Integrated load for ground shadow area space debris detection

Abstract

The invention discloses an integrated load for detecting space debris in an earth shadow area. The integrated load consists of a shell, a space camera, a lamp panel and a circuit control box, the shell serves as an outer frame of a load; the space camera and the circuit control box are connected together and are connected with the shell together; the lamp panel is connected to a top plate in the shell; the device is a combination of modularized and customized parts, is convenient to produce and process, and has the advantages of low cost, simple structure, high universality and short production period; a visible light source is used for illumination, a visible light space camera is used for monitoring ground shadow area space debris, and ground shadow area space debris data is supplemented.

Description

Technical Field

[0001] The present invention provides an integrated payload for detecting space debris in the Earth's shadow region, which relates to the need for monitoring space debris using a visible light source and a visible light space camera, and belongs to the field of satellite structure design. Background Art

[0002] Space optical technology refers to the use of optical sensors, such as infrared, visible light, or radar, to collect information about the Earth's surface and near-Earth space. Since the Soviet Union successfully launched the first artificial satellite in October 1957, humanity has increasingly valued the resources of outer space. In 1960, Discoverer 14 successfully transmitted film back to Earth, marking the first application of space optical technology in the satellite sector. Since then, space optical technology has been widely applied in a number of key areas, including remote sensing observation, astronomical exploration, and space target monitoring. Examples include the US Landsat series and the Soviet Resurs series of Earth resources satellites. my country, while relatively late to the game, successfully launched the Resource-1 satellite in 1999 for land surveys. Space optical technology can identify ground object types, monitor ground changes, and perform classification and analysis using spectral images. It holds significant significance in agriculture, forestry, water resources, urban planning, environmental monitoring, and disaster assessment.

[0003] As a key payload, space cameras undertake the crucial task of observing space targets. In recent decades, advancements in optical technology have expanded spectral imaging from single-channel cameras to dozens of hyperspectral cameras, with spatial resolution increasing from 30 meters to less than 1 meter in high-resolution cameras. By wavelength, they can be categorized as visible light cameras, near-infrared cameras, and ultraviolet cameras; by spectral imaging method, they can be divided into panchromatic cameras, multispectral cameras, wide-spectral cameras, and hyperspectral cameras. Space cameras are playing an increasingly important role in many fields, such as astronomical observation and weather forecasting, and have become a vital tool for human exploration of Earth and even outer space.

[0004] A space camera consists of an optical lens group, a support structure, and an imaging sensor. The optical lens group and the imaging sensor are installed on the support structure to ensure that the optical plane of the optical lens group is parallel to the image plane of the sensor. Therefore, the design and material selection of the support structure greatly affect the final imaging quality. Improper material selection of structural parts is sensitive to temperature changes, resulting in deformation of the overall structure. Unreasonable structural configuration design and insufficient rigidity are affected by vibration during transportation and launch, which can easily lead to displacement between optical components and poor final imaging effect.

[0005] Space cameras are primarily classified as passive and active imaging. Most optical remote sensing payloads employ passive imaging, while lidar and some night-vision infrared cameras employ active imaging. For example, the advanced terrain laser altimetry system aboard NASA's ICESat-2 satellite is a core single-photon detection system comprised of four key components: a high-power laser generating a pulsed beam, a diffraction spectrometer for spatial light field modulation, a precision laser alignment mechanism ensuring beam pointing accuracy, and finally, a star sensor for space attitude calibration.

[0006] CubeSats are miniature satellites based on standard cube-shaped units, offering significant advantages in cost, flexibility, and rapid deployment. They have become a key platform for space cameras. For example, NASA's CIRiES project utilizes CubeSats to monitor the atmospheric environment. Compared to other satellite payloads, CubeSats feature compact design, high space utilization, and a high degree of integration between mechanical, thermal, and electrical subsystems. For optical payloads, simply increasing the size of the space camera cannot improve performance. CubeSat miniature optical cameras have become a key payload for space target detection and hold great promise for future development.

[0007] Traditional visible-light-band space optical cameras use passive imaging. When the target enters the Earth's shadow, sunlight is blocked by the Earth, rendering visible-light observation ineffective. Active imaging with a light source can effectively address these issues. Furthermore, with the increasing demands on various CubeSat indicators, such as payload capacity and mechanical performance, the mission requirements for optical payloads are becoming more stringent. To efficiently utilize the space onboard CubeSats, innovations in optical payload structures are urgently needed. This requires an integrated design of the CubeSat's light source and space camera, resulting in a mature optical payload solution. Summary of the Invention

[0008] (1) Purpose of the invention: The purpose of the present invention is to provide an integrated payload for detecting space debris in the Earth's shadow region. The payload consists of a customized component housing, a space camera, a light board, and a circuit control box. The housing serves as the external structure of the payload, providing external support and protection for the payload ladder control, and also provides mounting holes and light board mounting holes. The space camera uses a lens group to focus the light path and a CMOS sensor to form an image. The light board uses visible light to illuminate space debris. The circuit control box contains a CMOS image processing, light board driver, and charging and discharging circuit board.

[0009] (2) Technical solution

[0010] An integrated payload for detecting space debris in Earth's shadow region, characterized in that it comprises a space camera, a housing, a light board, and a circuit control box; the housing comprises five thin metal plates forming a rectangular outer shell of the entire payload; the space camera is connected to the circuit control box via threaded fasteners, and both are connected to the housing via threaded fasteners; the light board is fixed to the housing, with the plane of the light board parallel to the optical plane of the space camera;

[0011] The space camera is composed of five parts: a mirror frame, a secondary mirror, a primary mirror, a calibration mirror, and a CMOS board. The mirror frame is the main support structure of the space camera. The secondary mirror, the primary mirror, the calibration mirror, and the mirror frame are pressed together by a pressure ring, and the pressure ring can be glued. The CMOS board and the mirror frame are connected by three threaded fasteners.

[0012] The mirror frame is divided into three layers: the secondary mirror layer, the primary mirror calibration mirror layer, and the CMOS connection column layer. The secondary mirror layer and the primary mirror calibration mirror layer are connected by four "L"-shaped columns, and the CMOS connection column layer is connected to the primary mirror calibration mirror layer. The mirror frame has a stepped boss design at the secondary mirror, primary mirror, and calibration mirror installation locations to ensure that the secondary mirror, primary mirror, and calibration mirror are uniquely installed. The mirror frame has three threads: an M94 thread on the secondary mirror layer, and M86 and M34 threads on the primary mirror calibration mirror layer, which are used to fix the matching pressure rings respectively.

[0013] The secondary mirror has a maximum diameter of 94 mm and is installed on the secondary mirror layer of the mirror frame. The secondary mirror is divided into a large curvature radius surface and a small curvature radius surface. The large curvature radius surface is the bottom surface, and the small curvature radius surface is the top surface. The mounting surface between the secondary mirror and the mirror frame is at the process edge of the bottom surface, and the mounting surface between the secondary mirror and the pressure ring is at the process edge of the top surface.

[0014] The primary mirror has a maximum diameter of 86 mm and is mounted on the primary mirror calibration mirror layer of the mirror frame. The primary mirror has a lower concave surface and an upper convex surface. The upper convex surface has a reflective film. The mounting surface between the primary mirror and the mirror frame is the upper convex surface process edge, while the mounting surface between the primary mirror and the matching pressure ring is the lower concave surface process edge. There is a circular hole in the center of the primary mirror.

[0015] The maximum diameter of the correction mirror is 34 mm, and it is installed on the calibration mirror layer of the main mirror of the mirror frame. The calibration mirror is divided into a lower concave surface and an upper convex surface. The mounting surface between the calibration mirror and the mirror frame is the lower concave surface process edge, and the mounting surface between the calibration mirror and the matching pressure ring is the upper convex surface process edge.

[0016] The rectangular shell is composed of five parts: side plate 1, side plate 2, bottom plate, side plate 3, and top plate. The five thin plates together form the external supporting shell structure of the load.

[0017] There are four M3 threaded holes and four M2.5 threaded holes on the top plate, which are used to fix the light board and the top plate to the circuit control box respectively; a rectangular hole is opened in the center of the top plate for wiring;

[0018] There are four M2.5 threaded holes and one rectangular hole on the bottom plate. The threaded holes are used to fix the bottom plate and the circuit control box, and the rectangular hole is used for wiring.

[0019] There are two M3 threaded holes on the side panel 1 for fixing the side panel 1 and the space camera;

[0020] The second side panel is an L-shaped panel with a long side and a short side. There are four M2.5 threaded holes on the long side for fixing the second side panel to the circuit control box.

[0021] There are ten bosses and rectangular grooves on the side panel three. There is a threaded hole in the center of the boss for fixing the cubic satellite heat conduction plate. There are four M2.5 threaded holes on the side panel three for fixing the side panel two and the circuit control box.

[0022] The light board is composed of a plurality of light bulb arrays, the light bulb surface is the front side, and the back side is the back side; the back side of the light board contacts the top board and is fixed by four M3 threaded fasteners at the four corners; the light board bus enters the circuit control box through the rectangular hole in the center of the top board and is connected to the circuit driver board;

[0023] The circuit control box consists of a front frame, circuit board 1, circuit board 2, circuit board 3, circuit board 4, circuit board 5, a supercapacitor, a rear frame, and studs; the distance between the front frame and circuit board 1 is 10.59 mm, and the distance between circuit board 1, circuit board 2, circuit board 3, circuit board 4, and circuit board 5 is 17 mm; the front frame, circuit board 1, circuit board 2, circuit board 3, circuit board 4, circuit board 5, and rear frame are connected by M3 studs;

[0024] The front frame is a rectangular cross-section frame with a rectangular cross-section beam in the middle. The cross-section beam has two M3 threaded holes for fixing the mirror holder and the front frame. The four sides of the rectangular cross-section frame have two M2.5 threaded holes for fixing the shell. There are four rounded corners at the four corners of the front frame, and four M3 threaded holes in the rounded corners are used to fix studs.

[0025] The first mounting hole of the circuit board meets the CubeSat circuit board standard, and the FPC slot on the circuit board should be connected to the FPC slot on the space camera CMOS for data transmission;

[0026] The second, third and fourth mounting holes of the circuit board meet the CubeSat circuit board standard and are used for light board control;

[0027] The four mounting holes of the circuit board meet the standards of cubic satellite circuit boards, and several supercapacitors are welded on them for charging the light boards;

[0028] (3) Advantages

[0029] The advantages of the integrated payload for detecting space debris in the Earth's shadow region of the present invention are:

[0030] ① The present invention proposes a new space camera that can be used to detect space debris in the Earth's shadow region.

[0031] The integrated payload proposed in this invention for detecting space debris in the Earth's shadow region consists of a space camera and a light panel. This modular and customizable design facilitates manufacturing and processing. This integrated payload offers the advantages of low cost, simple structure, high versatility, and a short production cycle.

[0032] ③ The integrated payload proposed in this invention for detecting space debris in the Earth's shadow region adopts a lightweight design. The space camera has been optimized with a total mass of 599g and a structural mass of 175g. While achieving lightweight, it also has a field of view of 8°×8°, capable of observing stars of magnitude 12. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is the overall structural diagram of the micro-nano satellite described in the present invention.

[0034] Figure 2 This is an internal installation diagram of the micro-nano satellite described in the present invention.

[0035] Figure 3 This is a diagram showing the relationships between the various components of the micro-nano satellite described in the present invention.

[0036] The product codes in the figure are explained as follows:

[0037] 1. Space camera 1a. Mirror frame 1b. Secondary mirror

[0038] 1c. Primary mirror 1d. Correction mirror 1e. CMOS board

[0039] 2. Shell 2a. Side panel 1 2b. Side panel 2

[0040] 2c. Bottom plate 2d. Side plate 3 2e. Top plate

[0041] 3. Light board 4. Circuit control box 4a. Front frame

[0042] 4b. Circuit board 1 4c. Circuit board 2, circuit board 3, circuit board 4 4d. Circuit board 5

[0043] 4e. Supercapacitor 4f. Rear frame 4g. Stud DETAILED DESCRIPTION

[0044] The present invention will be described in further detail below with reference to the accompanying drawings.

[0045] See also Figure 1 、 Figure 2 、 Figure 3The present invention provides an integrated payload that can be used for detecting space debris in the Earth's shadow area, which is composed of a space camera 1, a shell 2, a light board 3, and a circuit control box 4; the relationship between them is: the space camera 1 and the circuit control box 4 are connected by threaded fasteners; the shell 2 is connected to the space camera 1 and the circuit control box 4 by threaded fasteners to form a rectangular shell of the payload; the light board 3 is fixed on the top plate 2e in the shell 2.

[0046] The space camera is composed of five parts: a mirror frame 1a, a secondary mirror 1b, a primary mirror 1c, a calibration mirror 1d, and a CMOS board 1e. The mirror frame 1a is the main support structure of the space camera. The secondary mirror 1b, the primary mirror 1c, the calibration mirror 1d and the mirror frame 1c are pressed together by a pressure ring, and the pressure ring can be filled with glue. The CMOS board 1e is connected to the mirror frame 1a by three threaded fasteners. The material of the mirror frame 1a is duralumin.

[0047] The shell is composed of five parts: side panel 1 2a, side panel 2b, bottom panel 2c, side panel 3 2d, and top panel 2e; their mutual relationship is: side panel 1 2a, side panel 2b, and side panel 3 2d constitute the side surface of the shell, among which side panel 2b is an "L"-shaped thin plate, and bottom panel 2c and top panel 2e serve as the upper and lower surfaces of the shell; side panel 1 2a, side panel 2b, bottom panel 2c, side panel 3 2d, and top panel 2e are all connected to the space camera 1 through threaded fasteners and the circuit control box 4; the top panel 2e is connected to the light board 3; there are ten bosses and rectangular grooves on side panel 3 2d, and there is a threaded hole at the center of the boss for fixing the cubic satellite heat conduction plate; the material of side panel 1 2a, side panel 2b, bottom panel 2c, side panel 3 2d, and top panel 2e is hard aluminum.

[0048] The light panel 3 is fixed on the top panel 2e.

[0049] The circuit control box consists of a front frame 4a, circuit board 1 4b, circuit board 2 4c, circuit board 3 4c, circuit board 4 4c, circuit board 5 4d, supercapacitor 4e, rear frame 4f, and stud 4g; the distance between the front frame 4a and circuit board 1 4b is 10.59 mm, and the distance between circuit board 1 4b, circuit board 2 4c, circuit board 3 4c, circuit board 4 4c, and circuit board 5 4d is 17 mm; the front frame 4a, circuit board 1 4b, circuit board 2 4c, circuit board 3 4c, circuit board 4 4c, circuit board 5 4d, and rear frame 4e are connected by stud 4f.

Claims

1. An integrated payload for detecting space debris in Earth's shadow region, characterized by: It consists of a space camera, a housing, a light board, and a circuit control box. The housing is composed of five metal sheets, forming a rectangular shell for the entire payload. The space camera is connected to the circuit control box via threaded fasteners, and both are connected to the housing via threaded fasteners. The light board is fixed to the housing, and the plane of the light board is parallel to the optical plane of the space camera. The space camera is composed of five parts: a mirror frame, a secondary mirror, a primary mirror, a calibration mirror, and a CMOS board. The mirror frame is the main supporting structure of the space camera. The secondary mirror, the primary mirror, the calibration mirror, and the mirror frame are pressed together by a pressure ring, and the pressure ring can be filled with glue. The mirror frame is divided into three layers: the secondary mirror layer, the primary mirror calibration mirror layer, and the CMOS connection column layer. The secondary mirror layer and the primary mirror calibration mirror layer are connected by four "L"-shaped columns, and the CMOS connection column layer is connected to the primary mirror calibration mirror layer. The frame has a stepped boss design at the secondary mirror, primary mirror, and calibration mirror mounting points to ensure that the secondary mirror, primary mirror, and calibration mirror are uniquely mounted. The mirror frame has three threads: an M94 thread on the secondary mirror layer, and M86 and M34 threads on the primary mirror calibration mirror layer, which are used to fix the matching pressure rings. The secondary mirror has a maximum diameter of 94 mm and is installed on the secondary mirror layer of the mirror frame. The secondary mirror is divided into a large curvature radius surface and a small curvature radius surface. The large curvature radius surface is the bottom surface, and the small curvature radius surface is the top surface. The mounting surface between the secondary mirror and the mirror frame is at the process edge of the bottom surface, and the mounting surface between the secondary mirror and the pressure ring is at the process edge of the top surface. The primary mirror has a maximum diameter of 86 mm and is mounted on the primary mirror calibration mirror layer of the mirror frame. The primary mirror has a lower concave surface and an upper convex surface. The upper convex surface has a reflective film. The mounting surface between the primary mirror and the mirror frame is the upper convex surface process edge, while the mounting surface between the primary mirror and the matching pressure ring is the lower concave surface process edge. There is a circular hole in the center of the primary mirror. The maximum diameter of the correction mirror is 34 mm, and it is installed on the calibration mirror layer of the main mirror of the mirror frame. The calibration mirror is divided into a lower concave surface and an upper convex surface. The mounting surface between the calibration mirror and the mirror frame is the lower concave surface process edge, and the mounting surface between the calibration mirror and the matching pressure ring is the upper convex surface process edge. The rectangular shell is composed of five parts: side plate 1, side plate 2, bottom plate, side plate 3, and top plate. The five thin plates together form the external supporting shell structure of the load. There are four M3 threaded holes and four M2.5 threaded holes on the top plate, which are used to fix the light board and the top plate to the circuit control box respectively; a rectangular hole is opened in the center of the top plate for wiring; There are four M2.5 threaded holes and one rectangular hole on the bottom plate. The threaded holes are used to fix the bottom plate and the circuit control box, and the rectangular hole is used for wiring. There are two M3 threaded holes on the side panel 1 for fixing the side panel 1 and the space camera; The second side panel is an L-shaped panel with a long side and a short side. The long side has four M2.5 threaded holes for fixing the second side panel to the circuit control box. There are ten bosses and rectangular grooves on the side panel three. There is a threaded hole in the center of the boss for fixing the cubic satellite heat conduction plate. There are four M2.5 threaded holes on the side panel three for fixing the side panel two and the circuit control box. The light board is composed of a plurality of light bulb arrays, the light bulb surface is the front side, and the back side is the back side; the back side of the light board contacts the top board and is fixed by four M3 threaded fasteners at the four corners; the light board bus enters the circuit control box through the rectangular hole in the center of the top board and is connected to the circuit driver board; The circuit control box consists of a front frame, circuit board 1, circuit board 2, circuit board 3, circuit board 4, circuit board 5, supercapacitor, rear frame, and studs. The distance between the front frame and circuit board 1 is 10.59 mm, and the distance between circuit board 1, circuit board 2, circuit board 3, circuit board 4, and circuit board 5 is 17 mm; the front frame, circuit board 1, circuit board 2, circuit board 3, circuit board 4, circuit board 5, and rear frame are connected by M3 studs. The front frame is a rectangular cross-section frame with a rectangular cross-section beam in the middle. The cross-section beam has two M3 threaded holes for fixing the mirror holder and the front frame. The four sides of the rectangular cross-section frame have two M2.5 threaded holes for fixing the shell. There are four rounded corners at the four corners of the front frame, and four M3 threaded holes in the rounded corners are used to fix studs. The first mounting hole of the circuit board meets the CubeSat circuit board standard, and the FPC slot on the circuit board should be connected to the FPC slot on the space camera CMOS for data transmission; The second, third and fourth mounting holes of the circuit board meet the CubeSat circuit board standard and are used for light board control; The four mounting holes of the circuit board meet the standards of cubic satellite circuit boards, and several supercapacitors are welded on them for charging the light boards.

2. The payload for detecting space debris in the Earth's shadow region according to claim 1, characterized in that: The material of each component of the housing and the mirror frame is hard aluminum.

3. The payload for detecting space debris in the Earth's shadow region according to claim 1, characterized in that: The secondary mirror is made of H-K9L, and the primary and corrective mirrors are made of H-ZLaF75B.

4. The payload for detecting space debris in the Earth's shadow region according to claim 1, characterized in that: The circuit board material is FR-4.

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