A hydrazine fueled piston engine for providing 11.2 kW was developed to satisfy the need for an efficient power supply in the range from 3.7 to 74.6 kW 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 and above and cruise for extended periods. A remotely piloted aircraft and the associated flight control techniques for this application were designed. The engine is geared down internally (2:1) to accommodate a 1.8 m diameter propeller. An alternator is included to provide electrical power. The pusher-type engine is mounted onto the aft closure of the fuel tank, which also provides mounting for all other propulsion equipment. About 20 hrs of run time demonstrated good efficiency and adequate life. One flight test to 6.1 km was 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 :

    1979-01-01


    Type of media :

    Conference paper


    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