Johns Hopkins University

David F Persons

Clint T Apland

Robert A Summers

Aaron Q Rogers

David R Weir

Michael T Marley

An adaptor system includes a space vehicle separation plate operably coupled to a space vehicle, a launch vehicle adaptor plate operably coupled to a launch vehicle capable of carrying the space vehicle into space for release of the space vehicle from the launch vehicle, an actuator release mechanism assembly, a bend/shear restrain assembly that is non-coaxial with the actuator-release connector, and a biasing element. The actuator-release mechanism assembly may be configured to separably couple the space vehicle separation plate to the launch vehicle adaptor plate. The actuator-release mechanism assembly may pass through the launch vehicle adaptor plate to engage the space vehicle separation plate to hold the space vehicle separation plate substantially parallel to the launch vehicle adaptor plate prior to release of the space vehicle separation plate.

Adaptor system for deploying small satellites

An actuator includes a capturing part, a retained part and a heating element which applies heat to the retained part or the capturing part responsive to selective application of power to the at least one heating element. The capturing part attaches to a first object and has a first coefficient of thermal expansion. The retained part attaches to a second object and has a second coefficient of thermal expansion. The retained part is insertable into the capturing part in a first state of the actuator. The retained part is held in contact with the capturing part via an interference fit to hold the first and second objects proximate to each other in a second state. The retained part is ejected from the capturing part in a third state. Applying heat via the heating element causes a transition between the second and the first or third states of the actuator.

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Columbia, MD, United States of America

David F Persons