CSA Engineering has developed a vibration isolation system for use on a medium launch vehicle (Delta II class) which will reduce structure-borne lateral loads imposed on a spacecraft from launch vehicles. Whole-spacecraft isolation is a challenging problem requiring a great deal of system-level and detail design engineering. The concept was to incorporate an isolation system into the payload attach fitting (PAF), which is the structure that connects the spacecraft to the launch vehicle. This program used actual models of spacecraft and launch vehicles. Selected launch environment loads were used in the design trade studies. At the conclusion of the design phase, complete coupled-loads analyses were also performed by McDonnell Douglas Aerospace to verify the performance of the isolation system. Full-scale prototype hardware (69 inches in diameter) was fabricated and tested to verify the analytical models. The isolated payload attach fitting was one-for-one replacement for the original, and flight version will weigh only 5% more than a conventional fitting.

EELV Secondary Payload Adapter (ESPA)

CSA Engineering and the Air Force Research Lab are developing a secondary payload adapter for use on evolved expendable launch vehicles (EELV). This adapter will utilize excess lift capacity on EELV flights and allow up to six small secondary spacecraft to be flown.

• Support 15,000 lb primary spacecraft

• Support six 400 lb secondary spacecraft

• Standard 24 x 24 x 30 payload volume

• Standard 15" interface for secondaries

CSA has designed launch environment mitigation solutions for several launch vehicles:

Contact paul.wilke@csaengineering.com to discuss CSA's capabilities and your requirements.