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Method for simulating solar motion
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A technology for simulating the sun and the sun. It is applied in the field of simulating object motion and simulating solar motion. It can solve the problems of reducing model unreliability, increasing the pressure of satellite remote control channels, and being unable to eliminate model truncation errors. It achieves the effect of small errors and simple calculations.
Inactive Publication Date: 2010-10-13
SHANGHAI ENG CENT FOR MICROSATELLITES
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[0012] The above method includes the remote control process, which increases the pressure on the satellite remote control channel and reduces the unreliability of the model; the remote control process can only eliminate the error caused by the small change of astronomical parameters to the model, but cannot eliminate the model truncation error
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Embodiment 1
[0030] see figure 1 , the invention discloses a method for simulating solar motion, the method comprising the steps of:
[0031] Step A. Obtaining the true celestial longitude of the sun and the flat celestial longitude of the sun in the set time period. The solar true celestial longitude and the solar flat celestial longitude of the set time period can be obtained through accurate models or forecasts from authoritative departments.
[0032] Step B. Analyzing and comparing the above two sets of data to obtain the fluctuation curve of the Taiyangzhenhuang meridian relative to the Taiyangpinghuang meridian in the time period.
[0033] Step C, according to the satellite attitude determination accuracy requirements, the fluctuation curve is fitted, and the obtained solar eclipse longitude U S ; s = M 0 +k 1 d+k 2 sin(2π / 365.25d); where, M 0 is a known moment t 0 The true celestial longitude of the sun; d=t / (24*3600), t is relative to t 0 time; k 1 , k 2 is the coefficie...
Embodiment 2
[0040] In the present embodiment, the method for simulating solar motion comprises the steps:
[0041] Step A', obtain the solar true celestial longitude and the solar flat celestial longitude of each day between 0:00 on January 1, 2007 and 0:00 on January 1, 2015 through an accurate model or the forecast of an authoritative department.
[0042] Step B', analyze and compare the two sets of data, and obtain the fluctuation curve of the true yellow meridian of the sun relative to the flat yellow meridian of the sun during the time period from 0:00 on January 1, 2007 to 0:0 on January 1, 2015; the fluctuation curve Such as figure 2 shown.
[0043] Step C', according to the satellite attitude determination accuracy requirements, the fluctuation curve is fitted. The accuracy of attitude determination using satellites is required to be 0.5 degrees, and only one fitting is required. Taking the true yellow meridian at 0:0 on January 5, 2008 as the starting point, the fitting analy...
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Abstract
The invention discloses a method for simulating solar motion which comprises the steps as follows: step A. solar true longitude and solar mean longitude in a set time period are obtained; step B. the two groups of data are analyzed and compared to obtain a volatility curve of solar true longitude relative to solar mean longitude in the time peorid; step C. fitting is carried out to the volatilitycurve according to attitude determination precision requirement of a satellite, so as to obtain solar true longitude US; step D. the obtained solar true longitude US]is fit and substituted into solarmotion model to obtain solar reference information which is needed for attitude determination of the satellite. The method for simulating solar motion of the invention uses a simple method to describecomplex solar motion discipline and has simple operation. At the same time, the method for simulating solar motion is free of remote-control correcting means. The method for simulating solar motion has small error and the error is stable and free of increasing along with time.
Description
technical field [0001] The invention belongs to the technical field of attitude measurement of spacecraft and satellites, and relates to a method for simulating the motion of an object, in particular to a method for simulating the motion of the sun. Background technique [0002] Due to the complex system, high cost and irreparable features of satellites, reliability requirements are often put at the top of the list. As one of the satellite core technologies, the reliability of the attitude control technology determines the success or failure of the satellite mission. Using simple and reliable components and methods, on the other hand, increases system redundancy configuration. [0003] The satellite attitude controlsystem consists of two parts: attitude determination and control. Its task is to ensure that the satellite attitude meets the mission requirements. Attitude determination is the basis of control, which consists of attitude sensor, attitude determination algori...
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