Systems and methods of improving the operation of an aircraft during flight are disclosed. In one embodiment, the method comprises deploying spoilers as the speed of the aircraft approaches the maximum operating Mach number of the aircraft, and keeping the spoilers deployed when the speed of the aircraft is substantially at the maximum operating Mach number.

An airfoil assembly comprising an airplane wing, a spoiler, and a flap for unmanned and high endurance aircraft. The spoiler is located on an upper surface of the airplane wing while the flap is located on a lower surface of the airplane wing. The spoiler and the flap can occupy at least one-third, and up to three-quarters, the chord span of the airplane wing. The spoiler and the flap are both capable of moving upwards and downwards with respect to the airplane wing through their respective frames.

An aircraft wing with a wing structure and a spoiler movable between a stowed configuration and a deployed configuration are disclosed. The spoiler includes an actuator configurable between an engaged mode and a disengaged mode. When the actuator is in the engaged mode, the actuator can restrict movement of the spoiler and move the spoiler between the stowed configuration and deployed configuration. In the disengaged mode, the actuator allows free movement of the spoiler, such that the spoiler may pop up due to reduced air pressure on the aircraft wing.

A spoiler for an aircraft wing is movable between a stowed configuration and a deployed configuration in a “pop-up” manner. The spoiler includes a hinged top flap movable between a first position and a second position, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator. When the hinged top flap is in the second position, airflow over the top surface of the aircraft wing acts to pull the spoiler into the deployed position.

Disclosed herein are aspects of a hybrid unmanned aerial vehicle (UAV). In one embodiment, the hybrid UAV includes a fuselage configured to hold cargo, and at least one wing. The wing has a body that includes upper and lower surfaces and is configured to generate lift to enable the UAV to glide through the air. At least one rotor assembly is held within the body of the wing between the upper and lower surfaces of the wing. The upper and lower surfaces of the wing include upper and lower doors, respectively, extending above and below, respectively, the rotor assembly. The upper and lower doors are configured to be opened during gliding of the UAV to an open position that exposes the rotor assembly such that the rotor assembly is configured to draw air through the body of the wing and thereby generate lift.

Systems and methods of improving the operation of an aircraft during flight are disclosed. In one embodiment, the method comprises deploying spoilers as the speed of the aircraft approaches the maximum operating Mach number of the aircraft, and keeping the spoilers deployed when the speed of the aircraft is substantially at the maximum operating Mach number.

A system for detecting and controlling the position of a spoiler of an aircraft wing is described herein comprising: a hydraulic actuator having a piston rod operably connected to the spoiler, the piston rod being moveable between a retracted position, a neutral position and an extended position; and means for providing power to said hydraulic actuator; and a mechanical device for detecting whether the piston rod is in the retracted position, the neutral position or the extended position; and means, operatively connected to the mechanical device, that is configured to provide a change in a load applied to said hydraulic actuator, wherein said means is configured to change said load based on whether said piston rod is detected as being in said retracted position or said extended position.

A seal is provided. The seal includes a seal panel having lateral sides. The seal also includes a seal locking mechanism coupled to the seal panel. The seal locking mechanism is configured to resiliently move, under impetus of an actuator, between an unbowed position of the seal locking mechanism and a bowed position of the seal locking mechanism.

An aircraft wing with a wing structure and a spoiler movable between a stowed configuration and a deployed configuration are disclosed. The spoiler includes an actuator configurable between an engaged mode and a disengaged mode. When the actuator is in the engaged mode, the actuator can restrict movement of the spoiler and move the spoiler between the stowed configuration and deployed configuration. In the disengaged mode, the actuator allows free movement of the spoiler, such that the spoiler may pop up due to reduced air pressure on the aircraft wing.

Methods and apparatus for automatically extending aircraft wing flaps in response to detecting an excess energy steep descent condition are described. An example control system of an aircraft includes one or more processors. The one or more processors determine whether the aircraft is experiencing an excess energy steep descent (EESD) condition. In response to determining that the aircraft is experiencing the EESD condition, the one or more processors command an actuator of the aircraft coupled to a flap of the aircraft to extend the flap from a current flap position to a subsequent flap position defined by a flap extension sequence.