Accession Number : ADA047678
Title : Preliminary Design Study of an Integrated Tail Rotor Servo Power Module.
Descriptive Note : Final rept.,
Corporate Author : UNITED TECHNOLOGIES CORP STRATFORD CONN SIKORSKY AIRCRAFT DIV
Personal Author(s) : Maciolek,Joseph R ; Wallischeck,Karl
PDF Url : ADA047678
Report Date : Sep 1977
Pagination or Media Count : 163
Abstract : The purpose of the work performed was to determine the feasibility of generating the hydraulic power required to control the tail rotor pitch of a utility helicopter by locating tail-rotor-driven hydraulic supply systems within the tail rotor servo. This relocation of the hydraulic supply system would eliminate the weight, the cost and the excessive vulnerability of the long hydraulic lines in conventional servo systems. Using the YUH-60 as a design subject, a preliminary design of an integrated servo power module with electrical (fly- by-wire) inputs was performed. This study confirms the advantages of generating the hydraulic power at the tail rotor gearbox. When combined with a fly-by-wire controller, the weight saving for a UTTAS design would be the order of 10 lbs. Compared with the current conventional system, the MTBF of the system would increase by a 7 to 1 factor. Production cost savings could be almost $2000 per aircraft.
Descriptors : *FLY BY WIRE CONTROL, *HELICOPTERS, *HYDRAULIC SERVOMECHANISMS, TAIL HELICOPTER ROTORS, SCHEMATIC DIAGRAMS, WEIGHT REDUCTION, COST BENEFITS, RELIABILITY, VULNERABILITY ANALYSIS, SURVIVAL(GENERAL), MAINTAINABILITY
Subject Categories : Helicopters
Hydraulic and Pneumatic Equipment
Distribution Statement : APPROVED FOR PUBLIC RELEASE