Solar radio telescope tracking error real-time correction method

Abstract

The application discloses a real-time correction method for tracking errors of a solar radio telescope, and comprises the following steps: dividing a running track of the solar radio telescope into at least one track section, calibrating a solar projection of a starting point and an ending point of each track section, measuring azimuth angle errors and elevation angle errors of the starting point and the ending point of each track section, calculating an azimuth angle error slope and an elevation angle error slope of each track section, calculating the azimuth angle errors and the elevation angle errors of any position on each track section according to the error slopes, and correcting azimuth angles and elevation angles of any position on each track section in real time. The tracking precision of the solar radio telescope can be improved by using the method.

Description

Technical Field

[0001] This invention belongs to the field of space science, specifically relating to a method for real-time correction of tracking errors in solar radio telescopes. Background Technology

[0002] The solar radio telescope is a ground-based instrument for observing the F10.7 solar radiation index. It mainly consists of three parts: a parabolic antenna, a receiver, and a pointing drive mechanism. The antenna or antenna array collects solar radiation electromagnetic waves and transmits them to the receiver via a feed line. The receiver records the solar radiation electromagnetic waves, processes them according to specific requirements, and then displays them. In the field of space weather applications, the F10.7 solar radiation index is the intensity of solar radiation within a 100MHz bandwidth centered at 2800MHz (electromagnetic waves with a wavelength of 10.7cm). It is an important parameter characterizing the level of solar activity, and its fluctuations have a significant impact on the Earth's middle and upper atmosphere, ionosphere, and space weather. The F10.7 solar radiation index is an essential driving index for space environment applications and a crucial space environment index for aerospace engineering. Real-time and accurate monitoring of the F10.7 solar radiation index has significant scientific and engineering application value.

[0003] With the continuous development of solar radio observation technology in my country, high-precision, unattended, and remote control of observation equipment will increasingly become urgent tasks. The tracking accuracy of the solar radio telescope is the most important factor in ensuring the accuracy of the F10.7 solar radiation index measurement; its receiving antenna must be accurately pointed to the sun in real time. Currently, automatic tracking technology for solar radio telescope antennas mainly uses the synchronous satellite method for coarse calibration of the antenna, and uses inverse coordinate transformation for error compensation; calibration tower technology can also be used, where a suitable calibration tower is set up near the antenna field to calibrate the antenna's pointing accuracy. However, these methods cannot correct tracking errors caused by the solar radio telescope's servo control system and antenna foundation in real time. Summary of the Invention

[0004] The technical problem to be solved by this invention is to correct the tracking error during the operation of a solar radio telescope in real time.

[0005] To achieve the above objectives, the present invention provides a method for real-time correction of tracking errors in solar radio telescopes, comprising:

[0006] Step 1: Divide the trajectory of the solar radio telescope into at least one trajectory segment;

[0007] Step 2: Measure the azimuth and elevation angle errors of the starting and ending points of each trajectory segment;

[0008] Step 3: Calculate the azimuth error slope and elevation error slope for each trajectory segment;

[0009] Step 4: Calculate the azimuth and elevation angle errors at any position on each trajectory segment based on the error slope;

[0010] Step 5: Correct the azimuth and elevation angles of any position on each trajectory segment in real time.

[0011] An improvement to the above method is that step 1 involves dividing the trajectory of the solar radio telescope into 3 to 7 trajectory segments.

[0012] An improvement based on the above method is that step 2 performs solar projection calibration on the starting and ending points of each trajectory segment, and measures the azimuth and elevation angle errors of the starting and ending points of each trajectory segment.

[0013] An improvement to the above method is the slope K of the azimuth error for each trajectory segment in step 3. Φ and elevation angle error slope K θ The calculation method is as follows:

[0014]

[0015]

[0016] in, The azimuth angle of the starting point of the trajectory segment; The azimuth angle of the end point of the trajectory segment; The azimuth error of the starting point of the trajectory segment; Δθ1 is the azimuth error at the end point of the trajectory segment; Δθ2 is the elevation angle error at the start point of the trajectory segment; Δθ3 is the elevation angle error at the end point of the trajectory segment.

[0017] An improvement to the above method is the azimuth error at any position on each trajectory segment in step 4. and elevation angle error Δθ t The calculation method is as follows:

[0018]

[0019]

[0020] in, Azimuth angle of the starting point of the current trajectory segment; K represents the azimuth angle before correction at any position on the current trajectory segment; Φ The slope of the azimuth error of the current trajectory segment; K represents the azimuth error of the starting point of the current trajectory segment; θ Δθ1 is the elevation angle error slope of the current trajectory segment; Δθ1 is the elevation angle error of the starting point of the current trajectory segment.

[0021] An improvement to the above method is the corrected azimuth angle at any position on each trajectory segment in step 5. The method for calculating the elevation angle θ is as follows:

[0022]

[0023]

[0024] in, This represents the azimuth error at any position on the current trajectory segment; Δθ is the azimuth angle before correction at any position on the current trajectory segment. t θ represents the elevation angle error at any position on the current trajectory segment. t The elevation angle before correction for any position on the current trajectory segment.

[0025] Compared with the prior art, the advantage of the present invention is that it can correct the tracking error of the solar radio telescope in real time, thereby improving the tracking accuracy of the solar radio telescope. Attached Figure Description

[0026] Figure 1 The diagram shows a flowchart of a real-time tracking error correction method for solar radio telescopes.

[0027] Figure 2 The image shows a schematic diagram of the trajectory of the solar radio telescope. Detailed Implementation

[0028] This invention divides the trajectory of a solar radio telescope into at least one trajectory segment, performs solar projection calibration on the start and end points of each trajectory segment, measures the azimuth and elevation errors at the start and end points of each trajectory segment, calculates the azimuth and elevation error slopes for each trajectory segment, calculates the azimuth and elevation errors at any position on each trajectory segment based on the error slopes, and performs real-time correction of the azimuth and elevation angles at any position on each trajectory segment.

[0029] The technical solution of the present invention will now be described in detail with reference to the accompanying drawings.

[0030] like Figure 1 As shown, the present invention provides a method for real-time correction of tracking errors in a solar radio telescope, comprising:

[0031] Step 1: Based on the actual observation requirements of the solar radio telescope, divide the trajectory into at least one trajectory segment; considering both the required accuracy and reasonable workload, dividing the trajectory into 3 to 7 trajectory segments is a more reasonable range.

[0032] Step 2: By performing solar projection calibration on the starting and ending points of each trajectory segment, the center of the solar radio telescope antenna is aligned with the sun, and the azimuth and elevation angle errors of the starting and ending points of each trajectory segment are measured.

[0033] like Figure 2 As shown, when the solar radio telescope reaches position 1, the azimuth and elevation angles of its trajectory segment are... Due to tracking errors caused by the solar radio telescope's servo control system and antenna foundation, the antenna pointing of the solar radio telescope is deviated; therefore, the azimuth and elevation angle errors after solar projection calibration are different from those before calibration.

[0034] Similarly, when the solar radio telescope reaches position 2, the end point of its trajectory segment, its azimuth and elevation angles are... After solar projection calibration, the azimuth and elevation angle errors compared to before calibration are:

[0035] Step 3: Calculate the azimuth error slope and elevation error slope for each trajectory segment;

[0036] The azimuth error slope K for each trajectory segment is calculated using the following formula. Φ and elevation angle error slope K θ :

[0037]

[0038]

[0039] Step 4: Calculate the azimuth and elevation angle errors at any position on each trajectory segment based on the error slope.

[0040] like Figure 2 As shown, when the telescope returns to the area between the start and end points of the trajectory segment at a certain time t, the azimuth and elevation angles before correction are: The azimuth error and elevation error are calculated using the following formula based on the error slope:

[0041]

[0042]

[0043] Step 5: Correct the azimuth and elevation angles at any position on each trajectory segment.

[0044] like Figure 2 As shown, when the telescope returns to the area between the start and end points of the trajectory segment at a certain time t, the azimuth and elevation angles before correction are: The corrected azimuth and elevation angles are calculated using the following formula:

[0045]

[0046]

[0047] By dividing the trajectory of the solar radio telescope into at least one trajectory segment using the above method, the azimuth and elevation error slopes of all trajectory segments on the trajectory of the solar radio telescope can be determined, and the tracking error at any position on the trajectory of the solar radio telescope can be corrected in real time.

[0048] In this embodiment, the trajectory of the solar radio telescope is divided into three trajectory segments. Solar projection calibration of the trajectory is performed at four time points: 9:00, 11:00, 13:00, and 15:00. The azimuth, elevation, azimuth error, and elevation error are measured at each of these locations. Each two adjacent selected points constitute one trajectory segment, resulting in a total of three trajectory segments. The slopes of the azimuth and elevation errors for each of the three trajectory segments are calculated, as shown in the table below.

[0049]

[0050] The azimuth and elevation angle errors at any position on the three trajectory segments are calculated based on the error slope. The azimuth and elevation angles at any position on the three trajectory segments are then corrected for the errors. The actual test results meet the high-precision tracking requirements of the solar radio telescope.

[0051] This method is used to correct the tracking error of the solar radio telescope, achieving the goal of real-time correction of the tracking error at any position on the solar radio telescope's trajectory, thus improving the tracking accuracy of the solar radio telescope.

[0052] This method is applicable not only to real-time correction of tracking errors of solar radio telescopes, but also to real-time correction of trajectory errors of equipment tracking the sun, satellites, or other moving targets.

[0053] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to the embodiments, those skilled in the art should understand that modifications or equivalent substitutions to the technical solutions of the present invention do not depart from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A method for real-time correction of tracking errors in a solar radio telescope, comprising: Step (1): Divide the trajectory of the solar radio telescope into at least one trajectory segment; Step (2): Measure the azimuth and elevation angle errors of the starting and ending points of each trajectory segment; Step (3): Calculate the azimuth error slope and elevation error slope for each trajectory segment; Step (4): When the telescope moves to a certain position again, calculate the azimuth error and elevation error of that position based on the error slope of the trajectory segment to which that position belongs; Step (5): Correct the azimuth and elevation angles of the telescope's current position in real time; In step (2), the starting and ending points of each trajectory segment are calibrated by solar projection, and the azimuth and elevation errors of the starting and ending points of each trajectory segment are measured.

2. The real-time correction method for tracking errors of a solar radio telescope according to claim 1, characterized in that, Step (1) involves dividing the trajectory of the solar radio telescope into 3-7 trajectory segments.

3. The real-time correction method for tracking errors of a solar radio telescope according to claim 1, characterized in that, The azimuth error slope K of each trajectory segment in step (3) Φ and elevation angle error slope K θ The calculation method is as follows: in, The azimuth angle of the starting point of the trajectory segment; The azimuth angle of the end point of the trajectory segment; The azimuth error of the starting point of the trajectory segment; Δθ1 is the azimuth error at the end of the track segment; Δθ2 is the elevation angle error at the start of the track segment; Δθ3 is the elevation angle error at the end of the track segment.

4. The real-time correction method for tracking errors of a solar radio telescope according to claim 1, characterized in that, The azimuth error at any position on each trajectory segment in step (4) and elevation angle error Δθ t The calculation method is as follows: in, This is the azimuth angle of the starting point of the current trajectory segment; K represents the azimuth angle before correction at any position on the current trajectory segment; φ The slope of the azimuth error of the current trajectory segment; K represents the azimuth error of the starting point of the current trajectory segment; θ Δθ1 is the elevation angle error slope of the current trajectory segment; Δθ1 is the elevation angle error of the starting point of the current trajectory segment.

5. The real-time correction method for tracking errors of a solar radio telescope according to claim 1, characterized in that, The corrected azimuth angle at any position on each trajectory segment in step (5) The method for calculating the elevation angle θ is as follows: in, This represents the azimuth error at any position on the current trajectory segment; Δθ is the azimuth angle before correction at any position on the current trajectory segment. t θ represents the elevation angle error at any position on the current trajectory segment. t The elevation angle before correction for any position on the current trajectory segment.

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