Honeywell International Inc.

Steve C Johnson

Yasuo Ishihara

Kevin J Conner

Gang He

Thea Lynn Feyereisen

Gary Ostrom

Glen Burlingame

Esko Mannisto

James Ehlers

Ivan Sandy Wyatt

Charles D Bateman

Santosh Mathan

C Don Bateman

Mark Giddings

Robert A Champion

Gary A Ostrum

Courtney Ashford

Gary A Ostrom

Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing an altitude parameter and a safety envelope for a designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter is decreased. Otherwise, an alert is generated if the aircraft is outside of the safety envelope.

Runway landing alert system and method

Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing a Runway Awareness Advisory System (RAAS) envelope for the designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter of the RAAS envelope is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter of the RAAS envelope is decreased. Otherwise, an alert is generated if the aircraft is outside of the RAAS envelope.

A system and method of shifting a premature descent protection envelope for an aircraft has been developed. First, a premature descent protection envelope (PDP) is determined including a first boundary at a first distance from the runway. Next, a nominal approach path is determined for approaching the runway and an approach path angle. Also, a flight path angle of the aircraft is determined. The first boundary is shifted in an upward direction from the runway in response to the aircraft being below the nominal approach path, and the flight path angle being greater than the nominal approach path angle.

System and method for modulating premature descent protection envelope

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.

Systems and methods for monitoring low speed of a rotorcraft

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.

A method of predicting a parameter for an aircraft includes detecting an actual approach profile of the aircraft. The actual approach profile includes an actual approach angle. The method also includes comparing, by a processor, the actual approach profile to a predetermined approach profile to determine a difference between the actual and predetermined approach profiles. The predetermined approach profile includes a predetermined approach angle. The method further includes determining, by the processor, an effective approach angle by combining the actual approach angle and the predetermined approach angle according to a factor that varies based on the difference between the actual and predetermined approach profiles. Moreover, the method includes determining, by the processor, the predicted parameter based on the effective approach angle.

Method and system for determining effective approach angle and predicting aircraft landing distance

A system and method are provided that improve upon existing aircraft display systems by generating and updating an overrun image that may be overlaid on a variety of panoramic and landscape images on a display device. The overrun image displays stopping locations for all relevant available stopping devices, as determined from the far end of the selected runway. In addition, the aircraft display system determines an advisory zone on the selected runway and presents limited symbols and images in and near the advisory zone that indicate distances and relevant information.

System and method for displaying runway overrun information

An enhanced runway awareness system and method directed to reducing audible alerts during runway selection is provided. The runway awareness system includes a navigation system, an audio system, and a control module. The control module receives and processes, from the navigation system, aircraft state data and runway position and location data. The control module determines that (a) the aircraft is approaching a first runway, and commands the audio system to emit an approach alert associated with (a); subsequent to commanding the audio system to emit the approach alert associated with (a), the control module prohibits the audio system from emitting an 'on runway' alert associated with (a) responsive to determining that (b) the aircraft is on the first runway.

Aircraft systems and methods for managing runway awareness and advisory system (RAAS) callouts

A method is provided for monitoring a landing approach of an aircraft. The method includes receiving instrument landing system (ILS) signals; determining a glideslope deviation from the ILS signals; disabling, when the glideslope deviation is less than a first predetermined threshold, at least one glideslope alert function; evaluating a current glideslope condition by comparing a designated glideslope angle to a glideslope check value; and re-enabling the at least one glideslope alert function when the glideslope check value differs from the designated glideslope angle by more than a second predetermined threshold.

Aircraft systems and methods for providing landing approach alerts

Systems and methods for intelligently alerting the flight crew of a cabin depressurization. An example system includes a cabin altimeter that generates a cabin pressure value, an alerting device, such as a speaker system and a processing device in data communication with the cabin altimeter and the alerting device. The processing device determines if there is a problem with the cabin pressure received from the cabin altimeter, determines rate of change of the cabin pressure, and sets at least one of an alert volume or an alert frequency based on the cabin pressure and the rate of change of the cabin pressure if it was determined that a problem exists with the cabin pressure. The processing device also issues a cabin depressurization alert over the alerting device based on at least one of the set alert volume or alert frequency, if there is a problem with the cabin pressure value.

Cabin altitude alerting systems and methods

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.

System and method for runway selection through scoring

A method for providing alerts or indications to an aircrew of an aircraft that is in-flight and approaching a destination airport includes receiving an aircrew runway selection from the aircrew of the aircraft, automatically generating a probable runway selection by the aircraft, and determining a position of the in-flight aircraft with reference to a threshold point. If the aircraft is prior to the threshold point, the method includes generating alerts and indications to the aircrew based solely on the received runway selection into the FMS from the aircrew of the aircraft and not on the automatically-generated probable runway selection from the aircraft. Alternatively, if the aircraft is past the threshold point, the method includes generating alerts and indications to the aircrew based solely on the automatically-generated probable runway selection from the aircraft and not on the received runway selection into the FMS from the aircrew of the aircraft.

Systems and methods for destination selection for vehicle indications and alerts

A method for managing a premature descent envelope during descent of an aircraft is provided. The method receives glideslope deviation data by an instrument landing system (ILS) onboard the aircraft; compares, by the ILS, the glideslope deviation data to an acceptable band of glideslope deviation values; and when the glideslope deviation data is within the acceptable band, expands, by a terrain awareness and warning system (TAWS), the premature descent envelope to produce an increased premature descent envelope for the aircraft.

Methods and apparatus for managing a premature descent envelope during descent of an aircraft

Systems and methods for improving sink rate alerting for rotary wing aircraft. In one example, the system includes a radio altimeter that produces an altitude value, a processor that is in signal communication with the user interface device and the radio altimeter. The processor receives an altitude value, a position value for the aircraft and landing zone (LZ) information. The processor determines if the aircraft is on an approach to land at an LZ that is raised above surrounding terrain based on the received position value and LZ information. The processor receives sink rate information for the aircraft and generates a sink rate alert based on the received sink rate information and the aircraft altitude value if the sink rate information is greater than a sink rate value adjusted according to the LZ information. An output device outputs the generated sink rate alert. The LZ information includes an altitude value.

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North Bend, WA, United States of America

Steve C Johnson