Stratford, CT, United States
Stratford, CT, United States

The Sikorsky Aircraft Corporation is an American aircraft manufacturer based in Stratford, Connecticut. It was established by Igor Sikorsky in 1925. Its parent company is United Technologies Corporation. Wikipedia.


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Patent
Sikorsky Aircraft | Date: 2017-05-17

Embodiments of the invention include a vehicle including an engine and a rotor including a plurality of rotor blades in a path of exhaust from the engine. The vehicle includes a rotor control assembly configured to connect the rotor to a rotation force source to rotate the rotor and configured to rotate the rotor at a prescribed minimum rotation rate greater than zero based on at least one of disengaging the rotor from the rotation force source and receiving a control signal to disengage the rotor from the rotation force source. The rotor control assembly is designed to rotate the rotor at the prescribed minimum rotation rate based on at least one system attribute of the vehicle that is affected by a rotation rate of the rotor.


Patent
Sikorsky Aircraft | Date: 2017-02-08

A method of electrical system fault detection and location determination includes measuring a baseline time domain reflectometry (TDR) waveform along a wire path of the electrical system and obtaining an operating TDR waveform along the wire path. The operating TDR waveform is compared to the baseline TDR waveform to derive a difference TDR waveform, and a difference energy is calculated utilizing the difference TDR waveform. The difference energy is monitored over time for peaks in the difference energy and potential electrical system faults are identified via the peaks in the difference energy.


Patent
Sikorsky Aircraft | Date: 2017-03-15

A flexible fuel bladder assembly for an aircraft includes a flexible fuel bladder positioned at an airframe and having an opening to allow a flow of fuel into and/or out of the fuel bladder. A breakaway valve is operably connected to the fuel bladder at the opening to control a flow of fuel therethrough. A non-contacting or loose fitting reaction feature is affixed to the airframe and is interactive with the breakaway valve such that movement of the breakaway valve relative to the reaction feature results in breakage of a valve body of the breakaway valve and closure of the breakaway valve to prevent flow of fuel therethrough while also allowing for a second reaction mode to cause breakage of a valve body should the connecting hose be pulled relative to the breakaway valve.


Patent
Sikorsky Aircraft | Date: 2017-05-17

An aircraft comprising an airframe; a rotor system mounted to the airframe, the rotor system including a plurality of rotor blades, each of the plurality of rotor blades including a root portion extending to a tip portion through an airfoil portion, the airfoil portion having a leading edge and a trailing edge; at least one control surface mounted within the airfoil portion of at least one of the plurality of rotor blades; at least one actuator configured to actuate the at least one control surface; and at least one actuator configured to pitch at least one of the plurality of rotor blades about a blade pitch axis


Patent
Sikorsky Aircraft | Date: 2017-05-24

A method of kinematic motion planning includes accessing a list of a plurality of nodes (108) defining a plurality of potential kinematic path locations between a starting position (110) and an ending position (118) of a vehicle (200). A plurality of constraint sets (114) is determined that apply one or more vehicle motion constraints based on a plurality of spatial regions (118) defined between the starting position (110) and the ending position (118). The constraint sets (114) are applied in determining a plurality of connections (116) between the nodes (108) to form a kinematic motion path (120) based on locations of the nodes (108) relative to the spatial regions (118). The kinematic motion path (120) is output to a dynamic path planner (104) to complete creation of a motion path plan (122) for the vehicle (200).


Patent
Sikorsky Aircraft | Date: 2017-01-11

Embodiments are directed to obtaining at least one sample of load or load path data from at least one piezoelectric sensor associated with a structure, comparing the at least one sample of data to at least one prior sample of data obtained from the at least one sensor, and providing a status of a health of the structure based on the comparison.


Patent
Sikorsky Aircraft | Date: 2017-03-15

One aspect is a structural fault estimation system for a rotor system. The structural fault estimation system includes a plurality of sensors operable to provide a plurality of measured rotor loads and motion of the rotor system. A rotor loads and motion estimator is operable to produce a plurality of estimated rotor loads and motion for the rotor system. A rotor fault estimator is operable to determine residual rotor loads and motion as a difference between the measured rotor loads and motion and the estimated rotor loads and motion, and estimate fault magnitudes for the rotor system using least squares relative to fault models and the residual rotor loads and motion. The structural fault estimation system can perform structural fault estimation in real-time on an aircraft while in operation.


Patent
Sikorsky Aircraft | Date: 2017-02-08

A method of drive system diagnostics of an aircraft includes capturing high load drivetrain component vibration data at select steady-state and/or high-load transient operating conditions of the aircraft and processing the captured vibration data to improve reliability and/or accuracy of the captured vibration data. The processed vibration data is utilized to provide a health assessment of the drivetrain components and achieve earlier detection of incipient faults. A health monitoring system for drivetrain components of an aircraft includes a plurality of vibration sensors positioned at drivetrain components of an aircraft to capture drivetrain component vibration data at transient operating conditions of the aircraft. One or more processing modules process the captured vibration data to improve reliability and/or accuracy of the captured data, and a fault reasoning module calculates a health indicator of the drivetrain components.


Patent
Sikorsky Aircraft | Date: 2017-02-08

One aspect is a flight control system for a rotary wing aircraft including a main rotor system and an elevator control system. A flight control computer of the flight control system includes processing circuitry configured to execute control logic. The control logic includes an inverse plant model that produces a main rotor feed forward command based on a pitch rate command, and a load alleviation control filter configured to reduce loads on a main rotor system and produce an elevator command for an elevator control system. A transformed elevator command filter produces a main rotor pitch adjustment command based on the elevator command, and a main rotor command generator generates an augmented main rotor feed forward command for the main rotor system based on the main rotor feed forward command and the main rotor pitch adjustment command.


Patent
Sikorsky Aircraft | Date: 2017-05-31

A method of monitoring usage to determine accumulated component fatigue damage includes evaluating available data for calculating an accumulated component fatigue damage for a component over a pre-determined time frame. The method includes determining at least one available method for calculating the accumulated component fatigue damage based on the available data. The method includes determining the accumulated component fatigue damage for the component using the at least one available method.

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