Warning system for tactical rotary wing aircraft

Claim 2

A ground proximity warning system for alerting the pilot of a rotary wing aircraft of insufficient terrain clearance, comprising: means for receiving a signal representative of the airspeed of the aircraft; means for receiving a signal representative of the altitude above ground of the aircraft; and means responsive to said airspeed signal and said altitude above ground signal receiving means for generating a warning if the altitude above ground of the aircraft is below a predetermined value determined for the airspeed at which the aircraft is flying, wherein said warning generating means includes means for providing said warning if said aircraft descends below a first altitude above ground at a first airspeed, and for providing said warning if said aircraft descends below a second lower altitude above ground at a higher airspeed.

Claim 3

A warning system as recited in claim 1 wherein said warning generating means includes means for generating a first warning if the aircraft is flying below a predetermined airspeed, and a second distinct warning if the aircraft is flying above said predetermined airspeed.

Claim 4

A ground proximity warning system as recited in claim 1 further including means responsive to a signal representative of a tactical phase of flight for preventing the generation of said warning when the aircraft is in a tactical phase of flight.

Claim 5

A ground proximity warning system as recited in claim 1 further including means responsive to a signal representative of a tactical phase of flight for preventing the generation of said warning when the aircraft is in a tactical phase of flight and the airspeed of the aircraft is above a predetermined airspeed.

Claim 6

A ground proximity warning system as recited in claim 4 wherein said predetermined airspeed is approximately 60 knots.

Claim 7

A ground proximity warning system as recited in claim 5 wherein said warning is provided at an altitude of approximately 130 feet at an airspeed of approximately 60 knots and at an altitude of approximately 150 feet at airspeeds of approximately 40 knots and below.

Claim 8

A ground proximity warning system as recited in claim 2 further including means responsive to a signal representative of a tactical phase of flight for preventing the generation of said first and second warnings when the aircraft is in a tactical phase of flight.

Claim 9

A ground proximity warning system as recited in claim 2 further including means responsive to a signal representative of a tactical phase of flight for preventing the generation of said second warning and for preventing the generation of said first warning when the aircraft is in a tactical phase of flight and the airspeed of the aircraft is above a predetermined airspeed.

Claim 10

A ground proximity warning system as recited in claim 8 wherein said predetermined airspeed is approximately 60 knots.

Claim 11

A ground proximity warning system as recited in claim 8 wherein said warning is provided at an altitude of approximately 130 feet at an airspeed of approximately 60 knots and at an altitude of approximately 150 feet at airspeeds of approximately 40 knots and below.

Claim 12

A warning system as recited in claim 1 wherein said warning generating means includes means for generating said warning if said aircraft descends below an altitude of approximately 150 feet above the ground if the airspeed of the aircraft is below approximately 40 knots, and for generating said warning if said aircraft descends below an altitude of approximately 75 feet above the ground when the airspeed of the aircraft is greater than approximately 120 knots.

Claim 13

A warning system as recited in claim 11 wherein the altitude required to generate a warning decreases linearly between an airspeed of approximately 40 knots and an airspeed of approximately 120 knots.

Claim 14

A warning system as recited in claim 12 wherein said system includes means for preventing the generation of a warning at altitudes below approximately 10 feet above the ground.

Claim 15

A warning system as recited in claim 12 wherein said warning generating means includes means for generating a first warning when the aircraft is flying at airspeeds below approximately 120 knots and for generating a second distinct warning when the aircraft is flying at airspeeds above approximately 120 knots.

Claim 16

A warning system is recited in claim 1 further including means for preventing the generation of a warning when the aircraft is taking off.

Claim 17

A warning system as recited in claim 1 wherein said aircraft has landing gear that is movable between an up position and a down position, and wherein said system includes means for receiving a signal representative of the position of the landing gear of the aircraft, and wherein said warning generating means is responsive to the landing gear position signal providing means for altering the altitudes above ground below which the warning is generated so that the altitude above ground below which the warning is generated increases with an increase in airspeed when the landing gear is down.

Claim 18

A ground proximity warning system for alerting the pilot of a rotary wing aircraft of insufficient terrain clearance, comprising: means for receiving a signal representative of the airspeed of the aircraft; means for receiving a signal representative of the altitude above ground of the aircraft; and means responsive to said airspeed and altitude signal receiving means for generating a warning if the altitude above ground is below a predetermined value determined for the airspeed at which the aircraft is flying, said warning generating means including means for providing a warning if the altitude above ground of the aircraft drops below approximately 100 feet and the airspeed of the aircraft is in excess of approximately 120 knots, wherein said warning generating means includes means for decreasing the altitude above ground below which the warning is generated as the airspeed of the aircraft decreases.

Claim 19

A ground proximity warning system for alerting the pilot of a rotary wing aircraft of insufficient terrain clearance, comprising: means for receiving a signal representative of the airspeed of the aircraft; means for receiving a signal representative of the altitude above ground of the aircraft; and means responsive to said airspeed and altitude signal receiving means for generating a warning if the altitude above ground is below a predetermined value determined for the airspeed at which the aircraft is flying, said warning generating means including means for providing a warning if the altitude above ground of the aircraft drops below approximately 100 feet and the airspeed of the aircraft is in excess of approximately 120 knots, wherein said warning generating means includes means for decreasing the altitude above ground below which the warning is generated as the airspeed of the aircraft decreases.

Claim 20

A warning system as recited in claim 17 wherein said warning generating means includes means for generating said warning at an altitude of approximately 10 feet above the ground when the airspeed of the aircraft is approximately 58 knots.

Claim 21

A warning system as recited in claim 18 wherein said generating means includes means for linearly increasing the altitude above ground below which the warning is generated as a function of increasing airspeed between an airspeed of approximately 58 knots and an airspeed of approximately 120 knots.

Claim 22

A ground proximity warning system for alerting the pilot of a rotary wing aircraft having a landing gear that is movable between an up position and a down position of insufficient terrain clearance, comprising: means for receiving a signal representative of the airspeed of the aircraft; means for receiving a signal representative of the altitude above ground of the aircraft; means for receiving a signal representative of the position of the landing gear of the aircraft; and means responsive to said airspeed signal receiving means, said altitude above ground signal receiving means and said landing gear position signal receiving means for generating a warning if the altitude of the aircraft is below a predetermined value for the airspeed at which the aircraft is flying which increases with increases in airspeed when the landing gear is down, wherein said warning generating means is operative to alter the altitude above ground below which a warning is generated such that it decreases with increases in airspeed when the landing gear is up.

Claim 23

A ground proximity warning system for alerting the pilot of a rotary wing aircraft having a landing gear that is movable between an up position and a down position of insufficient terrain clearance, comprising: means for receiving a signal representative of the airspeed of the aircraft; means for receiving a signal representative of the altitude above ground of the aircraft; means for receiving a signal representative of the position of the landing gear of the aircraft; and means responsive to said airspeed signal receiving means, said altitude above ground signal receiving means and said landing gear position signal receiving means for generating a warning if the altitude of the aircraft is below a predetermined value for the airspeed at which the aircraft is flying which increases with increases in airspeed when the landing gear is down, wherein said warning generating means is operative to alter the altitude above ground below which a warning is generated such that it decreases with increases in airspeed when the landing gear is up.

Claim 24

A warning system as recited in claim 20 wherein said warning generating means includes means for generating said warning if the aircraft descends below an altitude of approximately 150 feet above the ground if the airspeed of the aircraft is below approximately 40 knots and for generating the warning if the aircraft descends below an altitude of approximately 75 feet above the ground when the airspeed of the aircraft is greater than approximately 120 knots, and the landing gear is up.

Claim 25

A warning as recited in claim 21 wherein said warning generating means includes means for generating said warning at an altitude of approximately 10 feet above the ground when the airspeed of the aircraft is approximately 58 knots and for linearly increasing the altitude above ground below which the warning is generated as a function of increasing airspeed between an airspeed of approximately 58 knots and an airspeed of approximately 120 knots.

Claim 26

A ground proximity warning system for alerting the pilot of a rotary wing aircraft having a landing gear that is movable between an up position and a down position of insufficient terrain clearance, comprising: means for receiving a signal representative of the airspeed of the aircraft; means for receiving a signal representative of the altitude above ground of the aircraft; means for receiving a signal representative of the position of the landing gear of the aircraft; and means responsive to said airspeed signal receiving means, said altitude above ground signal receiving means and said landing gear position signal receiving means for generating a warning if the altitude of the aircraft is below a predetermined value determined for the airspeed at which the aircraft is flying wherein the altitude at which the warning is given decreases with increasing airspeed.

Claim 27

A ground proximity warning system for alerting the pilot of a rotary wing aircraft having a landing gear that is movable between an up position and a down position of insufficient terrain clearance, comprising: means for receiving a signal representative of the airspeed of the aircraft; means for receiving a signal representative of the altitude above ground of the aircraft; means for receiving a signal representative of the position of the landing gear of the aircraft; and means responsive to said airspeed signal receiving means, said altitude above ground signal receiving means and said landing gear position signal receiving means for generating a warning if the altitude of the aircraft is below a predetermined value determined for the airspeed at which the aircraft is flying wherein the altitude at which the warning is given decreases with increasing airspeed.