CN111709088A - Method and device for processing light pressure area of target spacecraft - Google Patents
Method and device for processing light pressure area of target spacecraft Download PDFInfo
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Abstract
The invention discloses a method and a device for processing the light pressure area of a target spacecraft. Wherein, the method comprises the following steps: determining target parameters, wherein the target parameters at least comprise an effective surface element of a target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft and a light pressure coefficient factor; and determining the light pressure area of the effective surface element of the target spacecraft according to the target parameters. The invention solves the technical problem of low precision of light pressure area estimation of the newly launched spacecraft in the related technology.
Description
Technical Field
The invention relates to the field of spaceflight, in particular to a method and a device for processing the light pressure area of a target spacecraft.
Background
The spacecraft is influenced by radiation of a large number of photon streams generated by the sun in the orbit process, namely the solar radiation pressure, and the solar radiation pressure is also called as the solar light pressure because the radiation energy is mostly concentrated in a visible light wave band. Photons are reflected or absorbed when they strike the spacecraft body and the solar panel, and different forms of force are generated by differently shaped illuminated surfaces.
According to the existing research and practical task experience, the sunlight pressure is the most main perturbation force influencing the determining and forecasting precision of the deep space exploration spacecraft orbit, and the orbit dynamics model error mainly comes from the sunlight pressure model. The sunlight pressure is influenced by various factors including the characteristics of the spacecraft, attitude change, control error, solar activity and the like, and the sunlight pressure area is an important index for representing the sunlight pressure, is a key parameter required in the determination and prediction of the precise orbit of the spacecraft, and directly influences the precision of orbit determination and orbit prediction. Scholars at home and abroad conduct a plurality of researches on the sunlight pressure problem, and establish various sunlight pressure models which are mainly divided into three categories: analytical/physical models, empirical models, and semi-empirical models.
The analysis model is mainly established according to the physical characteristics of the geometry, the size, the body, the optical characteristics (scattering characteristics and absorption characteristics) and the like of the surface material of the solar sailboard of the spacecraft, the modeling is usually completed before the spacecraft is launched, the on-orbit data is not required to be utilized, and the method is suitable for the newly launched spacecraft. The analytical model proposed at the earliest was a sphere model, and ROCK series models, T30 models, G2A models, and the like were developed later. In contrast, the physical background of the model is clear, and the input parameters are clear, so that the orbit calculation and the orbit prediction are convenient to perform. However, after the spacecraft is operated in orbit for a long time, the surface material can be aged and finally the optical characteristics can be changed along with the change of time and space environment. The empirical modeling method is characterized in that an optical pressure model formula is established by utilizing a large amount of historical data such as a long-term precise ephemeris and the like according to the on-orbit running state of the spacecraft after being launched, and an optical pressure model is obtained by obtaining and fitting optimal model parameters, and the accuracy is high, and the optical pressure model mainly comprises a Colombo model, an ECOM model and the like. However, the method needs to rely on a large amount of long-term observation data for support, absorbs the influence of various perturbation forces, is lack of physical connotation, and is not beneficial to analyzing the change of the light pressure independently. The semi-empirical model combines the advantages of an analytic model and an empirical model, gives consideration to the motion information of the in-orbit running state of the spacecraft after launching while comprehensively considering the self basic information and the attribute of the spacecraft before launching, and mainly comprises a JPL model, an Ad box-wing model and the like.
In the deep space exploration task of China, each spacecraft does not have a special sunlight pressure model at present, and the common method is to simplify the shape and the structural composition of the spacecraft and estimate the projection area (cross-sectional area) and the light pressure area of the spacecraft in the illumination direction. To improve the accuracy of the light pressure model, not only the mutual shielding relationship of different parts of the detector in the illumination direction needs to be considered, but also the reflection characteristics of different materials on the surface to sunlight need to be considered, and the calculation and shielding judgment process is complex.
Aiming at the problem of low precision of light pressure area estimation of the newly launched spacecraft in the prior art, an effective solution is not provided at present.
Disclosure of Invention
The embodiment of the invention provides a method and a device for processing the light pressure area of a target spacecraft, which are used for at least solving the technical problem of low precision of light pressure area estimation of a newly launched spacecraft in the related technology.
According to an aspect of the embodiments of the present invention, there is provided a method for processing a light pressure area of a target spacecraft, including: determining target parameters, wherein the target parameters at least comprise an effective surface element of a target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft and a light pressure coefficient factor; and determining the light pressure area of the effective surface element of the target spacecraft according to the target parameters.
Optionally, the determining the effective bin of the target spacecraft in the target parameter comprises: acquiring a three-dimensional model of the target spacecraft; performing rotation transformation on the three-dimensional model according to the target attitude of the target spacecraft at the current moment; projecting the three-dimensional model after rotation transformation onto a two-dimensional screen; blanking the three-dimensional model projected onto the two-dimensional screen; performing illumination rendering on the three-dimensional model subjected to blanking processing; and determining an effective surface element of the target spacecraft in the target parameters according to the surface element parameters of the three-dimensional model after illumination rendering.
Optionally, before obtaining the three-dimensional model of the target spacecraft, the method further comprises: and constructing a three-dimensional model of the target spacecraft according to the target characteristics of the target spacecraft, wherein the target characteristics at least comprise structure, appearance, size and surface material.
Optionally, constructing the three-dimensional model of the target spacecraft according to the target characteristic of the target spacecraft comprises: and distinguishing surface materials in the target characteristics of the target spacecraft by using different colors, wherein the scattering characteristics of the surface materials to the target light source are diffuse reflection.
Optionally, determining the physical area of the active bin of the target spacecraft in the target parameter comprises: determining the display size of the effective surface element of the target spacecraft on a two-dimensional screen; and obtaining the physical area of the effective surface element of the target spacecraft according to the actual physical scale corresponding to the display size.
Optionally, determining the optical pressure coefficient factor of the effective bin of the target spacecraft in the target parameter comprises: acquiring material optical characteristic parameters of effective surface elements of the spacecraft, wherein the material optical characteristic parameters at least comprise effective surface element pairs of the spacecraftSolar energyReflection coefficient, specular reflection coefficient, diffuse reflection coefficient; and determining the optical pressure coefficient factor of the effective surface element according to the optical characteristic parameters of the material.
Optionally, determining the optical pressure area of the effective surface element of the target spacecraft according to the target parameter comprises: determining the projection area of the effective surface element of the target spacecraft according to the included angle between the effective surface element of the target spacecraft and incident light and the physical area of the effective surface element of the target spacecraft; and determining the light pressure area of the effective surface element of the target spacecraft according to the projection area of the effective surface element of the target spacecraft and the light pressure coefficient factor of the effective surface element of the target spacecraft.
Optionally, the target spacecraft comprises at least a plurality of active bins, the method further comprising: sequentially determining the light pressure areas of a plurality of effective surface elements; and accumulating and summing the light pressure areas of the effective surface elements to obtain the light pressure area of the effective surface element of the whole target spacecraft.
According to another aspect of the embodiments of the present invention, there is also provided an apparatus for processing a light pressure area of a target spacecraft, including: the device comprises a first determination module, a second determination module and a third determination module, wherein the first determination module is used for determining target parameters, and the target parameters at least comprise an effective surface element of a target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft and an optical pressure coefficient factor; and the second determining module is used for determining the light pressure area of the effective surface element of the target spacecraft according to the target parameter.
According to another aspect of the embodiments of the present invention, there is also provided a computer-readable storage medium, where the computer-readable storage medium includes a stored program, where when the program runs, the apparatus on which the computer-readable storage medium is located is controlled to execute the method for processing the optical pressure area of the target spacecraft described in any one of the above.
According to another aspect of the embodiments of the present invention, there is also provided a processor, configured to execute a program, where the program executes the method for processing the light pressure area of the target spacecraft described in any one of the above.
In the embodiment of the invention, target parameters are determined, wherein the target parameters at least comprise an effective surface element of a target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft and a light pressure coefficient factor; according to the target parameters, the light pressure area of the effective surface element of the target spacecraft is determined, and the purpose of accurately determining the light pressure area of the effective surface element of the target spacecraft is achieved by determining the effective surface element of the target spacecraft, and the included angle, the physical area and the light pressure coefficient factor of the effective surface element of the target spacecraft and incident light, so that the technical effect of improving the precision of calculating the solar light pressure area of the complex spacecraft is achieved, and the technical problem of low precision of estimating the light pressure area of the new launch spacecraft in the related technology is solved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a flow chart of a method of processing a light pressure area of a target spacecraft in accordance with an embodiment of the present invention;
FIG. 2 is a flow chart of a method of processing the optical pressure area of a target spacecraft in accordance with an alternative embodiment of the present invention;
FIG. 3 is a schematic illustration of a spacecraft coordinate system and sunlight incident angle according to an embodiment of the present invention;
FIG. 4 is a schematic view of a cuboid subjected to sunlight pressure according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of simulated values of light pressure area and relative deviations of a rectangular parallelepiped according to an embodiment of the present invention;
fig. 6 is a schematic diagram of a processing arrangement of the optical pressure area of a target spacecraft in accordance with an embodiment of the invention.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
Example 1
In accordance with an embodiment of the present invention, there is provided an embodiment of a method for processing a photo-voltaic area of a target spacecraft, it is noted that the steps illustrated in the flowchart of the drawings may be performed in a computer system, such as a set of computer-executable instructions, and that while a logical order is illustrated in the flowchart, in some cases the steps illustrated or described may be performed in an order different than here.
Fig. 1 is a flowchart of a method for processing a light pressure area of a target spacecraft according to an embodiment of the present invention, as shown in fig. 1, the method includes the steps of:
step S102, determining target parameters, wherein the target parameters at least comprise an effective surface element of a target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft and a light pressure coefficient factor;
and step S104, determining the optical pressure area of the effective surface element of the target spacecraft according to the target parameters.
In a specific implementation process, after target parameters at least including an effective surface element of the target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft and a light pressure coefficient factor are determined, the light pressure area of the effective surface element of the target spacecraft is determined through the target parameters.
Through the steps, the target parameters can be determined, wherein the target parameters at least comprise an effective surface element of the target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft and an optical pressure coefficient factor; according to the target parameters, the light pressure area of the effective surface element of the target spacecraft is determined, and the purpose of accurately determining the light pressure area of the effective surface element of the target spacecraft is achieved by determining the effective surface element of the target spacecraft, and the included angle between the effective surface element of the target spacecraft and incident light, the physical area and the light pressure coefficient factor, so that the technical effect of improving the precision of calculating the solar light pressure area of the complex spacecraft is achieved, and the technical problem of low precision of light pressure area estimation of a new launching spacecraft in the related technology is solved.
Optionally, the determining the effective bin of the target spacecraft in the target parameter comprises: acquiring a three-dimensional model of a target spacecraft; performing rotation transformation on the three-dimensional model according to the target attitude of the target spacecraft at the current moment; projecting the three-dimensional model after rotation transformation onto a two-dimensional screen; blanking the three-dimensional model projected onto the two-dimensional screen; performing illumination rendering on the three-dimensional model subjected to blanking processing; and determining an effective surface element of the target spacecraft in the target parameters according to the surface element parameters of the three-dimensional model after illumination rendering.
As an optional embodiment, when determining the effective bin of the target spacecraft in the target parameters, a three-dimensional model of the target spacecraft may be obtained. Specifically, according to a three-dimensional model file of the spacecraft provided by an industrial department, three-dimensional modeling software 3DS MAX is used for model format conversion, editing, processing and processing, different materials are used for representing and distinguishing different components and loads (a cabin body, a solar cell panel, an antenna and the like) of the spacecraft, and the scattering characteristic of the materials to a light source is set to be diffuse reflection.
Alternatively, the target model data file in the 3DS file format may be read programmatically using specialized software. In order to calculate the effective surface element of the complex target spacecraft, data such as the positions of all points on the target surface, the direction of an external normal line, the area of the surface element, the type of a component where the surface element is located and the like are needed. The 3DS file format is a hierarchical structure composed of blocks, the basic block, i.e., the main block, including: version, edit information and key frame information, wherein the primary block in each basic block contains various information. Data such as light source information and camera information are not required for calculation, and therefore the read data in the 3DS satellite model file includes material information, vertex information, plane element information, and the like of the target object. Reading required information into a custom data structure, and then drawing a target model by utilizing OpenGL, wherein the main reading operation comprises the following steps: firstly, defining a series of data structures, such as the material, material library, position vector and the like of an object; then reading the 3DS file and storing the file into an object; finally, classes for processing various objects are defined for drawing the target.
Optionally, after obtaining the three-dimensional model of the target spacecraft, performing rotation transformation on the three-dimensional model according to the target attitude of the target spacecraft at the current time, for example, performing rotation transformation on the three-dimensional model according to the target attitude of the target spacecraft at the current time (including a rotation angle of the cabin, a rotation angle of the solar wing and the antenna, and the like).
Optionally, after the three-dimensional model is subjected to rotation transformation, the three-dimensional model after the rotation transformation is projected onto a two-dimensional screen, the three-dimensional model projected onto the two-dimensional screen is subjected to blanking processing, the visualization and blanking functions of OpenGL can be applied, the three-dimensional target is projected onto the two-dimensional screen by adopting an orthogonal projection mode, a depth buffer area is started for depth testing, blanking of the target spacecraft and display of a visible part are completed simultaneously, the accuracy and the speed of calculation are improved, and therefore the fault of program logic judgment on the surface element shielding relation is avoided.
Optionally, after blanking the three-dimensional model projected onto the two-dimensional screen, performing illumination rendering on the three-dimensional model after blanking, and determining an effective bin of the target spacecraft in the target parameters according to bin parameters of the three-dimensional model after illumination rendering. This embodiment can adopt the illumination model, through setting up suitable parameter, reads the pixel surface element colour value in the frame buffer memory after the illumination is rendered up, obtains the surface element of each effective surface element and the contained angle of incident light and the class isoparametric of the material that the surface element represents, and then calculates the light pressure area of each surface element, calculates the light pressure area of whole target through the accumulation at last.
Optionally, before obtaining the three-dimensional model of the target spacecraft, the method further includes: and constructing a three-dimensional model of the target spacecraft according to the target characteristics of the target spacecraft, wherein the target characteristics at least comprise structure, appearance, size and surface material.
As an alternative embodiment, a three-dimensional model is established according to target characteristic information of the spacecraft, such as structure, appearance, size, surface material and the like, and is processed correspondingly. For example, the three-dimensional modeling software 3DMAX can be used for geometric shape modeling of a complex structure spacecraft, and a three-dimensional model containing material information is established through modification and editing, wherein the file format of the three-dimensional model is 3 DS.
It should be noted that, the three-dimensional model of the target spacecraft is constructed based on the target characteristics of the target spacecraft, the structure, the shape and the size are used as the target characteristics, the surface material is used as the target characteristics, and the surface material of the target spacecraft can be obtained through the three-dimensional model, so that the influence of reflection characteristics of different surface materials on sunlight on the accuracy of the light pressure area is considered in the subsequent light pressure area calculation, and the calculation precision is improved.
Optionally, constructing the three-dimensional model of the target spacecraft according to the target characteristic of the target spacecraft includes: different colors are used to distinguish surface materials in the target characteristics of the target spacecraft, wherein the scattering characteristics of the surface materials to the target light source are diffuse reflection.
As an alternative embodiment, in the process of building a three-dimensional model containing material information, different color types can be used to distinguish different types of materials such as a star coating and a solar cell of a spacecraft, and the scattering characteristic of the material to a target light source is set to be diffuse reflection. The target light source is a light source set according to an application scenario.
By means of the method, the surface material in the target characteristic of the target spacecraft can be distinguished according to the diffuse reflection color subsequently, and therefore the corresponding surface element parameters can be calculated more accurately.
Optionally, the determining the physical area of the effective bin of the target spacecraft in the target parameter comprises: determining the display size of an effective surface element of the target spacecraft on a two-dimensional screen; and obtaining the physical area of the effective surface element of the target spacecraft according to the actual physical scale corresponding to the display size.
As an alternative embodiment, there is a certain proportionality coefficient between the display size of the effective bin on the two-dimensional screen and the actual physical scale corresponding to the display size, for example, the proportionality coefficient between the display size and the actual physical scale may be 1:50, 1:100, etc., and the specific scale unit may be centimeter, millimeter, decimeter, meter, etc. Specifically, at a scale factor of 1:100, the display size of the effective bin on the two-dimensional screen is: and if the length is 1 cm and the width is 2 cm, the corresponding actual physical dimensions are 100 cm and 200 cm, and the physical area of the effective surface element of the target spacecraft can be further calculated according to an area formula.
Optionally, the determining the optical pressure coefficient factor of the effective bin of the target spacecraft in the target parameter comprises: acquiring material optical characteristic parameters of an effective surface element of the spacecraft, wherein the material optical characteristic parameters at least comprise a reflection coefficient, a specular reflection coefficient and a diffuse reflection coefficient of the effective surface element of the spacecraft on sunlight; and determining the optical pressure coefficient factor of the effective surface element according to the optical characteristic parameters of the material.
As an optional embodiment, information such as reflection coefficients, specular reflection coefficients, diffuse reflection coefficients and the like of different surface materials of the spacecraft on sunlight can be obtained through modes such as experimental measurement and data processing.
In a specific implementation process, the light pressure coefficient factor of the effective surface element may be obtained as follows:
wherein the light pressure coefficient factor k represents the ratio of the light pressure area of the surface element to the projection area, and can be usedk(γβ, theta), theta is the incident angle of the sun's rays on a certain tiny plane,γfor the reflection coefficient (dimensionless),βis a specular coefficient (dimensionless).
Optionally, determining the optical pressure area of the effective surface element of the target spacecraft according to the target parameter comprises: determining the projection area of the effective surface element of the target spacecraft according to the included angle between the effective surface element of the target spacecraft and incident light and the physical area of the effective surface element of the target spacecraft; and determining the light pressure area of the effective surface element of the target spacecraft according to the projection area of the effective surface element of the target spacecraft and the light pressure coefficient factor of the effective surface element of the target spacecraft.
As an optional embodiment, the light pressure area of the effective surface element of the target spacecraft may be determined by an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft, and a light pressure coefficient factor of the effective surface element of the target spacecraft in the target parameters.
Optionally, firstly, the projection area of the effective surface element of the target spacecraft can be determined according to the included angle between the effective surface element of the target spacecraft and incident light and the physical area of the effective surface element of the target spacecraft; and then determining the optical pressure area of the effective surface element of the target spacecraft according to the projection area of the effective surface element of the target spacecraft and the optical pressure coefficient factor of the effective surface element of the target spacecraft. The light pressure coefficient factor of the effective surface element of the target spacecraft can be determined firstly, then the projection area of the effective surface element of the target spacecraft is determined according to the included angle between the effective surface element of the target spacecraft and incident light and the physical area of the effective surface element of the target spacecraft, and then the light pressure area of the effective surface element of the target spacecraft is determined according to the light pressure coefficient factor and the projection area.
By the method, the accurate and reliable optical pressure area of the effective surface element of the target spacecraft can be obtained.
Optionally, the target spacecraft comprises at least a plurality of active bins, and the method further comprises: sequentially determining the light pressure areas of a plurality of effective surface elements; and accumulating and summing the light pressure areas of the effective surface elements to obtain the light pressure area of the effective surface element of the whole target spacecraft.
The optical pressure areas of a plurality of effective surface elements can be obtained through the implementation mode of the invention, and then the optical pressure areas of the effective surface elements are accumulated and summed, so that the optical pressure area of the effective surface element of the whole target spacecraft can be obtained. Therefore, the embodiment of the invention can be used for calculating the light pressure area of any effective surface element of the target spacecraft and calculating the light pressure area of the effective surface element of the whole target spacecraft.
An alternative embodiment of the invention is described in detail below.
The invention provides an analytical light pressure area calculation method for a spacecraft, which at least solves the problem of low precision of light pressure area estimation of a newly launched spacecraft.
Wherein, the target characteristics of the spacecraft in the implementation process mainly refer to the information of the shape, the size, the composition structure, the optical characteristics of surface materials and the like of the spacecraft; the surface material optical properties refer to the reflectance, specular reflectance and diffuse reflectance of the material.
The spacecraft generally comprises a star platform, a solar panel, an antenna, a payload and the like, and the surface material mainly comprises a structural material, a thermal control coating, a multi-layer thermal insulation material, a solar cell and the like. Generally, the front surface of the sailboard is provided with solar cells, and the back surface of the sailboard is provided with a sprayed black paint coating. The surface of the star body is covered by a plurality of layers of heat insulating materials. The optical reflection and absorption characteristics of different materials also differ. Because the surface of a complex spacecraft can not be described by using an analytical expression, the concept of micro surface elements is needed to be adopted, an illuminated surface is divided into all micro plane elements, and then the sunlight pressure of the whole spacecraft is analyzed on the basis of a mechanical model under the condition of planar illumination.
Firstly, establishing an analytical light pressure model of the spacecraft. The light pressure model comprises a three-dimensional model for representing each component of the spacecraft and a reflectivity parameter for representing the optical characteristic of the surface material of the spacecraft. The reflectivity parameters of the surface material of the three-dimensional model are respectively the same as those of each part of the real satellite.
And calculating the integral sunlight pressure area parameter of the spacecraft by utilizing the established analysis type sunlight pressure model and solving the algebraic sum of the sunlight pressure areas of all micro-planes on the surface of the spacecraft. When the sunlight irradiates a certain micro plane and theta is an incident angle, the sunlight pressure area parameter S of the micro planepComprises the following steps:
wherein gamma is a reflection coefficient (dimensionless), β is a specular coefficient (dimensionless), the diffuse reflection coefficient is equal to gamma (1-gamma β), ScThe projection area of the surface element in the incident direction is as follows:
Sc＝A cosθ
in the formula, a is the actual illuminated area of the surface element, and the ratio of the light pressure area of the surface element to the projection area is expressed by a light pressure coefficient factor k, that is:
where the magnitude of k is related to the optical properties of the bin and the orientation of the bin.
On the basis of a calculation formula of sunlight pressure on a micro-plane, for a spacecraft with various surface materials, three-dimensional and non-planar, the reflection coefficient of a surface element made of the i-th material is set to be gammaiCoefficient of mirror surface of gammaiCoefficient factor k is k (gamma)i,βiθ) that the projected area S expressed in the form of integral can be obtainedcComprises the following steps:
Sc＝∫cosθds
area of light pressure SpCan be expressed as:
Sp＝∫k(γi,βi,θ)cosθds
theoretically, the light pressure area of any target can be calculated according to the formula, but in an actual situation, the surface of a spacecraft model with a complex shape is difficult to describe by an analytic expression, and a shielding relation exists between a star body and a solar cell panel in the solar irradiation direction under different orbital flight attitudes, so that the light pressure area of the spacecraft is calculated, the target is generally required to be subdivided into a plurality of micro plane surface elements, then the mutual shielding relation of the micro surface elements in the illumination direction is judged, the micro surface elements shielded by other surface elements are removed, then the effective light pressure area of the remaining micro surface elements is calculated, and finally the light pressure area of the whole target is obtained through accumulation calculation.
In the process, the model file can be obtained after being processed through three-dimensional modeling, but the judgment process of the mutual occlusion relation of the surface elements is complex, multiple times of circulating calculation and comparison are needed, and the calculation precision and the calculation efficiency are difficult to obtain.
In order to calculate the light pressure area of a complex target and solve the contradiction between calculation accuracy and efficiency and surface element shielding judgment, the invention adopts a light pressure area calculation method based on target characteristics, corresponding calculation tool software is developed by utilizing an open graphics library OpenGL, FIG. 2 is a flow chart of a processing method of the light pressure area of a target spacecraft according to an optional embodiment of the invention, and as shown in FIG. 2, the method comprises the following contents in the implementation process: the method comprises the steps of three-dimensional modeling of the spacecraft, obtaining optical characteristic parameters of materials, programming and reading a spacecraft model file, orthogonal projection and blanking processing, setting an illumination model, performing illumination calculation, calculating the light pressure area of each effective surface element, calculating the light pressure area of the whole spacecraft and the like.
The specific implementation steps are as follows:
step 1: and (4) three-dimensional modeling of the spacecraft. Establishing a three-dimensional model according to target characteristic information such as the structure, the shape, the size, the surface material and the like of the spacecraft and carrying out corresponding processing;
as an alternative embodiment, a target three-dimensional model is built according to target characteristic information and basic characteristics of the structure, the shape, the size, the surface material and the like of the spacecraft. The method comprises the steps of utilizing three-dimensional modeling software 3DMAX to carry out geometric shape modeling on the spacecraft with the complex structure, establishing a target three-dimensional model containing material information through modification and editing, wherein the file format is 3DS, using different color types to distinguish different types of materials such as a star coating and a solar cell of the spacecraft, and setting the scattering characteristic of the materials to a light source to be diffuse reflection. The orbit coordinate system is mainly used in the modeling process (RTNCoordinate system), spacecraft body coordinate system, and pitch angle α, yaw anglebAngle of rollcAnd the solar panel turning angle tau to describe the target attitude, using azimuth and elevation
The solar incident angle is described. FIG. 3 is a schematic diagram of a spacecraft coordinate system and a sunlight incident angle according to an embodiment of the invention, as shown in FIG. 3, a target object coordinate systemo-xyzAt the initial state (each attitude angle is 0 °) andRTNthe coordinate systems coincide.
Step 2: obtaining information such as reflection coefficients and mirror coefficients of different surface materials of the spacecraft on sunlight;
as an optional embodiment, information such as reflection coefficients, specular reflection coefficients and diffuse reflection coefficients of different surface materials of the spacecraft on sunlight is obtained through experimental measurement and data processing.
And step 3: programming and reading a spacecraft model file, editing, controlling and drawing a three-dimensional model, reading and calculating information such as positions of all points on the surface of a target, normal directions, surface element areas and the like;
as an optional embodiment, computing tool software developed based on OpenGL is used to read the processed 3DS format three-dimensional model file, so as to implement editing, controlling and drawing of the model. In order to calculate the light pressure area of a complex target, information such as the position of each point on the surface of the target, the direction of an external normal, the surface element area, and the material type represented by the surface element needs to be read and used.
The 3DS file format is a hierarchical structure composed of blocks, and the basic block, i.e., the main block, includes three versions, edit information, and key frame information. The primary block in each basic block contains various information. In the method, data such as light source information and camera information are not required, so that the 3DS file data needing to be processed in an important mode comprises material information, vertex information, surface element information and the like of the target object. The method comprises the steps of reading a 3DS file into a custom data structure, then drawing a target model by utilizing OpenGL, and mainly reading operation comprises the following steps: firstly, defining a series of data structures, such as object materials, material libraries, position vectors and the like; reading the 3DS file and storing the file in an object; defining classes for processing various objects.
And 4, step 4: orthogonal projection and blanking processing. Performing rotation transformation according to the target posture by adopting an orthogonal projection mode, starting a depth cache and performing depth test to complete target blanking and display of a visible part;
as an optional embodiment, the method utilizes the characteristic that the depth value between each pixel and a viewpoint is stored in the OpenGL depth cache, projects a three-dimensional target to a two-dimensional screen in an orthogonal projection mode, performs rotation transformation on the target according to the target attitude angle at the current moment, then starts the depth cache and performs depth test, and completes target blanking and display of a visible part at the same time, thereby effectively improving the processing speed. In the orthogonal projection mode, the size of the target displayed on the screen is independent of the actual distance of the target, and the larger number of target pixels means that the target surface is divided more finely, i.e. the actual area represented by each pixel is smaller.
And 5: adopting a Phong illumination model, performing illumination processing, and reading color values in a frame cache to obtain included angles between each effective surface element and incident light and surface element material types;
as an optional embodiment, the Phong illumination model is adopted in the method, the light source is an unattenuated directional light source, the ambient light and specular reflection light source are 0, the RGB color component value of the diffuse reflection light source is (1, 1, 1), parameters such as an included angle between a surface element of each effective surface element and incident light and the type of a material represented by the surface element are obtained by reading and calculating the color value of the pixel surface element in the frame buffer after rendering processing, and the light pressure area of each surface element is calculated, and finally the light pressure area of the whole target is calculated by accumulation.
Setting a screen display areamLine and firstnThe pixel element of the row is P'mnThe actual bin P of the target surface represented bymnHas an area of smn，PmnThe included angle between the normal direction of (A) and the incident direction of sunlight is thetamnPost OpenGL rendering pixel panel P'mnIs proportional to the angle thetamnCosine value of (A), from which bin P is derivedmnThe projected area in the direction of illumination is:
S'mn＝smncosθmn
step 6: calculating the light pressure area of each effective surface element according to an analytical light pressure model formula and by combining the related parameter information obtained in the previous step;
as an alternative embodiment, the light pressure area of the bin in the illumination direction is:
Smn＝k(γmn,βmn,θmn)smncosθmn
wherein, k (γ)mn,βmn,θmn) Is a bin PmnScale factor of type of material, S'mnI.e. the actual area represented by a single screen pixel, is related to the parameters of the orthographic projection model, SmnThe physical area can be calculated from the actual physical dimensions represented by the height and width of the display window. The light pressure coefficient factor k represents the ratio of the light pressure area of the surface element to the projection area, namely:
and 7: and calculating the algebraic sum of the light pressure areas of the effective surface elements to obtain the light pressure area of the whole target. And calculating the light pressure area of the target with the complex structure under different conditions by changing the target posture and the light source position, namely the illumination direction.
As an alternative embodiment, by calculating the algebraic sum of the light pressure area and the projected area of each effective surface element, the light pressure area and the projected area of the whole target can be obtained, as shown in the following formula:
Sp＝∑Smn，Sc＝∑S'mn
the light pressure area of the complex structure target under different conditions can be obtained by randomly changing the target posture and the light source position, namely the illumination direction.
Because the blanking processing speed of the target model and the reading speed of the pixel colors in the frame buffer are high, the calculation speed of the method is high, the calculation time is less than 0.05s each time, and the method can be used for the occasion of calculating the light pressure area in real time in the flight test task of the spacecraft. In order to test the accuracy of the light pressure area calculation method, comparison verification is carried out by taking a cuboid as a target. Fig. 4 is a schematic diagram of sunlight pressure applied to a rectangular parallelepiped according to an embodiment of the present invention, as shown in fig. 4, assuming that the length of the rectangular parallelepiped is l, the width is w, and the height is h, the rectangular parallelepiped rotates clockwise around the oy axis of the coordinate system o-xyz, the rotation angle is represented by θ (corresponding to yaw rotation of the spacecraft body), and the incident direction of sunlight is the same as the negative direction of the ox axis. Fig. 4 shows the attitude when θ is 0 °. For any rotation angle theta, the projection area S of the cuboid in the incident directioncComprises the following steps:
Sc＝hl·|cosθ|+wh·|sinθ|
light pressure area S of cuboid in illumination directionpComprises the following steps:
the light pressure area S of the cuboid can be calculated according to the formulapAnd the projected area ScAnd the ratio k thereof.
The target characteristic parameter of the cuboid is ① geometric dimensionl＝1.5m，w＝1.0m、h2.0m, ② surface material single, material reflection coefficientγ0.5, mirror surface coefficientβ＝0.2。
Is provided with a cuboidThe theoretical value of the light pressure area is SpTheoretically, the simulation calculation result is SpSimulation, the absolute deviation between the simulated value and the theoretical value is:
ΔSp＝Sp simulation-STheory of p
Relative deviation of simulated values of light pressure areapComprises the following steps:
p＝ΔSp/Stheory of p×100％
FIG. 5 is a schematic diagram of simulated values of light pressure area and relative deviation of a rectangular parallelepiped according to an embodiment of the present invention, as shown in FIG. 5, when the rotation angle is measuredθWhen the change is from 0 degree to 180 degrees and the change interval is 1 degree, the light pressure area simulation value of the cuboid and the relative deviation thereof are obtained by the method.
Through comparison, the relative deviation between the simulated value of the light pressure area of the cuboid and the theoretical value is less than 0.3 percent, and the absolute deviation is less than 0.01m2And the actual requirements are met.
Example 2
According to another aspect of the embodiments of the present invention, there is also provided a device for processing the optical pressure area of a target spacecraft, fig. 6 is a schematic diagram of the device for processing the optical pressure area of a target spacecraft according to the embodiments of the present invention, and as shown in fig. 6, the device for processing the optical pressure area of a target spacecraft includes: a first determination module 62 and a second determination module 64. The processing device for the optical pressure area of the target spacecraft will be described in detail below.
A first determining module 62, configured to determine target parameters, where the target parameters at least include an effective surface element of the target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft, and an optical pressure coefficient factor; and a second determining module 64, connected to the first determining module 62, for determining the optical pressure area of the effective surface element of the target spacecraft according to the target parameter.
It should be noted that the above modules may be implemented by software or hardware, for example, for the latter, the following may be implemented: the modules can be located in the same processor; alternatively, the modules may be located in different processors in any combination.
It should be noted that the first determining module 62 and the second determining module 64 correspond to steps S102 to S104 in embodiment 1, and the modules are the same as the examples and application scenarios realized by the corresponding steps, but are not limited to the disclosure of embodiment 1. It should be noted that the modules described above as part of an apparatus may be implemented in a computer system such as a set of computer-executable instructions.
Optionally, the first determining module includes: the first acquisition unit is used for acquiring a three-dimensional model of the target spacecraft; the transformation unit is used for performing rotation transformation on the three-dimensional model according to the target attitude of the target spacecraft at the current moment; the projection unit is used for projecting the three-dimensional model after the rotation transformation onto a two-dimensional screen; the blanking unit is used for carrying out blanking processing on the three-dimensional model projected onto the two-dimensional screen; the rendering unit is used for performing illumination rendering on the three-dimensional model subjected to blanking processing; and the first determining unit is used for determining an effective surface element of the target spacecraft in the target parameters according to the surface element parameters of the three-dimensional model after illumination rendering.
Optionally, before obtaining the three-dimensional model of the target spacecraft, the apparatus further includes: the building module is used for building a three-dimensional model of the target spacecraft according to target characteristics of the target spacecraft, wherein the target characteristics at least comprise structure, appearance, size and surface material.
Optionally, the building module includes: and the distinguishing unit is used for distinguishing the surface material in the target characteristic of the target spacecraft by using different colors, wherein the scattering characteristic of the surface material to the target light source is diffuse reflection.
Optionally, the first determining module includes: the second determining unit is used for determining the display size of the effective surface element of the target spacecraft on the two-dimensional screen; and the obtaining unit is used for obtaining the physical area of the effective surface element of the target spacecraft according to the actual physical scale corresponding to the display size.
Optionally, the first determining module includes: the second acquisition unit is used for acquiring material optical characteristic parameters of an effective surface element of the spacecraft, wherein the material optical characteristic parameters at least comprise a reflection coefficient, a specular reflection coefficient and a diffuse reflection coefficient of the effective surface element of the spacecraft on sunlight; and the third determining unit is used for determining the optical pressure coefficient factor of the effective surface element according to the optical characteristic parameter of the material.
Optionally, the second determining module includes: the fourth determining unit is used for determining the projection area of the effective surface element of the target spacecraft according to the included angle between the effective surface element of the target spacecraft and the incident light and the physical area of the effective surface element of the target spacecraft; and the fifth determining unit is used for determining the light pressure area of the effective surface element of the target spacecraft according to the projection area of the effective surface element of the target spacecraft and the light pressure coefficient factor of the effective surface element of the target spacecraft.
Optionally, the target spacecraft includes at least a plurality of effective bins, and the apparatus further includes: the third determining module is used for sequentially determining the light pressure areas of the plurality of effective surface elements; and the obtaining module is used for accumulating and summing the light pressure areas of the effective surface elements to obtain the light pressure area of the effective surface element of the whole target spacecraft.
Example 3
According to another aspect of the embodiments of the present invention, there is also provided a computer-readable storage medium, which includes a stored program, wherein when the program runs, the apparatus on which the computer-readable storage medium is located is controlled to execute the method for processing the optical pressure area of the target spacecraft described in any one of the above.
Example 4
According to another aspect of the embodiments of the present invention, there is also provided a processor for executing a program, where the program executes a method for processing a light pressure area of a target spacecraft according to any one of the above methods.
The above-mentioned serial numbers of the embodiments of the present invention are merely for description and do not represent the merits of the embodiments.
In the above embodiments of the present invention, the descriptions of the respective embodiments have respective emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments.
In the embodiments provided in the present application, it should be understood that the disclosed technology can be implemented in other ways. The above-described embodiments of the apparatus are merely illustrative, and for example, the division of the units may be a logical division, and in actual implementation, there may be another division, for example, multiple units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection through some interfaces, units or modules, and may be in an electrical or other form.
The 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 units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
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 may be embodied in the form of a software product, which is stored in a storage medium and includes 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 Read-Only Memory (ROM), a Random Access Memory (RAM), a removable hard disk, a magnetic or optical disk, and other various media capable of storing program codes.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (11)
1. A method for processing the optical pressure area of a target spacecraft is characterized by comprising the following steps:
determining target parameters, wherein the target parameters at least comprise an effective surface element of a target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft and a light pressure coefficient factor;
and determining the light pressure area of the effective surface element of the target spacecraft according to the target parameters.
2. The method of claim 1, wherein determining the effective bin of the target spacecraft in the target parameters comprises:
acquiring a three-dimensional model of the target spacecraft;
performing rotation transformation on the three-dimensional model according to the target attitude of the target spacecraft at the current moment;
projecting the three-dimensional model after rotation transformation onto a two-dimensional screen;
blanking the three-dimensional model projected onto the two-dimensional screen;
performing illumination rendering on the three-dimensional model subjected to blanking processing;
and determining an effective surface element of the target spacecraft in the target parameters according to the surface element parameters of the three-dimensional model after illumination rendering.
3. The method according to claim 1, wherein prior to obtaining the three-dimensional model of the target spacecraft, the method further comprises:
and constructing a three-dimensional model of the target spacecraft according to the target characteristics of the target spacecraft, wherein the target characteristics at least comprise structure, appearance, size and surface material.
4. The method of claim 3, wherein constructing the three-dimensional model of the target spacecraft based on the target characteristics of the target spacecraft comprises:
and distinguishing surface materials in the target characteristics of the target spacecraft by using different colors, wherein the scattering characteristics of the surface materials to the target light source are diffuse reflection.
5. The method of claim 1, wherein determining the physical area of the active bins of the target spacecraft of the target parameters comprises:
determining the display size of the effective surface element of the target spacecraft on a two-dimensional screen;
and obtaining the physical area of the effective surface element of the target spacecraft according to the actual physical scale corresponding to the display size.
6. The method of claim 1, wherein determining an optical pressure coefficient factor for an active bin of the target spacecraft of a target parameter comprises:
acquiring material optical characteristic parameters of an effective surface element of the spacecraft, wherein the material optical characteristic parameters at least comprise a reflection coefficient, a specular reflection coefficient and a diffuse reflection coefficient of the effective surface element of the spacecraft on sunlight;
and determining the optical pressure coefficient factor of the effective surface element according to the optical characteristic parameters of the material.
7. The method according to any one of claims 1 to 6, wherein determining the optical pressure area of the active bin of the target spacecraft in dependence on the target parameter comprises:
determining the projection area of the effective surface element of the target spacecraft according to the included angle between the effective surface element of the target spacecraft and incident light and the physical area of the effective surface element of the target spacecraft;
and determining the light pressure area of the effective surface element of the target spacecraft according to the projection area of the effective surface element of the target spacecraft and the light pressure coefficient factor of the effective surface element of the target spacecraft.
8. The method according to any one of claims 1 to 6, wherein the target spacecraft comprises at least a plurality of active bins, the method further comprising:
sequentially determining the light pressure areas of a plurality of effective surface elements;
and accumulating and summing the light pressure areas of the effective surface elements to obtain the light pressure area of the effective surface element of the whole target spacecraft.
9. An apparatus for processing the optical pressure area of a target spacecraft, comprising:
the device comprises a first determination module, a second determination module and a third determination module, wherein the first determination module is used for determining target parameters, and the target parameters at least comprise an effective surface element of a target spacecraft, an included angle between the effective surface element of the target spacecraft and incident light, a physical area of the effective surface element of the target spacecraft and an optical pressure coefficient factor;
and the second determining module is used for determining the light pressure area of the effective surface element of the target spacecraft according to the target parameter.
10. A computer-readable storage medium, comprising a stored program, wherein the program, when executed, controls an apparatus on which the computer-readable storage medium is located to perform the method for processing an optical pressure area of a target spacecraft according to any one of claims 1 to 8.
11. A processor, characterized in that the processor is configured to run a program, wherein the program is configured to execute the method for processing the optical pressure area of a target spacecraft according to any one of claims 1 to 8 when running.
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