Abstract: A test apparatus includes a first grip, a second grip movable relative to the first grip, a test specimen disposed to provide a load path between the first grip and the second grip, and a test chamber disposed to both substantially envelope the test specimen and move with one of the first grip and the second grip. The test chamber does not contact the test specimen. Another test apparatus includes, a first grip, a second grip movable relative to the first grip, a test specimen disposed to provide a load path between the first grip and the second grip, a first test chamber disposed to both substantially envelope the test specimen and move with one of the first grip and the second grip, and a second test chamber disposed to both substantially envelope both the test specimen and the first test chamber.

Abstract: An exemplary ducted fan includes a duct having a central longitudinal axis, a rotor hub and stator hub extending along the central longitudinal axis, rotor blades extending from the rotor hub, each of the rotor blades operable to rotate about its own pitch-change axis, the pitch-change axes lying in a rotor plane that is generally perpendicular to the central longitudinal axis, each of the rotor blades having a rotor trailing edge and a rotor chord length, stators extending from the stator hub to an interior surface of the duct, each of the stators having a stator leading edge and a stator thickness, and a first separation between the rotor plane and the stator leading edge of not less than approximately 1.5 times the stator thickness.

Abstract: In an embodiment, an aircraft includes first and second wings. The aircraft also includes a plurality of propulsion assemblies, the plurality of propulsion assemblies including a propulsion assembly connected to each end of each of the first and second wings. The aircraft also includes first and second vertical supports disposed between the first and second wings. The aircraft also includes a storage pod disposed between the first and second vertical supports. The storage pod includes a nose portion that extends forward of the plurality of propulsion assemblies. The nose portion includes at least one radar and at least one camera. Other embodiments of this aspect include corresponding computer systems, apparatus, and computer programs recorded on one or more computer storage devices, each configured to perform the actions of the methods.

Abstract: In an embodiment, a method includes receiving flight data related to an aircraft that includes an engine installed therein. The flight data includes values of an engine parameter. The method also includes determining values of a measured installation delta for the engine based, at least in part, on the flight data. The method also includes determining values of a measured power parameter for the engine based, at least in part, on the flight data. The method also includes generating a mathematical model of a plurality of installation deltas for the engine as a function of the engine parameter, where the plurality of installation deltas include the measured installation delta and an unmeasured installation delta. The method also includes validating the mathematical model based, at least in part, on the values of the measured installation delta. The method also includes generating a performance profile of the engine.

Abstract: In an embodiment, an aircraft includes a fuselage and a first support boom extending from the fuselage and having a first boom thickness. The aircraft also includes a first propulsion assembly coupled to the first support boom. The first propulsion assembly includes a first rotor hub and first rotor blades extending from the first rotor hub and operable to rotate in a first rotor plane with the first rotor hub. The aircraft also includes a first separation between the first rotor plane and the first support boom of not less than approximately 1.5 times the first boom thickness.

Abstract: An exemplary anti-torque system for a rotorcraft includes a fan located inside of a channel that extends inside of a fuselage from an inlet proximate a forward end of the tail boom to an outlet at an aft end of the tail boom, the outlet is oriented to direct airflow from the channel onto a rudder coupled to a trailing edge of a vertical stabilizer.

Abstract: In an embodiment, an aircraft includes an airframe and a first propulsion assembly coupled to the airframe. The first propulsion assembly includes a first rotor hub and a first plurality of rotor blades non-uniformly spaced about the first rotor hub and operable to rotate in a rotor plane with the first rotor hub. The aircraft also includes a second propulsion assembly coupled to the airframe. The second propulsion assembly includes a second rotor hub and a second plurality of rotor blades non-uniformly spaced about the second rotor hub and operable to rotate in a rotor plane with the second rotor hub.

Abstract: A vehicle has a pod carrier, a pod rotatably connected to the pod carrier, and an energy attenuating system (EAS) disposed between the pod and the pod carrier to attenuate forces associated with a deflection of the pod relative to the pod carrier. A method of operating an energy attenuating system (EAS) is provided for attenuating energy associated with movement between a pod and a pod carrier. The method includes providing a vehicle having a pod carrier and providing the pod carrier with an EAS configured in an undeflected state.

Abstract: An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

Abstract: A liquid inertia vibration elimination (“LIVE”) system for a rotor system having n number of blades. The LIVE system includes a first tuned vibration reduction component configured to provide a maximum vibratory isolation at a frequency below 2*n/rev and a second tuned vibration reduction component configured to provide a maximum vibratory isolation at a frequency above 3*n/rev.

Abstract: A weighing system includes a support, a load cell mounted to the support, and a part platform suspended from the load cell to receive a part to be weighed. The load cell is operable to generate thousands of weight values for the part per second over a period of less than twenty seconds. The load cell is operable to output a weight of the part by averaging the weight values over the period of less than twenty seconds. A method of weighing the part suspended from the load cell is also disclosed.

Abstract: A cart for supporting a part to be inspected in a non-destructive testing (NDT) machine. The cart includes a base with wheels, a first support extending upright from the base, a second support extending upright from the base, and mounting fixtures being removably attachable to the first and second supports and having mounting ends engageable with the part to support the part from the first support or the second support. The base is displaceable with the wheels to enter and exit the NDT machine. The cart is lockable upon being within the NDT machine to secure the cart in position.

Abstract: A rotor system comprising a driveshaft; at least one motor for providing rotational energy for the driveshaft; an overrunning clutch connected to the motor and disposed around the driveshaft, wherein the overrunning clutch is rotated by the at least one motor; and a pump assembly associated with the at least one motor, the pump assembly comprising a large bore through which the driveshaft passes such that the pump assembly is arranged concentric to the driveshaft, the pump assembly further comprising a gerotor pump comprising inner and outer gerotor pump gears, wherein an inner bore of the gerotor pump engages and is driven by the overrunning clutch; and a cover disposed over the gerotor pump for providing a sump for the gerotor pump.

Abstract: Methods and systems for performing a validation process on a part to be process are provided. An identifier associated with the part is received. A listing of at least one automated process based on the identifier is displayed. An indication of a selected automated process from the listing is received. First instructions are transmitted to an automated process device for performing an automated processing program in accordance with the selected automated process. Processing results associated with the part are received from the automated process device. Second instructions are transmitted to a validation process device for performing a validation program in accordance with a validation process associated with the selected automated process. Validation results associated with the part are received from the validation process device. The processing results and the validation results are stored in association with the identifier.

Abstract: A flight control computer (FCC) has an index calculation component (ICC) configured to compare a reasonableness of at least a first value of a variable and a second value of the variable. A method of operating a flight control computer (FCC) includes providing an index calculation component (ICC) configured to compare a reasonableness of at least a first value of a variable and a second value of the variable.

Abstract: A reduced performance monitoring system for a tiltrotor aircraft includes a physical component of the tiltrotor aircraft configured to displace over time in response to an input, a simulation component configured to generate a simulated displacement response of the physical component, and a comparison module configured to compare a measured physical displacement response of the physical component to the simulated displacement response of the physical component.

Abstract: Embodiments are directed to a pourable foam comprising a first resin component comprising a polymeric methylene diphenyl diisocyanate, a second resin component comprising a polyol, and a barium sulfate powder component. The barium sulfate powder component is combined with the second resin component prior to combining the first and second resin components. The barium sulfate component may comprise between 1% and 50% of the pourable foam. The pourable foam may be used to repair or create aircraft components.

Abstract: A rotor system has a mast axis, a first rotor rotatable about the mast axis in a first direction and the first rotor has a first number of first rotor blades, and a second rotor rotatable about the mast axis in a second direction and the second rotor has a second number of second rotor blades that is different than the first number. The second direction is opposite the first direction.

Abstract: In an embodiment, a ducted fan assembly includes a housing that further includes a rotor. The ducted fan assembly also includes a rim that defines an opening surrounding at least a portion of the housing. The ducted fan assembly also includes a movable leading edge that is attached to the rim and extends around at least a portion of a perimeter of the ducted fan assembly, where the movable leading edge is adjustable between at least a first position and a second position.

Abstract: In an embodiment, a ducted fan assembly includes a housing that further includes a rotor. The ducted fan assembly also includes a plurality of stators that extend outward from the housing. The ducted fan assembly also includes a control vane pivotally attached to at least one of the plurality of stators. The ducted fan assembly also includes a rim that extends around at least a portion of a perimeter of the ducted fan assembly and is supported by the plurality of stators and the control vane, where the rim defines an opening surrounding at least a portion of the housing.