Environmental Research Institute of Michigan

Other

Donald B Jones

Michael E Dobbs

Douglas D Jones

Thomas Patrick Ryan

Peter Tchoryk, Jr

A fringe shift measurement system is provided and includes an optical phase mask configured to receive light fringes from optical flats. The optical phase mask has first and second halves, each half having alternating patterns of opaque rings and transparent rings. The first half pattern is phase-shifted with respect to the second half pattern. The first and second halves are configured to alternately block the light fringes or allow the light fringes to pass through the optical phase mask. A splitter is configured to direct the light fringes from the optical phase mask in desired directions. Concentrators are positioned to receive light fringes from the splitter and configured to focus the light fringes in a desired location. Detectors are configured to receive the focused light fringes from the concentrators and configured to convert the focused light fringes into digital signals. A control unit is configured to analyze the digital signals.

Fringe shift measurement system having an optical phase mask with phase-shifted first and second halves

A stringed musical instrument has a head assembly, a tail, and an elongate neck extending from the head assembly to the tail. The neck defines a fingerboard having a surface layer and a substrate. The surface layer includes an exposed surface formed of sheet metal deformed to unitarily define a plurality of frets thereon. A plurality of strings extends from the head assembly along the neck and adjacent to the fingerboard. In another variation, the surface layer has an exposed surface unitarily defining frets thereon. Each fret forms a peak, and the surface layer defines a plurality of troughs separated by the peaks. Each trough has a single arcuate shape extending between each peak. A method of forming the stringed musical instrument is also disclosed.

Unitary fingerboard and method of making same

A method of manufacturing in space and a spacecraft assembly to accomplish such manufacture. The spacecraft assembly includes a spacecraft including a plurality of canister compartments circumferentially spaced about the central axis of the spacecraft and opening in a docking face of the spacecraft, a plurality of canisters respectively positioned in the compartments, and a passive docking mechanism proximate the docking face and proximate the central axis, and a service vehicle comprising a plurality of canister compartments spaced circumferentially about the central axis of the service vehicle, a plurality of canisters respectively positioned in the compartments, and a manipulator assembly including an active docking structure, including a boom extending forwardly from the docking face, and a canister handling assembly mounted on the boom. In one embodiment, the spacecraft remains permanently in orbit, a manufacturing process is performed on the spacecraft to produce an end product which is housed in the canisters, and the service vehicle periodically visits the orbiting spacecraft to perform a canister exchange with the spacecraft, utilizing the canister exchange with the spacecraft, utilizing the canister handling assembly, and replenishing the spacecraft supplies.

Spacecraft payload exchange system

This invention is an automatic capture and docking mechanism for a pair of spacecraft. A largely passive capture mechanism disposed on a first spacecraft includes a concave cone section with the narrower interior end to admit a ball of a predetermined diameter. When tripped, a capture device restricts the diameter of passage for capture of the ball. In the release position passage for the ball is unrestricted. The capture device is preferably reset by the other spacecraft to release the ball. A docking mechanism disposed on the second spacecraft includes a convex cone section constructed to mate with the concave cone section, ball at the end of a cable and a boom. The cable may be extended from or retracted to the apex of the convex cone section. A rotary drive coupled to the convex cone section permits relative rotation of the spacecraft. The boom may be extended from or retracted into the second spacecraft. The spacecraft dock by directing the extended ball into the cylinder, where it is captured. The cable and boom retract to dock. The active docking mechanism releases and resets the capture device to undock. A pyrotechnic cutter disposed inside the boom can cut the cable for emergency release.

Automatic compliant capture and docking mechanism for spacecraft

A robotic substrate manipulator constructed for substrate handling during thin film deposition in the vacuum of outer space. The robotic substrate manipulator includes a cassette holding a plurality of substrates preferably including six cassettes in a carousel. A circular cylinder encloses the carousel with an access door at a location accessible by a manipulator arm assembly. Substrates are retained within the cassette via a passive retention system. This manipulator arm assembly includes an arm with a gripper at one end. The gripper includes a pair of opposed fingers normally urged closed by at least one finger spring that may be opened by a solenoid. The manipulator arm assembly includes a vertical driver and a horizontal rotary driver permitting motion of substrates from the cassette to a processing station. Position gauges on both the vertical motion driver and the horizontal rotary motion driver permit feedback regarding the manipulator arm assembly position. In the preferred embodiment the processing station employs the vacuum of space in thin film deposition.

Growing community of inventors

Ann Arbor, MI, United States of America

Donald B Jones