CN112613197B - Method for analyzing shielding area of rotating solar sailboard by star - Google Patents
Method for analyzing shielding area of rotating solar sailboard by star Download PDFInfo
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Abstract
The invention discloses a method for analyzing the sheltering area of a rotating solar sailboard by a star, which relates to the technical field of aircraft design and comprises the following steps: exporting a satellite design structure chart through modeling software, converting the satellite design structure chart through model conversion software, and adjusting parameters to obtain a model file which can be recognized by a visual real-time computing system; establishing a satellite mathematical simulation system, and generating and outputting information; carrying out satellite model, configuration of satellite operation, on-orbit operation visualization and expected verification, establishing a coordinate system, a vector and a plane required by analysis work and exporting data in a visualization real-time computing system; and calculating the shielding area of the rotating solar panel by the star according to the derived data. The problem that theoretical calculation is too tedious and difficult to check is solved at least partially, and the calculation result is compared with visual display for checking, so that errors possibly caused by pure theoretical calculation are avoided, and the satellite designer can use the satellite conveniently.
Description
Technical Field
The invention relates to the technical field of aircraft design, in particular to a method for analyzing the shielding area of a rotating solar panel by a star.
Background
The on-orbit operation direction of the internet satellite integrated multi-type high-power communication equipment needs to be changed according to task requirements, so that a Solar Array Drive Assembly (SADA) is needed to Drive the sailboards to align days, and energy supply is provided.
Due to the limitation of carrying capacity and satellite in-orbit flexibility, the area of the sailboard cannot be increased, so that the dynamic real-time analysis of the illuminated area of the sailboard solar cell piece according to the satellite in-orbit position and the direction of the solar illuminated sailboard is very important. Through ground simulation analysis, on the one hand, the basis can be provided for whole star structural design, and on the other hand, the support can be provided for solar wafer piece cloth, and the optimal of satellite system energy and the highest utilization ratio under different working conditions are finally guaranteed.
However, when ground simulation analysis of a satellite on the shielding area of a rotating solar sailboard is carried out in the prior art, pure theoretical calculation is always carried out under the worst in-orbit condition when the satellite calculates energy and the area of the sailboard, the condition of the sailboard with SADA drive is not considered in most conditions, and the problems that the theoretical calculation is too complicated and the verification is difficult exist.
Disclosure of Invention
The invention aims to solve the problems that theoretical calculation is too complicated and is difficult to verify when ground simulation analysis of a shield area of a rotating solar panel by a star is carried out in the prior art, and adopts a dynamic visual analysis method to at least partially solve the problems.
Because the position of the satellite on the orbit changes in real time and the attitude is changeable according to the task requirement, the method analyzes the exposure rate of the sailboard according to the information of the satellite, the position of the sun, the rotation of the sailboard and the like, calculates the specific shielding area and shielding area by theory, and rechecks and displays the calculation in real time by a visualization means.
Specifically, the invention provides a dynamic visualization analysis method combining modeling software, model conversion software, a satellite mathematical simulation system and a visual real-time computing system, which comprises the following steps:
exporting a satellite design structure chart through modeling software, converting the satellite design structure chart through model conversion software, and adjusting parameters to obtain a model file which can be recognized by a visual real-time computing system; the model file includes: a fixed member provided by the star body; a rotating member provided by a windsurfing board driven by the SADA.
Establishing a satellite mathematical simulation system, and generating and outputting information; in the satellite mathematical simulation system, the generated and output information includes: satellite orbit dynamics information, satellite attitude dynamics information and satellite SADA rotation model information; the satellite orbit dynamics information comprises: calculating satellite in-orbit position information obtained in real time according to the initial orbit information and the orbit control information; the satellite attitude dynamics information includes: resolving the obtained satellite in-orbit pointing information in real time according to the tasks and the working modes; the satellite SADA rotation model information includes: and calculating the position relation information of the sailboard and the satellite body system in real time according to the SADA rotation guidance rate.
Configuring a satellite model in a visual real-time computing system; the configuration of the satellite model comprises: importing the model file into a visual real-time computing system, completing the setting of the rotation characteristic of the rotating component, and completing the definition of the component and an external interface; the rotating member rotation characteristic includes: axis of rotation, direction of rotation and rotation range.
Configuring satellite operation in a visual real-time computing system; the configuration of the satellite operation includes: and interacting the satellite orbit dynamics information and the satellite attitude dynamics information with a visual real-time computing system in a data flow mode, and outputting real-time rotation by the rotating part according to the satellite SADA rotation model information.
Performing on-orbit operation visualization and expected verification in a visualization real-time computing system;
establishing a coordinate system, a vector and a surface required by analysis work in a visual real-time computing system, and exporting data; establishing a coordinate system, a vector and a plane required by analysis work in a visual real-time computing system comprises the following steps: establishing a satellite body coordinate system, a sailboard coordinate system, a sun vector, an envelope vector of a satellite body and an envelope vector of a sailboard; the projection vector of the envelope vector of the satellite body on the sailboard is established according to the sun vector;
exporting the data comprises the following steps: determining the vertex coordinates of the sailboard, the vertex coordinates of the satellite star, the contour coordinates of the protrusions on the satellite star, satellite orbit parameters, world time and sun inclination angles based on the satellite body coordinate system; converting the data into a sailboard coordinate system through a conversion matrix; and exporting the data in a form of a visual real-time computing system report according to a settable time interval.
Calculating the shielding area of the rotating solar panel by the star according to the derived data; displaying each point under a sailboard coordinate system by using a data analysis tool, and connecting each coordinate point to form an envelope; integrating the intersection areas among the envelopes by adopting a Monte Carlo algorithm to obtain the intersection areas; calculating the intersection area of the current time in real time along with the advance of the time sequence; the intersection area is the shielding area of the star body on the rotating solar panel, and is displayed in real time in a visual interface;
connecting the coordinate points together to form an envelope comprises: directly connecting the vertexes of the sailboards to represent the envelope of the sailboards; connecting projection points of the vertex of the star on the sailboard with convex hulls to represent the enveloping projection of the star; and connecting convex hulls of the outlines of the protrusions on the star bodies to represent envelope projection of the outlines of the protrusions on the star bodies.
The method for analyzing the sheltering area of the rotating solar sailboard by the star body can recheck and display the calculation in real time by a visual means in the analysis process, and has at least the following beneficial effects: compared with the prior art, a large amount of theoretical calculation is avoided, the calculation result can be compared with visual display for verification, errors possibly caused by pure theoretical calculation are avoided, and the satellite designer can use the satellite navigation system conveniently.
Drawings
FIG. 1 shows the overall system framework for real-time visualization of computation of star-to-SADA driven windsurfing occlusion in an embodiment of the method of the present invention.
Fig. 2 shows the export and conversion of the satellite model files in an embodiment of the method of the invention.
Figure 3 shows a satellite structure in one embodiment of the method of the invention.
Fig. 4 shows a satellite mathematical simulation system and information output in the method of the invention.
FIG. 5 illustrates a dynamic display of occlusion shape and size in a visual interface in one embodiment of a method of the present invention.
FIG. 6 shows the real-time output of the visualization calculation of the windsurfing board occlusion area by the stars in one embodiment of the method of the present invention.
Detailed Description
It should be noted that the components in the figures may be exaggerated and not necessarily to scale for illustrative purposes. In the figures, identical or functionally identical components are provided with the same reference symbols.
In the present invention, "disposed on …", "disposed over …" and "disposed over …" do not exclude the presence of an intermediate therebetween, unless otherwise specified. Further, "disposed on or above …" merely indicates the relative positional relationship between two components, and may also be converted to "disposed below or below …" and vice versa in certain cases, such as after reversing the product direction.
In the present invention, the embodiments are only intended to illustrate the aspects of the present invention, and should not be construed as limiting.
In the present invention, the terms "a" and "an" do not exclude the presence of a plurality of elements, unless otherwise specified.
It is further noted herein that in embodiments of the present invention, only a portion of the components or assemblies may be shown for clarity and simplicity, but those of ordinary skill in the art will appreciate that, given the teachings of the present invention, required components or assemblies may be added as needed in a particular scenario. Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
It is also noted herein that, within the scope of the present invention, the terms "same", "equal", and the like do not mean that the two values are absolutely equal, but allow some reasonable error, that is, the terms also encompass "substantially the same", "substantially equal". By analogy, in the present invention, the terms "perpendicular", "parallel" and the like in the directions of the tables also cover the meanings of "substantially perpendicular", "substantially parallel".
The numbering of the steps of the methods of the present invention does not limit the order of execution of the steps of the methods. Unless specifically stated, the method steps may be performed in a different order.
The invention is further elucidated with reference to the drawings in conjunction with the detailed description.
FIG. 1 shows the overall system framework for real-time visualization calculation of the occlusion of a windrow with a SADA-driven windsurfing board by a star in an embodiment of the method of the present invention. The modeling software is Pro/ENGINEER (Proe), the satellite mathematical simulation system is based on MATLAB, the visual real-time computing system is satellite Tool software STK (satellite Tool kit) of American Analytical Graphics company, the data processing and shielding calculation is based on Python, and the specific steps are as follows:
satellite design Structure As shown in FIG. 3, the two-dimensional SADA has two rotational degrees of freedom, i.e., a rotation point G and a rotation point H, wherein the rotation point G can be around YbMaking a 360 deg. rotation, while the rotation point H can be around XfAnd rotating within a set angle range. A connecting rod is arranged between the rotating point G and the rotating point H, and the rotating point H is connected with the sailboard through the connecting rod. Wherein, ObH length a, HOfLength b, rotation angle d for rotation point H, and rotation angle β for rotation point G.
According to a satellite design structure diagram, an Obj format model file is exported through modeling software Pro/ENGINEER (Proe), then, LightWave software is used for converting the Obj file into an Mdl model file which can be identified by STK, a star body and a sailboard driven by SADA are structurally separated, the star body is set as a fixed part, the sailboard driven by the SADA is set as a rotating part, and parameter adjustment is carried out to complete the mapping of the Mdl file and an actual model.
And establishing a satellite mathematical simulation system, wherein the satellite orbit dynamics comprises the following steps: resolving satellite in-orbit position information in real time according to the initial orbit information and the orbit control information; satellite attitude dynamics: resolving satellite in-orbit pointing information in real time according to tasks and working modes; satellite SADA rotation model: and solving the position relation between the sailboard and the satellite body system in real time according to the SADA rotation guidance rate. And outputs the above information as a whole.
And configuring the STK satellite model. And importing the Mdl file of the satellite into the STK to complete the setting of the rotation characteristics (the rotation axis, the rotation direction and the rotation range) of the rotating component, and completing the definition of the component and an external interface, thereby facilitating the driving of a subsequent program.
And configuring for STK satellite operation. And interacting the satellite pointing information and the position information with the STK in a data stream mode, and operating the STK in real time according to the information output by the satellite mathematical simulation system. The rotating member rotates in real time according to the output of the SADA rotation model.
And performing the STK on-orbit operation visualization and expected verification work. And then carrying out shielding analysis work of the satellite body on the sailboard solar cell. Establishing a coordinate system, a vector and a surface required by the establishment of analysis work required by the subsequent analysis work on a satellite body and a sailboard, and mainly comprising the steps of establishing a satellite body coordinate system, a sailboard coordinate system, a sun vector, an envelope vector of the satellite body, an envelope of the sailboard, and establishing a projection vector of the body envelope vector on the sailboard according to the sun irradiation direction. And exporting the data in the form of an STK report.
The windsurfing coordinate system is defined as follows:
satellite body coordinate system Ob-XbYbZbFirst along YbDirection translation a, then rotation point G rotation angle α, then:
translation amount t1＝[0 -a 0]Rotation matrix T1Expressed as:
the G-point rotation and translation process is represented as:
second, the rotation point H is rotated by an angle θ and then along YfThe direction is translated by the length b. Rotation matrix T2Comprises the following steps:
translation vector t2Is [ 0-b 0]. The rotation and translation process of the H point is expressed as:
the sun vector is S (m, n, P), the coordinate of any point is P (x, y, z), and the projection point of the point on the windsurfing board plane along the sun vector direction is P ' (x ', y '), then:
the included angle between the sun vector and the normal of the sailboard is beta, and the sun vector of the sailboard coordinate system is S ═ 0 cos beta sin beta
Then along the sun vector direction, the satellite body is projected and crossed with the sailboard coordinate system Of-XfYfZfThe OXY plane of (a) results in its projection profile.
Data to be derived (coordinates are satellite body coordinates, taking a single sailboard as an example):
| four vertex coordinates of sailboard (dynamic) |
| Eight vertex coordinates of satellite star (dynamic) |
| Projection contour coordinates on satellite body (dynamic) |
| Satellite orbit parameters |
| Sampling time interval |
| World time |
| Inclination of the sun |
And respectively converting the derived data into a coordinate system of a sailboard coordinate system according to the definition of a conversion matrix in the sailboard coordinate system, wherein the edge of the sailboard parallel to the side surface of the star body is used as an X axis of the reference coordinate system, and the edge of the sailboard vertical to the side surface of the star body is used as a Y axis of the reference coordinate system to establish the coordinate system.
And constructing a related coordinate system and a vector according to the model, and determining the coordinates of the points. And derives correlation data at intervals.
And calculating a similarity area based on the STK derived data.
And displaying each point under a reference coordinate system by using a python data analysis tool, and connecting each coordinate point according to a certain rule to form an envelope.
The rules are as follows:
1. the four vertices of the windsurfing board are directly connected and are used for representing the envelope of the windsurfing board.
2. And convex hull connection of projection points of eight vertexes of the star body is used for representing envelope projection of the star body.
3. The convex hull connection of the projection outline on the star body is used for the envelope projection of the surface projection outline.
After the envelopes are formed, the intersection areas between the envelopes are integrated by adopting a Monte Carlo algorithm to obtain the intersection areas. As the time series progresses, the intersecting occlusion area at the current time is calculated in real time and displayed in real time in the QtGUI interface, see fig. 5.
And finally, performing on-orbit long-time simulation, and calculating the shielding area of the sailboard under various working conditions and sun irradiation conditions according to the STK output data. According to the geometric shielding model, the modeling is carried out through STK software, and the on-orbit running state and the shielding area of the spacecraft can be dynamically displayed in real time in the STK software environment. And visual display can be carried out at any time node of the satellite life cycle and under different beta angles according to requirements, and all possible conditions are traversed to the greatest extent. And then, acquiring relevant data of the re-orbit of the satellite through STK software, and calculating the shielding area through Python to obtain all shielding conditions and the shielding area of the whole life cycle of the satellite. FIG. 6 is a view showing the real-time output of visualization calculation of the windsurfing board shading area by the stars.
Claims (4)
1. A method for analyzing the sheltered area of a rotating solar sailboard by a star is characterized in that a dynamic visual analysis method combining modeling software, model conversion software, a satellite mathematical simulation system and a visual real-time computing system is adopted, and the method comprises the following steps:
exporting a satellite design structure diagram through modeling software, converting the satellite design structure diagram through model conversion software, and adjusting parameters to obtain a model file which can be recognized by a visual real-time computing system, wherein the model file comprises: a fixed member provided by the star body; a rotating member provided by a windsurfing board driven by a SADA;
establishing a satellite mathematical simulation system, and generating and outputting information, wherein the information comprises satellite orbit dynamics information, satellite attitude dynamics information and satellite SADA rotation model information;
configuring a satellite model in a visual real-time computing system, wherein a model file is imported into the visual real-time computing system, the setting of the rotation characteristics of a rotating part is completed, and the definition of the part and an external interface is completed, wherein the rotation characteristics of the rotating part comprise a rotating shaft, a rotating direction and a rotating range;
configuring satellite operation in a visual real-time computing system, wherein satellite orbit dynamics information and satellite attitude dynamics information are interacted with the visual real-time computing system in a data flow mode, and a rotating component outputs real-time rotation according to satellite SADA rotation model information;
performing on-orbit operation visualization and expected verification in a visualization real-time computing system;
establishing a coordinate system, a vector and a surface required by analysis work in a visual real-time computing system, and exporting data, wherein the establishing of the coordinate system, the vector and the surface required by the analysis work comprises establishing a satellite body coordinate system, a sailboard coordinate system, a sun vector, an envelope vector of a satellite body and an envelope vector of a sailboard; the projection vector of the envelope vector of the satellite body on the sailboard is established according to the sun vector; exporting the data comprises the following steps: determining the vertex coordinates of the sailboard, the vertex coordinates of the satellite star, the contour coordinates of the protrusions on the satellite star, satellite orbit parameters, world time and sun inclination angles based on the satellite body coordinate system; converting the data into a sailboard coordinate system through a conversion matrix; exporting data in a form of a visual real-time computing system report according to a settable time interval; and
calculating the sheltering area of the rotating solar panel by the star according to the derived data, wherein the method comprises the following steps: displaying each point under a sailboard coordinate system by using a data analysis tool, and connecting each coordinate point to form an envelope; integrating the intersection areas among the envelopes by adopting a Monte Carlo algorithm to obtain the intersection areas; calculating the intersection area of the current time in real time along with the advance of the time sequence; the intersection area is the shielding area of the star body on the rotating solar panel, and is displayed in real time in a visual interface; wherein connecting the coordinate points together to form an envelope comprises: directly connecting the vertexes of the sailboards to represent the envelope of the sailboards; connecting projection points of the vertex of the star on the sailboard with convex hulls to represent the enveloping projection of the star; and connecting convex hulls of the outlines of the protrusions on the star bodies to represent envelope projection of the outlines of the protrusions on the star bodies.
2. The method of claim 1, wherein the satellite orbital dynamics information comprises: and calculating the on-orbit position information of the satellite in real time according to the initial orbit information and the orbit control information.
3. The method of claim 1, wherein the satellite attitude dynamics information comprises: and resolving the obtained satellite in-orbit pointing information in real time according to the task and the working mode.
4. The method of claim 1, wherein the satellite SADA rotation model information comprises: and calculating the position relation information of the sailboard and the satellite body system in real time according to the SADA rotation guidance rate.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103116363A (en) * | 2013-01-23 | 2013-05-22 | 四川钟顺太阳能开发有限公司 | Method and system for sun trajectory tracking of photovoltaic generators |
| CN103136444A (en) * | 2013-01-29 | 2013-06-05 | 北京空间飞行器总体设计部 | Analysis method of illuminated status of solar panel under different control modes of navigation satellite |
| CN104615841A (en) * | 2015-03-05 | 2015-05-13 | 哈尔滨工业大学 | Spacecraft solar panel three-dimensional dynamic simulation method taking shielding effect into consideration |
| CN108920829A (en) * | 2018-06-29 | 2018-11-30 | 中国空间技术研究院 | A kind of solar light pressure torque calculation method of band large size net-shape antenna satellite |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9702592B2 (en) * | 2007-03-02 | 2017-07-11 | Solar Revolution Llc | Systems and methods for solar energy utilization |
| CN103150414B (en) * | 2012-06-13 | 2017-07-18 | 中国空间技术研究院 | The big antenna pair solar wing sheltering analysis method of telecommunication satellite based on STL |
| CN106096148B (en) * | 2016-06-14 | 2019-05-24 | 中国空间技术研究院 | A kind of high inclination-angle orbiter solar array pointing method under simple gesture stability |
| US10521664B2 (en) * | 2016-11-04 | 2019-12-31 | Loveland Innovations, LLC | Systems and methods for autonomous perpendicular imaging of test squares |
| CN107421551B (en) * | 2017-08-02 | 2020-02-07 | 北京国电高科科技有限公司 | Method and device for detecting rotation of satellite sailboard |
| CN109711082B (en) * | 2019-01-08 | 2023-08-08 | 上海卫星工程研究所 | Combined analysis method for illumination condition and sailboard shielding of large elliptic frozen orbit satellite |
| CN109927940B (en) * | 2019-02-19 | 2021-02-02 | 上海卫星工程研究所 | Thermal protection device for solar array driving mechanism |
-
2021
- 2021-01-08 CN CN202110029028.8A patent/CN112613197B/en active Active
- 2021-01-08 CN CN202110971542.3A patent/CN113642188B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103116363A (en) * | 2013-01-23 | 2013-05-22 | 四川钟顺太阳能开发有限公司 | Method and system for sun trajectory tracking of photovoltaic generators |
| CN103136444A (en) * | 2013-01-29 | 2013-06-05 | 北京空间飞行器总体设计部 | Analysis method of illuminated status of solar panel under different control modes of navigation satellite |
| CN104615841A (en) * | 2015-03-05 | 2015-05-13 | 哈尔滨工业大学 | Spacecraft solar panel three-dimensional dynamic simulation method taking shielding effect into consideration |
| CN108920829A (en) * | 2018-06-29 | 2018-11-30 | 中国空间技术研究院 | A kind of solar light pressure torque calculation method of band large size net-shape antenna satellite |
Non-Patent Citations (4)
| Title |
|---|
| Visual Modeling and Simulation Research of A kind of On-orbit Servicing Spacecraft;Bingshuai Li et al.;《Applied Mechanics and Materials》;20140424;第538卷;第184-187页 * |
| 图像检测在航天器太阳帆板遮挡分析中的应用;邵益凯 等;《图像检测在航天器太阳帆板遮挡分析中的应用》;20160715;第33卷(第7期);第116-120页 * |
| 组合体太阳帆板遮挡分析及可视化;李文 等;《计算机仿真》;20130315;第30卷(第3期);第105-108页 * |
| 航天器太阳电池阵遮挡影响及电源系统仿真优化方法研究;杨炀;《中国博士学位论文全文数据库 工程科技Ⅱ辑》;20190115(第01期);C042-159 * |
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