Patents by Inventor James E. Cusworth

James E. Cusworth 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).

  • Patent number: 10766608
    Abstract: An aircraft landing gear structure includes a retract actuator and a shrink mechanism. The retract actuator is configured to transition a strut assembly of the aircraft landing gear structure between an extended configuration and a retracted configuration via the shrink mechanism, thereby reducing the overall longitudinal length of the strut assembly. The retract actuator is also configured to retract the aircraft landing gear into a stowage area of the aircraft during flight, via a retraction mechanism. The retraction mechanism may be a walking beam that rotates about a retraction axis to retract the aircraft landing gear structure, while simultaneously actuating the shrink mechanism, such as via a drive link coupling the retraction mechanism and the shrink mechanism. The shrink mechanism may be mechanically slaved to the retraction mechanism. The shrink mechanism may be a locking link assembly.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: September 8, 2020
    Assignee: The Boeing Company
    Inventors: Mitchell Loren Ray Mellor, James E. Cusworth
  • Publication number: 20200255129
    Abstract: A tail skid shock absorber including an outer shock absorber canister, a crushable indicator cartridge disposed within the outer shock absorber canister, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit.
    Type: Application
    Filed: April 10, 2020
    Publication date: August 13, 2020
    Inventors: James E. CUSWORTH, Michael P. HUESTED, Justin D. COTTET
  • Patent number: 10710736
    Abstract: There is provided a latch indication system for a fan cowl of an air vehicle. The system has a door movable between a closed position and an open position, and has a handle movable between a handle stowed position and a handle deployed position. The system has a linkage assembly mechanically connecting the handle to a cover assembly. The cover assembly has a movable member movable between a movable member stowed position and a movable member deployed position, such that when the door is in the closed position and the handle is in the handle stowed position, the system indicates that one or more latch assemblies of the fan cowl are in a latched condition, and when the door is in the open position and the handle is in the handle deployed position, the system indicates that one or more of the latch assemblies are in an unlatched condition.
    Type: Grant
    Filed: October 30, 2017
    Date of Patent: July 14, 2020
    Assignee: The Boeing Company
    Inventors: Michael A. Fleming, James E. Cusworth
  • Publication number: 20200198773
    Abstract: An aircraft landing gear structure according to the present disclosure includes a strut assembly and a wheel assembly operatively coupled to the strut assembly. The strut assembly includes an upper tubular housing and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing such that the overall length of the strut assembly is transitioned between an extended configuration and a retracted configuration for stowage during flight. The wheel assembly includes a forward link pivotally coupled to the upper tubular housing and a truck beam that is pivotally coupled to the lower tubular housing such that translation of the lower tubular housing with respect to the upper tubular housing causes pivoting of the forward link and the truck beam with respect to one another, thereby tilting and/or raising a wheel of the wheel assembly with respect to the upper tubular housing.
    Type: Application
    Filed: February 12, 2020
    Publication date: June 25, 2020
    Inventors: Mark Nicholas Simpson, Mitchell Loren Ray Mellor, James E. Cusworth, Justin Cottet, Richard Kevin Johnson, George Sonnenburg
  • Patent number: 10669016
    Abstract: A tail skid shock absorber including an outer shock absorber canister, a crushable indicator cartridge disposed within the outer shock absorber canister, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit.
    Type: Grant
    Filed: April 21, 2017
    Date of Patent: June 2, 2020
    Assignee: The Boeing Company
    Inventors: James E. Cusworth, Michael P. Huested, Justin D. Cottet
  • Patent number: 10669017
    Abstract: A strut assembly for an aircraft landing gear structure is transitioned between an extended configuration, corresponding to the aircraft being off the ground, and a retracted configuration, in which the strut assembly is shortened along its longitudinal axis with respect to the extended configuration, for stowage during flight. The strut assembly includes an upper bulkhead supported by an upper tubular housing, and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing. To transition the strut assembly to the retracted configuration, translation of the upper bulkhead with respect to the upper tubular housing mechanically causes translation of the lower tubular housing to a retracted position, such that the overall length of the strut assembly is reduced. The strut assembly may be an oleo strut assembly.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: June 2, 2020
    Assignee: The Boeing Company
    Inventors: Mark Nicholas Simpson, Mitchell Loren Ray Mellor, James E. Cusworth, Justin Cottet
  • Publication number: 20200115042
    Abstract: Methods of retracting a strut assembly for stowing aircraft landing gear comprise longitudinally translating an upper bulkhead within an upper tubular housing from a lower position to an upper position by pressurizing an upper bulkhead space between an upper plate of the upper bulkhead and an upper bulkhead restriction structure that is fixed to the upper tubular housing. Other methods of retracting a strut assembly for stowing aircraft landing gear comprise flowing liquid from an upper liquid chamber positioned above an upper bulkhead within an upper tubular housing to a recoil chamber, wherein during the flowing, the liquid is prevented from passing from the recoil chamber to a pressure chamber that is defined between the upper bulkhead and a lower bulkhead, thereby longitudinally translating a lower tubular housing upward.
    Type: Application
    Filed: December 13, 2019
    Publication date: April 16, 2020
    Inventors: Justin Duane Cottet, James E. Cusworth, Malcolm Scott Bryant, George Sonnenburg
  • Patent number: 10597146
    Abstract: An aircraft landing gear structure includes a strut assembly and a wheel assembly operatively coupled to the strut assembly. The strut assembly includes an upper tubular housing and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing such that the overall length of the strut assembly is transitioned between an extended configuration and a retracted configuration for stowage during flight. The wheel assembly includes a forward link pivotally coupled to the upper tubular housing and a truck beam that is pivotally coupled to the lower tubular housing such that translation of the lower tubular housing with respect to the upper tubular housing causes pivoting of the forward link and the truck beam with respect to one another, thereby tilting and/or raising a wheel of the wheel assembly with respect to the upper tubular housing.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: March 24, 2020
    Assignee: The Boeing Company
    Inventors: Mark Nicholas Simpson, Mitchell Loren Ray Mellor, James E. Cusworth, Justin Cottet, Richard Kevin Johnson, George Sonnenburg
  • Patent number: 10562614
    Abstract: An aircraft landing gear structure includes a strut assembly configured to transition between a compressed configuration, an extended configuration, and a retracted configuration. The strut assembly has a compressed length, an extended length, and a retracted length, such that the compressed length and retracted length are less than the extended length. The strut assembly includes an upper tubular housing, an upper bulkhead configured to be translated between a lower position and an upper position, a lower tubular housing operatively coupled to the upper tubular housing, a lower bulkhead supported by the lower tubular housing, and a pressure chamber defined between the lower bulkhead and the upper bulkhead. A volume of strut liquid and a mass of strut gas are positioned within the pressure chamber. A method of retracting a strut assembly includes longitudinally translating an upper bulkhead within an upper tubular housing from a lower position to an upper position.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: February 18, 2020
    Assignee: The Boeing Company
    Inventors: Justin Duane Cottet, James E. Cusworth, Malcolm Scott Bryant, George Sonnenburg
  • Publication number: 20190127075
    Abstract: There is provided a latch indication system for a fan cowl of an air vehicle. The system has a door movable between a closed position and an open position, and has a handle movable between a handle stowed position and a handle deployed position. The system has a linkage assembly mechanically connecting the handle to a cover assembly. The cover assembly has a movable member movable between a movable member stowed position and a movable member deployed position, such that when the door is in the closed position and the handle is in the handle stowed position, the system indicates that one or more latch assemblies of the fan cowl are in a latched condition, and when the door is in the open position and the handle is in the handle deployed position, the system indicates that one or more of the latch assemblies are in an unlatched condition.
    Type: Application
    Filed: October 30, 2017
    Publication date: May 2, 2019
    Inventors: Michael A. Fleming, James E. Cusworth
  • Publication number: 20180304998
    Abstract: A tail skid shock absorber including an outer shock absorber canister, a crushable indicator cartridge disposed within the outer shock absorber canister, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit.
    Type: Application
    Filed: April 21, 2017
    Publication date: October 25, 2018
    Inventors: James E. CUSWORTH, Michael P. HUESTED, Justin D. COTTET
  • Publication number: 20180244372
    Abstract: An aircraft landing gear structure according to the present disclosure includes a strut assembly and a wheel assembly operatively coupled to the strut assembly. The strut assembly includes an upper tubular housing and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing such that the overall length of the strut assembly is transitioned between an extended configuration and a retracted configuration for stowage during flight. The wheel assembly includes a forward link pivotally coupled to the upper tubular housing and a truck beam that is pivotally coupled to the lower tubular housing such that translation of the lower tubular housing with respect to the upper tubular housing causes pivoting of the forward link and the truck beam with respect to one another, thereby tilting and/or raising a wheel of the wheel assembly with respect to the upper tubular housing.
    Type: Application
    Filed: February 28, 2017
    Publication date: August 30, 2018
    Inventors: Mark Nicholas Simpson, Mitchell Loren Ray Mellor, James E. Cusworth, Justin Cottet, Richard Kevin Johnson, George Sonnenburg
  • Publication number: 20180244373
    Abstract: An aircraft landing gear structure according to the present disclosure includes a retract actuator and a shrink mechanism. The retract actuator is configured to transition a strut assembly of the aircraft landing gear structure between an extended configuration and a retracted configuration via the shrink mechanism, thereby reducing the overall longitudinal length of the strut assembly. The retract actuator is also configured to retract the aircraft landing gear into a stowage area of the aircraft during flight, via a retraction mechanism. In some examples, the retraction mechanism is a walking beam that rotates about a retraction axis to retract the aircraft landing gear structure, while simultaneously actuating the shrink mechanism, such as via a drive link coupling the retraction mechanism and the shrink mechanism. In some examples, the shrink mechanism is mechanically slaved to the retraction mechanism. The shrink mechanism is a locking link assembly in some examples.
    Type: Application
    Filed: February 28, 2017
    Publication date: August 30, 2018
    Inventors: Mitchell Loren Ray Mellor, James E. Cusworth
  • Publication number: 20180244371
    Abstract: A strut assembly for an aircraft landing gear structure according to the present disclosure is transitioned between an extended configuration, corresponding to the aircraft being off the ground, and a retracted configuration, in which the strut assembly is shortened along its longitudinal axis with respect to the extended configuration, for stowage during flight. The strut assembly includes an upper bulkhead supported by an upper tubular housing, and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing. To transition the strut assembly to the retracted configuration, translation of the upper bulkhead with respect to the upper tubular housing mechanically causes translation of the lower tubular housing to a retracted position, such that the overall length of the strut assembly is reduced. In some examples, the strut assembly is an oleo strut assembly.
    Type: Application
    Filed: February 28, 2017
    Publication date: August 30, 2018
    Inventors: Mark Nicholas Simpson, Mitchell Loren Ray Mellor, James E. Cusworth, Justin Cottet
  • Publication number: 20180079494
    Abstract: An aircraft landing gear structure includes a strut assembly configured to transition between a compressed configuration, an extended configuration, and a retracted configuration. The strut assembly has a compressed length, an extended length, and a retracted length, such that the compressed length and retracted length are less than the extended length. The strut assembly includes an upper tubular housing, an upper bulkhead configured to be translated between a lower position and an upper position, a lower tubular housing operatively coupled to the upper tubular housing, a lower bulkhead supported by the lower tubular housing, and a pressure chamber defined between the lower bulkhead and the upper bulkhead. A volume of strut liquid and a mass of strut gas are positioned within the pressure chamber. A method of retracting a strut assembly includes longitudinally translating an upper bulkhead within an upper tubular housing from a lower position to an upper position.
    Type: Application
    Filed: September 21, 2016
    Publication date: March 22, 2018
    Inventors: Justin Duane Cottet, James E. Cusworth, Malcolm Scott Bryant, George Sonnenburg