Abstract: A high integrity navigation system is created using a low integrity navigation computer monitored by a high integrity system. A navigation sensor (e.g. DGPS, GPS, ILS, MLS, and the like) is programmed with a desired trajectory. The navigation sensor calculates the vehicle position and generates a deviation signal indicative of the deviation of the vehicle from the desired trajectory. The navigation computer uses the deviation signal in the control law computations to generate steering commands for controlling the vehicle. The navigation sensor monitors the deviation of the vehicle from the desired trajectory. If the deviation exceeds a predetermined threshold, an integrity alarm signal is communicated to a display or other alarm to alert the operator.

Abstract: A DSRC car-mounted equipment which prevents an IC card from being inserted when the temperature lies outside a tolerable temperature range, in order to avoid the thermal deformation and low-temperature breakage of the IC card. The DSRC car-mounted equipment comprises a communication control unit for executing a dedicated narrow-range communication with an on-the-road equipment 1, an IC card accommodation portion 9, a contact portion 10 connected to an electrode portion D of the IC card, a car-mounted equipment controller for reading and writing data to, and from, the IC card, a circuit board 8 constituting the IC card accommodation portion, temperature sensors 11 and 12 disposed near the IC card accommodation portion, a temperature-judging unit for judging whether the temperature data are within the temperature range tolerated by the IC card, and alarm unit 6 and 7 for producing an alarm when the temperature data lie outside the tolerable temperature range.

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 positioning and ground proximity warning method for vehicle includes the steps of outputting global positioning system signals to an integrated positioning/ground proximity warning system processor; outputting an inertial navigation solution to an integrated positioning/ground proximity warning processor; measuring air pressure, and computing barometric measurements which is output to the integrated positioning/ground proximity warning processor; measuring time delay between transmission and reception a radio signal from a terrain surface, and computing radio altitude measurement which is output to the integrated positioning/ground proximity warning processor; accessing a terrain database for obtaining current vehicle position and surrounding terrain height data which is output to the integrated positioning/ground proximity warning processor; and receiving the position, velocity and time information or said pseudorange and delta range measurements of said global positioning system, the inertial navigation s

Abstract: A terrain awareness system and method which provides increased warning times to the pilot of an aircraft of a hazardous flight condition while minimizing nuisance warnings. An important aspect of the invention is that the terrain background information as well as the terrain advisory and warning indications may be displayed on a navigational or weather display, normally existing within an aircraft, which reduces the cost of the system and obviates the need for extensive modifications to existing displays, such as a navigational and weather radar type display.

Abstract: A terrain awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as a terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.

Abstract: A terrain-awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as a terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.

Abstract: A positioning method for a production system for positioning the location of a positioning head (2 12, 27) in relation to a work object, comprising a positioning body (1, 11), e.g. a robot or a machine tool, a positioning control unit (3) for the positioning body (1, 11) and a control data system (4) for the positioning control unit (3), wherein the control data system (4) communicates with a three-dimensional localisation measuring system (6) comprising at least one recording device (7) which determines and adjusts the location of the positioning head (2, 12, 27) in space and a positioning device for a production system for positioning the location of a positioning head (2, 12, 27) in relation to a work object, comprising a positioning body (1, 11), e.g.

Abstract: Signals from warning systems are passed to a hazard prioritization computer. The prioritization computer also receives inputs from the aircraft's air data and inertial reference system. The alert prioritization computer includes three functional modules: (1) hazard detection, identification and monitoring, (2) threat assessment and (3) display and alert prioritization logic. The hazard prioritization computer processes the warning system signals, along with stored data from a hazard database to compute a severity component of threat and a proximity component of threat. These two components are processed to produce an overall threat value for each hazard. This overall threat value is then processed to provide alert and display generation and prioritization for the flight crew and/or the aircraft's auto-flight system.

Abstract: An apparatus and method for automatically and independently determining aircraft altitude and alerting the pilot to deviations from a target altitude exceeding a specified tolerance. The alerter comprises an altitude sensing means for sensing the present altitude of the aircraft. The invention discloses three sources for altitude information namely, a self-contined sensor such as a pressure transducer, a Global Positioning System receive, or an altitude encoder. A target entry means is used for entering the target altitude. An indicating means signals an altitude alerting condition upon the detection of a condition wherein the absolute difference is larger than the tolerance value. The altitude alerting apparatus may also comprise a display means for display of the present aircraft altitude information.

Abstract: A back-up proximity sensor for a vehicle is formed with an array of sensor pairs. Each sensor pair includes a lower passive infrared sensor (PIR) having a first field of view and an upper PIR having a second field of view. Each lower PIR and upper PIR is vertically mounted with respect to one another. The lower PIR and upper PIR of each sensor pair are angularly directed such that the respective fields of view intersect, thereby establishing a detection zone in a region behind a vehicle. The sensor pairs are arranged in a substantially adjacent, semicircular configuration to provide a continuous area of coverage behind a vehicle. A detection circuit receives output signals from each sensor pair and generates an output signal indicative of a warm body being detected by both the upper and lower sensors in a selected sensor pair, eliminating false alarms generated by warm bodies outside the region of the desired detection zone.

Abstract: An intelligent strobe system for vehicle applications includes strobe modules connected between the positive and negative DC power rails of the vehicle. One of the strobe modules includes a transmitter circuit for generating sinusoidal data and transmitting the data over the DC power rails. Other strobe modules include a receiver circuit to receive and decode the sinusoidal data to control the flash sequence.

Abstract: When a vehicle is moving out of a lane of a road, an image processing computer unit judges the hazardous condition. Then, a power steering control computer unit calculates a correction reaction force based on the steering angular velocity and increases a steering reaction force so as to generate a large steering effort. This lane moving-out prevention system is constituted such that only when the steering angular velocity is large, i.e., when a driver turns a steering wheel sharply, the steering reaction force is increased, thereby no additional reaction force is produced when the driver makes a normal turn.

Abstract: A control architecture having improved fault detection and correction capabilities is disclosed. The system comprises primary and monitor control systems, each having an associated control signal. A fault detector generates an alarm signal based upon differences observed between the primary and monitor control signal. The detector comprises an integrator and a memory means, and alarm signals are generated based upon the total amount of difference observed over a predetermined period of time. In one embodiment of the invention, primary and monitor control signals are averaged to provide a signal that is more fault tolerant than the individual control signals.

Abstract: A radar based terrain and obstacle detection device for aircraft detects obstacles and terrain ahead of the aircraft. An alert is sounded if the obstacle or terrain is above a clearance plane positioned ahead of the aircraft.

Abstract: A novel intelligence support of an aircraft crew and the like employing videocards with pictogram signs indicating corrective action to be taken by the crew for emergency flight situations and monitoring the achieving of such corrective action.

Abstract: The apparatus of this invention includes a pilot-induced oscillation (PIO) detector, a PIO compensator and a pilot input modifier. The PIO detector is coupled to receive aircraft state signal including the aircraft's pitch, roll and yaw attitudes. The PIO detector is also coupled to receive pilot control signal generated by the aircraft's pilot by manipulation of flight control instruments. Preferably, the PIO detector includes a feature calculator and a discriminator. Based on the aircraft state signal and the pilot control signal, the feature calculator generates at least one feature signal indicative of whether a PIO or non-PIO condition exists in the aircraft. The feature calculator supplies the feature signal to the discriminator, that uses the feature signal to determine whether or not a PIO condition exists.

Abstract: The present invention provides a device for indicating an operating point of an aircraft comprising a sensor to measure air speed and a sensor to measure vertical acceleration. The device also comprises a processor in communicative connection with each of the airspeed sensor and the vertical acceleration sensor. The processor is also in communicative connection with a display. The display presents an operating envelope diagram of the aircraft. The display also displays the current operating point of the aircraft relative to the operating envelope diagram. The present invention also provides a method for indicating an operating point of an aircraft in which the operating envelope diagram and the measured operating point of the aircraft are displayed upon the same display.

Abstract: A method and apparatus for use with an aircraft autopilot to prevent an aircraft part from striking the ground during near ground maneuvers by employing a protection circuit between the outer loop and the inner loop of the control chain between the autopilot and the control surface, the prevention circuit producing an output signal when there is a possibility of ground strike which output signal operates to reduce the control surface command signal from the inner loop to the control surface and thus be rapidly responsive to aircraft attitude changes that could produce ground strike.

Abstract: Method and apparatus for measuring the alertness level of the flight crew of an aircraft and raising it when necessary. The system also detects departures from the planned flight profile and provides aural warning.

Abstract: A terrain awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as a terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.

Abstract: An apparatus (700) for inhibiting operation of an electronic device (702) during take-off and landing of an aircraft (802) has a sensor (704) that measures a lateral acceleration. A control circuit (706) is coupled to the sensor (704) and has an output (708) coupled to the electronic device (702).