A hydrazine-fueled piston-type engine for providing 11.2 kW (15 hp) has been developed to satisfy the need for an efficient power supply in the range from 3.7 to 74.6 kW (5 to 100 hp) where existing nonair-breathing power supplies such as fuel cells or turbines are inappropriate. The engine was developed for an aircraft to fly to 21.3 km (70,000 ft) and above and cruise for extended periods. The NASA Hugh L. Dryden Flight Research Center developed a remotely piloted aircraft and the associated flight control techniques for this application. About 20 hr of run time have demonstrated good efficiency and adequate life. One flight test to 6.1 km (20,000 ft) has been made using the engine with a small fixed-pitch four-bladed propeller. The test was successful in demonstrating operational characteristics and future potential.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Hydrazine monopropellant reciprocating engine development


    Contributors:

    Publication date :

    1979-11-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





    Hydrazine-Based Green Monopropellant Blends

    Masse, Robert K. / Glassy, Benjamin A. / Spores, Ronald A. et al. | AIAA | 2024



    Hydrazine Azide as an Additive for Monopropellant Hydrazine

    THOMAS F. SEAMANS AND GEORGE R. HUSON | AIAA | 1971