The design and performance of a spacecraft employing arcjet nuclear electric propulsion, suitable for use in the Space Nuclear Power System Reference Mission, are outlined. The vehicle design is based on a 92 kW ammonia arcjet system operating at an I(sp) of 1050 s and an efficiency of 45 percent. The arcjet/gimbal system, power processing unit, and propellant feed-system are described. A 100 kW(e) space nuclear power system is assumed and the spacecraft mass is baselined at 5250 kg excluding the propellant, propellent feed system, and integrated chemical boost engine. A radiation/arcjet efflux diagnostics package is included in the performance analysis. Three mission scenarios are described and are capable of demonstrating the full capability of the space nuclear power source. The missions considered include power system deployment to possible SDI platform orbits and a spacecraft storage mission to an orbit of three times geosynchronous (GEO) with return to GEO corresponding to Delta V's between 7400 m/s, and 7900 m/s. This spacecraft meets the Reference Mission constraint of low developmental risk and is scaleable to power levels projected for future space platforms.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Spacecraft and mission design for the SpaceNuclear PowerSystem Reference Mission


    Contributors:

    Publication date :

    1987-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Spacecraft mission design

    Brown, Charles D. | SLUB | 1996


    Spacecraft mission design

    Brown, Charles D. | SLUB | 1992


    Spacecraft mission design

    Brown, Charles D. | SLUB | 1998


    Spacecraft mission design

    Brown, Charles D. | TIBKAT | 1998