Abstract: A multimode clutch assembly is positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling unit having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly shifts the bypass assembly between engaged and disengaged positions. An engagement status sensor is configured to determine the engagement status of the bypass assembly. In the disengaged position, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.

Abstract: A failsafe multimode clutch assembly positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly uses pressurized lubricating oil to shift the bypass assembly between the engaged position and a disengaged position. A lock assembly enables and disables actuation of the bypass assembly. In the disengaged position, the overrunning mode of the freewheeling unit enables a unidirectional torque transfer mode of the clutch assembly. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.

Abstract: A side-by-side off-road utility vehicle comprising a vehicle operational status switch for controlling the operational status of the vehicle, a side-by-side seating structure, a plurality of safety restraint devices operable to retain one or more vehicle passenger in the side-by-side seating structure, and a prime mover RPM controller. The prime mover RPM controller operable to output commands to the one or more prime mover of the vehicle to limit a rotational speed of the prime mover(s) when the vehicle is in an On operational status and a selected one or more of the one or more safety restraints is in a disengaged status.

Abstract: Automatic low-speed aircraft maneuver wind compensation is implemented by an aircraft flight control system flight control computer (FCC) configured to receive or retrieve steady wind data and retrieve groundspeed data for the aircraft. The FCC computes two-dimensional relative horizontal airspeed (i.e., horizontal relative to the surface of the earth) for the aircraft, using the steady wind data and the groundspeed data for the aircraft, and computes relative changes in trim controls of the aircraft using the two-dimensional relative horizontal airspeed of the aircraft. The resulting relative changes in controls of the aircraft due to relative horizontal airspeed changes are applied to flight element control actuators.

Abstract: A rotor system includes a rotor assembly and a duct system. The rotor assembly includes rotor blades extending from a mast axis and configured to rotate about the mast axis. The duct assembly includes a moveable duct portion and a stationary duct portion. In a first duct configuration, the moveable duct portion surrounds a first portion of the rotor assembly, the stationary duct portion surrounds a second portion of the rotor assembly, and the moveable duct portion and the stationary duct portion enclose the rotor assembly. In a second duct configuration, the stationary duct portion surrounds the second portion of the rotor assembly, and the moveable duct portion is moved away from the first portion of the rotor assembly, such that the rotor assembly is not enclosed.

Abstract: Embodiments are directed to solid lubricant assemblies for providing over temperature protection for bearings and gears in rotorcraft systems. A solid lubricant enters a fluid state above a certain temperature and is positioned so that fluid lubricant is applied to the bearings or gears.

Abstract: An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

Abstract: A blade-pitch change mechanism includes a motor comprising a rotating motor shaft and a housing, a solenoid coupled to a first end of the rotating motor shaft and to the housing, and a hub coupled with a second end of the rotating motor shaft. The hub includes a cylindrical puck having formed therein a gated castellated groove and connected to the second end of the rotating motor shaft and a cylindrical blade-pitch hub selectively couplable with the cylindrical puck via a plurality of drive pins and having formed therein a blade-pitch adjustment groove.

Abstract: A tailsitter aircraft includes an airframe having first and second wings with first and second pylons extending therebetween, a thrust array attached to the airframe, payloads and payload saddle assemblies coupled to the pylons each configured to secure a respective payload. The thrust array includes propulsion assemblies configured to transition the airframe between a forward flight orientation for wing-borne lift and a VTOL orientation for thrust-borne lift. Each payload saddle assembly includes a latch assembly and a retainer configured to secure the respective payload against a respective pylon. A latch assembly is movable between various positions including an open position and a closed position and is configured to secure the respective payload in the closed position and release the respective payload in the open position. Each latch assembly is configured to move from the closed position to the open position to release the respective payload in the VTOL orientation.

Abstract: A battery system is described with methods and systems for thermally isolating a battery module experiencing thermal runaway. In one embodiment, a thermal actuator can cut a busbar coupling neighboring battery modules together, thereby preventing or slowing the spread of thermal runaway. In other embodiments, a fusible material can joint portions of a busbar. High temperatures can cause the fusible material to melt off of the busbar portions and thereby break the thermal or electrical conductivity between busbar portions and neighboring modules.

Abstract: In an embodiment, an apparatus includes: a gearbox including: a housing having an opening; an input pinion disposed in the housing; a moving feature mechanically coupled to the input pinion, the moving feature and the input pinion being operable to convert between power and torque; and first sensors disposed on the moving feature, the first sensors having batteries, where the moving feature is operable to rotate about a common axis, each of the first sensors being exposed by the opening as the moving feature rotates about the common axis.

Abstract: Techniques involve an air flow assembly to provide pressurized air, e.g., for use by an air-cushion vehicle (ACV) or other craft. The air flow assembly includes a volute having a central chamber, a lift duct, and a thruster duct. The air flow assembly further includes a set of guide members disposed between the central chamber and the thruster duct, and linkage coupled to the set of guide members. The linkage is constructed and arranged to transition the set of guide members between a closed configuration in which the set of guide members closes an opening between the central chamber and the thruster duct, and an opened configuration in which the set of guide members opens the opening between the central chamber and the thruster duct.

Abstract: Embodiments are directed to an aircraft fuselage comprises two keel beams and two roof beams. Each keel beam is formed as a single component having no joints. Each keel beam comprises a first portion that is configured to define a floor of an aircraft and a second portion that is configured to define a tail section of an aircraft. The second portion is positioned at an angle relative to the first portion. Each roof beam is coupled to the second portion of a corresponding keel beam at a point remote from the first portion. Each roof beam and a corresponding keel beam are positioned along a single butt line relative to an aircraft fuselage centerline. Frame members are coupled to both keel beams and both roof beams.

Abstract: A laminated elastomeric journal bearing has an outer sleeve having an inner surface, at least a portion of each end of the inner surface being a concave surface of revolution, and an inner sleeve having an outer surface, at least a portion of each end of the outer surface being a convex surface of revolution. Alternating layers of elastomer and metal are located between the sleeves, with adjacent surfaces of the layers and the sleeves being adhered to each other.

Abstract: A folding step system includes a housing forming an interior space and a step comprising a step surface. The step is movable between a stowed configuration in which substantially all of the step surface is disposed within the interior space and a deployed configuration in which at least a portion of the step surface is disposed outside of the interior space and at least a portion of the step surface is disposed within the interior space.

Abstract: An aircraft includes a fuselage having a former therein and a work platform system. The work platform system includes a platform that is moveable between a stowed configuration and a deployed configuration. The work platform system also has a hinge pin received by the platform. A platform stop is carried by the former and configured to inhibit rotation of the platform about the hinge pin when the platform is in the deployed configuration. The hinge pin is carried by the former.

Abstract: A telescoping tail assembly for use on an aircraft having a fore-aft length. The telescoping tail assembly includes a housing extending in an aftward direction, a tailboom slidable along the housing into various positions including an extended position and a retracted position and one or more control surfaces coupled to the tailboom. The tailboom increases the fore-aft length of the aircraft in the extended position and decreases the fore-aft length of the aircraft in the retracted position.

Abstract: A pitch change link may include a shaft having a first end region and a second end region, and a bearing cartridge on at least one of the first end region and the second end region. The bearing cartridge may include a bearing and a bearing ring at least partially surrounding the bearing. The bearing ring may have a geometric symmetry and a cross section that is wider at a first end than at a second end, the first end may oppose the second end.

Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.