CN116166049A - Inter-star distance maintaining control method for unstable multi-star serial formation system - Google Patents
Inter-star distance maintaining control method for unstable multi-star serial formation system Download PDFInfo
- Publication number
- CN116166049A CN116166049A CN202310454702.6A CN202310454702A CN116166049A CN 116166049 A CN116166049 A CN 116166049A CN 202310454702 A CN202310454702 A CN 202310454702A CN 116166049 A CN116166049 A CN 116166049A
- Authority
- CN
- China
- Prior art keywords
- satellites
- satellite
- distance
- target reference
- orbit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000015572 biosynthetic process Effects 0.000 title claims abstract description 146
- 238000000034 method Methods 0.000 title claims abstract description 42
- 238000012423 maintenance Methods 0.000 claims abstract description 110
- 238000011217 control strategy Methods 0.000 claims abstract description 26
- 230000010363 phase shift Effects 0.000 claims description 3
- 239000000446 fuel Substances 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 5
- 238000004458 analytical method Methods 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 238000007726 management method Methods 0.000 description 2
- 239000013566 allergen Substances 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009918 complex formation Effects 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
- G05D1/104—Simultaneous control of position or course in three dimensions specially adapted for aircraft involving a plurality of aircrafts, e.g. formation flying
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The disclosure relates to an inter-star distance maintenance control method for an unstable multi-star serial formation system. The method comprises the following steps: each satellite in the formation system is respectively used as a candidate reference satellite, and a target reference satellite in the formation system is determined according to the relative orbit attenuation rate of other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite; converting the distance constraint between satellites in the formation system into the distance maintenance constraint between other satellites in the formation system and the target reference satellite; selecting a formation distance maintenance control strategy according to the distance maintenance constraint, the relative position relation and the self-orbit attenuation rate of other satellites in the formation system and the target reference satellite; the distance hold control is planned based on a hold control strategy. The method can be used for guiding the multi-satellite short-distance formation low-orbit satellite system with different load types, different face quality ratios and different control performances to develop distance maintenance control work, effectively reduce configuration maintenance control batches and save satellite fuel.
Description
Technical Field
The disclosure relates to the technical field of spacecraft measurement and control, in particular to an inter-satellite distance maintenance control method of an unstable multi-satellite serial formation system.
Background
The multi-star formation system realizes data acquisition, processing and analysis through inter-star cooperative work, can complete a plurality of complex space tasks, and has wide application prospects in the fields of space science, space application, space safety and the like. In particular to a short-distance serial formation system consisting of a plurality of satellites with different load types, which can realize cooperative application of quick sensing, comprehensive reconnaissance, tracking monitoring and the like. The satellites of the system have different loads, different surface quality ratios and different track attenuation rates, are unstable formation, have complex formation distance maintenance control constraint conditions and have certain technical difficulty; the risk of inter-satellite collision is high, and the requirement for controlling the retaining ring is high; frequent control, more control batches and large workload.
Accordingly, there is a need to provide a new solution to ameliorate one or more of the problems presented in the above solutions.
It should be noted that the information disclosed in the above background section is only for enhancing understanding of the background of the present disclosure and thus may include information that does not constitute prior art known to those of ordinary skill in the art.
Disclosure of Invention
It is an object of the present disclosure to provide a method of maintaining control of inter-star distances of an unstable multi-star serial formation system, which overcomes one or more problems due to limitations and disadvantages of the related art, at least to some extent.
According to the inter-star distance maintenance control method for the unstable multi-star serial formation system provided by the embodiment of the disclosure, the method comprises the following steps:
each satellite in the formation system is respectively used as a candidate reference satellite, and a target reference satellite in the formation system is determined according to the relative orbit attenuation rate of other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite;
converting the distance constraint between satellites in the formation system into the distance maintenance constraint between other satellites in the formation system and the target reference satellite;
selecting a formation distance maintenance control strategy according to the distance maintenance constraint, the relative position relation and the self-orbit attenuation rate of other satellites in the formation system and the target reference satellite;
and planning a distance maintenance control based on the maintenance control strategy.
In an embodiment of the disclosure, the step of determining the target reference satellite in the formation system according to the relative orbit attenuation rate of the other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite by using each satellite in the formation system as the candidate reference satellite includes:
And calculating the relative orbit attenuation rates of other satellites in the formation system and the candidate reference star.
In an embodiment of the disclosure, the step of determining the target reference satellite in the formation system according to the relative orbit attenuation rate of the other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite by using each satellite in the formation system as the candidate reference satellite includes:
and summing absolute values of the relative orbit attenuation rates of the other satellites corresponding to each candidate reference satellite to obtain the comprehensive orbit attenuation rate of the candidate reference satellite.
In an embodiment of the disclosure, the step of summing absolute values of the relative orbit attenuation rates of the other satellites corresponding to each candidate reference satellite to obtain a comprehensive orbit attenuation rate of the candidate reference satellite includes:
and drawing relative orbit attenuation rate distribution curves of other satellites corresponding to different candidate reference satellites according to the relative orbit attenuation rates of each candidate reference satellite and other satellites and each candidate reference satellite, and selecting the candidate reference satellite with the concentrated relative orbit attenuation rate distribution and the minimum comprehensive orbit attenuation rate as the target reference satellite by combining the comprehensive orbit attenuation rate of each candidate reference satellite.
In an embodiment of the disclosure, the step of selecting the formation distance maintenance control policy according to a distance maintenance constraint, a relative positional relationship, and a self-orbit attenuation rate of the other satellites in the formation system and the target reference satellite includes:
the other satellites are positioned in front of the target reference star and the self-orbit attenuation rate of the target reference star is smaller than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the right, when the satellites are positioned at the maximum distance of the distance retaining constraint in front of the target reference star and the orbit of the satellites is higher than that of the target reference star, the satellites drift backwards relative to the target reference star, after a preset period of time, the satellites drift forwards relative to the target reference star and reach the maximum distance of the distance retaining constraint in front of the target reference star again, and when the orbit of the satellites is lower than that of the target reference star, the orbit of the satellites is controlled to rise; the preset distance threshold is a maximum distance from a minimum distance of the distance keeping constraint to the distance keeping constraint.
In an embodiment of the disclosure, the step of selecting the formation distance maintenance control policy according to a distance maintenance constraint, a relative positional relationship, and a self-orbit attenuation rate of the other satellites in the formation system and the target reference satellite includes:
the other satellites are in front of the target reference star, the self-orbit attenuation rate of the target reference star is smaller than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the left, when the satellites are located at the minimum distance of the distance retaining constraint in front of the target reference star and the orbit of the satellites is lower than that of the target reference star, the satellites drift forward relative to the target reference star, after the preset time period, the satellites drift backward relative to the target reference star and reach the minimum distance of the distance retaining constraint in front of the target reference star again, and when the orbit of the satellites is lower than that of the target reference star, the orbit of the satellites is controlled to drop.
In an embodiment of the disclosure, the step of selecting the formation distance maintenance control policy according to a distance maintenance constraint, a relative positional relationship, and a self-orbit attenuation rate of the other satellites in the formation system and the target reference satellite includes:
The other satellites are positioned in a preset distance threshold behind the target reference star, the self-orbit attenuation rate of the target reference star is smaller than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the right, when the satellites are positioned at the minimum distance of the distance retaining constraint behind the target reference star and the orbit of the satellites is lower than that of the target reference star, the satellites drift backwards relative to the target reference star, after the preset time period, the satellites drift forwards relative to the target reference star, and the orbit of the satellites reaches the minimum distance of the distance retaining constraint behind the target reference star again, and when the orbit of the satellites is lower than that of the target reference star, the orbit of the satellites is controlled to rise.
In an embodiment of the disclosure, the step of selecting the formation distance maintenance control policy according to a distance maintenance constraint, a relative positional relationship, and a self-orbit attenuation rate of the other satellites in the formation system and the target reference satellite includes:
the other satellites are within a preset distance threshold behind the target reference star, the self-orbit attenuation rate of the target reference star is larger than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the left, when the satellite is positioned at the maximum distance of the distance retaining constraint behind the target reference star and the orbit of the satellite is lower than that of the target reference star, the satellites drift forwards relative to the target reference star, after the preset time period, the satellites drift backwards relative to the target reference star and reach the maximum distance of the distance retaining constraint behind the target reference star again, and when the orbit of the satellite is higher than that of the target reference star, the orbit of the satellites is controlled to drop.
In an embodiment of the disclosure, the step of planning the distance maintenance control based on the maintenance control policy includes:
and calculating the control quantity of the satellite and the configuration maintenance period of the satellite and the target reference star according to the semi-long axis, the orbital angular velocity and the daily semi-long axis attenuation of other satellites.
In an embodiment of the present disclosure, the calculating the control amount of the satellite according to the semi-long axis, the orbital angular velocity, the daily semi-long axis attenuation of the other satellites, and the configuration maintaining period of the satellite and the target reference star includes:
known as (i)
The semi-major axis of each of said satellites is +.>
Daily semi-major axis attenuation is +.>
Then->
The orbital angular velocity of the individual satellites>
The method comprises the following steps:
first, the
The orbital angular velocity of each of the satellites is derived over time as:
assume the first
The preset distance threshold value between the satellite and the target reference star is +.>
, wherein ,
indicate->
Keeping a constrained minimum distance, +.>
First->
The maximum distance at which the distance of each said satellite from said target reference star remains constrained is obtainable by formula (2)：
Then the first
The amount of phase shift of each of said satellites relative to said target reference star >
The method comprises the following steps: />
The controlled quantity can be obtained from formula (4)
The method comprises the following steps:
then the first
The configuration maintenance period of the satellite and the target reference star>
The method comprises the following steps:
wherein ,
is the gravitational constant->
。
The technical scheme provided by the embodiment of the disclosure can comprise the following beneficial effects:
according to one embodiment of the present disclosure, through the above method, on one hand, different satellites in a formation system are used as candidate reference satellites, relative orbit attenuation rates of other satellites in the formation system and the candidate reference satellites are calculated, distance maintenance control target reference satellite selection is performed, then a distance constraint between satellites is converted into a maintenance control requirement with the target reference satellite as an origin, and then a distance maintenance control strategy in the formation system is designed based on the distance maintenance constraint, the relative position relationship and the self orbit attenuation rate. The method can be used for guiding the multi-satellite short-distance formation low-orbit satellite systems with different load types, different face quality ratios and different control performances to develop distance maintenance control work, effectively reduce configuration maintenance control batches, save satellite fuel, reduce the influence on system application service, save human resources, improve the satellite management level of a space measurement and control unit and improve the economic benefit of the formation system.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the disclosure and together with the description, serve to explain the principles of the disclosure. It will be apparent to those of ordinary skill in the art that the drawings in the following description are merely examples of the disclosure and that other drawings may be derived from them without undue effort.
FIG. 1 schematically illustrates a flow chart of steps of a method for inter-star retention control of an unstable multi-star serial formation system in an exemplary embodiment of the present disclosure;
FIG. 2 schematically illustrates a schematic configuration of a multi-star close-range serial formation system in an exemplary embodiment of the present disclosure;
FIG. 3 schematically illustrates a multi-star close-range serial formation system configuration conversion schematic in an exemplary embodiment of the present disclosure;
FIG. 4 schematically illustrates a schematic view of a distance maintenance ring with a large relative track decay rate with a satellite in front of a target reference star in an exemplary embodiment of the present disclosure;
FIG. 5 schematically illustrates a schematic view of a distance maintenance ring with a small relative track decay rate with a satellite in front of a target reference star in an exemplary embodiment of the present disclosure;
FIG. 6 schematically illustrates a schematic view of a distance maintenance ring with a large relative track decay rate with a satellite behind a target reference star in an exemplary embodiment of the present disclosure;
FIG. 7 schematically illustrates a schematic view of a distance maintenance ring with a small relative track decay rate with a satellite behind a target reference star in an exemplary embodiment of the present disclosure;
FIG. 8 schematically illustrates a schematic configuration of a simulated tandem formation system in an exemplary embodiment of the present disclosure;
FIG. 9 schematically illustrates a schematic diagram of a relative orbital decay rate profile of different candidate reference satellites for other satellites in an exemplary embodiment of the disclosure;
FIG. 10 schematically illustrates a schematic diagram of different candidate reference satellites versus other satellite integrated orbit attenuation rates in an exemplary embodiment of the present disclosure;
FIG. 11 schematically illustrates the use of S in an exemplary embodiment of the present disclosure 2 Schematic diagram of the distance maintenance range of each satellite when the target reference is;
fig. 12 schematically illustrates a schematic diagram of formation distance maintenance control in an exemplary embodiment of the present disclosure.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. However, the exemplary embodiments may be embodied in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
Furthermore, the drawings are merely schematic illustrations of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus a repetitive description thereof will be omitted. Some of the block diagrams shown in the figures are functional entities and do not necessarily correspond to physically or logically separate entities. These functional entities may be implemented in software or in one or more hardware modules or integrated circuits or in different networks and/or processor devices and/or microcontroller devices.
The embodiment provides a method for controlling inter-star distance maintenance of an unstable multi-star serial formation system. Referring to what is shown in fig. 1, the method may include:
step S101: and respectively taking each satellite in the formation system as a candidate reference satellite, and determining a target reference satellite in the formation system according to the relative orbit attenuation rate of other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite.
Step S102: and converting the distance constraint between the satellites in the formation system into the distance maintenance constraint between the other satellites in the formation system and the target reference satellite.
Step S103: and selecting a formation distance maintenance control strategy according to the distance maintenance constraint, the relative position relation and the self-orbit attenuation rate of other satellites in the formation system and the target reference star.
Step S104: and planning a distance maintenance control based on the maintenance control strategy.
According to the method, on one hand, different satellites in the formation system are used as candidate reference satellites, the relative orbit attenuation rate of other satellites in the formation system and the candidate reference satellites is calculated, distance maintenance control target reference satellite selection is carried out, then the distance constraint among satellites is converted into a maintenance control requirement with the target reference satellite as an origin, and then a distance maintenance control strategy in the formation system is designed based on the distance maintenance constraint, the relative position relationship and the self orbit attenuation rate. The method can be used for guiding the multi-satellite short-distance formation low-orbit satellite systems with different load types, different face quality ratios and different control performances to develop distance maintenance control work, effectively reduce configuration maintenance control batches, save satellite fuel, reduce the influence on system application service, save human resources, improve the satellite management level of a space measurement and control unit and improve the economic benefit of the formation system.
Next, each step of the above-described method in the present exemplary embodiment will be described in more detail with reference to fig. 1 to 12.
In step S101, each satellite in the formation system is used as a candidate reference satellite, and a target reference satellite in the formation system is determined according to the relative orbit attenuation rate of the other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite. Specifically, as shown in fig. 2, a typical short-range multi-star serial formation satellite system consists of 6 satellites with different loads and different aspect ratios, wherein the formation configuration keeps the nominal distance between two adjacent satellites as S, and the distance constraint between the satellites is as follows
. If the control is performed according to the inter-satellite distance maintenance requirement, the position relation and attenuation trend of adjacent satellites need to be considered in the control of each satellite, each time of control of one satellite in the system causes the inter-satellite distance maintenance of other satellites to be more complex, and the regularity of each satellite control plan, control quantity determination, retaining ring selection and the like is poor, so that the whole formation system is poor. Therefore, if a certain satellite is selected as the target reference satellite, the maintenance control can be simplified and easy to implement, the overall control times of the formation system can be reduced, and the relative attenuation and maintenance control rules of each satellite can be easily grasped through long-term operation data analysis.
The selection of the distance maintenance target reference star is based on the principles of small overall control quantity of the formation system, relatively uniform control quantity of each satellite, less control batch and longer configuration maintenance time. Therefore, the target reference star can be selected based on the relative orbit attenuation rate of each satellite. According to the historical ephemeris of each satellite, different satellites are used as candidate reference satellites, and the daily relative orbit attenuation rate of other satellites and the candidate reference satellites in the formation system is calculated. The daily relative orbit attenuation rate of other satellites and candidate reference satellites in the formation system is used for determining target reference satellites in the formation system. The manner in which the target reference star in the queuing system is specifically determined is set forth in the following embodiments.
In step S102, a constraint on a distance between satellites in the formation system is converted into a constraint on a distance between other satellites in the formation system and the target reference satellite. Specifically, after the target reference star is determined, the inter-satellite constraint is converted into a maintenance control requirement with the target reference star as an origin, namely, the distance constraint among satellites in the formation system is converted into the distance maintenance constraint between other satellites and the target reference star, so that the subsequent selection of the formation distance maintenance control strategy is facilitated.
In one embodiment, the distance constraint between satellites in the formation system is:
the method comprises the steps of carrying out a first treatment on the surface of the Wherein S represents the nominal distance between two adjacent stars, < > or->
Representing a distance maintenance range error; the distances between other satellites and the target reference star in the formation system are kept constrained as follows: />
, wherein ,/>
Indicate->
Satellite (S),>
representing the minimum safe distance of inter-satellite collision prevention.
The formation system shown in fig. 2 reduces the risk of collision between satellites according to the control requirement of the formation system, and can convert the control requirement into the target reference satellite selected in step S102, and convert the tangential distance maintenance range of other satellites. A certain satellite is selected as a target reference star, which is defined as
The other satellites are sequentially arranged to the two sides with the target reference star as the center. Consider the minimum safe distance +.>
First->
Personal satellite->
And target reference star->
Can be converted into
As shown in fig. 3.
In step S103, a formation distance maintenance control strategy is selected according to the distance maintenance constraint, the relative positional relationship, and the self-orbit attenuation rate of the other satellites in the formation system and the target reference satellite. Specifically, the formation distance maintenance control strategy can be determined by keeping constraint on the distance between other satellites in the formation system and the target reference satellite, the relative position relationship between other satellites in the formation system and the target reference satellite, and the self-orbit attenuation rate of other satellites in the formation system and the self-orbit attenuation rate of the target reference satellite. The specific way of selecting the formation distance maintenance control strategy is described in the following embodiment, and details thereof are not described in this embodiment.
In step S104, distance hold control is planned based on the hold control strategy. Specifically, based on the above-determined maintenance control strategy, the distance maintenance control of each other satellite with respect to the target reference star is planned. Wherein, the distance maintenance control of other satellites relative to the target reference star is specifically planned and explained in the following embodiments.
In one embodiment, the step of determining the target reference satellite in the formation system according to the relative orbit attenuation rate of the other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite by using each satellite in the formation system as the candidate reference satellite includes:
and calculating the relative orbit attenuation rates of other satellites in the formation system and the candidate reference star. Specifically, according to the self-orbit attenuation rate of the candidate reference satellite, the self-orbit attenuation rate of other satellites in the formation system is calculated, and the relative orbit attenuation rate of the other satellites in the formation system and the candidate reference satellite is calculated.
In one embodiment, the step of determining the target reference satellite in the formation system according to the relative orbit attenuation rate of the other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite by using each satellite in the formation system as the candidate reference satellite includes:
And summing absolute values of the relative orbit attenuation rates of the other satellites corresponding to each candidate reference satellite to obtain the comprehensive orbit attenuation rate of the candidate reference satellite. Specifically, the absolute values of the relative orbit attenuation rates of other satellites corresponding to each candidate reference satellite are summed to obtain the comprehensive orbit attenuation rate of the candidate reference satellite. The comprehensive orbit attenuation rate of the candidate reference satellites is used for determining the target reference satellites in the formation system together with the relative orbit attenuation rate of other satellites corresponding to each candidate reference satellite in the subsequent process of determining the candidate reference satellites.
In one embodiment, the step of summing absolute values of the relative orbit attenuation rates of the other satellites corresponding to each candidate reference satellite to obtain a comprehensive orbit attenuation rate of the candidate reference satellite includes:
and drawing relative orbit attenuation rate distribution curves of other satellites corresponding to different candidate reference satellites according to the relative orbit attenuation rates of each candidate reference satellite and other satellites and each candidate reference satellite, and selecting the candidate reference satellite with the concentrated relative orbit attenuation rate distribution and the minimum comprehensive orbit attenuation rate as the target reference satellite by combining the comprehensive orbit attenuation rate of each candidate reference satellite. Specifically, a distribution curve of the relative orbit attenuation rates of other satellites corresponding to the candidate reference satellites is drawn through the relative orbit attenuation rates of other satellites and each candidate reference satellite in the formation system, then the comprehensive orbit attenuation rate of each candidate reference satellite is combined, the relative orbit attenuation rate distribution is concentrated, and the candidate reference satellite with the minimum comprehensive orbit attenuation rate is used as the target reference satellite.
Further, if the target reference satellite cannot be reasonably selected by the relative orbit attenuation rate of other satellites and the candidate reference satellite in the formation system and the comprehensive orbit attenuation rate of each candidate reference satellite, the control performance of the satellite needs to be further considered, and the control performance is a control step. The minimum firing time determines the control step size of the satellite and the policy optimization degree of the hold control. And counting the control step length of the formation system satellites, wherein the satellite control retaining ring with the long control step length is not easy to be optimized, and the control times of the satellite control retaining ring are reduced as much as possible, so that the satellite with the long control step length is preferably selected as a target reference satellite.
In the formation system, the relative orbit attenuation rate and the integrated orbit attenuation rate of other satellites and the target reference satellite directly determine the phase holding control amount and the overall control period of each satellite, so that a satellite with a smaller integrated orbit attenuation rate is preferentially selected as the target reference satellite. Under the condition that the comprehensive orbit attenuation rate is equivalent, a satellite with a larger control step length is selected as a target reference satellite.
In one embodiment, the step of selecting the formation distance maintenance control strategy according to the distance maintenance constraint, the relative position relation and the self-orbit attenuation rate of the other satellites in the formation system and the target reference satellite comprises the following steps:
The other satellites are positioned in front of the target reference star and the self-orbit attenuation rate of the target reference star is smaller than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the right, when the satellites are positioned at the maximum distance of the distance retaining constraint in front of the target reference star and the orbit of the satellites is higher than that of the target reference star, the satellites drift backwards relative to the target reference star, after a preset period of time, the satellites drift forwards relative to the target reference star and reach the maximum distance of the distance retaining constraint in front of the target reference star again, and when the orbit of the satellites is lower than that of the target reference star, the orbit of the satellites is controlled to rise; the preset distance threshold is a maximum distance from a minimum distance of the distance keeping constraint to the distance keeping constraint.
Specifically, any other satellite is in front of the target reference satellite, and the preset distance threshold is
，/>
Keep the maximum value of constraint for distance, +.>
The constraint minimum is maintained for distance. The self orbit attenuation rate of the target reference star is smaller than that of the satellite, the distance retaining ring between the satellite and the target reference star is a quadratic curve with an opening to the right, and when the satellite is positioned in front of the target reference star, the distance retaining constraint maximum value +. >
That is, the satellite is located +.>
At the moment, the orbit of the satellite is higher than the orbit of the Yu Mubiao reference satellite, the satellite drifts backwards relative to the target reference satellite, and after a preset period of time, the orbit of the satellite is lower than the orbit of the target reference satellite because the self-orbit attenuation rate of the satellite is higher than that of the target reference satellite, the satellite drifts forwards relative to the target reference satellite, and the distance is kept to be the maximum value of the constraint->
I.e. the satellite is located at
Where the orbit of the satellite is lower than that of the target reference satellite, the satellite is controlled to be up-orbited, and thus reciprocated, the distance between the satellite and the target reference satellite is maintained as shown in fig. 4.
In one embodiment, the step of selecting the formation distance maintenance control strategy according to the distance maintenance constraint, the relative position relation and the self-orbit attenuation rate of the other satellites in the formation system and the target reference satellite comprises the following steps:
the other satellites are in front of the target reference star, the self orbit attenuation rate of the target reference star is smaller than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the left, when the satellite is located at the minimum distance of the constraint of the distance in front of the target reference star and the orbit of the satellite is lower than that of the target reference star, the satellites drift forward relative to the target reference star, after the preset period, the satellites drift backward relative to the target reference star, and the orbit of the satellites reaches the minimum distance of the constraint of the distance in front of the target reference star again, and when the orbit of the satellites is lower than that of the target reference star, the orbit of the satellites is controlled to drop.
Specifically, any other satellite is in front of the target reference satellite, and the preset distance threshold is
The self orbit attenuation rate of the target reference star is larger than that of the satellite, the distance retaining ring of the satellite and the target reference star is a conic with an opening to the left, and the distance retaining ring is kept to be a constraint minimum distance when the distance of the satellite in front of the target reference star is +.>
That is, the satellite is located +.>
Where the satellite orbits below the targetThe orbit of the reference star drifts forward relative to the target reference star, and the orbit of the satellite drifts backward relative to the target reference star after the preset time period, and the satellite reaches the minimum distance of keeping constraint for the distance after the orbit of the satellite is higher than the orbit of the satellite because the self orbit attenuation rate of the target reference star is larger than the self orbit attenuation rate of the satellite>
That is, the satellite is located +.>
The orbit of the satellite is the orbit of the high Yu Mubiao reference satellite, the orbit of the satellite is controlled to be reduced, and the distance between the satellite and the target reference satellite is kept as shown in fig. 5.
In one embodiment, the step of selecting the formation distance maintenance control strategy according to the distance maintenance constraint, the relative position relation and the self-orbit attenuation rate of the other satellites in the formation system and the target reference satellite comprises the following steps:
The other satellites are positioned in a preset distance threshold behind the target reference star, the self-orbit attenuation rate of the target reference star is smaller than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the right, when the satellite is positioned at the minimum distance of the distance retaining constraint behind the target reference star and the orbit of the satellite is lower than that of the target reference star, the satellites drift backwards relative to the target reference star, after the preset time period, the satellites drift forwards relative to the target reference star, and the orbit of the satellites reaches the minimum distance of the distance retaining constraint behind the target reference star again, and when the orbit of the satellites is lower than that of the target reference star, the satellite is subjected to ascending control.
Specifically, any other satellite is behind the reference satellite, and the preset distance threshold is
The self orbit attenuation rate of the target reference star is smaller thanThe self orbit attenuation rate of the satellite, the distance retaining ring of the satellite and the target reference star is a quadratic curve with an opening rightward, and when the distance of the satellite behind the target reference star is kept to be the constrained minimum distance +. >
I.e. satellite is located +.>
The orbit of the satellite is lower than that of the target reference star, the satellite drifts backwards relative to the target reference star, and after a preset period of time, the orbit of the satellite is lower than that of the target reference star, the satellite drifts forwards relative to the target reference star, and the distance is kept to be the minimum distance of constraint again>
The satellite is located->
The orbit of the satellite is the orbit of the high Yu Mubiao reference satellite, the orbit of the satellite is controlled to be up-orbit, and the distance between the satellite and the target reference satellite is kept as shown in fig. 6.
In one embodiment, the step of selecting the formation distance maintenance control strategy according to the distance maintenance constraint, the relative position relation and the self-orbit attenuation rate of the other satellites in the formation system and the target reference satellite comprises the following steps:
the other satellites are within a preset distance threshold behind the target reference star, the self-orbit attenuation rate of the target reference star is larger than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the left, when the satellite is positioned at the maximum distance of the distance retaining constraint behind the target reference star and the orbit of the satellite is lower than that of the target reference star, the satellites drift forward relative to the target reference star, after the preset time period, the satellites drift backward relative to the target reference star, and the orbit of the satellites reaches the maximum distance of the distance retaining constraint behind the target reference star again, and when the orbit of the satellites is higher than that of the target reference star, the orbit of the satellites is controlled to drop.
Specifically, any other satellite is behind the target reference satellite, and the preset distance threshold is
The self orbit attenuation rate of the target reference star is larger than that of the satellite, the distance retaining ring of the satellite and the target reference star is a conic with an opening to the left, and the distance behind the target reference star is kept to be restricted by the maximum distance +.>
I.e. satellite is located +.>
The orbit of the satellite is lower than that of the target reference star, the satellite drifts forwards relative to the target reference star, the orbit of the satellite is higher than that of the Yu Mubiao reference star after the preset time period, the satellite drifts backwards relative to the target reference star, and the distance is kept to be the maximum distance of constraint>
The satellite is located->
The orbit of the satellite is lower than that of the target reference satellite, the orbit reduction control is carried out on the satellite, and the orbit reduction control is carried out on the satellite, so that the distance between the satellite and the target reference satellite keeps the ring as shown in figure 7.
In one embodiment, the step of planning the distance maintenance control based on the maintenance control strategy includes:
and calculating the control quantity of the satellite and the configuration maintenance period of the satellite and the target reference star according to the semi-long axis, the orbital angular velocity and the daily semi-long axis attenuation of other satellites. Specifically, the planning maintenance control mainly comprises the control quantity of the satellite and the configuration maintenance period of the satellite and the target reference star. The control amount of the satellite and the configuration maintenance period of the satellite and the target reference star are described in the following embodiments, which are not described in detail.
In one embodiment, the step of calculating the control amount of the satellite according to the semi-long axis, the orbital angular velocity, the daily semi-long axis attenuation of the other satellites, and the configuration maintenance period of the satellite and the target reference satellite includes:
known as (i)
The semi-major axis of each of said satellites is +.>
Daily semi-major axis attenuation is +.>
Then->
The orbital angular velocity of the individual satellites>
The method comprises the following steps:
first, the
The orbital angular velocity of each of the satellites is derived over time as:
assume the first
The preset distance threshold value between the satellite and the target reference star is +.>
, wherein ,
indicate->
Keeping a constrained minimum distance, +.>
First->
The maximum distance that the distances of the satellites from the target reference star remain constrained is obtainable by equation (2):
then the first
The amount of phase shift of each of said satellites relative to said target reference star>
The method comprises the following steps:
the controlled quantity can be obtained from formula (4)
The method comprises the following steps: />
Then the first
The configuration maintenance period of the satellite and the target reference star>
The method comprises the following steps:
wherein ,
is the gravitational constant->
。
Specifically, the control amount is obtained according to the formulas (1) to (5), and the configuration maintenance period of the satellite and the target reference star is obtained according to the formula (6) on the basis of the control amount. It should be noted that, each control amount, configuration holding period, etc. of the actual holding control need to consider factors such as satellite control step length, control error, space environment prediction error, etc., and perform numerical fitting according to historical precise ephemeris and orbit change conditions, so as to make corresponding adjustment.
The disclosure is further illustrated by example 1 below.
Example 1
Assuming a multi-satellite serial formation system consisting of 6 satellites, each satellite is respectively marked as S 1 、S 2 、S 3 、S 4 、S 5 、S 6 . Each satellite was operated in a solar synchronous orbit at a nominal distance of 500km altitude with an inter-satellite constraint of 70±35km, as shown in fig. 8.
1. Calculating the relative orbit attenuation rate, and reasonably selecting a target reference star maintained by a formation system
1. Relative track decay rate analysis
Respectively calculating S according to the satellite history precise ephemeris 1 、S 2 、S 3 、S 4 、S 5 、S 6 When each satellite was used as a candidate reference satellite, the relative daily orbits corresponding to the other satellites were attenuated as shown in table 1.
TABLE 1 relative orbital decay Rate (m/day) of different candidate reference satellites for other satellites
The distribution curves of the relative orbit attenuation rates of other satellites corresponding to different candidate reference satellites are shown in fig. 9, and the comprehensive orbit attenuation rate of each corresponding satellite relative to a certain satellite is shown in fig. 10. It can be seen that in S 2 When the satellite is a candidate reference satellite, the relative orbit attenuation rate of other satellites is maximally-3.82 m/day; the relative orbit attenuation distribution of other satellites is most concentrated and none exceeds 4.0m/day; and the comprehensive track attenuation rate is minimum, and the minimum comprehensive track attenuation rate is 12.64m/day. Therefore, it is preferable to select S 2 The candidate reference star is a target reference star.
2. Control performance analysis
Suppose S 1 、S 2 、S 3 、S 4 、S 5 、S 6 The minimum ignition duration of each satellite is 1.0s, 0.25s, 1.0s and 0.25s respectively; the control step sizes are 5m, 7m, 5m, 4m, 6m and 6m respectively. As can be seen, S 2 The minimum ignition time length of the star is 1S, the control step length is about 7m, the control performance is poor, and when other stars are taken as target reference, S 2 The desired range of star retention ring is difficult to achieve. Therefore, preference is given to S 2 Is a target reference star.
When different satellites are taken as candidate reference satellites, the relative orbit attenuation rate of other satellites and the control performance of each satellite are comprehensively considered, and S is selected 2 Is a target reference star.
2. Conversion inter-satellite distance maintenance constraints
According to FIG. 8, the inter-satellite distance constraint of each satellite in the formation system is 70+ -35 km, and in order to maintain the inter-satellite safe distance, the nearest distance between two adjacent satellites is not less than 10km, and the control requirement can be converted into S 2 Star is the target reference star, other S -1 ’、S 0 ’、S 1 ’、S 2 ’、S 3 ’、S 4 ' respectively correspond to S in an allergen formation 1 、S 2 、S 3 、S 4 、S 5 、S 6 As shown in fig. 11, the distance of each satellite after conversion remains constrained, and the preset distance thresholds are respectively:
（1）S -1 ’：-100～-40km；
（2）S 1 ’：40～100km；
（3）S 2 ’：110～170km；
（4）S 3 ’：180～240km；
（5）S 4 ’：250～310km。
3. selecting a formation distance maintenance strategy
To S pair 4 ' Star hold control as an example, S 4 ' Star located at target reference Star S 0 ' forward running, preset distance threshold value of 250-310 km, target reference star S 0 ' self-track decay rate is greater than S 4 ' self orbit attenuation Rate of Star, target reference Star S 0 ' and S 4 The distance between two stars is a quadratic curve with an opening to the left.
S 4 The' star control process is shown in fig. 12. In the initial state, S 4 ' Star located at target reference Star S 0 ' 250km ahead, S 4 ' the orbit of the star is lower than the target reference star S 0 ' orbit (i.e. at point A), relative to the target reference star S 0 ' forward drift, target reference S 0 ' and S 4 ' the distance between two stars is gradually far; target reference star S 0 ' and S 4 The altitude is the same when the distance between two stars reaches 310km (i.e. at the point B), due to S 4 ' the self orbit attenuation rate of the star is smaller than that of the target reference star S 0 ' self-orbit attenuation Rate, target reference Star S at this time 0 ' and S 4 ' distance between two stars is asymptotic; after a preset period of time has elapsed, S 4 The orbit of the' star will be high Yu Mubiao reference star S 0 ' orbit, relative to target reference S 0 ' backward drift, target reference S 0 ' and S 4 ' Star two stars drift again to 250km (i.e. at point C). At this time pair S 4 ' the star performs one-time orbit-down control, so that the target reference star S can be reciprocally moved 0 ' and S 4 The distance between the 'star and the two stars' is controlled in a retaining ring of 250-310 km.
4. Planning distance maintenance control
Still in S 4 ' Star hold control task for example, S 4 ' Star relative target reference Star S 0 The relative track attenuation rate is 2.63m/day, the distance range is 250-310 km, S can be calculated 4 ' Star and target reference Star S 0 The' configuration maintains a period. Consider S 4 The minimum ignition time of the star is 0.25s, the control step length is 6m, and in combination with factors such as the satellite calibration coefficient, the control error, the current space environment condition, the orbit forecast error and the like, the actual control quantity is about-60 m each time through the modeling to ensure that the double-star distance keeping range is not beyond the ring, and the configuration keeping period is about 45 days.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any adaptations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
Claims (10)
1. The inter-satellite distance maintenance control method for the unstable multi-satellite serial formation system is characterized by comprising the following steps of:
each satellite in the formation system is respectively used as a candidate reference satellite, and a target reference satellite in the formation system is determined according to the relative orbit attenuation rate of other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite;
converting the distance constraint between satellites in the formation system into the distance maintenance constraint between other satellites in the formation system and the target reference satellite;
selecting a formation distance maintenance control strategy according to the distance maintenance constraint, the relative position relation and the self-orbit attenuation rate of other satellites in the formation system and the target reference satellite;
and planning a distance maintenance control based on the maintenance control strategy.
2. The method for maintaining control between satellites in an unstable multi-satellite serial formation system according to claim 1, wherein the step of determining the target reference satellite in the formation system according to the relative orbit attenuation rate of the other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite by using each satellite in the formation system as the candidate reference satellite comprises:
And calculating the relative orbit attenuation rates of other satellites in the formation system and the candidate reference star.
3. The method for maintaining control between satellites in an unstable multi-satellite serial formation system according to claim 2, wherein the step of determining the target reference satellite in the formation system according to the relative orbit attenuation rate of the other satellites corresponding to each candidate reference satellite in the formation system and the candidate reference satellite by using each satellite in the formation system as the candidate reference satellite comprises:
and summing absolute values of the relative orbit attenuation rates of the other satellites corresponding to each candidate reference satellite to obtain the comprehensive orbit attenuation rate of the candidate reference satellite.
4. The method for maintaining control over the inter-satellite distance of the unstable multi-satellite serial formation system according to claim 3, wherein the step of summing absolute values of the relative orbit attenuation rates of the other satellites corresponding to each candidate reference satellite to obtain the integrated orbit attenuation rate of the candidate reference satellite comprises:
and drawing relative orbit attenuation rate distribution curves of other satellites corresponding to different candidate reference satellites according to the relative orbit attenuation rates of each candidate reference satellite and other satellites and each candidate reference satellite, and selecting the candidate reference satellite with the concentrated relative orbit attenuation rate distribution and the minimum comprehensive orbit attenuation rate as the target reference satellite by combining the comprehensive orbit attenuation rate of each candidate reference satellite.
5. The method for controlling inter-satellite distance maintenance of an unstable multi-satellite serial formation system according to claim 1, wherein the step of selecting the formation distance maintenance control strategy according to distance maintenance constraints, relative positional relationships and self-orbit attenuation rate of other satellites in the formation system, comprises:
the other satellites are positioned in front of the target reference star and the self-orbit attenuation rate of the target reference star is smaller than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the right, when the satellites are positioned at the maximum distance of the distance retaining constraint in front of the target reference star and the orbit of the satellites is higher than that of the target reference star, the satellites drift backwards relative to the target reference star, after a preset period of time, the satellites drift forwards relative to the target reference star and reach the maximum distance of the distance retaining constraint in front of the target reference star again, and when the orbit of the satellites is lower than that of the target reference star, the orbit of the satellites is controlled to rise; the preset distance threshold is a maximum distance from a minimum distance of the distance keeping constraint to the distance keeping constraint.
6. The method for controlling inter-satellite distance maintenance of an unstable multi-satellite serial formation system according to claim 5, wherein the step of selecting the formation distance maintenance control strategy according to distance maintenance constraints, relative positional relationships and self-orbit attenuation rate of other satellites in the formation system, comprises:
the other satellites are in front of the target reference star, the self-orbit attenuation rate of the target reference star is smaller than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the left, when the satellites are located at the minimum distance of the distance retaining constraint in front of the target reference star and the orbit of the satellites is lower than that of the target reference star, the satellites drift forward relative to the target reference star, after the preset time period, the satellites drift backward relative to the target reference star and reach the minimum distance of the distance retaining constraint in front of the target reference star again, and when the orbit of the satellites is lower than that of the target reference star, the orbit of the satellites is controlled to drop.
7. The method for controlling inter-satellite distance maintenance of an unstable multi-satellite serial formation system according to claim 6, wherein the step of selecting the formation distance maintenance control strategy according to distance maintenance constraints, relative positional relationships and self-orbit attenuation rates of other satellites in the formation system, comprises:
the other satellites are positioned in a preset distance threshold behind the target reference star, the self-orbit attenuation rate of the target reference star is smaller than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the right, when the satellites are positioned at the minimum distance of the distance retaining constraint behind the target reference star and the orbit of the satellites is lower than that of the target reference star, the satellites drift backwards relative to the target reference star, after the preset time period, the satellites drift forwards relative to the target reference star, and the orbit of the satellites reaches the minimum distance of the distance retaining constraint behind the target reference star again, and when the orbit of the satellites is lower than that of the target reference star, the orbit of the satellites is controlled to rise.
8. The method for controlling inter-satellite distance maintenance of an unstable multi-satellite serial formation system according to claim 7, wherein the step of selecting the formation distance maintenance control strategy according to distance maintenance constraints, relative positional relationships and self-orbit attenuation rates of other satellites in the formation system, comprises:
the other satellites are within a preset distance threshold behind the target reference star, the self-orbit attenuation rate of the target reference star is larger than that of the satellites, the distance retaining ring of the satellites and the target reference star is a quadratic curve with an opening to the left, when the satellite is positioned at the maximum distance of the distance retaining constraint behind the target reference star and the orbit of the satellite is lower than that of the target reference star, the satellites drift forwards relative to the target reference star, after the preset time period, the satellites drift backwards relative to the target reference star and reach the maximum distance of the distance retaining constraint behind the target reference star again, and when the orbit of the satellite is higher than that of the target reference star, the orbit of the satellites is controlled to drop.
9. The method for maintaining control of inter-star distances in an unstable multi-star serial formation system according to claim 8, wherein the step of planning the distance maintenance control based on the maintenance control strategy comprises:
and calculating the control quantity of the satellite and the configuration maintenance period of the satellite and the target reference star according to the semi-long axis, the orbital angular velocity and the daily semi-long axis attenuation of other satellites.
10. The method according to claim 9, wherein the step of calculating the control amount of the satellite and the configuration holding period of the satellite and the target reference satellite according to the semi-major axis, the orbital angular velocity, and the daily semi-major axis attenuation of the other satellites comprises:
known as (i)
The semi-major axis of each of said satellites is +.>
Daily semi-major axis attenuation is +.>
Then->
The orbital angular velocity of the individual satellites>
The method comprises the following steps: />
First, the
The orbital angular velocity of each of the satellites is derived over time as:
assume the first
The preset distance threshold value between the satellite and the target reference star is +.>
, wherein ,/>
Indicate->
Keeping a constrained minimum distance, +. >
First->
The maximum distance that the distances of the satellites from the target reference star remain constrained is obtainable by equation (2):
then the first
The amount of phase shift of each of said satellites relative to said target reference star>
The method comprises the following steps:
the controlled quantity can be obtained from formula (4)
The method comprises the following steps:
then the first
The configuration maintenance period of the satellite and the target reference star>
The method comprises the following steps:
wherein ,
is the gravitational constant->
。/>
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310454702.6A CN116166049B (en) | 2023-04-25 | 2023-04-25 | Inter-star distance maintaining control method for unstable multi-star serial formation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310454702.6A CN116166049B (en) | 2023-04-25 | 2023-04-25 | Inter-star distance maintaining control method for unstable multi-star serial formation system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116166049A true CN116166049A (en) | 2023-05-26 |
| CN116166049B CN116166049B (en) | 2023-07-07 |
Family
ID=86418649
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310454702.6A Active CN116166049B (en) | 2023-04-25 | 2023-04-25 | Inter-star distance maintaining control method for unstable multi-star serial formation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116166049B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117311394A (en) * | 2023-11-28 | 2023-12-29 | 中国西安卫星测控中心 | Inter-satellite phase overrun control method in non-strict multi-satellite serial formation system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6845303B1 (en) * | 2002-11-05 | 2005-01-18 | Lockheed Martin Corporation | Micro-satellite and satellite formation for inverse and distributed proximity operations |
| CN109062243A (en) * | 2018-10-31 | 2018-12-21 | 长光卫星技术有限公司 | A kind of autonomous collision avoidance method of spacecraft energetic optimum under multiple constraint |
| CN111422379A (en) * | 2020-03-20 | 2020-07-17 | 上海航天控制技术研究所 | Formation satellite cooperative orbit control method |
| US11091280B1 (en) * | 2018-06-05 | 2021-08-17 | United States Of America As Represented By The Administrator Of Nasa | Modelling and analyzing inter-satellite relative motion |
| CN114254262A (en) * | 2021-11-22 | 2022-03-29 | 浙江大学 | Method and device for maintaining autonomous configuration of heterogeneous quality ratio satellite constellation and electronic equipment |
| CN115309174A (en) * | 2022-07-21 | 2022-11-08 | 银河航天(北京)网络技术有限公司 | Method and electronic equipment for combined control of near-earth orbit satellite formation |
-
2023
- 2023-04-25 CN CN202310454702.6A patent/CN116166049B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6845303B1 (en) * | 2002-11-05 | 2005-01-18 | Lockheed Martin Corporation | Micro-satellite and satellite formation for inverse and distributed proximity operations |
| US11091280B1 (en) * | 2018-06-05 | 2021-08-17 | United States Of America As Represented By The Administrator Of Nasa | Modelling and analyzing inter-satellite relative motion |
| CN109062243A (en) * | 2018-10-31 | 2018-12-21 | 长光卫星技术有限公司 | A kind of autonomous collision avoidance method of spacecraft energetic optimum under multiple constraint |
| CN111422379A (en) * | 2020-03-20 | 2020-07-17 | 上海航天控制技术研究所 | Formation satellite cooperative orbit control method |
| CN114254262A (en) * | 2021-11-22 | 2022-03-29 | 浙江大学 | Method and device for maintaining autonomous configuration of heterogeneous quality ratio satellite constellation and electronic equipment |
| CN115309174A (en) * | 2022-07-21 | 2022-11-08 | 银河航天(北京)网络技术有限公司 | Method and electronic equipment for combined control of near-earth orbit satellite formation |
Non-Patent Citations (2)
| Title |
|---|
| 何益康;彭仁军;杜耀珂;: "基于大气阻力的卫星编队沿航迹方向的变结构控制", 上海航天, no. 04 * |
| 林来兴;车汝才;: "卫星编队飞行精确动力学模型与三维定位系统", 宇航学报, no. 03 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117311394A (en) * | 2023-11-28 | 2023-12-29 | 中国西安卫星测控中心 | Inter-satellite phase overrun control method in non-strict multi-satellite serial formation system |
| CN117311394B (en) * | 2023-11-28 | 2024-03-12 | 中国西安卫星测控中心 | Inter-satellite phase overrun control method in non-strict multi-satellite serial formation system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116166049B (en) | 2023-07-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109214564B (en) | Autonomous task planning method for ground remote sensing satellite with multiple planning modes | |
| CN116166049B (en) | Inter-star distance maintaining control method for unstable multi-star serial formation system | |
| CN109062243B (en) | Autonomous collision avoidance method for optimizing spacecraft energy under multiple constraints | |
| CN110986974B (en) | Complex dynamics environment-oriented multi-spacecraft task intelligent planning and control method | |
| CN103632053A (en) | Combined scheduling method of satellite-ground measurement and control resources of low-mid-orbit satellite constellation based on orbit determination constraint satisfaction | |
| US10752384B2 (en) | Orbit control device and satellite | |
| US8954207B1 (en) | Method of enhancing on-board state estimation using communication signals | |
| WO2022111230A1 (en) | Distributed centerless space-based time reference establishing and maintaining system | |
| CN112632756A (en) | Satellite earth shadow autonomous forecasting method and system based on sun sensor | |
| CN115081884B (en) | Distributed on-board online many-to-many task planning method | |
| CN115392813B (en) | On-orbit event arrangement and resource allocation planning method based on hierarchical optimization | |
| WO2024045778A1 (en) | Space debris collision avoidance method and apparatus taking orbit altitude adjustment task into consideration | |
| CN112629543A (en) | Orbit planning method for large elliptical orbit and small-inclination-angle circular orbit | |
| CN106094529A (en) | Thruster Auto-calibration method in-orbit under formation task multiple-pulse control condition | |
| CN106815400B (en) | Automatic design method for rail adjustment scheme | |
| Li et al. | Orbit determination and prediction for Beidou GEO satellites at the time of the spring/autumn equinox | |
| CN116424576B (en) | Constellation configuration maintaining method and system based on reference configuration dynamic determination strategy | |
| Swift | NSWC's GPS orbit/clock determination system | |
| CN116862167A (en) | Low-orbit remote sensing satellite constellation emergency task planning method based on multi-knapsack model | |
| CN110053788A (en) | Constellation long-term retention control frequency estimation method considering complex perturbation | |
| CN113093246A (en) | Ground multi-target point imaging rapid judgment and task parameter calculation method | |
| Wu et al. | Problem A of the 9th China trajectory optimization competition: Results found at Tsinghua University | |
| CN115186178B (en) | Agile remote sensing satellite task solution space searching method based on step length self-adaption | |
| Ali et al. | Modeling of CubeSat orientation scenario and solar cells for internet of space provision | |
| Golikov | THEONA—a numerical-analytical theory of motion of artificial satellites of celestial bodies |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |