There are many factors which influence the selection of spacestation orbit,such as mission requirements,radiation environment,meteoroid/debris environment,configuration of space station,vehiclecapability,launch window and logistics demands of space station.
High velocity impact on long duration and large size spacecraft by meteoroid and space debris is a threat to spacecraft safety operation,Which can in turn lead to significant damage and catastrophic failure.
Space environment is all the environment effecting based-space action, including all kinds of energy, electric particles, neutral particles, electromagnetism radiation of different wave bands, magnetic field, micro-meteor, space fragment, temperature and micro-gravity field and so on.
The rules governing the motion of equipment attached to spacecraft under the high-speed impact of micrometers or debris in space were studied with such spacecraft attachment equipment as solar energy plates and aerials simulated as simple attachment plate to establish the relationship among the elevation of attachment plate, impact speed, diameter of projectile, yield strength of material, and thickness of attachment plate.
The model can be used in designing particle detectors, measuring physicochemical properties of micrometeoroid and technogenic particles, and processing ion spectra.
A study of micrometeoroid and orbital debris (MMOD) long-term effects on solar cell samples of solar panels returned from the space station "MIR" has been carried out.