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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

Active Publication Date: 2014-02-19
AEROSPACE DONGFANGHONG SATELLITE
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  • Abstract
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Problems solved by technology

[0006] In the traditional analysis method of drift angle, geometric analysis and formula derivation are used for calculation. The biggest disadvantage of this method is that it relies on too many assumptions, which directly leads to insufficient calculation accuracy. It can only be used as a qualitative analysis and cannot be used. A low-precision result to verify the correctness and accuracy of the on-board algorithm
Moreover, with the use of satellite pitching and attitude maneuvering capabilities, the characteristics of the complex derivation process and low accuracy of the geometric analysis method are more apparent
The correction accuracy of the drift angle is closely related to the imaging quality. Therefore, the traditional qualitative analysis method forms an uncontrolled loophole in the design and verification process of the satellite imaging link, which is not conducive to quantitatively grasping the satellite’s Orbit image quality

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  • Simulation analysis method for drift correction angle during remote sensing satellite attitude maneuver
  • Simulation analysis method for drift correction angle during remote sensing satellite attitude maneuver
  • Simulation analysis method for drift correction angle during remote sensing satellite attitude maneuver

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Embodiment

[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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Abstract

The invention relates to a simulation analysis method for a drift correction angle during remote sensing satellite attitude maneuver. According to the present invention, a simulation tool is adopted to establish a satellite and a satellite sensor, and the longitude and the latitude of the intersection point of a sensor visual axis and an earth model are acquired in the given time period; according to the longitude and the latitude, feature points are established on the earth model; the coordinates of each feature point at the current time point and the next time point in a J2000 coordinate system are acquired; in the J2000 coordinate system, the following velocity vector of the current feature point at the current time in the J2000 coordinate system, and the movement velocity vector of the current feature point relative to the satellite in the J2000 coordinate system are respectively acquired; the vector composition of the velocity is adopted to acquire the total velocity vector of the movement of the current feature point relative to the satellite in the J2000 coordinate system; a CCD imaging plane is established in the satellite model; the projection of the total velocity vector in the CCD imaging plane of the satellite is acquired by projecting; the included angle formed by the projection vector and the normal line direction of the CCD linear array is the drift correction angle.

Description

technical field [0001] The invention relates to a method for acquiring the drift correction angle on the satellite during satellite attitude maneuvering through simulation analysis. Background technique [0002] The definition of drift angle is derived from aviation terminology. It is defined as when there is a crosswind, the actual track of the aircraft is inconsistent with the heading of the aircraft, and the angle between the heading line and the track line is called the drift angle. When the satellite revolves around the earth, due to the rotation of the earth, the objects on the surface of the earth will have an implicated speed along the direction of the earth's self-propagating angular velocity. Inconsistent direction (course line), also known as drift angle. [0003] The definition of the drift correction angle is derived from the satellite with attitude maneuvering capability. When the satellite is performing pitch and roll maneuvers, in order to ensure the satelli...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00
Inventor 朱兴鸿王瑞陆春玲
Owner AEROSPACE DONGFANGHONG SATELLITE