This paper investigates the effect of a temperature shock on small spacecraft with symmetrically arranged flexible elements. A two-dimensional thermoelasticity problem is posed. The disturbing has been determined. assessment main factors arising from elements was carried out. Approximate dependences were obtained for components displacement vector element points. Numerical simulation out symmet...

Minimizing the modal vibration induced by on-off thrusters is a challenging problem for designers of flexible spacecraft. This thesis presents the first study of PulseWidth, Pulse-Frequency (PWPF) modulated thruster control using the method of command input shaping. Input shaping for systems with linear actuators has been successfully developed to reduce modal vibrations. Recently, this method ...

In this paper, we design a robust adaptive controller for a flexible spacecraft model. Specifically, the proposed framework involves a new and novel controller architecture involving a modification term in the update law that minimizes an error criterion involving the distance between the weighted regressor vector and the weighted system error states. This modification term allows for fast adap...

A hybrid control scheme for vibration reduction of flexible spacecraft during rotational maneuvers is investigated by using variable structure output feedback control (VSOFC) for attitude control and smart materials for active vibration suppression. The proposed control design process is twofold: design of the attitude controller using VSOFC theory acting on the hub and design of an independent...

In order to support the development of high–precision spacecraft, current state Stewart vibration isolation platform in field aerospace micro–vibration was surveyed. First, based on analyses causes and characteristics spacecraft micro–vibration, principles, characteristics, advantages disadvantages four technologies are summarized. Second, process platform, from structural proposal theoretical ...