The Mars Lasercom Program involves sensitive satellite and electro-optical packages that are mounted on a honeycomb panel that is attached to the spacecraft. Because the vibration and shock response characteristics of this panel are critical to the survival of the electronic and optical components this project involved evaluating shock and vibration mitigation techniques to protect these components. After performing a comprehensive search of commercially available shock and vibration isolators it was determined that the most appropriate isolators for this project would be the Lord Corp HTC Series mounts. Tradeoffs between different design options were weighed and several designs were further evaluated with two final designs determined to be optimal, one that would isolate the panel and one that would rigidly attach it. Both designs should use a 1.5" aluminum honeycomb core and a core foil thickness of .001". The rigidly attached concept should be attached at the five points, while the isolated concept should be use three isolators along the bottom edge and four isolators along the top edge of the panel to attach to the spacecraft.

• This report represents the work of one or more WPI undergraduate students submitted to the faculty as evidence of completion of a degree requirement. WPI routinely publishes these reports on its website without editorial or peer review.

Creator

• Holland, Jared David

Publisher

• Worcester Polytechnic Institute

Identifier

• 04B016M

Advisor

• Johari, Hamid
• Gatsonis, Nikolaos A.

Year

• 2004

Center

• MIT Lincoln Laboratory-Lexington, Massachusetts Project Center - MQP

Sponsor

• MIT Lincoln Laboratory

Date created

• 2004-01-01

Resource type

• Major Qualifying Project

Major

• Mechanical Engineering

Rights statement

• In Copyright