Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude motors is disposed in each cavity of the plurality of cavities.

Abstract: A handheld device and method for entering data and controlling functions of an aerial vehicle are disclosed. The handheld device includes an interface that communicates with a processor and a memory of the aerial vehicle; input devices that receive input from an operator of the handheld device, a display device that displays information related to the input received from the operator via the input devices, and one or more processors. The one or more processors can receive input data from the input devices to modify a field value maintained in the memory of the aerial vehicle. The one or more processors can present, at the display device, an output data corresponding to the input data, and periodically transmit one or more signals to modify the field value maintained in the memory of the aerial vehicle via the interface based on the input data.

Abstract: A drain assembly includes a drain tube and a flapper assembly. The drain tube extends between a first tube end and a second tube end. The first tube end is configured to fluidly attach to an inlet plenum assembly of an engine system of a rotorcraft. The flapper assembly is positioned along the second tube end and comprises a flapper door that is configured to allow fluid to drain from the drain assembly to an engine compartment of the engine system of the rotorcraft. The flapper door is configured to prevent fluid, engine compartment gases, or flame from flowing into the drain assembly through the second tube end of the drain tube.

Abstract: Flow batteries can include a first half-cell containing a first aqueous electrolyte solution. a second half-cell containing a second aqueous electrolyte solution, and a separator disposed between the first half-cell and the second half-cell. The first aqueous electrolyte solution contains a first redox-active material, and the second aqueous electrolyte solution contains a second redox-active material. At least one of the first redox-active material and the second redox-active material is a nitroxide compound or a salt thereof. Particular nitroxide compounds can include a doubly bonded oxygen contained in a ring bearing the nitroxide group, a doubly bonded oxygen appended to a ring bearing the nitroxide group, sulfate or phosphate groups appended to a ring bearing the nitroxide group, various heterocyclic rings bearing the nitroxide group, or acyclic nitroxide compounds.

Abstract: A rotor blade assembly for a rotary wing aircraft includes a main rotor blade body comprising an upper blade skin, a lower blade skin, an inboard end, an outboard end, and a trailing edge. The rotor blade assembly further includes a trailing edge actuator assembly. The trailing edge actuator assembly includes an upper actuator skin and a lower actuator skin defining a cavity and a trailing edge flap, a control panel disposed in the cavity and coupled to one of the upper actuator skin or the lower actuator skin and one or more actuators disposed in the cavity and configured to apply force to the control panel to cause the trailing edge flap to deflect. The trailing edge actuator assembly is coupled to the trailing edge of the main rotor blade body.

Abstract: The embodiments relate to systems and methods for wavefront error (WFE) correction of a conformal optical component using a planar lens. The embodiments include a conformal optical component transmissive to electromagnetic radiation (EMR), which is propagated through the conformal optical component along a path axis. The conformal optical component is rotationally asymmetric about the path axis. A planar corrector lens is configured to correct a WFE of the conformal optical component. The planar corrector lens defines a lens axis. Accordingly, use of a single planar corrector lens for WFE correction of a conformal optical component reduces bulk and manufacturing complexity.

Abstract: A vibration control assembly includes a housing having an interior region and an inner mass including a cage disposed within the interior region of the housing and being rotatable within the housing about a first axis and a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis. At least one driving source includes a stator and is operable to interact with a magnetic field of the inner mass to drive rotation of the inner mass about at least one of the first axis and the second axis, wherein the at least one driving source is mounted within the interior region of the housing.

Abstract: Provided herein are various improvements to optical-inertial stabilization systems, such as those employed on electro-optical systems that receive or emit optical energy. In one example, a system includes an optical reference element rigidly coupled to a primary mirror. The optical reference element propagates a reference signal through optic elements that form at least a portion of an optical path corresponding to the primary mirror. A measurement of the reference signal is made after propagation through the optic elements to determine errors associated with the optical path. The system can also include inertial sensors rigidly coupled to the primary mirror and optical reference element to form an assembly. The inertial sensors are configured to measure inertial rotation of the assembly. Rotational adjustments about two axes can be produced for the assembly based at least on the inertial rotation properties to correct for disturbance or drift.

Abstract: Systems, methods, and software described herein provide enhancements for the deployment and management of sensor resources across spaceborne, airborne, and ground-based physical nodes. In one implementation, a method includes collecting sensor data from physical sensors distributed over a geographic region, and establishing logical sensors based at least on requirements indicated by data requestors. The method includes allocating selected portions of the sensor data to the logical sensors to form composite sensor data based on locations monitored by the physical sensors that correspond to the requirements, and providing the composite data in one or more data streams to the data requestors as originating from the logical sensors.

Abstract: An actuation system for an aircraft can include an actuator and a plurality of clutches connected to and structured to be moved by the actuator. The actuation system can include a plurality of control levers connected to the plurality of clutches and structured to be moved by the plurality of clutches when the plurality of clutches are moved by the actuator. The actuation system can include a processor connected to the actuator and to the plurality of clutches. The processor can identify one or more clutches connected to one or more control levers of the plurality of control levers for controlling an operation of the aircraft, and cause the one or more clutches connected to the one or more control levers to be in an engaged stat. The processor can activate the actuator to cause movement of the one or more control levers via the one or more clutches.

Abstract: A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member. The at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.

Abstract: A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.

Abstract: A rotor blade assembly for a rotary wing aircraft includes a main rotor blade body comprising an upper blade skin, a lower blade skin, an inboard end, an outboard end, and a trailing edge. The rotor blade assembly further includes a trailing edge actuator assembly. The trailing edge actuator assembly includes an upper actuator skin and a lower actuator skin defining a cavity and a trailing edge flap, a control panel disposed in the cavity and coupled to one of the upper actuator skin or the lower actuator skin and one or more actuators disposed in the cavity and configured to apply force to the control panel to cause the trailing edge flap to deflect. The trailing edge actuator assembly is coupled to the trailing edge of the main rotor blade body.

Abstract: A clip to facilitate a coupling of an object to a suction cup includes a body having a first surface and a second surface disposed opposite to the first surface. The body defines an opening extending from the first surface to the second surface. The clip also includes a tongue adapted to engage with the suction cup and extending inside the opening from the body. The tongue includes a first end attached to the body and a second end arranged at a gap from the body.

Abstract: A rotatable swashplate is rotatable relative to a stationary swashplate around a shaft and connects to a pitch control rod assembly. The rotatable swashplate includes an upper portion and a lower portion. The upper portion is extendable outside of a stationary swashplate and includes a plurality of lugs each configured to attach to a pitch control rod assembly, an innermost wall configured to receive a shaft, and a membrane. The lower portion is positionable within the stationary swashplate and has an outermost wall and at least one extension extending radially between the outermost wall and the innermost wall. The membrane extends radially over the at least one extension.

Abstract: An apparatus for securing first and second skins to a core in a composite rotor blade includes an elongated member configured to be installed through a passage in the core of the composite rotor blade. The elongated member has a first end configured to be attached to an outer surface of the first skin and a second end configured to be attached to an outer surface of the second skin. The apparatus also includes a first patch configured to adhere the first end to the outer surface of the first skin, and a second patch configured to adhere the second end to the outer surface of the second skin such the elongated member extends from the outer surfaces of the first and second skins through the passage in the core.

Abstract: An additive friction stir deposition system for refractory metals is disclosed herein. The additive friction stir deposition system includes a tool assembly and an induction element. The tool assembly includes a metal shaft defining a shaft central channel, and a ceramic tip defining a tip central channel. The metal shaft and the ceramic tip are configured to interlock to prevent relative rotation therebetween. The induction element is positioned adjacent to the ceramic tip. As a refractory metal feedstock is fed through the shaft central channel and the tip central channel, the induction element heats the portion of the refractory metal feedstock within the tip central channel, but does not heat the ceramic tip itself. Accordingly, the refractory metal feedstock can be heated prior to application to a workpiece without heating the tip of the tool assembly, improving performance of the additive friction stir deposition system and the resulting workpiece.

Abstract: A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.

Abstract: According to an aspect, an ejector member includes an annular member; a vent arranged at the annular member, the vent having an inlet at a first surface of the annular member, the vent further having an outlet arranged radially inward from a second surface of the annular member; and a vane extending radially inward from the second surface of the annular member.