M.m.a. Design, LLC

Other

Shane Eric Stamm

Thomas Jeffrey Harvey

Toby Justin Harvey

Mitchell T Wiens

Mark A Bailey

Christopher A Pelzmann

Seth Murray

Greg Wolos

Ryan Tucker Southern

A deployable structure for use in establishing a reflectarray antenna is provided that includes a flexible reflectarray and a deployment structure that includes an endless pantograph for deploying the flexible reflectarray from a folded, undeployed state towards a deployed state in which the flexible reflectarray is substantially planar. In a particular embodiment, the deployment structure includes a plurality of tapes that engage the endless pantograph and are used to establish a positional relationship between the deployed reflectarray and another component of the reflectarray antenna.

Deployable structure for use in establishing a reflectarray antenna

A deployable thin membrane apparatus for use with a spacecraft is provided. The apparatus includes a flexible membrane structure and a deployment mechanism for transitioning the membrane structure from an undeployed state towards a deployed state in which the membrane can perform a function needed by a spacecraft. In one embodiment, the deployment mechanism includes a plurality of pantographs that each engage the membrane structure, a rotatable disk structure that engages and coordinates the transition of the pantographs from an undeployed state towards a deployed state, and a spring system for providing energy that is used to rotate the disk structure.

Deployable thin membrane apparatus

A thin membrane structure for stabilizing a spacecraft is provided. The spacecraft has a first end and a second end. The spacecraft has a center of pressure and a center of gravity. The thin membrane structure comprises a module secured to the spacecraft and a structure having a polygonal base and a plurality of triangular side panels meeting in a point opposite the base with the point secured to the module. Prior to deployment, the structure is entirely contained within the module. Subsequent to deployment, the structure expands to a pyramidal shape with the distance between the center of pressure and the center of gravity increasing to a length greater than approximately one-half the length of the spacecraft.

Thin membrane structure

An anchoring device for use in a rock-crevice defined by a first rock wall and an opposing second rock wall. The anchoring device comprises an axle member having a longitudinal axis. A first cam is rotatable about the longitudinal axis of the axle member and contactable with the first rock wall with the first cam having a first side wall and a second side wall. A second cam is rotatable about the longitudinal axis of the axle member and contactable with the second rock wall with the second cam having a first side wall and a second side wall. The first side wall of the first cam is aligned with the first side wall of the second cam and the second side wall of the first cam is aligned with the second side wall of the second cam. Upon a first force being applied to the first cam by the first rock wall and a second force being applied to the second cam by the second rock wall in a direction generally toward the longitudinal axis, the axle member is free from any created moment.

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Boulder, CO, United States of America

Shane Eric Stamm