Structurally tunable cores

US11001375B2 · kind B2 · utility

Assignee

• The Boeing Company · US

Inventors

• Peter Holemans · Wallingford, US
• Michael J. DeLuca · Boca Raton, US
• Douglas R. Ludin · Malvern, US

Key dates

• Filing date: Mar 18, 2019
• Grant date: May 11, 2021
• Expiry date: Jul 30, 2039

Classification

• Technology area (CPC B): Performing Operations; Transporting
• CPC primary: B64C2027/003
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

Structurally tunable cores are described that can be implemented, for example, in aircraft components. An example flex beam for coupling a rotor blade to a rotor hub includes a first composite laminate, a second composite laminate, a third composite laminate, first resilient core members and second resilient core members. The first composite laminate forms a first skin of the flex beam. The second composite laminate is located opposite the first composite laminate and forms a second skin of the flex beam. The third composite laminate is located between the first composite laminate and the second composite laminate. The first resilient core members extend between the first composite laminate and the third composite laminate. The second resilient core members extend between the second composite laminate and the third composite laminate.