Abstract: The system for presenting visual features to a pilot of an aerial vehicle contains a flight display. The flight display includes a display screen, a programmable device, an input device, and a memory. A plurality of visual features is contained in the memory. A plurality of feature characteristics is contained in the memory. Each of the feature characteristics is linked to at least one of the features. An environmental device communicates with the input device. The environmental device inputs an approximately present environmental condition of the aerial vehicle to the input device. The programmable device compares the approximately present environmental condition to the feature characteristics to determine which of the features stored in the memory to display on the flight display.

Abstract: In distance maps used in order to facilitate the navigation of craft such as an aircraft, the distances estimated take into account obstacles to be circumvented but not the maneuverability of the craft. The adaptation route required by the craft in order to take the right direction is not taken into account so that certain distance estimates for accessible points located in the neighborhood of the craft are unrealistic. In order to make a distance map more realistic, it is proposed that an obstacle of concave shape associated with the craft be added behind the position of the craft, forcing the estimations of distances to be circumvented an area that is inaccessible to the craft for reasons of maneuverability.

Abstract: The system contains a receiver in communication with a programmable device. The receiver receives a first horizontal distance from the aircraft to a threshold of the runway, an angle of a glide path, and a threshold crossing height. The programmable device determines a projected ground distance from the aircraft to the threshold. The programmable device determines a projected ground distance from the threshold to a glide path intercept point. The programmable device determines a vertical value along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point. The programmable device determines a synthetic altitude above runway for the aircraft.

Abstract: A flight deck display system for an aircraft includes a processor architecture configured to receive aircraft instrument data (e.g., altimeter or airspeed) and position data for the aircraft and, based upon the instrument data and the position data, generate image rendering display commands. The system also includes a display element configured to receive the image rendering display commands and, in response thereto, to render a graphical instrument tape. The instrument tape includes a graphical representation of a scrolling altitude or airspeed range that dynamically scrolls in response to changes in the altitude/airspeed data, along with a graphical representation of a position-dependent altitude/airspeed clearance element that conveys an altitude/airspeed restriction for an approaching geographic position of the aircraft. The content of the position-dependent clearance element is influenced by the position data.

Abstract: Method and system for analyzing and processing information on one or more aircraft flight paths, using a four-dimensional coordinate system including three Cartesian or equivalent coordinates (x, y, z) and a fourth coordinate ? that corresponds to a distance estimated along a reference flight path to a nearest reference path location corresponding to a present location of the aircraft. Use of the coordinate ?, rather than elapsed time t, avoids coupling of along-track error into aircraft altitude and reduces effects of errors on an aircraft landing site. Along-track, cross-track and/or altitude errors are estimated and compared with a permitted error bounding space surrounding the reference flight path.

Abstract: A flight instrument, having an electronic display, is configured to fit within a standard instrument mount and within an array of standard instrument mounts. The instrument has the ability to emulate any standard or other instrument. This instrument can share its installed optional sensors with other instances of itself that do not include the optional sensors by way of network interfaces. The instrument can contain emulation for all standard instruments and have a menu to select which to display.

Abstract: Systems and methods for managing a visual display in a ground proximity warning system. In one embodiment, a system includes at least one aircraft sensor system operable to acquire aircraft data and a ground proximity warning computer coupled to the aircraft sensor system that is operable to process the aircraft data to generate ground proximity warning data corresponding to a sensed ground obstruction. An indicating system includes at least one visual display device that is operable to display terrain elevations and to display a visual symbol corresponding to at least one of the ground obstructions, wherein at least one of the computer and the visual display device is controllable to selectively alter an appearance of the visual symbol relative to the terrain elevations.

Abstract: A system and method uses light signals to detect and display the position of an airborne vehicle, such as a helicopter, during takeoff or landing or low speed, low altitude operation. A transmitter on the vehicle emits light signals while an optical receiver retrieves reflected light signals. Using light detection and ranging techniques, various parameters, such as altitude, ground speed and relative wind, are calculated based on the Doppler shift within the reflected light signals. The signals are transmitted in three different directions to facilitate the measurements of different Doppler shifts. The parameters are also displayed on a screen or other visual device within the vehicle.

Abstract: Systems and methods are provided for using a display system for a first vehicle. The system includes a processor adapted to receive data representative of a position of the first vehicle and operable, in response thereto, to supply one or more image rendering display commands and a display device coupled to receive the image rendering display commands and operable, in response thereto, to simultaneously render (i) a first vehicle icon representing the position of the first vehicle and (ii) one or more altitude lines, wherein each altitude line extends at least partially across the image and represents a vertical distance from the first vehicle.

Abstract: The flight display includes a vertical terrain profile display having a format that includes a side-on vertical terrain profile comprising a plurality of color filled vertical alerting bands representing areas of terrain that are within defined limits above and below the airplane altitude. A symbol is positioned relative to the side-on vertical terrain profile for representing an altitude and position of the aircraft. Displays of range and altitude are positioned relative to the symbol and side-on vertical terrain profile in predetermined increments. In another broad aspect the side-on vertical terrain profile includes a plurality of color filled horizontal absolute altitude bands representing the absolute altitude of the terrain. These displays may be accompanied by nested color filled blocks representing weather hazards and/or terrain alerting prediction icons.

Abstract: This device furnishes a map for assisting navigation at low-level altitude while representing the zone flown over with points shown in false colors and/or textures or symbols corresponding to the vertical speeds needed to fly over them.

Abstract: A method, computer software product, and system to generate altitude callouts according to proximity to a runway at an airport or heliport includes determining whether the helicopter is flying in proximity to the runway and automatically selecting an altitude threshold increment set based upon the determination. The threshold increment set including a plurality of altitude threshold values. A calculated terrain clearance value is calculated for each of the plurality of altitude threshold values. A suitable warning is automatically generated according to the comparison. Selecting an altitude threshold increment set includes selecting one of the group consisting of first altitude threshold increment set including a plurality of higher altitude threshold values and a second altitude increment set including the plurality of higher altitude threshold values and further including a plurality of lower altitude threshold values.

Abstract: A method of estimating the airspeed of an aircraft during low airspeed conditions includes measuring a negative impact pressure using a pitot-static probe on the aircraft. Then, the method includes estimating a non-zero airspeed of the aircraft as a function of the measured negative impact pressure.

Abstract: Apparatus and methods for enhancing the accuracy of height above ground measurements in which the registration error between successive images taken of the terrain over which an aircraft is flying is minimized, the earlier image having first been transformed according to measurements of the aircraft linear and angular velocities, the focal length and attitude of the image sensor, and an initial, coarse height estimate. By an iterative process, a more accurate height estimate is obtained.

Abstract: A method and apparatus is disclosed for displaying a dynamic parameter of an aircraft, the apparatus comprises a display unit receiving a display signal and displaying a scale that changes dynamically and non-linearly in accordance with a selected display algorithm, the display unit further displaying a pointer pointing to said scale in accordance with a reading of said dynamic parameter, thereby emphasizing a range of said reading of said dynamic parameter.

Abstract: An improved system and methods for correlating an interrogation-based air traffic surveillance intruder, such as an Traffic alert and Collision Avoidance System (TCAS) intruder, and a GPS-based air traffic surveillance target, such as an Automatic Dependent Surveillance Broadcast (ADS-B) target to minimize or eliminate the display of two symbols for the same intruder/target on the CDTI of an aircraft. The method comprises the steps of receiving ADS-B data at a processing unit and calculating select component deltas for the ADS-B data versus an entry in a TCAS intruder file. Progressive weights are assigned to the deltas and the progressive weights are summed, resulting in a total confidence score. Total confidence scores of ADS-B target and TCAS intruder pairs are compared to determine correlation between the ADS-B target and the TCAS intruders.

Abstract: Methods and apparatus are provided for generating an integrated vertical situation display. The method comprises generating a profile view frame, producing a first profile view of a first track of the vehicle in the profile view frame beginning at about a current position of the vehicle and ending at about a predetermined location, and extending a second profile view of a second track of the vehicle from about the predetermined location. The apparatus comprises a display configured to display a profile view frame and a specially configured processor coupled to the display. The processor is configured to produce a first profile view relating to a first track of the vehicle beginning at about a current position of the vehicle and ending at a predetermined location, and generate a second profile view relating to a second track of the vehicle extending from about the predetermined location.

Abstract: A system and method for advanced warning of severe weather for general aviation aircraft is presented. An aircraft includes an onboard weather tracker which monitors atmospheric condition changes. The weather tracker uses data from an onboard barometric altimeter and a GPS device to calculate air pressure changes in order to identify when the aircraft is flying into a low-pressure zone. The weather tracker uses the air pressure's rate of change and the aircraft's speed to determine the criticality of a situation and appropriately notifies a pilot. The weather tracker provides the pilot with local airport information and alternative flight pattern information per the pilot's request.

Abstract: A method and system for transmitting engine control data to or from the engine control unit of an engine. The system includes a local communication unit capable of establishing a wireless communication link with a remote communication unit and a link for transferring data between the local communication unit and the engine control unit. In operation, a wireless communication link is established between the local communication unit and the remote communication unit. Engine control data is transferred between the local communication unit and the engine control unit and transmitted between the local communication unit and the remote communication unit via the wireless communication link.

Abstract: Pilot error is reduced and auto pilot operation is improved by the addition of capture information to the information provided on a cockpit display. The capture information, such as, for example, capture start point, last point to initiate capture, trajectory during capture, and capture overshoot region provide information to the pilot regarding the correct initiation of capture. Pilots are therefore better able to evaluate the ongoing performance of the automation or auto pilot systems and to trust that the auto pilot is functioning as desired. Furthermore, the pilot operating the aircraft in manual mode receives guidance based on this information to better know when to initiate capture of the assigned altitude or vertical path.

Abstract: A method of generating a synthetic pressure altitude is disclosed. The method includes providing a static air temperature to a data processing device. The method also includes providing a wind velocity, a ground velocity, and a geometric altitude to the data processing device. Further, the method includes performing a numerical integration based on the static air temperature, the wind velocity, the ground velocity, and the geometric altitude. The wind velocity and the ground velocity are used to estimate pressure gradients not included in a static air column model.

Abstract: A method for detecting an inaccurate barometric pressure adjustment setting on a barometric altimeter is described. The method includes receiving a barometric corrected altitude from the altimeter, receiving an altitude from a global positioning satellite (GPS) system, comparing the barometric corrected altitude with the altitude received from the GPS system, actuating an alarm if the altitudes differ by an amount larger than a threshold value, the threshold value being dependent upon one or more of the received altitudes.

Abstract: An integrated cabin pressure control system valve that uses a dual, redundant channel electronic control unit for both control of the valve and to supply alarm, indication, and control signals to the aircraft's avionics system. Each channel in the electronic control unit includes an instrumentation and control circuit that uses multiple, dissimilar sensors and signals for warnings, indications, and controls. This configuration reduces the likelihood for a common mode failure that could result in a postulated gradual decompression without indication event.

Abstract: A device for enhancing altitude awareness in an avionics display is disclosed. The device includes an altitude indicator that displays a current altitude on the avionics display. A scrolling display of altitude levels is displayed with the altitude indicator on the avionics display. The scrolling display includes a plurality of scaled numbers that represent predetermined intervals of altitude levels surrounding the current altitude. The scrolling display also includes a non-numeric graphic construct that is displayed adjacent the plurality of scaled numbers. The graphic construct has first and second substantially mirror-image portions that are positioned on first and second opposing sides of the plurality of scaled numbers. A controller causes the altitude indicator to display the current altitude on the avionics display.

Abstract: An apparatus, system, method and computer program product to verify proper operation of an aircraft altimetry system. Aural and visual alerts may optionally be provided when a fault in the altimetry is detected.

Abstract: A process and apparatus are disclosed for estimating changes in the vertical mode of flight of an aircraft. The process and apparatus utilize a vertical motion detection method (VMD) and a modified altitude post processor logic to reduce the time delay for determination of vertical mode of flight changes.

Abstract: A system and method for providing highly accurate measurements of the altitude above ground level (AGL) of an aircraft flying over local terrain. A current AGL altitude of the aircraft over local terrain is obtained by activating a radar altimeter on the aircraft for a single short duration or pulse. A mean sea level (MSL) elevation of the local terrain is determined by identifying the terrain from the then-current aircraft geographical position coordinates and utilizing known terrain topography data. The actual MSL altitude of the aircraft can then be determined. An uncorrected MSL altitude of the aircraft is then determined from conventional static air pressure measurements and the difference between the actual MSL altitude and the uncorrected MSL altitude of the aircraft yields a local barometric correction factor for use in determining MSL altitude measurements of the aircraft as the aircraft flies over and continues its flight away from the local terrain.

Abstract: The indicator (1A) according to the invention comprises means (13) for determining first and second target values respectively of a variable and of its derivative with respect to time, and display means (5, 6, 7) which depict on a display screen (7) a means of indication (14) of the first target value, which is arranged in such a way as to indicate this first target value on a graduated scale (8), and a means of indication (16B) of the second target value which is associated at least with an indicator element (11) indicating said derivative so that, when the latter points toward said means of indication (16B), said variable of the aircraft becomes equal to and remains equal to said first target value and said derivative is equal to said second target value.

Abstract: In an altitude and vertical speed indicator for aircraft, an altitude indicator includes a graduated scale vertically mobile past a fixed marker and a vertical speed indicator includes a pointer rotatable about the point of intersection of a straight line segment through the fixed marker and a straight line segment through the pointer and pointing towards the mobile scale. The angle defined by the fixed marker and the pointer is representative of the vertical speed value.

Abstract: The angle of attack of an airfoil moving through the air can be detected and a display provided electronically through use of an all-solid-state system powered by a D.C. source. A wind vane mounted on one end of a shaft is exposed to the airflow while a windowed mask is provided at the other end of the shaft. By providing an appropriate array of openings in the mask, and a series of associated optical transmitters and receivers on opposed sides of the mask, extremely fine sensitivity can be provided in detection of angle of rotation of the mask and thus in the angle of rotation of the vane. The angle of the vane is directly established by the angle of attack. The detected angle of attack is then displayed on a vertically oriented light bar on the instrument panel, for instance in a light aircraft.

Abstract: A method, an apparatus and a computer program product are provided for accurately determining the vertical speed of an aircraft in a manner independent of signals provided by an air data computer, an inertial reference system and an inertial navigation system. Initially, a first vertical velocity of the aircraft is determined based upon a pressure altitude value associated with the aircraft. A second vertical velocity of the aircraft is also obtained from a GPS receiver carried by the aircraft. The first and second vertical velocities are then combined to determine the vertical speed of the aircraft. In this regard, the first and second vertical velocities are combined by complimentarily filtering the first and second vertical velocities. More particularly, the first vertical velocity is typically low pass filtered to remove high frequency noise that is attributable to the relatively low resolution of the first vertical velocity value.

Abstract: The invention discloses a method of preventing potentially hazardously misleading attitude data. The method includes deriving a value for a leveling parameter from inertial and velocity data, monitoring the leveling parameter for a characteristic indicative of producing potentially hazardously misleading attitude data, and disregarding at least some air data if the characteristic is detected. The computer readable medium contains instructions to cause an attitude heading computer to perform the steps of (1) deriving a leveling parameter from velocity data and inertial data; (2) monitoring the leveling parameter for a characteristic indicative of producing hazardously misleading attitude data; and (3) not accounting for at least some velocity data in leveling algorithms if the characteristic is detected. The invention also includes a second embodiment of a method of preventing potentially hazardously misleading attitude data.

Abstract: A new and useful apparatus for automatically correcting for the actual altitude of an aircraft, under non-ISA temperature conditions is provided. An apparatus according to the present invention can be particularly useful in automatically providing altitude correction output to a navigation and control system for an aircraft at selected points along an aircraft flight path where terrain clearance under non-ISA temperature conditions is an important operational parameter.

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: Indicator of a variable for an aircraft. The indicator (1A) according to the invention comprises means (13) for determining first and second target values respectively of a variable and of its derivative with respect to time, and display means (5, 6, 7) which depict on a display screen (7) a means of indication (14) of the first target value, which is arranged in such a way as to indicate this first target value on a graduated scale (8), and a means of indication (16B) of the second target value which is associated at least with an indicator element (11) indicating said derivative so that, when the latter points toward said means of indication (16B), said variable of the aircraft becomes equal to and remains equal to said first target value and said derivative is equal to said second target value.

Abstract: A combined altitude and height-above-ground indicator for an aircraft enables the altitude and the height of an aircraft to be displayed simultaneously. The combined indicator includes a first sensor and a second sensor which respectively sense altitude and height above ground, means for processing the information supplied by the first and second sensors, and means for displaying the sensed altitude and height-above-ground information by superimposing the altitude and height-above-ground information on the same scale against a pointer. The scale includes a transparent first part which represents a pressure-altitude display, and a second part which is a mask positioned under the first part so that it masks the background of the indicator for altitude levels which are below the measured height above ground.

Abstract: A combined altitude and height-above-ground indicator for an aircraft includes a first sensor and a second sensor which respectively sense altitude and height-above-ground, a processor for processing the information supplied by the first and second sensors, and a display for displaying the altitude and height-above-ground information, showing the two items of information against each other, on the same scale against at least one pointer.

Abstract: An integrated flight control indicator for providing visual information indicative of aircraft flight parameters has a sky arc and an earth arc which are visually distinguishable from one another. The sky arc and the earth arc cooperate to generally define a circle wherein the relative lengths of the sky arc and the earth arc indicate the pitch of the aircraft. A horizon line extends approximately between the two intersections of the sky arc and the earth arc so as to provide a visual indication of the roll of the aircraft. Other indicia are provided for indicating radar or barometric altitude, vertical speed, heading, ground track, minimum altitude break, etc. Thus, the present invention provides a visual indication suitable for use in instrument panel displays, heads-up display, and helmet-mounted displays.

Abstract: An integrated flight control indicator for providing visual information indicative of aircraft flight parameters has a sky arc and an earth arc which are visually distinguishable from one another. The sky arc and the earth arc cooperate to generally define a circle wherein the relative lengths of the sky arc and the earth arc indicate the pitch of the aircraft. A horizon line extends approximately between the two intersections of the sky arc and the earth arc so as to provide a visual indication of the roll of the aircraft. Other indicia are provided for indicating radar or barometric altitude, vertical speed, heading, ground track, minimum altitude break, etc. Thus, the present invention provides a visual indication suitable for use in instrument panel displays, heads-up display, and helmet-mounted displays.

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 method for calibrating a pressure-sensing altitude sensor of an aircraft while the aircraft is in flight. The method includes the steps of obtaining a set of reference atmospheric pressures as a function of height above a base station by affixing a reference pressure sensor to a balloon. As the balloon is released into the atmosphere, the reference sensor continuously measures the atmospheric pressures and transmits the data back to the base station while a ground-based radar disposed adjacent the base station measures the height of the balloon. An aircraft flying in a vicinity of the base station can calibrate its pressure-sensing altitude sensors by measuring the atmospheric pressure outside the aircraft and its geometric height relative to the base station and then comparing the pressure measurements with corresponding reference pressure values at a geometric height that is substantially that same as the geometric height of the aircraft.

Abstract: An altimeter is disclosed which includes an arcuate top portion and an arcuate bottom portion. Side portions connect the arcuate top portion to the arcuate bottom portion. The side portions have a curvature less than a curvature of the top portion or the bottom portion, thus giving the altimeter a narrower footprint while preserving important features of conventional dial-type altimeters. An indicator moves about the perimeter of the altimeter based on altitude information, thus displaying altitude of the aircraft.

Abstract: A precision equivalent landing system. In one embodiment, a position determining system is coupled to an aircraft. The position determining system generates lateral position information of the aircraft with respect to a landing approach path. An altimeter is also coupled to the aircraft. The altimeter generates vertical position information of the aircraft with respect to the landing approach path. A graphic display disposed within the aircraft concurrently displays a visual representation of the lateral position of the aircraft with respect to the landing approach path and the vertical position of the aircraft with respect to the landing approach path. In so doing, the present invention provides both relative position and altitude of an incoming aircraft with respect to a landing approach path. Thus, the present invention provides a precision equivalent landing system without requiring the equipment and expense associated with ILS or FAA MLS precision landing systems.

Abstract: The present invention provides ground proximity warning system and method for aircraft, particularly rotary wing aircraft such as helicopters. The warning system generally includes a barometric altitude rate detector, such an altimeter and a rate circuit, disposed to detect the rate of change of the barometric altitude of the aircraft. A controller is coupled to the detector for receiving the barometric altitude rate signals and adjusting the signals based on the ground effect from the main rotors when the aircraft is near the ground. Typically, the controller decreases the barometric altitude rate signals to compensate for the apparent increase in barometric altitude rate caused by ground effects. This reduces the number of nuisance warnings that may otherwise occur during takeoffs, landings or other low altitude flight conditions.

Abstract: An ambiguous dial indicator intuitively communicates the relative value of setpoints to an operator. The ambiguous dial indicator includes an ambiguous scale and a pointer or needle. The setpoints are represented by "bugs" which are adjacent to the ambiguous scale. The bugs are limited to a predetermined range about the pointer such that when a setpoint is outside of the predetermined range the associated bug is limited to an edge of the range. When several setpoints are outside of the predetermined range the several associated bugs saturate or park at the edges of the range. The invention is particularly useful in head-up displays and helmet mounted displays.

Abstract: Disclosed is a collision avoidance device with reduced energy balance for aircraft, in particular for avoiding collision with the ground. This device comprises means for the geographical localization of the aircraft, a database containing a description of safety altitudes, means for the construction of an air floor about the vertical passing through the aircraft, the altitude of the floor being greater than or equal to the safety altitudes about this vertical, means for predicting the air position of the aircraft, means to compare this position with the air floor, means for the computation of avoidance paths and means to determine the energy balance of each of the computed paths. Application to equipment for aircraft, notably for civilian airliners.

Abstract: The invention relates to an audible altimeter for use by parachutists. The altimeter comprises a sensor means 6 for sensing ambient air pressure, an electronic processor 5, a sounder device 4 and control buttons 2,3. The electronic processor 5 is programmed to determine the height of the altimeter above ground level and send said signals to said sounder device 4 during the parachutist's descent causing said sounder device 4 to emit a first audible signal at a first predetermined height above ground level and a second audible signal at a second predetermined height.

Abstract: An artificial horizon altitude warning system is provided for helping to prevent a controlled flight of an aircraft into the ground. The artificial horizon altitude warning system comprises an altimeter for gathering altitude information about the aircraft and generating an altitude signal; a laser assembly for producing a light in a cockpit of the aircraft; and a controller for receiving the altitude signal and for positioning the light in the cockpit to form an artificial line based on the altitude signal, the artificial line being positioned so as to be disposed along tin arcuate length corresponding to the location of an actual horizon as viewed by a pilot of the aircraft.

Abstract: The invention is a process and a device for determining an estimation of the altitude of an aircraft from at least two independent measurements of the altitude, by polling. The aircraft must include at least one inertial reference system. A signal representing a first or second derivative of the altitude is diverted from the inertial reference system, polling is undertaken on the magnitudes of like order deduced from the independent altitude measurements and from the derivative of the altitude, respectively, and an integration operation is undertaken so as to obtain the altitude estimation.

Abstract: One side of a primary flight display has a vertical airspeed scale, a round dial display, and a window. The round dial display provides global or macro airspeed information and a digital display of a present airspeed value is provided in the window. A vertical altitude scale is located on a second side of the PFD with a second round dial located along the altitude scale. The second dial is configured to provide a predetermined amount of rotation of the pointer for a predetermined change in altitude. A second window located along the altitude scale provides a digital present value of altitude.