Abstract
The possibility of developing power and transport systems for space applications is examined. It is suggested to use an MHD generator utilizing inhomogeneous gas-plasma flows of inert gas as the source of electric energy in such systems. The plasma of the current layers may be in the state of “frozen ionization,” when the degree of ionization exceeds the equilibrium level thereby providing for an effective MHD interaction with the enthalpy extraction coefficient of 0.4 and adiabatic efficiency of 0.8. Such a plasma is stable with respect to dissipative instabilities (ionization and overheating) and retains its positive properties at a stagnation pressure of the order of 1 MPa. The estimation of the mass-and-size characteristics of a closed-cycle solar MHD facility for space applications reveals that the specific power of the facility may amount to 500 W/kg. It is suggested that the propulsion unit should be provided by an electric rocket engine on the basis of an MHD accelerator, with the working medium provided by a nonuniform gas-plasma flow in which azimuthal plasma rings (T-layers) are inductively connected to the electric energy source. In a flow with T-layers, an efflux velocity of the order of 40 km/s is attained. With a mass flow rate of 50 g/s, the engine may develop a propulsive force of 2000 N.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
