Power transfer systems for future navy helicopters. Final report 25 Jun 70--28 Jun 72

Technical Report · Wed Nov 01 04:00:00 EST 1972

OSTI ID:7216994

Bossler, Jr, R B

The purpose of this program was to conduct an analysis of helicopter power transfer systems (pts), both conventional and advanced concept type, with the objective of reducing specific weights and improving reliability beyond present values. The analysis satisfied requirements specified for a 200,000 pound cargo transport helicopter (CTH), a 70,000 pound heavy assault helicopter, and a 15,000 pound non-combat search and rescue helicopter. Four selected gearing systems (out of seven studied), optimized for lightest weight and equal reliability for the CTH, using component proportioning via stress and stiffness equations, had no significant difference between their aircraft payloads. All optimized pts were approximately 70% of statistically predicted weight. Reliability increase is predicted via gearbox derating using Weibull relationships. Among advanced concepts, the Turbine Integrated Geared Rotor was competitive for weight, technology availability and reliability increase but handicapped by a special engine requirement. The warm cycle system was found not competitive. Helicopter parametric weight analysis is shown. Advanced development Plans are presented for the pts for the CTH, including total pts system, selected pts components, and scale model flight testing in a Kaman HH2 helicopter.

• Research Organization: Kaman Aerospace Corp., Bloomfield, CT (USA)
• OSTI ID: 7216994
• Report Number(s): AD-905180; R-1032
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330600* -- Advanced Propulsion Systems-- Vehicle Design Factors
AIRCRAFT
DESIGN
ENERGY CONSUMPTION
EXHAUST GASES
FUEL CONSUMPTION
GASEOUS WASTES
GEARS
MACHINE PARTS
MECHANICAL TRANSMISSIONS
ROTORS
TURBINES
TURBOMACHINERY
WASTES
WEIGHT