at 60℃, with a maximum thrust / tension of 80N.

[0091] In some specific embodiments, the drive shaft 1, driven shaft 2, and fixed frame 4 are made of GH3625 high-temperature alloy and are formed by CNC machining; the base 402 and the housing 401 are connected by electron beam welding; the slide rail 7 and positioning rod 5 are made of TC4 titanium alloy and the surface is anodized to improve wear resistance.

[0092] In some specific embodiments, the drive shaft 1 is installed as follows: the torsion screw 11 is fitted into the shaft of the drive shaft 1, the inner folded end is inserted into the pin hole of the shaft, the outer folded end is embedded in the pin hole of the housing 401, and the outer side of the housing 401 is sealed with a titanium alloy cap to ensure that there is no particulate contamination in a vacuum environment.

[0093] In some specific embodiments, the drive ring 6 is combined with the slide rail 7: two drive rings 6 are configured, with their square drive holes 601 matching the torsion column of the drive shaft 1 at a 15° rotation angle, and the sliding holes 602 fitting with the slide rail 7 with clearance, ensuring smooth sliding within a straightness range of ±0.1mm.

[0094] In some specific embodiments, the telescopic mechanism is connected as follows: the positioning ring 9 is locked onto the positioning rod 5 by an M4 positioning pin; the telescopic spiral 802 passes through the sliding sleeve 801, and its two ends are fixed to the connecting hole 603 of the drive ring 6 and the positioning ring 9 by hooks 901. Finally, the two sets of semi-circular light-shielding plates 3 are fixed onto the driven shaft 2 by tenons, completing the overall integration.

[0095] In some specific implementations, during the temperature control response test, a simulated space environment (-60℃ to +180℃) test is conducted: when the temperature rises from 20℃ to 180℃ (sunny side condition), the telescopic spiral 802 contracts by 18mm, the drive shaft 1 twists by 30°, and the light-shielding plate 3 is completely closed within 12s.

[0096] In some specific implementations, when the temperature drops from 60°C to -30°C (shaded side condition), the torsion screw 11 resets and drives the drive shaft 1 to rotate in the opposite direction, and the light shield 3 is fully opened.

[0097] This embodiment combines NiTi50 shape memory alloy with additive manufacturing technology to achieve intelligent shading function without motor drive. Compared with traditional mechanisms, the number of parts is reduced and the weight is lighter, providing an efficient solution for the adaptability of spacecraft to extreme thermal environments.

[0098] The light-shielding mechanism's light-shielding plate 3, telescopic screw 802, and torsion screw 11 are all made of shape memory alloy material with temperature-controlled response capabilities, and are integrated into a single unit using structural design and additive manufacturing (3D printing) 4D printing technology. This device is installed on the exterior of a spacecraft or capsule window. By responding to temperature changes, the light-shielding plate 3 automatically closes in sunlight and automatically opens in backlight or no-light conditions, maintaining a semi-open state under normal conditions to balance light shading and observation needs. This invention effectively solves the technical problems of existing window light-shielding mechanisms, such as slow response, complex structure, and susceptibility to damage, improving the intelligence and reliability of spacecraft and possessing broad engineering application prospects.

[0099] The above description of the embodiments is provided to enable those skilled in the art to understand and use the invention. It will be apparent to those skilled in the art that various modifications can be made to these embodiments, and the general principles described herein can be applied to other embodiments without inventive effort. Therefore, the present invention is not limited to the above embodiments, and any improvements and modifications made by those skilled in the art based on the disclosure of the present invention without departing from the scope of the invention should be within the protection scope of the present invention.

Claims

1. A spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy, characterized in that, It includes a fixed frame (4), a drive shaft (1) rotatably mounted on the fixed frame (4), a drive ring (6) slidably mounted on the drive shaft (1), a light shield (3) fixedly mounted on the drive shaft (1), and a telescopic drive mechanism (8) located between the fixed frame (4) and the drive ring (6); The telescopic drive mechanism (8) includes a sliding sleeve (801) and a telescopic spiral component (802) disposed in the sliding sleeve (801); the two ends of the sliding sleeve (801) are respectively connected to the fixed frame (4) and the drive ring (6); the telescopic spiral component (802) is a shape memory alloy spiral component, and its two ends are respectively connected to the two ends of the sliding sleeve (801); The drive shaft (1) is in the shape of a torsion prism. The inner hole shape of the drive ring (6) matches the cross-sectional shape of the drive shaft (1) and is fitted onto the drive shaft (1) in a conformal sliding manner to achieve a limiting sliding fit. This allows the telescopic spiral (802) to extend and retract when heated or cooled, and drive the drive ring (6) to slide along the drive shaft (1), thereby driving the drive shaft (1) to rotate and causing the light shield (3) to flip synchronously.

2. The spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy according to claim 1, characterized in that, The drive shaft (1) has rotating shafts (102) at both ends; the fixed frame (4) has a rotating shaft seat that supports the rotating shaft (102).

3. The spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy according to claim 2, characterized in that, A torsion helical component (11) is sleeved on the rotating shaft (102). The torsion helical component (11) is a shape memory alloy component, which is used to apply torque to assist the rotation of the drive shaft (1) when heated.

4. The spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy according to claim 3, characterized in that, The torsion helical component (11) is a shape memory alloy helical component, with one end fixed to the rotating shaft (102) and the other end fixedly connected to the rotating shaft seat.

5. The spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy according to claim 1, characterized in that, The drive shaft (1) is provided with a support frame (101) arranged in parallel, and a driven shaft (2) is provided between the support frames (101); one side of the light shield (3) is fixedly connected to the driven shaft (2).

6. The spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy according to claim 3, characterized in that, The drive shaft (1) is a quadrangular prism that twists around the axis of rotation, and the drive ring (6) is correspondingly a conformal square shape.

7. The spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy according to claim 3, characterized in that, The pivot seat includes a housing (401) for accommodating the pivot and having an opening, and a cover (12) provided at the opening.

8. The spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy according to claim 4, characterized in that, The fixing frame (4) includes bases (402) arranged side by side, and the rotating shaft seat is disposed on the corresponding base (402); The base (402) is provided with a positioning rod (5) and a slide rail (7) arranged side by side; One end of the sliding sleeve (801) is provided with a positioning ring (9), which is detachably fixed on the positioning rod (5); the other end is provided with a sliding block, which is slidably mounted on the slide rail (7).

9. A method for manufacturing a spacecraft self-opening and closing light-shielding mechanism based on any one of claims 1 to 8, characterized in that, The method includes the following steps: S1: Plan the linkage deformation path of the light shield (3), telescopic screw (802), and torsion screw (11), and verify the deformation coordination under different temperature ranges through experiments to ensure that the structure can achieve precise opening and closing actions within the preset temperature range. S2: Based on the linkage deformation path planning, construct a three-dimensional linkage model of the light shield (3) and the telescopic drive mechanism (8). The model includes the size parameters, connection method and shape memory effect trigger point of each component. S3: Using metal 3D printing technology, based on the three-dimensional linkage model constructed in step S2, shape memory alloy powder is integrated into a structural component with thermal response function to ensure the mechanical properties and phase transformation consistency of the structure. S4: Perform stepped heat treatment on the printed overall structure to eliminate internal stress generated during printing; at the same time, through shape constraint and release at heating temperature, set the initial memory shape, target recovery shape and response temperature threshold of the structure to ensure stable shape transformation under preset temperature excitation. S5: The molded structure processed in step S4 is precisely assembled into the spacecraft window system to simulate the extreme temperature difference environment of alternating high temperature on the sun-facing side and low temperature on the shaded side in space. The opening and closing response speed, repeated operation stability and extreme working condition tolerance of the shading mechanism are tested to verify the actual application performance of the device.

10. The method for preparing a spacecraft self-opening and closing light-shielding mechanism based on shape memory alloy according to claim 9, characterized in that, The self-opening and closing light-blocking mechanism is integrated with the spacecraft's observation window.

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