A satellite sun tracking sensor driving device

Abstract

The present invention relates to a satellite sun-tracking sensing and driving device, belonging to the technical field of spacecraft control, and comprising a central rotating shaft body and a first driving assembly; the central rotating shaft body is used for connecting with the shaft body of the solar wing of the spacecraft; the first driving assembly includes a first shaft body, a first elastic element and a first shape memory alloy elastic element; the first shaft body is sleeved outside the central rotating shaft body and is coaxial with the central rotating shaft body; the first shaft body is used for connecting with the shell of the spacecraft; a first contact point is arranged on the first shaft body, and a second contact point is arranged on the central rotating shaft body; a first hollow through groove is formed in a partial area of the first shaft body, and a first moving light-shielding plate is arranged inside the first shaft body; the first moving light-shielding plate is used for blocking the sunlight irradiating the first shape memory alloy elastic element through the first hollow through groove within a set time. The present invention realizes the automatic sun-tracking of the solar wing, and reduces the overall structural complexity and cost.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft control, and particularly to a satellite sun-tracking sensing and driving device. Background Art

[0002] For a satellite operating in a spin or dual-spin stabilized mode, due to its spin, during one rotation of the satellite body, the built-in solar cells on the satellite receive direct sunlight only for a very short period of time. Calculated by the equivalent direct irradiation area, only 1 / π of the solar cells are working full-time. Therefore, the electric energy available for the payload of the satellite is less. With the development of large military satellites, meteorological satellites, and commercial broadcast communication satellites, the requirements for the attitude control accuracy of satellites are getting higher and higher, and the capacity requirements for the payload are getting larger and larger. To maximize the utilization rate of solar cells, a driving device is provided in the satellite. Its main mission is to drive the battery array to rotate and make its normal line coincide with the sunlight beam to obtain as much electric energy as possible.

[0003] The solar array drive mechanism is one of the essential components for the satellite solar wing to track the sun. However, currently, the mechanism using sensors and motor drives is heavy and complex in structure, greatly increasing the usage cost and threshold. Summary of the Invention

[0004] The purpose of the present invention is to provide a satellite sun-tracking sensing and driving device, which utilizes the contraction characteristics of a shape memory alloy elastic element to achieve automatic sun-tracking of the solar wing, reducing the overall structural complexity and cost.

[0005] To achieve the above purpose, the present invention provides the following solution:

[0006] A satellite sun-tracking sensing and driving device includes a central rotating shaft body and a first driving component;

[0007] The central rotating shaft body is used to connect with the shaft body of the solar wing of the spacecraft;

[0008] The first driving component includes a first shaft body, a first elastic element, and a first memory alloy elastic element; the first shaft body is sleeved outside the central rotating shaft body, and the first shaft body is coaxial with the central rotating shaft body; the first shaft body is used to connect with the shell of the spacecraft;

[0009] A first contact point is provided on the first shaft body, and a second contact point is provided on the central rotating shaft body. One end of the first elastic element and one end of the first memory alloy elastic element are respectively connected to the first contact point, and the other end of the first elastic element and the other end of the first memory alloy elastic element are respectively connected to the second contact point;

[0010] A partial area of the first shaft body is provided with a first hollow through groove, and a first moving light-shielding plate is arranged inside the first shaft body; the first moving light-shielding plate is used to block the sunlight irradiating the first shape memory alloy elastic element through the first hollow through groove within a set time;

[0011] During operation, the central rotating shaft body is connected to the shaft body of the solar wing of the spacecraft, and the first shaft body is connected to the shell of the spacecraft; when sunlight irradiates the first shape memory alloy elastic element through the first hollow through groove, the first shape memory alloy elastic element deforms and generates a contraction force to drive the central rotating shaft body to rotate in the positive direction, thereby driving the solar wing of the spacecraft to rotate in the positive direction, while stretching the first elastic element, and the first moving light-shielding plate starts to block the sunlight irradiating the first shape memory alloy elastic element through the first hollow through groove; when the first moving light-shielding plate completely blocks the first shape memory alloy elastic element, the first shape memory alloy elastic element deforms under the stretching action of the first elastic element to drive the central rotating shaft body to rotate in the reverse direction, thereby driving the solar wing of the spacecraft to rotate in the reverse direction.

[0012] Optionally, the first moving light-shielding plate includes a conveying guide rail and a light-shielding plate body;

[0013] An annular groove is provided on the first shaft body, and the conveying guide rail is arranged on the annular groove;

[0014] The light-shielding plate body is arranged on the conveying guide rail.

[0015] Optionally, the first contact point includes a cuboid boss and a cylinder boss;

[0016] The cuboid boss is arranged on the first shaft body, and the cylinder boss is arranged on the upper surface of the cuboid boss;

[0017] A transverse through hole is provided on the cylinder boss;

[0018] One end of the first shape memory alloy elastic element is fixed on the cylinder boss through the transverse through hole.

[0019] Optionally, the included angle between the first contact point and the second contact point in the radial direction of the central rotating shaft body is greater than a first set angle.

[0020] Optionally, the first shape memory alloy elastic element is a shape memory alloy spring;

[0021] The shape of the shape memory alloy spring is arc-shaped, and the preparation material of the shape memory alloy spring is Ti-Ni series shape memory alloy material.

[0022] Optionally, the first elastic element is a spring;

[0023] The shape of the spring is arc-shaped, and the preparation material of the spring is 60Si2Mn.

[0024] Optionally, the material of the first moving light-shielding plate is a thin carbon fiber composite material.

[0025] Optionally, the satellite sun-tracking sensing drive device further includes a second drive assembly;

[0026] The second drive assembly includes a second shaft body, a second elastic element, and a second shape memory alloy elastic element; the second shaft body is sleeved outside the central rotating shaft body, and the second shaft body is arranged at the upper end of the first shaft body;

[0027] A third contact point is further arranged on the central rotating shaft body; the third contact point is separated from the second contact point by a first set distance in the axial direction of the central rotating shaft body; a fourth contact point is arranged on the second shaft body, one end of the third contact point is respectively connected to one end of the second elastic element and one end of the second shape memory alloy elastic element, and the fourth contact point is respectively connected to the other end of the second elastic element and the other end of the second shape memory alloy elastic element;

[0028] A second hollow through groove is formed in a partial area of the second shaft body, and a second moving light-shielding plate is arranged inside the second shaft body; the second moving light-shielding plate is used for shielding the sunlight irradiating the second shape memory alloy elastic element through the second hollow through groove within a set time;

[0029] When the first moving light-shielding plate starts to shield the first shape memory alloy elastic element, the second moving light-shielding plate starts to move towards the second elastic element and reduces the shielding of the second shape memory alloy elastic element.

[0030] Optionally, the fourth contact point is at the same height as the third contact point, and the second contact point is at the same height as the first contact point;

[0031] The included angle between the third contact point and the fourth contact point in the radial direction of the central rotating shaft body is greater than the first set angle.

[0032] According to the specific embodiments provided by the present invention, the following technical effects are disclosed by the present invention:

[0033] The present invention provides a satellite sun-tracking sensing and driving device. During operation, the central rotating shaft body is connected to the shaft body of the solar wing of the spacecraft, and the first shaft body is connected to the housing of the spacecraft. Initially, the first shape memory alloy elastic element is irradiated by all the sunlight passing through the first hollow through slot, receives the heat of the light, shrinks at high temperature to restore its initial shape, drives the central rotating shaft body to rotate in the positive direction, and thus drives the solar wing of the spacecraft to rotate in the positive direction, that is, realizes the sun-tracking of the solar wing. Since the first elastic element and the first shape memory alloy elastic element are both arranged at the same position, when the first shape memory alloy elastic element shrinks, it will stretch the first elastic element. During the movement of the satellite, the first moving light-shielding plate moves to block the sunlight irradiating the first shape memory alloy elastic element through the first hollow through slot. When the first moving light-shielding plate completely blocks the sunlight, the first shape memory alloy elastic element is in a low-temperature environment. At this time, driven by the contraction of the first elastic element, the first shape memory alloy elastic element stretches and drives the central rotating shaft body to rotate in the reverse direction, thereby driving the solar wing of the spacecraft to rotate in the reverse direction and continue to track the sun.

[0034] The present invention utilizes the self-characteristics of the shape memory alloy SMA material to realize the driving of the solar wing, without using a motor. On the one hand, it improves the energy utilization rate, and on the other hand, the structure is simple, reducing the total weight of the spacecraft and improving the economic benefits. Brief Description of the Drawings

[0035] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0036] Figure 1 It is a schematic structural diagram of the satellite sun-tracking sensing and driving device of the present invention;

[0037] Figure 2 It is a 3D schematic structural diagram of the satellite sun-tracking sensing and driving device of the present invention.

[0038] Symbol Description:

[0039] 1 - Spacecraft, 21 - First shaft body, 22 - Second shaft body, 31 - First elastic element, 32 - Second elastic element, 4 - Central rotating shaft body, 51 - First shape memory alloy elastic element, 52 - Second shape memory alloy elastic element, 61 - First moving light-shielding plate, 62 - Second moving light-shielding plate. Detailed Embodiment

[0040] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0041] Considering the period of the spacecraft's rotation around the earth, the satellite sun-tracking sensing and driving device of the present invention uses the characteristic that the SMA material shrinks when heated to drive the solar wing to rotate. At the same time, with the assistance of a light-shielding plate and a common spring, the reverse rotation of the solar panel is realized, achieving semi-range sun orientation. On this basis, using two sets of driving components can achieve full-range sun orientation. The present invention uses the shape memory alloy SMA as a mechanism element that integrates sensing and driving, uses a light-shielding plate to control the temperature inside the mechanism, and uses a restoring spring to assist in realizing reverse rotation, obtaining the characteristics of small mass, simple structure, and simple control, and having broad application prospects in the future.

[0042] To make the objectives, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0043] Shape memory alloy (SMA) refers to certain alloys whose crystal structure changes regularly with temperature in the solid state. When the external temperature changes above and below its transformation temperature, the shape memory alloy will shrink or expand. Due to the advantages of simple structure and light weight of the shape memory alloy, it has broad application prospects in the fields of clinical medicine and aerospace. In the aerospace field, shape memory alloys are used to drive satellite antenna deployment mechanisms, space unlocking devices, etc. Using shape memory alloys for driving can effectively reduce the structural complexity and the weight of the satellite.

[0044] As Figure 1 and Figure 2 shown, this embodiment provides a satellite sun-tracking sensing and driving device, including a central rotating shaft body 4 and a first driving component; the central rotating shaft body 4 is used to connect with the shaft body of the solar wing of the spacecraft 1; the first driving component includes a first shaft body 21, a first elastic element 31, and a first memory alloy elastic element 51; the first shaft body 21 is sleeved outside the central rotating shaft body 4, and the first shaft body 21 is coaxial with the central rotating shaft body 4; the first shaft body 21 is used to connect with the shell of the spacecraft 1.

[0045] Among them, the first shape memory alloy elastic element 51 is a shape memory alloy spring; the shape of the shape memory alloy spring is arc-shaped, and the preparation material of the shape memory alloy spring is a Ti-Ni series shape memory alloy material. The first elastic element 31 is a spring; the shape of the spring is arc-shaped, and the preparation material of the spring is 60Si2Mn.

[0046] A first contact point is provided on the first shaft body 21, and a second contact point is provided on the central rotating shaft body 4. The first contact point is respectively connected to one end of the first elastic element 31 and one end of the first shape memory alloy elastic element 51, and the second contact point is respectively connected to the other end of the first elastic element 31 and the other end of the first shape memory alloy elastic element 51, and the included angle between the first contact point and the second contact point in the radial direction of the central rotating shaft body is greater than a first set angle. Specifically, the first set angle is 180°, and the first set angle can also be set to an angle greater than 180° according to actual needs. If the first set angle is too small, it may cause the contraction amount of the first shape memory alloy elastic element to be insufficient when contracting, so that the solar panel on the solar wing cannot face the sun directly.

[0047] Further, the first contact point includes a cuboid boss and a cylinder boss; the cuboid boss is arranged on the inner wall of the first shaft body 21, and the cylinder boss is arranged on the upper surface of the cuboid boss; a transverse through hole is provided on the cylinder boss. One end of the first shape memory alloy elastic element 51 is fixed on the cylinder boss through the transverse through hole, and one end of the first elastic element 31 is also fixed on the cylinder boss through the transverse through hole.

[0048] The specific setting of the second contact point is the same as the above specific setting of the first contact point, and the difference is that the cuboid boss of the second contact point is arranged on the outer wall of the central rotating shaft body 4. Further, the second contact point is at the same height as the first contact point, that is, the cuboid boss in the first contact point is at the same height as the cuboid boss in the second contact point, and the included angle between the cuboid boss in the first contact point and the cuboid boss in the second contact point in the radial direction of the central rotating shaft body is at least 180 degrees.

[0049] A first hollow through groove is formed in a partial area of the first shaft body 21, and a first moving light-shielding plate 61 is arranged inside the first shaft body 21; the first moving light-shielding plate 61 is used for shielding the sunlight irradiating the first shape memory alloy elastic element 51 through the first hollow through groove within a set time. The first moving light-shielding plate 61 includes a conveying guide rail and a light-shielding plate body; an annular groove is formed in the first shaft body, and the conveying guide rail is arranged on the annular groove; the light-shielding plate body is arranged on the conveying guide rail, and when the light-shielding plate body moves on the conveying guide rail, the radius of its moving track is slightly larger than the inner diameter of the inner wall of the first shaft body. In addition, the light-shielding plate body is an arc-shaped curved plate. The material of the light-shielding plate body is a carbon fiber composite thin plate to ensure that the heat generated by solar radiation is controllable.

[0050] In a specific embodiment, the first shaft body 21 is divided into two symmetrical parts, one part is hollowed out to form a hollow through groove, an annular groove is formed inside the other part, a conveying guide rail is arranged at the bottom of the annular groove, and the light-shielding plate body is arranged on the conveying guide rail.

[0051] In the initial position, the arc-shaped shape memory alloy spring is stationary and arranged opposite to the hollow through groove. One end of the arc-shaped shape memory alloy spring is arranged in the transverse through hole of the cylindrical boss on the inner wall of the first shaft body 21, and the other end of the arc-shaped shape memory alloy spring is arranged in the transverse through hole of the cylindrical boss on the outer wall of the central rotating shaft body 4. Correspondingly, the arc-shaped spring is symmetrically arranged with the arc-shaped shape memory alloy spring, and in the initial position, the light-shielding plate body is arranged in the annular groove, and at this time, the position of the arc-shaped spring is opposite to the position of the light-shielding plate body.

[0052] During operation, the central rotating shaft body 4 is connected to the shaft body of the solar wing of the spacecraft 1, and the first shaft body 21 is connected to the housing of the spacecraft 1. At this time, the first shape memory alloy elastic element is in the spring state after deformation, and the light-shielding plate body is fully opened, and the solar wing is then facing the sun directly. When sunlight passes through the first hollow through groove and irradiates the first shape memory alloy elastic element 51, when the temperature of the first shape memory alloy elastic element 51 reaches the transformation temperature, the first shape memory alloy elastic element 15 returns to its initial state and generates a contraction force at the same time, so as to drive the central rotating shaft body 4 to rotate in the positive direction, thereby driving the solar wing of the spacecraft 1 to rotate in the positive direction and track the sunlight. The contraction force generated by the first shape memory alloy elastic element 51 will stretch the first elastic element 31. At the same time, the first movable light-shielding plate starts to block the sunlight irradiating the first shape memory alloy elastic element 51 through the hollow through groove at a set speed. When the satellite moves to the position closest to the sun, the light-shielding plate completely blocks the sunlight irradiating the first shape memory alloy elastic element 51, the internal temperature decreases, the first elastic element 31 reaches the stretching limit and starts to contract, and drives the first shape memory alloy elastic element 51 to change its shape (return to its spring shape state) in a low-temperature environment. At the same time, under the action of the first elastic element, the central rotating shaft body rotates in the reverse direction, thereby driving the solar wing of the spacecraft to rotate in the reverse direction and still facing the sun directly. Specifically, the positive direction is set to be clockwise, and the reverse direction is set to be counterclockwise; or, the positive direction is set to be counterclockwise, and the reverse direction is set to be clockwise.

[0053] Preferably, the satellite solar tracking sensing and driving device further includes a second driving component; the second driving component includes a second shaft body 22, a second elastic element 32 and a second shape memory alloy elastic element 52; the second shaft body 22 is sleeved outside the central rotating shaft body 4, and the second shaft body 22 is arranged at the upper end of the first shaft body 21.

[0054] A third contact point is further arranged on the central rotating shaft body 4; the third contact point and the second contact point are separated by a first set distance in the axial direction of the central rotating shaft body 4; a fourth contact point is arranged on the second shaft body, and the third contact point is respectively connected to one end of the second elastic element 32 and one end of the second shape memory alloy elastic element 52, and the fourth contact point is respectively connected to the other end of the second elastic element 32 and the other end of the second shape memory alloy elastic element 52.

[0055] The fourth contact point and the third contact point are at the same height, and the included angle between the third contact point and the fourth contact point in the radial direction of the central rotating shaft body 4 is greater than the first set angle.

[0056] Part of the second shaft body 22 is provided with a second hollow through groove, and a second movable light-shielding plate 62 is arranged inside the second shaft body 22; the second movable light-shielding plate 62 is used to block the sunlight irradiating the second shape memory alloy elastic element 32 through the second hollow through groove within a set time.

[0057] The internal setting of the second driving assembly is the same as that of the first driving assembly, and the second hollow through groove formed on the second shaft body 22 in the second driving assembly is vertically opposite to the first hollow through groove formed on the first shaft body 21. In the initial working state, the light-shielding plate body of the second movable light-shielding plate is not arranged on its corresponding conveying track, but has moved to the second hollow through groove and completely blocks the sunlight irradiating the second shape memory alloy elastic element through the second through groove, as specifically shown in Figure 2 shown.

[0058] When the first movable light-shielding plate starts to block the first shape memory alloy elastic element, the second movable light-shielding plate starts to move towards the second elastic element and reduces the shielding of the second shape memory alloy elastic element, so that when the first movable light-shielding plate completely blocks the first shape memory alloy elastic element, the second movable light-shielding plate is completely opened and there is no shielding for the second elastic element. Specifically, the start time and moving speed of the first movable light-shielding plate, and the start time and moving speed of the second movable light-shielding plate can all be set by a preset controller.

[0059] In a specific application, the specific working process of the satellite sun-tracking sensing driving device of the present invention is as follows:

[0060] 1) In the initial state, since the light-shielding plate in the first driving assembly is completely opened, the SMA spring is heated by solar radiation and its temperature rises. Under high temperature conditions, it contracts to restore its initial shape, and the SMA spring drives the central rotating shaft body to rotate, making the solar panel face the sunlight. At this time, when the satellite starts to move in the earth orbit, the light-shielding plate body blocks the sunlight at a set speed.

[0061] 2) When the overall light-receiving surface of the satellite reaches the maximum position, the light-shielding plate body is completely closed and the temperature drops. At this time, the shape memory alloy spring returns to the spring-shaped deformation state under the driving of the contraction elastic force of the ordinary spring body, and at the same time drives the central rotating shaft body to rotate in the reverse direction to ensure that the solar panel faces the sunlight. At this time, the half-course sun orientation is completed.

[0062] 3) During the process of the light-shielding plate body in the first driving component closing, the light-shielding plate body in the second driving component gradually opens; after the first driving component completes a half-course orientation towards the sun and stops working, when the second driving component starts to move, the second driving component drives the fixed shaft body to move in the opposite direction, realizing the sun wing's tracking towards the sun and completing a cycle of movement (the movement process of the second driving component is basically the same as that of the first driving component), that is, the full-course orientation towards the sun is completed through the coordinated work of the first driving component and the second driving component.

[0063] Compared with the prior art, the present invention also has the following advantages:

[0064] (1) The present invention completely relies on mechanical system control and can realize the sensing drive for sun tracking without other motors and sensors, greatly reducing the control difficulty and usage threshold, solving the problem of large volume and mass caused by the prior art, and being beneficial to the integration and lightweight of the entire control system. Moreover, through the flexible steady-state mechanism and the energy during the actuation process of the shape memory alloy spring for solar radiation heat energy regulation, continuous reciprocating motion is achieved, improving the reliability of the control system.

[0065] (2) The present invention can adjust the output of the actuating force by adjusting the size parameters of the shape memory alloy spring, enabling the present invention to have high adaptability.

[0066] (3) The present invention can adjust the actuation frequency of the actuation system within a certain range by adjusting the movement speed of the light-shielding plate body, having high versatility.

[0067] In this specification, each embodiment is described in a progressive manner. The key point of each embodiment is to illustrate the differences from other embodiments. For the same and similar parts among the embodiments, reference can be made to each other.

[0068] In this article, specific examples are used to elaborate on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, based on the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A satellite sun-tracking sensing and driving device, characterized in that The satellite sun-tracking sensing and driving device includes a central rotating shaft body, a first driving component and a second driving component; The central rotating shaft body is used for connecting with the shaft body of the solar wing of the spacecraft; The first driving component includes a first shaft body, a first elastic element and a first shape memory alloy elastic element; the first shaft body is sleeved outside the central rotating shaft body, and the first shaft body is coaxial with the central rotating shaft body; the first shaft body is used for connecting with the shell of the spacecraft; A first contact point is arranged on the first shaft body, and a second contact point is arranged on the central rotating shaft body. One end of the first elastic element and one end of the first shape memory alloy elastic element are respectively connected to the first contact point, and the other end of the first elastic element and the other end of the first shape memory alloy elastic element are respectively connected to the second contact point; A first hollow through groove is formed in a partial area of the first shaft body, and a first moving light-shielding plate is arranged inside the first shaft body; the first moving light-shielding plate is used for shielding the sunlight irradiating the first shape memory alloy elastic element through the first hollow through groove within a set time; the first moving light-shielding plate includes a conveying guide rail and a light-shielding plate body; a circular groove is formed in the first shaft body, and the conveying guide rail is arranged on the circular groove; the light-shielding plate body is arranged on the conveying guide rail; The second driving component includes a second shaft body, a second elastic element and a second shape memory alloy elastic element; the second shaft body is sleeved outside the central rotating shaft body, and the second shaft body is arranged at the upper end of the first shaft body; a second hollow through groove is formed in a partial area of the second shaft body, and a second moving light-shielding plate is arranged inside the second shaft body; the second moving light-shielding plate is used for shielding the sunlight irradiating the second shape memory alloy elastic element through the second hollow through groove within a set time; When the first moving light-shielding plate starts to shield the first shape memory alloy elastic element, the second moving light-shielding plate starts to move towards the second elastic element and reduces the shielding of the second shape memory alloy elastic element; During operation, the central rotating shaft body is connected to the shaft body of the solar wing of the spacecraft, and the first shaft body is connected to the shell of the spacecraft; when sunlight irradiates the first shape memory alloy elastic element through the first hollow through groove, the first shape memory alloy elastic element deforms and generates a contraction force to drive the central rotating shaft body to rotate in the positive direction, thereby driving the solar wing of the spacecraft to rotate in the positive direction, and at the same time stretching the first elastic element, and the first moving light-shielding plate starts to shield the sunlight irradiating the first shape memory alloy elastic element through the first hollow through groove; when the first moving light-shielding plate completely shields the first shape memory alloy elastic element, the first shape memory alloy elastic element deforms under the stretching action of the first elastic element to drive the central rotating shaft body to rotate in the reverse direction, thereby driving the solar wing of the spacecraft to rotate in the reverse direction.

2. The satellite sun-tracking sensing and driving device according to claim 1, characterized in that, The first contact point includes a cuboid convex platform and a cylinder convex platform; The cuboid boss is arranged on the first shaft body, and the cylindrical boss is arranged on the upper surface of the cuboid boss; A transverse through hole is formed in the cylindrical boss; One end of the first shape memory alloy elastic element is fixed on the cylindrical boss through the transverse through hole.

3. The satellite sun-tracking sensing and driving device according to claim 1, characterized in that The included angle between the first contact point and the second contact point in the radial direction of the central rotating shaft body is greater than a first set angle.

4. The satellite sun-tracking sensing and driving device according to claim 1, characterized in that The first shape memory alloy elastic element is a shape memory alloy spring; The shape of the shape memory alloy spring is arc-shaped, and the preparation material of the shape memory alloy spring is a Ti-Ni based shape memory alloy material.

5. The satellite sun-tracking sensing and driving device according to claim 1, characterized in that The first elastic element is a spring; The shape of the spring is arc-shaped, and the preparation material of the spring is 60Si2Mn.

6. The satellite sun-tracking sensing and driving device according to claim 1, characterized in that, The material of the first moving light-shielding plate is a carbon fiber composite thin plate.

7. The satellite sun-tracking sensing and driving device according to claim 1, wherein, A third contact point is further arranged on the central rotating shaft body; the third contact point and the second contact point are separated by a first set distance in the axial direction of the central rotating shaft body; a fourth contact point is arranged on the second shaft body, the third contact point is respectively connected with one end of the second elastic element and one end of the second shape memory alloy elastic element, and the fourth contact point is respectively connected with the other end of the second elastic element and the other end of the second shape memory alloy elastic element.

8. The satellite sun-tracking sensing and driving device according to claim 7, wherein, The fourth contact point is at the same height as the third contact point, and the second contact point is at the same height as the first contact point; The included angle between the third contact point and the fourth contact point in the radial direction of the central rotating shaft body is greater than a first set angle.

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