Abstract: A method for detecting a rotating stall includes: determining a level of variation of a static pressure in a combustion chamber of the turbojet engine around an average value of this static pressure; comparing the level of variation of the static pressure relative to a first threshold; comparing a temperature measured at the outlet of a turbine of the turbojet engine relative to a second threshold; and if the level of variation of the static pressure is greater than the first threshold and the temperature at the outlet of the turbine is greater than the second threshold, detecting a presence of a rotating stall.

Abstract: A novel apparatus and method is described for sleep monitoring and control by providing tactile stimulation to a user as the user attempts to fall asleep which can be employed for intensive sleep retraining for the treatment of insomnia. A motion response to the tactile stimulation from the user is sensed indicating the user is still awake. The tactile stimulation is periodically repeated and the motion response is evaluated until sleep onset is determined. Following a relatively short set time asleep (e.g. approximately 3 minutes) the user is awakened and the process is reinitiated within a half hour. The technique can be implemented in a small device configuration comparable to a large ring which can be held to a single finger of the user by a band. The single finger both receives the tactile stimulation and provides a motion response and can provide feedback directly to the user.

Abstract: The present disclosure includes a flight control method and apparatus. An example includes determining, when an unmanned aerial vehicle is flying, a specific flight zone to be entered by the unmanned aerial vehicle, where a flight clearance is required for the unmanned aerial vehicle to enter the specific flight zone. Application information and information about the specific flight zone is sent to a server, where the application information is used to apply for the flight clearance to enter the specific flight zone, and the information about the specific flight zone is used to indicate the specific flight zone. A flight instruction is sent when a flight clearance sent by the server is received, so that the unmanned aerial vehicle enters the specific flight zone according to the flight instruction.

Abstract: An apparatus for generating tactile sensation by using a magnetic field, includes: a first magnet and a second one which are placed across a target as a subject to provide tactile sensation; and a first electromagnet placed between the target and the first magnet; wherein a strength of the whole magnetic field between the first and the second magnets is allowed to be adjusted by adjusting at least either of a direction and a strength of a magnetic field arising from the first electromagnet to control the strength of the force with which the target is pressed by the first and the second magnets. Because a magnet itself that generates a magnetic field without any complicated mechanical components may perform a function as an actuator that generates tactile sensation, the apparatus for generating tactile sensation may become simple, light and compact.

Abstract: A method and device for providing a pilot warning signal is provided, where such method can include providing a first signal to indicate a pedal angle of a pedal, providing a second signal which is directly dynamically dependent on the pedal angle, pairing up values of the first signal and the second signal at specific times, determining an angle change of the pairs of values and an increment of the pairs of values at two successive times, and generating the pilot warning signal when actuation of the pedal and a stimulated tumbling movement of the aircraft are ascertained and if the determined angle change of the pairs of values is greater than a first threshold value or the determined angle change of the increment of the pairs of values is greater than a second threshold value. A computer program product and a warning device are also provided.

Abstract: A system for tactile presentation of information to a pilot of an aircraft. The system comprises a pilot seat, a plurality of tactors, and a controller configured to control the plurality of tactors to tactually present the threat information to the pilot by producing one or more tactile stimuli based on situational awareness information. The tactors in the plurality of tactors are physically coupled to the pilot seat and the threat information is indicative of a threat to the aircraft. In some embodiments, at least one pressure sensor may be physically coupled to the pilot seat and the plurality of tactors may be configured to tactually present the threat information to the pilot based at least in part on data obtained by the at least one pressure sensor.

Abstract: The present disclosure provides a directionally filtered indicator light, wherein a directional filter is applied to a light source that is controlled to emit light when a condition or series of conditions are met. The directional filter, in turn, regulates the transmission of light from the light source so that a first group of individuals, located within a viewing angle, are the only individuals able to see the transmitted light. In one example, the directionally filtered indicator light of the present disclosure allows an indicator light on the interior of a passenger aircraft to be viewed from outside the aircraft in direct sunlight while substantially eliminating the presence of transmitted light from a passenger seating area.

Abstract: Disclosed are a method and system for improving real-time determination of flight parameters of an aircraft during flight. A selection module selects and delivers measured values of input parameters to an estimation unit, and the estimation unit uses the input parameters to estimate at least two selected flight parameters. The input parameters are received by the estimation unit on the basis of identified flight mechanics equations associated with the selected flight parameters. The estimation unit includes an extended Kalman filter, which is configured to receive the values of the input parameters and to output joint estimations of the selected flight parameters based on the flight mechanics equations, during the flight of the aircraft.

Abstract: The present general inventive concept relates to methods and systems to select and display information on an avionics display screen. The systems and methods allow for the selection and display of information using knobs to highlight and select the desired information for display, eliminating the need for a cursor function. The systems and methods also provide for multiple pages and/or multiple windows or “tiles” within these pages and/or windows simultaneously on a single screen of a display, with each window, page, and/or tile being fully controlled independently when selected. The present general inventive concept also relates to systems and methods to provide multiple cues on an electronic display system altitude tape to a pilot in advance and impending approach to a predefined altitude. The present general inventive concept also relates to systems and methods to employ variable resolution topographical data based on display range for an avionics navigation display.

Abstract: A hold line awareness system for alerting an occupant of an aircraft that the aircraft is approaching a hold line at an airport. In one broad aspect the invention includes an airport database located on an aircraft. The airport database is configured to store location information for a plurality of hold lines at the airport. A positioning system is located on the aircraft. The positioning system is configured to determine the aircraft location. A processor is located on the aircraft and is operatively connected to the airport database and the positioning system. The processor is configured to calculate the distance between the aircraft location and a hold line and provide a processor alerting output signal if the distance is less than a predetermined value. A sensory effector is located on the aircraft and operatively connected to the processor for receiving the processor alerting output signal and providing a tactile alert to an occupant in response thereto.

Abstract: A method of alerting an occupant of a seat assembly of the occurrence of a triggering event comprising the steps of monitoring for the occurrence of the triggering event, vibrating the seat assembly and/or probing the seat assembly.

Abstract: An electronic device (100) is configured to be operable with the user input attachment (102) so as to provide a user with the option of using a touch sensitive display (101) alone, or in conjunction with the control device or keypad having physical keys to enhance the tactile user experience. The electronic device (100) includes a touch sensitive display (101) and the controller (104) it is operable with a touch sensitive display (101). When the user input attachment (102) is coupled to the touch sensitive display (101), and identification module (106) is configured to identify the user input attachment (102) by way of a temporal signature signal (110). Once identified, and adaptation module (107) is configured to reconfigure the electronic device (100) in response to the user input attachment (102) being attached.

Abstract: A vibrator assembly for a vehicle for generating an oscillation of a vehicle part detectable by a person is provided. The vibrator assembly comprising a vehicle part having a supporting structure and a case connected with said supporting structure, and a vibrator surrounded by the case which is formed to stimulate the case to oscillate whereby the oscillations are perceivable by a person. The vibrator for stimulating the oscillations of the case is coupled via at least one spring element differing from the case with the supporting structure of the vehicle part so that the oscillations of the case are stimulated via the supporting structure.

Abstract: A present novel and non-trivial system, module, and method for presenting runway advisory information are disclosed. A runway reference may be established using data received from a source of navigation reference data, where such data could represent runway information, runway awareness zone information, landing awareness zone information, and/or runway threshold line information. Navigation data representative of at least aircraft location and input factor data may be received from a source. Phase of flight may be determined using input factor data, and a runway advisory data set may be generated as a function of phase of flight and the positional relationship between aircraft location and the runway reference. Runway advisory data set may be representative of advisory information comprised of visual runway advisory information, aural runway advisory information, tactile advisory information, or a combination thereof.

Abstract: An optical system for detecting ice and water on the surface of an aircraft includes an elongated transparent optical element having first and second end portions. A light source and light detector are disposed in one end of the optical element and a reflective surface is disposed in the opposite end portion. The reflective surface defines a critical angle and reflects light from the light source to the light detector when the critical angle is in contact with air and refracts the light toward the external environment when the reflective surface is in contact with ice or water. The system may also incorporate an optical element wherein the reflective surface includes a continuous array of convex elements extending outwardly from and across one end of the optical element and wherein each of the convex elements defines a critical angle.

Abstract: A system and method for generating lateral guidance image data and presenting information representative of the image data is disclosed. A system is disclosed for determining lateral guidance information based upon the elevation of terrain cells and a level of terrain threat associated with the elevation. A left or right turn angle, or both could be formed between a projected flight path and a vector extending to a tangent point of a terrain boundary to the left and right, respectively. The degree of angle could be determined for each, and lateral guidance image data based upon the boundary location of a level of terrain threat with respect to the projected flight path determined. A lateral processor provides an alert signal associated with the generation of the lateral guidance information and provide such signal to a crew visual and aural alerting system.

Abstract: A haptic/tactile input in which the behavior and/or appearance of the mechanical user interface input is configured to be adapted to the function and context of an electronic device to give feedback and cues to the user. The mechanical input for example, buttons, sliders, levers, and other input devices are made appear on the surface of the user interface when needed.

Abstract: A method of alerting an occupant of a seat assembly of the occurrence of a triggering event comprising the steps of monitoring for the occurrence of the triggering event, vibrating the seat assembly and/or probing the seat assembly.

Abstract: Methods and systems for a position indicating display system for an aircraft are provided. The system includes a map display unit configured to display a map representative of an area being traversed by the aircraft, and an overlay comprising an own ship depiction, said overlay displayed on the map for a period of time in response to an input from at least one of a user and an aircraft sensor.

Abstract: An airspace awareness and warning system (“AAWS”) provides input to an airspace alert (“AA”) processor from at least one real-time aircraft system or sensor, a navigation system, and an airspace database containing three-dimensional delineations of defined airspace; the processor determines an airspace clearance surface and an aircraft airspace alert surface, and if one surface penetrates the other, the processor generates an alert signal and provides an alert signal to a crew alerting system. The two surfaces are determined by the processor by executing an algorithm(s) embedded in software containing the disclosed embodiments and methods. At least one criterion used to define an aircraft airspace alert surface is programmed to include real-time and/or static input factor data provided by at least one system or sensor input from an aircraft. Such input factor could be used to define an airspace clearance surface.

Abstract: A vehicle warning system has an obstacle sensor for detecting approach of an obstacle to a vehicle, tactile information-generating elements for notifying a driver of the obstacle information based on information received from the obstacle sensor, and a controller for controlling the actuation of the tactile information-generating elements. The tactile information-generating elements are installed in the cushion of a driver seat, with a fore-and-aft and/or left-right arrangement. The controller controls the tactile information-generating elements based on the information from the obstacle sensor as well as information from one or more of a steering wheel-sensor, a blinker sensor, a brake sensor, and a vehicle speedometer.

Abstract: A helicopter tactile accedence warning system includes a control stick and a tactile warning device attached to the control stick. A computer or micro processor and a keyboard for entering a safe temperature profile are also provided as well as a thermocouple for measuring the turbine output temperature. The computer compares the actual temperature versus the safe temperature profile and generates a signal to activate the tactile warning device when the actual temperature falls outside of the safe temperature profile to warn a pilot to abort the start. The tactile warning device is also activated during flight operations when an over stress condition occurs to thereby warn the pilot to take corrective action. In addition, the tactile warning may be activated at a first frequency as an early warning and then at a second frequency as an indication of imminent danger.

Abstract: With the increasing popularity of multimedia presentations at business meetings and conferences, presenters often wish to be free to move about during their presentation. Moderators at a presentation or conference can use this invention to communicate with the presenters. Podium lights, buzzers, or other obtrusive signals are becoming less and less effective means of signaling during presentations. For this reason, the present invention employs remote controlled tactile notification rather than sight or sound. The moderator might inform the presenter that the allotted time has expired or numerous other messages may be signaled. A predetermined message or code is sent to the presenter by stimulating the presenter's sense of touch.

Abstract: A threat detection system interface that provides translates threat diction information into a tactile signal for a user to indicate the direction and distance of an identified threat relative to an object. The threat detection system interface having applications for use with military vehicles, and in particular military aircraft, but also having application in connection with flight training simulators, computer and/or video games.

Abstract: A tactile warning system for warning a helicopter pilot of a pre-selected altitude during a landing maneuver includes a collective control arm for control of the aircraft and a tactile warning device operatively connected to the collective control arm. The system includes a radio altimeter for sensing the actual altitude, a computer and keyboard for inputting a pre-selected height above the ground into the computer memory. A signal generator generates a signal indicative of the actual altitude as the aircraft approaches the ground. Then, when the actual altitude is equal to or less then the pre-selected altitude the system activates the tactile device. The warning system indicative of reaching a pre-selected height is also combined with a tactile warning system for avoiding “hot starts” and for avoiding other dangerous conditions.

Abstract: A method and apparatus for tactile cueing of aircraft controls (21) is disclosed. The apparatus of the present invention warns pilots of approaching limits on certain aircraft performance parameters. The most common warnings are for rotor speed exceeding a moving limit. The present invention uses tactile cueing through the collective stick (21). Tactile cueing means that the pilot does not need to scan the intruments to ascertain proximity to the aforementioned limits. Instead, the pilot can operate the aircraft within proper limits by touch, while maintaining situational awareness outside of the cockpit (20). The method and apparatus of the present invention provides customary friction resistance up to a limit position that is continuously updated. According to the present invention, continued motion of the collective (21) in a direction beyond that limit position results in a breakout force and an increasing resistive force.

Abstract: A system receives information regarding current flight conditions of a device such as an aircraft and determines the acoustic level of the sonic boom and/or other noise generated by the device during operation. The current acoustic level is compared to a desired level, and various cues are displayed to operators regarding corrective actions that can be taken to reduce or maintain the acoustic level at the desired level. The system also predicts future acoustic levels based on current operating conditions, and varies the urgency of the cues based on whether and how quickly the device will exceed the desired acoustic level. Options to limit maneuvers and to automatically adjust operating condition parameters can be enabled. Options to display additional information regarding past, current, and predicted acoustic levels can also be selected. Signals that can be used to automatically control the acoustic level of a device during operation can also be generated for use in devices that can operate autonomously.

Abstract: A remotely activated sensory stimulation device comprised of a case, a tactile stimulatory means, a receiving unit, a transmitting unit and a controller. The amplitude and frequency of the tactile stimulation is adjustable to provide different prompts or to alter the prompt. The device is further camouflaged with a second functionality to eliminate any social stigma. The device is useful for teaching individuals with a variety of learning disorders including Autistic Spectrum Disorder, Attention Deficit Disorder and Attention Deficit Hyperactivity Disorder.

Abstract: An information display method and system on board a passenger aircraft for automatically choreographing material to be presented throughout a journey of the aircraft. The method includes reading and parsing a string file of event triggers retrieved from a configuration file and sequentially determining if one of the triggers is to be activated by comparing it with navigational data of the aircraft. If the subject trigger is to be activated the system takes the action dictated by this trigger. All of the preceding steps are repeated throughout the journey of the aircraft. The system includes a configuration file for storing a plurality of the event triggers and screen formats for displaying flight information. The configuration file also stores a plurality of display modes, each mode representing a specific sequence of preselected display screen formats, with each display mode corresponding to an event trigger.

Abstract: In a method of controlling a vibrator, the vibrator is first driven towards a first frequency during a first interval and then is driven towards a second frequency during a second interval. In a preferred embodiment the first frequency is higher than the lowest resonance frequency of the vibrator and the vibrator is then allowed to reduce the frequency to a frequency lower than the resonance frequency. By letting the frequency vary in a pulsating manner in the vibrating device, the vibration can be sensed more easily by a human, and thereby making it possible to use a very small mass in the vibrating device, which therefore can be made using a small weight, while still making it possible to sense the vibration.

Abstract: A device for preventing detection of a traffic violation comprising an ultraviolet laser emitter that interferes with the photographing of a traffic violation or the violating car by an automatic camera installed on a traffic signal. The automobile is provided with a plurality of ultraviolet laser emitter devices adjacent to the license plate that prevent the photographing of the violating automobile's license plates. The automobile may also include ultraviolet laser emitter devices on its planar surface to further prevent the automatic photographing of the automobile.

Abstract: A method of communicating electronic information via a display device having a matrix of movable tactile elements. The method includes displaying a representation of a file containing hypertext links on a first portion of the matrix, and displaying a list of the hypertext links on a second portion of the matrix. The representation may include graphical elements and text symbols such as Braille.

Abstract: To provide an information device that makes it possible to easily reduce the overall reaction time and makes it difficult to overlook a warning. An information device includes an external force generator for supplying external force to an operator touched by the extremities, the hands or feet, of a driver at the time of operation of the vehicle. A judging member is provided for receiving an external signal and judging traffic conditions. A control member controls the driving of the external force generator based on the judgement result of the judging member.

Abstract: An apparatus for supplying tactile signals to the user of a vehicle or other machine to indicate the operational status or condition of the vehicle or machine, or a functional part thereof. A cam undergoes rotary movement within a flexible cylindrical wall having a corrugated inner surface, as with ridges of the like. The distal end of the cam contacts the inner surface as the cam rotates. The rotary motion of the cams modulated and regulated in response to output signals associated with operating conditions, for example, fluid pressure, engine speed, oil temperature, transmitted from corresponding sending units. The rotation of the cam causes periodic flexure of displacement of the wall which is palpable to the user. In one embodiment, the rotating cam causes one or more movable plungers to move to-and from in and out of the wall, also resulting in a tactile signal to the user. The cam may be driven by an electric motor which is responsive to the input signals.

Abstract: A flight warning system comprises an outside temperature probe for sensing outside temperature, a gyroscope for sensing aircraft bank angle, a static transducer for sensing static pressure, and a dynamic pressure sensor for receiving total pressure from a pitot tube. A computer is responsive to the gyroscope, static transducer, outside temperature probe and dynamic pressure sensor calculates whether the aircraft is entering a stall condition by comparing the aircraft's bank angle with the stall bank angle. The computer can also calculate whether sufficient altitude exists for the aircraft to safely return to a field after a power failure. An output device can also be provided for indicating the existence of said sufficient altitude, and a stall indicator can be provided for indicating whether the aircraft is entering a stall condition. A method for determining the existence of a stall condition with the aircraft is also disclosed.

Abstract: A pilot warning system is disclosed for a helicopter having a main rotor rotatable about a yaw axis, a fuselage connected to the main rotor and having a tail boom with a controllable force mechanism to counter-act the torque exerted on the fuselage by rotation of the main rotor. The pilot warning system acts on foot pedals operatively connected to the controllable force mechanism, with the pedal movement controlling the amount of force exerted by the controllable force mechanism on the tail boom to the control the orientation of the helicopter fuselage about the yaw axis. A position sensing device senses the location of at least one of the foot pedals between its first and second positions, and a warning indicator operatively connected to the position sensing device provides a warning to the pilot when the sensed foot pedal reaches a predetermined distance from one of the first and second positions.

Abstract: A two-stage alarm for a rotary wing aircraft, such as a helicopter which operates on a collective control arm. A moveable mass or weight is operatively connected to the collective control arm. The moveable weight may be of a reciprocating type or a rotor driven mass which is mounted eccentrically for rotation about an axs which is spaced from the center of gravity of the weight. In the latter case, a D.C. motor spins the weight rapidly about the axis at a first speed to produce a shaking action to the collective control arm as a warning of an approaching danger. The weight is moved more rapidly to produce a much more noticeable action at a second frequency, or at an increased amplitude as a warning of a more imminent or serious condition which requires immediate action.

Abstract: A device for providing a pedal operator with tactile indication that a pedal (32) has been depressed to a preselected position includes a cup-like housing (50), a ring-shaped magnet (52) mounted within the housing (50) and a displaceable member (54) provided with a pin (56) engageable by the pedal (32). The pin (56) extends through aligned openings in the magnet (52) and housing (50) and mounts the displaceable member (54) for linear sliding movement on the housing (50). Depression of the pedal (32) to the preselected position results in shifting of the displaceable member (54) away from the influence of the magnet (52) to provide the operator with a snap-like tactile indication of pedal position. The cup (50), magnet (52) and displaceable member (54) are each made of unitary, one-piece construction and of simple, circular geometry.

Abstract: An apparatus and method for compensating for asymmetrically produced total engine thrust caused by an engine failure in a multiengine aircraft. The presence of asymmetric total thrust is detected by monitoring aircraft performance parameters, including engine manifold pressures, airspeed, roll angle and yaw. When an engine failure resulting in the production of asymmetric thrust is detected at air speeds below a minimum controllable air speed for the aircraft, and during large aircraft bank angles, the power output from an operating engine is reduced to regain and maintain controllable flight conditions. Limiting the adverse yaw produced by an engine failure by reducing power output from operative engines reduces the tendency of the aircraft to roll into the inoperative engine, hence the aircraft is halted.

Abstract: A system for warning the pilot when the aircraft has reached a high yaw condition. A differential in pressure or angle of attack between the port and starboard sides of the aircraft is measured and converted into a measured sideslip angle. If the measured sideslip angle exceeds a predetermined maximum acceptable sideslip angle, a warning device, such as a rudder pedal shaker, is activated. The maximum acceptable sideslip angle is determined as a function of the ability of the aircraft flight controls to counteract a rolling moment generated by the yaw condition.

Abstract: An information display system comprising tactile output stimulators for providing spatial or directional information relative to an operator's egocentric coordinate system.

Abstract: An acceleration schedule, from which data is derived for use in calculating fuel flow during acceleration of a gas turbine engine, is modified each time the engine surges so as to avoid future surges.

Abstract: A system for tactilely alerting an aircraft pilot that the aircraft is in an uncoordinated turn condition and for indicating to the pilot the control adjustments required to correct the turn condition. The system includes a device for sensing the turn condition of the aircraft and a pair of tactile sensation generators in the vicinity of the pilot's legs. The condition sensing device controls activation of one or the other of the tactile sensation generators which indicates to the pilot which foot to depress on the rudder control to return to coordinated flight.