Satellite orbit capacity domain potential field characterization method and device

Abstract

The present application belongs to the technical field of satellite orbit mission planning, and discloses a satellite orbit capability domain potential field characterization method and device. The existing method simplifies the capability domain into an isotropic sphere, ignoring physical constraints and environmental effects, resulting in inaccurate capability characterization. The present application divides the satellite payload into environment-independent and environment-dependent types. A first action potential function of the environment-independent payload is constructed through a radial kernel function to determine the first inherent capability domain and the first instantaneous capability domain corresponding to the environment-independent payload. On the basis of the first action potential function, a second action potential function is constructed by fusing multiple constraint component functions excited by environmental factors to obtain the second instantaneous capability domain corresponding to the environment-dependent payload. The first instantaneous capability domain and the second instantaneous capability domain are mapped into multiple functional potential field clusters based on the macroscopic action potential function to construct the system capability domain of the satellite. The simulation results show that the situation sensitivity is improved by 67.3%, and the threat recognition degree is improved by 144.6%.

Description

Technical Field

[0001] This invention relates to the field of satellite orbit mission planning technology, specifically to a method and apparatus for characterizing the potential field of a satellite orbit capability domain. Background Technology

[0002] Satellite orbital interaction is a core support for maintaining space resource security and ensuring the stable progress of on-orbit missions. In complex missions such as space warfare, on-orbit servicing, and space debris removal, mission planning, by analyzing information from both or multiple parties, yields the optimal orbital and attitude maneuver schemes, making it a crucial element affecting the success or failure of orbital interaction missions.

[0003] However, current mission planning commonly employs a homogeneous and simplified assumption in characterizing satellite capabilities. Specifically, the capability range of a satellite is typically reduced to a homogeneous and isotropic traditional sphere model with a radius of "maximum effective range" (ZHANG KP, ZHANG Y, SHI H, et al. Escape-zone-based optimal evasionguidance against multiple orbital pursuers[J]. IEEE Transactions on Aerospace and Electronic Systems, 2023, 59(6): 7698-7714).

[0004] However, the traditional homogeneous and isotropic spherical model essentially ignores the complex field effects generated by the interaction between the physical properties of the payload and the space environment. For example, optical reconnaissance payloads are limited by the field of view and physically obstructed by the solar array, and their inherent effective area exhibits a highly asymmetric geometric topology; coherent communication or radar payloads are modulated by the Doppler effect of high-speed relative motion, and their effective area can only be closed within a specific radial velocity window.

[0005] It is evident that the simplified, homogeneous, and isotropic traditional sphere model described above makes it impossible to identify the opponent's potential energy blind spot during the task planning process, nor can it accurately define its own effective potential well, which greatly limits the effectiveness and engineering rationality of existing planning strategies.

[0006] Currently, research on characterizing satellite orbital action capabilities mainly focuses on two aspects: numerical scalarization and simple geometricization. The core logic of these methods is to map the capability to a one-dimensional scalar or a sphere characterized by a scalar dimension of "maximum action distance." While this method is highly efficient in macroscopic system evaluation, it loses the spatial distribution characteristics of satellite orbital action capabilities, resulting in lower engineering rationality.

[0007] Therefore, existing satellite orbit interaction capability modeling and evaluation methods lack specific methods that fit the characteristics of the satellite itself and the dynamic scenarios of orbital interactions, and it is difficult to meet actual needs by transferring mature models from existing fields. There is an urgent need to build a satellite orbit interaction capability characterization method that can accurately reflect the characteristics of the satellite platform and payload and has strong adaptability, so as to improve the accuracy of mission planning. Summary of the Invention

[0008] The purpose of this invention is to provide a method and apparatus for characterizing the potential field of a satellite orbital capability domain, so as to solve the problems mentioned in the background art.

[0009] The main design concept of this invention is as follows: Based on the aforementioned technical problems, this invention systematically abstracts the physical constraints of satellite payloads and the coupling effect of the space environment into a series of computable potential functions. An isotropic intrinsic potential field is uniformly described through a radial kernel function, and an anisotropic environmental coupling potential field is generated through the fusion of the maxima of multiple constraint component functions. Finally, using a field-source function mapping and macroscopic action potential function minimization fusion mechanism, heterogeneous payloads are aggregated into three system-level capability domains: query, jamming, and strike. This achieves a paradigm shift from an ideal sphere to a real physical envelope.

[0010] To achieve the above objectives, the present invention provides the following technical solution: On one hand, the present invention provides a method for characterizing the potential field of a satellite orbital capability domain, comprising: All payloads carried on the satellite are divided into environment-independent payloads and environment-dependent payloads; The first action potential function of the environment-independent load is constructed by the radial kernel function. The first inherent capability domain corresponding to the environment-independent load is determined based on the first action potential function. The first inherent capability domain is mapped to the geocentric inertial frame to obtain the first instantaneous capability domain. Based on the first action potential function, multiple constraint component functions excited by environmental factors are integrated to construct the second action potential function of the environment-dependent load. Based on the second action potential function, the second inherent capability domain corresponding to the environment-dependent load is determined. The second inherent capability domain is mapped to the geocentric inertial frame to obtain the second instantaneous capability domain. Based on the macroscopic potential function, the first and second instantaneous capability domains are mapped into multiple functional potential field clusters, and the satellite's system capability domain is constructed based on these multiple functional potential field clusters.

[0011] More preferably, the first inherent capability domain corresponding to the environment-independent load includes a uniform spherical potential field, a bounded toroidal potential field, and a gradient-decayed potential field.

[0012] More preferably, the first potential function of the environment-independent load is constructed through a radial kernel function, including: Constructing the radial kernel function ,make ; in, The first potential function representing an environment-independent load. Denotes the first arbitrary point in three-dimensional Euclidean space. Represents the first arbitrary point Distance to the center of an environment-independent load.

[0013] More preferably, the expression for the first instantaneous capability domain is obtained by mapping the first inherent capability domain to the geocentric inertial frame: ; in, This represents the first instantaneous capability domain of an environment-independent payload, where s represents the satellite and t represents time. Indicates the real-time position of the satellite's orbit. The attitude matrix representing the satellite's orbit. This represents the first intrinsic capability domain for environment-independent loads. Minkowski and, Represents any point in inertial space. Represents three-dimensional Euclidean space. Represents the attitude matrix The transpose of the matrix, This indicates the matrix transpose.

[0014] More preferably, the second inherent capability domain corresponding to the environment-dependent load includes a geometrical obstruction potential field, a directional beam potential field, and a kinematic dynamic potential field.

[0015] More preferably, the expression for the second potential function of the geometric blocking potential field is: ; in, Let G represent the second potential function of the geometric occlusion potential field, and let G represent the geometric occlusion potential field. Denotes the second arbitrary point in three-dimensional Euclidean space. This indicates taking the maximum value. Represents the second arbitrary point Distance to the center of the environment-dependent load This represents the maximum radius of the spherical shell region. Represents the minimum radius of the spherical shell region. Indicates the half angle facing away from the cone. Represents the unit direction vector. This represents the unit vector pointing to by the satellite. This represents the azimuth angle of the k-th wedge structure. This represents the angle width of the k-th wedge structure. Represents the second arbitrary point azimuth angle, Let K represent the angle difference normalization function, and K represent the number of wedge structures.

[0016] More preferably, the expression for the second potential function of the directional beam potential field is: ; in, Let D represent the second potential function of the directional beam potential field, and let D represent the directional beam potential field. Represents any point in the beam coordinate system. , , Represented as arbitrary points The three components, This represents the horizontal field of view of the main lobe region of the elliptical cone. This represents the pitch field of view of the main lobe region of the elliptical cone. Represents the tangent function. Indicates the center azimuth angle of the load. Indicates the angle width of the load. Represents any point The azimuth angle.

[0017] More preferably, the expression for the macroscopic potential function is: ; in, Let X represent the macroscopic potential function, and let X represent any functional potential cluster. Let t represent any point in inertial space, and let t represent time. This indicates taking the minimum value. This represents the instantaneous capability domain of the l-th load. This represents the set of loads belonging to the same functional potential cluster.

[0018] More preferably, the plurality of functional potential field clusters include: Query the potential field, which includes gradient decay potential field and geometric occlusion potential field; Interference capability potential fields, encompassing uniform spherical potential fields, directional beam potential fields, and kinematic dynamic potential fields; The strike capability potential field encompasses both the bounded cyclic potential field and the kinematic dynamic potential field. The system capability domain expression for a satellite constructed based on multiple functional potential field clusters is as follows: ; in, This represents the system capability domain of the satellite, where 's' represents the satellite. This indicates the number of functional potential clusters. This represents the union operation. The union symbol represents the set of sets. Let represent the macroscopic potential function of the i-th functional potential cluster at time t. It represents three-dimensional Euclidean space.

[0019] On the other hand, the present invention provides a satellite orbital capability domain potential field characterization device for implementing the satellite orbital capability domain potential field characterization method, comprising: The payload classification module is configured to classify all payloads carried on the satellite into environment-independent payloads and environment-dependent payloads; The inherent potential field characterization module is configured to construct the first action potential function of the environment-independent load through the radial kernel function, determine the first inherent capability domain corresponding to the environment-independent load based on the first action potential function, and map the first inherent capability domain to the geocentric inertial frame to obtain the first instantaneous capability domain. The coupled potential field characterization module is configured to, based on the first action potential function, integrate multiple constraint component functions excited by environmental factors to construct the second action potential function of the environment-dependent load, determine the second inherent capability domain corresponding to the environment-dependent load based on the second action potential function, and map the second inherent capability domain to the geocentric inertial frame to obtain the second instantaneous capability domain. The system capability characterization module is configured to map the first and second instantaneous capability domains into multiple functional potential field clusters based on the macroscopic action potential function, and to construct the satellite's system capability domain based on the multiple functional potential field clusters.

[0020] Compared with the prior art, the beneficial effects of the present invention are: 1. This invention incorporates heterogeneous payloads into the same characterization system through a unified mathematical framework of the potential function, and adopts the same potential field determination logic. This breaks down the barriers in traditional methods where different payloads need to be modeled separately and are difficult to cross-calculate, so that multi-payload collaborative analysis no longer depends on cumbersome geometric splicing, and lays a mathematical foundation for the mission orchestration of satellite platforms.

[0021] 2. This invention incorporates dynamic physical quantities such as field of view, relative velocity, Doppler shift, angular rate, and dwell time into the capability domain calculation by quantitatively analyzing the multiphysics constraints of the payload. This makes the capability domain no longer a fixed geometry, but a potential field that evolves in real time with the satellite's attitude maneuvering, orbital motion, and relative motion, thus enhancing the spatial dimension of capability pre-characterization.

[0022] 3. This invention, through a field-source function mapping mechanism, divides payloads into three functional potential field clusters: query, jamming, and strike, and fuses them using a macroscopic interaction potential function. This not only preserves the individual capabilities of each payload but also imbues the satellite system with a sense of its role. This function-oriented aggregation method significantly reduces the cognitive load of mission planning and enhances the intuitiveness and timeliness of situation assessment.

[0023] 4. This invention maps capability domain strips onto the satellite orbit, improving the accuracy of relative orbital state assessment. Simulation results show that, compared to existing spherical characterization methods, this invention improves situational sensitivity by an average of 67.3% and threat identification accuracy by an average of 144.6%. It maintains a high identification accuracy of over 0.85 under various complex constraints, reaching a maximum of 0.95, demonstrating extremely high reliability in assessment.

[0024] 5. This invention designs two universally applicable evaluation indicators: situational sensitivity and threat identification, enabling the objective measurement of the capability domain's representation accuracy. This quantitative verification chain ensures that the technical effects of this invention are no longer qualitative descriptions but rather statistically significant and credible conclusions, providing solid persuasiveness for engineering applications. Attached Figure Description

[0025] Figure 1 This is a flowchart of the satellite orbit capability domain potential field characterization method of the present invention; Figure 2 The instantaneous capability domain characterization results of the satellite carrying three environment-independent payloads according to the present invention are shown, where a is the instantaneous uniform spherical potential field, b is the instantaneous bounded toroidal potential field, and c is the instantaneous gradient decay potential field. Figure 3 The continuous potential field characterization results for three environment-independent payloads carried by the satellite of this invention are shown, where a is a continuous uniform spherical potential field, b is a continuous bounded toroidal potential field, and c is a continuous gradient decay potential field. Figure 4 The instantaneous potential field characterization results for three environment-dependent payloads carried by the satellite of this invention are shown, where a is the instantaneous geometric obstruction potential field, b is the instantaneous directional beam potential field, and c is the instantaneous kinematic dynamic potential field. Figure 5 The continuous potential field characterization results for three environmentally dependent payloads carried by the satellite of this invention are shown, where a is the continuous geometric obstruction potential field, b is the continuous directional beam potential field, and c is the continuous kinematic dynamic potential field. Figure 6 This is a simulation diagram of the continuous capability domain when the satellite of this invention carries a coherent laser communication payload; Figure 7 This is a satellite orbital plane situation diagram for the present invention; Figure 8 This is a satellite orbital normal situation diagram for the present invention. Detailed Implementation

[0026] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] Example 1: A method for characterizing the potential field of a satellite's orbital capability domain like Figure 1 As shown, this embodiment provides a method for characterizing the potential field of a satellite's orbital capability domain, specifically including the following steps: S1: Based on whether the payloads carried on the satellite are affected by the external environment, all payloads carried on the satellite are divided into environment-independent payloads and environment-dependent payloads; Based on whether satellite payloads are constrained by the external environment, such as illumination angle and relative velocity, satellite payloads are classified into environment-dependent payloads and environment-independent payloads.

[0028] The capacity of environment-independent loads is not affected by external environmental factors, and their capacity domain is consistent in all directions, exhibiting isotropic characteristics.

[0029] The capability domain of this type of payload is defined as the intrinsic potential field. Typical environment-independent payloads include omnidirectional electronic jammers, capture nets, and passive radio frequency detection payloads.

[0030] The capabilities of environment-dependent loads are significantly affected by external environmental factors, and their capability domains exhibit inconsistent performance in different directions, demonstrating anisotropy.

[0031] The capability domain of this type of payload is defined as the environmental coupling potential field. Typical environmentally dependent payloads include optical reconnaissance cameras, microwave directional disturbance payloads, and inter-satellite laser coherent link interference payloads.

[0032] S2: Construct the first action potential function of the environment-independent load through the radial kernel function, determine the first inherent capability domain corresponding to the environment-independent load based on the first action potential function, map the first inherent capability domain to the geocentric inertial frame, and obtain the first instantaneous capability domain. For the isotropic characteristics of environment-independent loads, the first action potential function is used to accurately characterize its capability domain.

[0033] Specifically, at time Construct the first action potential function To describe the potential field distribution of the environment-independent load capacity domain, the first action potential function transforms the abstract "spatial region" into a quantifiable "numerical distribution".

[0034] in, Denotes the first action potential function. This represents three-dimensional Euclidean space, corresponding to all possible three-dimensional coordinate points in the Cartesian coordinate system. That is, the physical space surrounding the satellite. This represents a mapping relationship, where the variable on the left is processed by the first action potential function. After processing, we obtain the variable on the right. It represents the set of real numbers.

[0035] First potential function The physical constraints of environment-independent loads are parameterized to characterize the first arbitrary point in space. The action determination value relative to the environment-independent load center, i.e., the value used to measure the first arbitrary point in space. Does it meet the operating conditions for environment-independent loads?

[0036] Based on this, solving the first action potential function yields the first intrinsic capability domain of the environment-independent load. That is, the set of all spatial points that make the value of the first potential function not greater than zero.

[0037] in, This represents the first intrinsic capability domain for environment-independent loads. Denotes the first arbitrary point in three-dimensional Euclidean space. , This indicates that the condition is met. Represents the first arbitrary point of the environment-independent load. The potential energy value, in this embodiment, This actually represents the current position of the satellite.

[0038] Next, using the real-time position of the satellite orbit attitude matrix of satellite orbit Through coordinate transformation Mapped to a geocentric inertial frame, the first instantaneous capability domain of the environment-independent load is obtained. .

[0039] The mathematical expression for this coordinate transformation is: ; in This represents the first instantaneous capability domain of an environment-independent payload, where s represents the satellite and t represents time. Minkowski sum, i.e., set translation operation, Represents any point in inertial space. Represents the attitude matrix The transpose of the matrix, This indicates the matrix transpose.

[0040] This indicates the coordinate transformation. This represents a mathematical determination. That is, any point in inertial space... Does it belong to It depends on whether its potential energy value after transformation to the geocentric inertial frame meets the feasibility conditions. .

[0041] To achieve unified modeling for different environment-independent loads, this invention further constructs a radial kernel function. For the first action potential function Perform unified parametric modeling, so that .

[0042] in, Represents the radial kernel function. Represents the first arbitrary point The distance to the center of the environment-independent load. Based on different combinations of performance parameters of the environment-independent load, this radial kernel function can determine the first intrinsic capability domain of three typical types of environment-independent loads, specifically including: A1: Uniform spherical potential field When the environment-independent load is only subjected to the maximum action distance When constrained, its first intrinsic capability domain is a region with a radius of [missing information]. The sphere. At this point, the potential energy increases linearly with distance, and the radial kernel function is defined as: ; when At that time, that is The corresponding radius is The feasible region of the sphere.

[0043] The uniform spherical potential field is suitable for loads such as omnidirectional electronic jammers. Its effective range is exactly the same in all directions, presenting as a regular uniform spherical potential domain.

[0044] A2: Bounded Ring Formation Field When environmentally independent loads are simultaneously limited by the minimum effective distance and maximum effective distance At that time, its first inherent capability domain is an inner radius of and outer radius The spherical shell. At this point, the potential energy exhibits bilateral constraint, and the radial kernel function is defined as: ; When distance In When the interval is, The feasibility conditions are met.

[0045] Bounded ring-shaped field is suitable for capturing loads such as flying nets. Its range of action has clear inner and outer boundaries, and it is characterized as a bounded ring-shaped capability domain.

[0046] A3: Gradient decay potential field When the environment-independent load performance The decays with distance and there exists an effective threshold. At this point, its first intrinsic capability domain is formed by truncation of the isosurface corresponding to the effectiveness threshold. The potential energy is defined by the effectiveness difference, and the radial kernel function is: ; The first inherent capability domain is determined by the effectiveness threshold. The corresponding isosurface is truncated. The gradient attenuation potential field is suitable for passive RF detection payloads, etc., and exhibits the physical gradient characteristic that the detection margin gradually decreases with increasing distance.

[0047] Depend on Figure 2 As shown in a, b, and c, the omnidirectional electronic jammer corresponds to a uniform spherical potential field, which is a regular uniform spherical potential field; the capture net corresponds to a bounded ring potential field, which is a bounded ring potential field with clear inner and outer boundaries; the passive radio frequency detection payload corresponds to a gradient attenuation potential field, which shows the physical gradient characteristics of the detection margin gradually decreasing with increasing distance.

[0048] Depend on Figure 3 As can be seen, the continuous capability domain characterization results are shown when the satellite carries the above three types of environment-independent payloads. The continuous capability domain is the result of taking the union of the instantaneous capability domains within a time window; the red dashed line in the figure represents the satellite trajectory. Among them, Figure 3 Figure a shows a continuous uniform spherical potential field. Figure 3 Figure b shows a continuous bounded toroidal field. Figure 3 Figure c shows a continuously gradient decaying potential field.

[0049] By sweeping the instantaneous envelope of a single point along the orbital path, a smooth and continuous cylindrical or tubular continuous game capability domain is formed, which intuitively reveals the spatiotemporal coverage of environment-independent loads throughout the entire game cycle.

[0050] S3: Based on the first action potential function, multiple constraint component functions excited by environmental factors are integrated to construct the second action potential function of the environment-dependent load. Based on the second action potential function, the second inherent capability domain corresponding to the environment-dependent load is determined. The second inherent capability domain is mapped to the geocentric inertial frame to obtain the second instantaneous capability domain. In view of the anisotropic characteristics of environment-dependent loads, this step, based on the first potential function, further considers multiple constraint components excited by environmental factors and constructs a second potential function for environment-dependent loads.

[0051] Based on the different constraint component functions, second action potential functions were constructed for three types of environment-dependent loads, thereby determining the corresponding second intrinsic capability domains for these three types of environment-dependent loads. Specifically, these include: B1: Geometric blocking potential field The geometrical obstruction potential field is used to describe the spatial constraints formed by both distance limitations and satellite platform structural obstruction. Its second action potential function... for: ; in, Let G represent the second potential function of the geometric occlusion potential field, and let G represent the geometric occlusion potential field. Denotes the second arbitrary point in three-dimensional Euclidean space. Describes the second arbitrary point in three-dimensional Euclidean space. Distance to the center of environment-dependent loads This represents the maximum radius of the spherical shell region. This represents the minimum radius of the spherical shell region.

[0052] First item Defined by The spherical shell region constitutes the effective range of environmentally dependent loads.

[0053] Second item The description is in half-width mode. The high potential energy shielding region formed by the opposing cone Indicates the half angle facing away from the cone. Indicates half-width The cosine function, Represents the unit direction vector. The first term represents the unit vector pointing to the satellite, and the second term indicates that the target is blocked when it is located inside the cone facing away from the satellite.

[0054] Third item Description by azimuth angle and angle width Defined A wedge-shaped shielding area, This represents the azimuth angle of the k-th wedge structure. This represents the angle width of the k-th wedge structure, where K represents the number of wedge structures. Represents the second arbitrary point azimuth angle, This represents the angle difference normalization function.

[0055] The geometric occlusion potential field manifests as the effective area after removing all physical obstructions within the spherical shell region. For an optical reconnaissance camera, it is modulated by the combined effects of field-of-view limitation, wedge-shaped occlusion of the body and heat sink, and strong light orientation constraint of the solar panel back cone, presenting a geometric occlusion field with a specific wedge-shaped notch that is non-convex and asymmetrical.

[0056] B2: Directional beam potential field Directional beam potential is used to describe the constraints imposed by the field-of-view directivity and internal avoidance requirements of environment-dependent loads.

[0057] Introducing beam system coordinate transformation ,in, Represents any point in the beam coordinate system. This represents the beam pointing rotation matrix, which transforms the global orientation to the beam coordinate system. This indicates the matrix transpose.

[0058] The second potential function of the directional beam potential field is then expressed as: ; in, Let D represent the second potential function of the directional beam potential field, and let the first term represent the directional beam potential field. Constructed with , The main lobe region of an elliptical cone with a half-angle. , , Representing any point The three components, This represents the horizontal field of view of the main lobe region of the elliptical cone. This represents the pitch field of view of the main lobe region of the elliptical cone. This represents the tangent function.

[0059] The first term indicates that only points located inside the elliptic cone are within the effective area of ​​action.

[0060] Second item The main lobe is defined by The described directional notch is used to avoid strong light or specific interference. Indicates the currently locked center azimuth angle of the load. This indicates the current locked angle width of the load.

[0061] The directional beam potential field exhibits a directional beam capability domain with a clear directionality, and there may be specific gap regions inside the beam.

[0062] B3: Kinematic dynamic potential field A kinematic dynamic potential field is used to describe dynamic constraints arising from relative motion states. The relative velocity of a satellite is defined. With instantaneous angular rate Its second action potential function The expression is: ; in, The second potential function represents the dynamic potential field of the kinematics. It represents the dynamic potential field of kinematics.

[0063] First item The radial velocity constraint under Doppler frequency shift limitation is described. Represents the relative radial velocity in the target direction. This indicates taking the absolute value. This indicates the maximum permissible radial velocity under load. The first term is expressed as... A symmetrical banded region with axis as its axis.

[0064] Second item Elimination of angular velocities exceeding the imaging threshold High dynamic range, Represents the second arbitrary point The instantaneous angular velocity at that point.

[0065] The kinematic dynamic potential field manifests as a kinematic dynamic action field perpendicular to the relative velocity vector, i.e., a velocity slice ring. For inter-satellite laser coherent link interference payloads, limited by Doppler and coherent capture thresholds, their effective range is closed only within a specific radial velocity window.

[0066] Depend on Figure 4 As can be seen, the second instantaneous capability domain characterization results are presented when the satellite carries the aforementioned three types of environment-dependent payloads. Among them, Figure 4 In this context, 'a' represents the instantaneous geometric blocking potential field. Figure 4 In the middle b, the instantaneous directional beam potential field is... Figure 4 In this context, c represents the instantaneous kinematic dynamic potential field.

[0067] Among them, the geometrical obstruction potential field is presented as a geometrical obstruction field with a specific wedge-shaped notch and is non-convex and asymmetrical, with the black dot in the middle indicating the satellite body; the directional beam potential field is presented as a directional beam field with clear directionality; and the kinematic dynamic potential field is represented as a velocity slice ring perpendicular to the relative velocity vector.

[0068] Depend on Figure 5 As can be seen, the continuous capability domain characterization results are shown when the satellite carries the above three types of environment-dependent payloads. Figure 5 In this context, 'a' represents a continuous geometric blocking potential field. Figure 5 In the middle b, the potential field is a continuous directional beam. Figure 5In this context, c represents the dynamic potential field of continuous kinematics.

[0069] As the satellite's attitude maneuvers and relative motion state change in real time, these complex anisotropic envelopes form non-uniform, dynamically fluctuating potential stripes through sweeping.

[0070] S4: Based on the macroscopic action potential function, the first instantaneous capability domain and the second instantaneous capability domain are mapped into multiple functional potential field clusters, and the system capability domain of the satellite is constructed based on the multiple functional potential field clusters; Based on the above-mentioned instantaneous capability domain of a single payload, this step constructs a multi-field source functional mapping mechanism to aggregate multiple payload capability domains on multiple satellites, ultimately forming a system capability domain with superimposed fields.

[0071] First, based on the physical properties of the load, the instantaneous capability domain of heterogeneous loads is divided into three types of functional potential field clusters, including query capability potential field, interference capability potential field, and strike capability potential field.

[0072] C1: Query capability potential field Query capability potential field This dataset aggregates all payload sources used for situational awareness and information acquisition, covering gradient decay potential fields and geometric occlusion potential fields. Here, 's' represents the satellite, 'Q' represents the query capability, and 't' represents time. These payloads are primarily used to acquire information such as the target's position, velocity, and imagery.

[0073] C2: Disruption potential field Disturbance potential field This dataset aggregates all payload field sources used for electromagnetic suppression or functional blinding, encompassing uniform spherical potential fields, directional beam potential fields, and kinematic dynamic potential fields. Here, 's' represents the satellite, 'J' represents the jamming capability, and 't' represents the time. These payloads are primarily used to interfere with enemy sensors or communication links.

[0074] C3: Striking Power Field Strike capability field This aggregates all payload field sources used for hard-kill or energy destruction, encompassing bounded toroidal potential fields and kinematic dynamic potential fields, where s represents the satellite, C represents the strike capability, and t represents time. These payloads are primarily used for the physical destruction or functional disruption of targets.

[0075] Then, regional fusion of the multi-source potential fields is performed. The macroscopic potential function is defined as the minimum value of the instantaneous capability domain of each load, i.e.: ; in, Let X represent the macroscopic potential function, and let X represent any functional potential cluster. Let t represent any point in inertial space, and let t represent time. This indicates taking the minimum value. The instantaneous capability domain of the l-th load (including uniform spherical potential field, geometrically obstructed potential field, bounded toroidal potential field, gradient decay potential field, directional beam potential field, and kinematic dynamic potential field) is represented. This represents the set of loads belonging to the same functional potential cluster.

[0076] The physical meaning of the above formula is: for a certain functional potential field cluster, its macroscopic potential function takes the minimum value of the instantaneous capability domain of all load members. That is, as long as there is a load that can play a role at that point, then that point belongs to the capability domain of the functional cluster.

[0077] Based on this, the system capability domain of the satellite under various types of payloads This refers to the feasible region of the macroscopic potential field, namely: ; in, This represents the system capability domain of the satellite, where 's' represents the satellite. This indicates the number of functional potential clusters. This represents the union operation. The union symbol represents the set of sets. Let represent the macroscopic action potential function of the i-th functional potential field cluster (including query capability potential field, interference capability potential field and strike capability potential field) at time t.

[0078] The above formula shows the system capability domain of the satellite. It is the union of all functional potential field cluster members, that is, as long as there is a load that can cover a certain point, that point belongs to the system's capability domain.

[0079] Example 2: A satellite orbital capability domain potential field characterization device Based on Example 1, this example provides a satellite orbital capability domain potential field characterization device, including the following modules: The payload classification module is configured to classify all payloads carried on the satellite into environment-independent payloads and environment-dependent payloads; The inherent potential field characterization module is configured to construct the first action potential function of the environment-independent load through the radial kernel function, determine the first inherent capability domain corresponding to the environment-independent load based on the first action potential function, and map the first inherent capability domain to the geocentric inertial frame to obtain the first instantaneous capability domain. The coupled potential field characterization module is configured to, based on the first action potential function, integrate multiple constraint component functions excited by environmental factors to construct the second action potential function of the environment-dependent load, determine the second inherent capability domain corresponding to the environment-dependent load based on the second action potential function, and map the second inherent capability domain to the geocentric inertial frame to obtain the second instantaneous capability domain. The system capability characterization module is configured to map the first and second instantaneous capability domains into multiple functional potential field clusters based on the macroscopic action potential function, and to construct the satellite's system capability domain based on the multiple functional potential field clusters.

[0080] Example 3: Simulation Experiment Based on the scheme of Embodiment 1 and the apparatus of Embodiment 2, simulation experiments were conducted. To quantify the effectiveness of the proposed characterization method through simulation verification, this embodiment first designed two universal evaluation metrics: D1: Situational Sensitivity Situation sensitivity measures the precision with which satellite orbital status is captured; a higher value indicates greater sensitivity in situation description. The formula for calculation is: ; in, Indicates the situational sensitivity value. This represents the total number of simulation steps. This represents the relative altitude of the target satellite at time j. Represents the relative altitude of the target satellite at time j. Normalization, Indicates the target satellite is in Normalization of the relative height of time, and These represent the upper and lower boundaries of the capability domain strip, respectively. Situation sensitivity reflects the response sensitivity of the capability domain strip to changes in the target trajectory.

[0081] D2: Threat Identification Threat identification score is used to quantify the accuracy of threat assessment; the closer the score is to 1, the closer the assessment result is to physical facts. Its calculation formula is: ; in, This indicates the threat identification score. The number of targets that fall within the capability domain stripe. This represents the number of threat events based on the geometric distance criterion. This metric reflects the accuracy of the capability domain in identifying threat events.

[0082] In this embodiment, three typical environment-independent payloads and three typical environment-dependent payloads were mounted on the Red Star 1 platform. The rationality of the proposed method was verified by comparing the effects of the three-dimensional potential field distribution. The satellite platform is... The rectangular structure of the platform The platform is equipped with solar panels, which form a back cone shading that serves as the physical reference for calculating the backward field source constraint. Large heat dissipation radiators are deployed on the sidewalls, forming a wedge-shaped structure that shields the surface around an azimuth angle of 90°.

[0083] The simulation duration was 7 days, with an orbit extrapolation step size of 10 minutes. Satellite payload parameters are shown in Table 1 below. Satellite orbit parameters are shown in Table 2 below. All angles are in degrees, and it is assumed that the attitude pointing is always in the optimal state.

[0084] A game scenario was constructed, comprising one red team satellite (denoted as Red Star-1) and three blue team satellites (denoted as Blue Star-1, Blue Star-2, and Blue Star-3, respectively). Each satellite carried one of the three environment-dependent payloads described in Table 1. In the simulation scenario, all three blue team satellites performed pulse maneuvers 48 hours and 72 hours after the initial time, approaching Red Star-1. The maneuver amounts are shown in Table 2. Red Star-1 did not perform any counter-maneuvers, and the game payloads did not take any actual action.

[0085] Table 1 Satellite Payload Parameters

[0086] Table 2 Satellite Orbit Parameters Simulation as Figure 6 As shown, this figure illustrates the continuous capability domain of satellites carrying coherent laser communication (kinematic payloads) in the longitude-semi-major axis phase diagram coordinate system. The horizontal axis represents the longitude of the nadir point, the vertical axis represents the altitude deviation relative to the geostationary orbit, the solid line represents the projection of the satellite orbit into the phase diagram coordinate system, and the shaded area represents the satellite's game-theoretic capability domain.

[0087] Satellite orbital plane status as Figure 7 As shown, the satellite's orbital normal status is as follows: Figure 8 As shown, the horizontal axis represents the longitude of the nadir point, and the vertical axis represents the latitude of the nadir point. The real-time red-blue latitude difference is always less than 0.05 degrees, indicating that the physical distance deviation between the two in the direction perpendicular to the orbital plane does not exceed 5km, which is negligible relative to the actual relative distance scale and does not affect the evaluation of the above indicators.

[0088] Based on the above definition of situational sensitivity, the situational sensitivity of the traditional spherical model described in the method and background sections of this invention is calculated under geometrically obstructed potential fields, directional beam potential fields, and kinematic dynamic potential fields. The calculation results are shown in Table 3 below. Table 3. Results of Situation Sensitivity Calculation Define the improvement rate of situational sensitivity of the method of this invention relative to the traditional sphere model. for: ; in, This indicates the situational sensitivity of the method of the present invention. This indicates the situational sensitivity of the traditional sphere model.

[0089] The rate of improvement in the situational sensitivity of the geometric occlusion potential field for: ; Improvement rate of situation sensitivity of directional beam potential field for: ; Improvement rate of state sensitivity of kinematic dynamic potential field for: ; The average improvement rate of situational sensitivity for the three types of environment-dependent loads for: ; As can be seen, the method of the present invention improves the situation sensitivity by an average of 81.48%, with the most significant improvements in the directional beam field and the kinematic dynamic potential field, reaching 146.4% and 96.0%, respectively. This indicates that the method of the present invention can keenly capture the micro-situational changes caused by load pointing changes and relative motion fluctuations, while the traditional spherical model ignores such dynamic characteristics, resulting in a flat situation curve that is difficult to reflect transient risks.

[0090] Based on the above definition of threat identification, the number of threat events obtained based on the geometric distance criterion, the number of consecutive time periods identified by the capability domain strip of the present invention, and the number of consecutive time periods identified by the capability domain strip of the traditional sphere model were statistically analyzed. The statistical results are shown in Table 4 below: Table 4. Statistical Results of Threat Event Identification Threat identification based on the geometric occlusion potential field of the method of this invention for: ; Threat identification based on geometric occlusion potential field using traditional spherical model for: ; Threat identification accuracy of directional wave velocity potential field based on the method of this invention for: ; Threat identification of directional wave velocity potential field based on traditional spherical model for: ; Threat identification based on the kinematic dynamic potential field of the method of this invention for: ; Threat identification based on the kinematic dynamic potential field of the traditional sphere model for: ; Define the threat recognition improvement rate of the method of this invention compared to the traditional sphere model. for: ; The threat recognition rate of the geometric occlusion potential field is improved. for: ; Threat identification rate improvement of directional beam potential field for: ; Threat recognition improvement rate of kinematic dynamic potential field for: ; Average improvement rate of threat identification for three types of environment-dependent payloads for: ; Therefore, the method of this invention achieves an average threat identification rate improvement of 151.85% for the three types of environment-dependent loads, and maintains a threat identification rate above 0.85 under various environmental constraints, with the highest rate reaching 0.95 in the directional beam potential field, demonstrating extremely high reliability. In contrast, the traditional spherical model has threat identification rates of 0.33 and 0.25 in the directional beam potential field and kinematic dynamic potential field, respectively, which easily generates a large number of false alarms and missed alarms, lacking decision-making reference value.

[0091] Simulation results verify the effectiveness and efficiency of the method of the present invention.

[0092] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention, and no reference numerals in the claims should be construed as limiting the scope of the claims.

[0093] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A method for characterizing the potential field of a satellite's orbital capability domain, characterized in that, include: All payloads carried on the satellite are divided into environment-independent payloads and environment-dependent payloads; The first action potential function of the environment-independent load is constructed by the radial kernel function. The first inherent capability domain corresponding to the environment-independent load is determined based on the first action potential function. The first inherent capability domain is mapped to the geocentric inertial frame to obtain the first instantaneous capability domain. Based on the first action potential function, multiple constraint component functions excited by environmental factors are integrated to construct the second action potential function of the environment-dependent load. Based on the second action potential function, the second inherent capability domain corresponding to the environment-dependent load is determined. The second inherent capability domain is mapped to the geocentric inertial frame to obtain the second instantaneous capability domain. Based on the macroscopic potential function, the first and second instantaneous capability domains are mapped into multiple functional potential field clusters, and the satellite's system capability domain is constructed based on these multiple functional potential field clusters.

2. The satellite orbital capability domain potential field characterization method according to claim 1, characterized in that, The first inherent capability domain corresponding to the environment-independent load includes a uniform spherical potential field, a bounded toroidal potential field, and a gradient-decayed potential field.

3. The satellite orbital capability domain potential field characterization method according to claim 2, characterized in that, The first potential function for environment-independent loads is constructed using a radial kernel function, including: Constructing the radial kernel function ,make ; in, The first potential function representing an environment-independent load. Denotes the first arbitrary point in three-dimensional Euclidean space. Represents the first arbitrary point Distance to the center of an environment-independent load.

4. The satellite orbital capability domain potential field characterization method according to claim 3, characterized in that, Mapping the first inherent capability domain to the geocentric inertial frame, the expression for the first instantaneous capability domain is: ； in, This represents the first instantaneous capability domain of an environment-independent payload, where s represents the satellite and t represents time. Indicates the real-time position of the satellite's orbit. The attitude matrix representing the satellite's orbit. This represents the first intrinsic capability domain for environment-independent loads. Minkowski and, Represents any point in inertial space. Represents three-dimensional Euclidean space. Represents the attitude matrix The transpose of the matrix, This indicates the matrix transpose.

5. The satellite orbital capability domain potential field characterization method according to claim 4, characterized in that, The second inherent capability domain corresponding to the environment-dependent load includes the geometrical obstruction potential field, the directional beam potential field, and the kinematic dynamic potential field.

6. The satellite orbital capability domain potential field characterization method according to claim 5, characterized in that, The expression for the second potential function of the geometrically obstructed potential field is: ； in, Let G represent the second potential function of the geometric occlusion potential field, and let G represent the geometric occlusion potential field. Denotes the second arbitrary point in three-dimensional Euclidean space. This indicates taking the maximum value. Represents the second arbitrary point Distance to the center of the environment-dependent load This represents the maximum radius of the spherical shell region. Represents the minimum radius of the spherical shell region. Indicates the half angle facing away from the cone. Represents the unit direction vector. This represents the unit vector pointing to by the satellite. This represents the azimuth angle of the k-th wedge structure. This represents the angle width of the k-th wedge structure. Represents the second arbitrary point azimuth angle, Let K represent the angle difference normalization function, and K represent the number of wedge structures.

7. The satellite orbital capability domain potential field characterization method according to claim 6, characterized in that, The expression for the second potential function of the directional beam potential field is: ； in, Let D represent the second potential function of the directional beam potential field, and let D represent the directional beam potential field. Represents any point in the beam coordinate system. , , Representing any point The three components, This represents the horizontal field of view of the main lobe region of the elliptical cone. This represents the pitch field of view of the main lobe region of the elliptical cone. Represents the tangent function. Indicates the center azimuth angle of the load. Indicates the angle width of the load. Represents any point The azimuth angle.

8. The satellite orbital capability domain potential field characterization method according to claim 1, characterized in that, The expression for the macroscopic potential function is: ； in, Let X represent the macroscopic potential function, and let X represent any functional potential cluster. Let t represent any point in inertial space, and let t represent time. This indicates taking the minimum value. This represents the instantaneous capability domain of the l-th load. This represents the set of loads belonging to the same functional potential cluster.

9. The satellite orbital capability domain potential field characterization method according to claim 8, characterized in that, The plurality of functional potential field clusters include: Query the potential field, which includes gradient decay potential field and geometric occlusion potential field; Interference capability potential fields, encompassing uniform spherical potential fields, directional beam potential fields, and kinematic dynamic potential fields; The strike capability potential field encompasses both the bounded cyclic potential field and the kinematic dynamic potential field. The system capability domain expression for a satellite constructed based on multiple functional potential field clusters is as follows: ； in, This represents the system capability domain of the satellite, where 's' represents the satellite. This indicates the number of functional potential clusters. This represents the union operation. The union symbol represents the set of sets. Let represent the macroscopic potential function of the i-th functional potential cluster at time t. It represents three-dimensional Euclidean space.

10. A satellite orbital capability domain potential field characterization device, used to implement the method described in any one of claims 1-9, characterized in that, include: The payload classification module is configured to classify all payloads carried on the satellite into environment-independent payloads and environment-dependent payloads; The inherent potential field characterization module is configured to construct the first action potential function of the environment-independent load through the radial kernel function, determine the first inherent capability domain corresponding to the environment-independent load based on the first action potential function, and map the first inherent capability domain to the geocentric inertial frame to obtain the first instantaneous capability domain. The coupled potential field characterization module is configured to, based on the first action potential function, integrate multiple constraint component functions excited by environmental factors to construct the second action potential function of the environment-dependent load, determine the second inherent capability domain corresponding to the environment-dependent load based on the second action potential function, and map the second inherent capability domain to the geocentric inertial frame to obtain the second instantaneous capability domain. The system capability characterization module is configured to map the first and second instantaneous capability domains into multiple functional potential field clusters based on the macroscopic action potential function, and to construct the satellite's system capability domain based on the multiple functional potential field clusters.

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