Method for avoiding strong light irradiation of low-orbit spacecraft

Abstract

A method for avoiding strong light irradiation of a low-orbit spacecraft comprises the steps that 1, a low-orbit satellite starts ground strong light detection according to task requirements, and obtained detection telemetry information is sent to an on-satellite processing unit in real time; 2, the on-satellite processing unit judges and detects the effectiveness of the telemetry information; 3, the on-satellite processing unit interprets strong light energy and azimuth vector information, and obtains the current task state of the satellite, the solar wing attitude pointing information and the optical load pointing information at the same time; 4, evaluating the energy intensity of the strong light, judging the damage capability to the optical load and the solar wing, and carrying out corresponding operation; 5, after autonomous attitude avoidance and optical load pointing adjustment are completed, whether the strong light energy is eliminated or not continues to be judged; and after the strong light irradiation threat is relieved, the satellite-borne processing unit receives a ground remote control instruction and starts a new task. According to the method, the low-orbit satellite can avoid the threat of strong light, and the current situation that the current satellite has no prevention and resistance capability in orbit is changed.

Description

Technical Field

[0001] The present invention relates to a method for avoiding strong light exposure for a low-orbit spacecraft, which is applicable to autonomous judgment and autonomous avoidance decision-making on strong light exposure during the satellite's on-orbit flight. Background Art

[0002] In recent years, ground-based high-intensity beam platforms, whether vehicle-mounted, ship-mounted, or ground-based, have rapidly advanced in terms of emission power and range, reaching the range of low-orbit satellite platforms. Through wide-area pointing and high-precision tracking and targeting, these platforms can rapidly track and illuminate high-value in-orbit spacecraft in real time, potentially damaging the satellite's primary optical payload and energy systems.

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

[0004] Strong light beams can also directly cause permanent damage to the satellite's solar panels, and through the interaction of heat accumulation with the solar panel materials, produce lethal and destructive effects such as ablation and damage.

[0005] At present, many high-value satellites are in an "unprotected" state in terms of solar array and optical payload protection, which is a weak link in the threat of strong light beam exposure faced by high-value satellites. Summary of the Invention

[0006] The technical problem solved by the present invention is: to overcome the shortcomings of the existing technology, to provide a method for low-orbit spacecraft to avoid strong light exposure, to enable low-orbit satellites to avoid the threat of strong light, and to change the current situation where satellites have no defense capability in orbit.

[0007] The technical solution of the present invention is:

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

[0009] Step 1: The low-orbit satellite starts strong light detection on the ground according to the mission requirements and sends 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 2: The onboard processing unit receives the detection telemetry information and determines the validity of the detection telemetry information;

[0011] In step 3, if the detection telemetry information is valid, the onboard processing unit interprets the glare energy and azimuth vector information, and simultaneously obtains the satellite's current mission status, solar array attitude and pointing, and optical payload pointing information, and then proceeds to step 4. If the detection telemetry information is invalid, the process returns to step 2, and the onboard processing unit continues to receive the detection telemetry information to determine its validity.

[0012] Step 4: The onboard processing unit evaluates the intensity of the strong light energy, determines the damage potential to the optical payload and solar panels, and performs corresponding operations. Specifically:

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

[0014] If the intensity of the strong light energy is less than the solar panel damage threshold and greater than or equal to the optical payload damage threshold, the onboard processing unit generates an instruction to control the satellite to perform optical payload pointing adjustment;

[0015] If the intensity of the strong light energy is less than the optical payload damage threshold, the onboard 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 onboard processing unit continues to judge whether the strong light energy has been eliminated; if the strong light energy has been eliminated, that is, the strong light illumination threat has been lifted, the onboard processing unit receives the ground remote control command and starts a new mission.

[0017] Furthermore, low-orbit satellites are equipped with high-sensitivity omnidirectional strong light probes for detecting strong light on the ground.

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

[0019] Determine whether the strong light energy in the detection telemetry information exceeds the optical payload damage threshold. If it does, the detection telemetry information is considered to be alarm telemetry. If the alarm telemetry is received three times in a row, the detection telemetry information is determined to be valid; otherwise, it is determined to be invalid.

[0020] Furthermore, the onboard processing unit evaluates the intensity of the strong light energy, specifically:

[0021] According to the conversion relationship between the satellite's orbital coordinate system, body coordinate system and strong light probe installation matrix, the strong light azimuth vector, solar wing normal vector and optical payload line of sight pointing vector are converted to the same reference coordinate system, which facilitates the calculation of the angle ∣α1∣ between the strong light azimuth vector and the solar wing normal vector, and the angle ∣α2∣ between the strong light azimuth vector and the optical payload line of sight pointing vector.

[0022] Furthermore, the coordinate system transformation is as follows:

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

[0024] ② The onboard processing unit converts the azimuth angle a and the pitch angle b into the direction vector in the satellite coordinate system according to the strong light probe installation matrix, and calculates the direction vector of the normal direction vector of the satellite solar panel in the satellite coordinate system. The specific method is as follows:

[0025] Set the satellite body coordinate system to (x T ,y T ,z T ), after the probe is mounted on the satellite, the rotation angle β of each probe around the Z axis of the satellite camera main payload is calibrated by the cubic mirror, so the coordinate system after conversion is (x S ,y S ,z S ), its transformation matrix is ​​expressed as:

[0026]

[0027] Where A is the installation matrix of the strong light probe;

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

[0029] ③ In the satellite coordinate system, calculate the angle ∣α1∣ between the normal direction vector of the solar wing and the glare azimuth vector;

[0030] ④ According to the optical payload installation matrix, calculate the direction vector of the optical payload line of sight in the satellite coordinate system;

[0031] ⑤ Calculate the angle ∣α2∣ between the optical payload's visual axis direction vector and the strong light azimuth vector in the satellite's coordinate system.

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

[0033] If the intensity of the strong light energy is greater than or equal to the solar panel damage threshold, the onboard processing unit generates an instruction containing the satellite platform attitude adjustment step, the optical payload pointing adjustment step, and the termination of the current mission and the shutdown of the optical payload. The satellite performs attitude avoidance and optical payload pointing adjustment according to the instruction, and at the same time stops the power supply to the optical payload and stops the current mission.

[0034] After executing this instruction to adjust the attitude, the angle between the normal direction vector of the solar wing and the directional vector of the strong light is 89°≤|α1|≤91°, among which the angle|α1|=90° is the best. The normal direction of the solar wing refers to the direction perpendicular to the plane of the solar panel.

[0035] Furthermore, if the intensity of the strong light energy is less than the solar wing damage threshold and greater than or equal to the optical payload damage threshold, the onboard processing unit generates an instruction to control the satellite to perform optical payload pointing adjustment, specifically:

[0036] If the intensity of the strong light energy is less than the solar panel damage threshold and 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;

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

[0038] In a second aspect, the present invention further proposes a processor, which is used to run a program, wherein the program, when running, executes the method for avoiding strong light exposure for a low-orbit spacecraft.

[0039] In a second aspect, the present invention further proposes a non-volatile storage medium, comprising: a computer program product, which, when executed, executes the method for a low-orbit spacecraft to avoid strong light exposure.

[0040] In a fourth aspect, the present invention further proposes a computer program product, which, when executed by a processor, implements the method for a low-orbit spacecraft to avoid strong light exposure.

[0041] The beneficial effects of the present invention compared with the prior art are:

[0042] The present invention provides a method for avoiding strong light threats on satellites in orbit. This method incorporates onboard strong light detection and autonomous avoidance protection into traditional satellite missions. Based on acquired intensity detection information, the method integrates the satellite platform's real-time mission information, attitude information, and optical payload pointing information, fully utilizing the current satellite platform's onboard processing capabilities to effectively extract strong light azimuth information and damage capability information. The method integrates satellite platform status information and mission information to generate satellite autonomous protection plan information and protection decision instructions in real time, establishing proactive autonomous decision-making and protection capabilities. This method addresses the current problem of high-value satellites lacking protection against strong light threats, effectively improving the survivability of on-orbit satellites facing strong light threats and filling the gap in satellite proactive avoidance and protection capabilities. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0044] Figure 2 Schematic diagram of the included angle between the visual axis direction and the irradiated strong light direction of the satellite optical payload of the present invention. DETAILED DESCRIPTION

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

[0046] Currently, many high-value satellites are left defenseless in terms of their solar arrays and optical payloads, presenting a vulnerable link to the threat of intense sunlight exposure. To effectively mitigate the potential threat of intense sunlight exposure to high-value satellites during in-orbit operation, autonomous detection, decision-making, and avoidance measures are being implemented onboard to enhance the satellite's on-orbit survivability.

[0047] At present, there is no relevant technology for autonomous defense decision-making when satellites are in orbit facing the threat of strong light from the ground. The present invention, through the design of autonomous detection, autonomous decision-making and autonomous avoidance protection methods, can minimize the damage caused by strong light to the satellite's optical payload and energy system, effectively improve the satellite's on-orbit survivability, and fill the gap in the on-orbit threat avoidance protection design of my country's high-value satellites.

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

[0049] Step 1: The low-orbit satellite is equipped with a high-sensitivity omnidirectional strong light probe for detecting strong light on the ground. According to the mission requirements, the low-orbit satellite starts strong light detection on the ground and sends 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;

[0050] Step 2: 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 detection telemetry information exceeds the optical payload damage threshold. If it does, the detection telemetry information is considered to be alarm telemetry. If the alarm telemetry is received three times in a row, the detection telemetry information is determined to be valid; otherwise, it is determined to be invalid.

[0052] In step 3, if the detection telemetry information is valid, the onboard processing unit interprets the glare energy and azimuth vector information, and simultaneously obtains the satellite's current mission status, solar array attitude and pointing, and optical payload pointing information, and then proceeds to step 4. If the detection telemetry information is invalid, the process returns to step 2, and the onboard processing unit continues to receive the detection telemetry information to determine its validity.

[0053] Step 4: The onboard processing unit evaluates the intensity of the strong light energy, determines the damage potential to the optical payload and solar panels, and performs corresponding operations. Specifically:

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

[0055] If the intensity of the strong light energy is less than the solar panel damage threshold and greater than or equal to the optical payload damage threshold, the onboard processing unit generates an instruction to control the satellite to perform optical payload pointing adjustment;

[0056] If the intensity of the strong light energy is less than the optical payload damage threshold, the onboard 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 onboard processing unit continues to judge whether the strong light energy has been eliminated; if the strong light energy has been eliminated, that is, the strong light illumination threat has been lifted, the onboard processing unit receives the ground remote control command and starts a new mission.

[0058] When the onboard processing unit evaluates the intensity of the strong light energy, the strong light azimuth vector, the solar wing normal vector and the optical payload line of sight pointing vector are converted to the same reference coordinate system according to the conversion relationship between the satellite's orbital coordinate system, the body coordinate system and the strong light probe installation matrix, so as to facilitate the calculation of the angle ∣α1∣ between the direction of the strong light azimuth vector and the direction of the solar wing normal vector, and the angle ∣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 as follows:

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

[0061] ② The onboard processing unit converts the azimuth angle a and the pitch angle b into the direction vector in the satellite coordinate system according to the strong light probe installation matrix, and calculates the direction vector of the normal direction vector of the satellite solar panel in the satellite coordinate system. The specific method is as follows:

[0062] Set the satellite body coordinate system to (x T ,y T ,z T ), after the probe is mounted on the satellite, the rotation angle β of each probe around the Z axis of the satellite camera main payload is calibrated by the cubic mirror, so the coordinate system after conversion is (x S ,y S ,z S ), its transformation matrix is ​​expressed as:

[0063]

[0064] Where A is the installation matrix of the strong light probe;

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

[0066] ③ In the satellite coordinate system, calculate the angle ∣α1∣ between the normal direction vector of the solar wing and the glare azimuth vector;

[0067] ④ According to the optical payload installation matrix, calculate the direction vector of the optical payload line of sight in the satellite coordinate system;

[0068] ⑤ Calculate the angle ∣α2∣ between the optical payload's visual axis direction vector and the strong light azimuth vector in the satellite's coordinate system.

[0069] The onboard processing unit interprets the intensity of the strong light and determines the damage potential of the current strong light exposure to the optical payload and the solar array based on the known threshold information. If the strong light exposure damage threshold is greater than 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:

[0070] If the intensity of the strong light energy is greater than or equal to the solar panel damage threshold, the onboard processing unit generates an instruction containing the satellite platform attitude adjustment step, the optical payload pointing adjustment step, and the termination of the current mission and the shutdown of the optical payload. The satellite performs attitude avoidance and optical payload pointing adjustment according to the instruction, and at the same time stops the power supply to the optical payload and stops the current mission.

[0071] After executing this instruction to adjust the attitude, the angle between the normal direction vector of the solar wing and the directional vector of the strong light is 89°≤|α1|≤91°, where the angle|α1|=90° is the best. The normal direction of the solar wing refers to the direction perpendicular to the plane of the solar wing panel. The angle|α1| is as follows: Figure 2 shown.

[0072] If the intensity of the strong light energy is less than the solar wing damage threshold and greater than or equal to the optical payload damage threshold, the onboard processing unit generates an instruction to control the satellite to perform optical payload pointing adjustment. Specifically, if the intensity of the strong light energy is less than the solar wing damage threshold and 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 between the optical payload's line of sight direction vector and the strong light azimuth vector |α2| should not be less than the full field of view angle 2θ of the optical payload, ensuring that the strong light does not enter the optical payload detector's photosensitive surface. Angle |α2| such as Figure 2 shown.

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

[0074] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. A method for avoiding strong light exposure for low-orbit spacecraft, characterized in that include: Step 1: The low-orbit satellite starts strong light detection on the ground according to the mission requirements and sends 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 2: The onboard processing unit receives the detection telemetry information and determines the validity of the detection telemetry information; In step 3, if the detection telemetry information is valid, the onboard processing unit interprets the glare energy and azimuth vector information, and simultaneously obtains the satellite's current mission status, solar array attitude and pointing, and optical payload pointing information, and then proceeds to step 4. If the detection telemetry information is invalid, the process returns to step 2, and the onboard processing unit continues to receive the detection telemetry information to determine its validity. Step 4: The onboard processing unit evaluates the intensity of the strong light energy, determines the damage potential to the optical payload and solar panels, and performs corresponding operations. Specifically: If the intensity of the strong light energy is greater than or equal to the solar panel damage threshold, the onboard processing unit generates instructions to control the satellite to perform attitude avoidance and optical payload pointing adjustment; If the intensity of the strong light energy is less than the solar panel damage threshold and greater than or equal to the optical payload damage threshold, the onboard processing unit generates an instruction to control the satellite to perform optical payload pointing adjustment; If the intensity of the strong light energy is less than the optical payload damage threshold, the onboard 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 onboard processing unit continues to judge whether the strong light energy has been eliminated; if the strong light energy has been eliminated, that is, the strong light illumination threat has been lifted, the onboard processing unit receives the ground remote control command and starts a new mission.

2. The method for avoiding strong light exposure for a low-orbit spacecraft according to claim 1, characterized in that: Low-orbit satellites are equipped with high-sensitivity omnidirectional strong light probes for detecting strong light on the ground.

3. The method for avoiding strong light exposure for a low-orbit spacecraft according to claim 1, characterized in that: The onboard processing unit determines the validity of the detection telemetry information, specifically: Determine whether the strong light energy in the detection telemetry information exceeds the optical payload damage threshold. If it does, the detection telemetry information is considered to be alarm telemetry. If the alarm telemetry is received three times in a row, the detection telemetry information is determined to be valid; otherwise, it is determined to be invalid.

4. The method for avoiding strong light exposure for a low-orbit spacecraft according to claim 1, characterized in that: The onboard processing unit evaluates the intensity of the strong light energy, specifically: According to the conversion relationship between the satellite's orbital coordinate system, body coordinate system and strong light probe installation matrix, the strong light azimuth vector, solar wing normal vector and optical payload line of sight pointing vector are converted to the same reference coordinate system, which facilitates the calculation of the angle ∣α1∣ between the strong light azimuth vector and the solar wing normal vector, and the angle ∣α2∣ between the strong light azimuth vector and the optical payload line of sight pointing vector.

5. The method for avoiding strong light exposure for a low-orbit spacecraft according to claim 4, characterized in that: The coordinate system transformation is as follows: ①The strong light probe detects strong light and calculates the azimuth angle a and pitch angle b of the strong light output in the probe coordinate system; ② The onboard processing unit converts the azimuth angle a and the pitch angle b into the direction vector in the satellite coordinate system according to the strong light probe installation matrix, and calculates the direction vector of the normal direction vector of the satellite solar panel in the satellite coordinate system. The specific method is as follows: Set the satellite body coordinate system to (x T ,y T ,z T ), after the probe is mounted on the satellite, the rotation angle β of each probe around the Z axis of the satellite camera main payload is calibrated by the cubic mirror, so the coordinate system after conversion is (x S ,y S ,z S ), its transformation matrix is ​​expressed as: Where A is the installation matrix of the strong light probe; Through the above conversion, the target angle information measured by the strong light probe is converted into the target angle information in the whole satellite coordinate system; the target angle information refers to the azimuth angle a and the pitch angle b; ③ In the satellite coordinate system, calculate the angle ∣α1∣ between the normal direction vector of the solar wing and the glare azimuth vector; ④ According to the optical payload installation matrix, calculate the direction vector of the optical payload line of sight in the satellite coordinate system; ⑤ Calculate the angle ∣α2∣ between the optical payload's visual axis direction vector and the strong light azimuth vector in the satellite's coordinate system.

6. The method for avoiding strong light exposure for a low-orbit spacecraft according to claim 4, characterized in that: If the intensity of the strong light energy is greater than or equal to the solar panel 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 the strong light energy is greater than or equal to the solar panel damage threshold, the onboard processing unit generates an instruction containing the satellite platform attitude adjustment step, the optical payload pointing adjustment step, and the termination of the current mission and the shutdown of the optical payload. The satellite performs attitude avoidance and optical payload pointing adjustment according to the instruction, and at the same time stops the power supply to the optical payload and stops the current mission. After executing this instruction to adjust the attitude, the angle between the normal direction vector of the solar wing and the directional vector of the strong light is 89°≤|α1|≤91°, among which the angle|α1|=90° is the best. The normal direction of the solar wing refers to the direction perpendicular to the plane of the solar panel.

7. The method for avoiding strong light exposure for a low-orbit spacecraft according to claim 4, characterized in that: If the intensity of the strong light energy is less than the solar panel damage threshold and 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 energy is less than the solar panel damage threshold and 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 command is executed, the angle between the optical payload's visual axis direction vector and the strong light azimuth vector |α2| should not be less than the optical payload's full field of view angle 2θ to ensure that strong light does not enter the optical payload detector's photosensitive surface.

8. A processor, characterized in that: The processor is used to run a program, wherein when the program is run, the method for avoiding strong light exposure for a low-orbit spacecraft according to any one of claims 1 to 7 is executed.

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

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

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