Small Satellite Design for High Sensitivity Magnetic Measurements

Abstract: The magnetic cleanliness of a spacecraft during magnetic measurements is an important aspect in the design of many space science missions. The adequate reduction or removal of the spacecraft's magnetic disturbance plays a vital role in allowing the ambient magnetic field to be measured with the required accuracy. There are three main approaches to reduce the impact of the spacecraft's magnetic disturbance on the final magnetic measurement, with each approach imposing its own set of changes and constraints on the spacecraft. In turn these changes and constraints introduce additional complexity and cost to the system design. The required changes in the spacecraft's mission profile and configuration also need to be factored in during the design phase of a spacecraft, but cannot be avoided if high quality measurements are desired.  One of these approaches is the use of a magnetic cleanliness programme, and such programmes have a long history of successful use on large satellite missions.CubeSats have become increasingly technically capable and have in recent years begun to undertake scientific missions with challenging sensitivity requirements, including for magnetic measurements. The small size of the CubeSat form factor poses some unique challenges to the implementation of magnetic cleanliness techniques, but are also in increased need of limiting the residual magnetic moment when compared to large satellites. This thesis details the early phases of the magnetic cleanliness programme on the FORESAIL-2 science mission. Nine magnetic cleanliness requirements on the FORESAIL-2 satellite platform were derived from the FORESAIL-2 measurement and instrument requirements. A simple magnetic model was established, the results of which were used to propose a configuration of spacecraft subsystems. The resulting preliminary configuration of subsystems reduced the effective magnetic field of the REPE payload at the sensor by 352pT, 30.1%, when compared to the worst-performing configuration. Subsequently an improved model, utilising RSS analysis, was created. Combined with updated location information for each subsystem, defined using the proposed configuration, this second model yielded an estimated magnetic field of 2710pT at the reference point. The results of the second model were also used to identify the CDE payload and the TT&C subsystem as potentially problematic from a magnetic cleanliness perspective. A list of ferromagnetic materials was compiled, and a total mass of 453.72g of ferromagnetic materials was estimated. The work presented in this thesis is expected to form the basis of FORESAIL-2's continued magnetic cleanliness programme throughout the design and integration phases of the project.  For example, the improved model could be extended to include the estimated magnetic dipole moment's of each subsystem. Additionally, the inventories of materials, currents, and frequencies established as part of this thesis can be maintained throughout the FORESAIL-2's development cycle, and used to update the estimated total magnetic field of the spacecraft platform.