Advanced Iso-Grid Fairing Qualification Test for Minotaur Launch Vehicle
Abstract
The development of the grid-stiffened fairing to be flown on the Minotaur launch vehicle has made significant progress over the past five years. This qualification structure was subjected to static qualification testing. The 6 m (20 ft) tall fairing was constrticted of a carbon fiber composite grid structure that was over-wrapped to create a laminated skin. Upon completion of curing and machining, the fairing was cut in half to create the classic clam shell fairing. Metallic joints were bonded and fastened to the fairing at all interfaces to complete the assembly process and simulate attachment of the base to a launch vehicle. Static qualification of the fairing tested the integrity of the fairing, thereby proving the design and manufacturing process. Loads were applied incrementally in a static loading scenario. The applied load envelope exceeded worst case dynamic flight conditions with an added safety factor of 25%. At peak load the fairing must maintain stiiictural integrity remaining within the defined dynamic displacement envelope.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 2003
- Accession Number
- ADA451647
Entities
People
- Greg Sanford
- Jeffry Welsh
- John E. Higgins
Organizations
- Air Force Research Laboratory