Space Systems/loral, LLC

Signature Bioscience, Inc.

Mds Sciex

Tyler A Palmer

Varouj G Baghdasarian

Kevin S Bodner

John J Hefti

Robert G Chapman

Mark A Rhodes

Barrett Bartell

Pejman Ghanouni

Min Zhao

A sample container for minimizing evaporation of a contained volume of sample includes a container housing, a repuncturable self-sealing membrane, and a collapsible sample bag. The container housing includes an open end and a hollow interior region. The repuncturable self-sealing membrane configured to self-seal after repeated punctures is engaged in the open end of the container housing and includes an exterior surface exposed to the external environment and an interior surface oriented toward the hollow interior region of the container housing. The collapsible sample bag includes a proximate end that is permanently attached to the interior surface of the repuncturable self-sealing membrane.

Repuncturable self-sealing sample container with internal collapsible bag

The present invention provides a method for detecting a molecular event, comprising (1) applying an electromagnetic test signal to a sample in which a molecular event is being detected, whereby the sample interacts with and modulates the test signal to produce a modulated test signal, and (2) detecting the modulated test signal, wherein the applying and detecting take place in a temperature-controlled environment, wherein the temperature-controlled environment comprises the sample, a radiating portion of a signal generating circuit, and a receiving portion of a signal detection circuit and wherein the applying and detecting take place in the environment at a temperature controlled to within &plusmn;0.5&deg; C.

Method and apparatus for detection of molecular events using temperature control of detection environment

A spacecraft having nested reflectors that are released and deployed during a single release event using one or more dual reflector holddowns. The nested reflectors are held in place prior to release by the holddowns and are released during the single release event. The nested reflectors are secured to the body of the spacecraft by hinges attached to respective reflector backup structures and are releasably secured to the body using the one or more dual reflector holddowns. The reflector backup structures are secured by reflector interface brackets of the respective holddowns. An exemplary holddown has a separable tubular housing that is longitudinally secured together between an end cap and a release device. A threaded shaft,extends through the tubular housing, the end cap and the release device. A retraction spring is disposed around the exterior of the housing. The reflector interface brackets are secured to the outer and inner housings that attach the plurality of reflectors to the holddown.

Spacecraft having a dual reflector holddown for deploying multiple reflectors in a single release event

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San Francisco, CA, United States of America

Tyler A Palmer