a. The electrical hazard mitigation plan shall include the following elements:
1. Assessment of the environmental characteristics of the mission, including:
(a) consideration of the spacecraft orbit, and
(b) whether this is LEO, MEO, GEO or extra-magnetospheric.
NOTE ECSS-E-ST-10-04 gives nominal and worst-case environment for various mission types.
2. Assessment of the electrical characteristics of the spacecraft, including:
(a) consideration of whether electric propulsion is used,
(b) whether the mission includes scientific field or plasma measurement instruments, and
(c) whether there are high voltage systems or systems with particular vulnerability.
3. Specification of relevant design requirements.
NOTE For tailoring guidelines on this, refer to Annex B.
4. Analysis, simulation or testing of exceptions.
NOTE This requirement is to ensure an individual assessment of the components that falls outside the requirements of this Standard.
5. Testing of design implementation.