Method for fast pointing of a communication satellite antenna beam in a production line

Abstract

The application provides a method for quickly positioning a beam pointing direction of a communication satellite antenna in a production line, comprising the following steps: selecting three non-collinear observation points in the space in the approximate main lobe area of a satellite payload antenna, using a measurement horn test to obtain three polar coordinates and corresponding gains; substituting the data into an equation to solve a satellite payload antenna beam pointing angle; using the solved pointing angle to calculate an amplitude error; if the calculation amplitude error accuracy is not within a set error range, continuously narrowing the area within the last collected area range, collecting angle and gain data of three non-collinear observation points, and repeatedly calculating the pointing angle until the accuracy requirement is met. The method has the advantages that the collected area can be continuously narrowed for iterative correction, and the technical problems of long iteration time and poor batch consistency of the existing algorithm can be solved.

Description

Technical Field

[0001] This invention relates to the field of radio direction finding, and more particularly to a method for rapid beam pointing positioning of a production line communication satellite antenna in a mass production environment. Background Technology

[0002] As the scale of low-Earth orbit communication satellite production continues to expand, satellite manufacturing faces the dual challenges of rapid production pressure and increasing quality requirements. Improving the response speed and efficiency of various equipment testing processes in the satellite manufacturing production line has become particularly crucial.

[0003] Antenna beam pointing and positioning is a fundamental step in the functional testing of satellite communication payloads, and improving its efficiency is particularly important. Current beam pointing and positioning methods on production lines mainly suffer from the following technical problems:

[0004] 1. Long iteration time: Traditional successive approximation method has a long positioning time and requires multiple iterations to achieve the required accuracy;

[0005] 2. Poor batch consistency: Due to strict control of the final assembly time, the satellites are tested directly in the anechoic chamber without being removed from the transfer vehicle. The position error of each satellite under test is large, and the parameters need to be adjusted based on the experience of the operators, resulting in poor consistency of measurement results of different satellites.

[0006] Therefore, there is an urgent need to develop a beam pointing technology solution that can achieve rapid response while ensuring testing accuracy. Summary of the Invention

[0007] This invention provides a method for rapid beam pointing positioning of a satellite antenna in production line communication, adapting to the large positioning error of satellite relay vehicles. It uses a three-dimensional Gaussian distribution antenna pattern as a preset model; angle and gain data are collected from three non-collinear observation points within an approximate main lobe region; the nonlinear model is linearized through logarithmic transformation to construct a system of two linear equations; the beam pointing angle is obtained by solving the equations; signal strength data from the actual communication link is collected to determine the pointing error; if the accuracy is insufficient, this pointing angle is used as the initial pointing parameter. This algorithm can continuously narrow the collection area for iterative correction, solving the technical problems of long iteration time and poor batch consistency in existing algorithms, thus overcoming the shortcomings of existing technologies.

[0008] This invention provides a method for rapid beam pointing and positioning of a satellite antenna for production line communication, comprising the following steps:

[0009] Step S1: Determine the positioning error of the anechoic chamber for the satellite relay vehicle. Combined with the measurement of the farthest distance the horn can be installed Determine the beamwidth of the measuring horn. ;

[0010] Step S2: Install the satellite to be tested onto the satellite transfer vehicle, and fix the satellite transfer vehicle within the positioning error range;

[0011] Step S3: Select three non-collinear observation points in the space within the approximate main lobe region of the satellite payload antenna, and use a measuring horn test to obtain three polar coordinates. (i=1,2,3) and corresponding gains (i=1,2,3);

[0012] Step S4: Establish the equation for solving the satellite beam pointing angle, and substitute the data into the equation to solve for the satellite payload antenna beam pointing angle;

[0013] Step S5: Using the obtained pointing angle, collect signal strength data of the actual communication link and calculate the amplitude error;

[0014] Step S6: Determine whether the calculated error meets the set error; if the calculated amplitude error accuracy is within the set error range, output the beam pointing angle obtained in this solution; if the calculated amplitude error accuracy is not within the set error range, continue to narrow the area within the previous acquisition area, acquire the angle and gain data of 3 non-collinear observation points, and return to repeat step S4.

[0015] Furthermore, this invention provides a method for rapid beam pointing and positioning of a production line communication satellite antenna, which also has the following features: In step S1, the half-power beamwidth of the horn is measured: The solution formula is as follows:

[0016] ;

[0017] in:

[0018] : Measure the half-power beamwidth of a loudspeaker;

[0019] Positioning error in the anechoic chamber of the satellite relay vehicle;

[0020] le: the furthest measured distance;

[0021] Select a measurement horn that meets the requirements for calculating the beamwidth.

[0022] Furthermore, the present invention provides a method for rapid positioning of the beam pointing of a satellite antenna for production line communication, which also has the following features: Step S3 includes the following steps:

[0023] Step S31: Power on the antenna of the satellite payload under test and set the required pointing angle;

[0024] Step S32: Taking the center point of the electrical axis on the satellite payload antenna as the origin, select three non-collinear observation points in the space within the approximate main lobe region of the satellite payload antenna to obtain three polar coordinates. (i=1,2,3);

[0025] Step S33: Move the horn in the darkroom to measure the three polar coordinates. (i=1,2,3) Collect actual signal strength data at the corresponding positions to obtain the corresponding gain points. (i=1,2,3).

[0026] Furthermore, the present invention provides a method for rapid positioning of the beam pointing of a satellite antenna for production line communication, which also has the following features: Step S4 includes the following steps:

[0027] Step S41: Select a three-dimensional Gaussian distribution for the satellite payload antenna pattern. The expression is:

[0028] ;

[0029] in: Peak gain;

[0030] Beam pointing angle (to be solved);

[0031] Related to beamwidth, determined by the half-power beamwidth of the antenna under test. calculate:

[0032] , ;

[0033] Step S42: Take the natural logarithm to construct the equation:

[0034] ;

[0035] in , ;

[0036] make have to:

[0037] (i=1,2,3)

[0038] Step S43: Input the observation point data and construct the difference equation:

[0039]

[0040] make

[0041] , , ;

[0042] , , ;

[0043] The system of equations is then:

[0044] . Attached Figure Description

[0045] Figure 1 This is a diagram showing the positional relationship between the satellite transfer vehicle and the measuring horn in the anechoic chamber in the embodiment.

[0046] Figure 2 This is a schematic flowchart illustrating a method for rapid positioning of the beam pointing of a satellite antenna in a linear communication system. Detailed Implementation

[0047] The present invention will be further described below with reference to specific embodiments.

[0048] Example

[0049] This invention provides a method for rapid beam pointing and positioning of a satellite antenna for production line communication, comprising the following steps:

[0050] Step S1: Anechoic Chamber Preparation: Determine the positioning error of the satellite relay vehicle in the anechoic chamber. Combined with the measurement of the farthest distance the horn can be installed Determine the beamwidth of the measuring horn. .

[0051] The location error of the transfer within a fixed area needs to be determined based on theoretical calculations and actual conditions. ;like Figure 1 As shown, the satellite transfer vehicle is parked within the fixed area of ​​the satellite, that is, within the positioning error range.

[0052] Based on the anechoic chamber dimensions, satellite relay, and the fixed position of the test horn, the maximum achievable distance between the horn and the satellite is the maximum measurement distance. .

[0053] Measuring the half-power beamwidth of a loudspeaker: The formula is as follows:

[0054] ;

[0055] in:

[0056] : Measure the half-power beamwidth of a loudspeaker;

[0057] Positioning error in the anechoic chamber of the satellite relay vehicle;

[0058] le: the furthest measured distance.

[0059] Select a measuring horn that meets the calculated beamwidth and install it in the appropriate position in the anechoic chamber for subsequent measurements. The positioning error of the satellite relay vehicle in the anechoic chamber increases the deviation of the relay vehicle's pointing angle towards the DUT. If the deviation is too large, the measuring horn in the anechoic chamber will not be able to receive signals; therefore, it is necessary to calculate the beamwidth of the measuring horn. This deviation is solved in this method.

[0060] Step S2: DUT Preparation: Install the satellite under test on the satellite transfer vehicle. The satellite transfer vehicle should be parked within the fixed area of ​​the satellite. The calculated measurement horn will be compatible.

[0061] Step S3: Select three non-collinear observation points in the space within the approximate main lobe region of the satellite payload antenna, and use a measuring horn test to obtain three polar coordinates. (i=1,2,3) and corresponding gains (i=1,2,3).

[0062] Step S31: Power on the antenna of the satellite payload under test and set the required pointing angle.

[0063] Step S32: Taking the center point of the electrical axis on the satellite payload antenna as the origin, select three non-collinear observation points in the space within the approximate main lobe region of the satellite payload antenna to obtain three polar coordinates. (i=1,2,3).

[0064] Step S33: Move the horn in the darkroom to measure the three polar coordinates. (i=1,2,3) Collect actual signal strength data at the corresponding positions to obtain the corresponding gain points. (i=1,2,3).

[0065] Step S4: Establish the equation for solving the satellite beam pointing angle, and substitute the data into the equation to solve for the satellite payload antenna beam pointing angle.

[0066] Step S41: Select a three-dimensional Gaussian distribution for the satellite payload antenna pattern. The expression is:

[0067] ;

[0068] in: Peak gain;

[0069] Beam pointing angle (to be solved);

[0070] Related to beamwidth, determined by the half-power beamwidth of the antenna under test. calculate:

[0071] , ;

[0072] Step S42: Take the natural logarithm to construct the equation:

[0073]

[0074] in , ;

[0075] make have to:

[0076] (i=1,2,3)

[0077] Step S43: Input the observation point data and construct the difference equation:

[0078]

[0079] make

[0080] , , ;

[0081] , , ;

[0082] The system of equations is then:

[0083] .

[0084] Step S5: Using the obtained pointing angle, collect the signal strength data of the actual communication link and calculate the amplitude error.

[0085] Power on the antenna of the satellite payload under test and set the pointing angle as follows: Moving the anechoic chamber to measure the loudspeaker, in By collecting actual signal strength data at the corresponding location, the corresponding antenna EIRP value can be calculated. By comparing it with its data packet data or design specifications, the amplitude error can be calculated.

[0086] Step S6: Determine whether the calculated error meets the set error, such as the amplitude error corresponding to 1 / 10 beamwidth.

[0087] If the accuracy of the calculated amplitude error is within the set error range, output the beam pointing angle obtained from this solution.

[0088] If the calculated amplitude error accuracy is not within the set error range, continue to narrow the area within the previous acquisition area, acquire the angle and gain data of 3 non-collinear observation points, and repeat from step S4 until the pointing accuracy is met.

[0089] It should be noted that the method for rapid beam pointing and positioning of a production line communication satellite antenna provided by the present invention is based on the satellite antenna pattern conforming to a three-dimensional Gaussian distribution. In antenna forms such as phased arrays, which provide good directivity and low sidelobe horizontal performance within a specified solid angle, the energy is highly concentrated, the coverage area (azimuth-elevation plane) is relatively uniform, and the energy attenuates rapidly as the angle deviates from the center.

[0090] In addition, the fixed error of the transfer vehicle will cause pointing deviation, and the actual antenna may also deviate from the three-dimensional Gaussian distribution. If the accuracy is not enough, this pointing angle is used as the initial pointing parameter. This algorithm can continuously narrow the area within the original acquisition range and perform iterative correction until the deviation meets the accuracy requirements.

[0091] The embodiments described above are merely some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

Claims

1. A method for rapid positioning of the beam pointing of a satellite antenna in production line communication, characterized in that: Includes the following steps: Step S1: Determine the positioning error of the anechoic chamber for the satellite relay vehicle. Combined with the measurement of the farthest distance the horn can be installed Determine the beamwidth of the measuring horn. ; Step S2: Install the satellite to be tested onto the satellite transfer vehicle, and fix the satellite transfer vehicle within the positioning error range; Step S3: Select three non-collinear observation points in the space within the approximate main lobe region of the satellite payload antenna, and use a measuring horn test to obtain three polar coordinates. (i=1,2,3) and corresponding gains (i=1,2,3); Step S4: Establish the equation for solving the satellite beam pointing angle, and substitute the data into the equation to solve for the satellite payload antenna beam pointing angle; Step S5: Using the obtained pointing angle, collect signal strength data of the actual communication link and calculate the amplitude error; Step S6: Determine whether the calculated error meets the set error; if the calculated amplitude error accuracy is within the set error range, output the beam pointing angle obtained in this solution; if the calculated amplitude error accuracy is not within the set error range, continue to narrow the area within the previous acquisition area, acquire the angle and gain data of 3 non-collinear observation points, and return to re-execute step S4.

2. The method for rapid positioning of satellite antenna beam pointing on a production line as described in claim 1, characterized in that: In step S1, the half-power beamwidth of the horn is measured: the solution formula is as follows: ； in: : Measure the half-power beamwidth of a loudspeaker; Positioning error in the anechoic chamber of the satellite relay vehicle; le: the furthest measured distance; Select a measurement horn that meets the requirements for calculating the beamwidth.

3. The method for rapid positioning of production line communication satellite antenna beam pointing as described in claim 1, characterized in that: Step S3 includes the following steps: Step S31: Power on the antenna of the satellite payload under test and set the required pointing angle; Step S32: Taking the center point of the electrical axis on the satellite payload antenna as the origin, select three non-collinear observation points in the space within the approximate main lobe region of the satellite payload antenna to obtain three polar coordinates. (i=1,2,3); Step S33: Move the horn in the darkroom to measure the three polar coordinates. (i=1,2,3) Collect actual signal strength data at the corresponding positions to obtain the corresponding gain points. (i=1,2,3).

4. The method for rapid positioning of satellite antenna beam pointing on a production line as described in claim 1, characterized in that: Step S4 includes the following steps: Step S41: Select a three-dimensional Gaussian distribution for the satellite payload antenna pattern. The expression is: ； in: Peak gain; Beam pointing angle; Related to beamwidth, determined by the half-power beamwidth of the antenna under test. calculate: , ； Step S42: Take the natural logarithm to construct the equation: ； in , ; make have to: , (i=1,2,3)； Step S43: Input the observation point data and construct the difference equation: ； make , ； ; , ； ; The system of equations is then: 。

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