A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.

An aerodynamic device includes a main aerodynamic body having a leading edge and a trailing edge, a flight control surface coupled to the main aerodynamic body near the trailing edge of the main aerodynamic body, and a rotating body coupled to the flight control surface. The rotating body is rotatable relative to the flight control surface between a stowed position and a deployed position to define a gap. The rotating body is rotated toward the main aerodynamic body while in the stowed position to close the gap. The rotating body is rotated away from the main aerodynamic body while in the deployed position to widen the gap. The gap adjusts an airflow flowing between the main aerodynamic body and the flight control surface.

A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

In an aspect a system for fly-by-wire flight control configured for use in electric aircraft including at least a sensor, wherein the sensor is communicatively connected a pilot control and configured to detect a pilot input from the pilot control and generate, as a function of the pilot input, command datum. A system includes a flight controller, the flight controller including a computing device and configured to perform a voting algorithm, wherein performing the voting algorithm includes determining that the sensor is an allowed sensor, wherein determining that the sensor is an allowed sensor includes determining that the command datum is an active datum, determining the command datum is an admissible datum, generating, as a function of the command datum and the allowed sensor, a control surface datum wherein the control surface datum is correlated to the pilot input.

A tail sitter aircraft includes a wing with a closed front section and a fuselage, from which the wing extends. The wing includes a first portion projecting from the fuselage and a second portion spaced from the first portion. The aircraft includes first and second connecting section that are interposed between the first and second portions. The fuselage extends parallel to a first axis and the first and second portions extend parallel to a second axis orthogonal to the first axis. The first axis is arranged, in use, vertically in a take-off/landing position and inclined with respect to the vertical direction in a cruising position.

This document details a series of inventions relating to the design and optimization of hybrid-to-electric aircraft. In particular, a system and method is presented to improve the effectiveness of mixed aerodynamic control surfaces which are actuated by a novel electromechanical actuator which allows the system to be tolerant to actuator faults and jams. In addition, innovations relating to integration and quick swap of large energy storage units such as batteries are disclosed, and further, an algorithm which may be used to optimize numerous aspects of the regional hybrid-to-electric aircraft known as Total Cost Door to Door or TCD2D.

A biplane flying device includes a fuselage, an upper wing, a lower wing, a first propulsion assembly and a second propulsion assembly. The upper wing is connected to one side of the fuselage. The upper wing has a first end and a second end opposite to each other. The lower wing is connected to the fuselage and opposite to the upper wing. The lower wing has a third end and a fourth end opposite to each other. The first end is opposite to the third end, and the second end is opposite to the fourth end. The first propulsion assembly is connected between the first end, the third end and the fuselage. The second propulsion assembly is connected between the second end, the fourth end and the fuselage.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

Systems, methods, and apparatus for controlling aircraft roll operations are disclosed. An example system includes a wing actuator coupled to an aileron of an aircraft, an alternate power unit (APU), a control wheel position sensor to measure a control wheel position of a control wheel of the aircraft, a flight control computer (FCC) coupled to the APU and the control wheel position sensor, the FCC to invoke the APU to provide power to the wing actuator, and transmit a control signal to the wing actuator, the control signal to invoke the wing actuator to control the aileron based on the control wheel position, and a differential linkage coupled to the wing actuator and the aileron, the differential linkage to convert first movement of the wing actuator into second movement to control the aileron, the first movement of the wing actuator based on the control wheel position.

Systems, methods, and apparatus for controlling aircraft roll operations are disclosed. An example system includes an aileron actuator including a mode selector valve to control fluid flow through the aileron actuator, and a valve spring coupled to the mode selector valve, the valve spring to adjust the mode selector valve from the active position to a block position, the block position to prevent fluid flow through the aileron actuator, a wing cable system coupled to the aileron actuator, a wing actuator coupled to the wing cable system, the wing actuator to control displacement of the aileron of the aircraft in response to the mode selector valve being in the block position, and a differential linkage coupled to the wing actuator and the aileron, the differential linkage to translate the displacement of the wing actuator into rotational movement to adjust the aileron from a first position to a second position.