An apparatus providing continuous tilt and variable pitch for rotors on a fixed wing VTOL aircraft. An actuator on a housing rotates a first pivot point on a motor mount to tilt a motor to horizontal and vertical positions. Simultaneously, an actuator on the motor mount rotates a fork on a second pivot point on the motor mount to adjust the pitch of the rotors attached to a free end of the motor's drive shaft. A lower swash plate on the drive shaft is attached to the fork. An upper swash plate on the drive shaft is attached to the rotors. The swash plates are attached to each other with a shaft bushing attached to a shaft ball bearing. The shaft bushing allows both swash plates to move linearly along the shaft when the fork is rotated. The shaft ball bearing allows the upper swash plate to rotate with the drive shaft while the lower swash plate remains stationary.

An apparatus providing continuous tilt and variable pitch for rotors on a fixed wing VTOL aircraft. An actuator on a housing rotates a first pivot point on a motor mount to tilt a motor to horizontal and vertical positions. Simultaneously, an actuator on the motor mount rotates a fork on a second pivot point on the motor mount to adjust the pitch of the rotors attached to a free end of the motor's drive shaft. A lower swash plate on the drive shaft is attached to the fork. An upper swash plate on the drive shaft is attached to the rotors. The swash plates are attached to each other with a shaft bushing attached to a shaft ball bearing. The shaft bushing allows both swash plates to move linearly along the shaft when the fork is rotated. The shaft ball bearing allows the upper swash plate to rotate with the drive shaft while the lower swash plate remains stationary.

An improved propeller system is disclosed, including at least one resilient component configured with a mounting arrangement of a propeller of the propeller system. The resilient component is made of a resilient material that allows the propeller to tilt about a tethering axis under conditions of differential lift force on blades of the propeller under an advancing condition and a retreating condition. The resilient component includes a pair of cutouts for locating inserts made of a rigid material and positioned with a longitudinal axis of the inserts oriented in radial direction. The orientation of the inserts results in a radially oriented line contact between the propeller and the inserts to ensure that tilting of the propeller is about longitudinal axis of the inserts, defining the tethering axis of the propeller system.

An improved propeller system is disclosed, including at least one resilient component configured with a mounting arrangement of a propeller of the propeller system. The resilient component is made of a resilient material that allows the propeller to tilt about a tethering axis under conditions of differential lift force on blades of the propeller under an advancing condition and a retreating condition. The resilient component includes a pair of cutouts for locating inserts made of a rigid material and positioned with a longitudinal axis of the inserts oriented in radial direction. The orientation of the inserts results in a radially oriented line contact between the propeller and the inserts to ensure that tilting of the propeller is about longitudinal axis of the inserts, defining the tethering axis of the propeller system.

The present disclosure is directed to unmanned aerial vehicle (UAV) comprising a convertible body operably coupled to at least one sensor, and further configured to rotate at least about a longitudinal axis, thereby providing a full field of regard for the at least one sensor, and a plurality of arms extending laterally from the convertible body, each arm of the plurality of arms having a rotor assembly coupled thereto.

The present disclosure is directed to unmanned aerial vehicle (UAV) comprising a convertible body operably coupled to at least one sensor, and further configured to rotate at least about a longitudinal axis, thereby providing a full field of regard for the at least one sensor, and a plurality of arms extending laterally from the convertible body, each arm of the plurality of arms having a rotor assembly coupled thereto.

A differential thrust vectoring system includes a first thruster, a second thruster, a main actuator, and a trim actuator. The system is configured such that actuation of the main actuator causes rotation of the thrusters together about an axis, whereas actuation of the trim actuator causes relative rotation of the first and second thrusters about the axis.

An aircraft includes a fuselage having a top surface opposite a bottom surface, a front section, a center section, and a rear section. A first mounting rod and a second mounting rod are coupled to the top surface. The first mounting rod and the second mounting rod are single rods. A first and a second wing are coupled to the center section. A plurality of power generator systems are coupled to the first mounting rod or the second mounting rod. Each power generator system includes a power source, a first propeller and a second propeller. The power source is configured to drive the first propeller and the second propeller. The first propeller and the second propeller have an axis of rotation, and are pivotable between a first position and a second position. A shroud encloses the power generator system.

An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. First and second yaw vanes extend aftwardly from the fuselage. A flight control system is configured to direct the thrust vector of the coaxial rotor system and control movements of the yaw vanes. In a VTOL orientation of the aircraft, differential operation of the yaw vanes and/or differential operations of first and second rotor assemblies of the coaxial rotor system provide yaw authority for the aircraft. In a biplane orientation of the aircraft, collective operation of the yaw vanes provides yaw authority for the aircraft.

A package delivery apparatus of a vehicle may include a servo, a servo arm rotated by the servo, a latch that rotates responsive to rotation of the servo arm, and a rod and slider that moves responsive to rotation of the servo arm. The components of the package delivery apparatus may move between a plurality of positions, including a loading position, a locking position, a sensing position, and a release position. The rotation of the latch may control loading, locking, sensing, and release of a package within a package path of the vehicle, and the movement of the rod and slider may control movement of a door assembly of the vehicle between open and closed positions.