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Lightweight, Flexible Thermal Protection System for Fire Protection
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Polyimide Wire Insulation Repair System
Distributed Propulsion Concepts and Superparamagnetic Energy Harvesting Hummingbird Engine
Aerofoam
Wet Active Chevron Nozzle for Controllable Jet Noise Reduction
Magnetic Relief Valve
Active Aircraft Pylon Noise Control System
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Celebrate Pi Day with NASA Goddard and Discover Pi-Sat

The Innovative Technology Partnerships Office (ITPO) at NASA’s Goddard Space Flight Center (Goddard) in Greenbelt, MD, invites you to celebrate Pi Day on March 14 and discover Pi-Sat. Current technology trends indicate a shift in satellite architectures from large, single satellite missions, to small, distributed spacecraft missions. At the center of this shift is the smallSat/cubesat architecture.

Posted in: Articles, News, Software

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Rigorous Antenna Noise Temperature Calculation Method for International Space Station Visiting Spacecraft

Lyndon B. Johnson Space Center, Houston, Texas The temperature of the orbiting space station’s Sun-facing side could be up to 250 °F (≈120 °C) and will be a significant antenna noise temperature contributor for visiting spacecraft communication and tracking systems during rendezvous. The conventional antenna noise temperature calculation does not take into account the space station reflection effects, and results in an underestimated antenna and system noise temperature. Thus, the visiting spacecraft communication and tracking system performance could be overestimated during rendezvous.

Posted in: Briefs, Electronics & Computers, Electronics & Computers, Software, Antennas, Telecommunications, Thermodynamics, Noise, Spacecraft

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Recurring Anomaly Detection System (ReADS)

Ames Research Center, Moffett Field, California NASA Engineering & Safety Center (NESC) subject matter experts analyze records in various International Space Station and shuttle databases to identify recurring anomalies. The key problems these experts face in analyzing such database records are:

Posted in: Briefs, Electronics & Computers, Electronics & Computers, Software, Analysis methodologies, Data acquisition and handling, Spacecraft

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Method for Automatic Optimization of Yaw Maneuvers for Orbiting Space Vehicles

Lyndon B. Johnson Space Center, Houston, Texas A new method for optimizing yaw attitude maneuvers on the International Space Station (ISS) was developed. Docking and undocking operations often require 180° yaw rotations, which are the most common large maneuvers on the ISS. When optimized, some large maneuvers, previously performed using thrusters, could be performed using control moment gyroscopes (CMGs) or with significantly reduced thruster firings. The ability to perform a non-propulsive or low-propulsive 180° yaw maneuver on the ISS has been proven through the zero propellant maneuver (ZPM) and the optimal propellant maneuver (OPM). The ZPM and OPM were created by Draper Laboratory using the computational approach. Each maneuver is unique, and can only be calculated on the ground because significant computer resources are needed for the calculations.

Posted in: Briefs, Electronics & Computers, Electronics & Computers, Software, Optimization, Simulation and modeling, Attitude control, Spacecraft guidance, Spacecraft

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Architecture Framework for Fault Management Assessment and Design

Marshall Space Flight Center, Alabama Modern spacecraft, aircraft, and surface vehicles support complex science missions in harsh environments. These spacecraft and vehicles provide diverse functionality that is deployed on increasingly complex and heterogeneous hardware and mechanical systems, with stringent dependability requirements.

Posted in: Briefs, Electronics & Computers, Electronics & Computers, Software, Failure analysis, Architecture, Reliability, Spacecraft

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Spacecraft Parameter Database Tool

Goddard Space Flight Center, Greenbelt, Maryland The GOES-R Program has requirements to maintain knowledge of the GOES-R satellite onboard memory contents, including managing general satellite operations tables; processor memory dumps for memory verification; creating command loads, memory (table) loads, and command sequences to operate the satellite; verifying stored command and memory (table) loads; and to provide for operator-initiated memory dumps from satellite processors. The principal limitation is the tie to specific spacecraft architecture.

Posted in: Briefs, Electronics & Computers, Electronics & Computers, Software, Computer software and hardware, Data management, Spacecraft

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Eliminating the Need for Payload-Specific Coupled Loads Analyses Without Mission Risk

Marshall Space Flight Center, Alabama Amore efficient structural verification process for small satellites has been demonstrated. This new process eliminates the need for payload-specific coupled loads analysis (CLA) and simplifies structural testing while not increasing mission risk. The process entails the following:

Posted in: Briefs, Electronics & Computers, Electronics & Computers, Software, Failure modes and effects analysis, Safety testing and procedures, Satellites

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