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Effects of Payload Motion on the Attitude Behavior of a Spinning Spacecraft (en Inglés)
Srihari Gowri Shankar (Autor)
·
Grin Verlag
· Tapa Blanda
Effects of Payload Motion on the Attitude Behavior of a Spinning Spacecraft (en Inglés) - Srihari Gowri Shankar
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Reseña del libro "Effects of Payload Motion on the Attitude Behavior of a Spinning Spacecraft (en Inglés)"
ISBN: 9783656028000 Géneros: Sinópsis: Masters Thesis from the year 2011 in the subject Engineering Mechanical Engineering grade none University of California Davis language English abstract Spacecraft systems almost always include subsystems such as imaging or scanning instruments that are designed to move relative to the main spacecraft body during some part of the spacecrafts mission Depending on the relative size and location of such moving parts their motion can have appreciable effects on the overall translational andor rotational motion of the spacecraft This research project investigates the impact of oscillatory motion of the spacecraftmounted payload on the global attitude behavior of the spacecraft The investigation is carried out by first deriving the equations of attitude motion of a spacecraft system that consists of a main cylindrical body to which are connected four slender rods each of which has a prescribed oscillatory motion relative to the main body The main body is given initial spin and transverse angular velocities and the resulting nutation angle is monitored over time The results obtained show that oscillatory motion of a payload relative to the main spacecraft body will in general attenuate the spacecrafts nutation The degree of nutation attenuation depends on several factors including the inertia of the payload compared to that of the spacecraft the location of the payload on the spacecraft the frequency of the payloads motion and the amplitude of such motion The implication of these results is that payload motion can be exploited to assist a spacecrafts nutation damper system In fact any movable payload can save as a backup nutation damper if the designated nutation damper should fail
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