Method and apparatus for reducing transient motion between an aircraft power member and structure during takeoff, landing and maneuvers

An aircraft Fluid Torque Restraint (FTR) for attaching an aircraft engine to an aircraft structure, comprising:

• (a) a first housing for attaching to said aircraft engine;
• (b) a second housing for also attaching to said aircraft engine;
• (c) a first inner member within said first housing and attached to said aircraft structure;
• (d) a second inner member within said second housing and also attached to said aircraft structure;
• (e) a flexible element interconnected between said first housing and said first inner member and interconnecting between said second housing and said second inner member and causing a spring-like interconnection therebetween;
• (f) a first fluid chamber formed within said first housing;
• (g) a second fluid chamber formed within said second housing;
• (h) an inertial fluid pathway connected between said first fluid chamber and said second fluid chamber for allowing inertial fluid communication therebetween;
• (i) an inertial fluid contained within and substantially filling said first fluid chamber, said second fluid chamber, and said inertial fluid pathway, said inertial fluid flowing in a direction along said inertial fluid pathway responsive to relative dynamic movement between said aircraft engine and said aircraft structure and causing a tuned fluid inertial effect coinciding with an operating frequency;
• and
• (j) a coupler formed along said inertial fluid pathway, said coupler including a body portion having a lip formed thereon, a coupler piston slidably received within said body portion, said coupler piston having a seat formed thereon, said coupler piston being positioned perpendicular to said direction of fluid flow within said fluid pathway, said coupler piston being free-floating, and when an inertial fluid flow velocity within said inertial fluid pathway is exceeded due to relative vertical transient movements between said aircraft engine and said aircraft structure, said seat on said coupler piston comes interacts with said lip on said body portion and causes a restriction of flow of said inertial fluid within said inertial fluid pathway to further limit transient vertical motions of said aircraft engine relative to said aircraft structure during takeoff and landing conditions.

A helicopter fluid pylon isolator for attachment between a helicopter fuselage and a helicopter pylon, comprising:

• (a) an inner member for attaching to said helicopter fuselage;
• (b) a housing for attaching to said helicopter pylon;
• (c) a flexible element interconnected between said inner member and said housing and causing a spring-like interconnection therebetween;
• (d) a first fluid chamber formed within said fluid pylon isolator;
• (e) a second fluid chamber within said fluid pylon isolator;
• (f) an inertial fluid pathway connected between said first fluid chamber and said second fluid chamber for allowing fluid communication therebetween;
• (g) an inertial fluid contained within and substantially filling said first fluid chamber, said second fluid chamber, and said inertial fluid pathway, said inertial fluid flowing in a direction along said inertial fluid pathway responsive to relative dynamic movement between inner member and said housing and causing a tuned inertial fluid effect for accomplishing isolation of said helicopter fuselage from said helicopter pylon;
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• (h) a coupler formed in said inertial fluid pathway, and in series spring relationship therewith, said coupler including a body portion having a lip formed thereon, a coupler piston telescopically received within said body portion, said coupler piston having a seat formed thereon, said coupler piston being positioned perpendicular to said direction of inertial fluid flow within said inertial fluid pathway, and when an inertial fluid flow velocity within said inertial fluid pathway is exceeded due to relative movement between said inner member and said housing, said seat on said coupler piston cooperates with said lip on said body portion and causes a restriction of inertial fluid flow within said inertial fluid pathway further limiting relative transient movement between said helicopter fuselage and said helicopter pylon during ground resonance conditions.

A method for limiting transient takeoff and landing motions between an aircraft power element, such as an engine or transmission and an aircraft structure which include a fluid mount attached therebetween, comprising:

• a) causing transient fluid flow between a first fluid chamber and a second fluid chamber of said fluid mount upon initially encountering one of said takeoff and landing wherein said fluid mount includes;
• i) means for attaching to said power element,
• ii) means for attaching to said aircraft structure,
• iii) a flexible element interconnected between said power element and said aircraft structure,
• iv) an inertial fluid pathway connected between said first fluid chamber and said second fluid chamber having a seat formed therein,
• v) an inertial fluid contained within and substantially filling said first fluid chamber, said second fluid chamber and said inertial fluid pathway,
• vi) a coupler formed along, and positioned in series relationship with, said inertial fluid pathway, and
• b) restricting said transient fluid flow upon encountering fluid velocities above a predetermined threshold thereby causing said coupler to contact said seat and therein causing a restriction of fluid flow within said inertial fluid pathway thereby restricting further relative transient motion between said aircraft power element and said aircraft structure.

A fluid mount for attaching an aircraft power member to an aircraft structural member, comprising:

• (a) housing means for attaching to said aircraft power member;
• (b) inner member means for attaching to said aircraft structural member;
• (c) a flexible element interconnected between said housing means and said inner member means causing a spring-like interconnection therebetween;
• (d) a first fluid chamber;
• (e) a second fluid chamber;
• (f) a fluid pathway connected between said first fluid chamber and said second fluid chamber for allowing fluid flow therebetween;
• (g) a fluid contained within, and substantially filling, said first fluid chamber, said second fluid chamber and said fluid pathway, said fluid flowing along said fluid pathway responsive to relative dynamic movement between said aircraft power member and said aircraft structural member;
• and
• (h) a coupler positioned in series relationship with said fluid pathway, said coupler including a body portion having a lip formed thereon, a coupler piston telescopically received within said body portion and having a seat formed thereon, said coupler piston being positioned perpendicular to said direction of flow of said fluid within said fluid pathway, and when a fluid flow velocity within said fluid pathway is exceeded due to relative transient motions between said aircraft power member and said aircraft structural member, said seat on said coupler piston comes into contact with said lip on said body portion and causes a restriction of fluid flow within said fluid pathway thereby restricting further relative transient motion between said aircraft power element and said aircraft structural member.