CN105183959A - Method for acquiring data transmission antenna shielding probability of satellite during in-orbit real-time transmission - Google Patents
Method for acquiring data transmission antenna shielding probability of satellite during in-orbit real-time transmission Download PDFInfo
- Publication number
- CN105183959A CN105183959A CN201510527488.8A CN201510527488A CN105183959A CN 105183959 A CN105183959 A CN 105183959A CN 201510527488 A CN201510527488 A CN 201510527488A CN 105183959 A CN105183959 A CN 105183959A
- Authority
- CN
- China
- Prior art keywords
- satellite
- antenna
- angle
- blocked
- sway
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Radio Relay Systems (AREA)
Abstract
The present invention relates to a method for acquiring a data transmission antenna shielding probability of a satellite during in-orbit real-time transmission. The method comprises the steps: firstly, calculating to obtain a ground flare angle of the satellite and a maximum side swing angle when a data transmission antenna is not shielded; secondly, establishing an STK simulation scene and drawing an area where the data transmission antenna can be shielded; thirdly, calculating a shielding probability by using an area ratio and an angle ratio; and finally, providing a formulation of a data transmission antenna shielding probability index according to the calculation result. According to the method provided by the present invention, a brand-new idea for analyzing the data transmission antenna shielding probability is provided, a new concept of area ratios and angle ratios is created, a method for calculating the data transmission antenna shielding probability by using the area ratios and the angle ratios is provided, the powerful two-dimensional and three-dimensional display functions of STK are combined together, and a very small amount of calculation is used for realizing analysis of the data transmission antenna shielding probability, so that the method is helpful for satellite users and satellite developers to evaluate and check the in-orbit working efficiency of a satellite, and provides an important basis for the satellite users and the satellite developers to formulate related indexes.
Description
Technical field
The invention belongs to spacecraft mission planning field, be specifically related to a kind of satellite number carried out in-orbit when passing in fact that obtains and pass the method that antenna blocks probability.
Background technology
Remote sensing satellite, particularly high resolving power earth observation Optical remote satellite, its duration of work will produce a large amount of view data.But be limited by the restriction of the aspects such as satellite volume, quality, power consumption, star being used for the amount of capacity of the solid-state memory (be called for short admittedly deposit) preserving data is subject to strict restriction.Therefore, adopt camera imaging, over the ground number biography antenna (passing antenna hereinafter referred to as number) to pass imaging pattern to the reality of land station's passback to come into one's own simultaneously.In order to ensure enough passback speed and transmission gain, requiring that number passes antenna in real biography process, realizing rotating by the driving of self servo control mechanism, allow antenna beam point to land station all the time.Because the imaging of high resolving power earth observation remote sensing satellite is substantially all carry out under attitude side-sway is biased offline mode, therefore the real mode of operation that passes also is all generally the real biography of side-sway.
In order to ensure the enough energy, satellite needs to install solar energy in large area windsurfing, and the incident angle according to sunshine rotates by windsurfing in satellite transit process, to improve charge efficiency.In order to prevent from affecting the working field of view over the ground of the equipment such as antenna, over the ground optical camera over the ground, windsurfing is often installed on the left and right sides of satellite, and its installation shaft is parallel to track system Y-axis, with plane-parallel, vertical with satellite transit direction, vertical with satellite orbit face.But when satellite is in the biased flight of wide-angle side-sway, windsurfing will carry out wide-angle deflection together along with celestial body.Because windsurfing installation shaft is parallel to track system Y-axis, then during side-sway, side windsurfing can be upturned away from direction, ground, and opposite side windsurfing can be bowed downwards near direction, ground.Near this side windsurfing on ground, likely can block by the logarithm Wave beam forming that passes antenna, make its cannot in real biography process " seeing " land station, thus real biography task cannot be completed.
Because satellite sailboard area is huge, and real biography of side-sway is the indispensable operation on orbit mode of high resolving power earth observation Optical remote satellite, and therefore eclipse phenomena is difficult to avoid completely.And from type design experience in the past, cannot be settled the matter once and for all by the optimization of the Configuration Design of satellite own.
Satellite user can accept the existence of eclipse phenomena, but it is low as far as possible to wish to block probability.Therefore need by means such as simulation analysis, the number calculated when satellite carries out that side-sway is real to be passed in-orbit passes antenna and blocks probability, and it can be used as satellite system index, and after satellite launch, period is examined by the method for long-time statistical in orbit.
Logarithm passed antenna to block the simulating analysis of probability comparatively inflexible in the past, and namely complete mechanicalization ground is according to satellite configuration design result, provides the largest enveloping condition that an antenna can not be blocked, and does not consider any other factors.Such result, cause analyzing out to block probability often very high, be not obviously inconsistent with real actual conditions in-orbit.
Summary of the invention
Technical matters to be solved by this invention is: overcome the deficiencies in the prior art, provides a kind of satellite number carried out in-orbit when passing in fact that obtains to pass the method that antenna blocks probability, according to the Configuration Design state of satellite, can calculate rapidly and block probability.
Technical scheme of the present invention is: a kind of satellite number carried out in-orbit when passing in fact that obtains passes the method that antenna blocks probability, and step is as follows:
1) obtain the maximum side-sway angle of satellite, and number passes antenna not by the maximum side-sway angle θ under circumstance of occlusion;
2) calculate the subtended angle over the ground obtaining satellite and count the maximum side-sway angle passing antenna and can not be blocked, judge whether maximum side-sway angle is greater than the maximum side-sway angle θ counting and pass antenna and can not be blocked, if step 1) in the satellite maximum side-sway angle that obtains be greater than step 2) in the number calculated pass the maximum side-sway angles that can not be blocked of antennas, then enter step 3); Otherwise show that number passes antenna and certainly can not be blocked, blocking probability is 0%, the number now obtained when satellite side-sway is real to be passed passes antenna and blocks probability level, and namely side-sway is real when passing, and number biography antenna can not be blocked;
3) in STK, draw the viewing area of satellite and land station;
4) required three-dimensional feature is set in STK
41) in STK, the angle that number passes antenna zero vector and satellite-land station's vector is drawn;
42) satellite body system YZ plane is set in STK;
5) number passes the region that may be blocked of antenna and is divided into two pieces, lays respectively at east side and west side that Satellite rolls off the production line, is defined as eastern section and west side that number passes the region that antenna may be blocked respectively; The side-sway angle arranging satellite in STK is the maximum positive side-sway angle that number biography antenna can not be blocked, and draws the eastern section that number passes the region that antenna may be blocked;
6) in STK, arrange the attitude of satellite is the maximum minus side pivot angle that number biography antenna can not be blocked, and draws the west section that number passes the region that antenna may be blocked;
7) number calculated when satellite side-sway is real to be passed passes antenna and blocks probability
71) acquisition area ratio is calculated
Determining step 6) number that obtains passes antennas and may to be blocked the eastern section in region and west section area, and the area calculating eastern section and region, west section accounts for the ratio of whole land station viewing area, and the computing formula obtaining area ratio is as follows:
Area ratio≤(eastern section area+west section area)/ground total area
72) acquisition angle ratio is calculated
Utilize step 1) in satellite maximum side-sway angle and step 2) in number pass the maximum side-sway angle that can not be blocked of antenna, calculate the maximum side-sway angle of maximum side-sway angle/satellite obtaining angle and can not be blocked than≤(satellite maximum side-sway angle-number passes the maximum side-sway angle that antenna can not be blocked)/satellite maximum side-sway angle=1-number biography antenna;
73) Probability p=area ratio * angle ratio≤(eastern section area+west section area)/ground total area * (1-number passes the maximum side-sway angle of maximum side-sway angle/satellite that antenna can not be blocked) is blocked in acquisition;
74) number now obtained when satellite side-sway is real to be passed passes antenna and blocks probability level, namely when satellite side-sway angle absolute value be no more than θ spend time, when side-sway passes in fact, number biography antenna can not be blocked, when satellite side-sway angle absolute value is spent more than θ, the probability that when side-sway passes in fact, number biography antenna is blocked is no more than p.
Step 2) subtended angle over the ground of Satellite and number pass the antenna maximum side-sway angle circular that can not be blocked and be:
Subtended angle=asin (earth radius/(satellite orbital altitude+earth radius))+surplus angle over the ground; Maximum side-sway angle=number that number biography antenna can not be blocked passes antenna by the subtended angle over the ground of the hard-over-satellite under circumstance of occlusion.
Step 3) in STK, draw the concrete grammar of the viewing area of satellite and land station as follows:
31) simulating scenes is set up;
32) satellite orbit is set up;
33) land station is set up;
34) earth station antenna is set up;
35) viewing area of satellite and land station is shown.
The present invention's advantage is compared with prior art:
(1) advantage that the present invention is maximum, block probability analysis method at traditional number biography antenna only to consider on the basis of satellite configuration design, satellite and land station's relative position relation are considered further, systematically analyze prerequisite condition element when blocking generation, make analysis result significantly close satellite real work state in-orbit;
(2) bright spot that the present invention is maximum is the concept creating area ratio and angle ratio.By area ratio, can the probability of first precondition---occlusion area---that blocks of more given generation antenna; By angle ratio, can the probability of another precondition---side-sway angle---that blocks of more given generation antenna.Area ratio is comprehensive with angle ratio, also just can provide the probability that number biography antenna blocks;
(3) the present invention is simple to operate, and the computing function utilizing STK powerful is completely as instrument, and calculated amount is very little, does not need programming, only needs to provide the input parameter carrying out simulation calculation.In analytic process, by manual fine-tuning scenario parameters continuous in STK and the satellitosis situation of change of observing in two-dimentional 3-D display frame, obtain analysis result;
(4) The present invention gives the formulation that a kind of new antenna blocks probability level, this formulation is for index formulation in the past, and it is more accurate to describe;
(5) the present invention has good general applicability.The present invention go for various have side-sway real pass on Gong can satellite carry out relevant simulation analysis, and in the development process of model of launching an artificial satellite, obtain checking.
Accompanying drawing explanation
Fig. 1 is the FB(flow block) that number of the present invention passes that antenna rotates planing method.
Embodiment
As shown in Figure 1, be the FB(flow block) of the inventive method, details are as follows for concrete steps:
1) obtain the maximum side-sway angle of satellite, and number passes antenna not by the hard-over under circumstance of occlusion
Satellite maximum side-sway angle, as one of most important system index of satellite, is proposed by satellite user, is the important input parameter of design of satellites.
Count and pass antenna by the hard-over under circumstance of occlusion, refer to when the rotation of number biography antenna is no more than this angle, in any case it rotates, all can not be blocked.This angle is larger, and the probability that number biography antenna is blocked is lower.This angle is only relevant to satellite configuration itself, is provided after completing satellite configuration design by satellite configuration design engineer.
Therefore, two angles that this step will obtain are all the input parameters will used as invention method.
2) calculate the subtended angle over the ground of satellite and count the maximum side-sway angle passing antenna and can not be blocked
21) subtended angle over the ground of satellite is calculated
The subtended angle over the ground of satellite, refers to the angle between satellite-the earth's core vector satellite-point of contact, earth's surface vector, is an acute angle.This angle is only relevant with satellite orbital altitude, and orbit altitude is higher, and subtended angle is less over the ground.
Computing formula is as follows:
Subtended angle over the ground
=asin (earth radius/(satellite orbital altitude+earth radius))
But consider earth surface characteristic, in conjunction with engineering experience in the past, General Requirements increases certain surplus angle on the basis of above-mentioned result of calculation, usually gets 2 ~ 3 degree.Then above-mentioned formula becomes:
Subtended angle over the ground
=asin (earth radius/(satellite orbital altitude+earth radius))+surplus angle
22) the maximum side-sway angle that number biography antenna can not be blocked is calculated
Number passes the maximum side-sway angle that antenna can not be blocked, and refers to when satellite side-sway is no more than this angle, and rotate in any case number passes antenna, its wave beam all can not be blocked.This angle is less than or equal to the maximum side-sway angle of satellite, and when its more close satellite maximum side-sway angle time, it will be lower that number passes the probability that antenna is blocked.
Computing formula is as follows:
Number passes the maximum side-sway angle that antenna can not be blocked
=number passes antenna not by the subtended angle over the ground of the hard-over-satellite under circumstance of occlusion
23) judge whether maximum side-sway angle is greater than the maximum side-sway angle counting and pass antenna and can not be blocked
If step 1) in " the satellite maximum side-sway angle " that obtain be greater than step 22) in " number passes the maximum side-sway angle that can not be blocked of antenna " of calculating, then enter step 3); Otherwise then mean that number passes antenna and certainly can not be blocked, blocking probability is 0%, directly enters step 8).
When blocking probability and being 0%, the number that can provide when satellite side-sway is real to be passed passes antenna and blocks probability level, as the system index of design of satellites.Its index formulation is as follows:
● when side-sway passes in fact, number biography antenna can not be blocked;
3) in STK, draw the viewing area of satellite and land station
According to the geographical location information of satellite orbit parameter and land station, drawn the viewing area of satellite and land station by STK software (SatelliteToolKit).STK be a aerospace Simulation analyze business software, there is two-dimentional three-dimensional visible interface, powerful, easy to operate, in the world and China's space industry all widely use.
In patent of the present invention to use be STK version be 8.1.The STK of different editions operationally can slightly distinguish.Due to the main contents of this and non-invention patent, do not repeat them here.The process obtaining satellite and land station viewing area with STK is as follows:
31) simulating scenes is set up
After opening STK software, the File-New on click tools hurdle, generates a simulating scenes.
32) satellite orbit is set up
Will set up satellite orbit in this step, its detailed process is as follows:
A. the Insert-New on click tools hurdle, selects Satellite in an open window, generates a new satellite.Select Cancel in an open window;
B. in the ObjectBrowser hurdle in left side, double-click the satellite of harsh one-tenth, open satellite setup of attribute window;
C. in setup of attribute window, click Basic-Orbit, open track and interface is set.In SemimajorAxis, insert the design load of satellite orbit semi-major axis, other adopts default value;
D. in setup of attribute window, click 2DGraphics-Pass, open two-dimentional window and interface is set.In VisibleSides, select Descending, namely only rail section falls in display.Hit OK closes window;
E. the satellite orbit just set up now can be seen in 2DGraphics interface;
F., in 3DGraphics interface, click the ViewFrom/To button of left side eye shape, open ViewFrom/ToforScenario1 window, in ViewFrom window, select the satellite just set up.Select the UnconstrainedRotation option of below, do not select Show " TrackBall " option.Hit OK closes window;
G. the dummy satellite just set up now can be seen in 3DGraphics.Mouse right and left key is utilized to get final product Scalable visual field or adjustment orientation, visual field;
33) land station is set up
Will set up land station in this step, its detailed process is as follows:
A. the Insert-New on click tools hurdle, selects Facility in an open window, generates a Ge Xin land station;
B. in the ObjectBrowser hurdle in left side, double-click the land station of harsh one-tenth, open land station's setup of attribute window;
C. in setup of attribute window, click Basic-Position, open earth station location and interface is set.In Latitude, Longitude and Altitude, insert the latitude of land station, longitude and height, other adopts default value.Hit OK.
D. the land station just set up now can be seen in 2DGraphics;
34) earth station antenna is set up
Will set up earth station antenna in this step, its detailed process is as follows:
A. the land station of harsh one-tenth is clicked
B. the Insert-New on click tools hurdle, selects Sensor in an open window, generates a new antenna;
C. in the ObjectBrowser hurdle in left side, double-click the antenna of harsh one-tenth, open antenna property and window is set;
D. in setup of attribute window, click Basic-Definition, open antenna basic setup window.In SensorType, select SimpleConic, the design load of earth station antenna visual field is set in ConeAngle.Hit OK;
35) viewing area of satellite and land station is shown
The viewing area of satellite and land station's (be in fact earth station antenna, hereafter all simplify acute pyogenic infection of finger tip with land station) will be shown in this step.Its detailed process is as follows:
A. in the ObjectBrowser hurdle in left side, double-click the antenna of harsh one-tenth, open antenna property and window is set;
B. in setup of attribute window, click 2DGraphics-Position, open a day line projection and window is set.In Projectto hurdle, select ObjectAltitude, in ProjectionAltitudeObject, select the satellite just now set up.Hit OK;
C. now can show the viewing area of satellite and land station in 2DGraphics interface, this region is a circle.
According to above step, the viewing area of satellite and land station can be drawn.Generally, according to crew station design requirement, when satellite is in this viewing area, earth station antenna can see satellite certainly; Meanwhile, according to design of satellites requirement, when satellite is in this viewing area, if do not consider, windsurfing blocks, then the number on satellite passes antenna also can see land station certainly.
4) three-dimensional features such as required vector, angle and plane are set in STK
STK software has powerful three dimensional display capabilities.This step adds the three-dimensional features such as vector, angle and the plane needed for Computer Aided Design by passing through in STK three-dimensional scenic, and the step come after for the inventive method is ready.Detailed process is as follows:
41) in STK, the angle that number passes antenna zero vector and satellite-land station's vector is drawn
The number that will draw in this step passes the angle of antenna zero vector and satellite-land station's vector, and its detailed process is as follows:
A. in STK, in ObjectBrowser hurdle, left side, click the satellite that will analyze, then up toolbar selects Satellite-VectorGeometry, open " VectorGeometryToolfor satellite name " window;
B. in an open window, right side CreateNewVector button is clicked.In an open window, a given vector name on Name hurdle; FixedinAxes is selected on Type hurdle; The Body (namely body coordinate system) of satellite is selected in ReferenceAxes; Cartesian is selected in Type; In X, Y, Z, fill out number pass the component of antenna zero vector under whole star body coordinate system, this component is design of satellites value, generally all can be designed to (0,0,1), and namely number passes when antenna is in zero-bit and points to substar along satellite+Z axis.Hit OK, sets up vector and completes.What set up here is that number passes antenna zero vector;
C. still in an open window, right side CreateNewVector button is clicked.A given vector name on Name hurdle; Displacement is selected on Type hurdle; The Center of satellite is selected at OriginPoint; The Center of land station is selected at DestinationPoint.Hit OK, sets up vector and completes.What set up here is satellite-land station's vector;
D. still in an open window, right side CreateNewAngle button is clicked.In an open window, a given angle name on Name hurdle; BetweenVectors is selected on Type hurdle; The number selecting step b to set up in FromVector passes antenna zero vector; The satellite selecting step c to set up in ToVector-land station's vector.Hit OK, sets up angle and completes.What set up here is the angle of above-mentioned two vectors;
E. click Close, close " VectorGeometryToolfor satellite name " window;
F., in STK, in ObjectBrowser hurdle, left side, double-click the satellite that will analyze, open satellite setup of attribute window;
G. in setup of attribute window, click 3DGraphics-Vector, in this interface, click Add, in the window newly opened, double-click two vector angles of satellite-land station's vector steps d foundation that step c sets up respectively, hit OK closes window.Here be that two vector angles that satellite-land station's vector steps d is set up set up by step c add in 3DGraphics;
H. satellite-land station's the vector finding step g to add in the Name hurdle in the 3DGraphics-Vector window upper left corner, clicks the square frame that it is corresponding in show hurdle, right side, there will be in square frame one little of hook.Here be that satellite-land station's vector that step g is added is shown in 3DGraphics;
I. the angle finding step g to add in the Name hurdle in the 3DGraphics-Vector window upper left corner, clicks the square frame that it is corresponding in show hurdle, right side, there will be in square frame one little of hook.Here be that the angle that step g is added is shown in 3D scene;
J. click the square frame on the left of ShowAngleValue hurdle on right side, there will be in square frame one little of hook.Here be that the angle value of the angle of step I display is shown in 3D scene;
K. hit OK.Now can show satellite-land station's vector in 3DGraphics, and number passes angle and the angle value thereof of antenna zero vector and satellite-land station's vector.
42) satellite body system YZ plane is set in STK
The satellite body system YZ plane that will draw in this step, its detailed process is as follows:
A. in STK, in ObjectBrowser hurdle, left side, click the satellite that will analyze, then up toolbar selects Satellite-VectorGeometry, open " VectorGeometryToolfor satellite name " window;
B. in an open window, right side CreateNewPlane button is clicked.In an open window, a given plane name on Name hurdle; Quadrant is selected on Type hurdle; YZ is selected in Quadrant hurdle; The Body (namely body coordinate system) of satellite is selected in ReferenceSystem.Hit OK, sets up plane and completes.What set up here is satellite body system YZ plane;
C. click Close, close " VectorGeometryToolfor satellite name " window;
D., in STK, in ObjectBrowser hurdle, left side, double-click the satellite that will analyze, open satellite setup of attribute window;
E. in setup of attribute window, click 3DGraphics-Vector, in this interface, click Add, in the window newly opened, double-click the satellite body system YZ plane that step b sets up, hit OK closes window.Here be that the satellite body system YZ plane that step b sets up is added in 3DGraphics;
F. the satellite body system YZ plane finding step e to add in the Name hurdle in the 3DGraphics-Vector window upper left corner, clicks the square frame that it is corresponding in show hurdle, right side, there will be in square frame one little of hook.Here be that the plane that step e adds is shown in 3DGraphics;
G. click the square frame on the left of TranslucentPlane hurdle on right side, there will be in square frame one little of hook.Here be that the plane that step f shows is shown as transparent in 3D scene.Transparency can be arranged by the Translucency on right side;
H. hit OK.Now can show satellite body system YZ plane in 3DGraphics.
5) in STK, the eastern section that number passes the region that antenna may be blocked is drawn
Utilize step 1) input parameter, step 2) result of calculation, step 3) viewing area and step 4) three-dimensional feature, number can be drawn pass the region that may be blocked of antenna on STK.Region herein, refers in particular to " in satellite and land station viewing area, number passes the region that antenna may be blocked ".
Content of operation in this step and satellite orbit fall rail Duan Shichuan or rail lift Duan Shichuan is relevant.Because the track of the Optical remote satellite of the current domestic overwhelming majority all designs according to falling rail Duan Shichuan, therefore this explanation is also described to fall rail section.The method of rail lift section, with to fall rail section basically identical, only need the sign adjusting side-sway angle, owing to using seldom, repeats no more in this explanation.
The region may blocked due to number biography antenna is divided into eastern section and west section, therefore carries out respectively describing.First be eastern section.Its detailed process is as follows:
51) in STK, arrange the attitude of satellite is the maximum positive side-sway angle that number biography antenna can not be blocked
Will arrange the attitude of satellite in this step is the maximum positive side-sway angle that number biography antenna can not be blocked, and its detailed process is as follows:
A., in STK, in ObjectBrowser hurdle, left side, double-click the satellite that will analyze, open satellite setup of attribute window;
B. in setup of attribute window, Basic-Attitude is clicked, in this interface, FixedinAxes is selected on first Type hurdle, " satellite name VVLH " is selected on ReferenceAxes hurdle, select YPRAngles on second Type hurdle, insert step 2 on Roll hurdle) in calculate " number passes the maximum side-sway angle that antenna can not be blocked " on the occasion of;
C. hit OK, now can see the deflection situation of the attitude of satellite in 3DGraphics.
52) display passes antenna and may to be blocked the eastern section in region
Detailed process is as follows:
A., in STK, the Start button on click tools hurdle, makes satellite orbit.Observe in 2DGraphics, until satellite flies in land station viewing area.DecreaseTimeStep button on click tools hurdle makes its travelling speed slow down.Observe in 3DGraphics, until step 41) " satellite-land station's vector " in-h be arranged in step 42) satellite body system YZ plane;
B. in ObjectBrowser hurdle, left side, double-click the satellite that will analyze, open satellite setup of attribute window.Basic-Orbit is clicked in setup of attribute window.Continuous adjustment RAAN parameter, has revised the Apply button in rear click interface at every turn, amendment is come into force; In 3DGraphics, observe step 41 while amendment) " number passes the angle angle value of antenna zero vector and satellite-land station's vector " in-j, until it equals step 1) in obtain " number pass antenna be not subject to circumstance of occlusion under hard-over ".It should be noted that the satellite orbit after amendment RAAN must ensure that satellite is in the east of land station;
C. constantly previous step 52 is repeated)-a and step 52)-b, satellite position in orbit and RAAN parameter are finely tuned, observe 3DGrahpics simultaneously, until above-mentioned two conditions are all met, that is: step 41) " satellite-land station's vector " in-h be arranged in step 42) satellite body system YZ plane; Step 41) " number passes the angle angle value of antenna zero vector and satellite-land station's vector " in-j equal step 1) in " counting the hard-over passing antenna and be not subject under circumstance of occlusion " of obtaining;
D., in 2DGraphics, under can seeing the star of satellite, the land station viewing area of circle be divide into two pieces by line tracking.Less that piece in east side is exactly " number pass antennas may be blocked the eastern section in region ".
6) in STK, the west section that number passes the region that antenna may be blocked is drawn
With step 5) method is similar, utilize step 1) input parameter, step 2) result of calculation, step 3) viewing area and step 4) three-dimensional feature, number can be drawn pass the west section in region that antenna may be blocked on STK.Its detailed process is as follows:
61) in STK, arrange the attitude of satellite is the maximum minus side pivot angle that number biography antenna can not be blocked
Will arrange the attitude of satellite in this step is the maximum minus side pivot angle that number biography antenna can not be blocked, and its detailed process is as follows:
A. in STK, in ObjectBrowser hurdle, left side, click the satellite that will analyze, copy, paste, by appearance satellite copied in ObjectBrowser hurdle;
What b. double-click will be analyzed copies satellite, opens satellite setup of attribute window;
C. in setup of attribute window, Basic-Attitude is clicked, in this interface, FixedinAxes is selected on first Type hurdle, " satellite name VVLH " is selected on ReferenceAxes hurdle, select YPRAngles on second Type hurdle, insert step 2 on Roll hurdle) in the negative value of " number passes the maximum side-sway angle that antenna can not be blocked " calculated;
D. hit OK, now can see the deflection situation copying the attitude of satellite in 3DGraphics.
62) display passes antenna and may to be blocked the west section in region
Detailed process is as follows:
A. in STK, the Start button on click tools hurdle, makes satellite orbit, observes in 2DGraphics, until it flies in land station viewing area.DecreaseTimeStep on click tools hurdle makes its travelling speed slow down.Observe in 3DGraphics, until step 41) " satellite-land station's vector " in-h be arranged in step 42) satellite body system YZ plane;
B. in ObjectBrowser hurdle, left side, double-click the satellite that will analyze, open satellite setup of attribute window.Basic-Orbit is clicked in setup of attribute window.Continuous adjustment RAAN parameter, has revised the Apply button in rear click interface at every turn, amendment is come into force; In 3DGraphics, observe step 41 while amendment) " number passes the angle angle value of antenna zero vector and satellite-land station's vector " in-j, until it equals step 1) in obtain " number pass antenna be not subject to circumstance of occlusion under hard-over ".It should be noted that the track after amendment RAAN must ensure that satellite is in the west of land station;
C. constantly previous step 62 is repeated)-a and step 62)-b, satellite position in orbit and RAAN parameter are finely tuned, until above-mentioned two conditions are all met, that is: step 41) " satellite-land station's vector " in-h be arranged in step 42) satellite body system YZ plane; Step 41) " number passes the angle angle value of antenna zero vector and satellite-land station's vector " in-j equal step 1) in " counting the hard-over passing antenna and be not subject under circumstance of occlusion " of obtaining;
D. enter 2DGraphics, under can seeing the star of satellite, the land station viewing area of circle be divide into three pieces by line tracking.Less that piece in east side is exactly step 52) " number pass antennas may be blocked the eastern section in region " that obtain in-d.Less that piece in west side is exactly " number pass antennas may be blocked the west section in region ".Two pieces of area sums, are " number pass antenna may be blocked region ".
7) number calculated when satellite side-sway is real to be passed passes antenna and blocks probability
In step 5) with step 6) terminate after, obtain " number pass antenna may be blocked region ", be divided into eastern section and west section.Utilize this result and step 1 below) in " satellite maximum side-sway angle " and step 2) in " number passes the maximum side-sway angle that can not be blocked of antenna ", the number calculated when satellite side-sway is real to be passed passes antenna and blocks probability.Its concrete steps are as follows:
71) reference area ratio
In 2DGraphics, observe step 62) eastern section of " number pass antenna may be blocked region " that obtains of-d and west section.The area in visual estimation eastern section and region, west section accounts for the ratio of whole land station viewing area, obtains area ratio.
Satellite is only being in step 62) in-d " number pass antenna may be blocked region " that obtain time, side-sway is real pass time just likely there is the situation that number biography antenna is blocked; Meanwhile, satellite is only in step 3) in just can carry out that side-sway is real to be passed in " satellite and the land station viewing area " that calculate.Therefore area ratio is defined as the ratio of above-mentioned two region areas.
Computing formula is as follows:
Area ratio
≤ (eastern section area+west section area)/total area
72) angle ratio is calculated
Utilize step 1) in satellite maximum side-sway angle and step 2) in " number passes the maximum side-sway angle that can not be blocked of antenna ", obtain angle ratio.
Satellite only exceedes step 2 at side-sway angle) in " number passes the maximum side-sway angle that can not be blocked of antenna " time, side-sway is real pass time just likely there is number and pass the situation that antenna is blocked; Meanwhile, the side-sway angle that satellite side-sway is real when passing can not exceed step 1) in " the maximum side-sway angle of satellite ".Therefore angle ratio is defined as both differences and the ratio at " the maximum side-sway angle of satellite ".
Computing formula is as follows:
Angle ratio
/ maximum side-sway angle ,≤(maximum side-sway angle-can not be blocked maximum side-sway angle)
The maximum side-sway angle that=1-can not be blocked/maximum side-sway angle
73) obtain and block probability
Utilize area ratio and angle ratio, the number can obtained when satellite side-sway is real to be passed passes antenna and blocks probability.
Computing formula is as follows:
Block probability
=area ratio * angle ratio
≤ (eastern section area+west section area)/total area
* (the maximum side-sway angle that 1-can not be blocked/maximum side-sway angle)
Above-mentioned formula calculates, and number when being exactly satellite side-sway reality biography passes antennas and blocks probability, and its result of calculation is not an exact value determined, but is less than a value.That is, the result calculated provides a maximal value of blocking probability.
74) number provided when satellite side-sway is real to be passed passes antenna and blocks probability level
Now, the number that can provide when satellite side-sway is real to be passed passes antenna and blocks probability level, as the system index of design of satellites.Its index formulation is as follows:
● satellite side-sway angle absolute value is no more than " XX " when spending, and side-sway is real when passing, and number passes antenna can not be blocked;
● satellite side-sway angle absolute value exceedes " XX " when spending, and side-sway is real when passing, and number passes that probability that antenna blocked is no more than " YY ".
XX and YY is herein respectively by step 2 in invention method) and step 7)-3 to calculate.
8) net result is exported
According to analysis before, step 8) net result can by step 2) directly arrive, also can by step 2) ~ step 7) obtain gradually, depend on step 2) Rule of judgment whether meet.
Case study on implementation
Suppose that simulated conditions is as follows:
● satellite transit is in 600km orbit altitude
According to the inventive method, computation process is as follows:
1) obtain the maximum side-sway angle of satellite, and number passes antenna not by the hard-over under circumstance of occlusion
In the implementation case, maximum for satellite side-sway angle and number are passed antenna and are not set to respectively by the hard-over under circumstance of occlusion:
The maximum side-sway angle of satellite: 35 °
Number passes antenna not by the hard-over under circumstance of occlusion: 90 °
Above-mentioned parameter is the default provided according to the experience in design of model in the past.In actual design, two parameter all should be learnt from else's experience the real data of strict demonstration and design.
2) calculate the subtended angle over the ground of satellite and count the maximum side-sway angle passing antenna and can not be blocked
21) subtended angle over the ground of satellite is calculated
Earth radius gets 6378km, and orbit altitude is 600km.Then can according to formulae discovery subtended angle over the ground.Surplus angle is taken as 3 °.Result is:
Subtended angle over the ground
=asin (earth radius/(satellite orbital altitude+earth radius))-surplus angle
＝asin(6378km/(6378km+600km))-3°
≈66°-3°
＝63°
22) the maximum side-sway angle that number biography antenna can not be blocked is calculated
By step 1) to obtain " number passes antenna by the hard-over under circumstance of occlusion " be 90 °, then can pass antenna according to formulae discovery number by the maximum side-sway angle under circumstance of occlusion not be:
Number passes the maximum side-sway angle that antenna can not be blocked
=number passes antenna not by the subtended angle over the ground of the hard-over-satellite under circumstance of occlusion
＝90°-63°
＝27°
23) judge whether maximum side-sway angle is greater than the maximum side-sway angle counting and pass antenna and can not be blocked
From step 1), the maximum side-sway angle of satellite is 35 °.
From step 22), the maximum side-sway angle that number biography antenna can not be blocked is 27 °.
Therefore, whether maximum side-sway angle is greater than the maximum side-sway angle that number biography antenna can not be blocked, then directly can not enter step 8), should step 3 be entered).
3) in STK, draw the viewing area of satellite and land station
The process obtaining satellite and land station viewing area with STK is as follows:
31) simulating scenes is set up
After opening STK software, the File-New on click tools hurdle, generates a simulating scenes.The scene of acquiescence is called Scenario1;
32) satellite orbit is set up
According to above-mentioned steps, set up satellite orbit, wherein SemimajorAxis inserts the design load of semi-major axis: 6378km+600km=6978km.Satellite name is the Satellite1 that software default is given.
33) land station is set up
According to above-mentioned steps, set up land station, wherein Latitude, Longitude and Altitude insert (0deg, 0deg, 0km) successively.Land station's name is the Facility1 that software default is given.Generate the land station that is positioned at east longitude 0 degree, north latitude 0 degree, sea level elevation 0km.
34) earth station antenna is set up
According to above-mentioned steps, set up earth station antenna, wherein ConeAngle inserts 85deg.Earth station antenna name is the Sensor1 that software default is given.Generate the earth station antenna that a field range is semi-cone angle 85 degree, that is the ground minimum elevations of this land station to satellite is 5 degree.
35) viewing area of satellite and land station is shown
According to above-mentioned steps, draw the viewing area of satellite Satellite1 and earth station antenna Sensor1.
4) three-dimensional features such as required vector, angle and plane are set in STK
41) in STK, the angle that number passes antenna zero vector and satellite-land station's vector is drawn
The number that will draw in this step passes the angle of antenna zero vector and satellite-land station's vector, and its detailed process is as follows:
A. in STK, in ObjectBrowser hurdle, left side, click Satellite1, then up toolbar selects Satellite-VectorGeometry, open " VectorGeometryToolforSatellite1 " window;
B. in an open window, right side CreateNewVector button is clicked.In an open window, in Name hurdle, LingWeiShiLiang is named to vector; FixedinAxes is selected on Type hurdle; The Body (namely body coordinate system) of satellite Satellite1 is selected in ReferenceAxes; Cartesian is selected in Type; Fill out in X, Y, Z (0,0,1), namely point to substar along satellite+Z axis.Hit OK, sets up vector and completes.What set up here is that number passes antenna zero vector LingWeiShiLiang;
C. still in an open window, right side CreateNewVector button is clicked.DiMianZhanShiLiang is named to vector on Name hurdle; Displacement is selected on Type hurdle; The Center of satellite Satellite1 is selected at OriginPoint; The Center of land station Facility1 is selected at DestinationPoint.Hit OK, sets up vector and completes.That set up here is satellite-land station vector DiMianZhanShiLiang;
D. still in an open window, right side CreateNewAngle button is clicked.In an open window, JiaJiao is named on Name hurdle to angle; BetweenVectors is selected on Type hurdle; In FromVector, select the number just now set up to pass antenna zero vector LingWeiShiLiang; Satellite-land station vector the DiMianZhanShiLiang just now set up is selected in ToVector.Hit OK, sets up angle and completes.That set up here is the angle JiaJiao of above-mentioned two vectors;
E. click Close, close " VectorGeometryToolforSatellite1 " window;
F. in STK, in ObjectBrowser hurdle, left side, double-click Satellite1, open satellite setup of attribute window;
G. in setup of attribute window, click 3DGraphics-Vector, in this interface, click Add, in the window newly opened, double-click the satellite-land station vector DiMianZhanShiLiang and two vector angle JiaJiao that just now set up, hit OK closes window.Here be that the two vector angle JiaJiao that the satellite-land station vector DiMianZhanShiLiang of step c foundation and steps d set up are added in 3DGraphics;
H. in the Name hurdle in the 3DGraphics-Vector window upper left corner, find the satellite-land station vector DiMianZhanShiLiang just now added, click the square frame that it is corresponding in show hurdle, right side, there will be in square frame one little of hook.Here be that satellite-land station vector DiMianZhanShiLiang that step g is added is shown in 3DGraphics;
I. in the Name hurdle in the 3DGraphics-Vector window upper left corner, find the angle JiaJiao just now added, click the square frame that it is corresponding in show hurdle, right side, there will be in square frame one little of hook.Here be that the angle JiaJiao that step g is added is shown in 3D scene;
J. click the square frame on the left of ShowAngleValue hurdle on right side, there will be in square frame one little of hook.Here be that the angle value of the angle JiaJiao of step I display is shown in 3D scene;
K. hit OK, now can show satellite-land station vector DiMianZhanShiLiang in 3DGraphics, and number passes angle JiaJiao and the angle value thereof of antenna zero vector LingWeiShiLiang and satellite-land station vector DiMianZhanShiLiang.
42) satellite body system YZ plane is set in STK
The satellite body system YZ plane that will draw in this step, its detailed process is as follows:
A. in STK, in ObjectBrowser hurdle, left side, click the satellite that will analyze, then up toolbar selects Satellite-VectorGeometry, open " VectorGeometryToolforSatellite1 " window;
B. in an open window, right side CreateNewPlane button is clicked.In an open window, YZ-PingMian is named on Name hurdle to plane; Quadrant is selected on Type hurdle; YZ is selected in Quadrant hurdle; The Body (namely body coordinate system) of satellite Satellite1 is selected in ReferenceSystem.Hit OK, sets up plane and completes.That set up here is satellite body system YZ plane YZ-PingMian;
C. click Close, close " VectorGeometryToolforSatellite1 " window;
D., in STK, in ObjectBrowser hurdle, left side, double-click the satellite that will analyze, open satellite setup of attribute window;
E. in setup of attribute window, click 3DGraphics-Vector, in this interface, click Add, in the window newly opened, double-click the satellite body system YZ plane YZ-PingMian just now set up, hit OK closes window.Here be that the satellite body system YZ plane YZ-PingMian that step b sets up is added in 3DGraphics;
F. in the Name hurdle in the 3DGraphics-Vector window upper left corner, find the satellite body system YZ plane YZ-PingMian just now added, click the square frame that it is corresponding in show hurdle, right side, there will be in square frame one little of hook.Here be that the plane that step e adds is shown in 3DGraphics;
G. click the square frame on the left of TranslucentPlane hurdle on right side, there will be in square frame one little of hook.Here be that the plane that step f shows is shown as transparent in 3D scene.Transparency is set to 80% by the Translucency on right side;
H. hit OK.Now can show satellite body system YZ plane YZ-PingMian in 3DGraphics.
5) in STK, the eastern section that number passes the region that antenna may be blocked is drawn
Utilize step 1) input parameter, step 2) result of calculation, step 3) viewing area and step 4) three-dimensional feature, number can be drawn pass the region that may be blocked of antenna on STK.Region herein, refers in particular to " in satellite and land station viewing area, number passes the region that antenna may be blocked ".
First be eastern section.Its detailed process is as follows:
51) in STK, arrange the attitude of satellite is the maximum positive side-sway angle that number biography antenna can not be blocked
Will arrange the attitude of satellite in this step is the maximum positive side-sway angle that number biography antenna can not be blocked, and its detailed process is as follows:
A. in STK, in ObjectBrowser hurdle, left side, double-click Satellite1, open satellite setup of attribute window;
B. in setup of attribute window, Basic-Attitude is clicked, in this interface, FixedinAxes is selected on first Type hurdle, " satellite name VVLH " is selected on ReferenceAxes hurdle, select YPRAngles on second Type hurdle, insert step 2 on Roll hurdle) in the number calculated pass the maximum side-sway angle that antennas can not be blocked on the occasion of 27deg;
C. hit OK, now can see the deflection situation of the attitude of satellite in 3DGraphics.
52) display passes antenna and may to be blocked the eastern section in region
Detailed process is as follows:
A., in STK, the Start button on click tools hurdle, makes satellite Satellite1 orbit.Observe in 2DGraphics, until satellite Satellite1 flies in land station Facility1 viewing area.DecreaseTimeStep on click tools hurdle makes its travelling speed slow down.Observe in 3DGraphics, until satellite-land station vector DiMianZhanShiLiang is positioned at satellite body system YZ plane YZ-PingMian.
B. in ObjectBrowser hurdle, left side, double-click Satellite1, open satellite setup of attribute window.Basic-Orbit is clicked in setup of attribute window.Continuous adjustment RAAN parameter, has revised the Apply button in rear click interface at every turn, amendment is come into force; While amendment, in 3DGraphics, observed number passes the angle value of the angle JiaJiao of antenna zero vector LingWeiShiLiang and satellite-land station vector DimianZhanShiLiang, until it equals step 1) middle " number passes antenna not by the hard-over under circumstance of occlusion " obtained---90 °.It should be noted that the satellite orbit after amendment RAAN must ensure that satellite Satellite1 is in the east of land station Facility1;
C. previous step 52 is repeated)-a and step 52)-b, satellite position in orbit and RAAN parameter are finely tuned, observe 3DGrahpics simultaneously, until above-mentioned two conditions are all met, that is: satellite-land station vector DiMianZhanShiLiang is positioned at satellite body system YZ plane YZ-PingMian; The angle JiaJiao angle value that number passes antenna zero vector LingWeiShiLiang and satellite-land station vector DimianZhanShiLiang equals step 1) middle " number passes antenna by the hard-over under circumstance of occlusion " obtained---90 °.
D., in 2DGraphics, under can seeing the star of satellite, the land station viewing area of circle be divide into two pieces by line tracking.Less that piece in east side is exactly " number pass antennas may be blocked the eastern section in region ".
6) in STK, the west section that number passes the region that antenna may be blocked is drawn
With step 5) method is similar, utilize step 1) input parameter, step 2) result of calculation, step 3) viewing area and step 4) three-dimensional feature, number can be drawn pass the west section in region that antenna may be blocked on STK.Its detailed process is as follows:
61) in STK, arrange the attitude of satellite is the maximum minus side pivot angle that number biography antenna can not be blocked
Will arrange the attitude of satellite in this step is the maximum minus side pivot angle that number biography antenna can not be blocked, and its detailed process is as follows:
A. in STK, in ObjectBrowser hurdle, left side, click Satellite1, copy, paste, by satellite Satellite2 that appearance one copies in ObjectBrowser hurdle;
B. double-click Satellite2, open satellite setup of attribute window;
C. in setup of attribute window, Basic-Attitude is clicked, in this interface, FixedinAxes is selected on first Type hurdle, " Satellite2VVLH " is selected on ReferenceAxes hurdle, select YPRAngles on second Type hurdle, insert step 2 on Roll hurdle) in the negative value-27deg of " number passes the maximum side-sway angle that antenna can not be blocked " that calculates;
D. hit OK, now can see the deflection situation of Satellite2 attitude in 3DGraphics.
62) display passes antenna and may to be blocked the west section in region
Detailed process is as follows:
A., in STK, the Start button on click tools hurdle, makes satellite Satellite2 orbit.Observe in 2DGraphics, until satellite Satellite2 flies in land station Facility1 viewing area.DecreaseTimeStep on click tools hurdle makes its travelling speed slow down.Observe in 3DGraphics, until satellite-land station vector DiMianZhanShiLiang is positioned at satellite body system YZ plane YZ-PingMian.
B. in ObjectBrowser hurdle, left side, double-click Satellite2, open satellite setup of attribute window.Basic-Orbit is clicked in setup of attribute window.Continuous adjustment RAAN parameter, has revised the Apply button in rear click interface at every turn, amendment is come into force; While amendment, in 3DGraphics, observed number passes the angle JiaJiao angle value of antenna zero vector LingWeiShiLiang and satellite-land station vector DiMianZhanShiLiang, until it equals step 1) middle " number passes antenna not by the hard-over under circumstance of occlusion " obtained---90 °.It should be noted that the track after amendment RAAN must ensure that satellite is in the west of land station;
C. previous step 62 is repeated)-a and step 62)-b, satellite position in orbit and RAAN parameter are finely tuned, until above-mentioned two conditions are all met, that is: satellite-land station vector DiMianZhanShiLiang is positioned at satellite body system YZ plane YZ-PingMian; The angle JiaJiao angle value that number passes antenna zero vector LingWeiShiLiang and satellite-land station vector DiMianZhanShiLiang equals step 1) middle " number passes antenna by the hard-over under circumstance of occlusion " obtained---90 °.
D. enter 2DGraphics, under can seeing the star of satellite, the land station viewing area of circle be divide into three pieces by line tracking.Less that piece in east side is exactly step 52) " number pass antennas may be blocked the eastern section in region " that obtain in-d.Less that piece in west side is exactly " number pass antennas may be blocked the west section in region ".Two pieces of area sums, are " number pass antenna may be blocked region ".
7) number calculated when satellite side-sway is real to be passed passes antenna and blocks probability
In step 5) with step 6) terminate after, obtain " number pass antenna may be blocked region ", be divided into eastern section and west section.Utilize this result and step 1 below) in " satellite maximum side-sway angle " and step 2) in " number passes the maximum side-sway angle that can not be blocked of antenna ", the number calculated when satellite side-sway is real to be passed passes antenna and blocks probability.Its concrete steps are as follows:
71) reference area ratio
In 2DGraphics, observe step 62) eastern section of " number pass antenna may be blocked region " that obtains of-d and west section.The area in visual estimation eastern section and region, west section accounts for the ratio of whole land station viewing area, obtains area ratio.Through estimation, shaded area accounts for 10% of whole land station viewing area area
Computing formula is as follows:
Area ratio
≤ (eastern section area+west section area)/total area
≈ 10% (visual estimation)
72) angle ratio is calculated
Utilize step 1) in satellite maximum side-sway angle and step 2) in " number passes the maximum side-sway angle that can not be blocked of antenna ", obtain angle ratio.
Computing formula is as follows:
Angle ratio
/ maximum side-sway angle ,≤(maximum side-sway angle-can not be blocked maximum side-sway angle)
The maximum side-sway angle that=1-can not be blocked/maximum side-sway angle
＝1-27°/35°
≈22.86％
73) obtain and block probability
Utilize area ratio and angle ratio, the number can obtained when satellite side-sway is real to be passed passes antenna and blocks probability.
Computing formula is as follows:
Block probability
=area ratio * angle ratio
≤10％*22.86％
≈3％
Above-mentioned formula calculates, and number when being exactly satellite side-sway reality biography passes antennas and blocks probability, and its result of calculation is not an exact value determined, but is less than a value.That is, the result calculated provides a maximal value of blocking probability.
74) number provided when satellite side-sway is real to be passed passes antenna and blocks probability level
Now, the number that can provide when satellite side-sway is real to be passed passes antenna and blocks probability level, as the system index of design of satellites.Its index formulation is as follows:
● when satellite side-sway angle absolute value is no more than 27 °, when side-sway passes in fact, number biography antenna can not be blocked;
● when satellite side-sway angle absolute value is spent more than 27 °, the probability that when side-sway passes in fact, number biography antenna is blocked is no more than 3%.
8) net result is exported
According to analysis before, step 8) net result can by step 2) directly arrive, also can by step 2) ~ step 7) obtain gradually, depend on step 2) Rule of judgment whether meet.In the implementation case, due to step 8) condition obtain satisfied, therefore net result is by step 2) ~ step 7) obtain gradually.
The content be not described in detail in instructions of the present invention, especially about the method for operating of STK, all belongs to the known technology of those skilled in the art.
Claims (3)
1. obtain the satellite number carried out in-orbit when passing in fact and pass the method that antenna blocks probability, it is characterized in that step is as follows:
1) obtain the maximum side-sway angle of satellite, and number passes antenna not by the maximum side-sway angle θ under circumstance of occlusion;
2) calculate the subtended angle over the ground obtaining satellite and count the maximum side-sway angle passing antenna and can not be blocked, judge whether maximum side-sway angle is greater than the maximum side-sway angle θ counting and pass antenna and can not be blocked, if step 1) in the satellite maximum side-sway angle that obtains be greater than step 2) in the number calculated pass the maximum side-sway angles that can not be blocked of antennas, then enter step 3); Otherwise show that number passes antenna and certainly can not be blocked, blocking probability is 0%, the number now obtained when satellite side-sway is real to be passed passes antenna and blocks probability level, and namely side-sway is real when passing, and number biography antenna can not be blocked;
3) in STK, draw the viewing area of satellite and land station;
4) required three-dimensional feature is set in STK
41) in STK, the angle that number passes antenna zero vector and satellite-land station's vector is drawn;
42) satellite body system YZ plane is set in STK;
5) number passes the region that may be blocked of antenna and is divided into two pieces, lays respectively at east side and west side that Satellite rolls off the production line, is defined as eastern section and west side that number passes the region that antenna may be blocked respectively; The side-sway angle arranging satellite in STK is the maximum positive side-sway angle that number biography antenna can not be blocked, and draws the eastern section that number passes the region that antenna may be blocked;
6) in STK, arrange the attitude of satellite is the maximum minus side pivot angle that number biography antenna can not be blocked, and draws the west section that number passes the region that antenna may be blocked;
7) number calculated when satellite side-sway is real to be passed passes antenna and blocks probability
71) acquisition area ratio is calculated
Determining step 6) number that obtains passes antennas and may to be blocked the eastern section in region and west section area, and the area calculating eastern section and region, west section accounts for the ratio of whole land station viewing area, and the computing formula obtaining area ratio is as follows:
Area ratio≤(eastern section area+west section area)/ground total area
72) acquisition angle ratio is calculated
Utilize step 1) in satellite maximum side-sway angle and step 2) in number pass the maximum side-sway angle that can not be blocked of antenna, calculate the maximum side-sway angle of maximum side-sway angle/satellite obtaining angle and can not be blocked than≤(satellite maximum side-sway angle-number passes the maximum side-sway angle that antenna can not be blocked)/satellite maximum side-sway angle=1-number biography antenna;
73) Probability p=area ratio * angle ratio≤(eastern section area+west section area)/ground total area * (1-number passes the maximum side-sway angle of maximum side-sway angle/satellite that antenna can not be blocked) is blocked in acquisition;
74) number now obtained when satellite side-sway is real to be passed passes antenna and blocks probability level, namely when satellite side-sway angle absolute value be no more than θ spend time, when side-sway passes in fact, number biography antenna can not be blocked, when satellite side-sway angle absolute value is spent more than θ, the probability that when side-sway passes in fact, number biography antenna is blocked is no more than p.
2. a kind of number obtained when satellite carries out real biography in-orbit according to claim 1 passes the method that antenna blocks probability, it is characterized in that: step 2) subtended angle over the ground of Satellite and number pass the maximum side-sway angle circular that antenna can not be blocked and be:
Subtended angle=asin (earth radius/(satellite orbital altitude+earth radius))+surplus angle over the ground; Maximum side-sway angle=number that number biography antenna can not be blocked passes antenna by the subtended angle over the ground of the hard-over-satellite under circumstance of occlusion.
3. a kind of number obtained when satellite carries out real biography in-orbit according to claim 1 passes the method that antennas block probability, it is characterized in that: step 3) in STK, draw the concrete grammar of the viewing area of satellite and land station as follows:
31) simulating scenes is set up;
32) satellite orbit is set up;
33) land station is set up;
34) earth station antenna is set up;
35) viewing area of satellite and land station is shown.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510527488.8A CN105183959B (en) | 2015-08-25 | 2015-08-25 | A kind of method that number obtained when the in-orbit progress of satellite is real to be passed passes antenna occlusion probability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510527488.8A CN105183959B (en) | 2015-08-25 | 2015-08-25 | A kind of method that number obtained when the in-orbit progress of satellite is real to be passed passes antenna occlusion probability |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105183959A true CN105183959A (en) | 2015-12-23 |
| CN105183959B CN105183959B (en) | 2018-03-09 |
Family
ID=54906038
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510527488.8A Active CN105183959B (en) | 2015-08-25 | 2015-08-25 | A kind of method that number obtained when the in-orbit progress of satellite is real to be passed passes antenna occlusion probability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105183959B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106647704A (en) * | 2016-12-19 | 2017-05-10 | 北京空间飞行器总体设计部 | Method for determining tracking precision of GEO orbital data transmission antenna |
| CN106095731B (en) * | 2016-08-18 | 2018-04-20 | 中国电子科技集团公司第五十四研究所 | A kind of satellite health blocks the computational methods that number over the ground passes the antenna time |
| CN111066261A (en) * | 2017-07-27 | 2020-04-24 | 普拉多斯公司 | Method for generating a network for providing, in particular, the internet over the entire surface of the earth, payload and aircraft implementing said method |
| CN113691301A (en) * | 2021-08-23 | 2021-11-23 | 深圳海卫通网络科技有限公司 | Method and device for measuring shielding of ship satellite communication antenna |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0618541A1 (en) * | 1993-04-01 | 1994-10-05 | International Business Machines Corporation | Interactive graphics computer system for planning star-sensor-based satellite attitude maneuvers |
| CN102700728A (en) * | 2012-06-18 | 2012-10-03 | 上海卫星工程研究所 | Method for determining sheltering of solar cell array during in-orbit running of satellite and application of method |
| CN103970991A (en) * | 2014-04-29 | 2014-08-06 | 上海卫星工程研究所 | Method for analyzing on-orbit sheltered condition of solar battery arrays of stationary orbiting satellite |
| CN104410361A (en) * | 2014-10-10 | 2015-03-11 | 中国空间技术研究院 | A satellite solar wing occlusion testing method |
-
2015
- 2015-08-25 CN CN201510527488.8A patent/CN105183959B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0618541A1 (en) * | 1993-04-01 | 1994-10-05 | International Business Machines Corporation | Interactive graphics computer system for planning star-sensor-based satellite attitude maneuvers |
| CN102700728A (en) * | 2012-06-18 | 2012-10-03 | 上海卫星工程研究所 | Method for determining sheltering of solar cell array during in-orbit running of satellite and application of method |
| CN103970991A (en) * | 2014-04-29 | 2014-08-06 | 上海卫星工程研究所 | Method for analyzing on-orbit sheltered condition of solar battery arrays of stationary orbiting satellite |
| CN104410361A (en) * | 2014-10-10 | 2015-03-11 | 中国空间技术研究院 | A satellite solar wing occlusion testing method |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106095731B (en) * | 2016-08-18 | 2018-04-20 | 中国电子科技集团公司第五十四研究所 | A kind of satellite health blocks the computational methods that number over the ground passes the antenna time |
| CN106647704A (en) * | 2016-12-19 | 2017-05-10 | 北京空间飞行器总体设计部 | Method for determining tracking precision of GEO orbital data transmission antenna |
| CN106647704B (en) * | 2016-12-19 | 2019-11-12 | 北京空间飞行器总体设计部 | A kind of GEO track number passes antenna tracking accuracy and determines method |
| CN111066261A (en) * | 2017-07-27 | 2020-04-24 | 普拉多斯公司 | Method for generating a network for providing, in particular, the internet over the entire surface of the earth, payload and aircraft implementing said method |
| CN111066261B (en) * | 2017-07-27 | 2022-03-08 | 普拉多斯公司 | System for providing a network on the surface of the earth, and associated payload and aircraft |
| CN113691301A (en) * | 2021-08-23 | 2021-11-23 | 深圳海卫通网络科技有限公司 | Method and device for measuring shielding of ship satellite communication antenna |
| CN113691301B (en) * | 2021-08-23 | 2022-08-02 | 深圳海卫通网络科技有限公司 | Method and device for measuring shielding of ship satellite communication antenna |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105183959B (en) | 2018-03-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112070894B (en) | Real environment navigation multipath real-time simulation method, device, medium and electronic equipment | |
| US20060256010A1 (en) | System and method for visualization of attitude and attitude/position dependent data | |
| CN105183959A (en) | Method for acquiring data transmission antenna shielding probability of satellite during in-orbit real-time transmission | |
| CN108680165B (en) | Target aircraft attitude determination method and device based on optical image | |
| CN110378349A (en) | The mobile terminal Android indoor scene three-dimensional reconstruction and semantic segmentation method | |
| CN104154919A (en) | Method for autonomous measurement of pose of tripod structure of solar panel on non-cooperative spacecraft | |
| CN104573251A (en) | Method for determining full-field-of-view apparent spectral radiance of satellite-borne optical remote sensor | |
| CN101719802B (en) | Device and calculation method for predicting maximum usable frequency (MUF) of short-wave communication | |
| CN106352566A (en) | Tower type solar thermal power generation sun-tracking analysis system | |
| CN103743488B (en) | Infrared imaging simulation method for globe limb background characteristics of remote sensing satellite | |
| CN103679780A (en) | A space target real time simulation method | |
| CN116341873B (en) | Multi-star resource scheduling and task planning method, system and storage medium | |
| Gubarev et al. | Using vision systems for determining the parameters of relative motion of spacecrafts | |
| CN106095731B (en) | A kind of satellite health blocks the computational methods that number over the ground passes the antenna time | |
| Liang et al. | Accuracy analysis of oblique photogrammetry measurement in 3D modeling of power line selection design | |
| CN106372036B (en) | A kind of satellite sun wing blocks the computational methods of number biography antenna time over the ground | |
| CN110220492A (en) | A kind of sub-satellite point solar elevation simulating analysis and system | |
| CN114485620A (en) | Orbital dynamics fused asteroid detector autonomous visual positioning system and method | |
| CN103544677A (en) | Space-air-ground integration situational expression engine and shaking elimination method | |
| CN103487055B (en) | A kind of star is used to the method combining restore target space distribution | |
| Baker et al. | Limb-based shape modeling: a demonstration on Itokawa | |
| CN108897029A (en) | Noncooperative target short distance Relative Navigation vision measurement system index evaluating method | |
| Deng et al. | Simulation and 3D Visualization of Mission Scheduling for Imaging Satellites | |
| CN105183961A (en) | Method for acquiring pointing angle of spacecraft two-dimensional rotating mechanism by using STK | |
| CN117421938B (en) | Ground task planning method and system for star tracking observation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |