Abstract: A reconnaissance rover configured for multiple agile and autonomous landings over a small body or moon. The reconnaissance rover comprises a detection unit, a processing unit, a control unit and a drive unit. The detection unit is configured to detect at least an environment in front of the reconnaissance rover, in the direction of a trajectory of the reconnaissance rover over a surface of the small body or moon. The detection unit is further configured to provide environmental data based on the detected environment. The processing unit is configured to update the trajectory based upon the provided environmental data. The control unit interacts with the drive unit to move the reconnaissance rover according to the updated trajectory.

Abstract: A reconnaissance rover configured for multiple agile and autonomous landings over a small body or moon. The reconnaissance rover comprises a detection unit, a processing unit, a control unit and a drive unit. The detection unit is configured to detect at least an environment in front of the reconnaissance rover, in the direction of a trajectory of the reconnaissance rover over a surface of the small body or moon. The detection unit is further configured to provide environmental data based on the detected environment. The processing unit is configured to update the trajectory based upon the provided environmental data. The control unit interacts with the drive unit to move the reconnaissance rover according to the updated trajectory.

Abstract: A cusped-field thruster for a space system, wherein the cusped-field thruster comprises: at least two substantially annular permanent magnets arranged in an antipolar manner, wherein a magnetic pole piece is formed between the permanent magnets, and an anode, which comprises a permanent-magnetic material. The cusped-field thruster is configured such that a cusp is formed in a region adjacent to the anode of the cusped-field thruster.

Abstract: A discharge chamber of an ion drive, an ion drive having a discharge chamber, and a diaphragm for being affixed in a discharge chamber of an ion drive. The discharge chamber comprises a diaphragm, wherein the diaphragm of the discharge chamber comprises a magnet and is disposed and/or affixed in the discharge chamber.

Abstract: A cusped-field thruster for a space system, wherein the cusped-field thruster comprises: at least two substantially annular permanent magnets arranged in an antipolar manner, wherein a magnetic pole piece is formed between the permanent magnets, and an anode, which comprises a permanent-magnetic material. The cusped-field thruster is configured such that a cusp is formed in a region adjacent to the anode of the cusped-field thruster.

Abstract: A discharge chamber of an ion drive, an ion drive having a discharge chamber, and a diaphragm for being affixed in a discharge chamber of an ion drive. The discharge chamber comprises a diaphragm, wherein the diaphragm of the discharge chamber comprises a magnet and is disposed and/or affixed in the discharge chamber.

Abstract: An inertial sensor includes an inertial reference for determining the attitude and position of a satellite or satellite parts. A test mass is situated in a space which is essentially free of electric and magnetic fields and is enclosed by a housing, and optical measuring sections are set up between reference elements on the housing and on the test mass, for determining the attitude and/or position of the test mass relative to the reference elements on the housing. A measuring arrangement is situated outside the housing for the optical measuring sections. The optical measuring sections are constructed as optical interferometric measuring elements; and the attitude and position of the test mass can be adjusted by means of the pressures of light exerted on the optical interferometric measuring sections upon the test mass.

Abstract: An inertial sensor includes an inertial reference for determining the attitude and position of a satellite or satellite parts. A test mass is situated in a space which is essentially free of electric and magnetic fields and is enclosed by a housing, and optical measuring sections are set up between reference elements on the housing and on the test mass, for determining the attitude and/or position of the test mass relative to the reference elements on the housing. A measuring arrangement is situated outside the housing for the optical measuring sections. The optical measuring sections are constructed as optical interferometric measuring elements; and the attitude and position of the test mass can be adjusted by means of the pressures of light exerted on the optical interferometric measuring sections upon the test mass.

Abstract: Optical waveguide ends are mechanically fixedly positioned so that an end portion projects from the clamp; electrode structure is disposed in relation to that projecting end for deflecting it in one or two directions basically perpendicular to the axis of the waveguide; and a high frequency oscillation is provided to the electrodes at an amplitude such that the inhomogenic field in the vicinity of the electrode structure moves that end portion, preferably at resonance frequency, to pass through maximum optical coupling with stationary optical input or output.