Ground proximity warning system having modified terrain closure rate warning on glide slope approach

Claim 2

A ground proximity warning system for an aircraft comprising: means responsive to a signal representative of the altitude of the aircraft above ground and to a signal representative of the terrain closure rate of the aircraft for generating a first signal when the terrain closure rate is within a predetermined envelope for the altitude at which the aircraft is flying; means responsive to a glid slope radio beam for generating a second signal if the aircraft deviates by more than a predetermined limit from the glide slope; and means for altering said predetermined envelope according to a predetermined relationship between the closure rate and the altitude of the aircraft above ground when said glide slope is detected and said aircraft has not deviated more than the predetermined limit from said glide slope.

Claim 3

A ground proximity warning system as recited in claim 1 wherein said predetermined envelope is altered to reduce the maximum altitude at which a first signal may be generated when said glide slope beam is detected and the aircraft has not descended more than said predetermined limit below the glide slope.

Claim 4

A ground proximity warning system as recited in claim 2 wherein said maximum altitude is reduced to approximately 700 to 900 feet above the ground.

Claim 5

A ground proximity warning system as recited in claim 1 wherein said terrain closure rate warning means includes means for limiting the maximum and minimum values of the terrain closure rate signal and means for altering at least one of said maximum and minimum values to alter said predetermined envelope.

Claim 6

In a ground proximity warning system having means for warning the pilot of an aircraft of an excessive closure rate with terrain according to a predetermined warning envelope and means for detecting a glide slope beam and the altitude of the aircraft above ground, the improvement comprising, means responsive to said glide slope beam detecting means for altering said predetermined warning envelope according to a predetermined relationship between the closure rate and the altitude of the aircraft above ground when said glide slope beam is detected.

Claim 7

In a ground proximity warning system having means for warning the pilot of an aircraft of an excessive closure rate with terrain according to a predetermined warning envelope and means for detecting a glide slope beam and the altitude of the aircraft above ground, the improvement comprising, means responsive to said glide slope beam detecting means for altering said predetermined warning envelope according to a predetermined relationship between the closure rate and the altitude of the aircraft above ground when said glide slope beam is detected.

Claim 8

The improvement recited in claim 5 wherein said warning envelope altering means includes means for limiting the maximum altitude at which the closure rate warning may be given.

Claim 9

The improvement recited in claim 6 wherein said warning envelope altering means includes means for limiting the maximum altitude at which a terrain closure rate warning may be given to approximately 700 to 900 feet above ground.

Claim 10

The improvement recited in claim 6 wherein said warning envelope altering means includes means for determining if the aircraft deviates more than a predetermined limit from the glide slope, and for altering said predetermined warning envelope only if the aircraft has not dropped more than said predetermined limit below the glide slope.

Claim 11

The improvement recited in claim 5 wherein said warning envelope altering means includes means for altering the maximum closure rate to which the excessive closure rate warning means is responsive.

Claim 12

A ground proximity warning system for an aircraft comprising: means for receiving a source of signals representative of the altitude of the aircraft above ground; means for receiving a glide slope radio beam; means for providing a signal representative of the terrain closure rate of the aircraft; means responsive to the altitude of the aircraft above ground signal receiving means and to the terrain closure rate signal providing means for generating a warning if the terrain closure rate is within a predetermined warning envelope for the altitude at which the aircraft is flying; means responsive to the glide slope signal receiving means for generating a warning if the aircraft deviates more than a predetermined limit from the glide slope; and means for altering said predetermined warning envelope according to a predetermined relationship between the terrain closure rate and the altitude of the aircraft above ground when said glide slope beam is received and said aircraft has not deviated more than said predetermined limit from said glide slope.

Claim 13

A ground proximity warning system for an aircraft comprising: means for receiving a source of signals representative of the altitude of the aircraft above ground; means for receiving a glide slope radio beam; means for providing a signal representative of the terrain closure rate of the aircraft; means responsive to the altitude of the aircraft above ground signal receiving means and to the terrain closure rate signal providing means for generating a warning if the terrain closure rate is within a predetermined warning envelope for the altitude at which the aircraft is flying; means responsive to the glide slope signal receiving means for generating a warning if the aircraft deviates more than a predetermined limit from the glide slope; and means for altering said predetermined warning envelope according to a predetermined relationship between the terrain closure rate and the altitude of the aircraft above ground when said glide slope beam is received and said aircraft has not deviated more than said predetermined limit from said glide slope.

Claim 14

A ground proximity warning system as recited in claim 10 wherein said excessive deviation from said glide slope warning generating means is further responsive to the altitude above ground of the aircraft and generates the warning if the aircraft deviates excessively below the glide slope for the altitude at which the aircraft is flying.

Claim 15

A ground proximity warning system as recited in claim 9 wherein said predetermined warning envelope is altered to reduce the maximum altitude at which a warning may be generated when said glide slope beam is detected and the aircraft has not descended more than said predetermined limit below the glide slope.

Claim 16

A ground proximity warning system as recited in claim 12 wherein said maximum altitude is reduced to approximately 700 to 900 feet above the ground.

Claim 17

A ground proximity warning system as recited in claim 9 wherein said terrain closure rate warning means includes means for limiting the maximum and minimum values of the terrain closure rate signal and means for altering at least one of said maximum and minimum values to alter said predetermined warning envelope.

Claim 18

A ground proximity warning system as recited in claim 9 wherein said predetermined warning envelope is altered to increase the minimum altitude at which a warning will be generated when said glide slope beam is detected and the aircraft has not descended by more than said predetermined limit below the glide slope.

Claim 19

A ground proximity warning system for an aircraft comprising: means for receiving a source of signals representative of the altitude of the aircraft above ground; means for receiving a source of signals representative of the glide slope; means for providing a signal representative of the terrain closure rate of the aircraft; means responsive to the altitude of the aircraft above ground signal receiving means and to the terrain closure rate signal providing means for generating a warning if the terrain closure rate is within a predetermined warning envelope for the altitude at which the aircraft is flying; and means responsive to said glide slope signal for altering said warning envelope according to a predetermined relationship between the terrain closure rate and altitude of the aircraft above ground when said glide slope signal has not deviated by more than a predetermined limit from said glide slope.

Claim 20

A ground proximity warning system for an aircraft comprising: means for receiving a source of signals representative of the altitude of the aircraft above ground; means for receiving a source of signals representative of the glide slope; means for providing a signal representative of the terrain closure rate of the aircraft; means responsive to the altitude of the aircraft above ground signal receiving means and to the terrain closure rate signal providing means for generating a warning if the terrain closure rate is within a predetermined warning envelope for the altitude at which the aircraft is flying; and means responsive to said glide slope signal for altering said warning envelope according to a predetermined relationship between the terrain closure rate and altitude of the aircraft above ground when said glide slope signal has not deviated by more than a predetermined limit from said glide slope.

Claim 21

A ground proximity warning system as recited in claim 16 wherein said predetermined warning envelope is altered to reduce the maximum altitude at which a warning may be generated when said flap position signal indicates the aircraft is in a landing mode.

Claim 22

A ground proximity warning system as recited in claim 16 wherein said predetermined warning envelope is altered to increase the minimum altitude at which a warning will be generated when said flap position signal indicates the aircraft is in a landing mode.

Claim 23

A ground proximity warning system for an aircraft as recited in claim 16 further including means for providing a signal representative of the flap position of the aircraft; and means responsive to said aircraft flap position signal providing means for altering the warning envelope as a function of closure rate and altitude of the aircraft above ground when said flap position signal indicates the aircraft is in a landing mode.