CN114493273A - Selection method and device of aerospace measurement and control arc section, electronic equipment and storage medium - Google Patents

Selection method and device of aerospace measurement and control arc section, electronic equipment and storage medium Download PDF

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CN114493273A
CN114493273A CN202210098636.9A CN202210098636A CN114493273A CN 114493273 A CN114493273 A CN 114493273A CN 202210098636 A CN202210098636 A CN 202210098636A CN 114493273 A CN114493273 A CN 114493273A
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measurement
control
control arc
arc sections
arc
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李斌
梁爽
刘成军
姜萍
陈俊刚
陈海
王炎娟
李晓明
赵兴乾
周心婷
马鹏德
郭祥艳
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Beijing Aerospace Control Center
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Abstract

The invention discloses a selection method and a device of an aerospace measurement and control arc segment, electronic equipment and a storage medium, wherein the method comprises the following steps: acquiring time data of all measurement and control arc sections corresponding to the spacecraft in a preset time period, wherein the time data of each measurement and control arc section comprises the following steps: an arc start time and an arc end time; determining the interrelation among the measurement and control arc sections according to the time data of the measurement and control arc sections, wherein the type of the interrelation comprises: covering, the interrelation between each measurement and control arc section includes: the relation between every two measurement and control arc sections and/or the relation between multiple measurement and control arc sections; in response to the fact that the mutual relation among the measurement and control arc sections is determined to be covered, the covered measurement and control arc sections are removed from all the measurement and control arc sections; and carrying out measurement and control operation on the spacecraft according to the measurement and control arc sections after the elimination treatment. By the method and the device, the resource utilization rate can be improved, and the economic cost of space activities is reduced.

Description

Selection method and device of aerospace measurement and control arc section, electronic equipment and storage medium
Technical Field
The invention relates to the technical field of aerospace measurement and control, in particular to a method and a device for selecting an aerospace measurement and control arc section, electronic equipment and a storage medium.
Background
In the process of executing a space mission, a spacecraft can face various uncertainties in the in-orbit flight and space test processes, in order to deal with uncertainties caused by different internal and external factors, state data of the in-orbit operation of the spacecraft can be continuously acquired, or in order to download scientific test data stored by the spacecraft, ground measurement and control equipment is usually arranged to participate in tracking as much as possible, and a measurement and control arc section is used to carry out measurement and control and data receiving work to the maximum extent.
Taking a tentative space mission as an example, as the name implies, the objective is to verify a new technology, and a system on a spacecraft, such as energy, thermal control, propulsion, environmental control, guidance, navigation, and the like, will largely adopt new products of the new technology, even the whole spacecraft itself is a new platform and new configuration, under such a situation, the operation state of the spacecraft is inevitably monitored for a long time as possible, the operation safety of the spacecraft is ensured, and various performances such as reliability and maturity of new products of the new technology are verified, so that multiple arc sections are inevitably arranged for continuous tracking.
Although some space missions adopt mature equipment, space mission activities are frequently carried out, such as earth observation of a spacecraft, earth observation in a large range is carried out, a large amount of observation data is generated, the data is limited by the storage capacity of the spacecraft and must be downloaded in time, and therefore multi-arc-section continuous tracking is required to be arranged, and a storage space is reserved for subsequent space activities. Some spacecrafts carry scientific test loads, the space scientific test loads are usually driven by a large number of complex instructions, remote control instructions need to be sent through ground measurement and control equipment for operation, and measurement and control support in a multi-arc section and long time is indispensable in order to ensure stable and continuous test process.
For a long time, when the aerospace task is executed, the task is always completed safely and satisfactorily as a primary target, and the use efficiency of measurement and control resources is not concerned. In order to achieve the task goal, the measurement and control system always calls all measurement and control resources to fully support, and in the time period of crossing the spacecraft, as long as the measurement and control equipment is visible, the measurement and control system is usually arranged to participate in tracking so as to ensure the total tracking time. Under the circumstance, a phenomenon that a plurality of measurement and control devices can perform tracking at the same time often occurs, and in fact, when one device performs tracking, other devices are in a standby state and do not perform measurement and control on the spacecraft.
That is to say, the existing method for invoking all measurement and control resources to perform measurement and control support on a transit spacecraft has the following disadvantages:
(1) too many measurement and control resources are occupied, and the use efficiency of the measurement and control resources is low;
(2) the standby loss of the equipment causes resource waste;
(3) the equipment and personnel operation cost is high, and the economic benefit is reduced.
Disclosure of Invention
In view of the above, the present invention provides a method and an apparatus for selecting an aerospace measurement and control arc segment, an electronic device, and a storage medium, so as to solve at least one of the above-mentioned problems.
According to a first aspect of the invention, a method for selecting an aerospace measurement and control arc segment is provided, and the method comprises the following steps:
acquiring time data of all measurement and control arc sections corresponding to the spacecraft in a preset time period, wherein the time data of each measurement and control arc section comprises the following steps: an arc start time and an arc end time;
determining the interrelation among the measurement and control arc sections according to the time data of the measurement and control arc sections, wherein the type of the interrelation comprises the following steps: covering, the interrelation between each measurement and control arc section includes: the relation between every two measurement and control arc sections and/or the relation between multiple measurement and control arc sections;
in response to the fact that the mutual relation among the measurement and control arc sections is determined to be covered, the covered measurement and control arc sections are removed from all the measurement and control arc sections;
and carrying out measurement and control operation on the spacecraft according to the measurement and control arc sections after the rejection processing.
According to a second aspect of the present invention, there is provided a selection device for an aerospace measurement and control arc segment, the device comprising:
the arc section data acquisition unit is used for acquiring time data of all measurement and control arc sections corresponding to the spacecraft in a preset time period, and the time data of each measurement and control arc section comprises: an arc start time and an arc end time;
the arc section relation determining unit is used for determining the interrelation among the measurement and control arc sections according to the time data of the measurement and control arc sections, and the type of the interrelation comprises the following steps: covering, the interrelation between each measurement and control arc section includes: the relation between every two measurement and control arc sections and/or the relation between multiple measurement and control arc sections;
the rejecting unit is used for responding to the mutual relation among the measurement and control arc sections to determine that the measurement and control arc sections are covered, and rejecting the covered measurement and control arc sections from all the measurement and control arc sections;
and the measurement and control unit is used for carrying out measurement and control operation on the spacecraft according to the measurement and control arc sections after the elimination processing.
According to a third aspect of the present invention, there is provided an electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing the steps of the method when executing the program.
According to a fourth aspect of the invention, a computer-readable storage medium is provided, on which a computer program is stored which, when being executed by a processor, carries out the steps of the above-mentioned method.
According to the technical scheme, the overlapping relation between the measurement and control arc sections is determined according to the acquired time data of the measurement and control arc sections, when the overlapping relation between the measurement and control arc sections is determined to be covered, the covered measurement and control arc sections are removed from all the measurement and control arc sections, and then the measurement and control arc sections are removed according to the measurement and control arc sections after the removal processing, so that the covered measurement and control arc sections can be removed on the premise that the total measurement and control time length is not changed, the number of devices participating in measurement and control can be reduced, the resource utilization rate is improved, and the economic cost of space activities is reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a flow chart of a space measurement and control arc segment selection method according to an embodiment of the invention;
FIG. 2 is a preferred flow diagram of a measurement and control arc segment according to an embodiment of the invention;
fig. 3(1) -fig. 3(3) are schematic diagrams of the overlapping state of any two measurement and control arc segments according to the embodiment of the invention;
FIG. 4 is a flowchart of the arc redundancy calculation for a two arc lap joint condition according to an embodiment of the present invention;
fig. 5(1) -fig. 5(4) are schematic diagrams of the overlapping states of any three measurement and control arc segments according to the embodiment of the invention;
FIG. 6 is a flow chart of arc redundancy calculation under a three-arc lap joint condition according to an embodiment of the present invention;
FIG. 7 is a flow diagram of redundant arc segment culling according to an embodiment of the invention;
FIG. 8 is a block diagram of a space flight measurement and control arc segment selection device according to an embodiment of the present invention;
fig. 9 is a schematic block diagram of a system configuration of an electronic apparatus 600 according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Applicants make a name explanation for the following terms:
measuring and controlling the arc section: the time range of the spacecraft can be observed by the ground measurement and control equipment when the spacecraft flies in orbit. In the range of the measurement and control arc segment, an antenna terminal arranged on the spacecraft points to ground measurement and control equipment, and the ground can receive telemetering data transmitted by the spacecraft; after the double-catching is completed, the ground can send a remote control instruction and an upper injection flight parameter to the spacecraft so as to measure and control the spacecraft.
Covering the arc section: and one of the two measurement and control arc sections is completely positioned in the time range of the other arc section and is completely covered by the other arc section.
And (3) overlapping arc sections: the time ranges of the measurement and control arc sections are partially overlapped.
At present, all measurement and control resources are called by a transit spacecraft to carry out measurement and control support. In fact, as the number of space missions increases year by year, the number of on-orbit spacecraft also increases rapidly, and the demand of measurement and control tasks is in a situation of accelerating increase, which is limited by the territory and the layout of measurement and control equipment.
Based on this, the embodiment of the invention provides a space flight measurement and control arc section selection scheme, which can reduce the number of devices participating in measurement and control, improve the resource utilization rate, reduce the economic cost of space flight activities and improve the economic benefit on the premise of ensuring that the total measurement and control time is not changed. Embodiments of the present invention are described in detail below with reference to the accompanying drawings.
Fig. 1 is a flowchart of a space flight measurement and control arc segment selection method according to an embodiment of the present invention, and as shown in fig. 1, the method includes:
step 101, acquiring time data of all measurement and control arc sections corresponding to the spacecraft in a preset time period, wherein the time data of each measurement and control arc section comprises: an arc start time and an arc end time.
Step 102, determining the interrelation (namely, the lap joint relation) between the measurement and control arc sections according to the time data of the measurement and control arc sections, wherein the type of the interrelation comprises: covering, the interrelation between each measurement and control arc section includes: the relation between each two measurement and control arc sections and/or the relation between multiple measurement and control arc sections.
And 103, in response to the fact that the mutual relation between the measurement and control arc sections is determined to be covered, removing the covered measurement and control arc sections from all the measurement and control arc sections.
In actual operation, when a measurement and control arc segment of measurement and control equipment is covered by other measurement and control arc segments, in the prior art, the measurement and control equipment is in a standby state, and measurement and control operation is not performed on a spacecraft. In the embodiment of the invention, the covered measurement and control arc sections are removed, and the corresponding measurement and control equipment does not need to be in a standby state, so that the number of the measurement and control equipment is reduced, and the resource utilization rate can be improved compared with the prior art.
And 104, carrying out measurement and control operation on the spacecraft according to the measurement and control arc sections after the elimination processing.
The overlapping relation between the measurement and control arc sections is determined according to the acquired time data of the measurement and control arc sections, when the overlapping relation between the measurement and control arc sections is determined to be covered, the covered measurement and control arc sections are removed from all the measurement and control arc sections, and then the measurement and control arc sections are removed according to the measurement and control arc sections after the removal processing, so that the measurement and control operation of the spacecraft is performed, the covered measurement and control arc sections can be removed on the premise that the total measurement and control time length is not changed, the number of devices participating in measurement and control can be reduced, the resource utilization rate is improved, and the economic cost of space activities is reduced.
For step 102, determining the correlation between the measurement and control arc sections according to the time data between every two measurement and control arc sections; and then, determining the interrelationship between the measurement and control arc sections according to the interrelationship between every two measurement and control arc sections.
Specifically, according to the mutual relationship between every two measurement and control arc sections, the covered measurement and control arc sections are removed (or not considered) firstly; and then, determining the interrelation among the measurement and control arc sections according to the measurement and control arc sections after the elimination treatment, wherein the covered measurement and control arc sections are mainly determined according to the time data of any three measurement and control arc sections.
For better understanding of the present invention, the following describes the embodiment of the present invention in detail with reference to the preferred flow of the measurement and control arc segment shown in fig. 2.
As shown in fig. 2, the preferable process of the measurement and control arc segment mainly comprises the following steps 1-3:
step 1, calculating the redundancy of the arc sections under the lapping state of the two arc sections;
step 2, calculating the redundancy of the arc sections in the multi-arc-section lap joint state;
and 3, removing redundant arc sections.
Through the steps 1-3, the optimal flow of the measurement and control arc section can be completed. The respective steps are described in detail below.
Redundancy calculation of arc sections under two arc section lapping state
In actual operation, the interrelation between the measurement and control arc sections is considered, and the simplest condition is the condition of two measurement and control arc sections. Any two measurement and control arc sections, the lapping state between the two measurement and control arc sections has 3 states, see fig. 3(1) -fig. 3 (3):
as shown in fig. 3(1), there is a blank between the arc segments 1 and 2, and the two are not overlapped with each other.
As shown in fig. 3(2), the arc segments 1 and 2 have overlapping time intervals, and are overlapped front and back.
As shown in fig. 3(3), the periods of the arc segments 1 and 2 overlap, and the period of the arc segment 1 is longer, the period of the arc segment 2 is shorter, and the arc segment 1 completely covers the arc segment 2, i.e. the above-mentioned covering relationship.
Recording the full set of the measurement and control arc segment as R ═ R1,R2,…,Rj,…,Rn) J is 1,2, …, n, wherein Rj＝(Sj,Ej,dj) Information representing an arc segment, Sj、EjRespectively showing the start and end time of the jth arc segment and the closed interval [ Sj,Ej]Representing the time range of the j-th arc segment, djRepresenting the redundancy of the jth arc segment, and the initial value is 0. Measuring and controlling arc segment complete set R with arc segment starting time SjAre arranged in ascending order of key values.
In order to be able to evaluate the two-arc overlap state quantitatively, in the limit i<j (i.e. S)i≤Sj) In this case, a function f (R) of the state of overlap of two arc segments is definedi,Rj) Denotes two front and rear arc segments Ri、RjIn an overlapping state therebetween. At the same time, let RjRedundancy d ofj＝f(Ri,Rj) Then the arc segment R can be obtained by the calculation of the lapping state functionjRedundancy of (2). The method comprises the following specific steps:
Figure BDA0003491607420000061
when f (R)i,Rj) 0, i.e. djWhen equal to 0, denotes an arc segment Ri、RjNo lap joint;
when f (R)i,Rj)1, i.e. djWhen 1, represents an arc segment Ri、RjSimple overlapping;
when f (R)i,Rj) 2, i.e. djWhen 2, represents an arc segment RjQuilt arc section RiComplete coverage, arc segment RjAre redundant arc segments. In particular, this will be the caseReferred to as individual covering.
FIG. 4 is a flowchart of the arc redundancy calculation under the two-arc lapping condition, as shown in FIG. 4, for each arc RjJ 2,3, …, n, setting loop variable i 1,2, …, j-1, and loop calculating arc segment Ri、RjFunction of overlap condition f (R)i,Rj) Of (d) and also the arc segment RjThe redundancy of (a), the meaning of each identifier is as described above.
The specific calculation process includes the following branches:
(1) if arc segment RiThe redundancy value of (1) is 2, and i ≠ j-1, then set i ═ i +1, skip the arc segment, select the next arc segment to participate in the calculation, wherein i ═ 1, …, j-1, R1For the first measuring-controlling arc segment, i.e. R1Is the earliest;
(2) if arc segment RjIf the redundancy value of (1) is not 2, and i ≠ j-1, then i ═ i +1 is set, and the next arc segment is selected to participate in the calculation, j ═ 2, …, n, RnFor the last measurement-control arc, i.e. RnIs the latest;
(3) if arc segment RjIf the redundancy value of (2) is greater than j +1, then calculating the redundancy of the next arc segment;
(4) if R isjAnd if the arc segment is the last arc segment of the measurement and control arc segment set R, ending the calculation.
Redundancy calculation of arc sections under (II) multi-arc section lapping state
In actual operation, the lapping state of the multiple arc sections can be simplified into the lapping state of three arc sections for processing, so that the arc section redundancy calculation under the lapping state of the multiple arc sections can be simplified into the arc section redundancy calculation under the lapping state of the three arc sections.
Before examining the overlap relationship between the three arc segments, it is necessary to exclude the case of individual coverage (fig. 3(3)), i.e. the redundancy d in (a)jThe arc segment with a value of 2 does not participate in the calculation.
Referring to fig. 5(1) -fig. 5(4), the lap joint state of the three is totally 4 states:
as shown in fig. 5(1), the arc segment 1, the arc segment 2, and the arc segment 3 are sequentially arranged, wherein the arc segment 1 and the arc segment 2 are simply overlapped, and the arc segment 3 is not overlapped with other two arc segments;
as shown in fig. 5(2), the arc segment 1, the arc segment 2 and the arc segment 3 are sequentially arranged, wherein the arc segment 2 and the arc segment 3 are simply overlapped, and the arc segment 1 is not overlapped with other two arc segments;
as shown in fig. 5(3), the arc segments 1,2 and 3 are sequentially arranged, two adjacent arc segments are simply overlapped, two non-adjacent arc segments are not overlapped, that is, the arc segments 1 and 2 are simply overlapped, the arc segments 2 and 3 are simply overlapped, but the arc segments 1 and 3 are not overlapped;
as shown in fig. 5(4), the arc segments 1,2 and 3 are arranged in sequence, and not only two adjacent arc segments are simply overlapped, but also two non-adjacent arc segments are simply overlapped to form a staggered overlap joint. In this case, arc segment 2 is completely covered by the union of arc segments 1, 3.
In order to be able to evaluate the three-arc overlap state quantitatively, in the limit i<j<k (i.e. S)i≤Sj≤Sk) In this case, a three arc segment overlap state function h (R) is definedi,Rj,Rk) Denotes the front and rear three arc segments Ri、Rj、RkIn the state of overlap between dj＝h(Ri,Rj,Rk) Then the arc segment R can be obtained by the calculation of the lapping state functionjThe redundancy of (2) is as follows:
h(Ri,Rj,Rk)＝f(Ri,Rk)×(f(Ri,Rj)+f(Rj,Rk))
in fact, function h (R)i,Rj,Rk) There are only two value states:
Figure BDA0003491607420000071
when h (R)i,Rj,Rk) 0, i.e. djWhen equal to 0, represents an arc segment RjNot a redundant arc segment;
when h (R)i,Rj,Rk) 2, i.e. djWhen 2, represents an arc segment Ri、RkOverlap joint, the union of which can be used to connect the arc sections RjComplete coverage, arc segment RjAre redundant arc segments. In particular, this case may be referred to as joint coverage.
Fig. 6 is a flowchart of calculating the redundancy of the arc segments in the three-arc-segment overlapping state according to the embodiment of the present invention, and as shown in fig. 6, according to the method for calculating the redundancy of the arc segments in the three-arc-segment overlapping state, for each arc segment RjJ 2,3, …, n-1, setting the loop variable i 1,2, …, j-1, and the loop variable k j +1, …, n, loop calculating arc segment Ri、Rj、RkFunction of overlap state h (R)i,Rj,Rk) Of (d) and also the arc segment RjThe redundancy of (a), the meaning of each identifier is as described above.
The specific calculation process includes the following branches:
(1) if arc segment RiThe redundancy value of (1) is 2, and i ≠ j-1, then set i ═ i +1, skip the arc segment, select the next arc segment to participate in the calculation, wherein i ═ 1, …, j-1, R1For the first measuring-controlling arc segment, i.e. R1Is the earliest;
(2) if arc segment RkThe redundancy value of (2) and k ≠ n, then k ═ k +1 is set, the arc segment is skipped, the next arc segment is selected to participate in the calculation, k ═ j +1, …, n, RnFor the last measurement-control arc segment, i.e. RnIs the latest;
(3) if arc segment RjIf the redundancy value is not 2 and i is not equal to j-1, respectively setting i to i +1, and selecting the next arc segment to participate in calculation;
(4) if arc segment RjIf the redundancy value is not 2 and k is not equal to n, respectively setting k as k +1, and selecting the next arc segment to participate in calculation;
(5) if arc segment RjIf the redundancy value of (2) is greater than j +1, then calculating the redundancy of the next arc segment;
(6) if R isjThe last arc segment of the measurement and control arc segment set R isAnd finishing the calculation.
(III) redundant arc segment culling
Fig. 7 is a flow chart of redundant arc segment elimination, as shown in fig. 7, the elimination of redundant arc segments is performed in three stages:
(1) according to the arc redundancy calculation method under the lapping state of the two arcs, the arc redundancy is calculated, and the arc which is covered independently is marked.
Specifically, i is defined<j, for any two arc sections Ri、RjCalculating the arc segment overlap state function f (R)i,Rj) Of the arc segment R is obtained simultaneouslyjRedundancy d ofjIf d isjA value of 2 indicates an arc segment RjQuilt arc section RiSingle covering, arc segment RjAre redundant arc segments. In the calculation process, if the redundancy value of a certain arc segment is 2, the arc segment is skipped over, and the next arc segment is selected to participate in the calculation.
(2) According to the arc redundancy calculation method under the three-arc lap joint state, the arc redundancy is calculated, and the arc covered jointly is marked.
Definition of i<j<k, for any three arc segments Ri、Rj、RkCalculating the function h (R) of the overlapping state of the arc segmentsi,Rj,Rk) Of the arc segment R is obtained simultaneouslyjRedundancy d ofjIf d isjA value of 2, representing the arc segment RjQuilt arc section Ri、RkCombined coverage, arc segment RjAre redundant arc segments. Similarly, in the calculation process, if the redundancy value of a certain arc segment is 2, the arc segment is skipped, and the next arc segment is selected to participate in the calculation.
(3) Circularly traversing the arc segment complete set R, and aiming at each arc segment RjAnd j is 1,2, …, n, and the redundancy of the arc segment is judged. If arc segment RjIf the redundancy value of (2) is greater, the arc segment R is indicatedjIf the arc segment is a redundant arc segment, the arc segment is removed, and the next arc segment is continuously judged; if arc segment RjIf the redundancy value is not 2, j is set to j +1, and the next arc segment is continuously judged.
According to the optimization method of the measurement and control arc sections, firstly, according to an arc section redundancy calculation method under the lapping state of two arc sections, a lapping state value between the two arc sections is calculated, and meanwhile, the redundancy of each arc section except the first arc section is obtained; then, according to an arc segment redundancy calculation method under a multi-arc segment overlapping state, the overlapping state value among three arc segments is calculated, and meanwhile, the redundancy of each arc segment except for the head arc segment and the tail arc segment is obtained; and finally, according to the redundancy of the arc sections, eliminating the arc sections which are covered individually and the arc sections which are covered jointly.
Thus, the embodiment of the invention has the following effective effects:
(1) according to the optimization method of the measurement and control arc section, the measurement and control redundant arc section is removed, and invalid occupation of measurement and control resources is reduced;
(2) the optimization method of the measurement and control arc section of the embodiment of the invention reduces the use time of the measurement and control equipment and improves the utilization rate of measurement and control resources under the condition of ensuring that the total measurement and control time is not reduced;
(3) the optimization method of the measurement and control arc section reduces equipment loss and working time of personnel, reduces the use cost of measurement and control resources, and improves economic benefits.
Based on similar inventive concepts, the embodiment of the invention also provides a selection device of the aerospace measurement and control arc segment, and the device is preferably used for realizing the process of the selection method of the aerospace measurement and control arc segment.
Fig. 8 is a structural block diagram of the aerospace measurement and control arc segment selection device, and as shown in fig. 8, the device includes: the arc section data acquisition unit 1, the arc section relation confirm unit 2, reject unit 3 and observe and control unit 4, wherein:
the arc segment data acquisition unit 1 is used for acquiring time data of all measurement and control arc segments corresponding to the spacecraft in a preset time period, and the time data of each measurement and control arc segment comprises: an arc start time and an arc end time;
the arc segment relation determining unit 2 is configured to determine, according to time data of each measurement and control arc segment, a correlation between the measurement and control arc segments, where the type of the correlation includes: covering, the interrelation between each measurement and control arc section includes: the relation between every two measurement and control arc sections and/or the relation between multiple measurement and control arc sections;
the rejecting unit 3 is used for rejecting the covered measurement and control arc sections from all the measurement and control arc sections in response to the fact that the mutual relation among the measurement and control arc sections is determined to be covering;
and the measurement and control unit 4 is used for carrying out measurement and control operation on the spacecraft according to the measurement and control arc sections after the elimination processing.
The interrelation between each measurement and control arc section is determined through the arc section relation determining unit 2 according to the time data of each measurement and control arc section acquired by the arc section data acquiring unit 1, when the interrelation between the measurement and control arc sections is determined to be covered, the covered measurement and control arc sections are removed by the removing unit 3 in all the measurement and control arc sections, and then the measurement and control unit 4 is right according to the measurement and control arc sections after the removal processing of the spacecraft for measurement and control operation, so that the covered measurement and control arc sections can be reduced on the premise of ensuring the total measurement and control time length to be unchanged, the number of devices participating in measurement and control can be reduced, the resource utilization rate is improved, and the economic cost of space activities is reduced.
Wherein, the arc segment relation determining unit 2 includes: pairwise relationship determination module and multi-arc segment relationship determination module, wherein:
the pairwise relation determining module is used for determining the mutual relation between the measurement and control arc sections according to the time data between each two measurement and control arc sections;
and the multi-arc-section relation determining module is used for determining the mutual relation among the measurement and control arc sections according to the mutual relation between every two measurement and control arc sections.
Specifically, the multi-arc segment relation determining module includes: eliminating the sub-modules and determining the sub-modules according to the multi-arc segment relation, wherein:
the rejecting submodule is used for rejecting the covered measurement and control arc sections according to the mutual relation between every two measurement and control arc sections;
and the multi-arc-section relation determining submodule is used for determining the correlation among the measurement and control arc sections according to the measurement and control arc sections after the elimination processing. Preferably, the multi-arc-segment relation determining sub-module is specifically configured to determine the covered measurement and control arc segments according to time data of any three measurement and control arc segments.
For specific execution processes of the units, the modules, and the sub-modules, reference may be made to the description in the foregoing method embodiments, and details are not described here again.
In practical operation, the units, modules and sub-modules may be combined or may be arranged singly, and the invention is not limited thereto.
The present embodiment also provides an electronic device, which may be a desktop computer, a tablet computer, a mobile terminal, and the like, but is not limited thereto. In this embodiment, the electronic device may be implemented by referring to the embodiments of the method and the aerospace measurement and control arc segment selection device, and the contents thereof are incorporated herein, and repeated descriptions are omitted.
Fig. 9 is a schematic block diagram of a system configuration of an electronic apparatus 600 according to an embodiment of the present invention. As shown in fig. 9, the electronic device 600 may include a central processor 100 and a memory 140; the memory 140 is coupled to the central processor 100. Notably, this diagram is exemplary; other types of structures may also be used in addition to or in place of the structure to implement telecommunications or other functions.
In one embodiment, the space measurement and control arc segment selection may be integrated into the central processor 100. The central processor 100 may be configured to control as follows:
acquiring time data of all measurement and control arc sections corresponding to the spacecraft in a preset time period, wherein the time data of each measurement and control arc section comprises the following steps: an arc start time and an arc end time;
determining the interrelation among the measurement and control arc sections according to the time data of the measurement and control arc sections, wherein the type of the interrelation comprises: covering, the interrelation between each measurement and control arc section includes: the relation between every two measurement and control arc sections and/or the relation between multiple measurement and control arc sections;
in response to the fact that the mutual relation among the measurement and control arc sections is determined to be covered, the covered measurement and control arc sections are removed from all the measurement and control arc sections;
and carrying out measurement and control operation on the spacecraft according to the measurement and control arc sections after the elimination treatment.
It can be known from the above description that the electronic equipment that this application embodiment provided, through the time data according to each observing and controlling arc section that obtains confirm each and observing and controlling the interrelation between the arc section, when the interrelation between the arc section of observing and controlling confirms for covering, follow the observing and controlling arc section that covers all observe and control and reject the processing in the arc section, it is right according to the observing and controlling arc section after rejecting the processing afterwards the spacecraft carries out observing and controlling operation, so, can reduce the observing and controlling arc section that covers under the unchangeable prerequisite of the length of time of guaranteeing total observing and controlling to can reduce the equipment quantity of participating in observing and controlling, improve the resource usage rate, reduce the economic cost of space activity.
In another embodiment, the selection device of the aerospace measurement and control arc segment may be configured separately from the central processing unit 100, for example, the selection device of the aerospace measurement and control arc segment may be configured as a chip connected to the central processing unit 100, and the selection function of the aerospace measurement and control arc segment is realized through the control of the central processing unit.
As shown in fig. 9, the electronic device 600 may further include: communication module 110, input unit 120, audio processing unit 130, display 160, power supply 170. It is noted that the electronic device 600 does not necessarily include all of the components shown in FIG. 9; furthermore, the electronic device 600 may also comprise components not shown in fig. 9, which may be referred to in the prior art.
As shown in fig. 9, the central processor 100, sometimes referred to as a controller or operational control, may include a microprocessor or other processor device and/or logic device, the central processor 100 receiving input and controlling the operation of the various components of the electronic device 600.
The memory 140 may be, for example, one or more of a buffer, a flash memory, a hard drive, a removable media, a volatile memory, a non-volatile memory, or other suitable device. The information relating to the failure may be stored, and a program for executing the information may be stored. And the central processing unit 100 may execute the program stored in the memory 140 to realize information storage or processing, etc.
The input unit 120 provides an input to the cpu 100. The input unit 120 is, for example, a key or a touch input device. The power supply 170 is used to provide power to the electronic device 600. The display 160 is used to display an object to be displayed, such as an image or a character. The display may be, for example, an LCD display, but is not limited thereto.
The memory 140 may be a solid state memory such as Read Only Memory (ROM), Random Access Memory (RAM), a SIM card, or the like. There may also be a memory that holds information even when power is off, can be selectively erased, and is provided with more data, an example of which is sometimes called an EPROM or the like. The memory 140 may also be some other type of device. Memory 140 includes buffer memory 141 (sometimes referred to as a buffer). The memory 140 may include an application/function storage section 142, and the application/function storage section 142 is used to store application programs and function programs or a flow for executing the operation of the electronic device 600 by the central processing unit 100.
The memory 140 may also include a data store 143, the data store 143 for storing data, such as contacts, digital data, pictures, sounds, and/or any other data used by the electronic device. The driver storage portion 144 of the memory 140 may include various drivers of the electronic device for communication functions and/or for performing other functions of the electronic device (e.g., messaging application, address book application, etc.).
The communication module 110 is a transmitter/receiver 110 that transmits and receives signals via an antenna 111. The communication module (transmitter/receiver) 110 is coupled to the central processor 100 to provide an input signal and receive an output signal, which may be the same as in the case of a conventional mobile communication terminal.
Based on different communication technologies, a plurality of communication modules 110, such as a cellular network module, a bluetooth module, and/or a wireless local area network module, may be provided in the same electronic device. The communication module (transmitter/receiver) 110 is also coupled to a speaker 131 and a microphone 132 via an audio processor 130 to provide audio output via the speaker 131 and receive audio input from the microphone 132 to implement general telecommunications functions. Audio processor 130 may include any suitable buffers, decoders, amplifiers and so forth. In addition, an audio processor 130 is also coupled to the central processor 100, so that recording on the local can be enabled through a microphone 132, and so that sound stored on the local can be played through a speaker 131.
The embodiment of the invention also provides a computer readable storage medium, on which a computer program is stored, and the computer program is executed by a processor to realize the steps of the space flight measurement and control arc segment selection method.
In summary, in order to overcome the problems of low measurement and control resource utilization efficiency, resource waste, high cost and the like caused by the existing measurement and control support of calling all measurement and control resources for a transit spacecraft, the embodiment of the invention provides a method for selecting a measurement and control arc section.
The preferred embodiments of the present invention have been described above with reference to the accompanying drawings. The many features and advantages of the embodiments are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of the embodiments which fall within the true spirit and scope thereof. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the embodiments of the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope thereof.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
The principle and the implementation mode of the invention are explained by applying specific embodiments in the invention, and the description of the embodiments is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.

Claims (10)

1. A selection method of an aerospace measurement and control arc segment is characterized by comprising the following steps:
acquiring time data of all measurement and control arc sections corresponding to the spacecraft in a preset time period, wherein the time data of each measurement and control arc section comprises the following steps: an arc start time and an arc end time;
determining the interrelation among the measurement and control arc sections according to the time data of the measurement and control arc sections, wherein the type of the interrelation comprises: covering, the interrelation between each measurement and control arc section includes: the relation between every two measurement and control arc sections and/or the relation between multiple measurement and control arc sections;
in response to the fact that the mutual relation among the measurement and control arc sections is determined to be covered, the covered measurement and control arc sections are removed from all the measurement and control arc sections;
and carrying out measurement and control operation on the spacecraft according to the measurement and control arc sections after the elimination treatment.
2. The method of claim 1, wherein determining the interrelationships between the measurement and control arc segments from the time data of the measurement and control arc segments comprises:
determining the correlation between all the measurement and control arc sections according to the time data between every two measurement and control arc sections;
and determining the interrelation among the measurement and control arc sections according to the interrelation between every two measurement and control arc sections.
3. The method of claim 2, wherein determining the interrelationship between the measurement and control arc segments according to the interrelationship between every two of the measurement and control arc segments comprises:
rejecting the covered measurement and control arc sections according to the interrelation between every two measurement and control arc sections;
and determining the correlation among the measurement and control arc sections according to the measurement and control arc sections after the elimination treatment.
4. The method of claim 3, wherein determining the interrelationship between the measurement and control arc segments comprises:
and determining the covered measurement and control arc sections according to the time data of any three measurement and control arc sections.
5. A selection device of an aerospace measurement and control arc segment is characterized by comprising:
the arc section data acquisition unit is used for acquiring time data of all measurement and control arc sections corresponding to the spacecraft in a preset time period, and the time data of each measurement and control arc section comprises: an arc start time and an arc end time;
the arc section relation determining unit is used for determining the interrelation among the measurement and control arc sections according to the time data of the measurement and control arc sections, and the type of the interrelation comprises the following steps: covering, the interrelation between each measurement and control arc section includes: the relation between every two measurement and control arc sections and/or the relation between multiple measurement and control arc sections;
the rejecting unit is used for responding to the mutual relation among the measurement and control arc sections to determine that the measurement and control arc sections are covered, and rejecting the covered measurement and control arc sections from all the measurement and control arc sections;
and the measurement and control unit is used for carrying out measurement and control operation on the spacecraft according to the measurement and control arc sections after the elimination processing.
6. The apparatus according to claim 5, wherein the arc segment relation determining unit includes:
the pairwise relation determining module is used for determining the mutual relation between the measurement and control arc sections according to the time data between every two measurement and control arc sections;
and the multi-arc-section relation determining module is used for determining the interrelation among the measurement and control arc sections according to the interrelation between every two measurement and control arc sections.
7. The apparatus of claim 6, wherein the multi-arc segment relationship determination module comprises:
the rejecting submodule is used for rejecting the covered measurement and control arc sections according to the mutual relation between every two measurement and control arc sections;
and the multi-arc-section relation determining submodule is used for determining the correlation among the measurement and control arc sections according to the measurement and control arc sections after the elimination processing.
8. The apparatus of claim 7, wherein the multi-arc relationship determination submodule is specifically configured to:
and determining the covered measurement and control arc sections according to the time data of any three measurement and control arc sections.
9. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, characterized in that the steps of the method of any of claims 1 to 4 are implemented when the processor executes the program.
10. A computer-readable storage medium, on which a computer program is stored which, when being executed by a processor, carries out the steps of the method of any one of claims 1 to 4.
CN202210098636.9A 2022-01-27 2022-01-27 Selection method and device of aerospace measurement and control arc section, electronic equipment and storage medium Pending CN114493273A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114955009A (en) * 2022-05-20 2022-08-30 北京航天飞行控制中心 Selection method, system, medium and equipment of earth orbit intersection butt joint

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114955009A (en) * 2022-05-20 2022-08-30 北京航天飞行控制中心 Selection method, system, medium and equipment of earth orbit intersection butt joint

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