A design method for a solar panel device of a sun-synchronous orbit satellite and a solar panel device designed by using this method

Abstract

The present invention discloses a design method for a solar panel device of a sun-synchronous orbit satellite and a solar panel device designed by using this method, belonging to the technical field of satellite solar panels, and solving the problems of difficult attitude adjustment of existing solar panels, high manufacturing cost and long development cycle. The method of the present invention includes: establishing a satellite body coordinate system, which coincides with the orbital coordinate system; making the rotation axis of the solar panel coincide with the rotation axis of the solar vector; calculating the angle β between the solar vector and the orbital plane; according to the angle β, obtaining the angle α between the normal line of the solar panel and the rotation axis of the solar panel, and the angle α and the angle β are complementary angles; designing the solar panel device according to the angle α. The present invention is applicable to the design of solar panel devices of remote sensing satellites with unchanged attitudes.

Description

Technical Field

[0001] This application relates to the technical field of satellite solar panels, and particularly to a design method for a solar panel device of a sun-synchronous orbit satellite and a solar panel device designed by using this method. Background Art

[0002] The solar panels of existing sun-synchronous orbit satellites adopt a single-axis SADA (Solar Array Drive Assembly), and the rotation axis of the SADA is perpendicular to the normal of the solar panel. Then, the attitude control system of the satellite can be used to achieve sun-pointing.

[0003] Existing solar panels need to use a solar panel servo system to always point the solar cell array at the sun and the payload at the mission direction to ensure that sufficient energy is provided for the satellite system without interruption of the mission. Most existing single-axis solar panel drive devices use a motor servo system, including a stepper motor, a reducer, and a servo control system, to achieve real-time sun-pointing of the solar panel, that is: existing solar panels all require two-axis control to be able to track the sun.

[0004] For remote sensing satellites that need to maintain a constant attitude during mission execution, if existing solar panels are used, operations similar to laser link establishment are required, which is not convenient for attitude adjustment, the operation is complex, the manufacturing cost is very high, and the development cycle is long. Summary of the Invention

[0005] The purpose of the present invention is to solve the problems of difficult attitude adjustment, high manufacturing cost, and long development cycle of existing solar panels, and provide a design method for a solar panel device of a sun-synchronous orbit satellite and a solar panel device designed by using this method.

[0006] The present invention is realized through the following technical solutions. On the one hand, the present invention provides a design method for a solar panel device of a sun-synchronous orbit satellite, and the method includes:

[0007] Establish a satellite body coordinate system, and the satellite body coordinate system coincides with the orbital coordinate system;

[0008] Coincide the rotation axis of the solar panel with the rotation axis of the solar vector;

[0009] Calculate the angle β between the solar vector and the orbital plane;

[0010] According to the angle β, obtain the angle α between the normal of the solar panel and the rotation axis of the solar panel, and the angle α and the angle β are complementary angles;

[0011] Design the solar panel device according to the angle α.

[0012] Furthermore, the angle β between the solar vector and the orbital plane is an average value of the angles between the solar vector and the orbital plane corresponding to several time periods.

[0013] Furthermore, the time period is one year.

[0014] On the other hand, the present invention provides a solar sail panel device using the solar sail panel device design method for a sun-synchronous orbit satellite as described above, the device comprising: a solar sail panel, a solar sail panel driving device, a connecting rod and an angle locking device;

[0015] The connecting rod and the rotation axis of the solar sail panel are in the same straight line;

[0016] The angle locking device is used to connect the connecting rod and the solar sail panel, and the angle between the straight line where the connecting rod is located and the normal line of the solar sail panel is α;

[0017] The other end of the connecting rod is connected to the solar sail panel driving device, and the solar sail panel driving device is used to drive the solar sail panel to rotate.

[0018] Furthermore, the connecting rod is fixedly connected to the solar sail panel.

[0019] Furthermore, the solar panel driving device is single-axis.

[0020] The existing solar sail panel of the present invention adopts a new design concept, which overcomes the prejudice of the existing technology, so that it does not need to be driven by the dual-axis drive method of existing similar products, and has the advantages of simple driving and low cost:

[0021] 1. Aiming at the characteristics of remote sensing satellites with stable attitude, the present invention designs a new solar sail panel configuration in which the SADA axis is not perpendicular to the normal axis of the solar sail panel, so that orientation to the sun can be achieved without adjusting the attitude;

[0022] 2. The solar panel device of the present invention can achieve a utilization rate of more than 98% for solar energy. Under the premise of ensuring a high utilization rate of solar energy, the present invention is easy to operate and has a simple structure, and thus has a short research cycle; the original single-axis control system needs to cooperate with the attitude adjustment of the satellite body to achieve real-time solar orientation of the panel, but in view of some sun-synchronous orbit satellites that perform long-term earth orientation, it is not easy to achieve a higher solar energy utilization rate using traditional single-axis SADA.

[0023] 3. The solar panel device of the present invention can adopt a single-axis SADA, which can save a large amount of cost and improve reliability compared with a two-axis SADA. At present, existing single-axis SADAs are integrated with sun sensors and servo drive systems, which can achieve sun orientation in the current attitude. The present invention can achieve the basic functions of a two-axis SADA by combining the Beta angle with a single-axis SADA.

[0024] The design method of the solar panel device of the sun-synchronous orbit satellite of the present invention can guide new ideas for the design of solar panel devices. The present invention is applicable to the design of solar panel devices of remote sensing satellites with unchanged attitudes. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the present application, the drawings required for the implementation manners will be briefly introduced below. Obviously, for those of ordinary skill in the art, other drawings can also be obtained based on these drawings without creative efforts.

[0026] Figure 1 It is a schematic structural diagram of the solar panel device of the present invention;

[0027] Among them, 1 - solar panel; 2 - angle locking device; 3 - connecting rod; 4 - solar panel drive device; 5 - satellite body; 6 - satellite's ground load; 7 - satellite operating orbit. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0028] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present invention, but should not be construed as limiting the present invention.

[0029] Embodiment 1. As Figure 1 shown, a design method of a solar panel device of a sun-synchronous orbit satellite, the method includes:

[0030] Establish a satellite body coordinate system, which coincides with the orbit coordinate system;

[0031] Specifically, the coordinate system is defined as follows: This coordinate system is established on the basis of a circular orbit. The satellite body coordinate system is based on the illustration, that is, Xb points to the satellite's running speed direction, Zb points in the same direction as the ground load direction at the bottom of the satellite, and Yb is given by the right-hand rule. The orbit coordinate system VVLH (Vehicle Velocity, Local Horizontal) has its X-axis pointing to the orbit speed direction, its Z-axis pointing to the center of the earth, and its Y-axis perpendicular to the orbit plane direction given by the right-hand rule.

[0032] Since the attitude of some satellites needs to remain unchanged during mission execution, the orbital coordinate system VVLH (Vehicle Velocity, Local Horizontal) coincides with the body coordinate system (XbYbZb). Hereinafter, the body coordinate system is used to describe the satellite motion.

[0033] Align the axis of rotation of the solar panel with the axis of rotation of the solar vector.

[0034] The origin of the body coordinate system is at the center of the satellite. The X-axis points in the forward direction of the satellite, the Z-axis points to the bottom of the satellite, and the Y-axis is determined by the right-hand rule. Moreover, the X, Y, and Z axes of the orbital coordinate system are respectively in the same directions as the Xb, Yb, and Zb axes of the body coordinate system.

[0035] It should be noted that for a satellite in a sun-synchronous orbit, the motion of the solar vector in the body coordinate system within each orbital period is a conical surface in the body coordinate system, and the axis of the conical surface is collinear with the Yb axis of the body coordinate system. Let the angle between the solar vector and the orbital plane (XbObZb) be the β angle. If the axis of rotation of the solar panel is aligned with the axis of rotation of the solar vector, attitude coordination control will no longer be required.

[0036] Calculate the angle β between the solar vector and the orbital plane.

[0037] According to the angle β, obtain the angle α between the normal of the solar panel and the axis of rotation of the solar panel. The angle α is complementary to the angle β.

[0038] Design the solar panel device according to the angle α.

[0039] In this embodiment, based on the configuration of the solar panel where the plane of the solar panel and the plane of rotation of the solar panel are not coplanar, by changing the preset angle α between the normal of the solar panel and the axis of rotation to be complementary to the β angle (the angle between the solar vector and the orbital plane) on this orbit, that is, α + β = 90°, and performing solar tracking control on the SADA, it can be satisfied that the motion plane of the solar vector and the normal vector of the solar panel are parallel on the same orbital plane, so that the energy utilization rate of the sun reaches the highest.

[0040] Embodiment 2 further limits the method for designing the solar panel device of a sun-synchronous orbit satellite described in Embodiment 1. In this embodiment, the angle β between the solar vector and the orbital plane is further limited, specifically including: the angle β between the solar vector and the orbital plane is the average value of the angles between the solar vectors and the orbital planes corresponding to several time periods.

[0041] First, calculate the β angle of the sun-synchronous orbit and determine the angle between the solar panel and the axis of rotation based on the average β angle. to determine the angle between the solar panel and the axis of rotation.

[0042] Average β Angle Calculation Method:

[0043] First, input the relationship between the β angle and time within a period, denoted as:

[0044] β = f(t)

[0045] Then the average β angle is:

[0046]

[0047] where: t n is the time interval of a period, f(t n ) is the β angle at the nth moment, and k is the total number of samples of the β angle used.

[0048] It should be noted that since the included angle β will have errors over time, using the average value to determine the included angle β can improve the calculation accuracy of the included angle β, thereby improving the utilization rate of solar energy.

[0049] The said time period is one year.

[0050] It should be noted that selecting one year as the time period can meet the calculation accuracy of the included angle β without refinement, thereby reducing the complexity of data.

[0051] Embodiment 3. A solar panel device adopting the design method of a solar panel device of a sun-synchronous orbit satellite described in any one of Embodiment 1 and Embodiment 2, the device includes: a solar panel, a solar panel drive device, a connecting rod, and an angle locking device;

[0052] The connecting rod is on the same straight line as the solar panel rotation axis;

[0053] The angle locking device is used to connect the connecting rod and the solar panel, and the included angle between the straight line where the connecting rod is located and the normal line of the solar panel is α;

[0054] It should be noted that the rotation axis of the solar panel and the plane where the solar panel is located are not coplanar, that is, this axis intersects the solar panel surface, and the included angle size is equal to the included angle between the solar vector and the orbital plane.

[0055] The other end of the connecting rod is connected to the solar panel drive device, and the solar panel drive device is used to drive the solar panel to rotate.

[0056] Use a single-axis SADA to drive the solar panel of this configuration to achieve real-time orientation towards the sun.

[0057] The connecting rod is fixedly connected to the solar panel.

[0058] For attitude-stabilized satellites, since there is no need to adjust the attitude, the connecting rod can be fixedly connected to the solar panel, thereby reducing the manufacturing cost and complexity.

[0059] The solar panel drive device is single-axis.

[0060] In this embodiment, a single-axis solar panel drive device is sufficient, which can also reduce the complexity and cost of the device.

[0061] The structure needs to include a single-axis solar panel drive device, an angle locking device, and a solar panel. When necessary, a telescopic device for the connecting rod can be added, and its function is to reduce the envelope space and save volume.

[0062] Based on the properties of the sun-synchronous orbit, this embodiment proposes a design method for the solar panel configuration. By calculating the characteristics of different orbits, it maximally utilizes solar energy, uses a unified configuration, reduces the development cost, shortens the development cycle, and is applicable to the design and development of low-cost satellites. Using this configuration, the solar energy utilization rate can reach more than 98%, and a large amount of cost can be saved compared with the two-axis SADA, improving the reliability.

[0063] For a sun-synchronous orbit satellite with an orbital altitude of 500 km, when the local time of the descending node is 9 o'clock, considering the influence of the J2 earth gravitational potential, starting from 7Jan 202204:00:00 UTCG, the included angle between the solar vector and the Y-axis of the satellite body coordinate system is 134.4°. Within one year of the satellite, the β angle varies within the range of 36.4° to 48.8°. After calculating the average β angle, the α angle is selected to be 42.5°, and its annual average efficiency is above 99%.

Claims

1. A design method for the solar panel device of a sun-synchronous orbit satellite, characterized in that, The method includes: Establish a satellite body coordinate system, which coincides with the orbital coordinate system. The origin of the satellite body coordinate system is at the center of the satellite. The X-axis points in the forward direction of the satellite, the Z-axis points to the bottom of the satellite, and the Y-axis is determined by the right-hand rule. The X-axis of the orbital coordinate system points in the direction of the orbital velocity, the Z-axis points to the center of the earth, and the Y-axis is perpendicular to the orbital plane and determined by the right-hand rule; Align the rotation axis of the solar panel with the rotation axis of the solar vector, and the rotation axis of the solar vector is collinear with the Y-axis of the satellite body coordinate system; Calculate the angle β between the solar vector and the orbital plane; Based on the angle β, obtain the angle α between the normal of the solar panel and the rotation axis of the solar panel, and the angle α is complementary to the angle β; Design the solar panel device according to the angle α; The solar panel device includes: a solar panel, a solar panel drive device, a connecting rod, and an angle locking device; The connecting rod is on the same straight line as the rotation axis of the solar panel; The angle locking device is used to connect the connecting rod and the solar panel. The angle between the straight line where the connecting rod is located and the normal of the solar panel is α. The rotation axis of the solar panel intersects the solar panel surface, and the included angle is equal to the angle β between the solar vector and the orbital plane; The other end of the connecting rod is connected to the solar panel drive device, and the solar panel drive device is used to drive the solar panel to rotate; The connecting rod is fixedly connected to the solar panel; The solar panel drive device is single-axis.

2. The design method for the solar panel device of a sun-synchronous orbit satellite according to claim 1, characterized in that, The angle β between the solar vector and the orbital plane is the average value of the angles between the solar vectors and the orbital plane corresponding to several time periods; 3. The design method for the solar panel device of a sun-synchronous orbit satellite according to claim 2, characterized in that, The time period is one year.

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