Usually, Reaction Wheel Assemblies (RWAs)are actuators used for satellite attitude control. During their functioning RWAs produce undesired disturbances transmitted through satellite structure and can significantly affect the performance of vibration-sensitive payload. Micro-vibrations of a satellite reaction wheel assembly are commonly analyzed in either hard-mounted or coupled boundary conditions, though coupled wheel-to-structure disturbance models are more representative of the real environment in which the wheel operates. Micro-vibration is a phenomenon that affects the payload pointing. In this article we want to assess a solution to passively damp and decouple the disturbance noise transferred from wheel to the supporting honeycomb panel. A couple of core and skins thicknesses of honeycomb plate; in addition, to cell thickness and size were evaluated to access their damping efficiency on micro-vibration source. Simulations show that, the core thickness is more effective for micro-vibration suppression and issues about micro-vibration in integrated design.
Parametric Essessment of Honeycomb Panel for Passive Micro-Vibration Damping Induced by Reaction Wheel
2019-06-01
1238108 byte
Conference paper
Electronic Resource
English