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 an air ground detection device disposed on the aircraft to confirm whether the aircraft is on the ground or in the air. A controller is coupled to the air ground detection device and configured to move between a ground state when the aircraft is on the ground and an airborne state when the aircraft is in the air. The controller may be used for a variety of applications within the aircraft, such as disabling a ground proximity warning device when the aircraft is on the ground and enabling the warning device when the aircraft is in the air. In addition, the air ground controller may be used to signal the beginning and the end of a flight for the aircraft's flight history fault memory.

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 an air ground detection device disposed on the aircraft to confirm whether the aircraft is on the ground or in the air. A controller is coupled to the air ground detection device and configured to move between a ground state when the aircraft is on the ground and an airborne state when the aircraft is in the air. The controller may be used for a variety of applications within the aircraft, such as disabling a ground proximity warning device when the aircraft is on the ground and enabling the warning device when the aircraft is in the air. In addition, the air ground controller may be used to signal the beginning and the end of a flight for the aircraft's flight history fault memory.

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: A ground proximity warning system (GPWS) for a rotary-wing aircraft provides a warning of excessive barometric altitude loss as a function of the product of time and the terrain clearance. The warning system is only enabled during a take-off mode of flight and is disabled during other modes of flight. The mode warning logic monitors the speed of the aircraft, the terrain clearance of the aircraft as well as the position of the landing gear to enable the altitude loss warning logic. When the barometric altitude loss as a function of the time product of the terrain clearance exceeds a predetermined value, the mode switching logic switches to an approach mode of flight to disable the excessive altitude loss warning system to minimize nuisance warnings during various maneuvers including ship-to-ship and oil platform-to-oil platform flight maneuvers.

Abstract: A warning system for aircraft equipped with an autopilot system having a radio altitude hold (R/A HOLD) function and/or a barometric altitude hold (ALTITUDE HOLD) function monitors the R/A HOLD and ALTITUDE HOLD function control switches, as well as the touch-controlled steering (TCS) control to determine when the functions have been engaged. When either of the R/A HOLD or ALTITUDE HOLD function control switches are selected while the autopilot system is engaged, the system samples the radio altitude or barometric altitude at the moment that the R/A HOLD or ALTITUDE HOLD functions are selected and stores the sample as a reference or datum. The system then compares the current radio altitude or barometric altitude with the datum. Should the actual radio altitude or barometric altitude exceed the datum by a predetermined amount, a warning is generated. In order to prevent spurious warnings, the system is disabled when the touch-control steering is active.

Abstract: A warning system provides a warning to the pilot of an aircraft during a take-off mode of flight of a relatively dangerous flight condition, such as improper configuration of the flaps during a take-off mode of flight prior to the aircraft becoming airborne. In order to avoid nuisance warnings, the warning system is disabled once the aircraft becomes airborne. The warning system monitors the flap position of the aircraft as well as the airspeed and provides a warning when the flaps are improperly configured during a take-off mode of flight. Different aural warnings are provided as a function of the airspeed of the aircraft.

Abstract: A system for warning the pilot of a tactical aircraft in a tactical maneuver such as a dive of the point at which recovery must be immediately initiated to prevent the aircraft from descending below a minimum desired altitude monitors and the altitude, descent rate and pitch angle of the aircraft, and issues a voice warning when recovery must be initiated. The system also provides warnings of dangerous flight conditions during non-tactical or common route segments of a flight such as the take-off, landing and cruise segments of a flight. Circuitry responsive to the arming of the weapons of the aircraft enables the tactical warning portion of the system and disables certain functions of the non-tactical portion of the sysem that may cause false warnings to be genrated during tactical manuevers.

Abstract: A system for warning the pilot of a tactical aircraft in a tactical maneuver such as a dive of the point at which recovery must be immediately initiated to prevent the aircraft from descending below a minimum desired altitude monitors the altitude, descent rate and pitch angle of the aircraft, and issues a voice warning when recovery must be initiated. The system also provides warnings of dangerous flight conditions during non-tactical or common route segments of a flight such as the take-off, landing and cruise segments of a flight. Circuitry responsive to the arming of the weapons of the aircraft enables the tactical warning portion of the system and disables certain functions of the non-tactical portion of the system that may cause false warnings to be generated during tactical maneuvers.

Abstract: A warning system for rotary wing aircraft that monitors the altitude above ground of the aircraft and issues a warning when there is insufficient terrain clearance. The warning criteria are optimized for rotary wing aircraft and are altered as a function of landing gear position and airspeed. Two distinct warnings are given. One indicates insufficient terrain clearance and the other warns the pilot if he attempts to land with the landing gear up. Logic circuitry is provided to modify the criteria necessary to generate a warning, and to inhibit certain warnings, as required by the mode of operation of the aircraft.

Abstract: A warning system for aircraft compares the rate of descent of the aircraft with its altitude above ground after take-off, and generates warning if the aircraft is experiencing an excessive descent condition for the radio altitude at which the aircraft is flying. The position of the landing gear, the speed of the aircraft and the engine power are mointored to enable the system only during the take-off or missed approach phases of operation in order to minimize false warnings during other phases. The relationship between radio altitude and descent rate required to generate a warning is optimized for small, high performance aircraft such as fighter or attack aircraft.

Abstract: A system that warns the pilot of an aircraft performing low level maneuvers of a dangerous flight profile monitors the altitude of the aircraft above ground, and provides a first specific warning to the pilot if the altitude of the aircraft drops below a predetermined minimum altitude above ground. The system further monitors the roll angle and descent rate of the aircraft to provide a second specific warning if the descent rate of the aircraft exceeds a predetermined rate determined by the roll angle of the aircraft if the aircraft is below a second predetermined altitude above ground.

Abstract: A system for providing a voice warning to the pilot of a fighter/attack aircraft when the aircraft is landing with the landing gear up monitors the radio altitude, airspeed and engine power of the aircraft and provides a predetermined voice warning if the landing gear is not down when the airspeed is less than a predetermined speed, for example, approximately 200 knots, the radio altitude is less than a predetermined altitude, for example, approximately 100 feet, and the engine is not developing take-off power.

Abstract: A warning system for rotary wing aircraft compares the accumulated altitude loss after take-off of the aircraft with its altitude above ground, and generates a warning if the altitude loss is excessive for the altitude above ground at which the aircraft is flying. The position of the landing gear, the speed of the aircraft and its altitude enable the system only during the take-off and missed approach phases of operation in order to minimize nuisance warnings during other phases. The relationship between radio altitude and altitude loss required to generate a warning is optimized for rotary wing aircaft such as helicopters.

Abstract: A system for warning the pilot of a rotary wing aircraft such as a helicopter of a flight condition that, if left uncorrected, would result in the tail of the aircraft striking the ground monitors the altitude above ground, descent rate, pitch and pitch rate of the aircraft and provides a warning if the relationship between the aforementioned parameters is such that a tail strike is imminent.

Abstract: A system for warning the pilot of an aircraft flying at low level, particularly over rising terrain, of an excessive closure condition that could result in controlled flight into terrain if left uncorrected. Specifically a warning system is disclosed that monitors the terrain closure rate of an aircraft under certain conditions. These conditions relate to the weapons not being armed, the aircraft flying between 100 and 1800 feet and the air speed exceeding 200 knots. When these conditions are met a warning is provided to the pilot that the terrain closure rate exceeds a predetermined safe limit for the radio altitude at which the aircraft is flying.

Abstract: A warning system for providing an aural warning to the pilot of a rotary wing aircraft monitors the altitude above ground and barometric descent rate of the aircraft and generates the warning if the descent rate of the aircraft is excessive for the altitude at which the aircraft is flying. The system provides two distinct warnings, one being an early warning advising the pilot of a hazardous condition, and the other being a warning alerting the pilot of imminent danger. The system also includes tactical and non-tactical modes of operation, wherein the warning criteria are adjusted to meet tactical and non-tactical flight conditions.