The Infona portal uses cookies, i.e. strings of text saved by a browser on the user's device. The portal can access those files and use them to remember the user's data, such as their chosen settings (screen view, interface language, etc.), or their login data. By using the Infona portal the user accepts automatic saving and using this information for portal operation purposes. More information on the subject can be found in the Privacy Policy and Terms of Service. By closing this window the user confirms that they have read the information on cookie usage, and they accept the privacy policy and the way cookies are used by the portal. You can change the cookie settings in your browser.
While attitude steering in the yaw and pitch axes effectively minimizes a residual Doppler centroid in spaceborne synthetic aperture radar systems, it can induce a ground–target pointing error due to the steered radar boresight. In other words, the beams after steering may no longer illuminate the desired target. In this letter, a novel method is proposed to compensate for the target error. The roll...
This paper focuses on unmanned aircraft guidance laws for a straight path and a circular orbit following using the vector field approach. The vector fields introduced in this paper can be applied to not only path following, but also other purposes such as arrival position, angle, and time control. Therefore, they could be applied to various missions providing advantages over other previous vector...
Nowadays, Earth observation satellites are widely used to acquire high quality, and the satellites should have more observation missions at the same time. In this case, it is useful to develop a systematic command generation method for satellite pointing to acquire wide area image efficiently. In this paper, three efficient methods are proposed to operate Earth observation satellite attitude pointing...
A lunar orbital capture guidance law is presented for a spacecraft with electrical propulsion system using Lyapunov feedback control approach. Construction of the Lyapunov function candidate is based on orbital elements which consist of angular momentum and eccentricity vectors. Unlike the orbit transfer problem between closed orbits, the lunar capture problem has two constraints. One thing is that...
Set the date range to filter the displayed results. You can set a starting date, ending date or both. You can enter the dates manually or choose them from the calendar.