Lord Corporation

Daniel Zameroski

Gerald P Whiteford

Benjamin Bozon

Baptiste Narbon

Alexandre Kursner

An engine mount device includes a housing, a carrier within a cavity in the housing, and a flexure flexibly connecting the carrier to the housing, with a pin disposed in a hole in the carrier to support an engine. A method of providing isolation in the engine mount device includes transmitting a force from the pin into the carrier; mechanically isolating the carrier from the housing via the flexure; and providing, via the flexure, a higher stiffness in one or more radial directions of the hole compared to a stiffness provided in an axial direction of the hole.

Flexure isolator and method of compliant isolation

Devices, systems, and methods for damping vibration of a structural component or power-transmission shafts are disclosed. Damping devices, systems, and methods utilize a lightweight damping device, which is targeted at reducing the resonant amplitude of the first several beaming modes and/or torsional modes of bending a structural component comprising a hollow shaft or strut. The damping device includes a stiff concentric tube with damping elements disposed at each end. The device is inserted within the original structural component or shaft and attached thereto. When the primary shaft undergoes bending due to modal characteristics, the damping elements react to dissipate energy, which effectively reduces the resonant amplitude.

Damping devices, systems and methods for hollow shafts, struts, and beams with bending modes

Aft-mounting systems, devices, and methods for turboprop and turboshaft engines include two or more coupling elementsthat are configured to couple an aft portion of an engine of an aircraft to a support structure of the aircraft. The two or more coupling elements are together configured to react forces generated in a vertical direction and in a lateral direction transverse to the engine but allow substantially unrestricted rotation of the engine with respect to the support structure about an axis of rotation of the engine.

Anti-torque aft-mounting systems, devices, and methods for turboprop/turboshaft engines

Aircraft isolator devices, systems, and methods for isolating a structural component within an aircraft can include an engine interface, airframe, and one or more (e.g., a plurality of) isolator devices attached to the engine interface and the airframe. In some aspects, the isolator devices have a housing, which has a first surface and a second surface that together at least partially define a perimeter of the housing and is configured for attachment to the airframe; an engine attachment component configured for attachment to the engine interface and disposed at least partially inside of the housing; and a plurality of elastomeric elements disposed on or over each of the first and second surfaces of the housing The plurality of elastomeric elements are spaced apart from the engine attachment component via the housing for improved heat dissipation from the engine, reducing operational temperatures of the elastomeric elements to prolong their use.

Isolator devices, systems and methods for aircraft

Aircraft support structures, systems, and methods are disclosed. In one embodiment, an aircraft system includes a rotating component and a support (e.g. strut) that supports the rotating component. The support includes a locking assembly (P) that is configured to lock, automatically, an inner member () of the support with respect to an outer member () of the support for stiffening the support in response to reaching or exceeding a predetermined threshold amount of displacement, load, stress, or rotation. The aircraft support structures, systems, and methods herein utilize self-locking and self-unlocking supports (e.g. struts) for increasing or decreasing a stiffness of the support.

Aircraft support structures, systems, and methods

An engine mount assembly for mounting an engine which produces a torque to a body having a persistent troublesome frequency vibration is disclosed. The engine mount assembly includes two fluid elastomeric chambers groundable to the body, an intermediate cradle link disposed between the two fluid chambers, a lateral link grounded to the body and the intermediate cradle, and a fluid conduit connecting the two fluid chambers. When subjected to torque a positive fluid pressure is generated within the fluid chambers and fluid conduit with the two fluid chambers share a plurality of loads while a transfer of the persistent troublesome frequency vibration from the body to the engine is inhibited.

Helicopter engine mounting assembly

The invention includes an aircraft engine mounting system for mounting an aircraft engine to an aircraft. The mounting system includes a yoke member having a first end and a second end, with an aircraft attachment between the first end and the second end, the aircraft attachment for interfacing the yoke member with the aircraft, the yoke member having a yoke member length (YL) from the first end to the second end. The mounting system preferably includes a first engine mount, the yoke member first end contained by the first engine mount, with the first engine mount having first engine mount housing grounded to the aircraft engine. The mounting system preferably includes a second engine mount, the yoke member second end contained by the second engine mount, with the second engine mount having a second engine mount housing grounded to the aircraft engine.

Aircraft engine mounting system and method of mounting aircraft engines

An engine attachment system (EAS) includes a forward collar (), an aft collar (), at least one truss subassembly () disposed between the forward collar and the aft collar for supporting an engine, and at least one vibration isolator () integrated with each of the forward and aft collars for isolating engine vibration and reducing noise. A method of attaching a turboprop engine includes providing an EAS and hoisting a turboprop engine at least partially within the at least one truss subassembly ().

Turboprop engine attachment systems and methods

An aircraft mounting system is provided having a yoke that is interlocked with engine mounts securable to the engine and the yoke is interchangeable with other yokes on other engines. An aft engine mount is also provided.

In an embodiment the system includes a method of mounting an engine in a rotary wing aircraft. The method includes providing a rotary wing aircraft having an aircraft body supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency (P) with a plurality of (N) rotary wings, the rotary wing aircraft body having a persistent in flight operational rotating frequency vibration. The method includes providing a first engine, the first engine for providing power to rotate the rotary wing system at the rotary wing system operational rotating frequency (P).

Helicopter engine mounting system and methods

In an embodiment the invention includes an aircraft engine mounting system () for mounting an aircraft engine to an aircraft. The aircraft engine mounting system preferably includes an airframe structure member having a first engine end () and a distal second engine end (), with an aircraft attachment between the first engine end and the distal second engine end, the aircraft attachment for interfacing the airframe structure member with the aircraft, the airframe structure member having an airframe structure member length (YL) from the first engine end to the distal second engine end. The aircraft engine mounting system preferably includes a first engine attachment structure member (), the airframe structure member first engine end () contained by the first engine attachment structure member, with the first engine attachment structure member having an outer engine mount member () grounded to the aircraft engine. The aircraft engine mounting system preferably includes a second engine attachment structure member (), the airframe structure member second engine end () contained by the second engine attachment structure member, with the second engine attachment structure member having an outer engine mount member () grounded to the aircraft engine. The aircraft engine mounting system preferably includes the first engine attachment structure member () and the second engine attachment structure member () grounded to the aircraft engine with a mounts spacing (MS) between the first engine.

In an embodiment the invention includes a method of mounting an engine in a rotary wing aircraft. The method includes providing a rotary wing aircraft having an aircraft body supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency (P) with a plurality of (N) rotary wings, the rotary wing aircraft body having a persistent in flight operational rotating frequency vibration. The method includes providing a first engine, the first engine for providing power to rotate the rotary wing system at the rotary wing system operational rotating frequency (P).

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McKean, PA, United States of America

Daniel Zameroski