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):

Report Date:

1953-01-02

Pagination or Media Count:

17.0

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.

Subject Categories:

  • Helicopters
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE