The boeing company (20240278905). Linear Actuator Driven Flap Mechanism simplified abstract

Linear Actuator Driven Flap Mechanism

Organization Name

the boeing company

Inventor(s)

Samuel L. Block of Bothell WA (US)

Kevin R. Tsai of Redmond WA (US)

Linear Actuator Driven Flap Mechanism - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240278905 titled 'Linear Actuator Driven Flap Mechanism

Simplified Explanation: The abstract describes a linear actuator driven flap mechanism for an aircraft wing that is compact and can be used in thinner, smaller aircraft wings.

• The flap mechanism is contained within the wing support and fairing of the aircraft wing.
• The rib frame of the flap mechanism is attached to the wingbox structure of the aircraft wing at two points.
• The rib frame defines a width with two webs.
• A linear actuator and motion linkage are positioned within the width of the rib frame.
• The linear actuator is not mechanically driven rotary actuation or mechanically driven linear actuation.

Potential Applications: 1. Aircraft manufacturing industry for designing thinner and smaller wings. 2. Aerospace engineering for improving wing efficiency and performance.

Problems Solved: 1. Allows for the use of compact flap mechanisms in modern aircraft designs. 2. Enhances the functionality of aircraft wings without increasing their size.

Benefits: 1. Improved aerodynamic performance. 2. Increased efficiency in aircraft design. 3. Enhanced maneuverability of aircraft.

Commercial Applications: The technology can be utilized in the development of next-generation aircraft with improved performance and efficiency, catering to the needs of the aviation industry.

Questions about Aircraft Wing Flap Mechanism: 1. How does the linear actuator driven flap mechanism improve aircraft wing performance? 2. What are the key advantages of using this innovative flap mechanism in aircraft design?

Original Abstract Submitted

a linear actuator driven flap mechanism for an aircraft wing is contained within a wing support and fairing of the aircraft wing. the rib frame of the flap mechanism is attached to the wingbox structure of the aircraft wing at a first and second point. the rib frame of the flap mechanism defines a width with a first and second web. a linear actuator and a motion linkage are positioned with the width between the first and second webs of the rib frame. the linear actuator is not mechanically driven rotary actuation or mechanically driven linear actuation. as a result of the compact construction, the flap mechanism can be employed in thinner, smaller aircraft wings being designed today.