United States of America As Represented by the Secretary of the Air Force

Gregory E Sanford

Thomas W Murphey

Sungeun K Jeon

Emil Valentin Ardelean

A spacecraft deployment mechanism employing a pair of bi-stable tape springs attached to a cylinder such that rotation of the cylinder extends or retracts the tape springs in opposite directions. The tape springs are fabricated such that they are stable when wrapped around a cylinder (stowed configuration) or when deployed and have a higher energy state when stowed than when deployed. A plurality of bi-stable tape spring mechanisms may be combined to create a deployment device that does not impart rotational torques to the spacecraft during deployment. Deployment may be accomplished by release of the stored energy in the coiled or packaged state progressing to the lower energy deployed state. Alternatively, a motor may be employed to rotate the cylinders for deploy or retrace the tape springs.

Deployable space boom using bi-stable tape spring mechanism

An improved test fixture to evaluate thin composite laminates commonly used in deployable space structures. The fixture is designed to impart a pure moment into the coupon, a necessary improvement to prior test methods where results are obtained by fitting material properties in a nonlinear structural analysis of the test. Fixture mechanics allow for direct calculation of the coupon flexural modulus and allowable flexural strain based on two key measurements, fixture displacement and applied load.

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Albuquerque, NM, United States of America

Gregory E Sanford