CN109543321B - Time window generation method and device - Google Patents
Time window generation method and device Download PDFInfo
- Publication number
- CN109543321B CN109543321B CN201811443434.3A CN201811443434A CN109543321B CN 109543321 B CN109543321 B CN 109543321B CN 201811443434 A CN201811443434 A CN 201811443434A CN 109543321 B CN109543321 B CN 109543321B
- Authority
- CN
- China
- Prior art keywords
- satellite
- current
- value
- longitude
- latitude
- 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.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
- G06T7/00—Image analysis
- G06T7/70—Determining position or orientation of objects or cameras
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Computer Vision & Pattern Recognition (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
- Navigation (AREA)
Abstract
The application provides a time window generation method and device. The method comprises the following steps: acquiring an object longitude value and an object latitude value of a target object; acquiring a current longitude value and a current latitude value of a satellite subsatellite point at the current moment; judging whether a target object at the current moment is in a preset observation area or not according to the object longitude value, the object latitude value, the current longitude value and the current latitude value; and determining the time range within which the target object can be observed in the satellite earth-orbiting flight according to the plurality of time points of the target object in the preset observation area. According to the scheme of the embodiment of the application, the time range in which the target object can be observed is determined according to the position of the target object and the positions of the subsatellite points at each time point, so that the calculation efficiency can be greatly improved, and the calculation time can be saved.
Description
Technical Field
The application relates to the technical field of satellite imaging, in particular to a time window generation method and device.
Background
When calculating the observation time window of the satellite for the object and the ground object, the coordinates of the imaging area of the satellite and the coordinates of the target object range are usually calculated first, and then whether the imaging area covers the target object is judged to determine whether the time period is the access time window or not within the time length from the moment when the imaging area and the target object begin to have the same latitude until the moment when the imaging area and the target object do not have the same latitude.
In the prior art, in the method for acquiring the observation time window, the coordinates of the imaging area at each time point are calculated each time, then the time period in which the target object is possibly covered by the imaging area is judged, and then the coordinate position of the imaging area and the relationship between the coordinates of the imaging area and the target object are calculated in the time period, so that the calculation method has large calculation amount and low efficiency.
Disclosure of Invention
In order to overcome the above-mentioned deficiencies in the prior art, the present application aims to provide a time window generating method, which includes:
acquiring an object longitude value and an object latitude value of a target object;
acquiring a current longitude value and a current latitude value of a satellite subsatellite point at the current moment;
judging whether a target object at the current moment is in a preset observation area or not according to the object longitude value, the object latitude value, the current longitude value and the current latitude value;
and determining the time range within which the target object can be observed in the satellite earth-orbiting flight according to the plurality of time points of the target object in the preset observation area.
Optionally, the method further comprises acquiring an image including the target object according to a time range in which the target object can be observed in the satellite earth-orbiting flight.
Optionally, the step of obtaining the current longitude value and the current latitude value of the sub-satellite point of the satellite at the current time includes:
acquiring an initial longitude value and an initial latitude value of a sub-satellite point at an initial moment;
acquiring a first operating angle of an intersatellite point of the satellite, which runs in the longitude direction relative to a zero-degree longitude line, and a second operating angle of the satellite, which runs in the latitude direction relative to a zero-degree latitude line, according to the initial longitude and the initial latitude;
and calculating the current longitude value and the current latitude value of the sub-satellite point at the current moment according to the first operating angle and the second operating angle.
Optionally, the step of obtaining, according to the initial longitude and the initial latitude, a first operating angle at which an intersatellite point of the satellite operates in a longitude direction relative to a zero-degree longitude line and a second operating angle at which the intersatellite point operates in a latitude direction relative to a zero-degree latitude line includes:
acquiring the orbit inclination angle of the satellite at the current moment;
acquiring a total operation angle of a satellite at the current moment relative to the initial moment;
and calculating the first running angle and the second running angle according to the initial longitude, the initial latitude, the total running angle and the orbit inclination angle.
Optionally, the method further comprises:
calculating the running speed of the satellite according to the orbit radius of the satellite;
calculating the orbit period of the satellite according to the running speed of the satellite and the orbit radius;
the step of obtaining the total operation angle of the satellite at the current moment relative to the initial moment comprises the following steps:
and calculating the total operation angle according to the orbit period of the satellite and the time point of the current time.
Optionally, the step of determining whether the target object at the current moment is in the preset observation area according to the object longitude value, the object latitude value, the current longitude value and the current latitude value includes:
judging whether the longitude difference between the object longitude value and the current longitude value is within a first preset range or not, and whether the latitude difference between the object latitude value and the current latitude value is within a second preset range or not;
and if the longitude difference is within a first preset range and the latitude difference is within a second preset range, the target object is in a preset observation area at the current moment.
Optionally, the step of determining, according to a plurality of time points of the target object within the preset observation area, a time range in which the target object can be observed in the satellite earth-orbiting flight includes:
judging whether a plurality of continuous time points of the target object in a preset observation area exist or not;
and if so, determining the time range in which the target object can be observed in the satellite earth-orbiting flight according to the time between the two end points of the continuous time points.
Another object of the present application is to provide a time window generating apparatus, the apparatus comprising: the device comprises a first acquisition module, a second acquisition module, a judgment module and a time determination module;
the first acquisition module is used for acquiring an object longitude value and an object latitude value of a target object;
the second acquisition module is used for acquiring the current longitude value and the current latitude value of the satellite subsatellite point at the current moment;
the judging module is used for judging whether a target object at the current moment is in a preset observation area according to the object longitude value, the object latitude value, the current longitude value and the current latitude value;
the time determination module is used for determining a time range within which the target object can be observed in the satellite earth-orbiting flight according to a plurality of time points of the target object in the preset observation area.
Optionally, the apparatus further includes a control module configured to control the image capturing device to capture an image including the target object according to a time range within which the target object can be observed during the satellite orbiting.
The second acquisition module comprises a first acquisition submodule, a second acquisition submodule and a calculation module;
the first obtaining submodule is used for obtaining an initial longitude value and an initial latitude value of a sub-satellite point at an initial moment;
the second acquisition submodule is used for acquiring a first operation angle of an intersatellite point of the satellite, which runs in the longitude direction relative to a zero-degree longitude line, and a second operation angle of the satellite, which runs in the latitude direction relative to a zero-degree latitude line, according to the initial longitude and the initial latitude;
the calculation module is used for calculating the current longitude value and the current latitude value of the current subsatellite point according to the first operation angle and the second operation angle.
Compared with the prior art, the method has the following beneficial effects:
according to the method and the device, the current longitude value and the current latitude value of the sub-satellite point of the satellite at the current moment are calculated, whether the target object is in the preset observation area of the satellite at the current moment is judged according to the current longitude value and the current latitude value, the object longitude value and the object latitude value of the target object, whether the target object can be observed at the moment is judged, and then the time range of observing the target object is determined according to a plurality of time points of the object in the observation area. In the process, the longitude and the latitude of the target object and each time sub-satellite point are only required to be calculated, so that the calculation amount is greatly reduced, and the generation efficiency of the time window can be greatly improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive effort.
Fig. 1 is a schematic block diagram of a time window generation apparatus provided in an embodiment of the present application;
fig. 2 is a first flowchart of a time window generation method according to an embodiment of the present disclosure;
fig. 3 is a schematic flowchart of a second method for generating a time window according to an embodiment of the present application;
fig. 4 is a schematic flowchart of a process for obtaining a current longitude value and a current latitude value according to an embodiment of the present application;
fig. 5 is a schematic flowchart of calculating a first operating angle and a second operating angle according to an embodiment of the present application;
fig. 6 is a schematic flow chart illustrating a process of determining whether a target object is in a preset observation region according to an embodiment of the present application;
FIG. 7 is a schematic diagram of determining a time window for viewing a target object according to an embodiment of the present disclosure;
fig. 8 is a schematic diagram of a track of a sub-satellite point provided in the embodiment of the present application;
FIG. 9 is a diagram illustrating results of generating a time window according to an embodiment of the present application;
fig. 10 is a first block diagram illustrating a time window generating apparatus according to an embodiment of the present disclosure;
fig. 11 is a block diagram of a second structure of a time window generation apparatus according to an embodiment of the present application.
Icon: 100-a time window generating device; 110-a processor; 120-a memory; 130-a communication unit; 200-time window generation means; 210-a first obtaining module; 220-a second acquisition module; 230-a judgment module; 240-time determination module; 221-a first acquisition submodule; 222-a second acquisition submodule; 223-a calculation module.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. 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 application.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
The terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is further noted that, unless expressly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
Referring to fig. 1, fig. 1 is a time window generating apparatus 100 provided in an embodiment of the present application, the apparatus includes a processor 110 and a memory 120, the memory 120 stores executable instructions, and the processor 110 is interactively connected to the memory 120 for executing the executable instructions.
In this embodiment, the time window generating apparatus 100 may further include a communication unit 130, and the communication unit 130 may be interactively connected with the processor 110 and the memory 120, respectively.
In the time window generating apparatus 100 of the embodiment, the Memory 120 may be, but is not limited to, a Random Access Memory 120 (RAM), a Read Only Memory 120 (ROM), a Programmable Read Only Memory 120 (PROM), an Erasable Read Only Memory 120 (EPROM), an electrically Erasable Read Only Memory 120 (EEPROM), and the like. The memory 120 is configured to store executable instructions, and the processor 110 executes the executable instructions after receiving the executable instructions.
Referring to fig. 2, fig. 2 is a schematic flowchart of a time window generation method that can be applied to the above-mentioned device according to an embodiment of the present application, where the method includes steps S110 to S140.
Step S110, an object longitude value and an object latitude value of the target object are obtained.
The embodiment is used for acquiring the longitude value (object longitude value) of the position of the target object and the latitude value (object latitude value) of the position of the target object. Specifically, the longitude value and the latitude value of the object may be stored longitude values and latitude values, or may be calculated from the position of the satellite and the image acquired by the satellite.
Referring to fig. 3, optionally, in the present embodiment, after step S110, the method further includes step S210 to step S220.
Since the orbit radius of the satellite is known, in this embodiment, in step S210, the operation speed of the satellite is calculated according to the orbit radius of the satellite.
Specifically, in this embodiment, when the running speed v of the satellite is calculated, the flying speed v may be calculated according to the universal gravitation formula, and the calculation formula of v is as follows:
wherein G is the universal gravitation constant of the earth, M is the mass of the satellite, R is the radius of the earth, and h is the flight altitude of the satellite.
And step S220, calculating the orbit period of the satellite according to the running speed of the satellite and the orbit radius.
The present embodiment is used for calculating the orbital period P of the satellite, and the calculation formula for calculating the orbital period P of the satellite is as follows:
in this embodiment, steps S210 to S220 may be performed before step S110.
And step S120, acquiring the current longitude value and the current latitude value of the satellite subsatellite point at the current moment.
The present embodiment is used to calculate the longitude value (current longitude value) of the satellite's subsatellite point and the latitude value (current latitude value) of the satellite's subsatellite point at the current time.
Referring to fig. 4, optionally, in this embodiment, step S120 includes substeps S121-S123.
Step S121, obtaining an initial longitude value and an initial latitude value of the sub-satellite point at the initial moment.
For example, if time t is represented by t, and time t is 0 as an initial time, then time t is 0, i.e., the longitude value of the satellite at the time point at which the satellite is located is the initial longitude value of the satellite at the time point, and time t is 0, i.e., the latitude value of the satellite at the time point at which the satellite is located is the initial latitude value of the satellite at the time point. When t is 0, longitude and latitude coordinates (w) of the subsatellite point0，h0)。
And step S122, calculating a first operation angle and a second operation angle of the subsatellite point. And acquiring a first operating angle of the satellite subsatellite point relative to the zero-degree longitude line in the longitude direction and a second operating angle relative to the zero-degree latitude line in the latitude direction according to the initial longitude and the initial latitude.
Referring to fig. 5, optionally, step S122 in this embodiment includes sub-steps S1221 to S1223.
And step S1221, acquiring the orbital inclination of the satellite at the current moment.
In this embodiment, the orbital inclination of the satellite may be known.
In step S1222, a total operating angle of the satellite at the current time with respect to the initial time is obtained. The total operation angle of the satellite at the current moment relative to the initial moment, namely the operation angle beta of the satellite at the time t relative to the initial position. The formula for calculating β is:
β＝2πt/P
step S1223, calculating the first running angle and the second running angle. The present embodiment is configured to calculate the first running angle and the second running angle according to the initial longitude, the initial latitude, the total running angle, and the track inclination.
The embodiment is used for calculating the radian of the satellite subsatellite point at the time t relative to the longitude direction and the latitude direction of the satellite subsatellite point position at the initial time.
The calculation formula of the first operating angle and the second operating angle of the sub-satellite point at the time t is as follows:
wherein (w)t,ht) And (5) latitude and longitude coordinates of the subsatellite point at the time t. Alpha is the orbital inclination angle (included angle between the orbital plane and the equatorial plane) of a certain known satellite, beta is the operated angle of the satellite relative to the initial position at the moment T (namely the interstellar point of the earth surface satellite is the radian of the operation relative to the initial moment at the moment T), and T represents the maximum value of T, namely the radian of the TAnd setting and judging whether the target object is at the end time point of the preset observation area or not according to requirements.
And step S123, calculating the current longitude value and the current latitude value of the sub-satellite point at the current moment. The embodiment is used for calculating the current longitude value and the current latitude value of the current sub-satellite point according to the first operating angle and the second operating angle.
The present embodiment is used to convert the first operating angle and the second operating angle at time t into a defined range of values:
wherein, (w't,h't) And the longitude and latitude coordinate conversion value of the subsatellite point at the time t is obtained. For example, the latitude and longitude calculation values of the sub-satellite point at time t can be converted to [0, 360 ] respectively]，[-90，90]。
In the embodiment, the first operation angle and the second operation angle at the moment t are converted into the limited numerical range, so that whether the target object is in the preset observation area can be conveniently and quickly calculated.
Referring to fig. 2, in step S130, it is determined whether the target object is in the preset observation area at the current moment.
Specifically, the present embodiment is configured to determine whether the target object is in a preset observation area at the current moment according to the object longitude value, the object latitude value, the current longitude value, and the current latitude value.
The present embodiment is used to determine whether a target object can be in an observable region of a satellite (a preset observation region). For example, the observation point may be an image acquisition device on a satellite. And setting a cone by taking the observation point and the satellite point as axes and taking the observation point as a fixed point, and then taking the area inside the cone as an observable area. At this time, the observable region of the satellite is a circular region.
Referring to fig. 6, optionally, in the present embodiment, the step S130 includes sub-steps S131 to S132.
Step S131, determining whether a longitude difference between the object longitude value and the current longitude value is within a first preset range. Whether the latitude difference between the object latitude value and the current latitude value is within a second preset range or not.
Specifically, it may be judged whether or not it is within a preset range.
When the preset observation region is all regions including a certain longitude range and a certain latitude range, the following formula manner can also be used for judgment.
Δ＝360(R+h)tanφ/(2πR)
σtIs a zero-one variable, where σ (t) ═ 1 denotes that the earth target observed object can be observed, and σ (t) ═ 0 denotes that the earth target observed object cannot be observed, where Φ is the observation angle of the satellite (the maximum angle of the cone-shaped observation region formed by the observation points of the satellite), and w is the observation angle of the satellited，hdRespectively representing the longitude (object longitude value) and latitude (object latitude value) of the target object
And a substep S132, if the longitude difference is within a first preset range and the latitude difference is within a second preset range, determining that the target object is in a preset observation area at the current moment.
For example, in this embodiment, step S120 to step S130 may be executed from the time when T is 0, and after step S120 to step S130 are executed, the current time point is updated to make T equal to T +1, and then step S120 to step S130 are repeated again until a preset stop condition is met, for example, a preset stop time point T is reached.
With continued reference to fig. 2, step S140 determines a time range within which the target object can be observed during the satellite orbiting. The method and the device are used for determining the time range in which the target object can be observed in the satellite earth-orbiting flight according to the plurality of time points of the target object in the preset observation area.
Referring to fig. 7, optionally, in the present embodiment, the step S140 includes substeps 141 to step S142.
Step S141, determining whether there are a plurality of consecutive time points of the target object in the preset observation area.
And step S142, if the time exists, determining a time range in which the target object can be observed in the satellite earth-orbiting flight according to the time between the two end points of the continuous time points.
This step may be performed by taking the value between two end points of a series of consecutive time points as a time range (time window) in which the target object can be observed after obtaining the series of consecutive time points.
Optionally, the method further comprises step S150. Referring to fig. 3, in step S150, the image of the target object is obtained according to the obtaining time window. That is, the image including the target object is acquired according to a time range in which the target object can be observed while the satellite is in orbit.
The scheme of the present embodiment is described below with an example of a specific generation time window.
The orbital altitude of the LEO satellite is set to 998.95 km, the orbital inclination (denoted as α) of the satellite is 85 °, the initial latitude and longitude coordinates are (0 ° ), and the observable inclination of the satellite is Φ equal to 27 °. According to the above steps, longitude and latitude coordinates of each subsatellite point at each time point in the [0, 5760] time range are obtained, and a trace of the subsatellite point in the predetermined time range T is drawn, as shown in FIG. 8. In fig. 8, 10 target objects, which are drawn as color triangle symbols, are randomly generated in china, and the longitude and latitude coordinates of the 10 target objects are shown in table 1.
TABLE 110 Latitude and longitude coordinates of target object
| Observation target | Latitude and longitude coordinate (degree and degree) |
| 1 | (83，35) |
| 2 | (78，24) |
| 3 | (93，7) |
| 4 | (128，44) |
| 5 | (88，48) |
| 6 | (78，5) |
| 7 | (128，13) |
| 8 | (77，4) |
| 9 | (131，47) |
| 10 | (90，1) |
Referring to FIG. 9, FIG. 9 illustrates a time window in the present embodiment.
Referring to fig. 9, another object of the present application is to provide a time window generating apparatus 200, in which the time window generating apparatus 200 includes a software function module that can be stored in the memory 120 in the form of software or firmware or solidified in an Operating System (OS) of a time window generating device. The device comprises: a first obtaining module 210, a second obtaining module 220, a judging module 230, and a time determining module 240.
The first obtaining module 210 is configured to obtain an object longitude value and an object latitude value of a target object.
In this embodiment, the first obtaining module 210 may be configured to execute the step S110, and please refer to the step S110 for the description of the first obtaining module 210.
The second obtaining module 220 is configured to obtain a current longitude value and a current latitude value of the satellite sub-satellite point at the current time.
In this embodiment, the second obtaining module 220 may be configured to perform the step S120, and please refer to the step S120 for the description of the second obtaining module 220.
The determining module 230 is configured to determine whether the target object is in a preset observation area at the current moment according to the object longitude value, the object latitude value, the current longitude value, and the current latitude value.
In this embodiment, the determining module 230 can be used to execute the step S130, and please refer to the step S130 for the description of the determining module 230.
The time determination module 240 is configured to determine a time range in which the target object can be observed in the satellite earth-orbiting flight according to a plurality of time points of the target object within the preset observation area.
In this embodiment, the time determination module 240 may be configured to execute step S140, and please refer to step S140 for the description of the time determination module 240.
Referring to fig. 10, optionally, the apparatus further includes a control module, configured to control the image capturing device to obtain an image including the target object according to a time range in which the target object can be observed in the satellite earth-orbiting flight.
The second obtaining module 220 includes a first obtaining sub-module 221, a second obtaining sub-module 222, and a calculating module 223.
The first obtaining sub-module 221 is configured to obtain an initial longitude value and an initial latitude value of the sub-satellite point at the initial time.
In this embodiment, the first obtaining sub-module 221 may be configured to perform the step S121, and please refer to the step S121 for the description of the first obtaining sub-module 221.
The second obtaining sub-module 222 is configured to obtain, according to the initial longitude and the initial latitude, a first operating angle at which an intersatellite point of the satellite operates in a longitude direction with respect to a zero-degree longitude line and a second operating angle at which the satellite operates in a latitude direction with respect to a zero-degree latitude line.
In this embodiment, the second obtaining sub-module 222 may be configured to perform the step S122, and please refer to the step S122 for the description of the second obtaining sub-module 222.
The calculating module 223 is configured to calculate a current longitude value and a current latitude value of the sub-satellite point at the current time according to the first operating angle and the second operating angle.
In this embodiment, the calculating module 223 can be used to execute step S123, and please refer to step S123 for the description of the calculating module 223.
To sum up, the embodiment of the present application calculates the current longitude value and the current latitude value of the satellite at the current time, and then determines whether the target object is in the preset observation area of the satellite at the current time according to the current longitude value and the current latitude value, and the object longitude value and the object latitude value of the target object, so as to determine whether the target object can be observed at the current time, and then determines the time range in which the target object can be observed according to a plurality of time points of the object in the observation area. In the process, the longitude and the latitude of the target object and each time sub-satellite point are only required to be calculated, so that the calculation amount is greatly reduced, and the generation efficiency of the time window can be greatly improved.
In the embodiments provided in the present application, it should be understood that the disclosed apparatus and method may be implemented in other ways. The apparatus embodiments described above are merely illustrative, and for example, the flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
In addition, functional modules in the embodiments of the present application may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part.
The functions, if implemented in the form of software functional modules and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present application, and shall be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A method for time window generation, the method comprising:
acquiring an object longitude value and an object latitude value of a target object;
acquiring a current longitude value and a current latitude value of a satellite subsatellite point at the current moment;
judging whether a target object at the current moment is in a preset observation area or not according to the object longitude value, the object latitude value, the current longitude value and the current latitude value;
determining a time range within which the target object can be observed in the satellite earth-orbiting flight according to a plurality of time points of the target object in the preset observation area;
the step of obtaining the current longitude value and the current latitude value of the satellite subsatellite point at the current moment comprises the following steps:
acquiring an initial longitude value and an initial latitude value of a sub-satellite point at an initial moment;
acquiring a first operating angle of an intersatellite point of the satellite, which runs in the longitude direction relative to a zero-degree longitude line, and a second operating angle of the satellite, which runs in the latitude direction relative to a zero-degree latitude line, according to the initial longitude and the initial latitude;
calculating a current longitude value and a current latitude value of the sub-satellite point at the current moment according to the first operating angle and the second operating angle;
wherein the step of obtaining a first operating angle at which the intersatellite point of the satellite operates in the longitudinal direction relative to the zero-degree longitude line and a second operating angle at which the intersatellite point of the satellite operates in the latitudinal direction relative to the zero-degree latitude line according to the initial longitude and the initial latitude comprises:
acquiring the orbit inclination angle of the satellite at the current moment;
acquiring a total operation angle of a satellite at the current moment relative to the initial moment;
calculating the first running angle and the second running angle according to the initial longitude, the initial latitude, the total running angle and the track inclination;
wherein the method further comprises:
calculating the running speed of the satellite according to the orbit radius of the satellite;
calculating the orbit period of the satellite according to the running speed of the satellite and the orbit radius;
the step of obtaining the total operation angle of the satellite at the current moment relative to the initial moment comprises the following steps:
calculating the total operation angle according to the orbit period of the satellite and the time point of the current time;
wherein the step of judging whether the target object at the current moment is in a preset observation area according to the object longitude value, the object latitude value, the current longitude value and the current latitude value comprises the following steps:
judging whether the longitude difference between the object longitude value and the current longitude value is within a first preset range or not, and whether the latitude difference between the object latitude value and the current latitude value is within a second preset range or not;
and if the longitude difference is within a first preset range and the latitude difference is within a second preset range, the target object is in a preset observation area at the current moment.
2. The method of generating a time window of claim 1, further comprising,
an image including the target object is acquired according to a time range in which the target object can be observed in the satellite earth-orbiting flight.
3. The method according to claim 1 or 2, wherein the step of determining the time range in which the target object can be observed in the satellite orbiting flight according to the plurality of time points of the target object in the preset observation area comprises:
judging whether a plurality of continuous time points of the target object in a preset observation area exist or not;
and if so, determining the time range in which the target object can be observed in the satellite earth-orbiting flight according to the time between the two end points of the continuous time points.
4. An apparatus for generating a time window, the apparatus comprising: the device comprises a first acquisition module, a second acquisition module, a judgment module and a time determination module;
the first acquisition module is used for acquiring an object longitude value and an object latitude value of a target object;
the second acquisition module is used for acquiring the current longitude value and the current latitude value of the satellite subsatellite point at the current moment;
the judging module is used for judging whether a target object at the current moment is in a preset observation area according to the object longitude value, the object latitude value, the current longitude value and the current latitude value;
the time determination module is used for determining a time range in which the target object can be observed in the satellite earth-orbiting flight according to a plurality of time points of the target object in the preset observation area;
the second acquisition module comprises a first acquisition submodule, a second acquisition submodule and a calculation module;
the first obtaining submodule is used for obtaining an initial longitude value and an initial latitude value of a sub-satellite point at an initial moment;
the second acquisition submodule is used for acquiring a first operation angle of an intersatellite point of the satellite, which runs in the longitude direction relative to a zero-degree longitude line, and a second operation angle of the satellite, which runs in the latitude direction relative to a zero-degree latitude line, according to the initial longitude and the initial latitude;
the calculation module is used for calculating the current longitude value and the current latitude value of the sub-satellite point at the current moment according to the first operation angle and the second operation angle;
the second obtaining submodule is specifically used for obtaining the orbital inclination angle of the satellite at the current moment; acquiring a total operation angle of a satellite at the current moment relative to the initial moment; calculating the first running angle and the second running angle according to the initial longitude, the initial latitude, the total running angle and the track inclination;
wherein, the judging module is specifically configured to: judging whether the longitude difference between the object longitude value and the current longitude value is within a first preset range or not, and whether the latitude difference between the object latitude value and the current latitude value is within a second preset range or not; and if the longitude difference is within a first preset range and the latitude difference is within a second preset range, the target object is in a preset observation area at the current moment.
5. The apparatus of claim 4, further comprising a control module configured to control the image capture device to capture the image including the target object based on a time frame in which the target object is observable during the satellite orbiting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811443434.3A CN109543321B (en) | 2018-11-29 | 2018-11-29 | Time window generation method and device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811443434.3A CN109543321B (en) | 2018-11-29 | 2018-11-29 | Time window generation method and device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109543321A CN109543321A (en) | 2019-03-29 |
| CN109543321B true CN109543321B (en) | 2020-11-03 |
Family
ID=65852375
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811443434.3A Active CN109543321B (en) | 2018-11-29 | 2018-11-29 | Time window generation method and device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109543321B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111637881B (en) * | 2020-05-07 | 2022-03-04 | 北京控制工程研究所 | Earth surface model graph-based method for forecasting earth surface attributes of subsatellite points |
| CN112849434B (en) * | 2021-01-28 | 2024-05-14 | 中国科学院微小卫星创新研究院 | Computing method and application of circular orbit satellite overhead moment |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103281126A (en) * | 2013-06-20 | 2013-09-04 | 中国科学院遥感与数字地球研究所 | Method for acquiring access time window for shooting and imaging ground target area by satellite |
| CN106885556A (en) * | 2017-02-27 | 2017-06-23 | 中国地质大学（武汉） | Pitching observation covering band determines method and device to a kind of scan-type satellite over the ground |
| CN106918317A (en) * | 2017-02-27 | 2017-07-04 | 中国地质大学（武汉） | Side-sway observation covering band determines method and device to a kind of scan-type satellite over the ground |
| CN108537447A (en) * | 2018-04-11 | 2018-09-14 | 北京航空航天大学 | Mission effectiveness computational methods, device and the electronic equipment of satellite |
-
2018
- 2018-11-29 CN CN201811443434.3A patent/CN109543321B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103281126A (en) * | 2013-06-20 | 2013-09-04 | 中国科学院遥感与数字地球研究所 | Method for acquiring access time window for shooting and imaging ground target area by satellite |
| CN106885556A (en) * | 2017-02-27 | 2017-06-23 | 中国地质大学（武汉） | Pitching observation covering band determines method and device to a kind of scan-type satellite over the ground |
| CN106918317A (en) * | 2017-02-27 | 2017-07-04 | 中国地质大学（武汉） | Side-sway observation covering band determines method and device to a kind of scan-type satellite over the ground |
| CN108537447A (en) * | 2018-04-11 | 2018-09-14 | 北京航空航天大学 | Mission effectiveness computational methods, device and the electronic equipment of satellite |
Non-Patent Citations (3)
| Title |
|---|
| Predicting the Visibility of LEO Satellites;IRFAN ALI等;《IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS》;19991031;第35卷(第4期);第1183-1190页 * |
| 卫星对区域目标的时间窗口快速计算方法;宋志明等;《计算机仿真》;20140930;第31卷(第9期);正文第2-4 * |
| 地球静止卫星覆盖地域的经纬度与覆盖的条件;蔡永芳;《数学的实践与认识》;19991231;正文第1节 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109543321A (en) | 2019-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5923286A (en) | GPS/IRS global position determination method and apparatus with integrity loss provisions | |
| CN110007317B (en) | Star-selection optimized advanced receiver autonomous integrity monitoring method | |
| US9726499B2 (en) | Method of determining a radius of protection associated with a navigation parameter of a hybrid inertial navigation system, and associated system | |
| CN109543321B (en) | Time window generation method and device | |
| CN102116626B (en) | Prediction and correction method of node of star point track image | |
| US20200025571A1 (en) | Navigation system | |
| Sang et al. | Experimental results of debris orbit predictions using sparse tracking data from Mt. Stromlo | |
| CN112114341B (en) | Low-earth-orbit satellite cooperative frequency measurement passive positioning method | |
| EP2799890B1 (en) | Method and system for determining the speed of an aircraft relative to the air | |
| JP5439980B2 (en) | Orbit determination apparatus and orbit determination method | |
| EP3598070A1 (en) | Methods for monitoring the output performance of state estimators in navigation systems | |
| JP4719658B2 (en) | Satellite observation plan program and satellite observation plan creation device | |
| CN111044053B (en) | Navigation method and device of single-steering-wheel unmanned vehicle and single-steering-wheel unmanned vehicle | |
| CN115630686B (en) | Method for recovering land water reserve anomalies from satellite gravity data using machine learning | |
| CN113496083B (en) | GPS mobile station vertical speed field optimization method and device | |
| CN116917771A (en) | Method for determining at least one system state by means of a Kalman filter | |
| de Santayana et al. | Surface characterization and optical navigation at the Rosetta flyby of asteroid Lutetia | |
| CN110210004B (en) | Ground evapotranspiration downscaling method and device | |
| CN114200491A (en) | Navigation data-based emergency spacecraft ephemeris determination method and system | |
| Hayati et al. | The Use of MODIS and Sentinel-1 Data Fusion to Estimate Precipitable Water Vapor Values | |
| Zhang et al. | Generating time series of medium-resolution albedo images by Kalman filtering algorithm | |
| CN116794693A (en) | GNSS autonomous orbit determination method for spacecraft | |
| CN117909641A (en) | Remote sensing constellation scale estimation method, system, equipment and medium | |
| RU2668659C1 (en) | Strap-down navigation system corrected by external position and speed information | |
| McGee et al. | Sensor Model and Filter Considerations for Terrain Relative Navigation |
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 |