The imaging stability enhancement of optical payload using multiple vibration isolation platforms

To reduce high frequency vibration propagated into the optical payload on spacecraft, multiple vibration isolation platforms are employed. This means that the vibration isolation platform can not only be used to isolate the disturbances caused by the actuators such as control moment gyros or the reaction wheels (RWs), but it can also be placed between the spacecraft bus and optical payload. The dynamic modeling of the spacecraft with multiple vibration isolation platforms and its applications are discussed. Firstly, the spacecraft dynamic model with only one vibration isolation platform is derived using the Newton-Euler approach. Then the integrated spacecraft dynamic formulation is obtained based on the above dynamic model with only one vibration isolation platform. Multiple vibration isolation platforms are used to interface the disturbance source with the spacecraft bus. For example, each RW could have a vibration isolation platform to reduce the vibration. The frequency domain characteristics and the safety reliability of the spacecraft with multiple vibration isolation systems are discussed based on the above dynamic model. Finally, the validity of the dynamic model of the integrated spacecraft with multiple vibration isolation platforms can be proved by numerical simulation. Other than that, the simulation results illustrate the ameliorative effect of multiple vibration isolation platforms on the optical payload attitude stabilization.