Honeywell International Inc.

Alliedsignal Inc.

The Garrett Corporation

William F Ryan

Daniel C Birchak

Albert Kang

Christopher Thomas

John Thurston

John Perek

Darrell Horner

Stephen G Abel

Glenn H Lane

David M Mathis

Abhay Naik

Doug Smith

Bharath Chandra G

Dan Birchak

James A Wissinger

Douglas T Hopper

Saravana Mahalingam

Steven Brian Rowe

Michael A Pepe

Joseph P Silk

Shek M Cheung

Jacob Bayer

Dieter Haase

David Muggeridge

Jagadeesh Hariwal

Lightning-dissipative A/C assemblies are provided, as are valve frames utilized within lightning-dissipative A/C assemblies. In embodiments, the lightning-dissipative A/C assembly includes a base dielectric component having a mount interface, a strike-susceptible metallic component coupled to the base dielectric component, and mounting hardware configured to engage the mount interface to attach the base dielectric component to an A/C. An electrically-conductive coating overlies or is formed over at least a portion of the base dielectric component to complete a lightning strike dissipation path. The lightning strike dissipation path extends from the strike-susceptible metallic component, through the electrically-conductive coating, through the mounting hardware, and to an A/C electrical ground plane when the lightning-dissipative A/C assembly is installed on the A/C. In one implementation, the base dielectric component assumes the form of a valve frame, while the strike-susceptible metallic component assumes the form of a valve door movably mounted to the valve frame.

Lightning-dissipative aircraft assemblies and valve frames utilized in the same

Outflow valve (OFV) assemblies including non-metallic frames and enhanced attachment features are provided. In embodiments, the OFV assembly includes a non-metallic frame to which at least one valve door is pivotally mounted. The non-metallic frame may, in turn, include a generally rectangular frame body, a central opening through the frame body, an outer peripheral flange extending around at least a portion of the frame body. Frame attachment interfaces are distributed or spaced around the outer peripheral flange of the non-metallic frame. The frame attachment interfaces include fastener openings and elevated platform regions, which project from an inboard side of the outer peripheral flange and through which the fastener openings extend. Base plates seat against the elevated platform regions. Fasteners engage the base plates and extend through the fastener openings to an outboard side of the outer peripheral flange to attach the OFV assembly to an aircraft fuselage.

Outflow valve assemblies including non-metallic frames and enhanced attachment features

A component mounting assembly includes a non-metallic frame, a nut plate, and a grounding strap. The non-metallic frame is adapted for mounting to an aircraft fuselage. The non-metallic frame includes an outer peripheral portion having one or more fastener openings formed therein, and extends to a first height above the outer peripheral portion. The nut plate is coupled to the outer peripheral portion and extends therefrom to a second height that is at least 50% of the first height. The grounding strap is coupled, via a threaded fastener, to the nut plate.

Device for electrically grounding aircraft components mounted on a composite skin fuselage

Embodiments of a cabin outflow valve having one or more laterally-tapered sealing surfaces are provided, as are cabin pressure controls system including cabin outflow valves. In one embodiment, the cabin outflow valve includes a frame and a first door, which is pivotally coupled to the frame and which is rotated by an actuator between open and closed positions. The first door includes, in turn, a torque input point at which the actuator applies a closing force when rotating the first door into a closed position. A laterally-tapered sealing surface extends along a lateral axis of the cabin outflow valve and has a profile height decreasing with increasing proximity to the torque input point. The laterally-tapered sealing surface helps to ensure the formation of a complete lateral seal when in the first door is rotated into the closed position to significantly reduce or eliminate leakage through the cabin outflow valve.

Cabin outflow valves having laterally-tapered sealing surfaces and cabin pressure control systems employing the same

A compressor system that is configured to compress the fluid from low pressure source to a higher pressure magnitude is powered from the same low pressure fluid source. The compressor system includes two piston assemblies that are coaxially coupled to one another, and that are of differing cross sectional areas. The low pressure fluid is used to move the larger piston assembly, which is in turn used to move the smaller piston assembly. Low pressure fluid is selectively admitted to the smaller piston assembly, and movement thereof is used to compress the low pressure fluid to a higher pressure magnitude. The compressor system uses a fluidic bistable amplifier, which also coupled to the low pressure fluid source, to control low pressure fluid flow to the larger piston assembly, to thereby control its movement.

Fluidic compressor

A fluidic pulse generator system includes two fluidic diverter valves that are both controlled by a single fluidic pilot valve. The fluidic pilot valve and the two fluidic diverter valves are each adapted to receive a flow of pressurized fluid. The flow of pressurized fluid through the fluidic pilot valve is controlled in response to pressurized fluid flow through a control valve. In turn, the flow of pressurized fluid through the two fluidic diverters valves is simultaneously controlled in response to the flow of pressurized fluid through the fluidic pilot valve.

Fluidic pulse generator system

A thruster valve has a continuously positionable piston between a closed position and a maximum open position. The piston moves in response to the difference in pressure between the pressure of the valve's inlet and thruster nozzle and the pressure behind the piston. A pivotable flapper valve regulates this pressure difference. When a change in thrust is required a force is applied to the flapper causing a change in this pressure difference which causes the piston to move until the desired thrust level is obtained.

Force driven hot gas proportional thruster valve

A pneumatically driven hydrostatic actuator and a pneumatically driven recirculating hydraulic actuator are provided. Each of these actuators consists of a hydraulic pump fluidly coupled to an actuator. The pump is driven by a low inertia pneumatic motor that extracts pressure energy from pressurized gas and converts it to rotary motion. The pneumatic motor is preferably made from stainless steel A286 so that it can operate using pressurized hydrogen gas. The components of both actuators are in a closely coupled relationship so that they can be arranged in a compact unitary package.

Pneumohydraulic actuator

Flight control apparatus (10) for a cannon-launched anti-tank projectile. A boom that structurally secures four fins (18) and four nozzles (20) to an afterbody (12) of the projectile, and that provides for fluid communication from the afterbody to the nozzles, is provided in the form of an assembly (14) comprising intersecured tubes (22, 24, 26, 28) which define a longitudinal axis (30) of the assembly. The boom assembly (14) considerably reduces the weight and fabrication cost associated with a conventional boom which is provided in the form of an integral multi-channeled cylinder.

Flight control apparatus for an anti-tank projectile

A fluidic thruster control system and method for guided missiles and the like, which utilizes a fluidic jet interaction device for controlling a downstream fluidic vortex amplifier to modulate exhaust flow through thrust nozzles.

Fluidic thruster control and method

Pressurized motive fluid flow passes through a single fluidic vortex orifice to opposite chambers of a differential area, double acting, linear servo-cylinder. While shifting in one direction the vortex orifice severely restricts the flow to the fluid chamber of the motor which is contracting in size so as to permit rapid movement of the piston in that direction, and whenever the piston is moving in an opposite direction the vortex orifice allows substantially unrestricted fluid flow to the same chamber which is now expanding in size, so that the piston can shift rapidly in this opposite direction.

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Phoenix, AZ, United States of America

William F Ryan