Parker-hannifin Corporation

International Telephone and Telegraph Corporation

Parker-hannifan Plc

Luc P Cyrot

Edward Hyrlik

Eric A Polcuch

Nancy Kay Keech

David McLaughlin

Jon Dustin Hitt

Charles B Hartin

Bruce Streeter

Jonathan S Olsoe

Stephane Wanchu

Edward F Hyrlik

A multi-disk brake assembly includes a static structure defining a plurality of slots, a plurality of disks including stator disks that are supported by the static structure and are non-rotatable, and rotor disks that are interleaved with the stator disks and are rotatable, the plurality of disks being axially moveable between an engaged position and a disengaged position, and a dust-collecting receptacle that is attachable to the static structure for securement during an operative state of the multi-disk brake assembly. The dust-collecting receptacle is in fluid communication with the plurality of slots for receiving and trapping dust from the plurality of disks through the plurality of slots. The dust-collecting receptacle is detachable relative to the static structure during a non-operative state of the multi-disk brake assembly.

Dust collector for multi-disk brake

A multi-disk brake assembly includes a stator disk that is non-rotatable, a rotatable rotor disk arranged adjacently and coaxially with the stator disk, and an axial retention device. The rotor disk and the stator disk are axially moveable between an engaged position during braking operation and a disengaged position during a released mode of operation. The axial retention device is axially moveable and supports at least one of the disks. The axial retention device includes a set of axially translatable pins or bolts that are pushed by the disks during the braking operation and maintain a predetermined space between the disks during the released mode of operation. The predetermined space and position of the disks is maintained when the brake assembly is subject to forces due to vehicle acceleration or cornering.

Positioning of disks in the brake released mode for multi disk brakes

An actuator assembly having a primary load path for tightly coupling an actuated surface to a reference structure and a secondary load path having a backlash portion for coupling the actuated surface to the reference structure with backlash, wherein the secondary load path is unloaded during an operative state of the primary load path and loaded during a failure state of the primary load path. The actuator assembly includes at least one sensor configured to sense the failure state of the primary load path when a relative displacement between a portion of the primary load path and a portion of the secondary load path exceeds a predetermined value or is within a predetermined range of values.

Horizontal stabilizer trim actuator failure detection system and method using position sensors

An actuator for actuating movement of a control surface relative to a structure can include a high-efficiency assembly and a low-efficiency assembly. The high-efficiency assembly can be connectable between a control surface and a structure for providing a first load transfer assembly and the assembly can have minimum backlash. The low-efficiency assembly is connectable between the control surface and the structure for providing a second load transfer assembly. The low-efficiency or irreversible assembly can be disposed in parallel relationship to the high-efficiency assembly and can have a higher backlash than the low-efficiency assembly. The low-efficiency assembly can be unloaded in normal operation. The actuator also can include a coupler for that can have a closed state in which both load transfer assemblies are synchronously driven by the drive mechanism, and an open state in which the drive mechanism is decoupled from the low-efficiency assembly and the low-efficiency assembly can inhibit movement of the control surface.

Aircraft stabilizer actuator

A flight control system and method including a primary flight control path between one or more pilot controls and control surface actuators on an associated aircraft, wherein the primary control path includes one or more flight control computers and one or more first data concentrators; and a secondary flight control path between the one or more pilot controls and the control surface actuators, wherein the secondary flight control path utilizes direct mode control laws to control the control surface actuators; wherein the primary flight control path and the secondary flight control path are independent from each other and the secondary flight control path is operative upon detection of a fault in the primary flight control path.

Flight control system with alternate control path

An actuator system () comprising a valve assembly () having an inner spool (), an outer spool (), and a sleeve (). An assembly () directly drives the inner spool () to move it relative to the outer spool (), and thereby hydromechanically causes the outer spool () to move relative to the sleeve (). A control assembly () provides current input to the drive assembly (), which converts current input into mechanical motion. The control assembly () senses the position of the inner spool () and regulates current in accordance with the sensed position.

Actuator system

A solenoid having one or more windings, a plurality of alternate windings of which are connected in electromagnetic field bucking relationship. An alternative construction utilizes layers of bifilar windings. A first winding of each bifilar winding pair in a first layer is adapted to procduce a field to buck the field of a second winding in the same bifilar winding pair.

Valve solenoid windings

A fluid control system includes a fluid motor 11, a control valve 12 for directing fluid flow to and from the motor 11, and a control valve actuator 14 for operating the control valve 12. The control valve actuator 14 includes an actuator member 32, a feedback member 44, and a spring 46 which exerts a force on the actuator member 32 whose magnitude varies with the relative positions of the actuator member 32 and the feedback member 44. A command pressure signal moves the actuator member 32 to operate the control valve 12 in order to direct fluid flow to and from the fluid motor 11. A feedback link 41 connects the feedback member 44 to the fluid motor 11. The actuator piston 32 is slidably carried on the feedback member 44, so that any drifting of the fluid motor 11 results in immediate movement of the actuator member 32 and control valve 12 to correct the drifting.

Fluid control system

A device for controlling hydraulic motors as in an aircraft 'fly-by-wire' system wherein redundant hydraulic motors and controls are required to protect against failure of portions of the system or device. The device includes two master valves for controlling flow of fluid to and from the motors, one controlled by electrical signals from a command station and the other controlled mechanically through manual or automatic operation. There is a transfer valve for selecting which of the master valves is to be operable and to provide for smooth transition of control from the electrically controlled valve to the mechanically controlled valve. The electrically controlled valve is positioned by means of an articulated command shaft of hybrid force displacement summing structure having redundant hydraulic drive units each controlled by redundant electro-hydraulic servo valves and wherein failed servo valves are accounted for in the force displacement summing structure in a manner to avoid the need for rapid failure detection and correction.

Growing community of inventors

Mission Viejo, CA, United States of America

Luc P Cyrot