Patents by Inventor R. Kyle Schmidt
R. Kyle Schmidt has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 9994309Abstract: A pitch trimmer assembly for an aircraft landing gear having a damping element arranged to be connected between a first and a second element of an aircraft landing gear and arranged to exert a first damping force when in a first state and a second damping force in a second state, the damping element being switchable between the first and second states in dependence on the relative positions of the first and second landing gear elements.Type: GrantFiled: February 4, 2014Date of Patent: June 12, 2018Assignee: Safran Landing Systems UK Ltd.Inventors: Ben Hodgkinson, R. Kyle Schmidt, David Smart
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Publication number: 20150375856Abstract: A pitch trimmer assembly for an aircraft landing gear having a damping element arranged to be connected between a first and a second element of an aircraft landing gear and arranged to exert a first damping force when in a first state and a second damping force in a second state, the damping element being switchable between the first and second states in dependence on the relative positions of the first and second landing gear elements.Type: ApplicationFiled: February 4, 2014Publication date: December 31, 2015Inventors: Ben Hodgkinson, R. Kyle Schmidt, David Smart
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Publication number: 20140107990Abstract: Method and system of determining ground-to-tyre friction coefficient for an aircraft landing event. The method uses an aircraft computational model to repeatedly model the landing event, varying one or more initial conditions of the aircraft model until a best match between a modelled value and a provided value of aircraft vertical acceleration is determined. The method uses initial conditions associated with the best match of modelled and provided vertical acceleration values and a strain value from a sensor on the aircraft landing gear, with the ground-to-tyre friction coefficient is a variable. The method models the landing gear to generate a modelled strain value and compares this with the measured strain value, and repeats the landing gear modelling step with a different value for the ground-to-tyre friction coefficient until a best match between the modelled strain value and the measured strain value is determined and outputting the respective friction coefficient value.Type: ApplicationFiled: March 16, 2012Publication date: April 17, 2014Applicant: Messler-Dowty LimitedInventors: Laura Collett, R. Kyle Schmidt, Pia Sartor
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Patent number: 8567716Abstract: An uplock assembly for retaining and releasing landing gear systems, said uplock assembly comprising: a thermal actuator comprising: a chamber configured to contain expansible material therein; a heating mechanism coupled to said chamber for heating said expansible material and causing volumetric expansion thereof; a piston slidably coupled to said chamber and adapted to extend in response to said volumetric expansion; and an uplock release mechanism releasably engaged by said piston when extended such that said engaged uplock release mechanism causes the release of said landing gear.Type: GrantFiled: December 19, 2008Date of Patent: October 29, 2013Assignee: Messier-Dowty Inc.Inventors: R. Kyle Schmidt, Michael Sinclair, Edward Chun Kei Chan
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Patent number: 8446294Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.Type: GrantFiled: August 11, 2009Date of Patent: May 21, 2013Assignee: Messier-Dowty Inc.Inventor: R. Kyle Schmidt
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Patent number: 8262019Abstract: The invention relates to a new method and system for health monitoring of aircraft landing gear. The system includes sensors that are attached to the landing gear structure and equipment (e.g., one or more of brakes, tires, hydraulics, electrical systems and switches) and analyzed to report and alert personnel such as pilots, maintenance personnel, airline operators, ground crew and regulatory authorities of the health of the landing gear and the potential need for service, maintenance or replacement. The system monitors and reports critical health issues as real-time information which can be analyzed in conjunction with an extensive database of information and used to alert pilots or other relevant personnel to the condition of the landing gear and actions that may be required as a result.Type: GrantFiled: October 12, 2011Date of Patent: September 11, 2012Inventors: R. Kyle Schmidt, Steven A. Gedeon
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Publication number: 20120053784Abstract: The invention relates to a new method and system for health monitoring of aircraft landing gear. The system includes sensors that are attached to the landing gear structure and equipment (e.g., one or more of brakes, tires, hydraulics, electrical systems and switches) and analyzed to report and alert personnel such as pilots, maintenance personnel, airline operators, ground crew and regulatory authorities of the health of the landing gear and the potential need for service, maintenance or replacement. The system monitors and reports critical health issues as real-time information which can be analyzed in conjunction with an extensive database of information and used to alert pilots or other relevant personnel to the condition of the landing gear and actions that may be required as a result.Type: ApplicationFiled: October 12, 2011Publication date: March 1, 2012Applicant: Messier-Dowty Inc.Inventors: R. Kyle Schmidt, Steven A. Gedeon
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Publication number: 20110056197Abstract: An uplock assembly for retaining and releasing landing gear systems, said uplock assembly comprising: a thermal actuator comprising: a chamber configured to contain expansible material therein; a heating mechanism coupled to said chamber for heating said expansible material and causing volumetric expansion thereof; a piston slidably coupled to said chamber and adapted to extend in response to said volumetric expansion; and an uplock release mechanism releasably engaged by said piston when extended such that said engaged uplock release mechanism causes the release of said landing gear.Type: ApplicationFiled: December 19, 2008Publication date: March 10, 2011Applicant: MESSIER-DOWTY INC.Inventors: R. Kyle Schmidt, Michael Sinclair, Edward Chun Kei Chan
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Patent number: 7845220Abstract: The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.Type: GrantFiled: August 24, 2007Date of Patent: December 7, 2010Assignee: Messier-Dowty Inc.Inventors: R. Kyle Schmidt, Simon Hou
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Publication number: 20100239361Abstract: This invention provides a pin assembly that is self-lubricating and includes a pin, a pin insert that is received within the pin and a quantity of lubricating agent. The present invention also provides an insert for a pin that may be used in a pin joint that contains an automatic lubrication dispensing mechanism.Type: ApplicationFiled: June 3, 2010Publication date: September 23, 2010Applicant: MESSIER-DOWITY INC.Inventor: R. KYLE SCHMIDT
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Publication number: 20100114411Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.Type: ApplicationFiled: August 11, 2009Publication date: May 6, 2010Applicant: Messier-Dowty Inc.Inventor: R. KYLE SCHMIDT
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Publication number: 20090293624Abstract: The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.Type: ApplicationFiled: August 24, 2007Publication date: December 3, 2009Applicant: MESSIER-DOWTY INC.Inventors: R. Kyle SCHMIDT, Simon Hou
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Patent number: 7589645Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.Type: GrantFiled: June 12, 2006Date of Patent: September 15, 2009Assignee: Messier-Dowty Inc.Inventor: R. Kyle Schmidt
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Publication number: 20080217107Abstract: This invention provides a pin assembly that is self-lubricating and includes a pin, a pin insert that is received within the pin and a quantity of lubricating agent. The present invention also provides an insert for a pin that may be used in a pin joint that contains an automatic lubrication dispensing mechanism.Type: ApplicationFiled: February 1, 2008Publication date: September 11, 2008Applicant: MESSIER-DOWTY INC.Inventor: R. Kyle SCHMIDT