Calculations were made with software package MARC K 7.2, and with the pre- and postprocessor MENTAT 3.2.

Calculations are made of,

- eigenfrequencies in deployed position; MARC allows for a more realistic mass distribution in the model than used in the 'Assessment' leading to better estimates of the eigenfrequencies;

- deployment; MARC is especially suited for non-linear processes, for large strains, and for large displacement as the antenna will experience during deployment;

- antenna response to antenna foot-point excitation owing to spacecraft maneuvering; the response to a random excitation and to a sudden pulse-like excitation, did not lead to dangerous level of accelerations or forces with could threaten the antenna.

The 3 lowest frequency global eigen-oscillations of the deployed antenna are

1) 3.89 Hz, torsion oscillations of Mast-1;

2) 3.992 Hz, bending oscillations of Mast-1 in the vertical plane (YZ-plane);

3) 5.253 Hz, torsion oscillations of Mast-1

- For a force moment with a minimum value of 500Nmm the antenna masts will deploy without danger for colliding with the spacecraft.

- For a force moment with a minimum value of 200 Nmm the dipole- and reflector elements will deploy properly.

- The strains during deployment will not cause mechanical damage.

- The antenna will not 'over-shoot' during deployment.

- If the reflectors open after >0.5s they will not hit the spacecraft.

- Mast-1 requires about 1s to deploy 90 degrees;

- Mast-2 requires about 2.4s to deploy 90 degrees;

- Manchet-1 and Manchet-2 prevents that the masts overshoot during deployment.

- After about 4s the rest vibrations have subsided.

- It has been demonstrated that the accelerations associated with foot-point excitations are too small to cause material damage to the deployed antenna.

The results are available in MARC data files from anonymous ftp site osf1.mpae.gwdg.de/pub/mpae/consert/outgoing :