A vehicle is described having an aerodynamically contoured lifting body comprising a plurality of cooperating body modules, wherein at least two of the modules are displaceably secured to each other. The modules include a thrust vectoring module operatively coupled to a propulsive mechanism. The thrust vectoring module is dynamically controlled to affect positioning and actuation of the propulsive mechanism to attain a desired positioning of the vehicle and at least one of a plurality of modes of operation thereof. The thrust vectoring module includes a nacelle module carrying the propulsive mechanism thereon and rotatably displaceable about one or more axes extending from the lifting body. The propulsive mechanism is positioned externally, internally, or in combinations thereof of the nacelle module and is tiltably displaceable about one or more axes of the nacelle module.

A rotorcraft is described and includes an inertial measurement unit (IMU) sensor mounted to the rotorcraft, the IMU sensor oriented relative to the rotorcraft such that a roll attitude of the rotorcraft occurs about a Z-axis and has a range of 90 degrees, a pitch attitude of the rotorcraft occurs about an X-axis and has a range of 180 degrees, and a yaw attitude of the rotorcraft occurs about a Y-axis and has a range of 180 degrees.

A method of reducing noise generated by a tilt-rotor aircraft includes transitioning the tilt-rotor aircraft into an airplane mode from a helicopter mode, and reducing a speed of a first pair of fans of the tilt-rotor aircraft to be less than a speed of a second pair of fans that are positioned in-line with the first pair of fans. A flight control system configured to reduce a noise level of a tilt-rotor aircraft includes a flight control computer comprising a processor, a propulsion system communicatively coupled to the flight control computer, a first pair of fans and a second pair of fans communicatively coupled with the flight control computer and the propulsion system. The processor is operable to implement a method that includes transitioning the tilt-rotor aircraft into an airplane mode from a helicopter mode, and reducing a speed of the first pair of fans to be less than a speed of the second pair of fans that are positioned in-line with the first pair of fans.

An unmanned aerial signal relay includes an unmanned aerial vehicle, including a communication relay unit and at least one antenna, communicatively connected to the communication relay unit; a tether comprising at least two wires and at least one fiber optic cable, the wires and cable communicatively connected to the unmanned aerial vehicle; and a surface support system comprising a spool physically connected to the tether and a ground-based receiver communicatively connected to the at least one fiber optic cable, wherein the unmanned aerial vehicle is powered by electrical energy provided by the at least two wires, and wherein the communication relay unit is configured to relay signals received from the at least one antenna via the fiber optic cable to the ground-based receiver. Various systems and methods related to an unmanned aerial signal relay are also described.

A system for altitude control of an autogyro includes an unpowered rotor for generating lift and a forward propulsion system for generating a horizontal thrust component of a thrust vector for propelling the autogyro forward during flight. The system for altitude control also includes at least one thrust steering control devices configured to steer thrust generated by the forward propulsion system such that the forward propulsion system generates a vertical thrust component of the thrust vector.

A differential thrust vectoring system including a first thruster rotation assembly configured to rotate a first thruster relative of an aircraft, a second thruster rotation assembly configured to rotate a second thruster of an aircraft, and an actuator. The system is configured such that actuation of the actuator causes disparate rotation about the tilt axis of the first and second thrusters.

Aircraft are configured to facilitate propeller blade pitch adjustability. According to one example, an aircraft can include a plurality of propellers, where each propeller includes plurality of blades. At least one pitch adjust mechanism may be associated with at least on propeller, where the pitch adjust mechanism is configured to adjust a pitch of the plurality of blades for at least one propeller in response to airflow from at least one other propeller influencing an airflow at the at least one propeller. Other aspects, embodiments, and features are also included.

A vectored thrust control module for an aircraft that includes a servo system that couples to the aircraft structure at an output shaft connection point. A thrust motor assembly is fully supported by the servo system and rotates a bladed component to provide thrust to the aircraft. Further, the thrust motor assembly is rigidly connected with the servo system to rotate together about a longitudinal axis thrust line with respect to the aircraft structure. The bladed component and the thrust motor assembly generate a line of thrust that extends through the connection point of the servo system to the aircraft structure.

Unmanned aerial vehicles (UAVs) which fly to destinations (e.g., for delivering items) may land on transportation vehicles (e.g., delivery trucks, etc.) for temporary transport. An agreement with the owner of the transportation vehicles (e.g., a shipping carrier) may be made, and the associated transportation vehicles that are available for landings may be identified by markers on the roof or other identification techniques. Different types of communications may be provided as part of a landing process (e.g., a notification regarding a proposed landing may be sent including a request for a confirmation that the proposed landing is acceptable, etc.). The routes of the transportation vehicles may be known and utilized to determine locations where UAVs will land on and take off from the transportation vehicles.

The battery thermal management system includes a battery pack, a circulation subsystem, and a heat exchanger. The system can optionally include a cooling system, a reservoir, a de-ionization filter, a battery charger, and a controller.