Low-orbit verification satellite

Abstract

The invention discloses a low-orbit verification satellite, and relates to the technical field of satellites, and the satellite comprises a satellite main body which is of a flat structure, is provided with a front surface and a back surface, is provided with an attitude orbit control system, and is used for driving the satellite main body to overturn through the attitude orbit control system; the verification load is mounted on the front surface of the satellite main body; the back load is mounted on the back surface of the satellite main body; the solar sailboard is connected with the satellite main body through a sailboard driving device, and the sailboard driving device is used for driving the solar sailboard to turn over; according to the technical scheme, after the verification task is completed, the satellite main body performs attitude overturning through the attitude orbit control system, the solar panel is overturned through the panel driving device, and the back load of the satellite main body is started, so that the redundant value of the verification satellite can be fully utilized, and the service life of the satellite is effectively prolonged. The method not only reduces the cost of a single task, but also greatly improves the utilization efficiency and economic benefits of verification satellites.

Description

Technical Field

[0001] This invention relates to the field of satellite technology, and more specifically to a low-Earth orbit verification satellite. Background Technology

[0002] The verification payloads of low-Earth orbit verification satellites are dedicated devices designed specifically for testing core technologies of subsequent large-scale constellations. Their core objective is to verify the feasibility, stability, and compatibility of key technologies in advance, avoiding risks during subsequent network deployment. These payloads are not the final operational payloads, but rather focus on "technology trial and error and parameter calibration," and can be specifically divided into four core categories.

[0003] I. Communication and Network Verification Payload: Core verification of "space-ground / inter-satellite interconnection capability".

[0004] These payloads are the core verification targets for low-Earth orbit communication constellations, focusing on testing signal transmission, protocol adaptation, and the feasibility of network architecture, which directly determines the communication quality of subsequent constellations.

[0005] II. Inter-satellite link verification payload: The core verification is the "autonomous networking capability between satellites".

[0006] Inter-satellite links are key to achieving "seamless global coverage" for low-Earth orbit constellations (without relying on ground gateway stations), and their payloads focus on verifying link establishment speed, transmission rate, and stability.

[0007] III. Platform Performance Verification Payload: The core verification is "the stable operation capability of the satellite platform".

[0008] The energy, attitude, and propulsion systems of low-Earth orbit satellite platforms directly affect their lifespan and operational efficiency. These payloads focus on "reliability testing of key subsystems of the platform".

[0009] IV. Space Environment Adaptation Payload: Core verification of "the satellite's tolerance to low-Earth orbit environment".

[0010] Low Earth orbit (200-2000km) space presents risks such as radiation, atmospheric drag, and space debris. These payloads are used to test the environmental adaptability and safety redundancy of satellites.

[0011] The verification payloads of low-Earth orbit (LEO) verification satellites are essentially "scaled-down" and "test versions" of key technologies for subsequent constellations. Each payload corresponds to a core technical problem to be solved. By obtaining real data through on-orbit testing, they "clear the mines" for payload design in mass-produced satellites. For example, the laser inter-satellite link payload verifies "whether high-speed networking can be achieved," and the radiation-resistant payload verifies "whether the equipment can survive for a long time." This data directly determines the technical roadmap and cost control of subsequent constellations.

[0012] After the communication technology verification mission, originally scheduled for 1-2 years, was completed, the satellite platform and its various systems were in good working order and the satellite still had great utilization value. However, because the mission was completed, its redundancy value was not utilized, resulting in economic and technological waste. Summary of the Invention

[0013] In view of this, the present invention provides a low-Earth orbit verification satellite to solve the problem that the redundancy value of existing low-Earth orbit verification satellites is not utilized.

[0014] The low-Earth orbit verification satellite provided by this invention includes: The satellite body has a flat structure with a front and a back. An attitude and orbit control system is installed on the satellite body, which is used to drive the satellite body to flip. The verification payload is mounted on the front of the satellite body; The back-mounted payload is installed on the back of the satellite body; The solar panel is connected to the satellite body via a solar panel drive device, which is used to drive the solar panel to rotate.

[0015] The low-Earth orbit (LEO) verification satellite provided by this invention utilizes a LEO verification satellite architecture, with a payload mounted on the back of the satellite body opposite the verification payload. After the originally planned short-term technical verification mission is completed, the satellite attitude is flipped, and the solar panels are flipped by the Solar Actuation and Activation (SADA) device to activate the back payload on the back of the satellite body. In this way, the redundancy value of the verification satellite is utilized to extend the satellite's service life. It shares a single satellite body including thermal control, energy, attitude and orbit control, structure, telemetry and control, and launch resources.

[0016] Optionally, the actuator of the attitude and orbit control system includes at least a momentum wheel and a magnetic torque generator. The momentum wheel drives the satellite to adjust its attitude by changing its own angular momentum. The magnetic torque generator changes its own magnetic moment by controlling the magnitude and direction of the coil current, and then interacts with the Earth's magnetic field to generate torque, thereby adjusting the satellite's attitude.

[0017] Optionally, the solar panels are connected to two symmetrical sides of the satellite body.

[0018] Optionally, the solar panel has multiple foldable sections.

[0019] Optionally, the solar panels are folded and stacked on the front of the satellite body.

[0020] Optionally, the back load has multiple foldable panels.

[0021] Optionally, the panel is folded and unfolded parallel to the back of the satellite body.

[0022] Optionally, the unfolded portion of the panel extends beyond both sides of the satellite body.

[0023] Optionally, solar panels are connected to the two symmetrical sides of the satellite body, and the extension direction of the unfolded panels is perpendicular to the extension direction of the solar panels.

[0024] Optionally, the satellite body has two long sides, and solar panels are connected to the two long sides respectively.

[0025] The technical solution of this invention, after completing the verification mission, involves the satellite body undergoing attitude rotation via the attitude and orbit control system, and the solar panels rotating via the panel drive device. After activating the payload on the back of the satellite body, the redundancy value of the verification satellite can be fully utilized, effectively extending its operational lifespan. This method not only reduces the cost per mission but also significantly improves the utilization efficiency and economic benefits of the verification satellite. Attached Figure Description

[0026] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 This is a top view of a low-orbit verification satellite according to an embodiment of the present invention; Figure 2 for Figure 1 A bottom view; Figure 3 for Figure 1 The image shown is a 3D view of the solar panel after it has been folded. Figure 4 for Figure 3 A three-dimensional diagram viewed from below; Figure 5 A perspective view of a low-Earth orbit verification satellite performing a verification mission according to an embodiment of the present invention; Figure 6 This is a three-dimensional view of the redundancy utilization of a low-orbit verification satellite according to an embodiment of the present invention.

[0028] Explanation of reference numerals in the attached figures: 1. Satellite body; 2. Solar panel; 3. Back payload; 4. Solar panel drive unit; 5. Verification payload. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for 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 the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0031] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0032] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0033] like Figure 1 , Figure 2 The image shows a specific implementation of a low-Earth orbit verification satellite provided in this embodiment, comprising: a satellite body 1, a verification payload 5, a back payload 3, a solar panel drive device 4, and a solar panel 2. The satellite body 1 has a flat structure with a front and a back. An attitude and orbit control system is installed on the satellite body 1, which drives the satellite body 1 to rotate. The verification payload 5 is installed on the front of the satellite body 1, and the back payload 3 is installed on the back of the satellite body 1. The solar panel 2 is connected to the satellite body 1 through the solar panel drive device 4, which drives the solar panel 2 to rotate.

[0034] The low-Earth orbit verification satellite provided in this embodiment, after completing its verification mission, performs attitude rotation via the attitude and orbit control system. The solar panels rotate via the panel drive device, and the back payload 3 is activated. This allows for full utilization of the verification satellite's redundancy, effectively extending its operational lifespan. This approach not only reduces the cost per mission but also significantly improves the utilization efficiency and economic benefits of the verification satellite.

[0035] In some embodiments, the actuator of the attitude and orbit control system includes at least a momentum wheel and a magnetic torque generator. The momentum wheel drives the satellite to adjust its attitude by changing its own angular momentum. The magnetic torque generator changes its own magnetic moment by controlling the magnitude and direction of the coil current, and then interacts with the Earth's magnetic field to generate torque, thereby adjusting the satellite's attitude.

[0036] It should be noted that the solar panel drive device 4 is a common type in the prior art. Specifically, the solar panel drive device (SADA), as a key core component of the spacecraft energy system, achieves the solar panel's solar orientation control and energy transfer functions through high-precision mechatronics design.

[0037] In some embodiments, the solar panel 2 has multiple foldable panels. When deployed, the multiple panels can cover a larger area, thereby increasing the effective light-receiving area for the satellite to receive solar energy.

[0038] like Figure 3 , Figure 4 As shown, in some embodiments, the solar panel 2 is folded and stacked on the front of the satellite body 1. When folded, the solar panel 2 provides some protection for the verification payload 5. Simultaneously, this layout simplifies the satellite structural design, reduces the need for additional protective devices or complex fixing structures, and lowers the satellite's weight and manufacturing cost.

[0039] like Figure 4 , Figure 5 As shown, in some embodiments, the back payload 3 has multiple foldable panels. During satellite launch, these panels can be folded up, significantly reducing the overall volume. During satellite launch, the space inside the rocket fairing is limited; the compact folding structure allows the back payload 3 to better fit this space, ensuring a successful satellite launch. After the satellite enters orbit, the multiple foldable panels can unfold in an orderly manner according to a preset program.

[0040] It should be noted that the back-mount 3 can be a synthetic aperture radar, or it can be a camera, antennas of different frequency bands (such as KA antennas, KU antennas), etc.

[0041] like Figure 5As shown, in some embodiments, the panel is folded and unfolded parallel to the back of the satellite body 1, and when folded, it fits the back of the satellite body 1, which enables the satellite to maintain a relatively regular shape during the launch phase and provides a certain degree of protection for the back load 3.

[0042] When a satellite is launched by a rocket, the space in the fairing is limited. This parallel folding method can minimize the space volume occupied by the satellite inside the rocket fairing.

[0043] like Figure 6 As shown, in some embodiments, the deployed portion of the synthetic aperture radar extends beyond both sides of the satellite body 1. This configuration significantly increases the effective antenna aperture. The larger aperture formed by the combination of multiple panels improves the radar's spatial resolution. For example, when monitoring ground infrastructure such as roads and bridges, the higher resolution can clearly distinguish lane lines and structural details of bridges, providing accurate data for infrastructure assessment. Simultaneously, the larger antenna aperture also helps to increase the radar's detection range, enabling coverage of a wider area.

[0044] like Figure 6 As shown, in some embodiments, solar panels 2 are each connected to one of the two symmetrical sides of the satellite body 1, and the synthetic aperture radar extends perpendicularly to the extension direction of the solar panels 2 after deployment. This arrangement can fully and rationally utilize the space resources on the satellite surface.

[0045] The synthetic aperture radar is deployed perpendicular to the solar panel 2, cleverly avoiding spatial conflict with the panel. In this way, both can occupy suitable positions on the limited satellite surface without interfering with each other, effectively improving the compactness and rationality of the overall satellite layout.

[0046] Working principle: like Figure 5 As shown, the low-orbit verification satellite provided in this embodiment adjusts the verification payload 5 on the front of the satellite body 1 to the ground through the attitude and orbit control system when carrying out verification missions.

[0047] like Figure 6 As shown, after completing the verification mission, the low-orbit verification satellite provided in this embodiment flips the satellite body 1 through the attitude and orbit control system, so that the back load 3 on the back of the satellite body 1 is aligned with the ground; at the same time, the solar panels are flipped through the solar panel drive device (SADA), and the satellite continues to carry out the next stage of its work mission.

[0048] Although embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations all fall within the scope defined by the present invention.

Claims

1. A low-Earth orbit verification satellite, characterized in that, include: The satellite body (1) has a flat structure with a front and a back. An attitude and orbit control system is provided on the satellite body (1), which is used to drive the satellite body (1) to flip. The verification payload (5) is mounted on the front of the satellite body (1); The back load (3) is mounted on the back of the satellite body (1); The solar panel (2) is connected to the satellite body (1) via a solar panel drive device (4), which is used to drive the solar panel (2) to rotate.

2. The low-Earth orbit verification satellite according to claim 1, characterized in that, The actuators of the attitude and orbit control system include at least a momentum wheel and a magnetic torque generator. The momentum wheel drives the satellite to adjust its attitude by changing its own angular momentum. The magnetic torque generator changes its own magnetic moment by controlling the magnitude and direction of the coil current, and then interacts with the Earth's magnetic field to generate torque, thereby adjusting the satellite's attitude.

3. The low-Earth orbit verification satellite according to claim 1, characterized in that, The solar panel (2) is connected to the two symmetrical sides of the satellite body (1).

4. The low-Earth orbit verification satellite according to claim 3, characterized in that, The solar panel (2) has multiple foldable sections.

5. The low-Earth orbit verification satellite according to claim 4, characterized in that, The solar panel (2) is folded and stacked on the front of the satellite body (1).

6. The low-Earth orbit verification satellite according to claim 1, characterized in that, The back load (3) has multiple foldable panels.

7. The low-Earth orbit verification satellite according to claim 6, characterized in that, The panel, when folded and unfolded, is parallel to the back of the satellite body (1).

8. The low-Earth orbit verification satellite according to claim 7, characterized in that, The unfolded portion of the panel extends out to both sides of the satellite body (1).

9. The low-Earth orbit verification satellite according to claim 8, characterized in that, The satellite body (1) is connected to two symmetrical sides with solar panels (2), and the extension direction of the panel after it is unfolded is perpendicular to the extension direction of the solar panel (2).

10. The low-Earth orbit verification satellite according to any one of claims 1-9, characterized in that, The satellite body (1) has two long sides, and solar panels (2) are connected to the two long sides respectively.

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