ECSS-E-ST-20-07C (REV. 1), SPACE ENGINEERING: ELECTROMAGNETIC COMPATIBILITY (07-FEB-2012)

ECSS-E-ST-20-07C (REV. 1), SPACE ENGINEERING: ELECTROMAGNETIC COMPATIBILITY (07-FEB-2012)., EMC policy and general system requirements are specified in ECSS‐E‐ST‐20. This ECSS‐E‐ST‐20‐07 Standard addresses detailed system requirements (Clause 4), general test conditions, verification requirements at system level, and test methods at subsystem and equipment level (Clause 5) as well as informative limits (Annex A). Associated to this standard is ECSS‐E‐ST‐20‐06 “Spacecraft charging”, which addresses charging control and risks arising from environmental and vehicleinduced spacecraft charging when ECSS‐E‐ST‐20‐07 addresses electromagnetic effects of electrostatic discharges. Annexes A to C of ECSS‐E‐ST‐20 document EMC activities related to ECSS‐E‐ST‐20‐07: the EMC Control Plan (Annex A) defines the approach, methods, procedures, resources, and organization, the Electromagnetic Effects Verification Plan (Annex B) defines and specifies the verification processes, analyses and tests, and the Electromagnetic Effects Verification Report (Annex C) document verification results. The EMEVP and the EMEVR are the vehicles for tailoring this standard. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS‐S‐ST‐00. Electromagnetic compatibility (EMC) of a space system or equipment is the ability to function satisfactorily in its electromagnetic environment without introducing intolerable electromagnetic disturbances to anything in that environment. The space system is designed to be compatible with its external natural, induced, or man‐made electromagnetic environment. Natural components are lightning for launchers, the terrestrial magnetic field for space vehicles. Spacecraft charging is defined as voltage building‐up of a space vehicle or spacecraft units when immerged in plasma. Electrostatic discharges result from spacecraft charging with possible detrimental effects. External man‐made interference, intentional or not, are caused by radar or telecommunication beams during ground operations and the launching sequence. Intersystem EMC also applies between the launcher and its payload or between space vehicles. Intrasystem EMC is defined between all electrical, electronic, electromagnetic, and electromechanical equipment within the space vehicle and by the presence of its self‐induced electromagnetic environment. It comprises the intentional radiated electromagnetic fields and parasitic emission from on‐board equipment. Both conducted and radiated emissions are concerned. An electromagnetic interference safety margin is defined at system critical points by comparison of noise level and susceptibility at these points.