Low-orbit spacecraft evades strong light irradiation method

Abstract

A method for low-Earth orbit (LEO) spacecraft to avoid intense light irradiation includes: 1. The LEO satellite initiates strong light detection of Earth according to mission requirements, and transmits the obtained telemetry information to the onboard processing unit in real time; 2. The onboard processing unit determines the validity of the telemetry information; 3. The onboard processing unit interprets the energy and azimuth vector information of the intense light, and simultaneously acquires the satellite's current mission status, solar array attitude pointing, and optical payload pointing information; 4. The intensity of the intense light energy is assessed, its damage capability to the optical payload and solar array is determined, and corresponding operations are performed; 5. After autonomous attitude avoidance and optical payload pointing adjustment are completed, the intensity of the intense light energy is further interpreted to determine whether it has been eliminated; After the threat of intense light irradiation is eliminated, the onboard processing unit receives remote control commands from the ground and initiates a new mission. This invention enables LEO satellites to avoid the threat of intense light, changing the current situation where satellites have no on-orbit protection capabilities.

Description

Technical Field

[0001] This invention relates to a method for low-Earth orbit spacecraft to avoid strong light irradiation, which is applicable to the autonomous judgment and avoidance decision of strong light irradiation during satellite flight. Background Technology

[0002] In recent years, ground-based high-intensity beam platforms, whether vehicle-mounted, shipborne, or ground-based, have rapidly developed in terms of launch energy and range, with their effective range now covering low-Earth orbit satellite platforms. Through wide-area airspace pointing and high-precision tracking and aiming, ground-based high-intensity beam platforms can rapidly and in real-time track and illuminate high-value on-orbit spacecraft, causing damage to the satellite's main optical payload and energy system.

[0003] Remote sensing satellites with optical imaging payloads as their primary payloads have optical imaging cameras with equivalent entrance pupil diameters reaching meters or larger, and optical gains of 10⁸ or higher. This increased optical gain lowers the damage threshold of the camera payload, meaning that strong, ground-based blinding light beams can cause blinding damage to the photosensitive surface of the primary payload detector within a short time. Low-energy, strong light beams incident on the primary payload camera can also lead to functional degradation and short-term saturation failure of the camera's photosensitive surface, affecting the optical mission of the primary payload.

[0004] The intense light beam can also cause permanent damage to the satellite's solar panels. Through the interaction of heat accumulation and the solar panel materials, it can produce destructive effects such as ablation and damage.

[0005] Currently, many high-value satellites are "unprotected" in terms of solar panels and optical payload protection, which is a weak link that makes them vulnerable to the threat of strong light beams. Summary of the Invention

[0006] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a method for low-orbit spacecraft to avoid strong light exposure, thereby enabling low-orbit satellites to avoid the threat of strong light and changing the current situation where satellites have no protection capabilities in orbit.

[0007] The technical solution of this invention is:

[0008] In a first aspect, the present invention proposes a method for low-Earth orbit spacecraft to avoid strong light exposure, comprising the following steps:

[0009] Step 1: According to mission requirements, the low-orbit satellite initiates strong light detection of the Earth and transmits the obtained detection telemetry information to the onboard processing unit in real time; the detection telemetry information includes strong light energy and azimuth vector information;

[0010] Step two: The onboard processing unit receives the detection telemetry information and determines the validity of the detection telemetry information;

[0011] Step 3: If the telemetry information is valid, the onboard processing unit interprets the strong light energy and azimuth vector information, and simultaneously acquires the satellite's current mission status, solar array attitude pointing, and optical payload pointing information, and then proceeds to step 4; if the telemetry information is invalid, it returns to step 2, and the onboard processing unit continues to receive telemetry information to determine its validity.

[0012] Step four: The onboard processing unit assesses the intensity of the intense light energy, determines its potential damage to the optical payload and solar array, and performs corresponding operations, specifically:

[0013] If the intensity of strong light energy is greater than or equal to the solar panel damage threshold, the on-board processing unit generates instructions to control the satellite to perform attitude avoidance and optical payload pointing adjustment.

[0014] If the intensity of strong light energy is less than the solar array damage threshold but greater than or equal to the optical payload damage threshold, the on-board processing unit generates instructions to control the satellite to perform optical payload pointing adjustment.

[0015] If the intensity of the strong light energy is less than the damage threshold of the optical payload, the on-board processing unit records the data but does not process it.

[0016] Step 5: After the autonomous attitude avoidance and optical payload pointing adjustment are completed, the on-board processing unit continues to determine whether the strong light energy has been eliminated; if the strong light energy is eliminated, that is, after the strong light irradiation threat is removed, the on-board processing unit receives the ground remote control command and starts a new mission.

[0017] Furthermore, the low-orbit satellite is equipped with a high-sensitivity omnidirectional high-intensity light detector for detecting high-intensity light on Earth.

[0018] Furthermore, the onboard processing unit determines the validity of the detected telemetry information, specifically as follows:

[0019] Determine whether the strong light energy in the telemetry information exceeds the optical payload damage threshold. If it does, the telemetry information is considered an alarm telemetry. If three consecutive alarm telemetry signals are received, the telemetry information is considered valid. Otherwise, it is considered invalid.

[0020] Furthermore, the on-board processing unit evaluates the intensity of strong light energy, specifically as follows:

[0021] Based on the transformation relationship between the satellite's orbital coordinate system, body coordinate system, and high-intensity light probe installation matrix, the high-intensity light azimuth vector, solar array normal vector, and optical payload line-of-sight pointing vector are converted to the same reference coordinate system, which facilitates the calculation of the angles |α1| between the direction of the high-intensity light azimuth vector and the direction of the solar array normal vector, and the angles |α2| between the direction of the high-intensity light azimuth vector and the direction of the optical payload line-of-sight pointing vector.

[0022] Furthermore, the coordinate system transformation specifically includes:

[0023] ① The strong light probe detects strong light illumination and calculates the azimuth angle a and elevation angle b output by the strong light in the probe coordinate system;

[0024] ② The onboard processing unit converts the azimuth angle 'a' and elevation angle 'b' into direction vectors in the satellite's body coordinate system based on the high-intensity light probe installation matrix. Simultaneously, it calculates the direction vector of the satellite's solar array normal in the satellite's body coordinate system. The specific method is as follows:

[0025] Set the satellite's coordinate system as (x T ,y T ,z T After the probes are mounted on the satellite, the rotation angle β of each probe around the Z-axis of the satellite camera's main payload is calibrated using a cubic mirror. Therefore, the transformed coordinate system is (x... S ,y S ,z S Its transformation matrix is ​​expressed as:

[0026]

[0027] Where A is the installation matrix of the high-intensity light probe;

[0028] Through the above conversion, the target angle information measured by the high-intensity light probe is converted into target angle information in the whole satellite coordinate system; the target angle information refers to the azimuth angle a and the elevation angle b.

[0029] ③ In the satellite body coordinate system, the angle α1 between the solar array normal vector and the strong light azimuth vector is calculated.

[0030] ④ Based on the optical payload mounting matrix, the direction vector of the optical payload line of sight in the satellite body coordinate system is calculated;

[0031] ⑤ Calculate the angle α2 between the optical payload line-of-sight vector and the strong light azimuth vector in the satellite body coordinate system.

[0032] Furthermore, if the intensity of the strong light energy is greater than or equal to the solar array damage threshold, the onboard processing unit generates instructions to control the satellite to perform attitude avoidance and optical payload pointing adjustment, specifically as follows:

[0033] If the intensity of strong light energy is greater than or equal to the solar panel damage threshold, the on-board processing unit generates instructions including the satellite platform attitude adjustment step size, the optical payload pointing adjustment step size, termination of the current mission, and shutdown of the optical payload. The satellite executes attitude avoidance and optical payload pointing adjustment according to the instructions, while stopping the power supply to the optical payload and stopping the current mission.

[0034] After executing the instruction to adjust the attitude, the angle between the solar array normal vector and the strong light azimuth vector is 89°≤|α1|≤91°, where the angle|α1|=90° is optimal. The solar array normal direction refers to the direction perpendicular to the plane of the solar array panel.

[0035] Furthermore, if the intensity of the strong light energy is less than the solar array damage threshold but greater than or equal to the optical payload damage threshold, the onboard processing unit generates instructions to control the satellite to perform optical payload pointing adjustments, specifically:

[0036] If the intensity of the strong light energy is less than the solar array damage threshold but greater than or equal to the optical payload damage threshold, the on-board processing unit generates instructions including optical payload pointing adjustment and payload shutdown instructions.

[0037] After the command is executed, the angle |α2| between the optical payload's line-of-sight vector and the strong light azimuth vector should not be less than the optical payload's full field of view 2θ, to ensure that strong light does not enter the optical payload's detector photosensitive surface.

[0038] Secondly, the present invention also proposes a processor for running a program, wherein the program executes the aforementioned method for low-Earth orbit spacecraft to avoid strong light irradiation.

[0039] Secondly, the present invention also proposes a non-volatile storage medium, comprising: a computer program product, which, when executed, performs the aforementioned method for avoiding strong light irradiation in low-Earth orbit spacecraft.

[0040] Fourthly, the present invention also proposes a computer program product that, when executed by a processor, implements the aforementioned method for low-Earth orbit spacecraft to avoid strong light irradiation.

[0041] The advantages of this invention compared to the prior art are:

[0042] This invention provides a satellite-to-orbit strong light threat avoidance method that introduces on-board strong light detection and autonomous avoidance protection into traditional satellite missions. Based on the acquired intensity detection information, it integrates real-time mission information, attitude information, and optical payload pointing information from the satellite platform. By fully utilizing the current on-board processing capabilities of the satellite platform, it effectively extracts information on the azimuth and damage capabilities of the irradiated strong light, fuses satellite platform status information and mission information, and generates real-time autonomous protection scheme information and protection decision commands. This forms an active and autonomous decision-making and protection capability, solving the problem of high-value satellites currently lacking protection against strong light threats. It effectively improves the survivability of on-orbit satellites facing strong light threats and fills the gap in on-orbit active avoidance and protection capabilities for satellites. Attached Figure Description

[0043] Figure 1This is a flowchart of the satellite on-orbit avoidance process of the present invention;

[0044] Figure 2 This is a schematic diagram showing the angle between the line of sight of the satellite optical payload of the present invention and the direction of the illuminating strong light. Detailed Implementation

[0045] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings.

[0046] Currently, many high-value satellites are "unprotected" in terms of solar panels and optical payload protection, representing a weak link in their vulnerability to strong light exposure. To effectively avoid potential strong light exposure threats to high-value satellites during on-orbit operation, on-orbit survivability can be improved through onboard autonomous detection, decision-making, and avoidance protection mechanisms.

[0047] Currently, there are no technologies related to autonomous defense decisions for satellites facing strong ground light threats while in orbit. This invention, through the design of autonomous detection, autonomous decision-making, and autonomous avoidance protection methods, minimizes the damage of strong light to satellite optical payloads and energy systems, effectively enhances the satellite's on-orbit survivability, and fills the gap in on-orbit threat avoidance and protection design for high-value satellites in my country.

[0048] like Figure 1 As shown, the present invention proposes a method for low-Earth orbit spacecraft to avoid strong light irradiation, comprising the following steps:

[0049] Step one: The low-Earth orbit satellite is equipped with a high-sensitivity omnidirectional high-intensity light detector for detecting high-intensity light on Earth. According to mission requirements, the low-Earth orbit satellite activates its high-intensity light detection function and transmits the obtained telemetry information to the onboard processing unit in real time; the telemetry information includes high-intensity light energy and azimuth vector information.

[0050] Step two: The onboard processing unit receives the detection telemetry information and determines the validity of the detection telemetry information;

[0051] Determine whether the strong light energy in the telemetry information exceeds the optical payload damage threshold. If it does, the telemetry information is considered an alarm telemetry. If three consecutive alarm telemetry signals are received, the telemetry information is considered valid. Otherwise, it is considered invalid.

[0052] Step 3: If the telemetry information is valid, the onboard processing unit interprets the strong light energy and azimuth vector information, and simultaneously acquires the satellite's current mission status, solar array attitude pointing, and optical payload pointing information, and then proceeds to step 4; if the telemetry information is invalid, it returns to step 2, and the onboard processing unit continues to receive telemetry information to determine its validity.

[0053] Step four: The onboard processing unit assesses the intensity of the intense light energy, determines its potential damage to the optical payload and solar array, and performs corresponding operations, specifically:

[0054] If the intensity of strong light energy is greater than or equal to the solar panel damage threshold, the on-board processing unit generates instructions to control the satellite to perform attitude avoidance and optical payload pointing adjustment.

[0055] If the intensity of strong light energy is less than the solar array damage threshold but greater than or equal to the optical payload damage threshold, the on-board processing unit generates instructions to control the satellite to perform optical payload pointing adjustment.

[0056] If the intensity of the strong light energy is less than the damage threshold of the optical payload, the on-board processing unit records the data but does not process it.

[0057] Step 5: After the autonomous attitude avoidance and optical payload pointing adjustment are completed, the on-board processing unit continues to determine whether the strong light energy has been eliminated; if the strong light energy is eliminated, that is, after the strong light irradiation threat is removed, the on-board processing unit receives the ground remote control command and starts a new mission.

[0058] When evaluating the intensity of strong light energy in the on-board processing unit, the strong light azimuth vector, solar array normal vector, and optical payload line-of-sight pointing vector are converted to the same reference coordinate system based on the transformation relationship between the satellite's orbital coordinate system, body coordinate system, and strong light probe installation matrix. This facilitates the calculation of the angles |α1| between the direction of the strong light azimuth vector and the direction of the solar array normal vector, and the angles |α2| between the direction of the strong light azimuth vector and the direction of the optical payload line-of-sight pointing vector.

[0059] The coordinate system transformation is specifically as follows:

[0060] ① The strong light probe detects strong light illumination and calculates the azimuth angle a and elevation angle b output by the strong light in the probe coordinate system;

[0061] ② The onboard processing unit converts the azimuth angle 'a' and elevation angle 'b' into direction vectors in the satellite's body coordinate system based on the high-intensity light probe installation matrix. Simultaneously, it calculates the direction vector of the satellite's solar array normal in the satellite's body coordinate system. The specific method is as follows:

[0062] Set the satellite's coordinate system as (x T ,y T ,z T After the probes are mounted on the satellite, the rotation angle β of each probe around the Z-axis of the satellite camera's main payload is calibrated using a cubic mirror. Therefore, the transformed coordinate system is (x... S ,y S ,z S Its transformation matrix is ​​expressed as:

[0063]

[0064] Where A is the installation matrix of the high-intensity light probe;

[0065] Through the above conversion, the target angle information measured by the high-intensity light probe is converted into target angle information in the whole satellite coordinate system; the target angle information refers to the azimuth angle a and the elevation angle b.

[0066] ③ In the satellite body coordinate system, the angle α1 between the solar array normal vector and the strong light azimuth vector is calculated.

[0067] ④ Based on the optical payload mounting matrix, the direction vector of the optical payload line of sight in the satellite body coordinate system is calculated;

[0068] ⑤ Calculate the angle α2 between the optical payload line-of-sight vector and the strong light azimuth vector in the satellite body coordinate system.

[0069] The onboard processing unit determines the intensity of the strong light and, based on known threshold information, assesses the potential damage to the optical payload and solar array from the current strong light irradiation. If the strong light irradiation damage threshold exceeds the solar array damage threshold, the onboard processing unit generates commands to control the satellite to perform attitude avoidance and optical payload pointing adjustments, specifically:

[0070] If the intensity of strong light energy is greater than or equal to the solar panel damage threshold, the on-board processing unit generates instructions including the satellite platform attitude adjustment step size, the optical payload pointing adjustment step size, termination of the current mission, and shutdown of the optical payload. The satellite executes attitude avoidance and optical payload pointing adjustment according to the instructions, while stopping the power supply to the optical payload and stopping the current mission.

[0071] After executing this command to adjust the attitude, the angle between the solar array normal vector and the strong light azimuth vector should be 89°≤|α1|≤91°, where the optimal angle is |α1|=90°. The solar array normal vector refers to the direction perpendicular to the plane of the solar panel. The angle |α1| is as follows: Figure 2 As shown.

[0072] If the intensity of the strong light is less than the solar array damage threshold but greater than or equal to the optical payload damage threshold, the onboard processing unit generates instructions to control the satellite to perform optical payload pointing adjustment. Specifically, if the intensity of the strong light is less than the solar array damage threshold but greater than or equal to the optical payload damage threshold, the onboard processing unit generates instructions including optical payload pointing adjustment and payload shutdown instructions. After the instructions are executed, the angle |α2| between the optical payload's line-of-sight vector and the strong light's azimuth vector should not be less than the optical payload's full field of view angle 2θ, ensuring that the strong light does not enter the photosensitive surface of the optical payload detector. The angle |α2| is as follows: Figure 2 As shown.

[0073] After autonomous attitude avoidance and optical payload pointing adjustments are completed, the onboard processing unit continues to determine whether the strong light threat has been eliminated. Once the strong light threat is resolved, the onboard processing unit receives remote control commands from the ground and initiates a new mission.

[0074] The parts of this invention not described in detail are common knowledge to those skilled in the art.

Claims

1. A method for low-Earth orbit spacecraft to avoid strong light irradiation, characterized in that... include: Step 1: According to mission requirements, the low-orbit satellite initiates strong light detection of the Earth and transmits the obtained detection telemetry information to the onboard processing unit in real time; the detection telemetry information includes strong light energy and azimuth vector information; Step two: The onboard processing unit receives the detection telemetry information and determines the validity of the detection telemetry information; Step 3: If the telemetry information is valid, the onboard processing unit interprets the strong light energy and azimuth vector information, and simultaneously acquires the satellite's current mission status, solar array attitude pointing, and optical payload pointing information, and then proceeds to step 4; if the telemetry information is invalid, it returns to step 2, and the onboard processing unit continues to receive telemetry information to determine its validity. Step four: The onboard processing unit assesses the intensity of the intense light energy, determines its potential damage to the optical payload and solar array, and performs corresponding operations, specifically: If the intensity of strong light energy is greater than or equal to the solar panel damage threshold, the on-board processing unit generates instructions to control the satellite to perform attitude avoidance and optical payload pointing adjustment. If the intensity of strong light energy is less than the solar array damage threshold but greater than or equal to the optical payload damage threshold, the on-board processing unit generates instructions to control the satellite to perform optical payload pointing adjustment. If the intensity of the strong light energy is less than the damage threshold of the optical payload, the on-board processing unit records the data but does not process it. Step 5: After the autonomous attitude avoidance and optical payload pointing adjustment are completed, the on-board processing unit continues to determine whether the strong light energy has been eliminated; if the strong light energy is eliminated, that is, after the strong light irradiation threat is removed, the on-board processing unit receives the ground remote control command and starts a new mission.

2. The method for low-Earth orbit spacecraft to avoid strong light irradiation according to claim 1, characterized in that: The low-orbit satellite is equipped with a high-sensitivity omnidirectional high-intensity light detector for detecting strong light on Earth.

3. A method for low-Earth orbit spacecraft to avoid strong light exposure according to claim 1, characterized in that: The onboard processing unit determines the validity of the telemetry information by: Determine whether the strong light energy in the telemetry information exceeds the optical payload damage threshold. If it does, the telemetry information is considered an alarm telemetry. If three consecutive alarm telemetry signals are received, the telemetry information is considered valid. Otherwise, it is considered invalid.

4. A method for low-Earth orbit spacecraft to avoid strong light irradiation according to claim 1, characterized in that: The on-board processing unit evaluates the intensity of strong light energy specifically as follows: Based on the transformation relationship between the satellite's orbital coordinate system, body coordinate system, and high-intensity light probe installation matrix, the high-intensity light azimuth vector, solar array normal vector, and optical payload line-of-sight pointing vector are converted to the same reference coordinate system, which facilitates the calculation of the angles |α1| between the direction of the high-intensity light azimuth vector and the direction of the solar array normal vector, and the angles |α2| between the direction of the high-intensity light azimuth vector and the direction of the optical payload line-of-sight pointing vector.

5. A method for low-Earth orbit spacecraft to avoid strong light irradiation according to claim 4, characterized in that: The coordinate system transformation is specifically as follows: ① The strong light probe detects strong light illumination and calculates the azimuth angle a and elevation angle b output by the strong light in the probe coordinate system; ② The onboard processing unit converts the azimuth angle 'a' and elevation angle 'b' into direction vectors in the satellite's body coordinate system based on the high-intensity light probe installation matrix. Simultaneously, it calculates the direction vector of the satellite's solar array normal in the satellite's body coordinate system. The specific method is as follows: Set the satellite's coordinate system as (x T ,y T ,z T After the probes are mounted on the satellite, the rotation angle β of each probe around the Z-axis of the satellite camera's main payload is calibrated using a cubic mirror. Therefore, the transformed coordinate system is (x... S ,y S ,z S Its transformation matrix is ​​expressed as: Where A is the installation matrix of the high-intensity light probe; Through the above conversion, the target angle information measured by the high-intensity light probe is converted into target angle information in the whole satellite coordinate system; the target angle information refers to the azimuth angle a and the elevation angle b. ③ In the satellite body coordinate system, the angle α1 between the solar array normal vector and the strong light azimuth vector is calculated. ④ Based on the optical payload mounting matrix, the direction vector of the optical payload line of sight in the satellite body coordinate system is calculated; ⑤ Calculate the angle α2 between the optical payload line-of-sight vector and the strong light azimuth vector in the satellite body coordinate system.

6. A method for low-Earth orbit spacecraft to avoid strong light irradiation according to claim 4, characterized in that: If the intensity of the strong light energy is greater than or equal to the solar array damage threshold, the onboard processing unit generates instructions to control the satellite to perform attitude avoidance and optical payload pointing adjustment, specifically: If the intensity of strong light energy is greater than or equal to the solar panel damage threshold, the on-board processing unit generates instructions including the satellite platform attitude adjustment step size, the optical payload pointing adjustment step size, termination of the current mission, and shutdown of the optical payload. The satellite executes attitude avoidance and optical payload pointing adjustment according to the instructions, while stopping the power supply to the optical payload and stopping the current mission. After executing the instruction to adjust the attitude, the angle between the solar array normal vector and the strong light azimuth vector is 89°≤|α1|≤91°, where the angle|α1|=90° is optimal. The solar array normal direction refers to the direction perpendicular to the plane of the solar array panel.

7. A method for low-Earth orbit spacecraft to avoid strong light irradiation according to claim 4, characterized in that: If the intensity of the strong light energy is less than the solar array damage threshold but greater than or equal to the optical payload damage threshold, the onboard processing unit generates a command to control the satellite to perform optical payload pointing adjustment, specifically: If the intensity of the strong light energy is less than the solar array damage threshold but greater than or equal to the optical payload damage threshold, the on-board processing unit generates instructions including optical payload pointing adjustment and payload shutdown instructions. After the command is executed, the angle |α2| between the optical payload's line-of-sight vector and the strong light azimuth vector should not be less than the optical payload's full field of view 2θ, to ensure that strong light does not enter the optical payload's detector photosensitive surface.

8. A processor, characterized in that, The processor is used to run a program, wherein the program executes a method for low-Earth orbit spacecraft to avoid strong light irradiation as described in any one of claims 1 to 7.

9. A non-volatile storage medium, characterized in that, include: A computer program product that, when executed, performs a method for avoiding strong light irradiation in a low-Earth orbit spacecraft as described in any one of claims 1 to 7.

10. A computer program product, characterized in that, When the computer program is executed by the processor, it implements the method for avoiding strong light irradiation of a low-orbit spacecraft as described in any one of claims 1 to 7.

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