An aircraft comprising: a fuselage, a continuous wing assembly extending from port to starboard sides of the aircraft, the wing assembly comprising a flexible wing body, at least one wing actuator (60, 80) connected to the wing assembly and adapted to flex the wing sufficiently to control the aircraft, a fuselage joint connecting the fuselage to the wing assembly, wherein the fuselage joint permits the fuselage to move independently of the wing assembly, the aircraft further comprising a fuselage actuator (130,150,170) connecting the fuselage and wing assembly to pivot the fuselage relative to the wing assembly, at least one sensor (202, 232) mountable to the aircraft and configured to acquire data from one or more of a portion of the aircraft and an environment of the aircraft, preferably, the at least one sensor (202, 232) acquires one or more of position data, inertial movement, ambient temperature, humidity, speed, and direction, and the at least one sensor (202, 232) is mounted on one or more of the wing, or on the fuselage of the aircraft, and a control system adapted to actuate the wing (60, 80) and fuselage (130, 150, 170) actuators in response to signals from the at least one sensor (202, 232) whereby the aircraft is controlled by a combination of wing flexure and fuselage rotation relative to the wing assembly in response to signals from the at least one sensor (202, 232), preferably, the fuselage joint is configured to permit the fuselage to rotate about at least two mutually orthogonal axes of rotation relative to the wing assembly or the fuselage joint is configured to permit rotatable movement of the fuselage about a first horizontal axis for permitting roll of the fuselage relative to the wing assembly and a second horizontal axis orthogonal to the first axis for adjusting pitch of the fuselage relative to the wing assembly; and the control system is adapted to accept and store programmed flight information and aircraft control instructions. a fuselage, a continuous wing assembly extending from port to starboard sides of the aircraft, the wing assembly comprising a flexible wing body, at least one wing actuator (60, 80) connected to the wing assembly and adapted to flex the wing sufficiently to control the aircraft, a fuselage joint connecting the fuselage to the wing assembly, wherein the fuselage joint permits the fuselage to move independently of the wing assembly, the aircraft further comprising a fuselage actuator (130,150,170) connecting the fuselage and wing assembly to pivot the fuselage relative to the wing assembly, at least one sensor (202, 232) mountable to the aircraft and configured to acquire data from one or more of a portion of the aircraft and an environment of the aircraft, preferably, the at least one sensor (202, 232) acquires one or more of position data, inertial movement, ambient temperature, humidity, speed, and direction, and the at least one sensor (202, 232) is mounted on one or more of the wing, or on the fuselage of the aircraft, and a control system adapted to actuate the wing (60, 80) and fuselage (130, 150, 170) actuators in response to signals from the at least one sensor (202, 232) whereby the aircraft is controlled by a combination of wing flexure and fuselage rotation relative to the wing assembly in response to signals from the at least one sensor (202, 232), preferably, the fuselage joint is configured to permit the fuselage to rotate about at least two mutually orthogonal axes of rotation relative to the wing assembly or the fuselage joint is configured to permit rotatable movement of the fuselage about a first horizontal axis for permitting roll of the fuselage relative to the wing assembly and a second horizontal axis orthogonal to the first axis for adjusting pitch of the fuselage relative to the wing assembly; and the control system is adapted to accept and store programmed flight information and aircraft control instructions.