Abstract: The invention relates to relates to a pressure cell configured for working according to the piezo-resistive principle and for use under high-energy radiation, particularly for use in space, i.e. to work under cosmic radiation. In order to reduce radiation drift effects during operation of the pressure cell, the pressure cell is treated with a radiation hardening procedure comprising an exposing of the cell with a radiation dose up to a saturation range of a radiation drift curve or above.

Abstract: The invention relates to relates to a pressure cell configured for working according to the piezo-resistive principle and for use under high-energy radiation, particularly for use in space, i.e. to work under cosmic radiation. In order to reduce radiation drift effects during operation of the pressure cell, the pressure cell is treated with a radiation hardening procedure comprising an exposing of the cell with a radiation dose up to a saturation range of a radiation drift curve or above.

Abstract: The invention relates to a drive arrangement in a spacecraft, comprising several drive units (TW1,TW2,TW3), several individually controllable drive units that can be continuously applied to a common, constant voltage potential (HV), and a control of the axial thrust in the respective drive units is achieved due to the fact that the production of plasma in the respective drive units is individually controlled. In particular, the time-variable control of the production of plasma occurs by the time-variable control of the flow of neutral working gas (AG) in the ionization chamber (IK).

Abstract: The invention relates to a surface section that is exposed to an ion flow, in particular for a drive arrangement in a spacecraft, comprising an electrostatic ion accelerator arrangement. According to the invention, in order to reduce erosion, an intermediate potential energy surface is provided, the surface being advantageous in that it allows a magnetic field that is essentially parallel to the surface section to be formed.

Abstract: The invention relates to an ion accelerator arrangement comprising an electrostatic acceleration field between a cathode to which a frame potential is applied and an anode to which a high-voltage potential is applied. The ion accelerator arrangement further comprises a gas supply system into which a gas-permeable, open porous insulator member is introduced. Also described is a high-voltage insulator arrangement that comprises such an insulator member and is suitable, inter alia, for such an ion accelerator arrangement and for the corona-resistant insulation of other components to which a high voltage is applied.

Abstract: The invention relates to an ion accelerator arrangement comprising an ionization chamber which is surrounded by a chamber wall and a magnetic arrangement that is disposed outside the chamber wall. Steps are taken to dissipate lost heat occurring on the chamber wall, and advantageous solutions are provided to protect permanent-magnet elements of the magnetic arrangement.

Abstract: The invention relates to an ion accelerator arrangement comprising an electrostatic acceleration field between a cathode to which a frame potential is applied and an anode to which a high-voltage potential is applied. The ion accelerator arrangement further comprises a gas supply system into which a gas-permeable, open porous insulator member is introduced. Also described is a high-voltage insulator arrangement that comprises such an insulator member and is suitable, inter alia, for such an ion accelerator arrangement and for the corona-resistant insulation of other components to which a high voltage is applied.

Abstract: The invention relates to an ion accelerator arrangement comprising an ionization chamber which is surrounded by a chamber wall and a magnetic arrangement that is disposed outside the chamber wall. Steps are taken to dissipate lost heat occurring on the chamber wall, and advantageous solutions are provided to protect permanent-magnet elements of the magnetic arrangement.

Abstract: The invention relates to a surface section that is exposed to an ion flow, in particular for a drive arrangement in a spacecraft, comprising an electrostatic ion accelerator arrangement. According to the invention, in order to reduce erosion, an intermediate potential energy surface is provided, the surface being advantageous in that it allows a magnetic field that is essentially parallel to the surface section to be formed.

Abstract: The invention relates to a drive arrangement in a spacecraft, comprising several drive units (TW1,TW2,TW3), several individually controllable drive units that can be continuously applied to a common, constant voltage potential (HV), and a control of the axial thrust in the respective drive units is achieved due to the fact that the production of plasma in the respective drive units is individually controlled. In particular, the time-variable control of the production of plasma occurs by the time-variable control of the flow of neutral working gas (AG) in the ionisation chamber (IK).

Abstract: A high-frequency electron source includes a discharge chamber having at least one gas inlet for a gas to be ionized and at least one extraction opening for electrons. The high-frequency electron source also includes a first electrode at least partially surrounding the discharge chamber and a keeper electrode at least partially surround the discharge chamber. The first electrode and the keeper electrode are configured to provide a high-frequency electric field therebetween.

Abstract: A high-frequency electron source includes a discharge chamber having at least one gas inlet for a gas to be ionized and at least one extraction opening for electrons. The high-frequency electron source also includes a first electrode at least partially surrounding the discharge chamber and a keeper electrode at least partially surround the discharge chamber. The first electrode and the keeper electrode are configured to provide a high-frequency electric field therebetween.