Satellite formation reconfiguration control method and system
By optimizing the small satellite formation reconfiguration control method and utilizing genetic algorithms and orbit recursion models, a pulse control strategy that meets the passive safety distance is generated, solving the problems of satellite collision and high fuel consumption in traditional methods, and achieving safe and efficient formation reconfiguration.
Patent Information
- Application Number
- CN202310547947.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2023-05-15
- Publication Date
- 2025-11-18
- Estimated Expiration
- 2043-05-15
AI Technical Summary
Traditional satellite formation reconfiguration control methods cannot effectively avoid small satellite collisions, resulting in low safety and high fuel consumption during the reconfiguration process.
Using the passive safety distance between small satellites as the optimization objective, a pulse control strategy is generated using a genetic algorithm. The strategy is then simulated and compared using an orbital recursion model to ensure that the distance between satellites meets the safety distance requirements and to avoid collisions.
It reduces fuel consumption during satellite formation reconfiguration and improves the safety of the reconfiguration process, avoiding satellite collisions.
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Figure CN116767514B_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of satellite formation control, and particularly relates to a satellite formation reconstruction control method and system. BACKGROUND
[0002] Compared with a traditional single large satellite, a small satellite formation can not only meet task requirements, but also has many advantages, such as small size, low cost, high reliability and strong flexibility. In order to prolong the on-orbit life of the satellite formation, the total fuel consumption required for formation configuration control is usually taken as an optimization target to obtain an impulse-based formation configuration reconstruction control optimization solution, but the traditional analytical fuel optimal solution cannot meet the collision avoidance problem in the reconstruction process, which is easy to cause damage to the small satellites in the small satellite formation reconstruction process, thereby increasing the risk of satellite reconstruction. SUMMARY
[0003] The present application discloses a satellite formation reconstruction control method and system, which takes a passive safety distance between small satellites as an optimization target to obtain a control scheme of an impulse control optimal solution of the small satellites, so as to control the small satellites to perform formation reconstruction, thereby reducing fuel consumption of the small satellites and improving the safety of small satellite formation reconstruction.
[0004] In order to achieve the above purpose, the present application discloses a satellite formation reconstruction control method, comprising:
[0005] According to preset reconstruction scene parameters and a fuel consumption formula, an impulse value in the satellite formation reconstruction process is obtained;
[0006] A plurality of first impulse control strategies corresponding to the impulse value are generated by a preset genetic algorithm, and the plurality of first impulse control strategies are filtered by a preset objective function and an optimization function in the genetic algorithm to generate a plurality of second impulse control strategies;
[0007] According to the plurality of second impulse control strategies, an orbit simulation is performed by a preset orbit recursion model to obtain passive safety distances respectively corresponding to the plurality of second impulse control strategies;
[0008] The passive safety distances respectively corresponding to the plurality of second impulse control strategies are compared with a preset distance threshold value respectively to obtain a third impulse control strategy corresponding to a passive safety distance greater than the distance threshold value;
[0009] The satellite formation is controlled to perform formation reconstruction according to the third impulse control strategy.
[0010] The application discloses a satellite formation reconstruction control method, after a scene parameter after formation reconstruction is acquired, a preset fuel consumption formula is used to obtain a pulse value required by a satellite formation to be formed in the case of minimum fuel consumption for formation reconstruction, so that fuel consumption during satellite formation reconstruction is reduced, then after the pulse value is obtained, the pulse value is input into a preset strategy model, a pulse control strategy corresponding to the pulse value is obtained by using the strategy model, then the pulse control strategy is input into a preset orbit recursion model, an orbit distance of a satellite corresponding to the pulse control strategy is output, and the orbit distance is compared with a preset distance threshold value, so that a distance between the satellites meets a passive safety distance requirement, collision between the satellites during formation reconstruction is avoided, and the safety of satellite formation reconstruction is improved, when the orbit distance is greater than or equal to the distance threshold value, the satellite to be formed is controlled by using the pulse control strategy to realize formation reconstruction.
[0011] As a preferred example, in the case of obtaining the pulse value in the satellite formation reconstruction process according to the preset reconstruction scene parameter and the fuel consumption formula, the following steps are specifically included:
[0012] The preset reconstruction scene parameter is processed by using a preset in-plane multi-pulse orbit transfer fuel optimal condition formula, and a pulse value required for each satellite in the plurality of satellites to complete formation reconstruction is obtained; the reconstruction scene parameter includes main star absolute orbit elements and relative orbit elements of a slave star before and after reconstruction.
[0013] The application uses a preset satellite formation reconstruction scene parameter and a preset fuel optimal condition formula to calculate and obtain a pulse value required for the satellite to complete formation reconstruction under the premise of meeting the fuel consumption optimal solution, so that the fuel consumption during satellite formation reconstruction is guaranteed to be the lowest.
[0014] As a preferred example, in the case of generating a plurality of first pulse control strategies corresponding to the pulse value by using a preset genetic algorithm, and filtering the plurality of first pulse control strategies by using a preset objective function and an optimization function in the genetic algorithm, the following steps are specifically included:
[0015] According to the pulse value, the pulse value is processed by using a preset genetic algorithm, and a plurality of first pulse control strategies are generated; the pulse control strategy includes a number of pulse applications, a single pulse application value and a pulse application time;
[0016] A passive safety distance corresponding to each pulse control strategy in the plurality of first pulse control strategies is calculated by using an objective function preset in the genetic algorithm;
[0017] According to the passive safety distance corresponding to each pulse control strategy, the optimization function preset in the genetic algorithm is used to filter the first pulse control strategies, and second pulse control strategies are generated.
[0018] The application discloses a method for generating pulse control strategies by using an optimized genetic algorithm according to pulse values of satellites, and then obtaining distances between satellite formations controlled according to the pulse control strategies by using a target function preset in the optimized genetic algorithm.
[0019] As a preferred example, the orbit distances between the satellites are obtained by using a preset orbit recursive model, and the method specifically comprises the following steps:
[0020] The orbit elements corresponding to the second pulse control strategies are obtained by using orbit element calculation equations preset in the orbit recursive model.
[0021] According to the orbit elements, passive safety distances corresponding to the orbit elements are obtained by using a passive safety distance calculation formula preset in the orbit recursive model.
[0022] After the pulse control strategies are obtained, orbit elements of the satellites after formation reconstruction are obtained by using orbit element calculation equations in a preset orbit recursive model, passive safety distances are generated according to the orbit elements, and whether the model meets passive safety requirements is determined according to the passive safety distances, so that the safety of formation reconstruction is improved.
[0023] In a second aspect, the application discloses a satellite formation reconstruction control system, which comprises a pulse module, a strategy module, a simulation module and a control module.
[0024] The pulse module is used to obtain pulse values in a satellite formation reconstruction process according to preset reconstruction scene parameters and a fuel consumption formula.
[0025] The strategy module is used to generate first pulse control strategies corresponding to the pulse values by using a preset genetic algorithm, and to filter the first pulse control strategies by using a target function and an optimization function preset in the genetic algorithm, so as to generate second pulse control strategies.
[0026] The simulation module is configured to simulate orbits according to the second pulse control strategies by a preset orbit recursion model, and obtain passive safety distances corresponding to the second pulse control strategies respectively.
[0027] The control module is configured to compare the passive safety distances corresponding to the second pulse control strategies respectively with a preset distance threshold, obtain a third pulse control strategy corresponding to a passive safety distance greater than the distance threshold, and control the satellite formation to reconstruct the formation according to the third pulse control strategy.
[0028] The application discloses a satellite formation reconstruction control method. After obtaining scene parameters after formation reconstruction, a preset fuel consumption formula is used to obtain a pulse value required for the satellite formation to be formed to reconstruct the formation in a case of minimum fuel consumption, so as to reduce fuel consumption during satellite formation reconstruction. Then, the pulse value is input into a preset strategy model, the strategy model is used to obtain a pulse control strategy corresponding to the pulse value, the pulse control strategy is input into a preset orbit recursion model, an orbit distance corresponding to the pulse control strategy is output, and the orbit distance is compared with a preset distance threshold, so that the distance between the satellites meets the passive safety distance requirement, collision between the satellites during formation reconstruction is avoided, and the safety of satellite formation reconstruction is improved. When the orbit distance is greater than or equal to the distance threshold, the pulse control strategy is used to control the satellite to be reconstructed to realize formation reconstruction.
[0029] As a preferred example, the strategy module comprises a first strategy unit and a second strategy unit.
[0030] The first strategy unit is configured to process the pulse value by a preset genetic algorithm according to the pulse value, and generate a plurality of first pulse control strategies. The pulse control strategy comprises a pulse application frequency, a single pulse application value and a pulse application time.
[0031] The second strategy unit is configured to calculate a passive safety distance corresponding to each pulse control strategy in the plurality of first pulse control strategies by a target function preset in the genetic algorithm, filter the plurality of first pulse control strategies by an optimization function preset in the genetic algorithm according to the passive safety distance corresponding to each pulse control strategy, and generate a plurality of second pulse control strategies.
[0032] The application discloses a method for generating a plurality of pulse control strategies according to pulse values of satellites, calculating distances between satellite formations after the satellite formations are controlled according to the pulse control strategies, and continuously optimizing the pulse control strategies according to preset constraint conditions to generate a plurality of second pulse control strategies.
[0033] As a preferred example, the simulation module comprises an orbit unit and a distance unit.
[0034] The orbit unit is configured to perform orbit simulation on the second pulse control strategies respectively according to orbit element calculation equations preset in an orbit recursive model to obtain orbit elements corresponding to the second pulse control strategies respectively.
[0035] The distance unit is configured to obtain passive safety distances corresponding to the orbit elements according to the orbit elements and a passive safety distance calculation formula preset in the orbit recursive model.
[0036] After the pulse control strategies are obtained, orbit elements of the satellites after the satellites are reconstructed according to the pulse control strategies are obtained according to orbit element calculation equations in a preset orbit recursive model, passive safety distances are generated according to the orbit elements, and whether the model meets passive safety requirements is determined according to the passive safety distances, so that the safety of formation reconstruction is improved.
[0037] As a preferred example, the control module comprises a comparison unit and a control unit.
[0038] The comparison unit is configured to compare passive safety distances corresponding to the second pulse control strategies respectively with a preset distance threshold to obtain third pulse control strategies corresponding to passive safety distances greater than the distance threshold.
[0039] The control unit is configured to control the satellite formation to perform formation reconstruction according to the third pulse control strategies.
[0040] The passive safety distances output by the orbit recursive model are compared with a preset distance threshold, so that whether the pulse control strategies meet passive safety parameter requirements is determined, and the safety of formation reconstruction is improved.
[0041] In a third aspect, the present application discloses a computer readable storage medium, which stores a computer program, and the program is executed by a processor to realize the satellite formation reconfiguration control method according to the first aspect.
[0042] In a fourth aspect, the present application discloses an electronic device, which comprises at least one processor, and a storage device configured to store at least one program, and when the at least one program is executed by the at least one processor, the at least one processor realizes the satellite formation reconfiguration control method according to the first aspect. BRIEF DESCRIPTION OF DRAWINGS
[0043] Figure 1 FIG. 1 is a flowchart of a satellite formation reconfiguration control method provided by an embodiment of the present application;
[0044] Figure 2 FIG. 2 is a structural diagram of a satellite formation reconfiguration control system provided by an embodiment of the present application. DETAILED DESCRIPTION
[0045] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative efforts fall within the scope of the present application.
[0046] EMBODIMENT
[0047] The satellite formation reconfiguration control method provided by the embodiments of the present application is described below with reference to FIG. 1. Figure 1 The method comprises steps 101 to 104, which are as follows.
[0048] Step 101: obtaining impulse values in the satellite formation reconfiguration process according to preset reconfiguration scene parameters and a fuel consumption formula.
[0049] In this embodiment, this step mainly comprises: processing the preset reconfiguration scene parameters by using a preset fuel-optimal condition formula of in-plane multi-impulse orbit transfer to obtain impulse values of each satellite in the plurality of satellites for completing formation reconfiguration; and the reconfiguration scene parameters comprise absolute orbit elements of a primary satellite and relative orbit elements of a secondary satellite before and after reconfiguration.
[0050] In this embodiment, this step specifically comprises: based on the preset reconfiguration scene parameters, i.e., the absolute orbit elements of the primary satellite and the relative orbit elements of the secondary satellite before and after reconfiguration, the fuel-optimal condition formula of in-plane multi-impulse orbit transfer is brought in as follows: The minimum total pulse value ΔV needed to complete the orbit reconstruction can be calculated RT , that is, the maximum value of a single pulse.
[0051] Step 102: A plurality of first pulse control strategies corresponding to the pulse value are generated by a preset genetic algorithm, and the plurality of first pulse control strategies are filtered by a preset target function and an optimization function in the genetic algorithm to generate a plurality of second pulse control strategies.
[0052] In this embodiment, the step mainly includes: according to the pulse value, a plurality of first pulse control strategies are generated by processing the pulse value through a preset genetic algorithm; the pulse control strategy includes the number of pulse applications, the single pulse application value and the pulse application time; the passive safety distance corresponding to each pulse control strategy in the plurality of first pulse control strategies is calculated by a target function preset in the genetic algorithm; and the plurality of first pulse control strategies are filtered by an optimization function preset in the genetic algorithm according to the passive safety distance corresponding to each pulse control strategy to generate a plurality of second pulse control strategies.
[0053] In this embodiment, the step specifically includes: according to the minimum total pulse value ΔV RT , the number of pulse applications is randomly generated by a preset genetic algorithm, that is, the number of pulse applications m is set to be any value, and the pulse strategy corresponding to m times of pulse applications is ΔV RT = {(ΔV RT ) j ; u j}, where j ∈ (1, m), u j corresponds to the time of pulse application. When the last pulse (ΔV RT ) m is applied, the relative orbit element value approaches the ideal final state (S RT ) f , it is indicated that the configuration reconstruction pulse control strategy is effective, and the fuel consumption index of the strategy can be calculated according to formula (1):
[0054]
[0055] Then, the satellite formation configuration reconstruction time is regarded as a constant, the maximization of the passive safety distance is focused on, the direction and size of the assumed number of pulses are obtained by an optimization algorithm, and the target function is:
[0056]
[0057] where R j is the distance between the satellite formation corresponding to each pulse application, and
[0058]
[0059] The passive safety distance at this time is the minimum value of the multiple pulse corresponding distances, and the minimum value of the multiple pulse corresponding distances is maximized by using a preset constraint function, as shown in formula (3).
[0060]
[0061] First, assuming that the number of in-plane pulses is n, the constraint condition formula (3) is expanded as follows:
[0062] 2(ΔV 1T +ΔV 2T +…+ΔV nT ) / n=|Δa0-Δa f |=0 (4)
[0063] -3(Δt2+…+Δt n +t)ΔV 1T / a-3(Δt3+…+Δt n +t)ΔV 2T / a
[0064] -…-3tΔV nT / a=du=0 (5)
[0065] 2(|ΔV 1T |+|ΔV 2T |+…+|ΔV nT |) / (na)=|Δe f -Δe0| (6)
[0066] According to the above objective function and constraint function, a plurality of pulse control strategies are obtained.
[0067] Step 103: According to the plurality of second pulse control strategies, the orbit simulation is performed by using a preset orbit recursive model, and the passive safety distances corresponding to the plurality of second pulse control strategies are obtained.
[0068] In this embodiment, this step mainly includes: performing orbit simulation on the plurality of second pulse control strategies by using orbit element calculation equations preset in the orbit recursive model, and obtaining orbit elements corresponding to the second pulse control strategies, respectively; and according to the orbit elements, the passive safety distances corresponding to the orbit elements are obtained by using a passive safety distance calculation formula preset in the orbit recursive model.
[0069] In the embodiment, the step is specifically: obtaining a plurality of second pulse control strategies by using the orbit recursive model to perform orbit simulation on the orbit elements, in the embodiment, the orbit recursive model is composed of a formation configuration control mechanism described by an E / I vector, a relative distance calculation formula of relative motion in a plane in a radial direction and along a track direction, and a relative orbit transfer calculation formula in the plane, in the embodiment, the formation configuration control mechanism described by the E / I vector is known from the formula (7):
[0070]
[0071] wherein Δe is a relative eccentricity vector, φ is a phase angle of the relative eccentricity vector, δe is a relative eccentricity vector coefficient, and At the same time, we can obtain sinφ=Δe y / δe,cosφ=Δe x / δe.
[0072] The relative distance of the relative motion in the plane in the radial direction and along the track direction can be described by orbit elements as follows:
[0073] Δr R =Δa-aδecos(u-φ) (8)
[0074]
[0075] wherein Δr R is a radial projection of the relative motion, Δr T is a projection of the relative motion in the along-track direction, a is a semi-major axis of the main satellite, Δa is a relative semi-major axis difference of the deputy satellite relative to the main satellite, u is a latitude amplitude angle, u0 is an initial value of the latitude amplitude angle, Δl=Δu+ΔΩcos i represents a relative longitude, sinφ=Δe y / δe,cosφ=Δe x / δe.
[0076] Since keeping the satellite formation stable means that the relative semi-major axis difference is zero, Δa=0 is substituted into the formula (2) and (3), and it is obtained that the motion in the plane is an ellipse with (0,aΔl) as the center and an eccentricity of Δe. The parameter vector of the relative motion in the plane is defined as: S RT =(aδe,aΔl,Δa,φ), and then the relative orbit transfer problem in the plane can be represented as: transferring the relative orbit from an initial state (S RT )0=(aδe0,aΔl0,Δa0,φ0) to a final state (S RT ) f =(aδe f ,aΔl f ,Δaf , φ f ). Wherein φ f may be fixed or free, which corresponds to two different situations of the relative orbit transfer problem in the plane. The relative orbit transfer problem in the plane can be solved by solving the simplified Gauss equation (10) based on the relative orbit elements:
[0077]
[0078] Wherein dΔa, dδe x , dδe y and dΔu are the orbit element difference after the radial and tangential impulse ΔV RT = [ΔV R ΔV T ] T After the impulse control strategy obtained by the genetic algorithm is input into the model based on the orbit recursive model, the orbit elements of the satellite formation reconstruction can be obtained.
[0079] After the orbit elements are obtained, the passive safety distance corresponding to the orbit elements is obtained by using the passive safety distance calculation formula preset in the orbit recursive model, and the passive safety distance calculation formula is as formula:
[0080]
[0081] The satellite formation reconstruction impulse strategy searched by the genetic algorithm is input into the orbit recursive program for parameter verification, and the actual orbit and passive safety parameters are output. Compared with the predetermined relative orbit elements after reconstruction and the predetermined passive safety parameter requirements, the obtained satellite formation reconstruction impulse strategy ΔV RT = {(ΔV RT ) j ;u j} is optimized effectively, which can meet the reconstruction requirements and passive safety requirements.
[0082] Step 104: comparing the passive safety distances corresponding to the plurality of second impulse control strategies respectively with the preset distance threshold value respectively, obtaining the third impulse control strategy corresponding to the passive safety distance greater than the distance threshold value, and controlling the satellite formation to perform formation reconstruction according to the third impulse control strategy.
[0083] On the other hand, the application discloses a satellite formation reconstruction control system, which comprises an impulse module 201, a strategy module 202, a simulation module 203 and a control module 204.
[0084] The pulse module 201 is configured to obtain a pulse value in a satellite formation reconstruction process according to a preset reconstruction scene parameter and a fuel consumption formula.
[0085] The strategy module 202 is configured to generate a plurality of first pulse control strategies corresponding to the pulse value by a preset genetic algorithm, and filter the plurality of first pulse control strategies by a preset objective function and an optimization function in the genetic algorithm to generate a plurality of second pulse control strategies.
[0086] The simulation module 203 is configured to perform orbit simulation according to the plurality of second pulse control strategies by a preset orbit recursive model to obtain passive safety distances corresponding to the plurality of second pulse control strategies respectively.
[0087] The control module 204 is configured to compare the passive safety distances corresponding to the plurality of second pulse control strategies respectively with a preset distance threshold to obtain a third pulse control strategy corresponding to a passive safety distance greater than the distance threshold, and control the satellite formation to perform formation reconstruction according to the third pulse control strategy.
[0088] In this embodiment, the strategy module 202 includes a first strategy unit and a second strategy unit.
[0089] The first strategy unit is configured to process the pulse value by a preset genetic algorithm according to the pulse value to generate a plurality of first pulse control strategies; the pulse control strategy includes a pulse application times, a single pulse application value and a pulse application time.
[0090] The second strategy unit is configured to calculate a passive safety distance corresponding to each pulse control strategy in the plurality of first pulse control strategies by an objective function preset in the genetic algorithm; and filter the plurality of first pulse control strategies by an optimization function preset in the genetic algorithm according to the passive safety distance corresponding to each pulse control strategy to generate a plurality of second pulse control strategies.
[0091] In this embodiment, the simulation module 203 includes an orbit unit and a distance unit.
[0092] The orbit unit is configured to perform orbit simulation on the plurality of second pulse control strategies respectively by an orbit element calculation equation preset in the orbit recursive model to obtain orbit elements corresponding to the second pulse control strategies respectively.
[0093] The distance unit is configured to obtain passive safety distances corresponding to the orbit elements by a passive safety distance calculation formula preset in the orbit recursive model according to the orbit elements.
[0094] In the embodiment, the control module 204 comprises a comparison unit and a control unit.
[0095] The comparison unit is configured to compare the passive safety distance corresponding to each of the second pulse control strategies with a preset distance threshold, and obtain a third pulse control strategy corresponding to the passive safety distance greater than the distance threshold.
[0096] The control unit is configured to control the satellite formation to perform formation reconstruction according to the third pulse control strategy.
[0097] In addition to the above method and system, the embodiment of the present application also provides a computer readable storage medium, which stores a computer program, and the program is executed by a processor to realize a satellite formation reconstruction control method as described in the embodiment, and an electronic device is also provided, which comprises at least one processor, and a storage device configured to store at least one program, and when the at least one program is executed by the at least one processor, the at least one processor realizes a satellite formation reconstruction control method as described in the embodiment.
[0098] The satellite formation reconstruction control method and system disclosed by the present application, after obtaining the scene parameters after formation reconstruction, obtain the pulse value required for the satellite formation to be formed to perform formation reconstruction in the case of minimum fuel consumption by using a preset fuel consumption formula, so as to reduce the fuel consumption during satellite formation reconstruction, then input the pulse value into a preset strategy model, obtain the pulse control strategy corresponding to the pulse value by using the strategy model, then input the pulse control strategy into a preset orbit recursion model, output the orbit distance of the satellite corresponding to the pulse control strategy, and compare the orbit distance with a preset distance threshold, so that the distance between the satellites meets the passive safety distance requirement, avoids collision between the satellites during formation reconstruction, and improves the safety of satellite formation reconstruction. When the orbit distance is greater than or equal to the distance threshold, the satellite to be formed for formation reconstruction is controlled to realize formation reconstruction by using the pulse control strategy.
[0099] The above specific embodiments further illustrate the purpose, technical solutions and advantages of the present application. It should be understood that the above description is only for specific embodiments of the present application and is not used to limit the protection scope of the present application. It should be particularly pointed out that any modification, equivalent replacement, improvement, etc. made by those skilled in the art within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims
1. A satellite formation reconfiguration control method, characterized in that, include: Based on the preset reconstruction scenario parameters and fuel consumption formula, the pulse values during the satellite formation reconstruction process are obtained; wherein, the preset reconstruction scenario parameters are processed by the preset in-plane multi-pulse orbit transfer fuel optimal condition formula to obtain the pulse value of each of the several satellites when the formation reconstruction is completed; the reconstruction scenario parameters include the absolute orbital elements of the primary satellite and the relative orbital elements of the secondary satellites before and after reconstruction. A preset genetic algorithm is used to generate several first pulse control strategies corresponding to the pulse value, and the preset objective function and optimization function in the genetic algorithm are used to filter the several first pulse control strategies to generate several second pulse control strategies. The orbit is simulated according to the plurality of second pulse control strategies by using a preset orbit recursive model to obtain the passive safety distances corresponding to the plurality of second pulse control strategies respectively; wherein, the orbit recursive model consists of the formation configuration control mechanism described by the E / I vector, the relative distance calculation formula in the radial and along-track directions of the relative motion in the plane, and the relative orbit transfer calculation formula in the plane; The passive safety distances corresponding to the plurality of second pulse control strategies are compared with preset distance thresholds to obtain a third pulse control strategy corresponding to a passive safety distance greater than the distance threshold, and the satellite formation is controlled to reconfigure the formation according to the third pulse control strategy.
2. The satellite formation reconfiguration control method as described in claim 1, characterized in that, The process of generating several first pulse control strategies corresponding to the pulse value using a preset genetic algorithm, and filtering the several first pulse control strategies using a preset objective function and optimization function in the genetic algorithm, specifically includes: Based on the pulse value, a preset genetic algorithm is used to process the pulse value to generate several first pulse control strategies; the pulse control strategy includes the number of pulses applied, the value of a single pulse application, and the pulse application time; The passive safety distance corresponding to each of the several first pulse control strategies is calculated by using the objective function preset in the genetic algorithm; Based on the passive safety distance corresponding to each pulse control strategy, the plurality of first pulse control strategies are filtered by the optimization function preset in the genetic algorithm to generate a plurality of second pulse control strategies.
3. The satellite formation reconfiguration control method as described in claim 1, characterized in that, The process of obtaining the orbital distances between the satellites using a preset orbital recursion model specifically includes: The orbital elements of the several second pulse control strategies are simulated by pre-setting the orbital element calculation equations in the orbital recursive model, and the orbital elements corresponding to the second pulse control strategies are obtained respectively. Based on the track elements, the passive safety distance corresponding to the track elements is obtained by using the passive safety distance calculation formula preset in the track recursive model.
4. A satellite formation reconfiguration control system, characterized in that, It includes a pulse module, a strategy module, an analog module, and a control module; The pulse module is used to obtain the pulse value during the satellite formation reconstruction process according to the preset reconstruction scenario parameters and fuel consumption formula; wherein, the preset reconstruction scenario parameters are processed by the preset in-plane multi-pulse orbit transfer fuel optimal condition formula to obtain the pulse value of each of the plurality of satellites when the formation reconstruction is completed; the reconstruction scenario parameters include the absolute orbital elements of the master satellite and the relative orbital elements of the slave satellites before and after reconstruction. The strategy module is used to generate several first pulse control strategies corresponding to the pulse value through a preset genetic algorithm, and to filter the several first pulse control strategies through the preset objective function and optimization function in the genetic algorithm to generate several second pulse control strategies. The simulation module is used to perform orbit simulation based on the plurality of second pulse control strategies using a preset orbit recursive model, and to obtain the passive safety distances corresponding to the plurality of second pulse control strategies respectively; wherein, the orbit recursive model consists of the formation configuration control mechanism described by the E / I vector, the relative distance calculation formulas in the radial and along-track directions of the relative motion in the plane, and the relative orbit transfer calculation formulas in the plane; The control module is used to compare the passive safety distances corresponding to the plurality of second pulse control strategies with preset distance thresholds, obtain the third pulse control strategy corresponding to the passive safety distance greater than the distance threshold, and control the satellite formation to reconfigure the formation according to the third pulse control strategy.
5. A satellite formation reconfiguration control system as described in claim 4, characterized in that, The strategy module includes a first strategy unit and a second strategy unit; The first strategy unit is used to process the pulse value according to the pulse value using a preset genetic algorithm to generate a plurality of first pulse control strategies; The pulse control strategy includes the number of pulses applied, the value of a single pulse application, and the pulse application time; The second strategy unit is used to calculate the passive safety distance corresponding to each of the plurality of first pulse control strategies through the objective function preset in the genetic algorithm; based on the passive safety distance corresponding to each pulse control strategy, the plurality of first pulse control strategies are filtered through the optimization function preset in the genetic algorithm to generate a plurality of second pulse control strategies.
6. A satellite formation reconfiguration control system as described in claim 4, characterized in that, The simulation module includes a track unit and a distance unit; The track unit is used to perform track simulation on the plurality of second pulse control strategies respectively by using the track element calculation equations preset in the track recursive model, and obtain the track elements corresponding to the second pulse control strategies respectively. The distance unit is used to obtain the passive safety distance corresponding to the track element based on the track element and through the passive safety distance calculation formula preset in the track recursive model.
7. A satellite formation reconfiguration control system as described in claim 4, characterized in that, The control module includes a comparison unit and a control unit; The comparison unit is used to compare the passive safety distances corresponding to the plurality of second pulse control strategies with preset distance thresholds to obtain the third pulse control strategy corresponding to a passive safety distance greater than the distance threshold. The control unit is used to control the satellite formation to reconfigure according to the third pulse control strategy.
8. A computer-readable storage medium, characterized in that, It stores a computer program that, when executed by a processor, implements a satellite formation reconfiguration control method as described in any one of claims 1 to 3.
9. An electronic device, characterized in that, include: At least one processor; A storage device configured to store at least one program, which, when executed by the at least one processor, causes the at least one processor to implement a satellite formation reconfiguration control method as described in any one of claims 1 to 3.