Approach to Reducing Vibroactivity of Small Spacecraft

Abstract

Flawless spacecraft operation and successful implementtation of their research in orbit mainly depend on technical and operational characteristics of the spacecraft orientation and stabilization control systems in space relative to the base frame of reference axes achieved through stabilizing properties of certain external and internal perturbations. The research was aimed at determining static and dynamic imbalances and analyzed the levels of influence of forces and moments created by non-contact electric motor-flywheel operating at the various rotor speeds. In order to reduce the static and dynamic imbalance of the non-contact electric motor-flywheel obtained as a result of ongoing experimental studies, it was proposed to introduce a vibration isolator with natural frequency significantly lower than that in the conventional systems in order to statically hold the non-contact electric motor-flywheel during ground and flight operation. The vibration isolator should have small mass and rigidity, as well as a wide range of operating temperatures, etc. Depending on the orbit altitude, the moments of external disturbing forces acting on the Iskra-5 spacecraft were determined. Electric DC motor-flywheels of various types were analyzed. It was shown that introduction of the non-contact electric motor-flywheel as the executive element of the orientation and stabilization control systems on small spacecraft improved the orientation accuracy. Ways to reduce the effect of vibration disturbances on the spacecraft structure from the non-contact electric motor-flywheel were considered