Patents by Inventor Robert Kyle Schmidt
Robert 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: 10640202Abstract: A shock absorber assembly having a wheel assembly including first and second coupling points, and first and second shock absorber elements. Each shock absorber element includes a housing portion defining a bore, and a rod slidably coupled within the bore such that the shock absorber element has a variable length. Each rod is coupled to a respective coupling point of the wheel assembly. The shock absorber assembly is arranged to maintain the relative positions of the first and second housing portions such that the longitudinal axis of the first bore has a generally fixed relationship with respect to the longitudinal axis of the second bore.Type: GrantFiled: January 15, 2015Date of Patent: May 5, 2020Assignee: Safran Landing Systems UK LTDInventors: Andraz Vatovec, Robert Kyle Schmidt
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Patent number: 10625850Abstract: An aircraft landing gear shock absorber assembly having an outer casing having a bore which extends through the outer casing. The bore has a first opening and a second opening. A rod is slidably coupled within the bore such that a first end of the rod projects out of the first opening of the bore, the first end of the rod being arranged to be attached to a wheel assembly. A closure is provided for the second opening of the bore. The bore has a reduced width portion relative to the second opening of the bore, and the rod includes a radially enlarged portion that is wider than the reduced width portion of the bore.Type: GrantFiled: August 22, 2017Date of Patent: April 21, 2020Assignee: SAFRAN LANDING SYSTEMS UK LTDInventor: Robert Kyle Schmidt
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Patent number: 10457383Abstract: An aircraft landing gear assembly includes a structural member coupled to another part by a joint including engagement formations or a relatively high friction coating arranged such that the joint inhibits pivotal movement of the structural member when the structural member is compressively loaded in an axial manner.Type: GrantFiled: January 16, 2017Date of Patent: October 29, 2019Assignee: Safran Landing Systems UK LTDInventor: Robert Kyle Schmidt
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Patent number: 10414510Abstract: A retractable landing gear includes a main strut having an upper end that is configured to connect to aircraft primary structure and a lower end configured to connect to an axle or bogie truck. An articulated stay has a distal end configured to connect to the aircraft structure and a proximal end pivotally connected to a cardan pin member. The cardan pin member has a cylindrical portion with a first recessed annular channel. The cardan pin member is retained in the socket by a ring assembly formed by two semi-annular ring members that slidably engages the first recessed channel. The ring assembly defines a second recessed annular channel. A collar is configured to be positioned over the second recessed channel, and to contract upon a change in temperature to lockingly engage the second recessed channel, to secure the split ring assembly in the first recessed channel.Type: GrantFiled: December 30, 2016Date of Patent: September 17, 2019Assignee: SAFRAN LANDING SYSTEMS CANADA INC.Inventor: Robert Kyle Schmidt
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Patent number: 10358209Abstract: A brake rod assembly for an aircraft landing gear. The brake rod assembly includes a support member, a first brake rod having a first pivot point and a second pivot point, and a second brake rod. The support member is coupled to the first pivot point, the second brake rod is coupled to the second pivot point, and the first and second pivot points are longitudinally spaced apart along a first portion of the first brake rod.Type: GrantFiled: March 11, 2016Date of Patent: July 23, 2019Assignee: SAFRAN LANDING SYSTEMS UK LTDInventors: Matthew Sexton, Robert Kyle Schmidt, Thomas Halford
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Patent number: 10196132Abstract: An aircraft landing gear assembly having a main strut configured to move between a deployed condition and a stowed condition, a damping device to oppose movement of the main strut as it approaches the deployed condition, a retraction actuator and a mechanical retraction linkage coupled between the aircraft and the main strut, and a locking device. The locking device is operable to change the retraction linkage between a locking condition in which the retraction actuator can apply a stowing force to the main strut through the retraction linkage to move the main strut from the deployed condition to the stowed condition, and an extensible condition in which the retraction linkage permits the main strut to be deployed by way of gravity.Type: GrantFiled: August 17, 2016Date of Patent: February 5, 2019Assignee: SAFRAN LANDING SYSTEMS UK LTDInventor: Robert Kyle Schmidt
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Publication number: 20180305000Abstract: An aircraft landing gear bogie beam including first and second ends and a mounting bearing for connection to an aircraft landing gear main strut between the ends. Each end has a respective axle, and each axle defines a wheel mounting portion on each side of the bogie beam. The bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about a respective longitudinal axis of the bogie beam by an amount that is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.Type: ApplicationFiled: April 18, 2018Publication date: October 25, 2018Inventor: Robert Kyle Schmidt
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Publication number: 20180304999Abstract: An aircraft landing gear assembly having a main strut pivotally coupled to an aircraft, a bogie beam pivotally connected to the main strut, a first axle mounted at the first end of the bogie beam and arranged to carry one or more first wheel assemblies and brake assemblies, each first brake assembly being attached to the bogie beam by a brake rod, and a second axle mounted at a second end of the bogie beam and arranged to carry one or more second wheel assemblies and brake assemblies. A double acting actuator is coupled between the strut and the bogie beam to apply a compressive or tensile force to the bogie beam. The ends of the bogie beam are arranged to position the bogie pivot axis below a plane intersecting the axes of rotation of the first and second wheel assemblies when the strut is in the deployed condition.Type: ApplicationFiled: April 11, 2018Publication date: October 25, 2018Inventors: Robert Kyle Schmidt, Neil Price
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Patent number: 10100848Abstract: A hydraulic actuator having a body defining a chamber, a piston rod including an annular groove and a piston head slidably housed within the chamber, the piston head having a number of segments each of which has a base portion mounted within the annular groove.Type: GrantFiled: April 14, 2016Date of Patent: October 16, 2018Assignee: SAFRAN LANDING SYSTEMS UK LTDInventors: Robert Kyle Schmidt, Matthew Hilliard
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Patent number: 10069494Abstract: A proximity sensor for detecting non-contact detection of a target using a fiber optic strain sensor and a system for operating multiple such proximity sensors is disclosed. The proximity sensor includes an optic fiber that has an optic fiber strain sensor that is coupled to a mass that moves in response to the target. The mass can be a magnet that moves when a ferrous target is within the magnetic field of the magnet causing the magnet to move and apply strain to the optic fiber strain sensor. The optic strain sensor can include periodic variation in the refractive index of the optic fiber, such as a fiber Bragg grating. The proximity sensor can include a second fiber optic sensor that is sensitive to temperature or a second fiber optic strain sensor coupled to a second magnet that operates in opposition to the first magnet. A system coupling multiple proximity sensors can include an interrogator that has an optical power source and a detector, each coupled to a processor.Type: GrantFiled: March 8, 2013Date of Patent: September 4, 2018Assignee: Safran Landing Systems Canada Inc./Safran Systemes D'Atterrissage Canada Inc.Inventor: Robert Kyle Schmidt
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Patent number: 10024379Abstract: A hydraulic shock absorber having an inner housing portion slidably coupled to an outer housing portion to define a variable size chamber for containing shock absorber fluid. The region where the inner and outer housing portions overlap defines an annulus between adjacent surfaces of the inner and outer housing portions which varies in size in accordance with the extension state of the shock absorber. A dynamic seal is coupled to a surface of the shock absorber within the annulus for confining shock absorber fluid to the chamber. The shock absorber fluid is an electro-rheological or magneto-rheological fluid and the shock absorber includes a device for generating a magnetic or electric control field within the chamber at a region adjacent dynamic seal in order to increase the viscosity of the shock absorber fluid adjacent to the dynamic seal to inhibit passage of the shock absorber fluid beyond the dynamic seal.Type: GrantFiled: April 7, 2016Date of Patent: July 17, 2018Assignee: Safran Landing Systems UK LTDInventors: Robert Kyle Schmidt, Matthew Baxter
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Publication number: 20180186446Abstract: A retractable landing gear includes a main strut having an upper end that is configured to connect to aircraft primary structure and a lower end configured to connect to an axle or bogie truck. An articulated stay has a distal end configured to connect to the aircraft structure and a proximal end pivotally connected to a cardan pin member. The cardan pin member has a cylindrical portion with a first recessed annular channel. The cardan pin member is retained in the socket by a ring assembly formed by two semi-annular ring members that slidably engages the first recessed channel. The ring assembly defines a second recessed annular channel. A collar is configured to be positioned over the second recessed channel, and to contract upon a change in temperature to lockingly engage the second recessed channel, to secure the split ring assembly in the first recessed channel.Type: ApplicationFiled: December 30, 2016Publication date: July 5, 2018Applicant: Safran Landing Systems Canada Inc.Inventor: Robert Kyle Schmidt
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Publication number: 20180170529Abstract: An aircraft assembly having landing gear with a known deployment value, apparatus for permitting landing gear deployment, down-lock sensing apparatus, a navigation system, a landing gear control system, a flight control system, and a deployment controller. The deployment controller is configured to: calculate a touch down value using the aircraft position and speed information provided by the aircraft navigation system; command the landing gear control system to provide the deploy signal when the touch down value reaches a deployment threshold value which is greater than the landing gear deployment value; and command the flight control system to execute a landing abort sequence if the controller does not receive the down-lock signal from the landing gear sensing apparatus within a deployment value window which is greater than or equal to the known deployment value for the landing gear but less than the touch down value.Type: ApplicationFiled: December 7, 2017Publication date: June 21, 2018Inventor: Robert Kyle Schmidt
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Patent number: 10000282Abstract: An aircraft landing gear assembly includes a mechanical structural linkage having a shock absorber and a linkage abutment which are biased apart by a mechanical spring. The force required to deform the spring sufficiently to place the linkage abutment at a predefined distance with respect to the shock absorber abutment is less than the breakout force of the shock absorber.Type: GrantFiled: May 17, 2016Date of Patent: June 19, 2018Assignee: Safran Landing Systems UK LtdInventor: Robert Kyle Schmidt
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Patent number: 9919793Abstract: An aircraft landing gear assembly having a main strut and an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on a mounting pin and arranged to define a brake rod anchor point. The adaptor member is coupled to a part of the landing gear assembly so as to react brake torque and can be formed from a different material than a portion of the main strut.Type: GrantFiled: October 14, 2015Date of Patent: March 20, 2018Assignee: SAFRAN LANDING SYSTEMS UK LTDInventors: Matthew Sexton, Robert Kyle Schmidt
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Patent number: 9914532Abstract: An aircraft landing gear shock absorber having an inner housing portion slidably coupled within an outer housing portion, and a chamber which defines a sealed fluid volume for containing shock absorber fluid within the shock absorber. The chamber includes a moveable wall portion arranged to move between a first position and a second position, and in the second position the effective volume of the chamber is decreased such that the shock absorber fluid pressure increases, to provide a bump to the shock absorber.Type: GrantFiled: March 2, 2016Date of Patent: March 13, 2018Assignee: SAFRAN LANDING SYSTEMS UK LTDInventor: Robert Kyle Schmidt
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Publication number: 20180057154Abstract: An aircraft landing gear shock absorber assembly having an outer casing having a bore which extends through the outer casing. The bore has a first opening and a second opening. A rod is slidably coupled within the bore such that a first end of the rod projects out of the first opening of the bore, the first end of the rod being arranged to be attached to a wheel assembly. A closure is provided for the second opening of the bore. The bore has a reduced width portion relative to the second opening of the bore, and the rod includes a radially enlarged portion that is wider than the reduced width portion of the bore.Type: ApplicationFiled: August 22, 2017Publication date: March 1, 2018Inventor: Robert Kyle Schmidt
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Patent number: 9878780Abstract: An aircraft landing gear assembly includes a bi-stable, split line tube biased to assume a tubular condition to serve in place of a lock link or side stay and an actuator configured to radially enlarge the tube at a region for folding.Type: GrantFiled: March 17, 2016Date of Patent: January 30, 2018Assignee: Safran Landing Systems UK LTDInventor: Robert Kyle Schmidt
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Patent number: 9879701Abstract: An actuator arranged to be movable between an extended condition and a compressed condition and being biased to an intermediate condition between and distinct from the extended condition and the compressed condition. The actuator includes a damping device arranged to define the damping coefficient of the actuator.Type: GrantFiled: April 24, 2014Date of Patent: January 30, 2018Assignee: Safran Landing Systems UK LTDInventors: Christopher Green, Robert Kyle Schmidt, David Smart
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Patent number: 9862483Abstract: An aircraft landing gear assembly includes a fibre composite leaf spring arranged as a down lock spring to make the lock link.Type: GrantFiled: March 17, 2016Date of Patent: January 9, 2018Assignee: Safran Landing Systems UK LTDInventor: Robert Kyle Schmidt