Space ion analyzer with mass spectrometer on a chip (msoc) using floating msoc voltages

A method performed by an ion analyzer for space applications, comprising:

• receiving, through an aperture of a housing of the ion analyzer that is affixed to a spacecraft and that has an interior axis, an ion stream including ions having a range of ion energies;
• focusing the ion stream along the axis responsive to a focus voltage;
• deflecting ions in the ion stream away from the axis based on energies of the ions and a deflector voltage difference applied across plates of the ion deflector;
• using a mass spectrometer on a chip (MSOC), directing ions produced by the deflecting to an ion detector array responsive to an MSOC voltage difference applied to plates of the MSOC;
• generating the focus voltage as a variable voltage referenced to a spacecraft ground;
• generating the deflector voltage difference with a controllable magnitude and referenced to the spacecraft ground;
• and
• generating the MSOC voltage difference with a controllable magnitude and referenced to an breaking potential controllable relative to the spacecraft ground.

An ion analyzer for space applications, comprising:

• a housing configured to be fixed to a spacecraft, the housing having an interior axis and an aperture to receive an ion stream including ions having a range of ion energies;
• an ion focuser to focus the ion stream along the axis responsive to a focus voltage;
• an ion deflector to deflect ions in the ion stream away from the axis based on energies of the ions and a deflector voltage difference applied across plates of the ion deflector;
• a mass spectrometer on a chip (MSOC) to direct ions from the ion deflector to an ion detector array responsive to an MSOC voltage difference applied to plates of the MSOC;
• a controller to generate control voltages including a breaking potential;
• and
• a voltage generator assembly responsive to the control voltages to:
• generate the focus voltage as a variable voltage referenced to a spacecraft ground responsive to the;
• the deflector voltage difference with a controllable magnitude and referenced to the spacecraft ground;
• and
• the MSOC voltage difference with a controllable magnitude and referenced to a breaking potential controllable relative to the spacecraft ground.