Accession Number : AD0016733


Title :   PULSE-JET HELICOPTER POWER CONTROL SYSTEM DEVELOPMENT


Descriptive Note : Quarterly rept. no. 1


Corporate Author : FAIRCHILD ENGINE AND AIRPLANE CORP COSTA MESA CA FAIRCHILD ELECTROTECHNICS DIV


Personal Author(s) : McJones, R W


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/016733.pdf


Report Date : 02 Jan 1953


Pagination or Media Count : 17


Abstract : A pulsejet helicopter power-control system is being developed to coordinate automatically fuel-flow and power requirements. Ideally, the control is to correct for all changes in flight path, gross weight, and altitude without adjustment by the pilot. Practically, the control may require occasional, minor adjustments. The fuel flow is to be maintained between lean and rich blowout limits at all operational altitudes and is to permit maximum thrust and throttling ranges. The rotor speed is to be maintained within + or - 5% for all operating conditions; variations of +10 and -20% over a 3-sec interval are to be tolerated in abrupt maneuvers. The system must weigh less than 0.5% of the maximum hourly fuel consumption and require less than 1% of the maximum rotor power. The most promising configuration involves a programing leakage between the collective pitch control and the throttle. A simple govenor is to be added as a trimming device if the linkage leaves large residual errors.


Descriptors :   *JET HELICOPTER ROTORS , REQUIREMENTS , THROTTLING , PITCH(INCLINATION) , RATES , FUELS , BLOWOUTS , WEIGHT , FUEL CONSUMPTION , POWER , THRUST , CONTROL , LIMITATIONS


Subject Categories : Helicopters
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE