| 摘要 |
<p>The invention concerns an electrothermal thruster (1) comprising a heating section (20) through which a propellant fluid (4) is intended to pass so that it is heated before it is exhausted, the heating section (20) being supplied by an electric power source (22). According to the invention, the electric power source (22) comprises photovoltaic cells (24) mounted on the heat exchanger (10) through which the propellant fluid (4) is intended to pass before it reaches the heating section (20). Application to the area of spacecraft propulsion.</p> |
