GEO Satellite Sunshade Configuration Optimization Method and Sunshade

Abstract

This invention provides a method for optimizing the configuration of a GEO satellite sunshade and the sunshade itself, including the following steps: Step A: Establishing an orbital coordinate system and calculating the solar vector, the angle between the Earth-axis composite plane and the orbital plane, and their maximum values; Step B: Selecting a suitable basic configuration of the sunshade based on the onboard layout requirements; Step C: Calculating the distance from the sunshade plate perpendicular to the orbital plane to the camera's line of sight; Step D: Drawing the upper curve of the sunshade plate; Step E: Determining whether the sunshade plate constructed based on the upper curve obstructs the camera's field of view; Step F: Drawing the tangent to the curve and using the tangent as the upper curve of the sunshade plate; Step G: Determining whether the sunshade plate constructed based on the tangent to the upper curve obstructs the camera's field of view. This invention eliminates the need for large-scale simulations using specialized optical simulation tools, facilitating rapid optimization of the large field-of-view camera and other onboard layouts by satellite engineers.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, specifically to a method for optimizing the configuration of a GEO satellite sunshade and the sunshade itself. Background Technology

[0002] Improving detection range and continuous observation time are key focuses in the development of remote sensing satellites. With the advancement of space exploration technology and optical instruments, the field of view of optical systems for GEO (Geostationary Orbit) satellite instruments will continue to increase. For future large-field-of-view, high-resolution optical systems, the size of their sunshades will far exceed the spatial envelope of the rocket fairing. Therefore, effective measures must be taken to ensure that the camera's external sunshade meets the space constraints imposed by the rocket fairing.

[0003] Currently, GEO satellites mostly use obliquely cut sunshades and adjust their attitude to avoid the sun. At the same time, they utilize the characteristics of sunlight to retain the sunshade in the direction of sunlight incidence, while removing the sunshade in other directions, so as to reduce the size and weight of the sunshade and meet the requirements of the rocket.

[0004] Existing literature primarily focuses on sunshade design to meet camera field of view and stray light suppression requirements, without optimizing the design based on the characteristics of GEO satellites in orbit. If the design is based on solar incidence and solar avoidance strategies during orbital operation, not only can the minimum sunshade height and lateral dimensions meet mission and launch requirements, but the shape can also be flexible and adaptable, solving the problem of insufficient onboard space.

[0005] In the paper "Solar Protection Attitude Control Correlation Design Method for Optical Imaging Satellite Cameras" (CN201810616048.3) published by Hong Zhenqiang, Song Xiaozheng, Li Jian, et al., a sunshade design method in periodic yaw mode was proposed. Compared with the traditional sunshade, the size is greatly reduced, but it requires the satellite attitude to be periodically yawed and offset, which is not conducive to inter-satellite link establishment in the same orbit and remote sensing of the earth, especially for small field-of-view cameras, and the application scope is narrow.

[0006] The paper "Real-time Sun Avoidance Method for Cameras with Oblique-Cut Sunshades on Geostationary Satellites" (CN201811348795.X) published by Qiao Guodong, Liu Xinyan, Zong Lisen, et al. proposed a "yaw-pitch joint attitude maneuver" strategy for sun avoidance, but did not involve the design of the sunshade.

[0007] The paper "Real-time Sun Avoidance Method for Cameras with Cylindrical Sunshades on Geostationary Satellites" (CN201710879530.1) published by Qiao Guodong, Liu Xinyan, Zong Lisen, et al. proposes a "rolling" attitude maneuver strategy for sun avoidance, but it does not involve the design of the sunshade.

[0008] The paper "A Light Shield Structure for Geostationary Orbit Remote Sensing Cameras" (CN201710371624.8) published by Sun Donghua, Wang Yue, Ning Xiaozhou, et al. proposed a light shield structure for geostationary orbit remote sensing cameras that integrates structural load-bearing, heat conduction, and light extinction functions, but did not involve the design of the light shield.

[0009] The paper "A Deployable Sunshade Device for a Geostationary Orbit Remote Sensing Camera" (CN201710858018.9) published by Cao Nailiang, Dong Deyi, Chai Fangmao, et al. proposed a deployable sunshade device for a 3-meter aperture geostationary orbit remote sensing camera, but the design of the sunshade was not mentioned. Summary of the Invention

[0010] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method for optimizing the configuration of a GEO satellite sunshade and the sunshade itself.

[0011] A method for optimizing the configuration of a GEO satellite radome according to the present invention includes:

[0012] Step A: Calculate the solar vector, the angle between the Earth axis composite plane and the orbital plane, and the maximum value;

[0013] Step B: Select the appropriate basic configuration of the sunshade based on the satellite layout requirements;

[0014] Step C: Calculate the distance from the light-shielding plate on the vertical track surface of the lens hood to the camera's line of sight;

[0015] Step D: Based on the calculation results of Step A and Step C, draw the upper edge curve of the light-shielding plate;

[0016] Step E: Determine whether the light shield constructed along the upper curve blocks the camera's field of view. If it does not block the camera's field of view, proceed to step F; otherwise, increase the L1 value and return to step D.

[0017] Step F: Draw the tangent line to the upper curve, and use the tangent line as the upper edge of the light-shielding plate;

[0018] Step G: Determine whether the light shield constructed according to the tangent of the upper curve blocks the camera's field of view. If it does not block the view, the tangent is feasible; otherwise, increase the L1 value and return to step D.

[0019] Preferably, step A includes:

[0020] The angle between the ground axis assembly plane and the track plane is:

[0021]

[0022] The maximum angle between the ground axis composite plane and the track plane is:

[0023]

[0024] The solar vector includes: the angular distance α between the satellite and midnight at the start of solar avoidance. g And the solar altitude angle β.

[0025] Preferably, the basic configuration of the light shield includes three light shields.

[0026] Preferably, the distance calculation method in step C includes:

[0027]

[0028] In the formula, θ is the half-cone angle of the camera's field of view, and D is the camera's aperture.

[0029] Preferably, in step D, MATLAB is used to plot a curve based on the coordinate values ​​of the upper edge of the light shield:

[0030]

[0031]

[0032]

[0033] In the formula, L1 is the width of the light-shielding plate perpendicular to the orbital plane, δ is the supplementary angle between adjacent light-shielding plates, z0 is the distance from the bottom of the inner light-shielding cover to the satellite's center of mass, and H... b For the corresponding The height of the light-shielding plate cross section.

[0034] Preferably,

[0035]

[0036] Preferably, in step E, the calculation is performed iteratively. Each H b Does it not obstruct the camera's field of view?

[0037] when At that time, it is feasible to follow the curve on the light-shielding plate.

[0038] Preferably, in step F, the tangent line of the upper curve is drawn using MATLAB, and after the tangent line is used as the upper edge of the light shield, the upper curve can be contained within the light shield.

[0039] Preferably, in step G, the tangent is used as the new upper edge curve of the light-shielding plate, and step E is repeated.

[0040] According to the GEO satellite sunshade configuration provided by the present invention, the configuration is obtained by the aforementioned GEO satellite sunshade configuration optimization method.

[0041] Compared with the prior art, the present invention has the following beneficial effects:

[0042] This invention calculates the upper edge of the sunshade based on its basic configuration and the satellite's orbital position at the solar avoidance starting point. It eliminates the need for large-scale simulations using specialized optical simulation tools, employing only trigonometric function operations, making it simple and easy to understand. This facilitates rapid optimization of the wide-field-of-view camera and other onboard layout by satellite engineers. It enhances the sunshade optimization design capabilities for GEO cameras, enabling rapid optimization of the wide-field-of-view camera and other onboard layout by satellite engineers. Attached Figure Description

[0043] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0044] Figure 1 The diagram shows a flowchart of the steps in the GEO satellite sunshade configuration optimization design method provided in an embodiment of the present invention.

[0045] Figure 2 The diagram shown is a schematic representation of the relationship between the sun and the sunshade at the solar avoidance starting point according to an embodiment of the present invention.

[0046] Figure 3 The diagram shown is a schematic representation of the configuration of a light-shielding plate and a circular light-shielding cover provided in an embodiment of the present invention.

[0047] Figure 4 The diagram shown is a schematic representation of the dimensional relationship between the light shield and the inner light shield according to an embodiment of the present invention.

[0048] Figure 5 The figure shows the upper curve and tangent of a side-mounted light shield provided in an embodiment of the present invention;

[0049] Figure 6 The figure shows the upper curve and tangent of the light-shielding plate of the vertical track surface provided in an embodiment of the present invention;

[0050] 1- Bottom of the inner sunshade;

[0051] 2-Inner sunshade;

[0052] 3-Solar Vector;

[0053] 4-Sunshade;

[0054] 5 - Upper edge of the inner sunshade;

[0055] 6- Sunshade plate on the vertical track surface;

[0056] 7-Side-mounted light-shielding panel;

[0057] 8-Railway surface;

[0058] 9- Circular sunshade;

[0059] 10 - Edge of camera field of view;

[0060] 11 - Curve along the upper edge of the side-mounted light shield;

[0061] 12 - Tangent to the curve along the side-mounted light shield;

[0062] 13 - Curve along the upper edge of the vertical track surface light shield;

[0063] 14 - Tangent to the curve along the vertical track surface light shield. Detailed Implementation

[0064] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0065] A method for optimizing the configuration of a GEO satellite sunshade includes the following steps:

[0066] Step A: Calculate the solar vector, the angle between the Earth axis composite plane and the orbital plane, and the maximum value;

[0067] Step B: Select the appropriate basic configuration of the sunshade based on the satellite layout requirements;

[0068] Step C: Calculate the distance from the light-shielding plate on the vertical track surface of the lens hood to the camera's line of sight;

[0069] Step D: Based on the calculation results of Step A and Step C, considering the installation environment of the light shield, select appropriate L1 and δ values, and draw the upper edge curve of the light shield.

[0070] Step E: Determine whether the light shield constructed along the upper curve blocks the camera's field of view. If it does not block the camera's field of view, proceed to step F; otherwise, increase the L1 value and return to step D.

[0071] Step F: Draw the tangent line to the upper curve, and use the tangent line as the upper curve of the light-shielding plate;

[0072] Step G: Determine whether the light shield constructed according to the tangent of the upper curve blocks the camera's field of view. If it does not block the view, the tangent is feasible; otherwise, increase the L1 value and return to step D.

[0073] In step A: The satellite operates in a GEO orbit. Around midnight, the satellite begins continuous attitude adjustments using "line-of-sight offset + servo yaw" to avoid direct sunlight on the camera's optical system. At other times, the satellite maintains normal Earth alignment. The origin of the orbital coordinate system is at the satellite's center of mass, +Z i The axis points to the Earth's center, +X iThe axis points in the direction of satellite flight, +Y i With +X i +Z i This forms a right-handed coordinate system. The solar vector, the angle between the combined surface of the Earth's axis and the orbital plane, and their maximum values ​​are:

[0074]

[0075] In the formula, α g β represents the angular distance between the satellite and midnight at the start of solar avoidance, and β is the solar altitude angle.

[0076] In step B: The basic configuration of the light shield is 3 plates.

[0077] In step C: the camera's field of view is a cone. In the formula, θ is the half-cone angle of the camera's field of view, and D is the camera's aperture.

[0078] In step D: Use MATLAB to plot a curve based on the coordinate values ​​of the upper edge of the light shield.

[0079]

[0080]

[0081]

[0082] In the formula, L1 is the width of the light-shielding plate perpendicular to the orbital plane, δ is the supplementary angle between adjacent light-shielding plates, z0 is the distance from the bottom of the inner light-shielding cover to the satellite's center of mass, and H... b For the corresponding Height of the light-shielding plate section:

[0083]

[0084] In step E: Traversal calculation Each H b Does it not obstruct the camera's field of view?

[0085] when At that time, the upper edge of the sunshade is feasible.

[0086] In step F: Using MATLAB, the tangent to the upper edge of the curve is drawn. After the tangent to the curve is used as the upper edge of the light-shielding plate, the curve can be contained within the light-shielding plate.

[0087] In step G: Using the tangent as the upper edge of the light-shielding plate, repeat step E. If the upper edge does not obstruct the camera's field of view, then the tangent is feasible.

[0088] The specific embodiments of the present invention will be further described below with reference to the accompanying drawings. The implementation steps are as follows: Figure 1 As shown.

[0089] 1) Calculate the solar vector, the angle between the Earth axis composite plane and the orbital plane, and their maximum values.

[0090] Take α g =21°, β∈[-23.5°,23.5°], then:

[0091]

[0092] 2) Select the appropriate basic configuration of the sunshade according to the on-board layout requirements.

[0093] Both sunshades and circular sunshades are acceptable, such as... Figure 3 As shown.

[0094] 3) Calculate the distance from the light shield on the vertical track surface to the camera's line of sight and the radius of the circular light shield.

[0095] b = 0.6748m.

[0096] 4) Draw the curve at the upper edge of the light-shielding plate.

[0097] like Figure 5 , Figure 6 As shown.

[0098] 5) Determine whether the light shield constructed along the upper curve blocks the camera's field of view.

[0099] Calculations show that for

[0100] 6) Use MATLAB to draw the tangent line along the curve.

[0101] like Figure 5 , Figure 6 As shown.

[0102] 5) Determine whether the light shield constructed based on the tangent of the upper curve blocks the camera's field of view.

[0103] Calculations show that for

[0104] The present invention also provides a GEO satellite sunshade configuration, which is obtained by the above-mentioned GEO satellite sunshade configuration optimization method.

[0105] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They 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, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0106] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for optimizing the configuration of a GEO satellite sunshade, characterized in that, include: Step A: Calculate the solar vector, the angle between the Earth axis composite plane and the orbital plane, and the maximum value; Step B: Select the appropriate basic configuration of the sunshade based on the satellite layout requirements; Step C: Calculate the distance from the light-shielding plate on the vertical track surface of the lens hood to the camera's line of sight; Step D: Based on the calculation results of Step A and Step C, draw the upper edge curve of the light-shielding plate; Step E: Determine whether the light shield constructed along the upper curve blocks the camera's field of view. If it does not block the camera's field of view, proceed to step F; otherwise, increase the width of the light shield on the vertical track surface and return to step D. Step F: Draw the tangent line to the upper curve, and use the tangent line as the upper edge of the light-shielding plate; Step G: Determine whether the light shield constructed according to the tangent of the upper curve blocks the camera's field of view. If it does not block the view, the tangent is feasible; otherwise, increase the width of the light shield perpendicular to the track surface and return to step D. In step D, MATLAB is used to plot a curve based on the coordinate values ​​of the upper edge of the light shield: In the formula, L1 is the width of the light-shielding plate perpendicular to the orbital plane, δ is the supplementary angle between adjacent light-shielding plates, z0 is the distance from the bottom of the inner light-shielding cover to the satellite's center of mass, and H... b For the corresponding The height of the light-shielding plate cross section, The angle between the ground axis assembly plane and the track plane, This represents the maximum angle between the combined surface of the Earth axis and the orbital surface. denoted as the camera's field of view semi-cone angle, and D as the camera's aperture.

2. The method for optimizing the configuration of a GEO satellite sunshade according to claim 1, characterized in that, Step A includes: The angle between the ground axis assembly plane and the track plane is: The maximum angle between the ground axis composite plane and the track plane is: The solar vector includes: the angular distance of the satellite from midnight at the start of solar avoidance. and solar altitude angle .

3. The method for optimizing the configuration of a GEO satellite sunshade according to claim 1, characterized in that, The basic configuration of a sunshade consists of three sunshade panels.

4. The method for optimizing the configuration of a GEO satellite sunshade according to claim 2, characterized in that, 。 5. The method for optimizing the configuration of a GEO satellite sunshade according to claim 1, characterized in that, In step E, the calculation is performed iteratively. Each H b Does it not obstruct the camera's field of view? when If the curve along the light-shielding plate is feasible, then increase the L1 value and return to step D.

6. The method for optimizing the configuration of a GEO satellite sunshade according to claim 1, characterized in that, In step F, by drawing the tangent of the upper curve as the upper edge of the light-shielding plate, the upper curve can be contained within the light-shielding plate.

7. The method for optimizing the configuration of a GEO satellite sunshade according to claim 1, characterized in that, In step G, the tangent is used as the new upper edge curve of the light-shielding plate, and step E is repeated.

8. A GEO satellite sunshade configuration, characterized in that, The configuration optimization method for the GEO satellite sunshade as described in any one of claims 1-7 is used.

Images