| 摘要 |
A high performance propulsion thruster especially for the attitude and orbit control of space craft or flying bodies in space, is equipped with a heating-up device for the propulsion gas flowing to a nozzle. The heating device is constructed with at least two electrical resistance heating elements for increasing the reliability and the specific impulses. The heat generated by the at least two electrical resistance heating elements is applied to a gas guide conduit which is integrated with the heating device. The gas guide conduit is made of a high temperature resistant metal or of a ceramic material. The heating device, or rather its units are constructed as modular units, preferably integrated with modular gas guide conduits. Thus, a plurality of such modular units can be combined to easily satisfy the requirements regarding dimension of such units and regarding the specific impulse of such units.
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