Abstract: A vehicle system is provided. The system includes a processor configured to receive data representative of a current attitude and a desired attitude and to generate display signals associated with the current attitude and the desired attitude. The system further includes a display device configured to receive the display signals and operable to selectively render an image including roll angle alert symbology. The roll angle alert symbology includes a first curved arrow.

Abstract: A system and method is provided for controlling the speed of an aircraft with a speed brake during landing. The system includes a speed brake control system and a speed brake controller coupled to the speed brake control system for arming the speed brake. An alert generator is coupled to the speed brake controller for generating an alert when the speed brake is not armed.

Abstract: A system and method for passively detecting aircraft wingtip strikes includes generating a digital base map represented by a plurality of aerodrome cells. A numeric value representative of the specific wingtip is assigned to each of the aerodrome cells. An index count array is generated that has a separate entry for each numeric value. A digital aircraft structure representative of an aircraft is generated, and is represented by a plurality of aircraft cells. A determination is made as to whether a portion of the aerodrome cells are or would be replaced with the plurality of aircraft cells. Each numeric value of the aerodrome cells that are or would be replaced is counted to determine a replacement count associated therewith and that is entered into the separate entry in the index count array for that numeric value. One or more potential aircraft wingtip strikes are detected based on the replacement counts.

Abstract: A method and system are provided for generating a low airspeed warning in an aircraft. This method creates a scale factor that is a factor of engine thrust and aircraft altitude. A low airspeed threshold is determined that varies according to the aircraft altitude with respect to a predetermined altitude band and the engine thrust with respect to a predetermined engine thrust band. A low airspeed alert is generated in response to the determination of the low airspeed threshold. This method provides a pilot with earlier knowledge of low airspeed conditions when the aircraft is in a target altitude band, increasing the pilot's response time and thereby enhancing overall aircraft safety.

Abstract: A system and method are provided for modifying the position or shape of a premature descent protection envelope with regard to a runway when an aircraft making an approach to the runway is below the nominal approach path and has a flight path angle greater than the nominal approach path angle.

Abstract: A system and method for selecting a runway, comprises retrieving runway feature data and aircraft data including aircraft heading with respect to the bearing of first and second runways. Runway boundary envelopes are created for each of the first and second runways, each having a predetermined score. A total score for each of the first and second runways is compared to determine which of the runways is selected.

Abstract: A system and method for passively detecting aircraft wingtip strikes includes generating a digital base map represented by a plurality of aerodrome cells. A numeric value is assigned to each of the aerodrome cells that is representative of the specific wingtip strike threat associated with that aerodrome cell. An index count array is generated that has a separate entry for each numeric value. A digital aircraft structure is generated that is representative of an aircraft, and is represented by a plurality of aircraft cells. A portion of the aerodrome cells are replaced with the plurality of aircraft cells. Each numeric value of the aerodrome cells that are replaced is counted to determine a replacement count associated therewith and that is entered into the separate entry in the index count array for that numeric value. One or more potential aircraft wingtip strikes are detected based on the replacement counts.

Abstract: Systems and methods for verifying that the flight crew has not made an error in entering takeoff flight performance data into the flight management system (FMS) using the electronic flight bag (EFB). The EFB includes a user interface that receives basic flight plan information and a processor. The processor automatically receives calculated takeoff performance data based on a previously entered basic flight plan, automatically receives user-entered takeoff performance data from a flight management system (FMS) located on a host aircraft, automatically compares the calculated takeoff performance data to the received takeoff performance data, and generates an entry error indication, if the comparison indicates that at least a portion of the entered takeoff performance data does not match the calculated takeoff performance data. An output device outputs the generated entry error indication.

Abstract: A system and method to display, when within an envelope of an ownship's flight path, a symbol representing wake turbulence from another aircraft based on aircraft type and flight parameters received from the other aircraft, the symbol being formatted to indicate the severity of portions of the wake turbulence. The format is modified periodically in accordance with the aircraft's flight path and a decay rate of the wake turbulence.

Abstract: A system and method are provided for alerting of remaining runway based on deceleration, following, for example, a landing or discontinued takeoff. An advisory system compares the current aircraft deceleration value to a predetermined threshold value when proceeding down the runway. If the current aircraft deceleration is less than the threshold value, the runway distance remaining callouts are triggered.

Abstract: A system and method provide an alert to a pilot of an aircraft aurally with a given volume and inflection, and/or visually with a text message which includes color, font, and pitch (size). The alert is rendered in distinct fashion for the expected and unexpected cases, e.g., an intended runway and an unintended runway. In a preferred embodiment, the alert for the intended runway is changed to a confirmation level, or one that is less likely to interfere with other information flow, while the alert for the unintended runway would be provided in a more conspicuous manner.

Abstract: Systems and methods for adjusting target approach speed for use in a “Too Fast” approach to landing condition. An exemplary system stores predefined maximum wind setting and a predefined reference speed and a pilot set bug speed value. A processing device sets a target speed equal to the bug speed, if the bug speed is less than the reference speed plus a value associated with a predefined maximum wind setting, and sets the target speed equal to the reference speed plus the max wind added value, if the manual bug speed is not less than the reference speed plus the max wind added value. An output device outputs an alert if the received aircraft speed is greater than the set target speed plus a predefined error value when the received aircraft location is within a threshold value of a touchdown point.

Abstract: A system and method to display, when within an envelope of an ownship's flight path, a symbol representing wake turbulence from another aircraft based on aircraft type and flight parameters received from the other aircraft, the symbol being formatted to indicate the severity of portions of the wake turbulence. The format is modified periodically in accordance with the aircraft's flight path and a decay rate of the wake turbulence.

Abstract: A vehicle heat pump air-conditioning system is provided, which is capable of securing a temperature linearity characteristic during dehumidifying heating, slowing progression of a frost formation on an exterior evaporator during heating, and stably continuing a heating operation while suppressing variations in a blowout temperature. In a cooling refrigeration cycle (14) becoming a base, an interior condenser (8) disposed in a HVAC unit (2) is connected to an exterior condenser (10) in parallel via switching means (15), an exterior evaporator (17) is connected to first decompression means (12) and an interior evaporator (7) in parallel via second decompression means (16), a heating heat pump cycle (18) is configured, the first decompression means (12) and the second decompression means (16) are on-off valve function attached decompression means (12, 16), and the exterior evaporator (17) and the interior evaporator (7) can be simultaneously used during dehumidifying heating and heating.

Abstract: Embodiments of a flight deck display system deployed onboard an aircraft are provided, as are embodiments of a method carried-out by a flight deck display system. In one embodiment, the flight deck display system includes a cockpit display device and a controller. The controller is configured to: (i) establish the speed trend of the aircraft over a predetermined time period; (ii) generate a primary flight display on the cockpit display device including a speed trend vector graphic representative of the established speed trend; and (iii) alter the appearance of the speed trend vector graphic in a first predetermined manner if a low speed change condition is detected during at least one of aircraft takeoff and landing.

Abstract: Systems and methods for verifying that the flight crew has not made an error in entering takeoff flight performance data into the flight management system (FMS) using the electronic flight bag (EFB). The EFB includes a user interface that receives basic flight plan information and a processor. The processor automatically receives calculated takeoff performance data based on a previously entered basic flight plan, automatically receives user-entered takeoff performance data from a flight management system (FMS) located on a host aircraft, automatically compares the calculated takeoff performance data to the received takeoff performance data, and generates an entry error indication, if the comparison indicates that at least a portion of the entered takeoff performance data does not match the calculated takeoff performance data. An output device outputs the generated entry error indication.

Abstract: Systems and methods to provide alerts when a rotorcraft is in a low airspeed condition. During takeoff or go-around, an aural alert is provided to the pilot before the aircraft slows to less than the effective translational lift speed. The aural, visual, and/or tactile alert gets the pilot's attention to manage the aircraft's airspeed before it is too late in this critical flight phase.

Abstract: An improved stable approach monitor (SAM) system provides an audible advisory to a pilot when an aircraft is on a final landing approach. More specifically, the SAM system compares a measured airspeed of the aircraft to a predetermined flap placard speed. If the measured airspeed exceeds the predetermined flap placard speed then the improved SAM system provides an audible advisory indicating the airspeed of the aircraft is too fast. Advantageously, this audible advisory should prevent the pilot from attempting to deploy the flaps at an excessive airspeed and in turn focuses the pilot's attention on the problem at hand, which would be to reduce the airspeed of the aircraft. Once the airspeed is equal to or below the predetermined flap placard speed, the improved SAM system may provide another audible advisory informing the pilot to commence deployment of the flaps.

Abstract: Systems and methods for alerting for potential tailstrike during landing. A processing device located onboard an aircraft determines whether the aircraft is in a landing operational mode. If the aircraft is determined within the landing operational mode, the processing device determines whether aircraft speed is less than a previously defined threshold speed and generates an alert signal if it is determined that the aircraft's speed is less than the previously defined threshold speed. An output device located onboard the aircraft, outputs an alert based on the generated alert signal.

Abstract: Systems and methods for selectively altering a ground proximity warning message. In an embodiment, a ground proximity warning system for a flight vehicle includes a processor that is configured to generate a look-ahead envelope that defines a region extending outwardly from the flight vehicle and to generate a terrain proximity message when the defined region intersects a terrain feature. An interface device is coupled to the processor that is operable to configure the system in a first operating mode wherein the generated terrain proximity message is selectively suppressed, and a second operating mode wherein the terrain proximity message is not suppressed.