A method and system for designing an offset solar wing configuration for an inclined orbit satellite

Abstract

The present invention provides a method and system for designing an offset solar wing configuration for an inclined orbit satellite, comprising: step S1: determining the power of the satellite platform, the size of the solar wing mounting surface, and the carrying envelope; step S2: obtaining the range of the solar altitude angle of the satellite's orbit; step S3: calculating the fixed offset angle of the solar wing and the area of ​​the solar wing substrate; step S4: selecting a suitable solar wing configuration; step S5: under the constraint that the solar wing SADA drive axis passes through the center of mass of the solar wing substrate, calculating the root hinge deployment angle of the solar wing configuration based on the solar wing offset angle, and selecting a solar wing configuration with a root hinge deployment angle greater than 30°; step S6: calculating the shielding area of ​​the solar wing body from the satellite body when the solar altitude angle is maximum; step S7: increasing the solar wing substrate area by an amount equal to the shielding area, and repeating steps S4 and S5 to obtain a solar wing configuration that meets the requirements. The present invention optimizes the solar wing design and significantly improves the light energy utilization efficiency of solar wing configurations on inclined orbits.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a method and system for designing a biased solar wing configuration for an inclined orbit satellite. Background Art

[0002] With the rapid development of aerospace technology, the demand for global observation in areas such as environmental monitoring and scientific exploration is growing. Many missions have proposed the advantages of using inclined orbits for global observation. As we all know, a difficult problem facing inclined orbit satellites is the poor lighting conditions on their solar panels.

[0003] Since the angle between the sun vector and the orbital plane on an inclined orbit changes widely within a year, the traditional solar wing configuration has low efficiency in utilizing light energy. In order to meet the electricity demand, it is necessary to add sail panels, which not only reduces the satellite's mass-to-load ratio, but is also not conducive to engineering implementation and cannot meet the mission requirements.

[0004] In the paper "A satellite biased solar wing adapted to different descending node locations" (patent number: ZL200820078863.0) published by Cui Yufu, Li Linlin, Li Taowei and others, it is mentioned that the solar wing offset can be achieved by adjusting the angle of the hinge between the first plates, thereby improving the energy shortage problem of the entire satellite. However, this method only introduces the specific operating means of the solar wing offset, and does not involve the design principles and methods of the offset solar wing.

[0005] In the paper "Assembly and Deployment Test of Offset Solar Wings" published in Aerospace Manufacturing Technology in 2010 by Yao Jun, Wu Yuanbo, Wu Yueying and others, the deployment test principles and assembly process plan of offset solar wings were mentioned, but the design principles and methods of offset solar wings were not involved. Summary of the Invention

[0006] In view of the defects in the prior art, the purpose of the present invention is to provide a method and system for designing the offset solar wing configuration of an inclined orbit satellite.

[0007] According to the present invention, a method for designing an offset solar panel configuration for an inclined orbit satellite includes:

[0008] Step S1: Determine the power, solar panel mounting surface size, and carrying envelope of the satellite platform based on the overall mission requirements;

[0009] Step S2: Obtain the solar altitude angle variation range of the satellite's orbit;

[0010] Step S3: Calculating the fixed offset angle of the solar wing and the area of ​​the solar wing substrate according to the variation range of the solar altitude angle and the power of the satellite platform;

[0011] Step S4: Determine the number of solar wing substrates based on the area, installation location, and transport envelope of the solar wing substrates, and select a suitable solar wing configuration;

[0012] Step S5: Under the constraint that the solar wing SADA drive shaft passes through the center of mass of the solar wing baseplate, the root hinge deployment angle of the solar wing configuration is calculated in combination with the solar wing offset angle, and a solar wing configuration with a root hinge deployment angle greater than 30° is selected;

[0013] Step S6: Calculate the shielding area of ​​the satellite body to the solar wing body when the solar altitude angle is maximum;

[0014] Step S7: Increase the area of ​​the solar wing substrate to be equal to the shielding area, and repeat steps S4 and S5 to obtain a solar wing configuration that meets the requirements.

[0015] Preferably, in step S1, the solar wing body is installed on the north and south side panels of the satellite platform, the length of the solar wing bracket is 1896 mm, the installation surface size is: length * width = 2650 mm * 1650 mm, and the carrying envelope is Φ3850 mm.

[0016] Preferably, in step S2, the variation range of the solar altitude angle on the satellite's orbit is obtained by simulation calculation.

[0017] Preferably, in step S3, the fixed offset angle of the solar wing is half of the range of variation of the solar altitude angle.

[0018] Preferably, in step S4, the thickness of the solar wing substrate is 23 mm, the thickness of the solar wing bracket is 30 mm, the distance between the solar wing substrates after folding is 14.5 mm, the distance between the solar wing substrates and the solar wing bracket is 14.5 mm, and the distance between the solar wing bracket and the satellite platform side panel is 31.5 mm.

[0019] According to the present invention, a system for designing an offset solar panel configuration for an inclined orbit satellite includes the following modules:

[0020] Module M1: Determine the satellite platform power, solar panel mounting surface dimensions, and launch envelope based on overall mission requirements;

[0021] Module M2: Get the range of the solar altitude angle of the satellite's orbit;

[0022] Module M3: Calculates the fixed offset angle of the solar wing and the area of ​​the solar wing substrate according to the range of the solar altitude angle and the power of the satellite platform;

[0023] Module M4: Determine the number of solar wing substrates based on the solar wing substrate area, installation location, and transportation envelope, and select the appropriate solar wing configuration;

[0024] Module M5: Under the constraint that the solar wing SADA drive shaft passes through the center of mass of the solar wing baseplate, the root hinge deployment angle of the solar wing configuration is calculated in combination with the solar wing offset angle, and the solar wing configuration with a root hinge deployment angle greater than 30° is selected;

[0025] Module M6: Calculate the shielding area of ​​the satellite body to the solar wing body when the solar altitude angle is maximum;

[0026] Module M7: Increase the solar wing substrate area equal to the shielding area, repeat modules M4 and M5, and obtain a solar wing configuration that meets the requirements.

[0027] Preferably, in the module M1, the solar wing body is installed on the north and south side panels of the satellite platform, the length of the solar wing bracket is 1896 mm, the installation surface size is: length * width = 2650 mm * 1650 mm, and the carrying envelope is Φ3850 mm.

[0028] Preferably, in the module M2, the variation range of the solar altitude angle on the satellite's orbit is obtained through simulation calculation.

[0029] Preferably, in the module M3, the fixed offset angle of the solar wing is half of the range of variation of the solar altitude angle.

[0030] Preferably, in the module M4, the thickness of the solar wing substrate is 23 mm, the thickness of the solar wing bracket is 30 mm, the distance between the solar wing substrates after folding is 14.5 mm, the distance between the solar wing substrates and the solar wing bracket is 14.5 mm, and the distance between the solar wing bracket and the satellite platform side panel is 31.5 mm.

[0031] Compared with the prior art, the present invention has the following beneficial effects:

[0032] 1. The present invention optimizes the design of solar wings and significantly improves the light energy utilization efficiency of solar wings on inclined orbits. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0034] Figure 1 A flowchart of the steps of a method for designing an offset solar panel configuration for an inclined orbit satellite according to one embodiment of the present invention;

[0035] Figure 2 A schematic diagram of a folded solar wing according to an embodiment of the present invention;

[0036] Figure 3 A schematic diagram of the fixed-offset solar wing design provided in one embodiment of the present invention;

[0037] Figure 4A schematic diagram showing the centroid calculation principle of a straight-line solar wing substrate according to an embodiment of the present invention;

[0038] Figure 5 A schematic diagram showing the centroid calculation principle of a T-shaped solar wing substrate according to an embodiment of the present invention;

[0039] Figure 6 A schematic diagram showing the centroid calculation principle of a cross-shaped solar wing substrate according to an embodiment of the present invention.

[0040] Explanation of the accompanying numbers: 1. Solar wing body; 2. North side plate of the platform; 3. Solar wing base plate; 4. Solar wing bracket; 5. Solar wing SADA; 6. Center of mass of the solar wing base plate; 7. Primary deployment hinge; 8. Secondary deployment hinge. DETAILED DESCRIPTION

[0041] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0042] The present invention provides a method for designing an offset solar wing configuration for an inclined orbit satellite. By analyzing the range of solar altitude angle variation of the satellite's orbit, based on the given satellite platform power, combined with the solar wing installation position size and carrier envelope constraints, a solar wing configuration with engineering feasibility is designed to improve the efficiency of solar wing utilization of light energy on inclined orbits. Figure 1 , specifically including the following steps:

[0043] Step S1: According to the overall mission requirements, determine the power of the satellite platform, the size of the solar panel installation surface, and the carrying envelope; Figure 2 As shown, the solar wing body 1 is installed on the north and south side panels of the satellite platform. In this embodiment, the solar wing body 1 at the north side panel 2 of the platform is taken as an example. The center axis of the solar wing SADA 5 is 200mm away from the top plate of the satellite platform. The length of the solar wing bracket 4 is 1896mm. The installation surface size is: length * width = 2650mm * 1650mm, and the load envelope is Φ3850mm.

[0044] Step S2: Get the range of solar altitude angle variation in the satellite's orbit. Get the range of solar altitude angle variation in the satellite's orbit through simulation calculation. Input the satellite orbit parameters into STK. Simulate and calculate the variation pattern of the angle between the sun and the earth and the orbital plane over time within one year, and draw a curve.

[0045] Step S3: Calculate the fixed offset angle of the solar wing and the substrate area according to the variation range of the solar altitude angle and the satellite platform power; Figure 3 As shown, the fixed offset angle of the solar wing is half of the range of the solar altitude angle, and the area of ​​the solar wing substrate 3 A = P / (C*S*η*cos(β / 2)); where P is the satellite platform power, C is the layout coefficient of the solar wing substrate 3, S is the solar constant, and β is the maximum solar altitude angle.

[0046] Step S4: Determine the number of substrates based on the area, installation position, and transport envelope of the solar wing substrate 3, and select the appropriate solar wing configuration; the thickness of the solar wing substrate 3 is 23mm, and the thickness of the solar wing bracket 4 is 30mm. After folding, the distance between the solar wing substrates 3 is 14.5mm, the distance between the solar wing substrate 3 and the solar wing bracket 4 is 14.5mm, and the distance between the solar wing bracket 4 and the north side plate 2 of the platform is 31.5mm. Figure 2 As shown. The number of substrates N = A / (L*B); where L is the length of the substrate and B is the width of the substrate. The available solar wing configurations are determined by the number of substrates: straight, T-shaped, and cross-shaped, as shown below. Figure 4 、 Figure 5 、 Figure 6 shown.

[0047] Step S5: Under the constraint that the solar wing SADA5 drive shaft passes through the solar wing baseplate mass center 6, the root hinge deployment angle of the solar wing configuration is calculated in combination with the solar wing offset angle, and a solar wing configuration greater than 30° is selected;

[0048] The solar wing root hinge in-orbit deployment angle α = arccos (AB*sin(β / 2) / OA); where AB is the distance from the hinge rotation center to the base plate mass center, and OA is the length of the solar wing bracket 4. Figure 3 The calculation method of AB value of different configurations is as follows:

[0049] (1) I-shaped solar wing

[0050] AB=[N+(NL)d1] / 2+d1 / 2, where N is the number of substrates, L is the length of the substrate, and d1 is the diameter of the hinge 7 when it is unfolded. The principle is as follows: Figure 4 shown.

[0051] (2) T-shaped solar wing

[0052] AB=[(N 2 -6)L+(N 2 -N-6)d1] / (2N)+d1 / 2, where N is the number of substrates, L is the length of the substrate, and d1 is the diameter of the hinge 7 when it is unfolded once. The principle is as follows Figure 5 As shown, the secondary unfolding hinges 8 are located on both sides of the X-axis substrate and are connected to the Y-axis substrate.

[0053] (3) Cross-shaped solar wing

[0054] AB=[(N 2 -10)L+(N 2 -N-10)d1] / (2N)+d1 / 2, where N is the number of substrates, L is the length of the substrate, and d1 is the diameter of the hinge 7 when it is unfolded once. The principle is as follows Figure 6 As shown, the secondary unfolding hinges 8 are located on both sides of the X-axis substrate and are connected to the Y-axis substrate.

[0055] Step S6: Calculate the shielding area of ​​the satellite body to the solar wing body 1 when the solar altitude angle is maximum; import the satellite model into Pro / E, and use the shadow function to calculate the shielding area of ​​the satellite body to the sun when the solar altitude angle is maximum.

[0056] Step S7: Increase the area of ​​the solar wing substrate 3 to be equal to the shielding area, and repeat steps S4 and S5 to obtain a solar wing configuration that meets the requirements.

[0057] Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, and units provided by the present invention in purely computer-readable program code, it is entirely possible to implement the same functions of the system and its various devices, modules, and units provided by the present invention in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; the devices, modules, and units for implementing various functions can also be considered as both software modules implementing the method and structures within the hardware component.

[0058] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0059] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A method for designing an offset solar panel configuration for an inclined orbit satellite, characterized in that: include: Step S1: Determine the power, solar panel mounting surface size, and carrying envelope of the satellite platform based on the overall mission requirements; Step S2: Obtain the solar altitude angle variation range of the satellite's orbit; Step S3: Calculating the fixed offset angle of the solar wing and the area of ​​the solar wing substrate (3) according to the variation range of the solar altitude angle and the power of the satellite platform; Step S4: determining the number of solar wing substrates (3) according to the area, installation position and transport envelope of the solar wing substrates (3), and selecting a suitable solar wing configuration; Step S5: Under the constraint that the driving shaft of the solar wing SADA (5) passes through the center of mass of the solar wing substrate (5), the root hinge deployment angle of the solar wing configuration is calculated in combination with the solar wing offset angle, and a solar wing configuration with a root hinge deployment angle greater than 30° is selected; Step S6: Calculate the shielding area of ​​the satellite body to the solar wing body (1) when the solar altitude angle is maximum; Step S7: increasing the area of ​​the solar wing substrate (3) to be equal to the shielding area, and repeating steps S4 and S5 to obtain a solar wing configuration that meets the requirements; In step S3, the fixed offset angle of the solar wing is half of the range of the sun's altitude angle.

2. The method for designing an offset solar panel configuration for an inclined orbit satellite according to claim 1, wherein: In step S1, the solar wing body (1) is installed on the north and south side panels of the satellite platform, the length of the solar wing bracket (4) is 1896 mm, the installation surface size is: length * width = 2650 mm * 1650 mm, and the carrying envelope is Φ3850 mm.

3. The method for designing an offset solar panel configuration for an inclined orbit satellite according to claim 1, wherein: In step S2, the variation range of the solar altitude angle on the satellite's orbit is obtained through simulation calculation.

4. The method for designing an offset solar panel configuration for an inclined orbit satellite according to claim 1, wherein: In step S4, the thickness of the solar wing substrate (3) is 23 mm, the thickness of the solar wing bracket (4) is 30 mm, the distance between the solar wing substrates (3) after folding is 14.5 mm, the distance between the solar wing substrates (3) and the solar wing bracket (4) is 14.5 mm, and the distance between the solar wing bracket (4) and the satellite platform side panel is 31.5 mm.

5. A system for designing offset solar panel configurations for inclined orbit satellites, characterized by: Includes the following modules: Module M1: Determine the satellite platform power, solar panel mounting surface dimensions, and launch envelope based on overall mission requirements; Module M2: Get the range of the solar altitude angle of the satellite's orbit; Module M3: Calculate the fixed offset angle of the solar wing and the area of ​​the solar wing substrate (3) according to the range of the solar altitude angle change and the satellite platform power; Module M4: Determine the number of solar wing substrates (3) according to the area, installation position, and transportation envelope of the solar wing substrates (3), and select a suitable solar wing configuration; Module M5: Under the constraint that the driving shaft of the solar wing SADA (5) passes through the center of mass of the solar wing substrate (5), the root hinge deployment angle of the solar wing configuration is calculated in combination with the solar wing offset angle, and the solar wing configuration with a root hinge deployment angle greater than 30° is selected; Module M6: Calculate the shielding area of ​​the satellite body to the solar wing body (1) when the solar altitude angle is maximum; Module M7: Increase the area of ​​the solar wing substrate (3) equal to the shielding area, repeat modules M4 and M5, and obtain a solar wing configuration that meets the requirements; In the module M3, the fixed offset angle of the solar wing is half of the range of the sun's altitude angle.

6. The offset solar panel configuration design system for an inclined orbit satellite according to claim 5, characterized in that: In the module M1, the solar wing body (1) is installed on the north and south side panels of the satellite platform, the length of the solar wing bracket (4) is 1896 mm, the installation surface size is: length * width = 2650 mm * 1650 mm, and the carrying envelope is Φ3850 mm.

7. The offset solar panel configuration design system for an inclined orbit satellite according to claim 5, characterized in that: In the module M2, the variation range of the solar altitude angle on the satellite's orbit is obtained through simulation calculation.

8. The offset solar panel configuration design system for an inclined orbit satellite according to claim 5, characterized in that: In the module M4, the thickness of the solar wing base plate (3) is 23 mm, the thickness of the solar wing bracket (4) is 30 mm, the distance between the solar wing base plates (3) after folding is 14.5 mm, the distance between the solar wing base plates (3) and the solar wing bracket (4) is 14.5 mm, and the distance between the solar wing bracket (4) and the satellite platform side plate is 31.5 mm.

Images