Abstract: A simulated payload apparatus (SPA) for testing in a flight motion system (FMS), which has a body for mounting in the FMS, and which simulates an actual payload during the FMS test. The SPA may include a plurality of adjustable weights that are mountable on and/or removable from the body to vary the mass and/or center of gravity of the SPA. The SPA may include an adjustable bracket for interfacing with a motion drive of the FMS, in which the bracket is positionable along the body to vary the moment of inertia of the SPA. The SPA may include an onboard electronic measurement device that is configured to measure a motion characteristic of the SPA and/or communicate information about the measured motion characteristic in real-time during the FMS test. The SPA may include a laser alignment for aligning the SPA relative to test equipment of the FMS.

Abstract: A method of controlling a path of a rotorcraft. The method comprises a step of generating a first path setpoint and a step of automatically generating a first autopilot command from the first path setpoint. The method comprises a step of generating a first pilot setpoint during which a movement of a control member is transformed into a first pilot setpoint, the first pilot setpoint and the first flight parameter being homogenous in that they are expressed in the same measurement unit. The method includes a step of generating a first human pilot command from the first pilot setpoint followed by a step of generating a path command by combining the first autopilot command and the human pilot command.

Abstract: A system for unmanned aircraft system (UAS) testing which incorporates a UAS flight control system and an optionally piloted vehicle (OPV) carrying the UAS flight control system. The OPV has an OPV flight control system and a flight control interpreter (FCI) which receives input from the UAS flight control system representing control parameters for a flight profile of the UAS. The FCI provides status commands as an output to the OPV flight control system to replicate the flight profile. These status commands are selected from the group consisting of data regarding attitude, vertical navigation, lateral navigation, turn rate, velocity and engine operations. The OPV flight control system includes a pilot override for emergency, flight safety or other contingencies allowing an on board pilot to assume control of the OPV.

Abstract: Two architectures for unmanned aerial vehicles (UAVs) and a method for executing a mission plan are provided. One architecture for a UAV includes a flight command and mission execution (FCME) component making strategic decisions, a flight technical control manager (FTCM) making tactical decisions and a vehicle management system (VMS) providing navigational support. The FCME and FTCM execute on one processor and the VMS executes on a separate processor. The second architecture includes redundant processors for executing the FCME and FTCM as well as redundant processors for executing the VMS. The UAV executes a mission plan, which may include flight plan(s), communication plan(s), weapons plan(s), sensor plan(s), and/or contingent flight plan(s). The UAV may control various optical sensors, training sensors, and lights as well.

Abstract: A system, method, and apparatus to train autopilots to fly a simulated aeronautical vehicle includes a three-degree of freedom gimbaled platform comprising a pitch, roll, and yaw axis; an autopilot comprising an inertial measurement unit mounted to the platform; motors that rotate the platform along the pitch, roll, and yaw axes; shaft encoders connected to the motors to calculate an angular position of the platform; motor drivers connected to the motors to power the motors; a microcontroller connected to the motor drivers; a quadrature encoder connected to the shaft encoders and the microcontroller; sensors that generate and sense environmental conditions affecting the platform and the autopilot; a flight simulator connected to the microcontroller; and a computer that executes the flight simulator causing actuation of the platform, causing the sensors to generate environmental conditions, and causing the autopilot to react to the environmental conditions.

Abstract: Two architectures for unmanned aerial vehicles (UAVs) and a method for executing a mission plan are provided. One architecture for a UAV includes a flight command and mission execution (FCME) component making strategic decisions, a flight technical control manager (FTCM) making tactical decisions and a vehicle management system (VMS) providing navigational support. The FCME and FTCM execute on one processor and the VMS executes on a separate processor. The second architecture includes redundant processors for executing the FCME and FTCM as well as redundant processors for executing the VMS. The UAV executes a mission plan, which may include flight plan(s), communication plan(s), weapons plan(s), sensor plan(s), and/or contingent flight plan(s). The UAV may control various optical sensors, training sensors, and lights as well.

Abstract: A illumination device comprises a transparent member in which a lenticular lens of a cylindrical shape is disposed in a longitudinal direction; and light emitting members disposed in a vertical direction at prescribed intervals inside the transparent member; in which a visual illusion of existence of light emitting rings, respectively arrayed in a horizontal direction and respectively disposed in a vertical direction inside the transparent member, is created by light emitted from the various light emitting members.

Abstract: Interactive simulation including force feedback. The system includes a computer game display unit programmed with simulation rules. A control unit is connected to the computer and provides information and control signals to the computer to interact with the stored simulation rules and to receive information and control signals from the computer. A movable structure for movement in at least two degrees-of-freedom by an operator is interconnected to the control unit by actuators. A programmable unit processes signals and information from the computer to generate signals to drive the actuators so as to apply forces in the at least two degrees-of-freedom to the movable structure and thereby to the operator. The applied forces are based on internal programming within the programmable unit, events occurring in the simulation and movements of and forces applied to the movable structure by the operator.

Abstract: The objective of this invention is to provide an image synthesis method, games machine, and information storage medium that make it possible for a game to be satisfyingly enjoyable, even when a single player is playing it. History information relating to the performance of the player is recorded during one game session, and this history information is reproduced in another game session. A virtual player performs based on the thus-reproduced history information, and thus acts so as to affect the game result of the player. The virtual player either assists the player or acts as a combat opponent. This makes it possible to implement a game that is interesting even in single-player mode.

Abstract: To simulate, for testing purposes, the subsystems of an aircraft that electrohydraulically position the movable control surfaces of an aircraft, circuitry is provided for receiving input control signals, generated, for example, by an autopilot, and for transforming such signals into electrical output signals that are the analogs of signals produced by linear variable differential transformers (LVDT) feedback devices that track the actual movements and positions of the aircraft control surfaces. The relatively slow acting hydraulic components of the aircraft control subsystems are simulated by integrating circuitry and the resulting integrated signals are used to modulate an AC reference signal, which is then applied to the primaries of isolation transformers, the secondaries of which produce the simulated, analog LVDT feedback signals and also present a load impedance to the autopilot that closely matches the output windings of the simulated LVTDs.