A variable camber system for an aircraft wing including a wing bracket extending downward from a wing, a flap bracket pivotably coupled to the wing bracket, and a flap pivotably coupled to the flap bracket such that the flap pivots around an axis of rotation through the flap. The variable camber system is configured to adjust position of both the flap and the flap bracket relative to the wing while maintaining position of the flap relative to the flap bracket. The variable camber system is also configured to adjust position of the flap relative to the flap bracket.

A variable camber system for an aircraft wing including a wing bracket extending downward from a wing, a flap bracket pivotably coupled to the wing bracket, and a flap pivotably coupled to the flap bracket such that the flap pivots around an axis of rotation through the flap. The variable camber system is configured to adjust position of both the flap and the flap bracket relative to the wing while maintaining position of the flap relative to the flap bracket. The variable camber system is also configured to adjust position of the flap relative to the flap bracket.

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

A braking force generation device is configured to have: a first mode in which a deflector and a blocker door are retracted with respect to a wing; a second mode in which, in a state where: (i) a leading edge of the deflector is separated from the wing; (ii) a trailing edge of the deflector is at or adjacent to the wing; and (iii) the blocker door is deployed: a first flow path is formed on a lower surface side of the deflector for fluid to flow from a rear of the wing to a front of the wing via a cross flow fan from an opening on a blocker door side to a leading edge opening on a leading edge side of the deflector in the first flow path; and a third mode in which a second flow path is formed on the lower surface side of the deflector.

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

The present disclosure provides methods and system for managing gust loading in an aircraft. A deflection angle of one or more spoilers of the aircraft is monitored. When the spoiler deflection angle is above a first threshold value, one or more aileron control signals are sent to the ailerons. The aileron control signals cause the ailerons to deflect based on the spoiler deflection angle.

The present disclosure provides methods and system for managing gust loading in an aircraft. A deflection angle of one or more spoilers of the aircraft is monitored. When the spoiler deflection angle is above a first threshold value, one or more aileron control signals are sent to the ailerons. The aileron control signals cause the ailerons to deflect based on the spoiler deflection angle.

This invention discloses an aerial device (AD) for manned or unmanned flight, comprising a fuselage main body coupled with two or more aerodynamic units via bearings. Each aerodynamic unit is independently moveable and controllable, and thus able to create their own unique aerodynamic vectors, all of which are combined in varying manners to control the flight of the AD. Each unit comprises a structural part, a thruster with a propeller, and a servo wing positioned behind the propeller. More aerodynamic units may be combined with the main body in order to create more control. The units may be programmed or controlled manually to offset or otherwise account for varying environmental conditions such as slope, wind, and turbulence. The apparatus may further be coupled with a PID controller with a multidimensional field of input and output parameters.