CN110108281B - Space astronomical observation task calculation analysis system, method, medium and device - Google Patents
Space astronomical observation task calculation analysis system, method, medium and device Download PDFInfo
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- CN110108281B CN110108281B CN201910376298.9A CN201910376298A CN110108281B CN 110108281 B CN110108281 B CN 110108281B CN 201910376298 A CN201910376298 A CN 201910376298A CN 110108281 B CN110108281 B CN 110108281B
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Abstract
The invention relates to a space astronomical observation task calculation analysis system, which comprises: the system comprises an object management and parameter configuration service module, a vector geometry dynamic creation service module, a time window sequence dynamic creation service module and an object visibility calculation analysis service module. Vectorization abstraction and integrated design are carried out on the calculation and analysis process of the space astronomical observation task, universal calculation and analysis support services of vector geometry dynamic creation, time window sequence dynamic creation and data element dynamic management are realized, and universal support of the related problems of space astronomical observation and calculation is realized. The invention adopts a service-oriented design idea, and the space astronomical observation task calculation analysis system carries out service-oriented design, thereby ensuring that each calculation analysis service module can be reused, is loosely coupled, has definite interfaces, independently contains stateless and is based on open standards, and realizing the servitization of the calculation analysis process. The invention also relates to a space astronomical observation task calculation analysis method, a medium and equipment.
Description
Technical Field
The invention relates to the technical field of space astronomical observation, in particular to a space astronomical observation task calculation analysis system, method, medium and equipment.
Background
In the face of astronomy and basic physics challenges and opportunities such as dark substances, dark energy, celestial origin and evolution and the like, European and American countries successively provide a plurality of large-scale space-based and foundation-based sky-patrol items, and the flagship items selected at present comprise: the project of ground-based large-caliber all-day inspection telescope, which is the first-push project of national academy of sciences, Euclidean project of European Bureau, and space-based short-wave infrared multiband imaging and seamless spectrum inspection plan of the United states are expected to be put into operation in the early 2020.
Space astronomical observation (space astronomical observation) refers to astronomical observation performed from high altitude several tens of kilometers from the ground to space outside the earth's atmosphere. Spatial astronomical observations are the basis for fundamental problem studies driving astronomy and physics. However, no special system is available in the prior art for performing the computational analysis of the spatial astronomical observation task. Therefore, a special space astronomical observation task computational analysis system is needed to realize the space astronomical observation task computational analysis.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art and provides a system, a method, a medium and equipment for computing and analyzing a space astronomical observation task.
The technical scheme for solving the technical problems is as follows: a spatial astronomical observation task computational analysis system, comprising:
the object management and parameter configuration service module is used for creating scenes and configuring and managing object parameters in the scenes;
the vector geometry dynamic creation service module is used for performing vector geometry dynamic creation in the scene to obtain a space model of constraint calculation;
the data element dynamic management service module is used for maintaining and managing all calculation data elements of the vector geometric dynamic creation service module and providing data support for task calculation analysis;
the time window sequence dynamic creation service module is used for dynamically creating a time window sequence of a required type in the scene;
and the object visibility calculation and analysis service module is used for calculating a display observation visible window meeting constraint conditions according to the link and observation visibility among the objects in the scene, the time window sequence and the space model.
In order to achieve the above object, the present invention further provides a method for computing and analyzing a space astronomical observation task, comprising:
carrying out scene creation and configuration management of object parameters in the scene;
vector geometric dynamic creation is carried out in the scene to obtain a space model of constraint calculation;
dynamically creating a sequence of time windows of a desired type in the scene;
and calculating a display observation visible window meeting constraint conditions according to the link and observation visibility among the objects in the scene, the time window sequence and the space model.
The invention also provides a computer-readable storage medium, which comprises instructions, and when the instructions are run on a computer, the instructions cause the computer to execute the space astronomical observation task calculation analysis method.
The invention also provides computer equipment which comprises a memory, a processor and a computer program which is stored on the memory and can run on the processor, wherein the processor realizes the space astronomical observation task calculation analysis method when executing the program.
The invention has the beneficial effects that: based on the resource constraint condition of the space astronomical observation task in the actual in-orbit operation process, the calculation and analysis related functions of the space astronomical observation task are packaged into service units, mutual and external service provision is realized among the service units through defined interaction interfaces, the service units are integrated into a calculation and analysis tool box of the space astronomical observation task, the calculation and analysis tool box is used for realizing the related basic calculation function of the astronomical observation task carried out by spacecraft load equipment, the calculation and analysis process of the observation task is specifically subjected to vectorization abstraction and integrated design, the general calculation and analysis support services of vector geometry dynamic creation, time window sequence dynamic creation and data element dynamic management are realized, and the general support of the related problems of the space astronomical observation and calculation is realized. By adopting a service-oriented design idea, the space astronomical observation task calculation analysis system carries out service-oriented design, ensures that each calculation analysis service module can be reused, is loosely coupled, has definite interfaces, independently contains stateless and is based on open standards, and realizes calculation analysis process servitization.
Drawings
FIG. 1 is a block diagram of a spatial astronomical observation task computation analysis system according to an embodiment of the present invention;
fig. 2 is a flowchart of a method for computing and analyzing a space astronomical observation task according to an embodiment of the present invention.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
Fig. 1 is a block diagram of a spatial astronomical observation task computation analysis system according to an embodiment of the present invention. As shown in fig. 1, the system includes: the system comprises an object management and parameter configuration service module, a vector geometry dynamic creation service module, a time window sequence dynamic creation service module and an object visibility calculation analysis service module.
The object management and parameter configuration service module is used for creating scenes and configuring and managing object parameters in the scenes; the vector geometry dynamic creation service module is used for performing vector geometry dynamic creation in the scene to obtain a space model of constraint calculation; the time window sequence dynamic creation service module is used for dynamically creating a time window sequence of a required type in the scene; and the object visibility calculation and analysis service module is used for calculating a display observation visible window meeting constraint conditions according to the link and observation visibility among the objects in the scene, the time window sequence and the space model.
It should be noted that the spatial astronomical observation task computation and analysis system provided by the embodiment of the present invention supports, but is not limited to, task constraint computation and analysis models for common 7 astronomical observations, including a bright star avoidance time window computation model, a sun and moon stray light avoidance computation model, a geogas light influence computation model, a south atlantic ocean abnormal area SAA computation model, an earth occlusion computation model, a occultation time window computation model, and other celestial body avoidance time window computation models.
In the above embodiment, based on resource constraint conditions of the space astronomical observation task in the actual in-orbit operation process, the calculation and analysis related functions of the space astronomical observation task are packaged into service units, and mutual and external service provision is realized between the service units through defined interactive interfaces, the service units are integrated into a calculation and analysis toolbox of the space astronomical observation task, the calculation and analysis toolbox is used for realizing the related basic calculation function of the astronomical observation task performed by spacecraft load equipment, specifically, the calculation and analysis process of the observation task is subjected to vectorization abstraction and integrated design, the general calculation and analysis support services of vector geometry dynamic creation, time window sequence dynamic creation and data element dynamic management are realized, and the general support of the related problems of the space astronomical observation and calculation is realized. By adopting a service-oriented design idea, the space astronomical observation task calculation analysis system carries out service-oriented design, ensures that each calculation analysis service module can be reused, is loosely coupled, has definite interfaces, independently contains stateless and is based on open standards, and realizes calculation analysis process servitization.
Optionally, the object management and parameter configuration service module includes a scene creation management unit, a spacecraft configuration management unit, a ground station configuration management unit, a rocket configuration management unit, an observed load configuration management unit, and a ground target configuration management unit.
The scene creation management unit is used for creating a scene and setting scene parameters; the spacecraft configuration management unit is used for setting flight orbit parameters, attitude flight modes and contained observation loads of the spacecraft; the ground station configuration management unit is used for setting site coordinates, AER (azimuth angle, elevation angle and distance) observation conditions and contained measuring equipment of the ground station; the rocket configuration management unit is used for setting the flight trajectory parameters and the flight attitude of the rocket; the observation load configuration management unit is used for setting the installation position, the installation direction and the view field shape of the observation load; the ground target configuration management unit is used for describing the ground target and associating the ground target with the observation equipment of the relevant spacecraft in the scene when calculating the observation window of the spacecraft relative to the ground target.
It should be noted that, 1) scene creation and management: the scene is a group of model and object organization structure objects, one scene can comprise objects such as a spacecraft, a rocket, a ground station, an observation load, a ground target and the like, the objects in the scene can be managed through a graphic interaction interface, and the operation time period, the step length and the like of the scene are set.
2) Spacecraft configuration management: the flight orbit parameters of the spacecraft (spacecraft ephemeris for a period of event), attitude flight mode and the contained observed loads can be set through the graphical interface. The attitude flight mode can support modes such as three-axis stable ground alignment, yaw maneuvering, sidesway, inertial attitude, sun pointing and the like and fixed attitude in a user-defined coordinate system.
3) Ground station configuration management: the site coordinates of the ground station, the RAE observation conditions and the included measuring equipment can be set through a graphical interface.
4) Rocket configuration management: the flight trajectory parameters (spacecraft ephemeris for a period of event) and the flight attitude of the rocket can be set through the graphical interface.
5) And (3) observing load configuration management: each spacecraft can contain a plurality of observation loads, and parameters such as the installation position, the installation direction and the shape of a visual field of the observation loads can be set through a graphical interface. The observation load view field can support the types of simple cone, rectangle, complex cone, push-broom and the like.
6) Ground target configuration management: the ground targets comprise point targets and area targets, the point targets can set the geographic coordinates of the target points, the area targets are described by a group of boundary points, and when the observation windows of the spacecraft relative to the ground targets are calculated, each ground target needs to be associated with observation equipment of a certain spacecraft in a scene.
In the above embodiment, the parameter settings of the mission scenario and the object (including the spacecraft, the ground station, the rocket, the observed load, the ground target, and the like) are made independent. Firstly, setting and changing task scenes and object parameters through a visual operation interface; secondly, the calculation analysis of a new task can be conveniently carried out by changing the parameters of a task scene and an object according to the change of the task calculation requirement; finally, the change of the parameters of the task scene and the object can be independently stored as a task scene file, so that the use and inheritance multiplexing of subsequent tasks are facilitated.
Optionally, the vector geometry dynamic creation service module includes: the device comprises a basic built-in coordinate system unit, a space point dynamic creating unit, a vector dynamic creating unit, a plane dynamic creating unit, a coordinate frame dynamic creating unit, a coordinate system dynamic creating unit and an angle dynamic creating unit.
The basic built-in coordinate system unit is used for defining a system built-in basic coordinate system, and the system built-in basic coordinate system consists of a coordinate origin and a coordinate frame;
the space point dynamic creating unit is used for dynamically creating space points; the space points comprise space entity object points and abstract calculation points; the space entity object point refers to a space object centroid or a geometrically fixed point; the abstract calculation points refer to virtual abstraction points calculated according to geometric relations;
the vector dynamic creating unit is used for dynamically creating a vector according to the existing space target and the coordinate system; or creating a vector according to the existing coordinate system and the fixed direction under the coordinate system; or creating a vector from a vector cross product; or creating a vector according to the intersection of the two surfaces; or creating a vector from a projection of the vector on a plane;
the plane dynamic creating unit is used for creating a plane according to the existing coordinate system and the vector, and the plane direction points to the normal vector direction of the plane;
the coordinate frame dynamic creating unit is used for creating a coordinate frame according to the existing coordinate frame and the vector;
the coordinate system dynamic creating unit is used for creating a coordinate system according to the existing space entity object point and a coordinate frame, wherein the gravity center or the center of the space entity object point is taken as a coordinate origin;
the angle dynamic creating unit is used for creating angles according to the vector and plane dynamic, and the angle dynamic creating unit comprises an angle creating unit used for creating angles according to the included angle of two existing vectors; or creating an angle according to the included angle of the two planes; or create an angle from the vector and the planar angle.
Note that, 1) the basic built-in coordinate system unit: the system built-in basic coordinate system such as EqJ2000, WGS84, TOD, BodyFixed, Topocentric, VVLH and the like is defined, and the coordinate system consists of a coordinate origin and a coordinate frame.
2) Dynamic creation unit of spatial points: the space points comprise space entity object points and abstract calculation points, wherein the entity object points refer to the mass center of space targets such as natural celestial bodies, spacecrafts, loads, ground stations and the like or a fixed point on geometry; the abstract calculation points are virtual abstract points calculated according to geometric relations such as vectors and planes.
3) The vector dynamic creating unit can dynamically create a new vector according to the existing space target, the coordinate system and the like; creating a vector according to an existing coordinate system (which can be a basic built-in coordinate system or a user self-created coordinate system) and a fixed direction under the coordinate system; creating a vector according to vector cross multiplication; creating a vector according to the intersection of the two surfaces; vectors are created from the projection of the vectors onto a plane.
4) A plane dynamic creation unit: a new plane is created by means of an existing coordinate system, vectors, etc., which plane has a direction pointing in its normal vector direction.
5) A coordinate frame dynamic creation unit: a new coordinate frame is created from an existing coordinate frame, vector, etc.
6) A coordinate system dynamic creation unit: and creating a new coordinate system according to the existing space entity object point and the coordinate frame, wherein the gravity center or the center of the space entity object point is used as the coordinate origin.
7) An angle dynamic creation unit: creating angles according to the dynamics of vectors, planes and the like, wherein the angles comprise 1) creating angles through the included angle of two existing vectors; 2) creating an angle through the included angle of the two planes; 3) the angle is created by the vector and the plane angle.
In the above embodiment, the vector geometry dynamic creation service module is a fully parameterized and customizable space vector relationship calculation and analysis support tool, and can support calculation and analysis of parameters such as angles, distances, positions and the like between almost all space vector objects by dynamically creating some spatial vector objects such as dynamics of a basic built-in coordinate system and spatial abstract computation points, vector dynamics, coordinate frame dynamics, coordinate system dynamics and angles and the like, and has strong flexibility, universality and expansibility.
Optionally, the data element dynamic management service module provides maintenance and management of all the calculation data elements of the vector geometry dynamic creation service module, and provides data support for task calculation analysis. The data elements comprise built-in data elements and user-defined data elements; the built-in data elements include: spacecraft orbit data, spacecraft attitude data, coordinate system rotation Euler angle/four-element/transfer matrix, solar angle data, spacecraft tracking data of a survey station to a spacecraft, spacecraft illumination area time window data and observation target coverage window data of load equipment; the user-defined data comprises: user-defined angle data, user-defined vector data, user-defined scalar data, and user-defined time window data.
Optionally, the time window sequence dynamic creation service module includes: a base type time window sequence creating unit, a scalar type time window sequence creating unit, and a conditional type time window sequence creating unit.
The basic type time window sequence creating unit is used for creating a time window sequence of a basic built-in time window type; the scalar type time window sequence creating unit is used for creating a scalar type time window sequence; the condition type time window sequence creating unit is used for creating a condition type time window sequence.
It should be noted that the time window sequence of the basic built-in time window type may include: defining a time window sequence of an illumination area and a ground shadow area of a spacecraft; the load equipment covers a time window sequence to the view field of the observation target; a sequence of observable time windows of the ground station to the spacecraft. Scalar type time window sequence is created to create a certain scalar type from spatial objects, vectors, angles, etc. objects. The conditional type time window sequence is created to describe whether a certain scalar defined satisfies a certain condition, such as creating a sequence type of illumination region time window that specifies an occlusion source.
In the above embodiment, the time window sequence dynamic creation service module supports basic built-in time window sequence types (defining time window sequences of an illumination area and a ground shadow area of a spacecraft; a field of view coverage time window sequence of a load device to an observation target; an observable time window sequence of a ground station to a spacecraft), dynamic creation of scalar types (creating a certain scalar type according to objects such as a space object, a vector, an angle and the like), dynamic creation of condition types (describing whether a certain defined scalar meets a certain condition), and creation of time window sequence types, which can support time window calculation analysis of all space observation tasks, and the design has very high versatility and flexibility.
Optionally, the object visibility calculation analysis service module includes: and a visibility calculation and analysis unit and a user-defined time window calculation and analysis unit are arranged in the mobile terminal.
The built-in visibility calculation and analysis unit is used for calculating a tracking visible window of the ground station relative to the spacecraft, an observation time window of the spacecraft load relative to the ground target under a preset constraint condition, an observation time window calculation of the spacecraft load relative to a preset sky area under the preset constraint condition and an observation time window built in the system;
and the user-defined time window calculation and analysis unit is used for calculating the corresponding observation time window in the preset time period according to the user-defined time window sequence type.
It should be noted that (1) the built-in visibility calculation analysis includes:
1) ground station tracking visible window with respect to spacecraft
And calculating and displaying an observation visible window of a certain ground station about a certain spacecraft under the condition that the ground station AER constraint condition is met for a period of time, wherein the observation visible window comprises the station entering time, AER (azimuth angle, elevation angle and distance), the highest elevation angle time, AER (azimuth angle, elevation angle and distance), the station leaving time, AER (azimuth angle, elevation angle and distance) and the duration information of the tracking arc.
2) The spacecraft load is observed in an observation time window of the ground target under the constraint conditions of SAA, illumination and the like for a period of time, and the observation time window comprises the starting time, the ending time and the observation duration of each observation fox section.
3) The observation time window of the spacecraft load in a certain sky area in a period of time under the constraint conditions of bright star, light interference, shielding and the like comprises the starting time, the ending time and the observation duration of each observation fox section.
4) And calculating a time window built in the system, and calculating a corresponding time window in a certain period of time according to other time window sequence types built in the system (a spacecraft illumination area, a ground shadow area, an illumination area at a certain point on the ground and the like). Including the start time, end time, and duration of each window segment that satisfies the condition.
(2) User-defined time window computational analysis
The user-defined time window calculation analysis calculates the corresponding time window in a certain period of time according to the user-defined time window sequence type (including various constraint conditions). Including the start time, end time, and duration of each window segment that satisfies the condition.
Optionally, the spatial astronomical observation task computation and analysis system further comprises a data element computation and display service module for customizing the display mode, the data elements, the output and display attributes, and computing and displaying the selected data elements.
Specifically, the selected data elements are calculated and displayed in a data list form according to a user-defined display mode. The data elements comprise built-in spacecraft orbit parameters, attitude parameters, solar angles and the like, and user-defined angle parameters and scalar parameters of each object, and the calculation results can be displayed in a curve and/or report mode. When the report is displayed, a user can calculate the content, the display sequence and the display format of the display data according to the self-defined report display template, and the display template can be created and stored. When the graph is displayed, a user can calculate and display data content according to a user-defined graph display template, the abscissa is time, the ordinate is data content to be displayed, a plurality of parameters can be displayed in one graph, the parameters are distinguished by different colors, and the color corresponding to each parameter is identified.
In the above embodiment, the data element calculation and display service module may provide two-dimensional, three-dimensional, report form, curve chart and other visual displays of the calculation result for the calculation and analysis of the spatial astronomical observation task, so that a system user can visually see and understand the calculation result.
The space astronomical observation task calculation and analysis system provided by the embodiment of the invention provides a human-computer interaction interface, performs environment configuration management, creation management of various vectors, coordinate frames, coordinate systems, angles, scalars, conditions, time sequences and other objects, creation management of report and graph calculation display templates, and report and graph curve display of calculation results.
The space astronomical observation task calculation analysis system provided by the embodiment of the invention is described in detail above in conjunction with fig. 1. The following describes in detail the spatial astronomical observation task computation analysis method provided by the embodiment of the present invention with reference to fig. 2.
As shown in fig. 2, the method for computing and analyzing space astronomical observation task includes:
carrying out scene creation and configuration management of object parameters in the scene;
vector geometric dynamic creation is carried out in the scene to obtain a space model of constraint calculation;
dynamically creating a sequence of time windows of a desired type in the scene;
and calculating a display observation visible window meeting constraint conditions according to the link and observation visibility among the objects in the scene, the time window sequence and the space model.
The embodiment of the invention also provides a computer-readable storage medium, which comprises instructions, and when the instructions are run on a computer, the computer is enabled to execute the space astronomical observation task calculation analysis method.
The embodiment of the invention also provides computer equipment which comprises a memory, a processor and a computer program which is stored on the memory and can run on the processor, wherein the processor realizes the space astronomical observation task calculation analysis method when executing the program.
The space astronomical observation task calculation analysis system provided by the embodiment of the invention provides the functions of object management and configuration service, vector geometry dynamic creation, data element dynamic management, time window sequence dynamic management, object visibility calculation analysis considering various constraint conditions and the like, the calculation process is flexible, and the constraint conditions can be dynamically combined and set.
In the several embodiments provided in the present application, it should be understood that the disclosed apparatus and method may be implemented in other ways. For example, the above-described apparatus embodiments are merely illustrative, and for example, a division of a unit is merely a logical division, and an actual implementation may have another division, for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed.
Units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment of the present invention.
In addition, functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit. The integrated unit can be realized in a form of hardware, and can also be realized in a form of a software functional unit.
The integrated unit, if implemented in the form of a software functional unit 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 invention essentially or partially contributes to the prior art, or all or part of the technical solution can 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 invention. 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.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (9)
1. A system for computing and analyzing a spatial astronomical observation task, comprising:
the object management and parameter configuration service module is used for creating scenes and configuring and managing object parameters in the scenes;
the vector geometry dynamic creation service module is used for performing vector geometry dynamic creation in the scene to obtain a space model of constraint calculation;
the vector geometry dynamic creation service module comprises:
the basic built-in coordinate system unit is used for defining a system built-in basic coordinate system, and the system built-in basic coordinate system consists of a coordinate origin and a coordinate frame;
a space point dynamic creating unit for dynamically creating space points; the space points comprise space entity object points and abstract calculation points; the space entity object point refers to a space object centroid or a geometrically fixed point; the abstract calculation points refer to virtual abstraction points calculated according to geometric relations;
the vector dynamic creating unit is used for dynamically creating vectors according to the existing space target and the coordinate system; or creating a vector according to the existing coordinate system and the fixed direction under the coordinate system; or creating a vector from a vector cross product; or creating a vector according to the intersection of the two surfaces; or creating a vector from a projection of the vector on a plane;
the plane dynamic creating unit is used for creating a plane according to the existing coordinate system and the vector, and the plane direction points to the normal vector direction of the plane;
the coordinate frame dynamic creating unit is used for creating a coordinate frame according to the existing coordinate frame and the vector;
the coordinate system dynamic creating unit is used for creating a coordinate system according to the existing space entity object points and a coordinate frame, wherein the gravity center or the center of the space entity object points is taken as a coordinate origin;
the angle dynamic establishing unit is used for dynamically establishing an angle according to the vector and the plane, and comprises the step of establishing the angle according to the included angle of two existing vectors; or creating an angle according to the included angle of the two planes; or creating an angle according to the vector and the plane included angle;
the data element dynamic management service module is used for maintaining and managing all calculation data elements of the vector geometric dynamic creation service module and providing data support for task calculation analysis;
the time window sequence dynamic creation service module is used for dynamically creating a time window sequence of a required type in the scene;
and the object visibility calculation and analysis service module is used for calculating a display observation visible window meeting constraint conditions according to the link and observation visibility among the objects in the scene, the time window sequence and the space model.
2. The system of claim 1, wherein the object management and parameter configuration service module comprises:
the scene creating management unit is used for creating a scene and setting scene parameters;
the spacecraft configuration management unit is used for setting flight orbit parameters, attitude flight modes and contained observation loads of the spacecraft;
the ground station configuration management unit is used for setting the site coordinates, AER observation conditions and included measuring equipment of the ground station;
the rocket configuration management unit is used for setting the flight trajectory parameters and the flight attitude of the rocket;
an observation load configuration management unit for setting an installation position, an installation direction, and a view field shape of an observation load;
and the ground target configuration management unit is used for describing the ground target and associating the ground target with the observation equipment of the relevant spacecraft in the scene when calculating the observation window of the spacecraft relative to the ground target.
3. The system of claim 1, wherein the data elements comprise a built-in data element and a user-defined data element; the built-in data elements include: spacecraft orbit data, spacecraft attitude data, coordinate system rotation Euler angle/four-element/transfer matrix, solar angle data, spacecraft tracking data of a survey station to a spacecraft, spacecraft illumination area time window data and observation target coverage window data of load equipment; the user-defined data comprises: user-defined angle data, user-defined vector data, user-defined scalar data, and user-defined time window data.
4. The system of claim 1, wherein the time window sequence dynamic creation service module comprises:
the basic type time window sequence creating unit is used for creating a time window sequence of a basic built-in time window type;
a scalar type time window sequence creating unit for creating a scalar type time window sequence;
and the condition type time window sequence creating unit is used for creating the condition type time window sequence.
5. The system of claim 1, wherein the object visibility computation analysis service module comprises:
the built-in visibility calculation and analysis unit is used for calculating a tracking visible window of the ground station relative to the spacecraft, an observation time window of the spacecraft load relative to the ground target under a preset constraint condition, an observation time window calculation of the spacecraft load relative to a preset sky area under the preset constraint condition and an observation time window built in the system;
and the user-defined time window calculation and analysis unit is used for calculating the corresponding observation time window in the preset time period according to the user-defined time window sequence type.
6. The system of any one of claims 1 to 5, further comprising a data element calculation and display service module for defining display modes, data elements, output and display attributes, and calculating and displaying selected data elements.
7. A method for computational analysis of a spatial astronomical observation task, implemented by the system for computational analysis of a spatial astronomical observation task according to any one of claims 1 to 6, comprising:
carrying out scene creation and configuration management of object parameters in the scene;
vector geometric dynamic creation is carried out in the scene to obtain a space model of constraint calculation;
the vector geometric dynamic creation in the scene to obtain a space model of constraint calculation includes:
defining a system built-in basic coordinate system, wherein the system built-in basic coordinate system consists of a coordinate origin and a coordinate frame;
dynamically creating space points; the space points comprise space entity object points and abstract calculation points; the space entity object point refers to a space object centroid or a geometrically fixed point; the abstract calculation points refer to virtual abstraction points calculated according to geometric relations;
dynamically creating a vector according to the existing space target and a coordinate system; or creating a vector according to the existing coordinate system and the fixed direction under the coordinate system; or creating a vector from a vector cross product; or creating a vector according to the intersection of the two surfaces; or creating a vector from a projection of the vector on a plane;
creating a plane according to the existing coordinate system and the vector, wherein the direction of the plane points to the normal vector direction of the plane;
creating a coordinate frame according to the existing coordinate frame and the vector;
establishing a coordinate system according to the existing space entity object point and a coordinate frame, wherein the gravity center or the center of the space entity object point is taken as a coordinate origin;
dynamically creating an angle according to the vector and the plane, wherein the angle is created according to the included angle of the two existing vectors; or creating an angle according to the included angle of the two planes; or creating an angle according to the vector and the plane included angle;
dynamically creating a sequence of time windows of a desired type in the scene;
and calculating a display observation visible window meeting constraint conditions according to the link and observation visibility among the objects in the scene, the time window sequence and the space model.
8. A computer-readable storage medium comprising instructions that, when executed on a computer, cause the computer to perform the method for spatial astronomical observation task computational analysis of claim 7.
9. A computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor implements the method for spatial astronomical observation task computational analysis as claimed in claim 7 when the program is executed by the processor.
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| CN201910376298.9A CN110108281B (en) | 2019-05-07 | 2019-05-07 | Space astronomical observation task calculation analysis system, method, medium and device |
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