A grid device for eliminating satellite surface reflections

Abstract

A kind of grid device for eliminating satellite surface reflected light, comprising: support structure, grid layer piece and grounding device;Multiple pieces of different height grid layer pieces are arrayed along the incident direction of sunlight;Each grid layer piece is fixed on the satellite surface by a plurality of support structures respectively;Grid layer piece is used to shield the reflected light reflected by satellite surface onto sensitive device;The surface of grid layer piece is provided with a thermal control coating;The grounding device is used to conduct the grid layer piece with satellite ground.This utility model realizes the optimization of satellite external thermal environment by pure passive and simple and easy thermal control measure.

Description

Technical Field

[0001] This utility model belongs to the field of thermal control technology for high-orbit spacecraft, and proposes a grid device that eliminates reflected light from the satellite surface by blocking it, thereby improving the environment of equipment sensitive to extra-space light. Background Technology

[0002] As satellite structures and thermal control technologies become increasingly complex, bright coatings (OSR sheets, aluminized films, F46 films, etc.) are frequently used on satellite surfaces to achieve temperature control and heat dissipation. During a satellite's orbit around the Earth, the angle of sunlight incident relative to the satellite changes dynamically, and the direction in which the bright coating reflects sunlight along a mirror-like pattern also changes constantly. Therefore, extraterrestrial sensitive devices located near the bright coating will inevitably have sunlight reflected onto their surfaces at some point, and the heat generated by this concentrated sunlight will keep the operating environment of these extraterrestrial devices at a relatively high temperature.

[0003] In existing technologies, replacing glossy coatings with materials that have low reflectivity (such as black carburized film) or non-glossy materials (such as white paint) can suppress directional reflection of light. However, these coatings have high infrared emissivity and surface temperature, which increases the infrared radiation heat generated by sensitive devices, making temperature control equally difficult.

[0004] Taking a high-orbit satellite laser terminal as an example, the satellite surface uses multiple layers of highly reflective surfaces such as SiOx films, F46 films, and OSR surfaces. These surfaces generally have a reflectivity greater than 80%, with specular reflection accounting for the vast majority. According to satellite thermal test data, the specular reflectivity of SiOx films is approximately 80%, F46 films approximately 90%, and OSR surfaces exceed 95%. When sunlight shines on the satellite surface and the reflected energy is concentrated on the laser terminal, the laser temperature rises rapidly, posing a significant risk of exceeding temperature limits. Utility Model Content

[0005] The technical problem solved by this invention is to overcome the shortcomings of existing technologies and provide a grid device for eliminating reflected light from satellite surfaces. This invention considers the problem of satellites being sensitive to external light or equipment being significantly affected by reflected light, and designs a grid device capable of eliminating directional reflected light. This device is installed along the path of the reflected light, eliminating adverse effects on external components (optically sensitive or thermally sensitive devices). Through purely passive and simple thermal control measures, the external thermal environment of the satellite is optimized.

[0006] The technical solution of this utility model is:

[0007] A grid device for eliminating reflected light from satellite surfaces includes: a support structure, grid layers, and a grounding device;

[0008] Multiple grid layers of different heights are arranged in an array along the direction of sunlight incidence;

[0009] Each grid layer is fixed to the satellite surface by multiple support structures; the grid layers are used to block reflected light from the satellite surface onto the sensitive devices.

[0010] The surface of the grid layers is coated with a thermal control coating;

[0011] The grounding device is used to connect the grid layer to the satellite ground.

[0012] Preferably, the spacing between two adjacent grid layers is the same, and the grid layer closer to the sensitive device has a higher plate height.

[0013] Preferably, a sensitive device is installed near the glossy coating on the satellite surface;

[0014] The grid layer is perpendicular to the surface of the glossy coating, and the surface of the grid layer is perpendicular to the satellite orbital plane;

[0015] The grid layer is fixed to the satellite surface with a glossy coating by multiple support structures, thereby blocking the glossy coating from reflecting light onto sensitive devices.

[0016] Preferably, the mathematical relationship between the spacing L between two adjacent grid layers and the height of the layer is as follows:

[0017] H1>(H0 / S0)×S,

[0018] Wherein, H1 is the height of the innermost grid layer, and the side closer to the sensitive device is defined as the inner side, and the side farther away from the sensitive device is defined as the outer side;

[0019] Define the structural point on the sensitive component that is closest to the satellite surface as the reference point; define the edge on the glossy coating that is farthest from the reference point as the farthest boundary;

[0020] The line connecting the vertices of the multiple grid layers intersects the farthest boundary; the sensing direction of the sensing device is perpendicular to the plane of the grid layer, and the sensing direction of the sensing device is perpendicular to the farthest boundary.

[0021] H0 is the normal distance from the reference point to the satellite surface;

[0022] S0 is the distance from the projection point of the reference point on the glossy coating to the farthest boundary of the glossy coating;

[0023] S is the distance from the farthest boundary of the glossy coating to the innermost grid layer.

[0024] Preferably, for grille devices that cannot directly cover the entire area of ​​the glossy coating, L

[0025] Preferably, the number of grid layers ranges from 1 to 5. ​

[0026] Preferably, the layer structure of the grid layer includes: a reflective screen and a spacer layer;

[0027] The reflector is made of double-sided aluminum-coated polyimide film, and the spacer layer is made of polyester mesh;

[0028] Each of the interval layers is equipped with a reflective screen on both sides;

[0029] Both outer surfaces of the grid layer are coated with a composite low emissivity coating, and the material is any one of CCAG coated stainless steel foil, aluminum-siloxane composite film or aluminized polyimide film.

[0030] Preferably, it further includes: a fixing device;

[0031] The fixing device is used to fix the grid layers and the support structure.

[0032] Preferably, the support structure has multiple annular cuts along the axial direction to form a narrow neck;

[0033] Each narrow neck is machined with a small hole, the axis of which is along the radial direction of the supporting structure;

[0034] The grid layers are fixed to the support structure by threading or screwing, using small holes and fixing devices.

[0035] Preferably, the diameter of the small hole on the support structure is in the range of 1.5mm to 2.5mm.

[0036] The advantages of this utility model compared with the prior art are as follows:

[0037] 1. The grid device in this utility model is installed on the outer surface of the spacecraft. The required interface is only a few points where the support structure is located. The position is relatively flexible and no post-assembly is required. This facilitates the layout of spacecraft external equipment and reduces the work of sub-assembly and final assembly.

[0038] 2. The device of this utility model is simple and easy to implement, and does not contain any active components; the support structure and fixing device are designed with good reliability, and have been verified by vibration test to withstand a sinusoidal vibration response of at least 30g;

[0039] 3. This utility model has a good effect on suppressing the reflection of sunlight. According to thermal analysis and modeling verification, the extreme heat flow is reduced by 90% and the laser terminal temperature is reduced by more than 3°C compared with the previous one after installing the grid device. Attached Figure Description

[0040] Figure 1 This is a schematic diagram illustrating the application scenario of this utility model.

[0041] Figure 2 This is a schematic diagram showing the composition and installation of the grid device of this utility model.

[0042] Figure 3 This is a schematic diagram of the support structure of this utility model.

[0043] Figure 4 This is a schematic diagram showing the dimensional requirements of the device of this utility model. Detailed Implementation

[0044] The present invention will be further described below with reference to the accompanying drawings and embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present 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, and these all fall within the protection scope of the present invention.

[0045] This utility model discloses a grid device for eliminating light reflected from the surface of a satellite, such as... Figure 1 As shown, it includes: a support structure 1, a grid layer 2, a fixing device, and a grounding device.

[0046] Multiple grid layers 2 of different heights are arranged in an array along the incident direction of sunlight; the spacing between two adjacent grid layers 2 is the same.

[0047] Each grid layer 2 is fixed to the satellite surface by multiple support structures 1; the support structures 1 are fixed by screws / threads or other reliable mechanical connections. The grid layer 2 is used to block reflected light from the satellite surface onto the sensitive device 3; the grid layer 2 closer to the sensitive device 3 has a higher plate height.

[0048] The grid layer 2 is made of hard metal or soft film material, and its surface is coated with a low emissivity thermal control coating.

[0049] The grounding device is used to connect the grid layer 2 to the satellite ground;

[0050] The fixing device is used to fix the grid layer 2 and the support structure 1.

[0051] The support structure 1 has multiple annular cuts along the axial direction to form a narrow neck;

[0052] Each narrow neck is machined with a small hole, the axis of which is along the radial direction of the support structure 1;

[0053] The grid layer 2 is fixed to the support structure 1 by means of wire binding or screwing, using small holes and fixing devices. The diameter of the small holes ranges from 1.5mm to 2.5mm.

[0054] Sensing devices 3 are installed around the locations on the satellite surface where a bright coating is applied. A grid layer 2 is fixed to the satellite surface with the bright coating by multiple support structures 1, thereby blocking the reflected light from the bright coating onto the sensing devices 3 (optical or thermal sensitive devices). The grid layer 2 is perpendicular to the surface of the bright coating, and the surface of the grid layer 2 is perpendicular to the satellite's orbital plane.

[0055] Sunlight will be reflected at the location of the satellite's bright coating at a specific moment and projected onto the sensitive device 3, affecting it with both light and heat. The grid device can be arranged directly at the location of the satellite's bright coating, or it can be arranged along the path of the light reflected to the sensitive device 3, blocking the reflected light from the bright coating onto the sensitive device 3.

[0056] There is a mathematical correspondence between the spacing between two adjacent grid layers 2 and the height of the layer. Specifically:

[0057] H1>H0 / S0×S,

[0058] H x ≤H 1-x ×L×(H0 / S0),

[0059] Where H1 is the height of the innermost grid layer 2 (the side closest to the sensitive device 3), H x H represents the height of the outermost (the side furthest from the sensitive device 3) grid layer 2; L represents the spacing between two adjacent grid layers 2; x represents the total number of grid layers 2, generally not exceeding 5. x-1 The height of the grid layer 2 adjacent to the outermost grid layer 2;

[0060] Define the structural point on the sensitive component that is closest to the satellite surface as the reference point; define the edge on the glossy coating that is farthest from the reference point as the farthest boundary;

[0061] The line connecting the vertices of the multiple grid layers 2 intersects the farthest boundary; the sensing direction of the sensing device 3 is perpendicular to the plane of the grid layer 2, and the sensing direction of the sensing device 3 is perpendicular to the farthest boundary.

[0062] H0 is the normal distance from the reference point to the satellite surface;

[0063] S0 is the distance from the projection point of the reference point on the glossy coating to the farthest boundary of the glossy coating;

[0064] S is the distance from the farthest boundary of the glossy coating to the innermost grid layer 2;

[0065] The spacing L between two adjacent grid layers 2 is greater than 50mm, which is to accommodate the requirement of reserving operating space in the structural design.

[0066] Generally, for grille devices that cannot directly cover the entire area of ​​the glossy coating, L should also be ensured.

[0067] The number of grid layers 2 ranges from 1 to 5.

[0068] Preferably, the grid layer 2 is made of multi-layer thermal insulation material composite, with 3 to 5 layers stacked. The layer structure of the grid layer 2 includes: a reflective screen and a spacer layer, with a reflective screen provided on both sides of any spacer layer; the reflective screen is a double-sided aluminized polyimide film, and the spacer layer is a polyester mesh.

[0069] Both outer surfaces of the layered structure are coated with a composite low emissivity coating, such as any one of the following: CCAG coated stainless steel foil, aluminum-siloxane composite film, or aluminized polyimide film.

[0070] The grid device of this utility model does not contain any active components and is composed entirely of metal and membrane materials; once fixed, it cannot be moved or rotated.

[0071] This invention can solve the problem of reduced thermal or optical imaging performance of satellite sensitive devices due to reflected light from the satellite surface. It minimizes the weight and interface requirements of the satellite body, identifies the reflected light path, and positions it in the correct location. It eliminates the thermal interface setting between the payload and the platform, eliminating the need for separate margins between the payload and the platform. It minimizes the contact thermal resistance between the heat source and the heat dissipation surface along the heat transfer path. By adopting passive temperature control, it can adapt to the high and low temperature conditions of the entire satellite in orbit, resulting in high reliability.

[0072] Example

[0073] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0074] This invention provides a grid device for eliminating light reflected from the surface of a satellite. Figure 1 The diagram shown illustrates a possible application scenario for this utility model. Figure 2 The diagram shown is a schematic representation of the structural composition of the device of this utility model. Figure 3 This is a schematic diagram of the support structure 1 of this utility model. Figure 4 A schematic diagram showing the dimensional requirements for the device design.

[0075] (1) Support structure 1, connected to the surface of the satellite body. The support structure 1 should take into account the connection interface with the grid layer 2 and the connection interface with the satellite surface. The height of the support structure 1 needs to be completely matched with the grid layer 2.

[0076] ​Preferably, support structure 1 is made of a long rod from a metal material such as stainless steel / aluminum alloy, with narrow necks at three different heights for mounting and fixing devices; the bottom should be threaded to match the mounting interface on the satellite body; a typical structural form is as follows: Figure 3 As shown;

[0077] In one embodiment of this utility model, multiple thin necks are arrayed along the axial direction, and each thin neck is processed with a maximum of one small hole. The axis of the small hole is along the radial direction of the support structure 1. The diameter of the small hole ranges from 1.5mm to 2.5mm. The grid layer 2 is fixed to the support structure 1 by means of wire binding or screw tightening.

[0078] (2) The grid layer 2 is a hard metal or soft film material with a pre-designed shape and size. The surface is coated with a thermal control coating with a low absorption-emissivity ratio by spraying or surface application. Each grid layer 2 has at least 4 fixing points connected to the support structure 1, and there must be fixing points at the four corners of the grid to ensure that it will not fall off.

[0079] (3) Grounding device, used to prevent static electricity in the space environment from accumulating on the grid surface. The grounding component is generally a welding plate type or copper foil type grounding wire that can be used by satellites. One end is connected to the grounding point of the grid layer 2, and the other end is connected to the 0 potential point on the satellite surface.

[0080] Preferably, the grounding device should be designed at the edge of the grid layer 2 near the star, and hollow copper rivets should be used to penetrate the grid layer 2 so that each layer of metal film inside is connected to the grounding point.

[0081] (4) External Dimensions: The external envelope formed by multiple rows should be within the path of sunlight that can reach the device. For example... Figure 4 As shown, the angle α between the top slope of the grille and the cabin plate is greater than the angle α between the farthest incident ray and the mirror surface if and only if... b At this point, the sunlight reflected by the glossy coating onto the sensitive equipment will be completely blocked by the grid device.

[0082] In this embodiment of the invention, each grid layer 2 is provided with a fixing point every 100mm to 150mm in the direction parallel to the star and a fixing point every 30 to 60mm in the direction perpendicular to the star. This ensures that the grid is securely fixed and will not fall off when the sinusoidal vibration response in the direction perpendicular to the star is below 28.0g.

[0083] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible variations and modifications to the technical solutions of the present invention using the disclosed methods and techniques without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the content of the technical solutions of the present invention, shall fall within the protection scope of the technical solutions of the present invention. Where there is no conflict, the embodiments of this application and the technical features thereof can be combined with each other.

[0084] The contents not described in detail in this utility model specification are common knowledge to those skilled in the art.

Claims

1. A grid device for eliminating reflected light from a satellite surface, characterized in that, include: Support structure (1), grid layers (2), and grounding device; Multiple grid layers (2) of different heights are arranged in an array along the incident direction of sunlight; Each grid layer (2) is fixed to the satellite surface by multiple support structures (1); the grid layer (2) is used to block reflected light from the satellite surface onto the sensitive device (3); The surface of the grid layer (2) is provided with a thermal control coating; The grounding device is used to connect the grid layer (2) to the satellite ground.

2. The grid device for eliminating reflected light from satellite surfaces according to claim 1, characterized in that, The spacing between two adjacent grid layers (2) is the same, and the grid layer (2) closer to the sensitive device (3) has a higher plate height.

3. The grid device for eliminating reflected light from satellite surfaces according to claim 1, characterized in that, Sensitive devices are installed near the glossy coating on the satellite surface (3); The grid layer (2) is perpendicular to the surface of the glossy coating, and the surface of the grid layer (2) is perpendicular to the satellite orbital plane; The grid layer (2) is fixed to the satellite surface with a bright coating by multiple support structures (1), thereby blocking the reflected light of the bright coating to the sensitive device (3).

4. A grid device for eliminating reflected light from a satellite surface according to claim 3, characterized in that, The mathematical relationship between the spacing L between two adjacent grid layers (2) and the height of the layer is as follows: H1>(H0 / S0)×S, H1 is the height of the innermost grid layer (2), and the side closer to the sensitive device (3) is defined as the inner side, and the side farther away from the sensitive device (3) is defined as the outer side. Define the structural point on the sensitive component that is closest to the satellite surface as the reference point; define the edge on the glossy coating that is farthest from the reference point as the farthest boundary; The line connecting the vertices of the multiple grid layers (2) intersects the farthest boundary; the sensing direction of the sensing device (3) is perpendicular to the plane of the grid layers (2), and the sensing direction of the sensing device (3) is perpendicular to the farthest boundary. H0 is the normal distance from the reference point to the satellite surface; S0 is the distance from the projection point of the reference point on the glossy coating to the farthest boundary of the glossy coating; S is the distance from the farthest boundary of the glossy coating to the innermost grid layer (2).

5. A grid device for eliminating reflected light from a satellite surface according to claim 4, characterized in that, For a grid device that cannot directly cover the entire area of ​​the glossy coating, the number of L grid layers (2) ranges from 1 to 5.

6. A grid device for eliminating reflected light from a satellite surface according to any one of claims 1-5, characterized in that, The layer structure of the grid layer (2) includes: a reflective screen and a spacer layer; 7. A grid device for eliminating reflected light from a satellite surface according to claim 6, characterized in that, The reflector is made of double-sided aluminum-coated polyimide film, and the spacer layer is made of polyester mesh; Each of the interval layers is equipped with a reflective screen on both sides; Both outer surfaces of the grid layer (2) are coated with a composite low emissivity coating, and the material is any one of CCAG coated stainless steel foil, aluminum-siloxane composite film or aluminum-coated polyimide film. Also includes:

8. A grid device for eliminating reflected light from a satellite surface according to claim 7, characterized in that, Fixture; The fixing device is used to fix the grid layer (2) and the support structure (1) together. The support structure (1) has multiple annular cuts along the axial direction to form a narrow neck; 9. A grid device for eliminating reflected light from a satellite surface according to claim 8, characterized in that, Each narrow neck is machined with a small hole, the axis of which is along the radial direction of the support structure (1); The grid layer (2) is fixed to the support structure (1) by means of threading and binding or screwing, using small holes and fixing devices. The diameter of the small hole on the support structure (1) ranges from 1.5mm to 2.5mm.

10. A grid device for eliminating reflected light from a satellite surface according to claim 9, characterized in that, ​

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