A method for displaying the on-orbit operation status of a spacecraft

Abstract

The present invention provides a method for displaying the on-orbit operation status of a spacecraft, and relates to the field of spacecraft simulation computing technology. The method includes: parsing an environment file, storing the parsed data information in a memory structure, wherein the data information includes one or more of the spacecraft quaternion, six orbital numbers, atomic oxygen density, incoming flow direction, illumination direction, and longitude and latitude; creating a playback control component, and using the playback control component to realize the display of the windward side, sun-exposed side, and / or running track of the spacecraft during on-orbit operation, wherein the playback control component sets the start and end time range of the playback control component according to the time of the original data in the memory structure to realize playback control of the displayed image. Compared with the prior art, the present invention can achieve the purpose of intuitively displaying the windward side, sun-exposed side, and running track of the spacecraft during on-orbit operation, and the method is simple and the display is accurate.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft simulation computing technology, and in particular to a method for displaying the on-orbit operation status of a spacecraft. Background Art

[0002] The erosion / undercutting of protective coating materials on the surface of spacecraft greatly affects the length of its actual service life, and the erosion / undercutting phenomenon mainly comes from the continuous exposure of the outer surface of the spacecraft to the atomic oxygen environment and ultraviolet radiation. The size of the atomic oxygen / ultraviolet radiation flux and the choice of coating materials determine the strength of the erosion / undercutting effect. Experimental research to select the optimal surface coating material is time-consuming and expensive, and is not suitable for material selection. This requires the use of simulation software to calculate the atomic oxygen / ultraviolet flux at various locations on the surface of the spacecraft according to the flight environment parameters, and use the flux to simulate the comprehensive effects of atomic oxygen / ultraviolet radiation of various materials and the erosion / undercutting effect. However, in the prior art, various simulation software does not take into account the different orbits, motion states, and attitudes of the solar wing of the spacecraft when calculating the atomic oxygen erosion / undercutting effect, and cannot intuitively display the operating status of the spacecraft, affecting the simulation effect. Summary of the invention

[0003] The problem that the present invention solves is that in the prior art, various simulation software do not take into account the different orbits, motion states and postures of the spacecraft and the like when calculating the atomic oxygen denudation / erosion effects, and are unable to intuitively display the operating status of the spacecraft, thus affecting at least one aspect of the simulation effect.

[0004] In order to solve the above problems, the present invention provides a method for displaying the on-orbit operation status of a spacecraft, comprising the following steps:

[0005] Step S1, parsing the environment file, and storing the parsed data information in a memory structure, wherein the data information includes one or more of the spacecraft quaternion, six orbital numbers, atomic oxygen density, incoming flow direction, illumination direction, and longitude and latitude;

[0006] Step S2, create a playback control component, and use the playback control component to realize the display of the windward side, the sunlit side and / or the running track of the spacecraft during its on-orbit operation, wherein the playback control component sets the start and end time range of the playback control component according to the time of the original data in the memory structure to realize the playback control of the displayed image.

[0007] Optionally, in step S2, the playback control of the displayed image includes playback control of the previous frame, the next frame, the first frame and the last frame.

[0008] Optionally, using the playback control component to realize the display of the windward side, the sunlit side and the operating track of the spacecraft during its in-orbit operation includes: using the playback control component to realize the display of the windward side, the sunlit side, the two-dimensional operating track surface and / or the three-dimensional operating track of the spacecraft during its in-orbit operation.

[0009] Optionally, in step S2, the using the playback control component to realize the display of the three-dimensional orbit of the spacecraft during on-orbit operation includes:

[0010] Step S201, using parameter settings to set the track display format;

[0011] Step S202, obtaining a model file, and adding the model file to the scene to represent the position of the spacecraft at different orbital points;

[0012] Step S203, information of the initial trajectory line, marking the coordinates of two points on the trajectory line, setting the rotation matrix, the color of the trajectory line and the width of the trajectory line;

[0013] Step S204, using a timer to send an orbit point update signal, and using the orbit point update signal to display the three-dimensional orbit of the spacecraft during its on-orbit operation.

[0014] Optionally, in step S201, the orbit display form includes a ground-fixed system trajectory form or an earth-fixed coordinate system trajectory form.

[0015] Optionally, when the orbit display form is the orbit form of the ground-fixed system, in step S204, the use of the orbit point update signal to complete the display of the three-dimensional orbit of the spacecraft during its in-orbit operation includes: after receiving the orbit point update signal data, assigning the longitude and latitude information to the rotating vehicle object so that it rotates around the y-axis and z-axis, assigning the obtained rotated matrix data to the vehicle object, and setting the coordinate position of the vehicle object, adding the coordinate position information of the vehicle object to the line structure data, completing the trajectory update, so as to complete the display of the three-dimensional orbit of the spacecraft during its in-orbit operation.

[0016] Optionally, in step S2, the using the playback control component to realize the display of the two-dimensional orbit of the spacecraft during on-orbit operation includes:

[0017] Step S205, using the map file to complete the drawing of the map;

[0018] Step S206, draw a latitude and longitude table and mark the latitude and longitude with labels;

[0019] Step S207, when the number of track points reaches 2 or more, data drawing begins, and the previous track point and the current track point are connected into a line using a preset function;

[0020] Step S208, obtaining the total number of orbital points that need to be drawn in real time, and looping according to step S207, completing the drawing of multiple orbital points to connect them into a trajectory line, so as to realize the display of the two-dimensional orbit of the spacecraft during its on-orbit operation.

[0021] Optionally, in step S2, the using of the playback control component to realize the display of the windward side and the sunlit side of the spacecraft during on-orbit operation includes:

[0022] Step S209, obtaining the current time step value and the windward exposure display mark to determine the designated windward result file or the exposure result file, parsing the designated windward result file or the exposure result file into the memory, and storing it in the form of an array;

[0023] Step S210, reading the grid file of the specified time step to store data in the specified data type, adding the result data in the windward result file or the sun exposure result file as an array to the specified data type object for identifying column data to generate unstructured grid data;

[0024] Step S211, completing the windward side display according to the incoming flow direction, and completing the sunlit side display according to the illumination direction.

[0025] Optionally, in step S211, the windward side display is completed according to the incoming flow direction, and the sunlit side display is completed according to the illumination direction, including: calculating the arrow direction and length of the incoming flow direction or the illumination direction, submitting the arrow data and the data object of the specified data type to the three-dimensional engine to complete the rendering work.

[0026] Optionally, in step S210, the specified data type is a dataset type.

[0027] The advantage of the method for displaying the on-orbit operation status of a spacecraft described in the present invention over the prior art is that the present invention utilizes simulation to simulate materials by changing space environment parameters, thereby achieving the purpose of intuitively displaying the windward side, sun-exposed side and operating orbit of the spacecraft during its on-orbit operation. It has obvious advantages and broad application prospects in technical applications such as promotion, teaching, demonstration and optimization selection of spacecraft surface coating materials for spacecraft simulation software, and makes it possible to directly use efficient Monte Carlo simulation methods based on technologies such as multi-core parallelism and data pruning, thereby improving the accuracy of atomic oxygen / ultraviolet radiation flux and its distribution on the spacecraft surface, which is of great significance. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a flow chart of a method for displaying the on-orbit operation status of a spacecraft in an embodiment of the present invention;

[0029] Figure 2This is a schematic diagram of the display result of the windward side of a spacecraft in orbit according to an embodiment of the present invention;

[0030] Figure 3 This is a schematic diagram of the display result of the sun-exposed surface of a spacecraft during on-orbit operation according to an embodiment of the present invention;

[0031] Figure 4 It is a schematic diagram of the display result of the three-dimensional orbit of the spacecraft during on-orbit operation in an embodiment of the present invention. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present application will be described clearly and in detail below with reference to the accompanying drawings.

[0033] In the description of the embodiments of the present application, the description of the term "some embodiments" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same implementation or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0034] It should also be noted that in the description of the embodiments of the present application, the term "include" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article, or terminal device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article, or terminal device. In the absence of further restrictions, the elements defined by the sentence "include..." do not exclude the existence of other identical elements in the process, method, article, or terminal device including the elements.

[0035] like Figure 1 As shown, an embodiment of the present invention provides a method for displaying the on-orbit operation status of a spacecraft, comprising the following steps:

[0036] Step S1, parsing the environment file, and storing the parsed data information in a memory structure, wherein the data information includes one or more of the spacecraft quaternion, six orbital numbers, atomic oxygen density, incoming flow direction, illumination direction, and longitude and latitude;

[0037] Step S2, create a playback control component, and use the playback control component to realize the display of the windward side, the sunlit side and / or the running track of the spacecraft during its on-orbit operation, wherein the playback control component sets the start and end time range of the playback control component according to the time of the original data in the memory structure to realize the playback control of the displayed image.

[0038] It should be noted that the memory structure in this embodiment is QList <posdata>postdata.

[0039] In some specific embodiments, in step S2, the playback control of the displayed image picture includes playback control of the previous frame, the next frame, the first frame and the last frame, thereby being able to fully control the displayed image picture.

[0040] In some embodiments, the use of the playback control component to realize the display of the windward side, the sunlit side and the operating track of the spacecraft during its in-orbit operation includes: using the playback control component to realize the display of the windward side, the sunlit side, the two-dimensional operating track surface and / or the three-dimensional operating track of the spacecraft during its in-orbit operation.

[0041] In a specific example, the start and end time ranges of the playback control component are set according to the time of postdata, and the playback control of the previous frame, next frame, first frame, and last frame is realized. When the play button is clicked, a signal is sent to drive the display of the windward side, the sun-receiving side, the two-dimensional orbital surface, and / or the three-dimensional orbital surface of the spacecraft in orbit. Thus, the control is convenient and accurate.

[0042] Optionally, in step S2, the using the playback control component to realize the display of the three-dimensional orbit of the spacecraft during on-orbit operation includes:

[0043] Step S201, using parameter settings to set the track display format;

[0044] Step S202, obtaining a model file, and adding the model file to the scene to represent the position of the spacecraft at different orbital points;

[0045] Step S203, information of the initial trajectory line, marking the coordinates of two points on the trajectory line, setting the rotation matrix, the color of the trajectory line and the width of the trajectory line;

[0046] Step S204, using a timer to send an orbit point update signal, and using the orbit point update signal to display the three-dimensional orbit of the spacecraft during its on-orbit operation.

[0047] As a result, the three-dimensional running track display is more intuitive and easier to observe.

[0048] In some embodiments, in step S201, the orbit display form includes a ground-fixed system trajectory form or an earth-fixed coordinate system trajectory form.

[0049] Optionally, when the orbit display form is a ground-fixed system trajectory form, in step S204, the use of the orbit point update signal to complete the display of the three-dimensional orbit of the spacecraft during its in-orbit operation includes: after receiving the orbit point update signal data, assigning the longitude and latitude information to the rotating vehicle object so that it rotates around the y-axis and z-axis, assigning the obtained rotated matrix data to the vehicle object, and setting the coordinate position of the vehicle object, adding the coordinate position information of the vehicle object to the line structure data, completing the update of the ground-fixed system trajectory, so as to complete the display of the three-dimensional orbit of the spacecraft during its in-orbit operation.

[0050] In some embodiments, in step S2, the using of the playback control component to realize the display of the two-dimensional orbit of the spacecraft during on-orbit operation includes:

[0051] Step S205, using the map file to complete the drawing of the map on the canvas;

[0052] Step S206, draw a latitude and longitude table and mark the latitude and longitude with labels;

[0053] Step S207, when the number of track points reaches 2 or more, data drawing begins, and the previous track point and the current track point are connected into a line using a preset function;

[0054] Step S208, obtaining the total number of orbital points that need to be drawn in real time, and looping according to step S207, completing the drawing of multiple orbital points to connect them into a trajectory line, so as to realize the display of the two-dimensional orbit of the spacecraft during its on-orbit operation.

[0055] In some specific embodiments, step S206, drawing a latitude and longitude table and marking the latitude and longitude with labels, includes: determining 12 grids on the x-axis, with a value range of (-180, 180), determining 12 grids on the y-axis, with a value range of (-90, 90); drawing straight lines of four borders according to the size of the window, drawing the x-axis scale with a line drawing function according to the width of the window and the number of grids; drawing the y-axis scale with a line drawing function according to the height of the window and the number of grids, and drawing labels at the designated scales for marking the latitude and longitude. The method is simple and the drawing is accurate.

[0056] In some specific embodiments, in step S207, a preset function is used to connect the previous track point and the current track point into a line, including: establishing variables to save the longitude and latitude of the previous track point and the longitude and latitude of the current track point, converting the longitude and latitude values ​​into coordinate values ​​of the actual point on the window through a conversion function, and calling the drawline function to connect the previous track point and the current track point into a line.

[0057] Therefore, the two-dimensional running track display is more intuitive, and the method is simple and easy to operate.

[0058] Optionally, in step S2, the using of the playback control component to realize the display of the windward side and the sunlit side of the spacecraft during on-orbit operation includes:

[0059] Step S209, obtaining the current time step value and the windward exposure display mark to determine the designated windward result file or the exposure result file, parsing the designated windward result file or the exposure result file into the memory, and storing it in the form of an array;

[0060] Step S210, reading the grid file of the specified time step to store data in the specified data type, adding the result data in the windward result file or the sun exposure result file as an array to the specified data type object for identifying column data to generate unstructured grid data;

[0061] Step S211, completing the windward side display according to the incoming flow direction, and completing the sunlit side display according to the illumination direction.

[0062] As a result, the display of the windward side and the sunlit side of the spacecraft during its in-orbit operation is more intuitive and easier to observe.

[0063] Optionally, in step S211, the display of the windward side according to the incoming flow direction and the display of the sun-exposed side according to the illumination direction include: calculating the arrow direction and length of the incoming flow direction or the illumination direction, submitting the arrow data and the data object of the specified data type to the three-dimensional engine, and completing the rendering work. Thus, the display effect of the windward side and the sun-exposed side is better.

[0064] Optionally, in step S210, the specified data type is a dataset type to facilitate data storage.

[0065] The schematic diagram of the effect of the windward side, the sun-receiving side and the three-dimensional running track of the spacecraft in orbit obtained by the method for displaying the on-orbit running status of the spacecraft described in this embodiment is as follows: Figure 2-4 As shown. It can be seen that the method for displaying the on-orbit operation status of a spacecraft described in this embodiment utilizes simulation and emulation, and by changing the space environment parameters and emulating the materials, the purpose of intuitively displaying the windward side, the sun-exposed side and the operating orbit of the spacecraft during its on-orbit operation can be achieved. It has obvious advantages and broad application prospects in technical applications such as the promotion, teaching, demonstration and optimization selection of spacecraft surface coating materials of spacecraft simulation software, and makes it possible to directly apply efficient Monte Carlo simulation methods based on multi-core parallelism and data pruning technologies, thereby improving the accuracy of atomic oxygen / ultraviolet radiation flux and its distribution on the surface of the spacecraft, which is of great significance.

[0066] Although the disclosure is disclosed as above, the protection scope of the disclosure is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the disclosure, and these changes and modifications will fall within the protection scope of the present invention.< / posdata>

Claims

1. A method for displaying the on-orbit operation status of a spacecraft, characterized in that: The steps include: Step S1, parsing the environment file, and storing the parsed data information in a memory structure, wherein the data information includes one or more of the spacecraft quaternion, six orbital numbers, atomic oxygen density, incoming flow direction, illumination direction, and longitude and latitude; Step S2, create a playback control component, and use the playback control component to realize the display of the windward side, the sunlit side, the two-dimensional orbital surface and / or the three-dimensional orbital surface during the spacecraft's on-orbit operation, wherein the playback control component sets the start and end time range of the playback control component according to the time of the original data in the memory structure to realize the playback control of the displayed image picture, wherein the playback control of the displayed image picture includes the playback control of the previous frame, the next frame, the first frame and the last frame.

2. The method for displaying the on-orbit operation status of a spacecraft according to claim 1, characterized in that: In step S2, the display of the three-dimensional orbit of the spacecraft during its on-orbit operation is realized by using the playback control component, including: Step S201, using parameter settings to set the track display format; Step S202, obtaining a model file, and adding the model file to the scene to represent the position of the spacecraft at different orbital points; Step S203, information of the initial trajectory line, marking the coordinates of two points on the trajectory line, setting the rotation matrix, the color of the trajectory line and the width of the trajectory line; Step S204, using a timer to send an orbit point update signal, and using the orbit point update signal to display the three-dimensional orbit of the spacecraft during its on-orbit operation.

3. The method for displaying the on-orbit operation status of a spacecraft according to claim 2, characterized in that: In step S201, the orbit display form includes a ground-fixed system trajectory form or an earth-fixed coordinate system trajectory form.

4. The method for displaying the on-orbit operation status of a spacecraft according to claim 3, characterized in that: When the orbit display form is the orbit form of the ground-fixed system, in step S204, the use of the orbit point update signal to complete the display of the three-dimensional orbit of the spacecraft during its in-orbit operation includes: after receiving the orbit point update signal data, assigning the longitude and latitude information to the rotating vehicle object so that it rotates around the y-axis and z-axis, assigning the obtained rotated matrix data to the vehicle object, setting the coordinate position of the vehicle object, adding the coordinate position information of the vehicle object to the line structure data, completing the trajectory update, and completing the display of the three-dimensional orbit of the spacecraft during its in-orbit operation.

5. The method for displaying the on-orbit operation status of a spacecraft according to claim 1, characterized in that: In step S2, the display of the two-dimensional orbit of the spacecraft during its on-orbit operation is realized by using the playback control component, including: Step S205, using the map file to complete the drawing of the map; Step S206, draw a latitude and longitude table and mark the latitude and longitude with labels; Step S207, when the number of track points reaches 2 or more, data drawing begins, and the previous track point and the current track point are connected into a line using a preset function; Step S208, obtaining the total number of orbital points that need to be drawn in real time, and looping according to step S207, completing the drawing of multiple orbital points to connect them into a trajectory line, so as to realize the display of the two-dimensional orbit of the spacecraft during its on-orbit operation.

6. The method for displaying the on-orbit operation status of a spacecraft according to claim 1, characterized in that: In step S2, the display of the windward side and the sunlit side of the spacecraft during on-orbit operation using the playback control component includes: Step S209, obtaining the current time step value and the windward exposure display mark to determine the designated windward result file or the exposure result file, parsing the designated windward result file or the exposure result file into the memory, and storing it in the form of an array; Step S210, reading the grid file of the specified time step to store data in the specified data type, adding the result data in the windward result file or the sun exposure result file as an array to the specified data type object for identifying column data to generate unstructured grid data; Step S211, completing the windward side display according to the incoming flow direction, and completing the sunlit side display according to the illumination direction.

7. The method for displaying the on-orbit operation status of a spacecraft according to claim 6, characterized in that: In step S211, the windward side display is completed according to the incoming flow direction, and the sunlit side display is completed according to the illumination direction, including: calculating the arrow direction and length of the incoming flow direction or the illumination direction, submitting the arrow data and the data object of the specified data type to the 3D engine, and completing the rendering work.

8. The method for displaying the on-orbit operation status of a spacecraft according to claim 6, characterized in that: In step S210, the specified data type is a dataset type.

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