A guided missile with a sleeve-shaped missile body, at least one engine for producing forward thrust, at least one flight direction control device, and at least one aerodynamic extension. The least one flight direction control device is rotatably mounted to a top area and/or a bottom area of the sleeve-shaped missile body for adjusting a flight direction of the guided missile. The least one aerodynamic extension comprises an aerodynamic cross-sectional shape that is arranged on a left-hand side and/or a right-hand side of the sleeve-shaped missile body.

A foldable wing with foldable trailing edge flap, that includes a main wing and a foldable trailing edge flap. The main wing includes a wing supporting skeleton and a plurality of skin supporting ribs. The foldable trailing edge flap includes a plurality of crank-shaped flap supporting ribs, a flexible flap skin, a connecting shaft, and a return spring. The plurality of crank-shaped flap supporting ribs are hinged with lower surfaces of corresponding plurality of skin supporting ribs through the connecting shaft to form a foldable trailing edge flap supporting skeleton that relies on the plurality of skin supporting ribs. The return spring makes an upper surface of a long side of each crank-shaped flap supporting rib attach closely to a lower surface of each skin supporting rib. The flexible flap skin is attached to an upper surface of the foldable trailing edge flap supporting skeleton.

An automatic takeoff flight control system controls an aircraft to automatically follow a predetermined set of control parameters upon taking off from the ground using both longitudinal and lateral control laws. The control system provides takeoff speed reduction to thereby reduce the takeoff distance (TOD) and, as a consequence, increase the takeoff weight (TOW). The control system sets the horizontal stabilizer (HSTAB) in a non-trimmed condition—named “mistrim”; and provides beta for optimum climb at takeoff, through lateral-directional surfaces commands.

A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35° C. to 1,650° C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.

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 method of retrofitting a wing of a fixed wing aircraft is disclosed including the steps of providing an existing aircraft wing with a main fixed wing portion, and the main fixed wing portion having a tip end and an existing movable flight control surface connected adjacent the tip end. The existing movable flight control surface is then removed from the main fixed wing portion, and a wing tip device and movable flight control surface are selected as a pair to replace the existing movable flight control surface, with the selected movable flight control surface having an aerodynamic surface of different shape to the shape of the flight control surface removed from the wing. The selected wing tip device and movable flight control surface are then fitted to the main fixed wing portion.

A flow control system includes a movable wing attachable to a wing of an aircraft, and a plasma actuator mountable on a surface of the movable wing. The flow control system is configured to control air flow around the wing by having the changing of the steering angle of the movable wing work in conjunction with the operation of the plasma actuator.

A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35° C. to 1,650° C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.