Engineering

The statements below refer to the design and operation of the power sub-system on a spacecraft. Select all those statements that are correct.Partial credit is available for each correct answer. Select only those statements you know to be correct because negative marking is appliedwithin this question (although it is not possible to get a negative mark for the question overall).Radioisotope Thermoelectric Generators (RTGS) are commonly applied to earth-orbiting spacecraft to provide power for the eclipse periodwhen the solar panels are ineffective.Jupiter is considered the approximate limit for solar-powered orbital missions; missions to planets beyond this will require RadioisotopeThermoelectric Generators (RTGS).When sizing solar arrays, the area required typically has to be factored up as the temperature decreases because the cells operate lessefficiently when cold.A spacecraft designed to operate in orbit at Mars will require generally require significantly smaller solar arays than one designed foroperation at Earth.When sizing solar arrays, the area required must be factored up to allow for the array efficiency to decrease with time due to degradation.When sizing solar arrays, the area required typically has to be factored up as the temperature increases because the cells operate lessefficiently when warm.Radioisotope Thermoelectric Generators (RTGS) have many moving parts, which limits their reliability for long-duration missions.For a spacecraft in planetary orbit, power for the eclipse period is commonly provided by a battery as a secondary power source, and anincreased solar array area to give extra power to charge the batteries whilst not in eclipse.