Drive arrangement in a spacecraft
The invention relates to a drive arrangement in a spacecraft, comprising several drive units (TW 1 ,TW 2 ,TW 3 ), 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).
1. Drive arrangement in a spacecraft, having multiple drive units, which can be changeably controlled, in terms of their drive power, by a control device, individually and independently of one another, whereby the individual drive units have an ionization chamber, a gas feed line, and an electrode arrangement, in each instance, and having a high-voltage supply device from which the individual drive units can be supplied with high voltage, whereby the high voltage forms an electrostatic acceleration field for a plasma in the individual drive units, which is present in a working gas fed to the ionization chamber and ionized there, wherein multiple drive units that are controllable independently of one another are simultaneously supplied with high voltage from a common high-voltage potential of the high-voltage supply device, and wherein the control device changeably controls the generation of plasma in the ionization chambers, to changeably control the drive power of the individual drive units, and wherein in order to generate a drive thrust in a thrust direction that does not coincide with the orientation of a drive unit, the control turns on multiple drive units at the same time, to generate drive power.
2. Arrangement according to claim 1 , wherein the control device for changeable control of the drive power of a drive unit changeably controls the inflow of neutral working gas into the ionization chamber of the drive unit, in each instance.
3. Arrangement according to claim 2 , wherein, independently of the changeable control of the inflow of working gas into the ionization chamber of one or more drive units, the high voltage is constantly applied at the electrode arrangement of all the multiple drive units.
4. Arrangement according to claim 2 , further comprising controllable gas valves in gas lines to the individual drive units.
5. Arrangement according to claim 4 , wherein the gas stream can be controlled continuously or by way of intermediate steps between closed valve and maximally open valve.
6. Arrangement according to claim 4 , wherein at least part of the multiple gas valves are configured as switching valves.
7. Arrangement according to claim 4 , wherein the controllable gas valve assigned to a drive unit is disposed at the drive unit.
8. Arrangement according to claim 1 , wherein flow resistance arrangements are provided in the gas feed lines.
9. Arrangement according to claim 1 , wherein the drive units, in the absence of plasma in the ionization chamber, are at high ohms in their high-voltage current circuit, in each instance, particularly possess a resistance of at least 100 kOhm.
10. Arrangement according to claim 1 , wherein a drive unit possesses a cathode disposed in the region of an exit opening of the ionization chamber and an anode disposed at the foot of the ionization chamber, opposite the exit opening, and the high voltage brings about an electrostatic field that passes through the ionization chamber.
11. Arrangement according to claim 10 , wherein the ionization chamber is laterally surrounded by a magnet arrangement and wherein the magnet arrangement generates a magnetic field in the ionization chamber, which has at least two cusp structures spaced apart in the longitudinal direction.
12. Arrangement according to claim 1 , wherein multiple drive units supplied from a common high-voltage potential are disposed on the spacecraft in different orientations.
13. Arrangement according to claim 1 , wherein different drive units are disposed on the spacecraft in fixed, different orientations.
14. Arrangement according to claim 1 , wherein the high-voltage generator contains multiple generator stages disposed electrically in parallel, which are guided to a common high-voltage output.
15. Arrangement according to claim 1 , wherein another high-voltage generator having additional drive units is provided, and wherein the two high-voltage generators are permanently connected with the drive units assigned to them in fixed manner, in each instance, by way of connections free of switching elements, and wherein they cannot be connected with drive units assigned to the other high-voltage generator, in each instance.