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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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A circuit using one power supply and two storage capacitors, which may be separately discharged in opposite directions through a relay in response to change in polarity of a signal, is described.
Louvers are used for overpressure safety venting in rooms or chambers where explosion hazards exist. The louvers have individually hinged closures that are held in locked position by commercially available magnets that quickly release them in an overpressure condition.
Fastener /Boydbolt/ has recently been designed to furnish positive lock and release characteristics that positively prevent accidental adverse functions of lock or release.
Electronic circuit connected to solenoid valve coils visually indicates the position of the valve stem. Transient suppression is provided to prevent damaging voltage spikes.
Circuit breaker consists of a preset current amplitude sensor, and a lamp-photo-resistor combination in a feedback arrangement which energizes a power switching relay. The ac input power is removed from the load at predetermined current amplitudes.
Valve assembly for controlling simultaneously more than one fluid flow, and having stable qualities under loads
Innovation allows fully-loaded container to be fastened to rear wall of recessed area. Assembly is designed to carry shear and tension loads. Retractable handle allows for visual verification if door is locked or unlocked.
Pull-in and Delatching Coils of cryogenic solenoid contain copper and low-resistance, low-temperature-coefficient alloy to limit current at low temperatures.
A neck ring releasably secured to a pressurized garment carries an open-ended ring normally in the engagement position fitted into an annular groove and adapted to fit into a complementary annular groove formed in a helmet. Camming means formed on the inner surface at the end of the helmet engages the open-ended ring to retract the same and allow for one motion donning even when the garment is pressurized. A projection on the end of the split ring is engageable to physically retract the split ring.
Mechanism engages and disengages parallel plates carrying couplings and connectors. Designed to lock items in place for handling, storage, or processing under remote control, mechanism has fail-safe feature which does not allow plates to separate completely unless both are supported.
The design and test details of a high precision hinge and locking mechanism created principally in support of the Lockheed space deployable Flexrib Parabolic Antenna concept are presented. These developed improvements in the detail design of ultra-precise rib hinge and contour adjustment mechanisms will allow radio frequency antenna reflectors to expand into the 15-50 meter diameter size class and to support the .013 mm. deployment repeatability tolerance required to support the 12+ GHz frequency range.
Structural column elements assembled quickly and easily with aid of new center joint. Joint alines column elements automatically and fastens them together securely. Tapered half columns are stacked like paper cups, unfolded, and connected to other similar elements to form truss structures.
Electromechanical interface transfers electric power, data and coolant from one system to another. Motor-actuated jackscrew moves connector on active half of interface to mating connector on passive half. Originally suggested for spacecraft, concept adaptable to underwater connections.
Fingers capture and clamp without accurate positioning. Fully open position, fingers encompass large envelope. When activated by rack and pinion, fingertips move together, thereby grasping object within envelope.
The primary purpose of the OMV is to dock with orbiting payloads and then either transfer them to a different orbit or return them to the Space Shuttle for servicing. Some such missions will involve docking with payloads equipped with a Flight Support System (FSS) type of interface; an example is the Hubble Space Telescope (HST). The design and development of a mechanism to be used for testing this docking concept on the NASA-Marshall test beds is described. The test results to date are also presented.
Mechanism makes rack hardware interchangeable, regardless of drawer height. Provides quick connection and disconnection of equipment drawer. Pivoting lever is heart of mechanism. At insertion, lever rotated slightly counterclockwise so bottom hook slips over pin; then rotated clockwise to engage pin and lever lock. Rotation of lever to full counterclockwise position disengages panel from rack.
Astronauts Nelson and Lounge are shown in the WETF while astronauts Covey and Hilmer observe topside.
The NASA Engineering (NE) Directorate at Kennedy Space Center provides engineering services to major programs such as: Space Shuttle, Inter national Space Station, and the Launch Services Program (LSP). The Av ionics Division within NE, provides avionics and flight control syste ms engineering support to LSP. The Launch Services Program is respons ible for procuring safe and reliable services for transporting critical, one of a kind, NASA payloads into orbit. As a result, engineers mu st monitor critical flight events during countdown and launch to asse ss anomalous behavior or any unexpected occurrence. The goal of this project is to take a tailored Systems Engineering approach to design, develop, and test Iris telemetry displays. The Flight Avionics Sequen cing Telemetry Delta-IV (FAST-D4) displays will provide NASA with an improved flight event monitoring tool to evaluate launch vehicle heal th and performance during system-level ground testing and flight. Flight events monitored will include data from the Redundant Inertial Fli ght Control Assembly (RIFCA) flight computer and launch vehicle comma nd feedback data. When a flight event occurs, the flight event is ill uminated on the display. This will enable NASA Engineers to monitor c ritical flight events on the day of launch. Completion of this project requires rudimentary knowledge of launch vehicle Guidance, Navigatio n, and Control (GN&C) systems, telemetry, and console operation. Work locations for the project include the engineering office, NASA telem etry laboratory, and Delta launch sites.