HEAVY-LIFT TURBOJET ROTOR SYSTEM. VOLUME 3. DESIGN LAYOUT STUDIES
Abstract
The report describes the design layout studies performed during the preliminary design of a tip turbojet rotor system applicable to a helicopter of 60,000 pounds to 80,000 pounds gross weight. The basic rotor system geometry for which these studies were performed was established by means of a parametric design study. Design investigations were directed primarily towards the components above the attachment of the rotor system to the airframe. These included rotor hub and blade retention configuration, rotor blade structural arrangement, power plant installation, flight controls, and airframe/rotor mounted fuel, lubrication, electrical, engine starting, and power management systems. Consideration was also given to tail rotor and accessories drive systems. These design studies and associated stress and weight analyses have established the practicability of the design and fabrication of the tip turbojet rotor system, as well as providing verification for the systems' weights established by the parametric design study weight equations. Development of a tip turbojet helicopter of 60,000 pounds to 80,000 pounds gross weight has been found to be well within the state of the art of all technologies associated with the design and fabrication of an aircraft of this type.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1965
- Accession Number
- AD0624762