| East Geostationary Orbit location |
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75 degrees West Longitude. |
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| Eclipse |
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Defined as when the solar disk is completely or partially occulted by the Earth or Moon as viewed from the spacecraft. |
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| Electromagnetic Compatibility (EMC) |
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The condition that prevails when various electronic devices are performing their functions according to design in a common electromagnetic environment. |
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| Electromagnetic Interference (EMI) |
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Electromagnetic energy which interrupts, obstructs, or otherwise degrades or limits the effective performance of electrical equipment. |
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| Electromagnetic Susceptibility |
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The potential for an undesired response by a component, subsystem, or system to conducted or radiated electromagnetic emissions. |
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| Element |
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A major grouping of Ground Segment functional capabilities, either Mission Management, Enterprise Management, Product Generation, or Product Distribution |
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| Embedded software |
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A fixed set of digital instructions stored in a device, which is designed to remain unchanged during operations, also called firmware. |
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| Emulated GVAR (eGVAR) |
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A unique GOES-R product generated only during the period of time when GOES-N/O/P operations overlap GOES-R operations. The product contains GOES-R data that is modified and formatted to be compatible with legacy GOES-N/O/P data systems. |
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| End of Life (EOL) |
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The point in the mission life where resources required to maintain operational specification have been effectively exhausted (e.g. propellant remaining only for de-orbit, components degraded, etc). |
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| End-Product |
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A collection of one or more geophysical variables derived from remotely sensed data (products) that is uniformly packaged, processed and formatted and made available to a user with associated ancillary data.
An end-product is a product with specific formatting as output by the Ground Segment. End-product is not interchangeable with product as specified in the Mission Requirements Document. |
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| End-to-End (E-T-E or ETE) |
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For an operational system, this includes data gathering by the satellite payload and on-board payload processing for downlink, data ingest and preparation, together with ground telemetry processing, product generation and distribution within stated latency and performance constraints. For a sub-system element such as an instrument, ground MM or PG, initiates at the receipt of data through its precedent interface, through completion at the element level to its delivery interface. |
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| End-to-End Test |
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A Program-defined test that verifies the interoperability of the space segment-to-ground segment interface in a configuration as close to flight-like as possible. |
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Engineering Data
(ABI specific) |
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All data available on-board about health, safety, environment, or status of the spacecraft and instruments.
- Spacecraft Engineering Data – The subset of engineering data from spacecraft sensor measurements and on-board computations
- Instrument Engineering Data – All non-science data provided by the instrument.
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| Engineering Review Board (ERB) |
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A group of Program and/or Project technical and management personnel convened to review all proposed changes to contract applicable documents per the GOES-R Configuration Management Plan (CMP). |
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| Engineering Telemetry |
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The state of health, health and safety, housekeeping, and diagnostic data that are transmitted to the ground and used in the control, monitoring, and operation of the satellite. |
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| Enterprise Management (EM) |
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Supports all operational functions by monitoring, assessing, and controlling the configuration of the operational systems, networks, and communications for the GOES-R ground segment. EM serves as the “glue” that links the MM, PG, and PD elements and provides for a degree of automated control. EM thus contributes to greater operational availability, efficiency, and safety of the GOES-R system. |
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| Environmental Test Requirements |
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The environmental test requirements of GEVS generally start at the component or unit-level assembly and continue hardware/software build through the end-to-end system level. The assurance program includes the part level. Validation testing may also include testing at the assembly and subassembly levels of assembly; for test record keeping, these levels are combined into a “subassembly” level. The validation program continues through launch, and on-orbit performance. |
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| Essential Loads |
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Power loads that are essential for safety and health of the space vehicle. |
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| Event (Ground Segment) |
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An activity or asynchronous change of state, which fulfills a predetermined set of criteria. |
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| Event (GLM) |
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A single sample exceeding the background threshold in a single frame. Event sources can include (but are not limited to) lightning, radiation, electronics noise, surface glint, and jitter. |
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| Expected Value (or Expected Utility) |
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The product of two numbers, probability and impact (value or amount at stake other than a monetary value, i.e. utility). |
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| Extendibility |
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The ability for a hardware or software system or component to accommodate modifications to increase its storage or functional capacity. |
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| Extensibility |
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The ability of a hardware or software system to accommodate expanded capabilities without significant changes in design. |
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| External Document |
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A document, such as a plan, specification, or standard that comes from an external source and is implemented by an organization as part of the QMS. Examples include military specifications and industry standards. |
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| Extreme Ultraviolet Sensor (EUVS) |
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Provides information on the full solar EUV spectrum that is critical to understanding and modeling the thermosphere and ionosphere. |
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