To precisely calculate geometric parameters of space-borne optical imaging systems, such as object distance, projection angle, ground sampling distance (GSD), swath width, the effect of earth curvature and projection angle, these imaging systems are researched as nadir imaging and roll imaging. In this paper, a precise geometric model is proposed, which is based on earth curvature and projection angle. Two types of space-borne optical imaging systems are simulated by the model. They are single camera and combined camera with large field of view (FOV). They are on 644.5km orbit, with full field of view 64.44°. The analysis shows that, the GSD of combined camera changes rapidly with field angle, the maximum GSD is 2.07 times of the minimum GSD. The GSD of single camera changes less rapidly with field angle, the maximum GSD is 1.75 times of the minimum GSD. The swath widths of sub-cameras of combined camera are different. The two marginal sub-cameras have larger swath width than the two central ones. Therefore precise calculation of geometric parameters is significative to ensure the imaging quality.
In order to achieve more imaging modes and higher imaging efficiency, the super agile remote sensing satellite is proposed and researched. Super agile remote sensing satellite can realize maneuvering imaging with large angular velocity and large angular acceleration. It has some new characteristics, such as curved imaging trail, variable imaging parameters. In this paper, the feature and theory of maneuvering imaging are studied. The analysis model of maneuvering imaging is established to precisely analyze the complicated and time-varying imaging parameters. Based the model, the change of defocus with roll angle, the change of ground sample distance with roll angle and field of view angle , the change of resultant velocity with different angular velocity, the change of line rate with angular velocity are analyzed. Then the requirements of number of TDI, the MTF of attitude stability, the MTF of synchronization error, the MTF of drift error, are precisely analyzed. The results show that the imaging parameters will change quickly with time and space. The ground sample distance changes from 0.25m to 1.62m. The resultant velocity changes from 7.05km/s to 59.41km/s. The line rate changes from 28.24 kHz to 237.68 kHz. Consequently, super agile remote sensing satellite needs higher line rate, bigger integral number, higher drift correction accuracy and higher synchronization accuracy to improve image quality of maneuvering imaging.
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