Abstract: An elongate cylindrical projectile including processing circuitry, a head assembly, a tail section assembly, a mid body section positioned between the head assembly and tail assembly, and a wing assembly, the wing assembly including a deployable wing which is stored in a closed position entirely within the mid body section and is deployed, using an actuator, to outside the mid body section in an open position in response to a command from the processing circuitry.

Abstract: A detection device comprising a first data processing unit configured to determine a first trend of the control surface control order as a function of time, the first trend being defined according to a reference parameter, a second data processing unit configured to determine at least one second trend of the control surface position value as a function of time, the second trend being also defined according to the reference parameter, and a monitoring unit configured to compare the first and second trends in order to verify the existence of a correlation between these first and second trends so as to detect an oscillatory failure as soon as a loss of correlation between the first and second trends appears, if necessary.

Abstract: An aircraft for vertical take-off and landing. The aircraft comprises a first wing, a second wing and a fuselage. The first wing comprises a first longitudinal wing axis and the second wing comprises a second longitudinal wing axis. The first wing extends along the first longitudinal wing axis and the second wing extends along the second longitudinal wing axis from the fuselage. The first wing is tiltable with a first rotational direction around the first longitudinal wing axis and the second wing is tiltable with a second rotational direction around the second longitudinal wing axis. In a fixed-wing flight mode, the wings do not rotate around a second axis. In a hover flight mode, the wings are tilted around the longitudinal wing axis with respect to its orientation in the fixed-wing flight mode and that the wing rotates around the second axis.

Abstract: A method for predicting aerodynamic impact for small appendages on aircraft, wherein the improvement comprises using an adaptable computational fluid dynamic model of airflow adjacent the appendage by isolating a patch surrounding the small appendage, measuring the load on the patch without the appendage in place and with the appendage in a place and subtracting the two for increasing computational accuracy of the load predictions for the small appendage to be able to measure the effect of the small appendage.

Abstract: A method and device for detecting oscillatory faults relating to an aircraft airfoil slaving chain. The device includes units that count the number of overshoots of a threshold value by the current value of a quantity related to the positional slaving of an airfoil. Oscillatory fault is detected based on the number of overshoots of the threshold value being greater than the current value by a predetermined number.

Abstract: Disclosed is a method and device for estimating forces exerted on at least one aircraft control surface. The method includes steps of, and the device includes components that carry out steps that include: generating current aircraft flight data; determining, from the generated aircraft flight data, a value Bl based on current deflection data and geometrical characteristics of a lever arm actuator of the at least one aircraft control surface; calculating, from the determined value Bl, at least one hinge moment; summing each calculated hinge moment; and dividing the sum by the value Bl to obtain an estimate of the forces exerted on the least one aircraft control surface.

Abstract: Disclosed is a method of detecting at least one oscillatory fault in at least one positional slaving chain for at least one airfoil of an aircraft. The method involves estimating a reference position of the airfoil in the absence of a fault, and calculating a residual value based on the difference between the estimated reference position and the actual position measured by at least one sensor. The calculated residual value is compared with at least one predetermined threshold value to determine the number of successive and alternating overshoots of the predetermined threshold value by the residual value, and oscillatory fault is determined based on the determined number.

Abstract: A system and method for enabling controlled twisting of a tip of a wing in response to the aerodynamic forces experienced by the wing. The structural stiffness of the wing is modulated to modulate the twist of the wing in the presence of aerodynamic forces.

Abstract: A wireless-controlled airplane includes a flying unit and an on-ground controller which is connected to the flying unit through a communication section and flies the flying unit. The flying unit includes a body, a drive section installed on the body, a propulsion apparatus which generates a propulsive force when driven by the drive section, a main wing including a plurality of wing elements which are installed so as to be able to move with respect to each other, an opening and closing mechanism which changes the relative positions of the wing elements to change the effective area of the main wing, and a dropping apparatus which selectively holds and drops a load. By changing the effective area of the main wing, the flight speed can be changed, so the capacity and size of the drive section for rotating the propulsion apparatus can be decreased.

Abstract: Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage with a first portion and a second portion. The system can further include a movable control surface coupled to the fuselage and extending generally in a horizontal plane. The control surface can be movable to a deflected position in which the control surface can be positioned to create a flow pattern proximate to the fuselage when the aerospace vehicle is located in a flow field. The flow pattern can be positioned to create a pressure differential between the first portion of the fuselage and the second portion of the fuselage. The first and second portions can be located so that the pressure differential produces a yawing moment on the aerospace vehicle.

Abstract: Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage with a first portion and a second portion. The system can further include a movable control surface coupled to the fuselage and extending generally in a horizontal plane. The control surface can be movable to a deflected position in which the control surface can be positioned to create a flow pattern proximate to the fuselage when the aerospace vehicle is located in a flow field. The flow pattern can be positioned to create a pressure differential between the first portion of the fuselage and the second portion of the fuselage. The first and second portions can be located so that the pressure differential produces a yawing moment on the aerospace vehicle.