AffiliationJet Propulsion Laboratory
European Space Agency
KeywordsStandard spacecraft interfaces
Standard instrument interfaces
Spacecraft onboard interfaces
Spacecraft communications protocols
Spacecraft communications standards
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RightsCopyright © International Foundation for Telemetering
Collection InformationProceedings from the International Telemetering Conference are made available by the International Foundation for Telemetering and the University of Arizona Libraries. Visit http://www.telemetry.org/index.php/contact-us if you have questions about items in this collection.
AbstractThe Consultative Committee for Space Data Systems (CCSDS), an international organization of national space agencies, is branching out to provide new standards to enhanced reuse of onboard spacecraft equipment and software. These Spacecraft Onboard Interface (SOIF) standards will be based on the well-known Internet protocols. This paper will provide a description of the SOIF work by describing three orthogonal views: the Services View that describes data communications services, the Interoperability view shows how to exchange data and messages between different spacecraft elements, and the Protocol view, that describes the SOIF protocols and services. This paper will give the reader an excellent introduction to the work of the international SOIF team.
SponsorsInternational Foundation for Telemetering
Showing items related by title, author, creator and subject.
Development of Software Toolsuite for Rapid Generation of Spacecraft Requirements from Mission Constraints for Spacecraft Proposal DevelopmentSahr, Eric (The University of Arizona., 2017)The development, testing, and results of a software suite for automated development of spacecraft requirements is discussed. This software suite will enable mission scientists and engineers to rapidly develop spacecraft requirements from a previously-developed set of mission requirements. The software, written in MATLAB, is controlled by a Master Controller script, whose purpose is to accept inputs from the user and call subfunctions responsible for designing the various spacecraft subsystem requirements. The software was tested through the use of a series of arbitrarily-generated mission requirements, with the test results being examined for potential feasibility and reasonableness. Case studies are examined which show the efficacy of the software suite to accurately generate spacecraft requirements. The first case study examines a set of software-developed spacecraft requirements intended to meet the mission requirements of the Mars Reconnaissance Orbiter. The second case study examines a set of infeasible mission requirements to the planet Uranus, in an effort to demonstrate that the software will generate realistic, but infeasible, spacecraft requirements when the mission requirements are themselves infeasible. Both case studies generate reasonable spacecraft requirements as expected, with the direct comparison between the Mars spacecraft resulting in very similar preliminary spacecraft designs. This software suite will enable spacecraft scientists and engineers to quickly assess the feasibility of mission concepts and proposal designs through rapid development of spacecraft requirements.
Using Telemetry to Measure Equipment Mission Life on the NASA Orion Spacecraft for Increasing Astronaut SafetyLosik, Len; Failure Analysis (International Foundation for Telemetering, 2012-10)The surprise failure of two NASA Space Shuttles and the premature failures of satellite subsystem equipment on NASA satellites are motivating NASA to adopt an engineering discipline specifically developed for preventing surprise equipment failures. The NASA Orion spacecraft is an Apollo module-like capsule planned to replace the NASA Space Shuttle reusable launch vehicle for getting astronauts to space and return to the earth safely as well as a crew escape vehicle stored at the ISS. To do so, NASA is adopting a non-Markov reliability paradigm for measuring equipment life based on the prognostic and health management program on the Air Force F-35 Joint Strike Fighter. The decision is based on the results from the prognostic analysis completed on the Space Shuttle Challenger and Columbia that identified the information that was present but was ignored for a variety of reasons prior to both accidents. The goal of a PHM is to produce equipment that will not fail prematurely and includes using predictive algorithms to measure equipment usable life. Equipment with transient behavior, missed by engineering analysis is caused from accelerated of parts will fail prematurely with 100% certainty. With the processing speed of today's processors, transient behavior is caused from at least one part suffering from accelerated aging. Transient behavior is illustrated in equipment telemetry in a prognostic analysis but not in an engineering analysis. Telemetry is equipment performance information and equipment performance has been used to increase reliability, but performance is unrelated to equipment remaining usable life and so equipment should be failing prematurely. A PHM requires equipment telemetry for analysis and so analog telemetry will be available from all Orion avionics equipment. Replacing equipment with a measured remaining usable life of less than one year will stop the premature and surprise equipment failures from occurring during future manned and unmanned space missions.
An Adaptable Spacecraft Telemetry SystemMaxwell, Marvin S.; Silverman, Joseph R.; Czarcinski, Eugene A.; Goddard Space Flight Center (International Foundation for Telemetering, 1965-05)Because of the limitations of hardwired telemetry systems, existing spacecraft are denied the capability of revising their sampling structure, their sampling rates, or the experiments and/or test points to be sampled. A centralized system to provide these capabilities is described in this paper. This system is called the Flexible Automatic Computer Telemetry System (FACTS). As initially conceived, the FACTS, through the use of a stored program, will be able to sample a large number of channels with great flexibility in sampling rates, sampling structure and the selection of experiments and/or test points. This paper outlines the basic spacecraft and ground station system and illustrates the flexibility which can be achieved with it. Selected diagrams are given along with a description of the operation of the various units in the system.