| 摘要 |
spacecraft. SUBSTANCE: proposed method of creating reactive thrust and microengine used for this purpose can be used in precision spacecraft control systems. Liquid fuel is fed to capillary structure arranged in microengine chamber to which heat energy is fed simultaneously and then fuel is transported through capillary structure, is evaporated and fumes, thus formed, are evacuated through nozzle. Heat energy is fed only to sections of structure surface pointed inwards the chamber on which evaporation of fuel is carried out. Microengine has chamber for collecting fumes of liquid fuel, space of chamber being connected at one side with ambient medium and at other side, with fuel supply system through capillary structure. Side of capillary structure pointed to chamber space has surface, for instance, in form of cylindrical projection on which resistance heating member is mounted, for instance, spiral made of alloy featuring high electric resistance. EFFECT: provision of small thrust values (less than 0.01 N) at minimum energy consumption, reduced overall dimensions and mass of microengine, improved convenience of thrust control. 3 cl, 1 dwg |
