Optimization of spacecraft orbit and shielding for radiation dose

An implementation of the optimization of spacecraft orbit and shielding thickness for the control of exposure from the natural orbital radiation environment is described. Many space missions, such as crewed flights and those carrying sensitive electronics, are constrained by a maximum allowable radiation dose to materials inside the vehicle. Generally, in the event of a radiation dose concern, additional shielding is added for radiation protection, thus adding more mass to the spacecraft. However, a modification to the orbit might also be used reduce the radiation dose, which, depending on the flexibility of the mission design, may provide a more advantageous solution. It is shown with established optimization techniques that there are many combinations of orbits and shieldings that will yield a specific dose. For a given design space, weighting the importance of the various spacecraft and mission design parameters, including shielding thickness and orbital parameters, allows for mission specific optimization, providing a flexible design tool.