Abstract: [Problem] To provide an aerial vehicle wherein the flight efficiency can be improved. [Solution] An aerial vehicle according to the present invention relates in particular to a aerial vehicle having a loading section whereon a payload and the like can be loaded. The aerial vehicle is capable of traveling at least forward and backward, is provided with lift generation sections, arm sections for holding the lift generation sections, a loading section disposed on the arm sections and positioned posterior to the center of gravity of the aerial vehicle, and a maintaining means for maintaining the aerial vehicle at least in the horizontal attitude, and the loading section has a first connection part for maintaining a loaded object at least in the horizontal attitude. On the basis of the above mentioned, the payload can be prevented from entering slipstream regions created by propellers, improving flight efficiency.

Abstract: Additive and subtractive manufacturing (e.g. 3D Printing) is used to form aeroelastic airfoils with control surface region(s) having conventional rib/spar structural topologies and a continuous skin (e.g smooth surface) formed over the entire outer surface of the airfoil. The control surface is moved with internal actuators resulting in a “morphing” airfoil as the skin stretches to follow the moving structure of the control surface region. The airfoil can include a plurality of different material moduli and geometric featuring to balance the appropriate control of stiffness with topological requirements.

Abstract: Embodiments are described for a stabilization system configured, in some embodiments, for stabilizing image capture from an aerial vehicle (e.g., a UAV). According to some embodiments, the stabilization systems employs both active and passive stabilization means. A passive stabilization assembly includes a counter-balanced suspension system that includes an elongated arm that extends into and is coupled to the body of a vehicle. The counter-balanced suspension system passively stabilizes a mounted device such as an image capture device to counter motion of the UAV while in use. In some embodiment the counter-balanced suspension system passively stabilizes a mounted image capture assembly that includes active stabilization means (e.g., a motorized gimbal and/or electronic image stabilization). In some embodiments, the active and passive stabilization means operate together to effectively stabilize a mounted image capture device to counter a wide range of motion characteristics.

Abstract: An unmanned aerial vehicle (UAV) apparatus includes an airframe, a propulsion system carried by the airframe and including at least one propulsion device, a movable component carried by the airframe, and a control system. The control system is programmed with instructions that, when executed, cause the control system to receive a first input corresponding to a characteristic of the movable component, receive a second input corresponding to a command to move the movable component, and direct a change in a setting of the at least one propulsion device in response to the first input and the second input.

Abstract: Systems, apparatuses, and methods are provided herein for stabilizing an unmanned aerial system. An apparatus for stabilizing an unmanned aerial system comprises a ring member and a pair of attachment members each having a first end and a second end, the first end being configured to attach to a multicopter and a second end being coupled to the ring member. Wherein the pair of attachment members holds the ring member such that a plane of a circumference of the ring member is generally parallel to blades of the multicopter.

Abstract: An electromechanical device for measuring the inclination of a support plane with high resolution, high accuracy and low sensitivity to outside disturbances, comprising a first electromechanical pendulum system, controlled in a closed loop to measure the static rotations of an inverted pendulum pivoted to a supporting structure which can be associated with the support plane whose inclination is to be measured. The measurement is performed by measuring the mechanical torque required to keep the inverted pendulum in a neutral position, i.e., in a position which is substantially perpendicular to the support plane. This is made possible by a first motor which is associated with the inverted pendulum and turns it as a function of its angular deviation from the neutral position measured by a first position sensor associated with the inverted pendulum.

Abstract: A method for obtaining the inertial properties of a movable rotating around a hinge line in an aircraft control surface. The method includes the steps of removing the mechanical connections of the actuators from the movable, leaving the movable free to rotate around its hinge line, further balancing the movable and calculating in a first approach its coarse static moment. The method includes refining the coarse static moment and obtaining simultaneously a frictional moment of the movable; incorporating an elastic element on the control surface and configuring a second order mechanical system; inducing forced oscillations on the movable at a certain frequency, this frequency being increased until it is sensibly close to the resonance frequency of the movable to produce a wave response; calculating, from the wave response, the moment of inertia of the movable.

Abstract: The present invention relates to an aircraft with a surveillance system characterized in that the direction of flight towards a target is achievable by shifting the center of gravity of the vehicle towards the target. The center of gravity is shifted towards the target by pointing the surveillance system at the target.

Abstract: The present invention relates to an aircraft with a surveillance system characterised in that the direction of flight towards a target is achievable by shifting the centre of gravity of the vehicle towards the target. The centre of gravity is shifted towards the target by pointing the surveillance system at the target.

Abstract: The invention provides an aircraft having a flight control system (20) comprising an aerodynamic lift generator, and a control system in use the lift provided by the lift generator. The lift control system in one embodiment uses a concentrated mass mounted within a longitudinal body of the aircraft, the concentrated mass comprising at least one existing aircraft function and/or system mounted on a support in a confined area. Bearings permit relative movement between the support for the concentrated mass and at least a portion of the lift generator. An actuator is provided for causing such relative movement whereby in use the center of aerodynamic lift and the center of gravity of the aircraft may be moved relative to one another for effecting flight control.

Abstract: The invention provides an aircraft having a flight control system (20) comprising aerodynamic lift generating means (14), and means for controlling in use the lift provided by the lift generating means, the lift control means comprising:

Abstract: A missile guidance system employs a strap down inertial measurement unit with a separate accelerometer and star sensor that are moved for preflight accelerometer initialization. During flight, light is directed on the accelerometer and inertial measurement unit to produce on the star sensor images of the light source, the accelerometer and the inertial measurement unit. The location of these images, which manifest the acceleration and position of the inertial measurement unit relative to the vehicle, are used to improve the accuracy of the inertial measurement unit data for vehicle guidance.

Abstract: A conventional aircraft having horizontal stabilizers and hinged elevators, which is controlled, preferably, through push-pull rods, is provided with a dynamic torque (bob) weight connected to a rotating member, in the direct line of control to the elevator surfaces. The torque member is located in the nose portion of the aircraft with its center of gravity angled up from 20.degree. to 50.degree. when the elevator surfaces are in the neutral position. The torque member is also mounted in a flexible manner to isolate it from horizontal tail vibrations, or flutter.

Abstract: A model airplane control device for automatically adjusting to wind conditions to maintain a generally level flight. The control device is responsive to changes in the inertial forces of the model airplane while in flight, eliminating the need for control cables to positively control the elevation of the model airplane. The device is designed to allow a child to hold a tethered model airplane in flight without having to control the vertical movement of the aircraft to make adjustments for variable wind conditions. The control device is connected to the elevator of the model airplane, so that movement of a balance arm will result in a responsive movement of the elevator. Included in the control assembly is a switching device which allows the operator to utilize a single airplane and alternately switch between automatic control of the airplane responsive to changes in inertial forces or acceleration in the airplane and the positive hand control responsive to the use of control lines.