GEO satellite beam pointing deviation calculation method based on maneuvering measurement analysis

Abstract

The invention relates to a GEO satellite beam pointing deviation calculation method based on maneuvering measurement analysis, and belongs to the technical field of satellite communication. The method comprises the following steps of: calculating a pitching deviation angle and a rolling deviation angle between a directional angle from a satellite space point S to a position point B of a calibration station and a directional angle from the satellite space point S to an actual directional center point C of a beam by using four calibration beam power data measured by the calibration station; then, calculating a pitching deviation angle and a rolling deviation angle of a pointing angle from a satellite space point S to a calibration station position point B relative to a pointing angle from the satellite space point S to a beam theoretical pointing center point A by using the space position information of the points A, B and C; and finally, calculating the satellite beam pointing deviation. The method is oriented to GEO fixed beam communication satellites, utilizes the measurement signals of the maneuvering calibration station to calculate the beam pointing deviation, and can be used for assisting in satellite beam pointing correction. According to the method, mobile platform deployment is supported, and compared with fixed site deployment, site building difficulty and cost are reduced.

Description

Technical Field

[0001] The present invention relates to the field of satellite communication technology, in particular to a GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis, which is applicable to a geosynchronous orbit satellite fixed beam and can assist the satellite in adjusting the beam pointing to a theoretical position. Background Art

[0002] For GEO fixed-beam communication satellites, the system needs to maintain beam pointing accuracy to facilitate network planning and generate accurate planning solutions, and assist users in implementing service switching based on coverage. When the satellite coverage area is the national territory, a ground fixed calibration station can be built to measure and calculate the satellite antenna pointing deviation, implement beam pointing control, and maintain the stability of the satellite beam service range.

[0003] However, it is difficult to build fixed calibration stations for GEO satellites with overseas coverage, and it is necessary to propose a GEO satellite beam pointing deviation calculation method based on mobile measurement analysis so that the calibration station can be deployed based on a mobile platform. At present, there is no such method in the existing technology. Summary of the invention

[0004] The purpose of the present invention is to provide a GEO satellite beam pointing deviation calculation method based on mobile measurement analysis. Aiming at the demand for mobile deployment of satellite beam calibration stations, the present invention proposes an innovative GEO satellite beam pointing deviation calculation method that can support the mobile platform deployment of calibration stations.

[0005] The technical solution adopted by the present invention is:

[0006] The GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis is applied to the beam calibration station and includes the following steps:

[0007] Step 1, obtain the longitude lgS of the satellite theoretical orbit determination point S, the longitude lgA and latitude ltA of the theoretical pointing center point A of the satellite beam on the ground, and load the four calibration beam pointing deviation power design data sets for east, west, south and north. The data in the data set are (pitchDevi, rollDevi, pe, pw, ps, pn), where pitchDevi is the pitch angle deviation, rollDevi is the roll angle deviation, pe is the east calibration beam power value, pw is the west calibration beam power value, ps is the south calibration beam power value, and pn is the north calibration beam power value;

[0008] Step 2: According to the data (pitchDevi, rollDevi, pe, pW, pS, pn), calculate the power-normalized pointing deviation data (pitchDevi, rollDevi, uew, usn), where uew is the normalized value of the east-west calibration beam power, and usn is the normalized value of the north-south calibration beam power. The calculation formula is as follows:

[0009]

[0010] Step 3: Generate the pointing deviation judgment matrix D:

[0011]

[0012] Among them, D i，j indicates (pitchDevi i，j ,rollDevi i，j ,uew i,j , usn i，j ), That is, row 0 contains 101 data points with a roll deviation angle of -0.5°, and each subsequent row contains a roll deviation angle increase of 0.01°; column 0 contains 101 data points with a pitch deviation angle of -0.5°, and each subsequent column contains a pitch deviation angle increase of 0.01°;

[0013] Step 4: The beam calibration station receives the calibration signals sent by the four calibration beams of the satellite and generates measurement data (p e , p w , p s , p n , lg, lt, t), where p e , p w , p s , p n is the power value of the east, west, south and north calibration beams measured by the beam calibration station, t is the measurement time, lg is the longitude of the calibration station, and lt is the latitude of the calibration station; calculate the normalized value u of the east-west beam power ew and the normalized value u of the north-south beam sn :

[0014]

[0015] Step 5, use u ew And the pointing deviation judgment matrix D is used to calculate the pitch angle deviation line;

[0016] Step 6, use u sn The rolling angle deviation line is calculated by using the pointing deviation judgment matrix D;

[0017] Step 7: Calculate the intersection of the pitch deviation line and the roll deviation line (pitchDevip ,rollDevi p ), pitchDevi p and rollDevi p That is, the pitch deviation angle and roll deviation angle between the pointing angle from the satellite space point S to the calibration station position point B and the pointing angle from the satellite space point S to the actual beam pointing center point C;

[0018] Step 8: Calculate the pitch deviation angle pitchDevi from the satellite space point S to the calibration station position point B relative to the satellite space point S to the beam theoretical pointing center point A according to the satellite theoretical orbit determination position (lgs, 0), the satellite beam theoretical pointing center position on the ground (lgb, ltb) and the calibration station position (lg, lt). s and roll deviation angle rollDevi s ;

[0019] Step 9: Based on the calculation results of Steps 7 and 8, calculate the pitch deviation angle pitchDevi from the satellite space point S to the actual beam pointing center point C relative to the satellite space point S to the theoretical beam pointing center point A. f and roll deviation angle rollDevi f , the calculation result is the satellite beam pointing deviation.

[0020] Furthermore, the specific method of step 5 is:

[0021] Step 5-1, select the deviation range [-0.5°, 0.5°], where the power of the west calibration beam decreases monotonically from west to east, the power of the east calibration beam increases monotonically, and the normalized values ​​of the east-west beams in each row of the pointing deviation judgment matrix D increase monotonically;

[0022] Step 5-2, take out the hpl-th row data from the pointing deviation judgment matrix D, ignoring the normalized value of the north-south calibration beam power, then any data in this row is (pitchDevi hpl,lpl ,rollDevi hpl,lpl ,uew hpl，lpl ), where lpl is the column number, from uew hpl，0 To UEW hpl,100 The value increases monotonically; start from the first column to find the first uew hpl，lpl Value greater than u ew The column number is lplR. If lplR = 1 or there is no column greater than u ew If there is no intersection in the row, then the intersection point of the hpl row data and the pitch deviation line (pitchDeviPh hpl ,rollDeviPh hpl ):

[0023]

[0024] rollDeviPh hpl =rollDevi hpl，lpl

[0025] Step 5-3: Repeat step 5-2 to calculate the intersection points from row 0 to row 100, i.e. the pitch deviation points (pitchDevi 0 ,-0.5)、(pitchDevi 1 ,-0.49),...,(pitchDevi 100 , 0.5), the line connecting the intersection points forms the pitch angle deviation line.

[0026] Furthermore, the specific method of step 6 is:

[0027] Step 6-1, select a deviation range of [-0.5°, 0.5°], where the power of the north calibration beam decreases monotonically from north to south, the power of the south calibration beam increases monotonically, and the normalized values ​​of the north and south beams in each column of the pointing deviation judgment matrix D decrease monotonically;

[0028] Step 6-2, take out the data of the lrlth column from the pointing deviation judgment matrix D, ignoring the normalized value of the east-west calibration beam power, then any data in this column is (pitchDevi hrl,lrl ,rollDevi hrl,lrl , usn hrl,lrl ), where hrl is the line number, from usn 0,lrl to usn 100,lrl The value is monotonically decreasing; start from the first row to find the first usn hrl,lrl Value is less than u sn The row number is hrlR. If hrlR = 1 or there is no row less than u sn If there is no intersection in the row, then the intersection of the row and the rolling deviation line is calculated according to the following formula (pitchDeviPl lrl ,rollDeviPl lrl ):

[0029]

[0030] pitchDeviPl lrl =pitchDevi hrl,lrl

[0031] Step 6-3, repeat step 6-2, calculate the intersection points of columns 0 to 100, that is, the rolling deviation points (-0.5, rollDevi 0)、(-0.49,rollDevi 1 )、......、(0.5,rollDevi 100 ), the line connecting the intersection points forms the rolling angle deviation line.

[0032] Furthermore, the specific method of step 7 is:

[0033] Step 7-1, obtaining the pitch deviation point of step 5 and the roll deviation point of step 6;

[0034] Step 7-2, obtain the coordinates of the hpl-th pitch deviation point P1 (p 1 , r 1 ) and the coordinates of the hpl+1th pitch deviation point P2 (p 2 , r 2 );

[0035] Step 7-3, obtain the coordinates of the lrlth rolling deviation point P3 (p 3 , r 3 ) and the coordinates of the lrl+1th rolling deviation point P4 (p 4 , r 4 );

[0036] Step 7-4, judging whether the line connecting the hpl-th pitch deviation point P1 and the hpl+1-th pitch deviation point P2 intersects with the line connecting the lrl-th rolling deviation point P3 and the lrl+1-th rolling deviation point P4, the judging method is as follows:

[0037] Step 7-4-1, determine whether the two line segments overlap at the pitch deviation angle axis and the roll deviation angle axis at the same time. If not, there is no intersection, and execute step 7-5. If yes, execute step 7-4-2;

[0038] Step 7-4-2, if the following two discriminants are both true, then they intersect, otherwise they do not intersect; the discriminants are as follows:

[0039] (P1-P4)×(P3-P4)*(P2-P4)×(P3-P4)≤0

[0040] (P4-P2)×(P1-P2)*(P3-P2)×(P1-P2)≤0

[0041] Step 7-5, if there is no intersection, take the next rolling deviation point, repeat steps 7-3 to 7-5, if the two lines intersect, calculate (pitchDevi p ,rollDevi p ), go to step 8; the formula is as follows:

[0042] pitchDevip =p3+Δt*(p4-p3)

[0043] rollDevi p =r3+Δt*(r4-r3)

[0044] Among them, Δt is an intermediate variable, and the calculation method is:

[0045]

[0046] Step 7-6, if the line connecting the hpl-th and hpl+1-th pitch deviation points does not intersect with the lines connecting the rolling deviation points, then take the next pitch point and repeat steps 7-2 to 7-6;

[0047] Step 7-7, if the lines connecting the pitch deviation points do not intersect with the lines connecting the roll deviation points, the calculation accuracy is exceeded and the satellite beam pointing deviation cannot be calculated.

[0048] Furthermore, the specific method of step 8 is:

[0049] Step 8-1, the satellite space point S is (lgS, 0, H+R), the beam theoretical pointing center point A is (lgA, ltA, R), and the calibration station location point B is (lg, lt, R), where the unit of longitude and latitude is °, H is the height of the GEO satellite, R is the radius of the earth, and the value range of ltA and lt is [0, 60];

[0050] Step 8-2: Calculate the pitch angle from the satellite space point S to the calibration station position point B. B , roll B ), the formula is as follows:

[0051]

[0052] Step 8-3, calculate the pointing angle (pitch) from the satellite space point S to the theoretical beam pointing center point A A , roll A ), the formula is as follows:

[0053]

[0054] Step 8-4, based on the results of Step 8-2 and Step 8-3, calculate (pitchDevi s ,rollDevi s ), the formula is as follows:

[0055] rollDevi s =roll B -roll A

[0056] pitchDevi s =pitch B -pitch A .

[0057] Furthermore, the specific method of step 9 is:

[0058] Step 9-1, calculate the beam pointing elevation deviation angle:

[0059] pitchDevi f =pitchDevi s -pitchDevi p

[0060] Step 9-2, calculate the beam pointing roll deviation angle:

[0061] rollDevi f =rollDevi s -rollDevi p

[0062] Step 9-3, obtain the satellite beam pointing deviation angle (pitchDevi f ,rollDevi f ).

[0063] Compared with the background technology, the present invention has the following beneficial effects:

[0064] 1. The present invention can support the deployment of satellite beam calibration stations based on mobile platforms;

[0065] 2. The present invention can assist in adjusting the satellite beam pointing, which is beneficial to maintaining the stability of the satellite coverage;

[0066] 3. The algorithm of the present invention is simple, the implementation complexity is very low, and it has the value of popularization and application. BRIEF DESCRIPTION OF THE DRAWINGS

[0067] Figure 1 It is a schematic diagram of the principle of the calculation method of satellite beam pointing deviation at the mobile calibration station.

[0068] Figure 2 It is a schematic diagram of using the calibration station measurement data to calculate the pitch angle deviation and roll angle deviation of the satellite's actual beam pointing relative to the direction from the satellite to the calibration station.

[0069] Figure 3 It is a flow chart of the GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis. DETAILED DESCRIPTION

[0070] The present invention is described in detail below with reference to the accompanying drawings.

[0071] A GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis is proposed. This method uses the four calibration beam power data measured by the calibration station to calculate the pitch deviation angle and roll deviation angle (pitchDevi) between the satellite space point S and the calibration station position point B pointing angle relative to the satellite space point S and the actual beam pointing center point C. p ,rollDevi p ); Then, the spatial position information of points A, B, and C is used to calculate the pitch deviation angle and roll deviation angle (pitchDevi s ,rollDevi s ); Finally, use (pitchDevi p ,rollDevi p ) and (pitchDevi s ,rollDevi s ) Calculate the satellite beam pointing deviation (pitchDevi f ,rollDevi f ).

[0072] Assume that point A is the theoretical pointing center of the satellite beam, point B is the location of the beam calibration station, point C is the actual pointing center of the satellite beam, and point S is the satellite position. Figure 1 Three points A, B and C on the ground are shown in FIG.

[0073] like Figure 3 As shown, the method specifically comprises the following steps:

[0074] Step (1): Initialize the calibration system, obtain the longitude lgS of the satellite's theoretical orbit determination point S, the longitude lgA and latitude ltA of the satellite's theoretical pointing center point A on the ground, and load the east-west, south-north, and north-south calibration beam pointing deviation power design data sets (pitchDevi, rollDevi, pe, pw, ps, pn) from the database, where pitchDevi is the pitch angle deviation, rollDevi is the roll angle deviation, pe is the east calibration beam power value, pw is the west calibration beam power value, ps is the south calibration beam power value, and pn is the north calibration beam power value. The data is stepped by 0.01°, and the pitch angle and roll angle errors are between [-0.5′, 0.5′]. The pointing deviation power design data set has a total of 10201 sets of data;

[0075] Step (2): According to the data (pitchDevi, rollDevi, pe, pw, ps, pn), calculate the power-normalized pointing deviation data (pitchDevi, rollDevi, uew, usn), where uew is the normalized power value of the east-west calibration beam, and usn is the normalized power value of the north-south calibration beam. The power normalization value range is (-1, 1). The calculation formula is as follows:

[0076]

[0077] Step (3): Generate the pointing deviation judgment matrix using the calculation results of step (2) Among them, D i,j indicates (pitchDevi i，j ,rollDevi i，j ,uew i,j , usn i，j ), That is, row 0 contains 101 data points with a roll deviation angle of -0.5°, and each subsequent row contains a roll deviation angle increase of 0.01°; column 0 contains 101 data points with a pitch deviation angle of -0.5°, and each subsequent column contains a pitch deviation angle increase of 0.01°;

[0078] Step (4): The mobile calibration station receives the calibration signals sent by the four calibration beams of the satellite and generates measurement data (p e , p w , p e , p s , p n , lg, lt, t), where t is the measurement time, lg is the longitude of the calibration station, and lt is the latitude of the calibration station. The normalized value u of the east-west beam power is calculated according to the formula in step (2) ew and the normalized value u of the north-south beam sn ;

[0079] Step (5): Using u from step (4) ew The power normalized pointing deviation matrix D in step (3) is used to calculate the pitch angle deviation line, which is composed of multiple points (pitchDevi 0 ,-0.5)、(pitchDevi 1 ,-0.49),...,(pitchDevi 100 , 0.5), the pitch angle deviation line includes the following steps:

[0080] Step (5-1): Within the selected deviation range [-0.5′, 0.5′], the power of the west calibration beam decreases monotonically from west to east, the power of the east calibration beam increases monotonically, and the normalized values ​​of the east-west beams in each row of the pointing deviation judgment matrix D increase monotonically;

[0081] Step (5-2): Take the hpl-th row of data from matrix D, (pitchDevi hpl,lpl ,rollDevi hpl,lpl ,uew hpl，lpl ), where lpl is the column number, from uew hpl，0 To UEW hpl,100 The value increases monotonically, starting from the first column to find the first uew hpl，lpl Value greater than u ew The column number is lplR. If lplR = 1 or no column is greater than u ew If there is no intersection in the row, then the intersection of the hpl row data and the pitch deviation line (pitchDeviPh hpl ,rollDeviPh hpl ) is calculated as follows:

[0082]

[0083] rollDeviPh hpl =rollDevi hpl,lpl

[0084] Step (5-3): Repeat step (5-2) to calculate the intersection points from row 0 to row 100, i.e. (pitchDevi 0 ,-0.5)、(pitchDevi 1 ,-0.49),...,(pitchDevi 100 , 0.5), the line connecting the intersection points forms the pitch angle deviation line.

[0085] Step (6): Using u from step (4) sn The power normalized pointing deviation matrix D in step (3) is used to calculate the roll angle deviation line, which is composed of multiple points (-0.5, rollDevi 0 )、(-0.49,rollDevi 1 ),…,(0.5,rollDevi 100 ), the rolling angle deviation line includes the following steps:

[0086] Step (6-1): Within the selected deviation range [-0.5°, 0.5°], the power of the north calibration beam decreases monotonically from north to south, the power of the south calibration beam increases monotonically, and the normalized values ​​of the north and south beams in each column of the pointing deviation judgment matrix D decrease monotonically;

[0087] Step (6-2): Take the lrlth column data from the matrix D, (pitchDevi hrl,lrl ,rollDevi hrl,lrl , usn hrl,lrl ), where hrl is the column number, from usn 0,lrl to usn 100,lrl The value is monotonically decreasing, starting from the first row to find the first USN hrl,lrl Value is less than u sn The row number is hrlR. If hrlR = 1 or there is no row less than u sn If there is no intersection in the row, then the intersection of the lrl column data and the rolling deviation line (pitchDeviPl lrl ,rollDeviPl lrl ) is calculated as follows:

[0088]

[0089] pitchDeviPl lrl =pitchDevi hrl,lrl

[0090] Step (6-3): Repeat step (6-2) to calculate the intersection points from column 0 to column 100, i.e. (-0.5, rollDevi 0 )、(-0.49,rollDevi 1 ),…,(0.5,rollDevi 100 ), the line connecting the intersection points forms the rolling angle deviation line.

[0091] Figure 2 It is a schematic diagram of using the calibration station measurement data to calculate the pitch angle deviation and roll angle deviation of the actual satellite beam pointing relative to the satellite to the calibration station pointing. The figure shows the calculation process of the pitch deviation angle and the roll deviation angle in the range of [-0.1, 0.1]. Among them, the pitch angle deviation line is composed of the intersection between the normalized values ​​of the east-west beam of the calibration station and the normalized value lines of the east-west beam power of each row of the matrix D, and the roll deviation line is composed of the intersection between the normalized values ​​of the north-south beam of the calibration station and the normalized value lines of the north-south beam power of each column of the matrix D. The intersection of the pitch angle deviation line and the roll deviation line is the pitch deviation angle and roll deviation angle between the pointing angle of the satellite space point S to the calibration station position point B relative to the pointing angle of point S to the actual beam pointing center point C.

[0092] Step (7): Based on the pitch deviation line and roll deviation line in steps (5) and (6), calculate the intersection point of the two lines (pitchDevi p ,rollDevi p), the intersection point is the pitch deviation angle and roll deviation angle between the pointing angle from the satellite space point S to the calibration station position point B relative to the pointing angle from the satellite space point S to the actual beam pointing center point C. The calculation steps are as follows:

[0093] Step (7-1): Obtain the pitch deviation point of step (5) and the roll deviation point of step (6);

[0094] Step (7-2): Get the coordinates of the hpl-th pitch deviation point P1 (p 1 , r 1 ) and the hpl+1th pitch deviation point P2 coordinates (p 2 , r 2 );

[0095] Step (7-3): Get the coordinates of the lrlth rolling deviation point P3 (p 3 , r 3 ) and the coordinates of the lrl+1th rolling deviation point P4 (p 4 , r 4 );

[0096] Step (7-4): Determine whether the line connecting the hpl-th pitch deviation point P1 and the hpl+1-th pitch deviation point P2 intersects the line connecting the lrl-th roll deviation point P3 and the lrl+1-th roll deviation point P4. The determination process is as follows:

[0097] Step (7-4-1): First, determine whether the two line segments overlap at the pitch deviation angle axis and the roll deviation angle axis at the same time. If the conditions are not met, there is no intersection, and execute step (7-5). If they overlap at the same time, there may be an intersection, and execute step (7-4-2);

[0098] Step (7-4-2): If the following two discriminants are both true, they intersect, otherwise they do not intersect, and execute step (7-5). The discriminant is as follows:

[0099] (P1-P4)×(P3-P4)*(P2-P4)×(P3-P4)≤0

[0100] (P4-P2)×(P1-P2)*(P3-P2)×(P1-P2)≤0

[0101] Step (7-5): If there is no intersection, take the next rolling deviation point and repeat the calculation process from step (7-3) to step (7-5). If the two lines intersect, (pitchDevip, rollDevip) can be calculated. After completion, execute step (8). The formula is as follows:

[0102]

[0103] pitchDevi p =p3+Δt*(p4-p3)

[0104] rollDevi p =r3+Δt*(r4--r3)

[0105] Step (7-6): If the lines connecting the hpl-th and hpl+1-th pitch deviation points do not intersect with the lines connecting the rolling deviation points, then take the next pitch point and repeat the calculation process from step (7-2) to step (7-6);

[0106] Step (7-7): If the lines connecting the pitch deviation points do not intersect with the lines connecting the roll deviation points, the calculation accuracy is exceeded and the satellite beam pointing deviation cannot be calculated, and step (10) is executed.

[0107] Step (8): Based on the satellite theoretical orbit position (lgs, 0), the theoretical pointing center position of the satellite beam on the ground (lgb, ltb) and the calibration station position (lg, lt), calculate the pitch deviation angle and roll deviation angle (pitchDevi) of the pointing angle from the satellite space point S to the calibration station position point B relative to the pointing angle from the satellite space point S to the theoretical pointing center point A of the beam. s ,rollDevi s ), the calculation steps are as follows:

[0108] Step (8-1): Satellite position S (lgS, 0, H+R), beam theoretically points to the center point A (lgA, ltA, R), calibration station position B (lg, lt, R), where the unit of longitude and latitude is °, H is the height of the GEO satellite, R is the radius of the earth, H = 42164 km, R = 6371 km, ltA and lt range from [0, 60];

[0109] Step (8-2): Calculate the pitch angle from the satellite space point S to the calibration station position point B. B , roll B ), where π = 3.1415926 is the circumference of a circle, and the formula is as follows:

[0110]

[0111] Step (8-3): Calculate the pointing angle (pitch) from the satellite space point S to the theoretical beam center point A. A , roll A ), the formula is as follows:

[0112]

[0113] Step (8-4): Calculate (pitchDevi) based on the results of steps (8-2) and (8-3) s ,rollDevi s ), the formula is as follows:

[0114] rollDevi s =roll B -roll A

[0115] pitchDevi s =pitch B --pitch A

[0116] Step (9): Based on the calculation results of steps (7) and (8), calculate the pitch deviation angle and roll deviation angle (pitchDevi f ,rollDevi f ), the calculation result is the satellite beam pointing deviation, and the calculation steps are as follows:

[0117] Step (9-1): Calculate the beam pointing elevation deviation angle using the following formula:

[0118] pitchDevi f =pitchDevi s -pitchDevi p

[0119] Step (9-2): Calculate the beam pointing roll deviation angle using the following formula:

[0120] rollDevi f =rollDevi s -rollDevi p

[0121] Step (9-3): According to steps (9-2) and (9-3), the satellite beam pointing deviation angle (pitchDevi f ,rollDevi f ), go to step (10).

[0122] Step (10): Output the calculation results and complete the calculation process.

[0123] The present invention is aimed at GEO fixed-beam communication satellites, and uses the measurement signal of the mobile calibration station to calculate the pointing deviation of the beam, which can be used to assist in satellite beam pointing correction. The present invention supports mobile platform deployment and can be used to implement satellite beam pointing deviation calculation based on mobile calibration station measurement and analysis, which reduces the difficulty and cost of station construction compared to fixed site deployment.

[0124] The present invention is described in detail above in conjunction with the accompanying drawings, but those skilled in the art should understand that the description is used to interpret the claims, and the protection scope of the present invention is based on the claims. On the basis of the present invention, any modifications made should be within the required protection scope.

Claims

1. A GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis is applied to a beam calibration station, characterized in that: The steps include: Step 1, obtain the longitude lgS of the satellite's theoretical orbit determination point S, the longitude lgA and latitude ltA of the theoretical pointing center point A of the satellite beam on the ground, and load the east-west, south-north four-calibration beam pointing deviation power design data set. The data in the data set are (pitchDevi, rollDevi, pe, pw, ps, pn), where pitchDevi is the pitch angle deviation, rollDevi is the roll angle deviation, pe is the east calibration beam power value, pw is the west calibration beam power value, ps is the south calibration beam power value, and pn is the north calibration beam power value; Step 2: According to the data (pitchDevi, rollDevi, pe, pw, ps, pn), calculate the power-normalized pointing deviation data (pitchDevi, rollDevi, uew, usn), where uew is the normalized value of the east-west calibration beam power, and usn is the normalized value of the north-south calibration beam power. The calculation formula is as follows: Step 3: Generate the pointing deviation judgment matrix D: Among them, D i,j indicates (pitchDevi i,j ,rollDevi i,j ,uew i,j ,usn i,j ), That is, row 0 contains 101 data points with a roll deviation angle of -0.5°, and each subsequent row contains a roll deviation angle increase of 0.01°; column 0 contains 101 data points with a pitch deviation angle of -0.5°, and each subsequent column contains a pitch deviation angle increase of 0.01°; Step 4: The beam calibration station receives the calibration signals sent by the four calibration beams of the satellite and generates measurement data (p e ,p w ,p s ,p n ,lg,lt,t), where p e ,p w ,p s ,p n is the power value of the east, west, south and north calibration beams measured by the beam calibration station, t is the measurement time, lg is the longitude of the calibration station, and lt is the latitude of the calibration station; calculate the normalized value u of the east-west beam power ew and the normalized value u of the north-south beam sn : Step 5, use u ew And the pointing deviation judgment matrix D is used to calculate the pitch angle deviation line; Step 6, use u sn The rolling angle deviation line is calculated by using the pointing deviation judgment matrix D; Step 7: Calculate the intersection of the pitch deviation line and the roll deviation line (pitchDevi p ,rollDevi p ), pitchDevi p and rollDevi p That is, the pitch deviation angle and roll deviation angle between the pointing angle from the satellite space point S to the calibration station position point B and the pointing angle from the satellite space point S to the actual beam pointing center point C; Step 8: Calculate the pitch deviation angle PitchDevi from the satellite space point S to the calibration station position point B relative to the satellite space point S to the beam theoretical pointing center point A based on the satellite theoretical orbit position (lgs, 0), the satellite beam theoretical pointing center position on the ground (lgb, ltb) and the calibration station position (lg, lt). s and roll deviation angle rollDevi s ; Step 9: Based on the calculation results of Steps 7 and 8, calculate the pitch deviation angle pitchDevi from the satellite space point S to the actual beam pointing center point C relative to the satellite space point S to the theoretical beam pointing center point A. f and roll deviation angle rollDevi f , the calculation result is the satellite beam pointing deviation.

2. The GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis according to claim 1 is characterized in that: The specific method of step 5 is: Step 5-1, select the deviation range [-0.5°, 0.5°], where the power of the west calibration beam decreases monotonically from west to east, the power of the east calibration beam increases monotonically, and the normalized values ​​of the east-west beams in each row of the pointing deviation judgment matrix D increase monotonically; Step 5-2, take out the hpl-th row data from the pointing deviation judgment matrix D, ignoring the normalized value of the north-south calibration beam power, then any data in this row is (pitchDevi hpl,lpl ,rollDevi hpl,lpl ,uew hpl,lpl ), where lpl is the column number, from uew hpl,0 To UEW hpl,100 The value increases monotonically; start from the first column to find the first uew hpl,lpl Value greater than u ew The column number is lplR. If lplR = 1 or there is no column greater than u ew If there is no intersection in the row, then the intersection point of the hpl row data and the pitch deviation line (pitchDeviPh hpl ,rollDevuPh hpl ): rollDeviPh hpl =rollDevi hpl,lpl Step 5-3: Repeat step 5-2 to calculate the intersection points from row 0 to row 100, i.e., the pitch deviation points (pitchDevi0, -0.5), (pitchDevi1, -0.49), ..., (pitchDevi 100 ,0.5), the line connecting the intersection points forms the pitch angle deviation line.

3. The GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis according to claim 2 is characterized in that: The specific method of step 6 is: Step 6-1, select the deviation range [-0.5°, 0.5°], where the power of the north calibration beam decreases monotonically from north to south, the power of the south calibration beam increases monotonically, and the normalized values ​​of the north and south beams in each column of the pointing deviation judgment matrix D decrease monotonically; Step 6-2, take out the data of the lrlth column from the pointing deviation judgment matrix D, ignoring the normalized value of the east-west calibration beam power, then any data in this column is (pitchDevi hrl,lrl ,rollDevi hrl,lrl ,usn hrl,lrl ), where hrl is the line number, from usn 0,lrl to usn 100,lrl The value is monotonically decreasing; start from the first row to find the first usn hrl,lrl Value is less than u sn The row number is hrlR. If hrlR = 1 or there is no row less than u sn If there is no intersection in the row, then the intersection of the row and the rolling deviation line is calculated according to the following formula (pitchDeviPl lrl ,rollDeviPl lrl ): pitchDeviPl lrl =pitchDevi hrl,lrl Step 6-3, repeat step 6-2, calculate the intersection points of columns 0 to 100, that is, the rolling deviation points (-0.5, rollDevi0), (-0.49, rollDevi1), ..., (0.5, rollDevi 100 ), the line connecting the intersection points forms the rolling angle deviation line.

4. The GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis according to claim 3 is characterized in that: The specific method of step 7 is: Step 7-1, obtaining the pitch deviation point of step 5 and the roll deviation point of step 6; Step 7-2, obtaining the coordinates (p1, r1) of the hpl-th pitch deviation point P1 and the coordinates (p2, r2) of the hpl+1-th pitch deviation point P2; Step 7-3, obtaining the coordinates (p3, r3) of the lrl-th rolling deviation point P3 and the coordinates (p4, r4) of the lrl+1-th rolling deviation point P4; Step 7-4, judging whether the line connecting the hpl-th pitch deviation point P1 and the hpl+1-th pitch deviation point P2 intersects with the line connecting the lrl-th rolling deviation point P3 and the lrl+1-th rolling deviation point P4, the judging method is as follows: Step 7-4-1, determine whether the two line segments overlap at the pitch deviation angle axis and the roll deviation angle axis at the same time. If not, there is no intersection, and execute step 7-5. If yes, execute step 7-4-2; Step 7-4-2, if the following two discriminants are both true, then they intersect, otherwise they do not intersect; the discriminants are as follows: (P1-P4)×(P3-P4)*(P2-P4)×(P3-P4)≤0 (P4-P2)×(P1-P2)*(P3-P2)×(P1-P2)≤0 Step 7-5, if there is no intersection, take the next rolling deviation point, repeat steps 7-3 to 7-5, if the two lines intersect, calculate (pitchDevi p ,rollDevi p ), go to step 8; the formula is as follows: pitchDevi p =p3+Δt*(p4-p3) rollDevi p =r3+Δt*(r4-r3) Among them, Δt is an intermediate variable, and the calculation method is: Step 7-6, if the line connecting the hpl-th and hpl+1-th pitch deviation points does not intersect with the lines connecting the rolling deviation points, then take the next pitch point and repeat steps 7-2 to 7-6; Step 7-7, if the lines connecting the pitch deviation points do not intersect with the lines connecting the roll deviation points, the calculation accuracy is exceeded and the satellite beam pointing deviation cannot be calculated.

5. The GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis according to claim 4 is characterized in that: The specific method of step 8 is: Step 8-1, the satellite space point S is (lgS, 0, H+R), the theoretical beam pointing center point A is (lgA, ltA, R), and the calibration station location point B is (lg, lt, R), where the unit of longitude and latitude is °, H is the height of the GEO satellite, R is the radius of the earth, and the value range of ltA and lt is [0, 60]; Step 8-2: Calculate the pitch angle from the satellite space point S to the calibration station position point B. B ,roll B ), the formula is as follows: Step 8-3, calculate the pointing angle (pitch) from the satellite space point S to the theoretical beam pointing center point A A ,roll A ), the formula is as follows: Step 8-4, based on the results of Step 8-2 and Step 8-3, calculate (pitchDevi s ,rollDevi s ), the formula is as follows: rollDevi s =roll B -roll A pitchDevi s =pitch B -pitch A 。 6. The GEO satellite beam pointing deviation calculation method based on maneuver measurement analysis according to claim 5 is characterized in that: The specific method of step 9 is: Step 9-1, calculate the beam pointing elevation deviation angle: pitchDevi f =pitchDevi s -pitchDevi p Step 9-2, calculate the beam pointing roll deviation angle: rollYou need to f =rollYouDevi s -rollYou need p Step 9-3, obtain the satellite beam pointing deviation angle (pitchDevi f ,rollDevi f ).

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