Simulation analysis method for drift correction angle during remote sensing satellite attitude maneuver
A technology of bias current correction angle and attitude maneuvering, applied in the direction of measuring devices, instruments, etc., can solve the problems of complex derivation process, inability to verify the correctness and accuracy of on-board algorithms, and insufficient calculation accuracy
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[0054] For a TDICCD remote sensing satellite in a sun-synchronous orbit at an altitude of 650 kilometers, the orbital parameters are: semi-major axis=7023.14 kilometers; eccentricity=0; orbital inclination=97.9708 degrees; perigee depression angle=0 degrees; ascending node longitude=337.752 degrees ; Mean anomaly = 0 degrees. According to the general satellite design, set the X of the satellite body coordinate system B o B Y B The plane is the CCD imaging plane. In the case of only considering the maneuverability of the satellite's side swing attitude, N=5000s, Δt=1s, through each step of the method of the present invention, by setting different side swing angles (0°, 15°, 25°, 35° are set here) °), high-precision bias current correction angle data can be obtained through simulation analysis. The specific results are as follows Image 6 As shown in the figure, the relationship between the bias current correction angle and the satellite latitude is given in the figure. Whe...
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