A system that includes sensors and data-acquisition, wireless data- communication, and data-processing subsystems has been developed as a means of both real-time and historical tracking of information indicative of deterioration in the mechanical integrity and performance of a high-geared ball valve or a linearly actuated valve that operates at a temperature between cryogenic and ambient.

The Sensor Units and a Base Station together constitute an instrumentation and data-acquisition system that can function alone or can be connected into a network that is part of a higher-level
In the original application for which the system is specifically designed, the valve is of a type used in controlling the flow of a propellant fluid (e.g., liquid hydrogen) during testing of a rocket engine. The data collected by use of this system are used to build a knowledge base of operational characteristics of valves, for the purpose of obtaining insight into operational lifetime and enabling prediction of valve operational lifetimes. This system can stand alone or can be incorporated into a network that is part of a higher-level “health”-management system. This system is also readily adaptable to commercial applications in which there are requirements for long-term monitoring of events associated with quantities that may include, but are not limited to, torsional strain, biaxial strain, linear strain, cryogenic temperatures, ambient temperatures, tripping of limit switches, current signals ranging from 4 to 20 mA, potential signals ranging from 0 to 10 V, and/or magnetic fields.

The data collected in the original application include the number of cryogenic valve cycles, the total number of all valve cycles, inlet temperature, outlet temperature, valve-body temperature, torsional strain, linear strain, valve preload position, total rotational or linear valve travel, and total number of directional changes. Events associated with the aforementioned data are recorded and are time-stamped with sufficient precision to enable synchronization within a time increment of 1 ms. The data are then organized into a text file and stored in a compact flash memory card, from whence the data can be uploaded.

The system (see figure) includes a base station and several self-contained, microprocessor-controlled sensor units that (1) can be mounted remotely from the base station and (2) transmit data to the base station via low-power, short-range [≤ 35 ft (up to about 10 m)] digital radio communication links in the frequency band from 902 to 928 MHz. Each sensor unit has overall dimensions of 3 by 2 1/2 by 2 in. (about 7.6 by 6.4 by 5.1 cm) — small enough to be mounted in the confined spaces typically available for mounting on valves of the type used in the original rocket-engine-testing application. Each sensor unit is potted in a flame-retardant epoxy and designed to draw a current of no more than 0.25 A at a supply potential of 9 V, as required for safe operation in an atmosphere that may contain hydrogen. The base station is not potted; instead, it is mounted in an enclosure that is purged with nitrogen.

NASA Tech Briefs Magazine

This article first appeared in the May, 2009 issue of NASA Tech Briefs Magazine.

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