CN114202621B - Method and device for realizing mass space target display based on B/S architecture - Google Patents
Method and device for realizing mass space target display based on B/S architecture Download PDFInfo
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Abstract
The embodiment of the application provides a method and a device for realizing mass space target display based on a B/S architecture. The method comprises the following steps: acquiring a first running ephemeris of a space target in a preset coordinate system comprising first warp height coordinates of the space target at all moments and first warp height coordinate variables of the space target at adjacent moments in a first time period; dividing the first time period according to a preset frequency, and determining a plurality of first sub-moments; calculating a second longitude and latitude height coordinate of the first sub moment according to the first longitude and latitude height coordinate and the first longitude and latitude height coordinate variable based on a second derivative algorithm; and mapping all the second longitude and latitude high coordinates into the first operating ephemeris to generate a space target operating track corresponding to the first time period. The application can improve the phenomenon of blocking and stopping when loading the operation scene of the whole space target, causes the problem that the effect of the whole space target for panoramic display is relatively poor, and achieves the effect of promoting the whole space target for panoramic display.
Description
Technical Field
The embodiment of the application relates to the technical field of space target operation, in particular to a method and a device for realizing mass space target display based on a B/S (browser/server) architecture.
Background
Space targets include three types, satellite, rocket body and space debris. The software development company for the current satellite operation display only has a good panoramic display effect on the satellite, but targets in space not only include the satellite, but also include a large amount of rocket debris and space debris.
In the process of implementing the invention, the inventor finds that a stuck phenomenon occurs when the current scheme is adopted to load the operation scene of the whole space target, so that the panoramic display effect of the whole space target is poor.
Disclosure of Invention
The embodiment of the application provides a method and a device for realizing mass space target display based on a B/S (browser/server) architecture, which can solve the problem that the panoramic display effect of the whole space target is poor due to the fact that a stuck phenomenon can occur when the operation scene of the whole space target is loaded.
In a first aspect of the application, a method for realizing mass space target display based on a B/S architecture is provided, which includes:
acquiring a first running ephemeris of a space target in a preset coordinate system, wherein the first running ephemeris comprises first warp-weft high coordinates of the space target at all moments and first warp-weft high coordinate variables of the space target at adjacent moments in a first time period;
dividing the first time period according to a preset frequency to generate a plurality of second time periods;
determining a plurality of first sub-moments according to a plurality of second time periods;
calculating a second longitude and latitude high coordinate of the first sub moment according to the first longitude and latitude high coordinate and the first longitude and latitude coordinate variable based on a second derivative algorithm;
and mapping all the second longitude and latitude high coordinates into the first running ephemeris to generate a space target running track corresponding to the first time period.
By adopting the technical scheme, the first running ephemeris of the space target in the preset coordinate system comprising the first warp-weft high coordinate of the space target at all the moments and the first warp-weft high coordinate variable of the space target at the adjacent moment in the first time period is obtained, and the first time period is divided according to the preset frequency to generate a plurality of second time periods; determining a first sub-moment according to a plurality of second time periods, and calculating a second longitude and latitude high coordinate of the first sub-moment according to the first longitude and latitude high coordinate and the first longitude and latitude high coordinate variable based on a second derivative algorithm; mapping all the second longitude and latitude high coordinates into a first operation ephemeris to generate a space target operation track corresponding to a first time period; in conclusion, when the operation track comprising a large number of space targets is displayed, the display scene can be more flow, the phenomenon of blocking is avoided, the problem that the effect of carrying out panoramic display on the whole space target is poor due to the fact that the phenomenon of blocking can occur when the operation scene of the whole space target is loaded can be solved, and the effect of improving the panoramic display effect on the whole space target is achieved.
In one possible implementation manner, the method further includes:
selecting a plurality of fourth time periods in a third time period after the first time period;
acquiring a second running ephemeris of the space target in the preset coordinate system, wherein the second running ephemeris comprises third longitude and latitude high coordinates of the space target at all moments and third longitude and latitude high coordinate variables of the space target at adjacent moments in a third time period;
dividing the fourth time period according to the preset frequency to generate a plurality of fifth time periods;
determining a plurality of second sub-moments according to a plurality of fifth time periods;
calculating a fourth longitude and latitude height coordinate of the second sub-moment according to the third longitude and latitude height coordinate and the third longitude and latitude height coordinate variable based on a second derivative algorithm;
and based on the error threshold, according to the third longitude and latitude high coordinate and the fourth longitude and latitude high coordinate in a plurality of third time periods, error correction is carried out on the long-term running track of the space target.
In a possible implementation manner, the performing error correction on the long-term operation trajectory of the space target according to the third longitude and latitude coordinate and the fourth longitude and latitude coordinate in the third time periods based on the error threshold includes:
comparing the third longitude and latitude height coordinate and the fourth longitude and latitude height coordinate at the same moment in a third time period to obtain a longitude and latitude height coordinate difference value;
judging whether the difference value of the longitude and latitude high coordinates exceeds the error threshold value;
and if so, regenerating the space target running track according to the third longitude and latitude high coordinate, and realizing error correction on the space target long-term running track.
In one possible implementation manner, the method further includes:
and adjusting the running time parameter of the space target running track according to the preset speed.
In a second aspect of the present application, a device for realizing mass space target display based on a B/S architecture is provided, which includes:
the first acquisition module is used for acquiring a first operating ephemeris of a space target in a preset coordinate system, wherein the first operating ephemeris comprises first longitude and latitude coordinates of the space target at all moments and first longitude and latitude coordinate variables of the space target at adjacent moments in a first time period;
the first dividing module is used for dividing the first time period according to a preset frequency to generate a plurality of second time periods;
a first determining module, configured to determine a plurality of first sub-moments according to a plurality of the second time periods;
the first calculating module is used for calculating a second longitude and latitude high coordinate of the first sub moment according to the first longitude and latitude high coordinate and the first longitude and latitude high coordinate variable based on a second derivative algorithm;
and the mapping module is used for mapping all the second longitude and latitude high coordinates into the first operating ephemeris to generate a space target operating track corresponding to the first time period.
In one possible implementation manner, the method further includes:
the selection module is used for selecting a plurality of fourth time periods in a third time period after the first time period;
the second acquisition module is used for acquiring a second running ephemeris of the space target in the preset coordinate system, wherein the second running ephemeris comprises third longitude and latitude high coordinates of the space target at all moments and third longitude and latitude high coordinate variables of the space target at adjacent moments in a third time period;
the second dividing module is used for dividing the fourth time period according to the preset frequency to generate a plurality of fifth time periods;
a second determining module, configured to determine a plurality of second sub-moments according to a plurality of the fifth time periods;
the second calculation module is used for calculating a fourth longitude and latitude height coordinate of the second sub-moment according to the third longitude and latitude height coordinate and the third longitude and latitude height coordinate variable based on a second derivative algorithm;
and the comparison module is used for realizing error correction on the long-term running track of the space target based on the error threshold value according to the third longitude and latitude high coordinate and the fourth longitude and latitude high coordinate in a plurality of third time periods.
In one possible implementation, the comparison module includes:
the comparison unit is used for comparing the third longitude and latitude height coordinate and the fourth longitude and latitude height coordinate at the same moment in a third time period to obtain a longitude and latitude height coordinate difference value;
the judging unit is used for judging whether the longitude and latitude high coordinate difference value exceeds the error threshold value;
and the generating unit is used for regenerating a space target running track according to the third longitude and latitude high coordinate if the third longitude and latitude high coordinate is true, so that error correction is carried out on the space target long-term running track.
In one possible implementation manner, the method further includes:
and the adjusting module is used for adjusting the running time parameter of the space target running track according to the preset speed.
In a third aspect of the present application, an electronic device is provided. The electronic device includes: a memory having a computer program stored thereon and a processor implementing the method as described above when executing the computer program.
In a fourth aspect of the application, a computer-readable storage medium is provided, on which a computer program is stored, which computer program, when being executed by a processor, carries out the steps of the method.
It should be understood that what is described in this summary section is not intended to limit key or critical features of the embodiments of the application, nor is it intended to limit the scope of the application. Other features of the present application will become apparent from the following description.
Drawings
The above and other features, advantages and aspects of various embodiments of the present application will become more apparent by referring to the following detailed description when taken in conjunction with the accompanying drawings. In the drawings, like or similar reference characters designate like or similar elements, and wherein:
FIG. 1 shows a flowchart of a method for implementing mass space target display based on a B/S architecture in the embodiment of the present application.
Fig. 2 shows a structure diagram of a device for realizing mass space target display based on a B/S architecture in the embodiment of the present application.
Fig. 3 shows a schematic structural diagram of an electronic device suitable for implementing embodiments of the present application.
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.
The method for realizing the display of the mass space targets based on the B/S architecture can be applied to the technical field of space target operation.
At present, most software development companies for satellite operation and display are developed secondarily based on a three-dimensional data visualization framework (cecum open source framework) in a browser and server architecture mode (B/S architecture). Specifically, the ceium open source framework provides a standard satellite loading interface and a file format, and the trajectory scene can be displayed by inputting required parameters into the interface. For example, the number of satellites in orbit in space is about 6000, and the panoramic display in the mode can achieve good effect.
However, space objects include satellites, rocket debris, and a large amount of space debris, and the number of space objects currently in orbit is probably more than 20000. When the whole space target is loaded in the mode to display the full set of motion scenes, the motion scenes are extremely blocked.
Aiming at the katon problem, another three-dimensional engine programming (Primitive API) is provided based on the ceium open source framework, and the position of a point can be loaded in the earth scene according to the three elements of longitude, latitude and height of the point. However, after 20000 space target positions are loaded by using this method, although the scene has no stuck phenomenon, this method cannot make the point move.
In order to solve the technical problem, the embodiment of the application provides a method for realizing mass space target display based on a B/S architecture. In some embodiments, the method for realizing the massive space target display based on the B/S architecture can be executed by electronic equipment.
FIG. 1 shows a flowchart of a method for implementing mass space target display based on a B/S architecture in the embodiment of the present application. Referring to fig. 1, the method for realizing the mass space target display based on the B/S architecture in the embodiment includes:
step S101: the method comprises the steps of obtaining a first running ephemeris of a space target in a preset coordinate system, wherein the first running ephemeris comprises first warp high coordinates of the space target at all moments and first warp high coordinate variables of the space target at adjacent moments in a first time period.
Step S102: and dividing the first time period according to a preset frequency to generate a plurality of second time periods.
Step S103: and determining a plurality of first sub-time moments according to a plurality of second time periods.
Step S104: and calculating a second longitude and latitude high coordinate of the first sub moment according to the first longitude and latitude high coordinate and the first longitude and latitude coordinate variable based on a second derivative algorithm.
Step S105: and mapping all the second longitude and latitude high coordinates into the first operating ephemeris to generate a space target operating track corresponding to the first preset time period.
By adopting the technical scheme, the first running ephemeris of the space target in the preset coordinate system comprising the first warp-weft high coordinate of the space target at all the moments and the first warp-weft high coordinate variable of the space target at the adjacent moment in the first time period is obtained, and the first time period is divided according to the preset frequency to generate a plurality of second time periods; determining a first sub-moment according to a plurality of second time periods, and calculating a second longitude and latitude high coordinate of the first sub-moment according to the first longitude and latitude high coordinate and the first longitude and latitude high coordinate variable based on a second derivative algorithm; mapping all the second longitude and latitude high coordinates into a first running ephemeris to generate a space target running track corresponding to a first preset time period; in conclusion, when the operation track comprising a large number of space targets is displayed, the display scene can be more flow, the phenomenon of blocking is avoided, the problem that the effect of carrying out panoramic display on the whole space target is poor due to the fact that the phenomenon of blocking can occur when the operation scene of the whole space target is loaded can be solved, and the effect of improving the panoramic display effect on the whole space target is achieved.
In step S101, the preset coordinate system includes an inertial coordinate system and a ground fixation coordinate system, which can be arbitrarily selected according to the calculation habit. And, data calculated in the inertial coordinate system or the ground-fixed coordinate system may be mutually converted in the inertial coordinate system and the ground-fixed coordinate system.
In the embodiment of the application, the first run ephemeris of the space target is the run ephemeris of the space target in the satellite orbit, that is, the position and the velocity of the space target at any time, which is solved by using a Two-Line Element (TLE file) based on a Simplified conventional perturbation model (SGP 4 model).
In the embodiment of the application, the first time period is the time for the space target to perform panoramic display in the operation process, namely the total time of short-term track simulation of the space target. The first warp and weft height coordinates of the space target at all moments in the first time period and the first warp and weft height coordinate variables (the speed of the first warp and weft height coordinates on the three-dimensional space coordinate axis) of the space target at the adjacent moments in the first time period are seven elements of the space target operation at all moments in the first time period, and the seven elements comprise time, warp and weft height coordinates (x, y, z) and warp and weft height coordinate variables (dx, dy, dz).
In step S102, the preset frequency is set according to the definition required for performing the panoramic display on the space target trajectory simulation, and the higher the preset frequency is, the higher the definition of performing the panoramic display on the space target trajectory simulation is.
In the embodiment of the application, the first time period is divided into a plurality of second time periods in an equal amount according to the preset frequency.
In step S103, the plurality of first sub-timings are timings at both ends of the plurality of second periods.
In step S104, a second longitude and latitude height coordinate of the first sub-time is iteratively calculated based on a second derivative algorithm.
In the embodiment of the application, based on the second derivative algorithm, starting from the first sub-time in the first time period, the longitude and latitude height coordinates of all the first sub-times in the first time period are iteratively calculated by adopting the following algorithm:
{
Return x_r,y_r,z_r, dx_r,dy_r,dz_r }
wherein x represents an x-axis coordinate point of the space target in a three-dimensional space coordinate system; y represents a y-axis coordinate point of the space target in a three-dimensional space coordinate system; z represents a z-axis coordinate point of the space target in a three-dimensional space coordinate system; r represents the radius of the space target running track; a represents the central celestial (earth) gravitational potential; g represents a gravitational constant; m represents the central celestial (earth) mass; dx represents the running speed of the space target on the x axis in a three-dimensional space coordinate system; dy represents the running speed of the space target on the y axis in the three-dimensional space coordinate system; dz represents the running speed of the space target on the z-axis in a three-dimensional space coordinate system; dx (x)2Representing the first derivative of the x-axis of the calculated space target in a three-dimensional space coordinate system; dy2Representing the first derivative of the calculated y-axis of the space target in a three-dimensional space coordinate system; dz2Representing the first derivative of the calculated z-axis of the space target in a three-dimensional space coordinate system; x _ r represents the calculated second derivative of the x axis of the space target in the three-dimensional space coordinate system; y _ r represents the calculated second derivative of the y axis of the space target in the three-dimensional space coordinate system; z _ r represents the calculated second derivative of the z-axis of the space target in the three-dimensional space coordinate system; dx _ r represents the running speed of the space target calculated next time on the x axis in the three-dimensional space coordinate system; dy _ r represents the space target calculated next time in three dimensionsA running speed on the y-axis in a spatial coordinate system; dz _ r represents the running speed of the space target calculated next time on the z axis in the three-dimensional space coordinate system; t represents a time constant (i.e., a preset frequency).
Based on the algorithm, all the first sub-moments in the first time period are traversed, and a new first warp-weft height coordinate (x, y, z) corresponding to each first sub-moment is calculated.
Note that, the new first warp height coordinate (x, y, z) corresponding to each first sub-time calculated based on the above algorithm is used as an input value in the above algorithm when calculating the next first sub-time.
In step S105, mapping the second longitude and latitude high coordinate to the first operating ephemeris, and if the preset frequency is set to 12, generating a space target operating trajectory corresponding to the first time period by using an animation playing principle of 12 frames per second; if the preset frequency is set to be 24, generating a space target running track corresponding to the first time period by using an animation playing principle of 24 frames per second. Based on the method, the scene is refreshed frame by frame, and the short-term track simulation of the space target can be realized.
The above algorithm will be exemplified based on specific numerical values.
Based on the original Primitive API of the ceium open source framework, different times are calculated according to the TLE file, and then a position point, namely longitude and latitude high coordinates (x, y, z) of the space target is calculated every 10 seconds. Based on this, the number of times of calculating a single point of one space object is 8640, and the number of times of calculating ten thousand space objects is 8640 x 10000, so that the huge calculation amount can cause the browser to be stuck at the front end. Meanwhile, all the position points needing to be rendered are reserved in the memory, and the browser is stuck.
Based on the method for calculating the position point based on the second derivative algorithm, the memory can be released every minute, and the occupation proportion of the memory is one thousandth of that of the original interface. Therefore, the problem that the panoramic display effect of the whole space target is poor due to the fact that the phenomenon of blocking can occur when the operation scene of the whole space target is loaded can be solved.
In some embodiments, the method further comprises: step S106 to step S111.
Step S106: and selecting a plurality of fourth time periods in a third time period after the first time period.
Step S107: and acquiring a second running ephemeris of the space target in the preset coordinate system, wherein the second running ephemeris comprises a third longitude and latitude high coordinate of the space target at all the moments and a third longitude and latitude high coordinate variable of the space target at the adjacent moment in a third time period.
Step S108: and dividing the fourth time period according to the preset frequency to generate a plurality of fifth times.
Step S109: and determining a plurality of second sub-time moments according to a plurality of fifth time periods.
Step S110: and calculating a fourth longitude and latitude high coordinate of the second sub-moment according to the third longitude and latitude high coordinate and the third longitude and latitude coordinate variable based on a second derivative algorithm.
Step S111: and based on the error threshold, according to the third longitude and latitude high coordinate and the fourth longitude and latitude high coordinate in a plurality of third time periods, error correction is carried out on the long-term running track of the space target.
In the embodiment of the application, a plurality of fourth time periods are selected from the equal interval time periods for the convenience of calculation and comparison in order to correct the long-term running track of the space target based on the calculation error of the second derivative algorithm. The equal interval time period is the same time interval from the current time for acquiring the calculation time period to the next time for acquiring the calculation time period in a third time period after the first time period.
It should be noted that, in the process of correcting the long-term operation trajectory of the space target, if the data of the actual long-term operation trajectory of the space target (i.e., the coordinates of the real space target originally recorded) can be compared with the data of the calculated long-term operation trajectory of the space target (i.e., the coordinates of the space target calculated based on the algorithm), the selection of the plurality of fourth time periods may not be performed at equal intervals.
In other words, under the condition that the coordinates of the real space target originally recorded can be compared with the coordinates of the space target calculated based on the algorithm, in a third time period after the first time period, the time interval from the current time period for acquiring the calculation time period to the next time period for acquiring the calculation time period is different.
In this embodiment of the application, the method for calculating the fourth longitude and latitude height coordinate of the second sub-time may refer to the method for calculating the second longitude and latitude height coordinate of the first sub-time based on steps S101 to S104, which is not described herein again.
In the embodiment of the application, the error threshold value is set according to the accuracy of panoramic display of the space target track simulation. Typically, the error threshold is one meter.
In some embodiments, step S111 includes: step a 1-step A3.
Step A1: and comparing the third longitude and latitude height coordinate with the fourth longitude and latitude height coordinate at the same moment in a third time period to obtain a longitude and latitude height coordinate difference value.
Step A2: and judging whether the difference value of the longitude and latitude high coordinates exceeds the error threshold value.
Step A3: and if so, regenerating the space target running track according to the third longitude and latitude high coordinate, and realizing error correction on the space target long-term running track.
In the embodiment of the present application, it is determined whether the difference between the longitude and latitude coordinates exceeds an error threshold, that is, it is determined whether the difference between any one of the longitude, the latitude, and the altitude in the difference between the longitude and latitude coordinates exceeds the error threshold. And if the difference value of any item of longitude, latitude or altitude in the longitude and latitude high coordinate difference value exceeds an error threshold value, carrying out error correction on the long-term running track of the space target.
Specifically, when the difference value of any one of longitude, latitude and altitude in the longitude and latitude high coordinate difference value exceeds the error threshold value, the corresponding third longitude and latitude high coordinate at the moment is found, and then the space target running track is regenerated according to the third longitude and latitude high coordinate based on the mode of generating the space target running track in the steps from S101 to S105, so that the error correction of the space target long-term running track is realized.
In some embodiments, the method further comprises: step S112.
Step S112: and adjusting the running time parameter of the space target running track according to the preset speed.
In the embodiment of the application, according to the speed multiplying option selected during the running of the scene, the time parameter in the track simulation can be adjusted, and the display of the accelerated scene is realized, namely the track information of the whole satellite circle is viewed in a short time.
Specifically, as shown in table 1, when the original double-speed display is performed, the back end is refreshed once a minute, and the front end is refreshed once a minute at a preset frequency, that is, when the back end is refreshed once a minute, the frequency of refreshing once a minute at the front end is 24 frames per minute. When the display is carried out at 60 times of speed, the rear end is refreshed once in one minute, and the front end is refreshed once in one minute at a preset frequency, namely, when the rear end is refreshed once in one minute, the frequency of refreshing once in one minute at the front end is 24 frames per minute by 60 frames per minute.
Table 1: run time parameter comparison table for time fast forward (60 times speed)
In the embodiment of the application, in the speed doubling logic for performing panoramic display on space target trajectory simulation, only specific data packets of the extrapolation number at the back end are modified in the back end logic, and only the function parameter t is modified in the front end logic.
Specifically, in the back-end logic, one minute later, the next point is obtained as x, y, z, dx, dy, dz at the time found at the speed of time × multiple of the previous point. Based on this, in the front-end logic, the front-end refresh frequency is not changed, and still is 1/24 seconds for one refresh, and when the function is called, the parameter t is 1/24 × speed.
It should be noted that, for simplicity of description, the above-mentioned method embodiments are described as a series of acts or combination of acts, but those skilled in the art will recognize that the present application is not limited by the order of acts described, as some steps may occur in other orders or concurrently depending on the application. Further, those skilled in the art should also appreciate that the embodiments described in the specification are exemplary embodiments and that the acts and modules referred to are not necessarily required in this application.
The above is a description of method embodiments, and the embodiments of the present application are further described below by way of apparatus embodiments.
Fig. 2 shows a structure diagram of a device for realizing mass space target display based on a B/S architecture in an embodiment of the present application. Referring to fig. 2, the apparatus for implementing a mass space target exhibition based on a B/S architecture includes a first obtaining module 201, a first dividing module 202, a first determining module 203, a first calculating module 204, and a mapping module 205.
The first obtaining module 201 is configured to obtain a first running ephemeris of a space target in a preset coordinate system, where the first running ephemeris includes first longitude and latitude coordinates of the space target at all times and first longitude and latitude coordinate variables of the space target at adjacent times within a first time period.
The first dividing module 202 is configured to divide the first time period according to a preset frequency to generate a plurality of second time periods.
A first determining module 203, configured to determine a plurality of first sub-time instants according to a plurality of second time periods.
The first calculating module 204 is configured to calculate a second longitude and latitude coordinate of the first sub-moment according to the first longitude and latitude coordinate and the first longitude and latitude coordinate variable based on a second derivative algorithm.
The mapping module 205 is configured to map all the second longitude and latitude high coordinates into the first operation ephemeris, and generate a space target operation trajectory corresponding to the first time period.
In some embodiments, the apparatus for implementing a mass space target display based on a B/S architecture further includes a selecting module 206, a second obtaining module 207, a second dividing module 208, a second determining module 209, a second calculating module 210, and a comparing module 211.
A selecting module 206, configured to select a plurality of fourth time periods within a third time period after the first time period.
And a second obtaining module 207, configured to obtain a second running ephemeris of the space target in the preset coordinate system, where the second running ephemeris includes a third longitude and latitude high coordinate of the space target at all times and a third longitude and latitude high coordinate variable of the space target at an adjacent time in a third time period.
The second dividing module 208 is configured to divide the fourth time period according to the preset frequency to generate a plurality of fifth time periods.
A second determining module 209, configured to determine a plurality of second sub-time instants according to a plurality of the fifth time periods.
And the second calculating module 210 is configured to calculate a fourth longitude and latitude high coordinate of the second sub-moment according to the third longitude and latitude high coordinate and the third longitude and latitude high coordinate variable based on a second derivative algorithm.
And the comparison module 211 is configured to correct the error of the long-term operation trajectory of the space target according to the third longitude and latitude high coordinate and the fourth longitude and latitude high coordinate in the plurality of third time periods based on the error threshold.
In some embodiments, the comparison module includes a comparison unit, a determination unit, and a generation unit.
And the comparison unit is used for comparing the third longitude and latitude high coordinate with the fourth longitude and latitude high coordinate at the same moment in a third time period to obtain a longitude and latitude high coordinate difference value.
And the judging unit is used for judging whether the difference value of the longitude and latitude high coordinates exceeds the error threshold value.
And the generating unit is used for regenerating a space target running track according to the third longitude and latitude high coordinate if the third longitude and latitude high coordinate is true, so that error correction is carried out on the space target long-term running track.
In some embodiments, the apparatus for implementing mass space target exhibition based on B/S architecture further includes an adjustment module 212.
And the adjusting module 212 is configured to adjust an operation time parameter of the space target operation trajectory according to a preset speed.
It can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working process of the described module may refer to the corresponding process in the foregoing method embodiment, and is not described herein again.
Fig. 3 shows a schematic structural diagram of an electronic device suitable for implementing embodiments of the present application. As shown in fig. 3, the electronic device 300 shown in fig. 3 includes: a processor 301 and a memory 303. Wherein the processor 301 is coupled to the memory 303. Optionally, the electronic device 300 may further include a transceiver 304. It should be noted that the transceiver 304 is not limited to one in practical applications, and the structure of the electronic device 300 is not limited to the embodiment of the present application.
The Processor 301 may be a CPU (Central Processing Unit), a general-purpose Processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array) or other Programmable logic device, a transistor logic device, a hardware component, or any combination thereof. Which may implement or perform the various illustrative logical blocks, modules, and circuits described in connection with the disclosure. The processor 301 may also be a combination of computing functions, e.g., comprising one or more microprocessors, a combination of a DSP and a microprocessor, or the like.
The Memory 303 may be a ROM (Read Only Memory) or other type of static storage device that can store static information and instructions, a RAM (Random Access Memory) or other type of dynamic storage device that can store information and instructions, an EEPROM (Electrically Erasable Programmable Read Only Memory), a CD-ROM (Compact Disc Read Only Memory) or other optical Disc storage, optical Disc storage (including Compact Disc, laser Disc, optical Disc, digital versatile Disc, blu-ray Disc, etc.), a magnetic Disc storage medium or other magnetic storage device, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and that can be accessed by a computer, but is not limited to these.
The memory 303 is used for storing application program codes for executing the scheme of the application, and the processor 301 controls the execution. The processor 301 is configured to execute application program code stored in the memory 303 to implement the aspects illustrated in the foregoing method embodiments.
Among them, electronic devices include but are not limited to: mobile terminals such as mobile phones, notebook computers, digital broadcast receivers, PDAs (personal digital assistants), PADs (tablet computers), PMPs (portable multimedia players), in-vehicle terminals (e.g., car navigation terminals), and the like, and fixed terminals such as digital TVs, desktop computers, and the like. The electronic device shown in fig. 3 is only an example, and should not bring any limitation to the functions and the scope of use of the embodiments of the present application.
The present application provides a computer-readable storage medium, on which a computer program is stored, which, when running on a computer, enables the computer to execute the corresponding content in the foregoing method embodiments. Compared with the prior art, in the embodiment of the application, the first running ephemeris of the space target in the preset coordinate system comprising the first warp-weft high coordinate of the space target at all moments and the first warp-weft high coordinate variable of the space target at the adjacent moment in the first time period is obtained, and the first time period is divided according to the preset frequency to generate a plurality of second time periods; determining a first sub-moment according to a plurality of second time periods, and calculating a second longitude and latitude high coordinate of the first sub-moment according to the first longitude and latitude high coordinate and the first longitude and latitude high coordinate variable based on a second derivative algorithm; mapping all the second longitude and latitude high coordinates into a first operation ephemeris to generate a space target operation track corresponding to a first time period; in conclusion, when the operation track comprising a large number of space targets is displayed, the display scene can be more flow, the phenomenon of blocking is avoided, the problem that the effect of carrying out panoramic display on the whole space target is poor due to the fact that the phenomenon of blocking can occur when the operation scene of the whole space target is loaded can be solved, and the effect of improving the panoramic display effect on the whole space target is achieved.
It should be understood that, although the steps in the flowcharts of the figures are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and may be performed in other orders unless explicitly stated herein. Moreover, at least a portion of the steps in the flow chart of the figure may include multiple sub-steps or multiple stages, which are not necessarily performed at the same time, but may be performed at different times, which are not necessarily performed in sequence, but may be performed alternately or alternately with other steps or at least a portion of the sub-steps or stages of other steps.
The foregoing is only a partial embodiment of the present application, and it should be noted that, for those skilled in the art, several modifications and decorations can be made without departing from the principle of the present application, and these modifications and decorations should also be regarded as the protection scope of the present application.
Claims (10)
1. A method for realizing the display of mass space targets based on a B/S architecture is characterized in that,
acquiring a first running ephemeris of a space target in a preset coordinate system, wherein the first running ephemeris comprises first longitude and latitude coordinates of the space target at all moments and first longitude and latitude coordinate variables of the space target at adjacent moments in a first time period;
dividing the first time period according to a preset frequency to generate a plurality of second time periods;
determining a plurality of first sub-time moments according to a plurality of second time periods;
calculating a second longitude and latitude height coordinate of the first sub moment according to the first longitude and latitude height coordinate and the first longitude and latitude coordinate variable based on a second derivative algorithm;
mapping all the second longitude and latitude high coordinates into the first operating ephemeris to generate a space target operating track corresponding to the first time period;
and iteratively calculating the second longitude and latitude high coordinate by adopting the following algorithm:
wherein x represents an x-axis coordinate point of the space target in a three-dimensional space coordinate system; y represents a y-axis coordinate point of the space target in a three-dimensional space coordinate system; z represents a z-axis coordinate point of the space target in a three-dimensional space coordinate system; r represents the radius of the space target running track; a represents the central celestial body gravitational potential; g represents a gravitational constant; m represents the central celestial mass; dx represents the running speed of the space target on the x axis in a three-dimensional space coordinate system; dy represents the running speed of the space target on the y axis in the three-dimensional space coordinate system; dz represents the running speed of the space target on the z-axis in a three-dimensional space coordinate system; dx (x)2Representing the first derivative of the x-axis of the calculated space target in a three-dimensional space coordinate system; dy2Representing the first derivative of the calculated y-axis of the space target in a three-dimensional space coordinate system; dz2Representing the first derivative of the calculated z-axis of the space target in a three-dimensional space coordinate system; x _ r represents the calculated second derivative of the x axis of the space target in the three-dimensional space coordinate system; y _ r represents the calculated second derivative of the y axis of the space target in the three-dimensional space coordinate system; z _ r represents the calculated second derivative of the z-axis of the space target in the three-dimensional space coordinate system; dx _ r represents the running speed of the space target calculated next time on the x axis in the three-dimensional space coordinate system; dy _ r represents the running speed of the space target calculated next time on the y axis in the three-dimensional space coordinate system; dz _ r represents the space target calculated next timeA travel speed on the z-axis in a three-dimensional spatial coordinate system; t represents a time constant.
2. The method of claim 1, further comprising:
selecting a plurality of fourth time periods in a third time period after the first time period;
acquiring a second running ephemeris of the space target in the preset coordinate system, wherein the second running ephemeris comprises third longitude and latitude high coordinates of the space target at all moments and third longitude and latitude high coordinate variables of the space target at adjacent moments in a third time period;
dividing the fourth time period according to the preset frequency to generate a plurality of fifth time periods;
determining a plurality of second sub-time moments according to a plurality of fifth time periods;
calculating a fourth longitude and latitude coordinate of the second sub-moment according to the third longitude and latitude coordinate and the third longitude and latitude coordinate variable based on a second derivative algorithm;
and based on the error threshold, according to the third longitude and latitude high coordinate and the fourth longitude and latitude high coordinate in a plurality of third time periods, error correction is carried out on the long-term running track of the space target.
3. The method according to claim 2, wherein the error correction of the long-term running trajectory of the space target according to the third longitude and latitude coordinate and the fourth longitude and latitude coordinate in a plurality of third time periods based on the error threshold value comprises:
comparing the third longitude and latitude height coordinate and the fourth longitude and latitude height coordinate at the same moment in a third time period to obtain a longitude and latitude height coordinate difference value;
judging whether the difference value of the longitude and latitude high coordinates exceeds the error threshold value;
and if so, regenerating a space target running track according to the third longitude and latitude high coordinate, and realizing error correction on the long-term running track of the space target.
4. The method according to any one of claims 1 or 2, further comprising:
and adjusting the running time parameter of the space target running track according to the preset speed.
5. A device for realizing mass space target display based on a B/S framework is characterized by comprising:
the first acquisition module is used for acquiring a first operating ephemeris of a space target in a preset coordinate system, wherein the first operating ephemeris comprises first longitude and latitude coordinates of the space target at all moments and first longitude and latitude coordinate variables of the space target at adjacent moments in a first time period;
the first dividing module is used for dividing the first time period according to a preset frequency to generate a plurality of second time periods;
a first determining module, configured to determine a plurality of first sub-moments according to a plurality of the second time periods;
the first calculating module is used for calculating a second longitude and latitude high coordinate of the first sub moment according to the first longitude and latitude high coordinate and the first longitude and latitude high coordinate variable based on a second derivative algorithm;
the mapping module is used for mapping all the second longitude and latitude high coordinates into the first operating ephemeris to generate a space target operating track corresponding to the first time period;
wherein the first computing module further comprises:
and iteratively calculating the second longitude and latitude height coordinate by adopting the following algorithm:
wherein x represents an x-axis coordinate point of the space target in a three-dimensional space coordinate system(ii) a y represents a y-axis coordinate point of the space target in a three-dimensional space coordinate system; z represents a z-axis coordinate point of the space target in a three-dimensional space coordinate system; r represents the radius of the space target running track; a represents the central celestial body gravitational potential; g represents a gravitational constant; m represents the central celestial mass; dx represents the running speed of the space target on the x axis in a three-dimensional space coordinate system; dy represents the running speed of the space target on the y axis in the three-dimensional space coordinate system; dz represents the running speed of the space target on the z-axis in a three-dimensional space coordinate system; dx (x)2Representing the first derivative of the x-axis of the calculated space target in a three-dimensional space coordinate system; dy2Representing the first derivative of the calculated y-axis of the space target in a three-dimensional space coordinate system; dz2Representing the first derivative of the calculated z-axis of the space target in a three-dimensional space coordinate system; x _ r represents the calculated second derivative of the x axis of the space target in a three-dimensional space coordinate system; y _ r represents the calculated second derivative of the y axis of the space target in the three-dimensional space coordinate system; z _ r represents the calculated second derivative of the z-axis of the space target in the three-dimensional space coordinate system; dx _ r represents the running speed of the space target calculated next time on the x axis in the three-dimensional space coordinate system; dy _ r represents the running speed of the space target calculated next time on the y axis in the three-dimensional space coordinate system; dz _ r represents the running speed of the space target calculated next time on the z axis in the three-dimensional space coordinate system; t represents a time constant.
6. The apparatus of claim 5, further comprising:
the selection module is used for selecting a plurality of fourth time periods in a third time period after the first time period;
the second acquisition module is used for acquiring a second running ephemeris of the space target in the preset coordinate system, wherein the second running ephemeris comprises third longitude and latitude high coordinates of the space target at all moments and third longitude and latitude high coordinate variables of the space target at adjacent moments in a third time period;
the second dividing module is used for dividing the fourth time period according to the preset frequency to generate a plurality of fifth time periods;
a second determining module, configured to determine a plurality of second sub-moments according to a plurality of the fifth time periods;
the second calculation module is used for calculating a fourth longitude and latitude height coordinate of the second sub-moment according to the third longitude and latitude height coordinate and the third longitude and latitude height coordinate variable based on a second derivative algorithm;
and the comparison module is used for realizing error correction on the long-term running track of the space target based on the error threshold value according to the third longitude and latitude high coordinate and the fourth longitude and latitude high coordinate in a plurality of third time periods.
7. The apparatus of claim 6, wherein the comparison module comprises:
the comparison unit is used for comparing the third longitude and latitude height coordinate and the fourth longitude and latitude height coordinate at the same moment in a third time period to obtain a longitude and latitude height coordinate difference value;
the judging unit is used for judging whether the longitude and latitude high coordinate difference value exceeds the error threshold value;
and the generating unit is used for regenerating a space target running track according to the third longitude and latitude high coordinate if the third longitude and latitude high coordinate is true, so that error correction is carried out on the space target long-term running track.
8. The apparatus of any one of claims 5 or 6, further comprising:
and the adjusting module is used for adjusting the running time parameter of the space target running track according to the preset speed.
9. An electronic device comprising a memory and a processor, the memory having stored thereon a computer program, wherein the processor, when executing the computer program, implements the method of any of claims 1-4.
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 according to any one of claims 1 to 4.
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