Payload Isolation System for Launch Vehicles

Reducing the dynamic response of spacecraft during launch will have a number of benefits in their design, test, and operations phases and will allow mission performance, rather than launch survivability, to be the primary goal of structural design. This SBIR proposes to integrate an isolation system into the interface adaptor between the launch vehicle and the spacecraft. Besides the increase in launch survivability, a pauload isolator system will also reduce cost, weight, and size of some spacecraft components; allow isolator redesign rather than spacecraft requalification; relieve launch vehicle loads; and relax dynamic coupling design, analysis and test requirements. Phase I of this effort will develop concepts and provide supporting analysis for an innovative payload/adaptor isolation system. Phase I will determine which passive and/or active vibration control technologiess are most applicable. A preliminary design of a payload/adaptor/isolation will be formulated, and analysis will be performed to determine it effectiveness. Work will also begin on a comprehensive spacecraft isolator design procedure. Phase II will demonstrate system effectiveness for representative payload and launch vehicle configurations through critical component hardware testing coupled with additional analysis and simulation. Phase III will provide a adaptor/isolator system for flight demonstration.