Private Enterprise and the Law of Outer Space
- Paper number
IAC-04-IISL.4.06
- Author
Mrs. Patricia Sterns, Law Offices of Sterns and Tennen, United States
- Year
2004
- Abstract
The environmental loads during the satellite launch process are the most critical factors in consideration of the structural strength of a satellite. These environmental loads usually occur in the events of launch vehicle lift-offs, main engines cutoff/ignitions, stage separations, and fairings jettison. These loadings cause the satellite to vibrate in different frequency ranges. Prevention of satellite structure damage by excessive vibration forms an important issue in satellite design practice.
The purpose of this research is to investigate the effect of low frequency vibration control using PZT on a large composite honeycomb panel for space application. Even if extensive studies using PZT in vibration control can be found in literature. Most studies were carried out in small and thin specimens. It is scarce to find actual applications in large sandwich composite panel. This study tends to investigate the vibration control effect in a 100 cm x 70 cm CFRP honeycomb panel, which is used commonly in small satellites.
As a first step, a validated finite element model of the composite sandwich panel was created based on the results from experimental modal testing. Secondly, modal strain energy was computed to allocate the effective areas for PZT application for each individual vibration mode. LC resistive shunt circuit method is applied in this study. Control circuit design will be detailed in this paper.
The vibration attenuation effect was demonstrated by experimental test measurement. Two kinds of test forcing functions, 161.5 Hz sinusoidal loading and 0-300 Hz random loading, are adapted for time-domain response verification. Results show that 22.0
- Abstract document