Space forecasting system and method for satellite-borne situation awareness load

Abstract

The invention discloses a space forecasting system and method for satellite-borne situation awareness load, and the method comprises the steps: S1, calculating the orientation, pitch angle and distance of each target satellite in a satellite orbit system, and screening out the target satellite in a given envelope ball of a satellite as an observable target; s2, analyzing observability of each observable target in each time period in a given time period based on the orientation, the pitch angle and the distance of the observable target under the satellite orbit system, so as to determine observation task time and a corresponding observation task target; s3, according to the observation task time and the corresponding observation task targets, information of all observable targets is generated by taking observation time periods as a sequence, and a corresponding annotation target library instruction is generated and sent to a satellite; according to the method, the active mastering ability of the space situation is enhanced through a ground forecasting means, a guarantee is provided for operation of an on-satellite system, and satellite-ground combined work can be achieved.

Description

Technical Field

[0001] The present invention relates to the field of satellite operation, and in particular to a space prediction system and method for satellite-borne situation awareness payloads. Background Art

[0002] In today's complex space environment, with the increasing frequency of space activities, situational awareness in the space field has become critical. In particular, the detection and tracking of existing satellites in orbit is of immeasurable significance for assessing potential threats, preventing accidental collisions, and ensuring the safety of space assets.

[0003] Therefore, it is necessary to study a method to enhance the ability to proactively grasp the space situation through forecasting means. Summary of the invention

[0004] The purpose of the present invention is to propose a system and method that can intelligently screen out targets in a ground target library that are about to enter the observation range, and predict the best observable period, observation angle, and appropriate observation load.

[0005] To achieve the above object, the present invention proposes a space prediction method for a satellite-borne situational awareness payload, comprising the following steps:

[0006] S1. Calculate the azimuth, pitch angle and distance of each target star in the local satellite orbit system, and select the target stars within the given envelope of the satellite as observable targets;

[0007] S2. Analyze the observability of each observable target in each time period based on the azimuth, elevation angle and distance of the observable target in the local satellite orbital system, so as to determine the observation task time and the corresponding observation task target;

[0008] S3. According to the observation mission time and the corresponding observation mission target, the information of each observable target is generated in the order of observation time periods, and the corresponding target library instructions are generated and sent to the satellite.

[0009] Preferably, step S1 comprises the following steps:

[0010] S11. Based on the existing six orbital numbers of the host star and the target star, a basic orbital model is established using Kepler's orbital theory. The dynamic orbital behavior of the host star and each target star is simulated using the numerical integration method. The future position and trajectory of the host star and all target stars are recursively calculated in super real time to obtain the six orbital numbers of the host star and each target star at any time within a given time period.

[0011] S12, calculating the azimuth, pitch angle and distance of the target star in the orbital system of the own star according to the six orbital numbers of the own star and the target star at any time in a given time period;

[0012] S13, calculate the azimuth, pitch angle and distance of each target star in the local satellite orbital system in turn, select the target stars within the given envelope of the satellite as observable targets, and output the azimuth, pitch angle and distance of the observable targets in the local satellite orbital system in the order of observation time periods.

[0013] Preferably, step S12 comprises the following steps:

[0014] S121. Calculate the position vectors R of the local star and the target star in the inertial system respectively. chaser_i and R target_i ;

[0015] S122. Calculate the position vector R of the target star in the local star orbit system target_orbit ; S123, based on the position vector R target_orbit , calculate the azimuth, pitch angle and relative distance between the target star and the local star in the orbital system.

[0016] Preferably, in step S121, the position vector R chaser_i and R target_i The function R = r·cos(f)·P+r·sin(f)·Q is used. Calculated, among which,

[0017]

[0018] Among them, a, e, I, Ω, ω, and f are the six orbital numbers. Specifically, a is the semi-major axis, e is the eccentricity, I is the orbital inclination, Ω is the right ascension of the ascending node, ω is the argument of perigee, and f is the true anomaly.

[0019] Preferably, in step S122, In step S123,

[0020]

[0021] Among them, φ is the azimuth angle of the target star in the local satellite orbit system, θ is the pitch angle of the target star in the local satellite orbit system, and d is the relative distance between the target star and the local satellite.

[0022] Preferably, step S2 comprises the following steps:

[0023] S21, converting the azimuth, elevation angle and distance of the observable target in the local satellite orbital system into the azimuth, elevation angle and distance of the observable target in the local satellite local system;

[0024] S22, based on the detailed specifications of each observation payload on the satellite, screening out the targets within the observation range and observation distance of each observation payload;

[0025] S23. Analyze the influence of the earth's shadow and the ground's atmospheric light on the observation line of sight, and determine the invisible period of each observable target;

[0026] S24, according to the position of the sun and the position of the observable target, simulate the lighting conditions of each observable target at different time periods, select the observation window with the most suitable lighting, and at the same time determine whether the sun in the observation window will affect the observation effect of the observation payload. If so, select the next most suitable observation window;

[0027] S25. Determine the observation task time and the corresponding observation task target.

[0028] Preferably, in step S3, the information of the observable target includes the observation payload used for observation, the ID of the observable target in the ground target library, the solar angle at the observation time, the azimuth, pitch angle, distance and sight angle of the observable target in the satellite system.

[0029] The present invention also proposes a space prediction system for a satellite-borne situational awareness payload, which is used to implement the space prediction method for a satellite-borne situational awareness payload, comprising: a calculation prediction module, a target observation analysis module and an instruction generation module;

[0030] The calculation prediction module is used to calculate the six orbital numbers of the host satellite and each target satellite at any time in a given time period, and then calculate the azimuth, pitch angle and distance of each target star in the host satellite orbit system, and then filter out the target stars in the satellite given envelope sphere. The calculation prediction module also sends the target stars in the satellite given envelope sphere and the azimuth, pitch angle and distance of each target star in the satellite given envelope sphere in the host satellite orbit system to the target observation analysis module;

[0031] The target observation analysis module analyzes the observability of each target star in a given envelope of the satellite in each time period based on the azimuth, pitch angle and distance of the target star in the local satellite orbital system, thereby determining the observation task time and the corresponding observation task target, and sending them to the instruction generation module;

[0032] The instruction generation module generates information of observable targets in the order of observation periods according to the observation task time and the corresponding observation task target, and generates an instruction to add a target library and sends it to the satellite.

[0033] Preferably, the calculation prediction module, target observation analysis module and instruction generation module are configured to output the calculation data of each step separately.

[0034] Compared with the prior art, the technical solution of the present invention has the following advantages and beneficial effects:

[0035] The present invention uses satellites equipped with high-precision observation payloads to perform refined detection of satellites in orbital space, intelligently screens out targets in a ground target library that are about to enter the observation range based on the satellite's own orbital recursion information, and predicts key information such as the best observable period, observation angle, and appropriate observation payload. The ground-based prediction method enhances the ability to proactively grasp the space situation, provides guarantees for the operation of the onboard system, and helps to achieve satellite-ground joint work.

[0036] This solution can assist mission planners to effectively focus satellite resources on key periods and targets through accurate target screening and observable period prediction, thereby improving detection efficiency and data collection accuracy. In the face of emergencies such as other satellite movements and orbit changes, this technical solution can be used to quickly adjust the observation plan, achieve dynamic response, and reduce calculation time.

[0037] The existing space target prediction system is basically distributed and relies on imported software, which is not enough to support space situational awareness tasks. However, this solution has high integration, simple operation and strong maintainability, which can meet the mission requirements of space situational awareness. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 A schematic diagram of a space prediction system for a satellite-borne situational awareness payload according to the present invention;

[0039] Figure 2 is an algorithm flow chart of the calculation prediction module of the present invention;

[0040] Figure 3 This is an algorithm flow chart of the target observation and analysis module of the present invention. DETAILED DESCRIPTION

[0041] The following will be combined with the embodiments of the present invention Figure 1 to Figure 3 , the technical solutions, structural features, objectives achieved and effects in the embodiments of the present invention are described in detail.

[0042] It should be noted that the drawings are in a very simplified form and use non-precise proportions. They are only used to conveniently and clearly assist in explaining the embodiments of the present invention, and are not used to limit the conditions for the implementation of the present invention. Therefore, they have no substantive technical significance. Any structural modification, change in proportional relationship or adjustment of size, without affecting the effects and purposes that can be achieved by the present invention, should still fall within the scope of the technical content disclosed by the present invention.

[0043] It should be noted that, in the present invention, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only the elements explicitly listed, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0044] The embodiment of the present invention discloses a space prediction system for a satellite-borne situation awareness payload, such as Figure 1 As shown, it includes a calculation prediction module, a target observation analysis module and an instruction generation module. The calculation prediction module is used to calculate the six orbital numbers of the host satellite and each target star at any time in a given time period, and then calculate the azimuth, pitch angle and distance of each target star in the host satellite orbit system, and then filter out the target star in the satellite given envelope sphere. The calculation prediction module also sends the target star in the satellite given envelope sphere and the azimuth, pitch angle and distance of each target star in the satellite given envelope sphere in the host satellite orbit system to the target observation analysis module; the result of the calculation prediction module is used as input, and the target observation analysis module analyzes the observability of each target star in the satellite given envelope sphere in each time period based on the azimuth, pitch angle and distance of the target star in the host satellite orbit system, so as to determine the observation task time and the corresponding observation task target, and send them to the instruction generation module; the instruction generation module generates the information to be observed in the order of observation time periods according to the observation task time and the corresponding observation task target, and generates the target library instruction to send to the satellite.

[0045] The calculation and prediction module has built-in orbital information of the sun and planets.

[0046] A space prediction method for a satellite-borne situation awareness payload according to an embodiment of the present invention is based on the above-mentioned space prediction system for a satellite-borne situation awareness payload. The method specifically comprises the following steps:

[0047] S1. Calculate the azimuth, pitch angle and distance of each target star in the local satellite orbit system, and select the target stars within the given envelope of the satellite as observable targets, such as Figure 2 As shown, the specific steps include:

[0048] S11. The existing six orbital numbers of the host star and the target star are input into the calculation prediction module. The calculation prediction module establishes a basic orbital model based on Kepler's orbit theory, applies a numerical integration method to simulate the dynamic orbital behavior of the host star and each target star, and recursively deduce the future position and trajectory of the host star and all target stars in super real time, thereby obtaining the six orbital numbers of the host star and each target star at any time within a given time period.

[0049] The target stars are target stars in a ground target library, and the ground target library stores known target stars.

[0050] The six existing orbital numbers of the host star and the target star are input into the calculation prediction module. The calculation prediction module also has built-in orbital information of the sun and the planets, so that the calculation prediction module can recursively deduce the dynamic orbital behavior of the host star and the target star according to Kepler's orbital theory and numerical integration method, as follows:

[0051] First, the initial position vector and initial velocity vector of the host star and the target star are calculated according to the given six orbital numbers. Then, at a certain time step, the fourth-order Runge-Kutta method is used to update the position vector and velocity vector. The position vector and velocity vector and other data calculated at each time step are sorted and stored. The dynamic orbital behavior of the host star and the target star can be intuitively displayed in a visual way (such as drawing a three-dimensional orbital trajectory diagram, a velocity variation curve over time, etc.). Then, according to the future position and trajectory of the host star and all the target stars, the six orbital numbers of the host star and each target star at any moment in a given time period are obtained.

[0052] The given time period is a time period set as required, for example, a time period related to the operation cycle of the satellite.

[0053] S12, calculating the azimuth, pitch angle and distance of the target star in the orbital system of the own star according to the six orbital numbers of the own star and the target star at any time, specifically comprising the following steps:

[0054] S121. Calculate the position vectors R of the local star and the target star in the inertial system respectively. chaser_i and R target_i ;

[0055] R chaser_i =cal_Pos_in(a c ,e c ,I c ,Ω c ,ω c ,f c )

[0056] R target_i =cal_Pos_in(a t ,e t,I t ,Ω t ,ω t ,f t )

[0057] Among them, a c ,e c ,I c ,Ω c ,ω c ,f c is the orbital element number of the star at a certain moment, a t ,e t ,I t ,Ω t ,ω t ,f t is the six orbital elements of the target star at a certain moment.

[0058] The above position vector R chaser_i and R target_i They are all calculated using the function R=cal_Pos_in(a,e,I,Ω,ω,f), where a, e, I,Ω,ω, and f are six orbital parameters. Specifically, a is the semi-major axis, e is the eccentricity, I is the orbital inclination, Ω is the right ascension of the ascending node, ω is the argument of perigee, and f is the true anomaly.

[0059] Where, R = r·cos(f)·P+r·sin(f)·Q,

[0060]

[0061] Substituting the six orbital numbers of the local star and the six orbital numbers of the target star into the function R respectively, their corresponding position vectors can be calculated.

[0062] S122. Calculate the position vector R of the target star in the local star orbit system target_orbit ;

[0063]

[0064] In order to facilitate subsequent representation, the calculated position vector R target_orbit Using position vector express.

[0065] S123, based on the position vector R target_orbit , calculate the azimuth angle φ, pitch angle θ of the target star in the local star orbit system and the relative distance d between the two stars;

[0066] in,

[0067] S13, calculate the azimuth, pitch angle and distance of each target star, sun and planet in the local orbital system in a given time period, select the target star within the given envelope of the satellite as the observable target, and output the observable targets and the azimuth, pitch angle and distance of the sun and planet in the local orbital system in the order of observation time periods;

[0068] The satellite given envelope sphere is an imaginary spherical space defined by a specific length (radius) with the satellite mass center as the sphere center, and the specific length is based on the satellite's own size (including the extended antenna and other auxiliary structures), the range of attitude changes that may occur during the operation of the satellite, and the surrounding space range that the payload carried by the satellite needs to cover for normal operation. The target star in the satellite envelope sphere is a target star that may collide with the satellite, so it is very necessary to screen it out and formulate a corresponding observation plan. In other embodiments, the azimuth, pitch angle and distance of the sun and the planets in the local orbit system may not be calculated and output.

[0069] S2, the target observation analysis module analyzes the observability of each target star in each time period in a given time period based on the azimuth, pitch angle and distance of the observable target in the local satellite orbit system, thereby determining the observation task time and the corresponding observation task target, such as Figure 3 As shown, the specific steps include:

[0070] S21, converting the azimuth, elevation angle and distance of the observable target in the local satellite orbital system into the azimuth, elevation angle and distance of the observable target in the local satellite local system;

[0071] S22, based on the detailed specifications of each observation payload on the satellite, screening out the targets within the observation range and observation distance of each observation payload;

[0072] There are many kinds of observation payloads (i.e. onboard situational awareness payloads) installed on the satellite, such as high-resolution visible light cameras, infrared cameras, microwave radars, laser ranging radars, etc. The installation matrix, polarity, detection range, detection distance, and sun protection angle of the satellite control module and each observation payload will affect its ability to observe observable targets. Traverse all observation payloads and select the targets that each observation payload can observe in turn;

[0073] S23. Analyze the influence of the earth's shadow and the ground's atmospheric light on the observation line of sight, and determine the invisible period of each observable target;

[0074] The Earth's shadow refers to the area in space where sunlight cannot directly reach due to the obstruction of the Earth. For optical detection line of sight, when the target star is in the Earth's shadow, it is not conducive to optical observation. For other observation methods (such as radar observation, etc.), when the target is in the Earth's shadow, it will change the electromagnetic environment of the space around the target, increase noise, and interfere with observation.

[0075] Geoluminescence generally refers to light scattered, reflected, and emitted by the Earth's atmosphere. It contains multiple wavelength components. Geoluminescence will reduce the contrast between the observed target and the background, and will also affect the temperature of the observed target.

[0076] Therefore, step S23 is set to analyze the time periods of each observable target within a given time period during which the target is affected by the ground shadow area and the ground air light and cannot be observed, and determine the invisible time period of each observable target;

[0077] S24, according to the position of the sun and the position of the observable target, simulate the lighting conditions of each observable target at different time periods within a given time period, select the observation window with the most suitable lighting, and at the same time determine whether the sun in the observation window will affect the observation effect of the observation payload. If so, select the next most suitable observation window;

[0078] S25. Determine the observation task time and corresponding observation task objectives:

[0079] The observation mission time is determined by comprehensively considering the invisible periods and observation windows of each observable target; the observation mission targets and corresponding observation payloads within each observation mission time are determined according to the specifications of each observation payload;

[0080] S3, according to the observation task time and the corresponding observation task target, the instruction generation module generates information of each observable target in the order of observation period, and generates corresponding target library instructions to send to the satellite;

[0081] After the observation task time and the corresponding observation task target determined by the target observation analysis module are input into the instruction generation module, the instruction generation module integrates the information and outputs the observation information of each observable target star in the order of observation time periods. The observation information of the observable target includes the observation payload used for observation, the ID of the observable target in the ground target library, the solar angle at the observation time, the azimuth, pitch angle, distance, target illumination angle of the observable target in the satellite system, etc.

[0082] The instruction generation module generates a corresponding target library instruction and sends it to the target library of the satellite, so that the satellite arranges the work flow according to the target library instruction, and the observation payload of the satellite detects, matches, tracks and outputs target information for each target star in a specific time period according to the observation plan. The target information can also be used as the input information of the next round of the space prediction system of this embodiment to carry out satellite-ground joint work.

[0083] In this embodiment, the calculation prediction module, the target observation analysis module and the instruction generation module can be configured to output the calculation data of each step separately, that is, the calculation prediction module can be configured to output: the six orbital numbers of the host star and each target star, the azimuth, pitch angle and distance of the target star in the host star orbit system, and the azimuth, pitch angle and distance of the observable targets in the host star orbit system in the order of observation time periods; the target observation analysis module can be configured to output: the azimuth, pitch angle and distance of the observable targets in the host star system, the targets within the observation range and observation distance of each observation payload, the invisible period of each observable target, the observation window of each observable target, the observation task time and the corresponding observation task target; the instruction generation module can be configured to output: the information of each observable target star, and the target library instruction. Through this configuration, it is convenient for ground staff to review and recalculate each step, avoid invalid satellite work, and improve efficiency and safety.

[0084] Although the content of the present invention has been described in detail through the above preferred embodiments, it should be appreciated that the above description should not be considered as a limitation of the present invention. After reading the above content, it will be apparent to those skilled in the art that various modifications and substitutions of the present invention will occur. Therefore, the protection scope of the present invention should be limited by the appended claims.

Claims

1. A space prediction method for a satellite-borne situational awareness payload, characterized in that: The following steps are involved: S1. Calculate the azimuth, pitch angle and distance of each target star in the local satellite orbit system, and select the target stars within the given envelope of the satellite as observable targets; S2. Analyze the observability of each observable target in each time period in a given time period based on the azimuth, pitch angle and distance of the observable target in the local satellite orbital system, so as to determine the observation task time and the corresponding observation task target; S3. According to the observation mission time and the corresponding observation mission target, the information of each observable target is generated in the order of observation time periods, and the corresponding target library instructions are generated and sent to the satellite.

2. The space prediction method for a satellite-borne situational awareness payload according to claim 1, characterized in that: Step S1 includes the following steps: S11. Based on the existing six orbital numbers of the host star and the target star, a basic orbital model is established using Kepler's orbital theory. The dynamic orbital behavior of the host star and each target star is simulated using the numerical integration method. The future position and trajectory of the host star and all target stars are recursively calculated in super real time to obtain the six orbital numbers of the host star and each target star at any time within a given time period. S12, calculating the azimuth, pitch angle and distance of the target star in the orbital system of the own star according to the six orbital numbers of the own star and the target star at any time in a given time period; S13, calculate the azimuth, pitch angle and distance of each target star in the local satellite orbital system in turn, select the target stars within the given envelope of the satellite as observable targets, and output the azimuth, pitch angle and distance of the observable targets in the local satellite orbital system in the order of observation time periods.

3. The space prediction method for a satellite-borne situational awareness payload according to claim 2, characterized in that: Step S12 includes the following steps: S121. Calculate the position vectors R of the local star and the target star in the inertial system respectively chaser_i and R target_i ; S122. Calculate the position vector R of the target star in the local star orbit system target_orbit ; S123, based on the position vector R target_orbit , calculate the azimuth, pitch angle and relative distance between the target star and the local star in the orbital system.

4. The space prediction method for a satellite-borne situational awareness payload according to claim 3, characterized in that: In step S121, the position vector R chaser_i and R target_i The function R = r·cos(f)·P+r·sin(f)·Q is used. Calculated, among which, Among them, a, e, I, Ω, ω, and f are the six orbital numbers. Specifically, a is the semi-major axis, e is the eccentricity, I is the orbital inclination, Ω is the right ascension of the ascending node, ω is the argument of perigee, and f is the true anomaly.

5. The space prediction method for a satellite-borne situational awareness payload according to claim 4, characterized in that: In step S122, In step S123, Among them, φ is the azimuth of the target star in the local orbit system, and θ is the azimuth of the target star in the local orbit system. is the pitch angle, and d is the relative distance between the target star and the local star.

6. The space prediction method for a satellite-borne situational awareness payload according to claim 1, characterized in that: Step S2 includes the following steps: S21, converting the azimuth, elevation angle and distance of the observable target in the local satellite orbital system into the azimuth, elevation angle and distance of the observable target in the local satellite local system; S22, based on the detailed specifications of each observation payload on the satellite, screening out the targets within the observation range and observation distance of each observation payload; S23. Analyze the influence of the earth's shadow and the ground's atmospheric light on the observation line of sight, and determine the invisible period of each observable target; S24, according to the position of the sun and the position of the observable target, simulate the lighting conditions of each observable target at different time periods, select the observation window with the most suitable lighting, and at the same time determine whether the sun in the observation window will affect the observation effect of the observation payload. If so, select the next most suitable observation window; S25. Determine the observation task time and the corresponding observation task target.

7. The space prediction method for a satellite-borne situational awareness payload according to claim 1, characterized in that: In step S3, the information of the observable target includes the observation payload used for observation, the ID of the observable target in the ground target library, the solar angle at the observation time, the azimuth, pitch angle, distance and sight angle of the observable target in the satellite system.

8. A space prediction system for a satellite-borne situational awareness payload, used to implement the space prediction method for a satellite-borne situational awareness payload as described in any one of claims 1 to 7, characterized in that: include: Calculation prediction module, target observation analysis module and instruction generation module; The calculation prediction module is used to calculate the six orbital numbers of the host satellite and each target satellite at any time in a given time period, and then calculate the azimuth, pitch angle and distance of each target star in the host satellite orbit system, and then filter out the target stars in the satellite given envelope sphere. The calculation prediction module also sends the target stars in the satellite given envelope sphere and the azimuth, pitch angle and distance of each target star in the satellite given envelope sphere in the host satellite orbit system to the target observation analysis module; The target observation analysis module analyzes the observability of each target star in a given envelope of the satellite in each time period based on the azimuth, pitch angle and distance of the target star in the local satellite orbital system, thereby determining the observation task time and the corresponding observation task target, and sending them to the instruction generation module; The instruction generation module generates information of observable targets in the order of observation periods according to the observation task time and the corresponding observation task target, and generates an instruction to add a target library and sends it to the satellite.

9. The space prediction system for onboard situational awareness payload according to claim 8, characterized in that: The calculation prediction module, target observation analysis module and instruction generation module are configured to output the calculation data of each step separately.

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