Pylon Restraint System
AssigneeTextron Innovations Inc.
InventorsPeter Quinn Romano, Jedediah Bryce Goodell, Joshua Andrew Emrich, Michael S. Seifert
Life of this patent
Estimating the term…
Abstract
In an embodiment, a rotorcraft includes an airframe; a main rotor transmission; one or more brackets mounting the main rotor transmission to the airframe, longitudinal axes of the one or more brackets being substantially parallel with a longitudinal axis of the rotorcraft; and one or more restraints mounting the main rotor transmission to the airframe, the one or more restraints being mounted at an angle non-orthogonal to the longitudinal axis of the rotorcraft and a lateral axis of the rotorcraft.
Claims20
A method for determining parameters for a transmission restraint in a rotorcraft, the method comprising:
- determining a plurality of inputs for a main rotor system, the main rotor system including a rotorcraft fuselage, a rotorcraft transmission, and a rotorcraft hub;
- determining, according to equations of motion for the main rotor system, a spring rate for a restraint for attaching the rotorcraft transmission to the rotorcraft fuselage;
- calculating, according to the spring rate, a distance between an attachment point of the restraint on the rotorcraft transmission and a virtual focal point of two brackets for attaching the rotorcraft transmission to the rotorcraft fuselage;
- and
- calculating an angle of restraint between the restraint and the rotorcraft fuselage based on the spring rate and the distance, wherein the angle of restraint is between 0° and 90°.
A method for providing a rotorcraft system, the method comprising:
- determining a plurality of inputs for a main rotor system of the rotorcraft system, the main rotor system including a rotorcraft fuselage, a rotorcraft transmission, and a rotorcraft hub;
- determining, using the inputs, a spring rate for each restraint of one or more restraints configured to attach the rotorcraft transmission to the rotorcraft fuselage;
- connecting a main rotor transmission to an airframe with one or more brackets, wherein longitudinal axes of the one or more brackets are substantially parallel with a longitudinal axis of the rotorcraft system;
- and
- connecting the main rotor transmission to the airframe with the one or more restraints, wherein each distance between an attachment point of each restraint at the the rotorcraft transmission and a virtual focal point of the one or more brackets is associated with the spring rate, and wherein the one or more restraints are mounted at an angle that is non-orthogonal to the longitudinal axis of the rotorcraft system and a lateral axis of the rotorcraft system, wherein an angle of restraint between each restraint of the one or more restraints and the rotorcraft fuselage is associated with the spring rate and the distance, and is between 0° and 90°.
A method for providing a rotorcraft system, the method comprising:
- providing a transmission configured to be coupled to a rotor hub that is configured to have one or more rotor blades attached thereto;
- and
- providing a transmission mounting assembly for mounting the transmission to an airframe, the providing transmission mounting assembly comprising:
- connecting a main rotor transmission to an airframe with one or more brackets, wherein longitudinal axes of the one or more brackets are substantially parallel with a longitudinal axis of the rotorcraft system;
- and
- connecting the main rotor transmission to the airframe with the one or more restraints, wherein each distance between an attachment point of each restraint at the rotorcraft transmission and a virtual focal point of the one or more brackets is associated with a spring rate for each of the restraints, wherein the spring rate for each of the constraints is associated with inputs for a main rotor system of the rotorcraft system by motion equations treating one or more of the inputs as portions of a harmonic oscillator, and wherein the one or more restraints are mounted at an angle that is non-orthogonal to the longitudinal axis of the rotorcraft and a lateral axis of the rotorcraft, wherein an angle of restraint between each restraint of the one or more restraints and lateral axis of the airframe is associated with the spring rate and the distance, and is between 0° and 90°.
Dependencies are inferred from the claim text.