Abstract: A threat emitter system comprising a threat emitter comprising a main power supply, an external power source, a first sequencer, a driver amp, a second sequencer, a main amp, and a radio; a three-way power supply; a mixer, synthesizer, pre-amp, and cooling fans receiving electrical power from the three-way power supply; and an antenna in communication with the main amp; a user interface in communication with radio; the radio in communication with the mixer; the mixer in communication with the synthesizer; a filter in communication between the mixer and the pre-amp; the driver amp in communication with the pre-amp; the first sequencer in communication with the driver amp; the driver amp in communication with the main amp; a second sequencer in communication with the main amp; and a processor with access to a memory storing instructions executable by the processor.

Abstract: A foot-braking simulation device for a simulator includes a mechanical braking module configured for supplying a linear effort value in response to a press on a brake pedal; an electromagnetic friction module configured for supplying a friction force value in response to the press on brake pedal; and a software calculation module configured for combining the values obtained from the mechanical braking and electromagnetic friction modules to calculate a control value, and generate variable force feedback on the brake pedal as a function of the control value.

Abstract: A method for determining a target virtual object is provided. In the method, a target search range corresponding to a target skill of a controlled virtual object is determined in response to a trigger operation of the target skill. The virtual object is controlled by a user. In response to the target search range including a plurality of first virtual objects in the target search range, at least one second virtual object that satisfies a defeated condition is obtained from the plurality of first virtual objects, the defeated condition indicating that a preset threshold of virtual health points will be reached after the target skill is performed on the first virtual object. A third virtual object that satisfies a target hit condition of the user is obtained from the at least one second virtual object. The target skill is performed on the third virtual object as the target virtual object.

Abstract: A virtual object control method is provided. When there is a need to trigger a skill, a terminal determines a to-be-cast range of a skill and a target virtual object in the to-be-cast range, and displays a cast indication pattern of the skill according to positions of a controlled virtual object and the target virtual object. The terminal adjusts, in response to a position of either virtual object of the controlled virtual object and the target virtual object being changed, the displaying of the cast indication pattern in real time. Thus, it is ensured that the terminal automatically adjusts a pointing direction of the cast indication pattern with the change in the position of the virtual object, so that the cast indication pattern may be associated with the position of the target virtual object. Apparatus and non-transitory computer-readable storage medium counterpart embodiments are also provided.

Abstract: Disclosed is an excavator safety simulator and methods for preventing damage to existing underground equipment prior to excavation by using a Virtual Reality (VR) environment with underground facilities and markings, and real world examples of dynamic climate scenarios and challenges that an excavator will likely encounter.

Abstract: Systems and methods of searching stored flight plan information using a custom search query including at least one aircraft parameter condition or environmental parameter condition. The systems and method include receiving, using a user interface module, a custom search query comprising an aircraft parameter condition or an environmental condition; searching, using a processor module, stored flight plan information for instances in the stored flight plan information that satisfy the aircraft parameter condition or environmental condition; and displaying, using a display module, the instances in the stored flight plan information that satisfy the aircraft parameter condition or environmental condition.

Abstract: A method for controlling an inerting system designed to inject a flow of inert gas into a fuel tank of an aircraft during a mission. The method includes: determining a value of a parameter of the mission of the aircraft at a given moment; determining the ratio between the determined value of the mission parameter and a value at the given moment of an equivalent parameter of a standard mission profile, and deducing a weight coefficient therefrom; using the weight coefficient to weight a value of the inert gas flow rate recommended by the standard mission profile for the value of the equivalent parameter at the given moment so that an appropriate inert gas flow rate to be injected is determined for the needs of the mission at the given moment; and commanding the inerting system to inject the inert gas flow rate determined at the given moment.

Abstract: The present invention relates to A power margin indicator device constituting a first limitation indicator for a rotorcraft, for providing a pilot of said rotorcraft with information about a power margin available on at least one engine and a main power transmission gearbox of said rotorcraft as a function of flying conditions, said device comprising: input means for collecting input data corresponding various operating parameters of said at least one engine and of said MGB; calculation means connected to said input means, said calculation means serving to determine a collective pitch margin for the blades of a rotor of said rotorcraft; and display means presenting said collective pitch margin.

Abstract: A method of managing a loss of power from a power plant having three engines. During a monitoring step, each engine is monitored in order to detect whether the engine is suffering a loss of power. During a verification step, it is determined whether the power plant is overpowered. During a signalling step, a first alert is generated when an engine has lost power but the power plant is in fact overpowered, and a second alert different from the first alert is generated when an engine has lost power and the power plant is not overpowered.

Abstract: Methods and systems for training an operator. One system includes a computing device including a processing unit and computer-readable medium. The computer-readable medium stores a training simulator application that is configured to receive an operating command from the operator, generate a simulated working environment and a simulated wheel loader having a simulated bucket, and generate an indicator providing depth-related information to an operator relating to a position of at least a portion of the simulated wheel loader with respect to a point-of-reference within the simulated working environment. The training simulator application is further configured to output the simulated working environment and the indicator for display to the operator, and automatically modify the indicator based on a position of the simulated wheel loader with respect to the point-of-reference.

Abstract: 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; a simulated control device able to receive a simulated command to simulate a flight condition of the aircraft; a plurality of simulation devices able to generate a simulated representation of the flight condition; and a processing unit configured to receive a first signal associated with the command given via the control device and to generate a second control signal for the plurality of simulation devices associated with the simulated aerodynamic loads. The processing unit cyclically generates a vortex ring, associates one or more 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.

Abstract: A method of failure simulation for an aircraft (7) having a power plant (10) with at least two turbine engines (11, 12), together the two engines develop an overall power, each engine (11, 12) being capable of delivering at least one contingency power in order to compensate for a total failure of other engines (11, 12). The device serves during a failure simulation to modify the overall power delivered by the power plant, with this modification being performed with the help of first adjustment means (20). Second adjustment means (30) serve to modify also the difference between the minimum power obtained during the simulated failure and the stabilized overall power, and also the time between said failure stabilizing on said overall power.

Abstract: A motion platform for use with a video simulation system is described. The platform is configured to provide simultaneous roll-axis and yaw-axis motion about a pivot point for simulating a aircraft environment. Additionally, the motion platform is configured to achieve motion using a single linear actuator, and thus is provided at a significantly reduced cost compared to conventional motion platforms. Other benefits of the motion platform include improved power efficiency, reduced weight for increased portability, and reduced maintenance due to only one linear actuator driving the system.

Abstract: The invention relates to a flight simulator vibration system, particularly to a crew seat (1), a flight control stick (20) and a panel (30) vibration system of a flight simulator with at least one plate of the crew seat (1), the flight control stick (20) and/or the panel (30) being equipped with predefined momentum weights (13, 16) and electric motors driving said respective momentum weights. Speed governors are controlling individually said electric motors (7, 8, 9, 21, 33, 34).

Abstract: An air rescue simulator, wherein the simulator comprises a helicopter passenger cabin, which is attached to a crane system.

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: A method for pilot situational awareness comprises calculating a location; providing terrain data for the calculated location; processing the terrain data and positioning a light source generally proximal to a view point of a pilot data to generate a synthetic image, the synthetic image representing an appearance of the terrain data illuminated by an appearance of the light source positioned generally proximal to the view point of the pilot; and displaying the synthetic image.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a simulator (10) for training at least one person, comprising a training room (20), the inner delimiting surface of which is provided with a color suitable for a color-based picture knock-out, wherein the simulator (10) comprises at least one semi-transparent head-mounted display (21; 21?), which is provided with two video cameras for stereoscopic images and a head tracker, which allows the line of sight of the respective wearer to be ascertained. The simulator (10) further comprises a simulation processor (22) having two picture generators for a stereoscopic representation of virtual pictures on the at least one head-mounted display (21; 21?), and the virtual pictures to be represented can be generated by a video mixer, which comprises means for isochronously mixing the images of the video cameras of the at least one head-mounted display (21, 21?) with computed virtual pictures in the respective line of sight.

Abstract: 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.

Abstract: The invention concerns a flight simulator device (1, 51) for simulating the flight behavior of an aircraft. The flight simulator device (1, 51) comprises a passenger compartment (6) with an input means to accommodate at least one person (P), an omnidirectionally movable carrier vehicle (2) with several wheels (4) and with drive units for driving the wheels (4), and a control device (5) connected to the input means and the drive units of the carrier vehicle (2), which is designed to actuate the drive units of the carrier device (2) on the basis of signals coming from the input means.

Abstract: The invention relates to a motion simulator for simulating a motion of a vehicle, particularly an aircraft, comprising: a multi-axis serial robot (1) comprising a rotatable base axis (2), and a seat (17) for an operator, wherein the seat (17) is attached to the multi-axis serial robot (1), so that the seat (17) can be moved in space by the multi-axis serial robot (1) for simulation of a real movement, wherein the motion simulator is adapted to simulate a long-lasting acceleration or deceleration by generating a centrifugal force acting on the operator. Further, the invention relates to a corresponding method.

Abstract: A system and method of controlling a gas turbine engine controller in a rotorwing aircraft includes determining when a fixed collective takeoff (FCTO) of the rotorwing aircraft is being conducted. A control loop gain of the gas turbine engine controller is at least selectively varied when the FCTO is being conducted.

Abstract: A method and system of simulating one-engine-inoperative (OEI) conditions in a multi-engine single-output aircraft which involves the operation of the engines above non-zero power settings, and operating each relative to one another to simulate power loss experienced during an actual failure of at least one engine.

Abstract: A video game controller hub receives a number of control input sets from an equal number of video game controllers, and provides a preferably smaller number of control input sets to a video game console. Each of the control input sets provided to the video game console by the controller hub is used to control a distinct on-screen entity, e.g. vehicle, character, or team. A number of players therefore collectively control a single on-screen entity. The reduction in the number of control input sets is performed according to reduction and combination schemes that are preferably specified by the user to suit a particular video game. The reduction in the number of control input sets increases the number of players that may concurrently participate in a video game without requiring support from the video game console or software, and the collaborative nature of the control of on-screen entities provides for exciting variations in game play.

Abstract: The present invention provides computer implemented methodology that permits the safe landing and recovery of rotorcraft following engine failure. With this invention successful autorotations may be performed from well within the unsafe operating area of the height-velocity profile of a helicopter by employing the fast and robust real-time trajectory optimization algorithm that commands control motion through an intuitive pilot display, or directly in the case of autonomous rotorcraft. The algorithm generates optimal trajectories and control commands via the direct-collocation optimization method, solved using a nonlinear programming problem solver. The control inputs computed are collective pitch and aircraft pitch, which are easily tracked and manipulated by the pilot or converted to control actuator commands for automated operation during autorotation in the case of an autonomous rotorcraft.

Abstract: 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.

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: A simulator structure with a deck for mounting various components including controls, one or two seats, an instrument panel and an image projector. The components are mounted to the deck using suitable fasteners, such as bolts and nuts. The image projector displays a computer-generated simulated environment. The instrument panel can include actual instruments or a computer-generated image. A dome-shaped image screen can be attached to the structure that can be tiltable on a horizontal axis or, alternatively, can be movable along an arcuate support.

Abstract: A flight simulating apparatus is capable of directing combinations of elevation, yaw, roll, pitch and three-space accelerations to a cockpit. Continuous rotation is provided by a rotational drive and elevation, roll and pitch are provided by linear positioning devices engaged with the rotational drive and extending upwardly from it. An x-y table and the elevation linear positioning device provide accelerating forces.

Abstract: A non-flying land based training or testing vehicle with helicopter style main controls and capable of transporting at least one human operator. A preferred embodiment includes a chassis; ground contacting wheels supporting the chassis; a power-plant for driving a wheel and propelling the vehicle; at least one seat for the operator. The controls simulating helicopter controls are within reach of the operator and operatively connected with a computer and electric/hydraulic mechanisms (for example only) to provide similar effects as helicopter controls when manipulated.

Abstract: A flight simulator apparatus capable of directing elevation, rotation, yaw, roll and pitch control of a an operators cockpit and linear motions in the horizontal x-y plane. A first linear actuator is engaged with a rotation actuator for providing motion about a vertical axis of rotation. The first actuator is enabled for vertical positioning of a gimbally mounted cockpit. A second actuator is engaged for positioning the cockpit using opposing linear hydraulic pistons. A third and fourth linear actuators, preferably linear motors drive the entire apparatus in mutually orthogonal horizontal directions for simulating linear inertial forces in the cockpit.

Abstract: In a shooting game toy, a target includes a display device that provides different image patterns to facilitate a communication of different states, or changes of state, of a shooting game or the toy. In a preferred embodiment, the display device is an electroluminescent display having a plurality of display elements that are activated in a predefined sequence corresponding to each state or change of state of the shooting game. For example, a routine hit of the target may be visually displayed as an image pattern representative of a conventional “outward burst” pattern, while a reset to a known state may be visually displayed as an inwardly contracting pattern, a destruction of the target as yet another visual pattern, and so on. By providing different display patterns at each target, the state of the game, or a change of state of the Game, is visually communicated to each participant having a view of the target, thereby enhancing the enjoyment of the shooting game.

Abstract: Full motion interactive simulator for use by two or more persons that can play a simulation game running on a display screen, where each player can alternate controlling the pitch and roll of a motion base platform supporting a vehicle on which the players sit. A joystick mounted in front of each player can be moved forward, backward, side-to-side, and in 360 degree circles to cause the platform to pitch and roll along any angle. The joystick can have separate buttons for firing weapons at targets on the display screen, controlling the position of images on the screen and answering questions by the system such as yes, and no to certain questions. Each player can have a set of foot pedals in front of their seats, where a left pedal can cause the screen image to rotate to the left, and the right pedal can cause the screen image to rotate to the right. The active player on the joystick controls both pedals at one time.

Abstract: A CPU of a control system controls a signal processor to effect various calculations to move a player's spaceship on a projection display screen, orient the player's spaceship toward a shooting direction, move a camera position at a rear viewpoint toward the player's spaceship, and orient the shooting direction outside of the projection display screen, based on shooting game data including image data, audio data, and program data stored in recording medium. The CPU also controls an image processor to write image data and audio data into a RAM based on the calculated results from the signal processor. The image data thus written in the RAM is displayed on a television monitor and projected onto the projection display screen.

Abstract: The present invention is related to a system which is portable and attache the body of a trainee so that the trainee can practice navigating of a model airplane at an arbitrary location, contrary to the system of a large-sized airplane. According to an object of the present invention there is provided a trainee navigates a model airplane virtually by simulating a model airplane using a computer by combining the three-dimensional virtual image of a model airplane and the actual image of the training site by a computer.

Abstract: A trainer for teaching the operation of aircraft fuel systems comprised of a fuselage frame portion and fuel tanks mounted to a platform. The trainer utilizes a fuel look-alike with a viscosity below 2.8 cs and a flashpoint above 200.degree. F.

Abstract: A mobile modular simulator system comprising a mobile base, a multimedia subsystem module demountably coupled with the mobile base, and a controller subsystem module demountably coupled with the mobile base, wherein the controller subsystem is configured for electronic coupling with the multimedia subsystem module for receiving input therefrom and for delivering output thereto to simulate an operating environment.

Abstract: The present invention provides a turbulence model that has been developed for blade-element helicopter simulation. This model uses an innovative temporal and geometrical distribution algorithm that preserves the statistical characteristics of the turbulence spectra over the rotor disc, while providing velocity components in real time to each of five blade-element stations along each of four blades, for a total of twenty blade-element stations. The simulator system includes a software implementation of flight dynamics that adheres to the guidelines for turbulence set forth in military specifications. One of the features of the present simulator system is that it applies simulated turbulence to the rotor blades of the helicopter, rather than to its center of gravity. The simulator system accurately models the rotor penetration into a gust field. It includes time correlation between the front and rear of the main rotor, as well as between the side forces felt at the center of gravity and at the tail rotor.

Abstract: The invention relates to a system for training helicopter pilots, more particularly to a system to be used as a highly efficient means for complementing present methods for training pilots. The object of the invention is avoiding the stress to which the trainee is subjected during the first flights and providing understanding of the helicopter behavior easily and without risk. The invention proposes a system basically comprised by a structure and a conventional helicopter permitting simulating stationary or translational actual flight without separating from the ground. The structure comprises a shiftable base having a support for free rotation of a frame from which the helicopter is suspended, so that it may raise and lower within set limits and also that it may be tilted to the sides in a restricted way. This giving the possibility of practicing various maneuvers, also considerably reducing the training cost.

Abstract: A helicopter flight simulator having improvements in visual cues and modeling. The unique visual cues include terrain following shadows and hazing, the latter approximating a set of atmospheric conditions. The unique modeling features include a user selectable zoom, horizontal and vertical ground avoidance, and an autorotation model.

Abstract: A helicopter flight simulator having improvements in visual cues and modeling. The unique visual cues include terrain following shadows and hazing, the latter approximating a set of atmospheric conditions. The unique modeling features include a user selectable zoom, horizontal and vertical ground avoidance, and an autorotation model.

Abstract: A trainer for the fuel system of an aircraft such as a helicopter which has full-scale aircraft and fuel system components for training in the operation and maintenance of the fuel system and which uses a fuel substitute which has a higher flashpoint and does not have the odor of aircraft fuel, but does have the specific gravity, dielectric constant and viscosity of aircraft fuel.

Abstract: In a simulator for helicopters, the images seen are displayed through the bottom windows by means of a system collimated to infinity, including, for each side of the cockpit, a projector (15, 16), a spherical mirror (12, 13) and a screen (17, 18).

Abstract: The radio controlled model pilot's station provides realism for the radio controlled modeler in flying his models. The present invention provides a chair having a motorized, rotatable seat to keep the model in view while positioning a throttle quadrant and other aircraft controls in realistic positions easily accessible to the pilot. A resilient pad and releasable clamps incorporated on a moveable radio shelf for quick mounting and removal of the control radio allow interchanging of radios for multiple models or increased battery endurance, while the movable radio shelf allows ingress to and egress from the chair by the pilot without removal of the radio.

Abstract: A remote controlled helicoper having a video radio frequency link to a fixed control location has a video camera with a field of view including the terrain forward of the helicopter, an airspeed display, a relative wind direction indicator, and a pitch indicator. A video monitor at the fixed location displays received video signals of the terrain, airspeed, relative wind direction and pitch permitting control of the helicopter over a radio link from the fixed location to the helicopter. The system provides training, experience, and practice in operation of the helicopter.

Abstract: A training stand for use in learning to fly remote control model helicopters without damaging the model. Model helicopters of various sizes can be removably connected to the training stand. The design of the training stand is such that the model helicopter can be made to fly forward, backward, sideways, up-and-down. The model helicopter can, also, be made to hover, rotate about its axis left and right and to pitch forward and backward while at all times remaining captive on the training stand.

Abstract: A system for training aircrews, particularly aircrews of relatively slow-moving aircraft such as helicopters in laser/electronic warfare countermeasure tactics and the use of laser/electronic warfare countermeasure equipment is provided. The system is operable with the aircraft's instruments to present the simulated threats whenever such threats are both with the line-of-sight of, and within the presentation range of the aircraft. Accordingly, such a system includes a plurality of independently operating threat-simulating transmitter units simulating both stationary and non-stationary threats by broadcasting omnidirectional radio frequency signals over a common carrier frequency. On-board equipment, carried on the aircraft determines whether the aircraft is both within the line-of-sight and within presentation range to the threat based upon receipt of the transmitter unit signals and the location of the threats relative to that of the aircraft.

Abstract: A helicopter simulator for simulating actual cockpit procedure and hover technique in a helicopter. The simulator having a helicopter airframe mounted on a platform which rotates on a stationary base. Inside the airframe are hydraulic controls used by the operator for raising and lowering the airframe to simulate taking off and landing, controls for tilting the airframe fore and aft and side to side along with controls for rotating the airframe in a clockwise or counterclockwise manner.