| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 434033000 | Helicopter | 7 |
| 20090186320 | MODULES AND METHODS FOR BIASING POWER TO A MULTI-ENGINE POWER PLANT SUITABLE FOR ONE ENGINE INOPERATIVE FLIGHT PROCEDURE TRAINING - A system and method for conducting flight procedures training in a rotary-wing aircraft with a multi-engine powerplant includes determining a variable bias relative an available power margin to simulate a reduced power available flight condition; and displaying symbology indicative of the simulated reduced power available flight condition. | 07-23-2009 |
| 20130108992 | MOTION SIMULATOR AND CORRESPONDING METHOD | 05-02-2013 |
| 20130203020 | Flight Simulator Device - The invention concerns a flight simulator device ( | 08-08-2013 |
| 20130209967 | APPARATUS AND METHOD FOR OPERATING A FLIGHT SIMULATOR WITH A SPECIAL IMPRESSION OF REALITY - An apparatus for operating a simulator with a special impression of reality is provided. The apparatus is configured for learning how to control a vehicle moving in three-dimensional reality. Controllable systems for detecting human stress reactions are provided. The controllable systems may be configured for sensing the resistance of the skin and for detecting movements of persons and physiognomy. | 08-15-2013 |
| 20140242553 | REAL-TIME SIMULATION SYSTEM OF THE EFFECTS OF ROTOR-WAKE GENERATED AERODYNAMIC LOADS OF A HOVER-CAPABLE AIRCRAFT ON THE AIRCRAFT ITSELF, AND METHOD THEREOF - A real-time simulation system of the aerodynamic loads generated by the wake of a rotor of a hover-capable aircraft on the aircraft itself is described, said system comprising: a cockpit seat for a pilot; a simulated control device of the aircraft able to receive a simulated command from the pilot to simulate a flight condition of the aircraft; simulation means able to generate a simulated representation of the flight condition; and a processing unit configured to receive as input a first signal associated with the command given via the control device and to generate and output a second control signal for the simulation means associated with the simulated aerodynamic loads. The processing unit cyclically generates a vortex ring with a radius, associates a number of control points with the vortex ring, computes the velocity induced on the control points, moves and updates the vortex ring, and generates the second signal on the basis of the velocities induced on the control points by the vortex rings. | 08-28-2014 |
| 20140302461 | METHOD OF DRIVING A MAIN ROTOR OF A ROTORCRAFT IN THE CONTEXT OF SIMULATING A FAILURE OF ONE OF THE ENGINES OF THE ROTORCRAFT - A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation. | 10-09-2014 |
| 20160049086 | AIRCRAFT SIMULATING APPARATUS FOR HELICOPTER HOVER SIMULATION - An aircraft simulating apparatus for helicopter hover simulation comprises a cabin containing in its interior a user interface with operating means adapted for simulating flight controls and at least one seat to accommodate a user in a pilot position to operate the flight controls, a carrying portion for supporting and moving the cabin, and a controller adapted to control-movements of the cabin in accordance with a hover simulation characteristics and dependent on the operation of the operating means for simulating flight controls. The carrying portion is adapted to move the cabin along translational movements in three spatial directions (X, Y, Z) and rotational movements around axes in three spatial directions (X, Y, Z), and includes a self-driven support vehicle adapted to perform movement on a ground surface at least along a forward direction (X′) and around one rotation axis (Z′) for rotating the forward direction (X′), and a robot arm supported by the support vehicle to be moved therewith while holding and supporting the cabin. | 02-18-2016 |
