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US 11,891,169 B2Granted
Insert for a blade of a rotary-wing aircraft
AssigneeTextron Innovations Inc.
InventorsPaul Branson Sherrill, Robert Alan Self
Life of this patent
Estimating the term…
Abstract
In an implementation, a rotor blade (alternatively referred to herein as “blade”) for a helicopter or other aircraft may include an outer layer. The outer layer may define a cavity. The outer layer may at least partially correspond to an airfoil, e.g., a wing. One or more inserts may be included within the cavity and be encompassed thereby. The first insert may have a density of at least 0.6 pounds per cubic inch.
Claims16
A blade for a rotary wing aircraft, comprising:
- an outer layer defining a cavity;
- and
- at least one inertia insert disposed within the defined cavity,
- wherein the at least one inertia insert includes a plurality of weight segments, and a binding agent surrounding one or more of the plurality of weight segments and separating the one or more of the plurality of weight segments from a neighboring weight segment;
- wherein the one or more of the plurality of weight segments include tungsten;
- and
- wherein a trailing surface of at least one of the plurality of weight segments is crescent shaped and the location of the center of gravity of the blade is based on the trailing surface, and
- wherein the one or more of the plurality of weight segments are configured to flex without fracture in response to a bending moment on the blade.
5 more elements
An insert for a helicopter blade, comprising:
- a plurality of weight segments;
- and
- a binding agent surrounding one or more of the plurality of weight segments and separating the one or more of the plurality of weight segments from a neighboring weight segment;
- wherein, the one or more of the plurality of weight segments include tungsten;
- and
- wherein a trailing surface of at least one of the plurality of weight segments is crescent shaped and the location of the center of gravity of the blade is based on the trailing surface, and
- wherein the one or more of the plurality of weight segments are configured to flex without fracture in response to a bending moment on the blade.
4 more elements
Dependencies are inferred from the claim text.