초록 ▼

To provide a predictive emergency warning to the pilot of flight and terrain conditions which will result in a collision with the ground unless the pilot takes immediate action, without issuing excessive nuisance warnings, the system uses input parameters from other aircraft systems such as the rada

To provide a predictive emergency warning to the pilot of flight and terrain conditions which will result in a collision with the ground unless the pilot takes immediate action, without issuing excessive nuisance warnings, the system uses input parameters from other aircraft systems such as the radar altimeter. Inertial Navigation System, and Central Air Data Computer which are processed in an on-board computer to determine when a warning is required. A software program which is part of the warning system provides a logic link between the on-board aircraft parameters and the on-board voice command (“pull-up, pull-up”). The software program is readily adaptable to all aircraft applications with varying amounts of modification depending on specific mission requirements for which this protection is required. A feature is the use of a continuously computing predictive warning algorithm (based on classical flight dynamics equations) in combination with unique inhibit logic equations. Another feature is the introduction of “extended coverage”logic which permits the altitude dependent, time limited use of an alternate (other than radar) altitude reference signal when the radar altimeter is beyond limits.

대표청구항 ▼

A low altitude warning system for aircraft to provide a warning to the pilot of flight and terrain conditions which will result in a collision with the ground unless the pilot takes immediate action, without issuing excessive nuisance warnings, using a computer on board the aircraft, said low altitu

A low altitude warning system for aircraft to provide a warning to the pilot of flight and terrain conditions which will result in a collision with the ground unless the pilot takes immediate action, without issuing excessive nuisance warnings, using a computer on board the aircraft, said low altitude warning system comprising: input means providing input parameters from other aircraft systems, including radar altitude from a radar altimeter, inertial velocities (Vx, Vy, Vz), pitch and bank angles (theta, phi) from an inertial navigation system (INS), and calibrated airspeed (vc) from a central air data computer (CADC); filter means for providing filtered signals of vertical inertial veocity (Vz), radar altitude (Hr), and rate of change of Vz and radar altitude from a low-pass (alpha-beta) filter, wherein the filter means receives inputs from the INS and the radar altimeter, and creates rate information; predictive means having inputs from said input means and said filter means for issuing a warning based on a prediction of the time necessary for recovery from an excessive closure with terrain condition based on pilot reaction time, flight path angle, MDA, bank angle, airspeed, and terrain slope, a predictive warning being issued if the sum of the following predictive factors is greater than the radar altitude; i. DDD