Wind shear detection system

Claim 2

A wind shear detection system for an aircraft comprising: means for receiving a longitudinal accelerometer signal; means for receiving a normal accelerameter signal; means for receiving a signal representative of the air speed of the aircraft; means for receiving a signal representative of the flight path angle of the aircraft; means for receiving a signal representative of the angle of attack of the aircraft; means for multiplying the normal accelerometer signal with the sum of the flight path angle and angle of attack representative signals, taking the difference between the resulting product and the sum of the longitudinal accelerometer signal and the airspeed representative signal and integrating the difference to provide a composite signal; and means for comparing the signal representative of airspeed with the composite signal and generating a signal representative of the difference therebetween indicative of wind shear.

Claim 3

The system recited in claim 1 further including means responsive to said comparing means for providing an alert is the difference between the airspeed and composite signals exceeds a predetermined amount.

Claim 4

The system recited in claim 1 further including means for receiving a signal representative of the roll angle of the aircraft, and for modifying said composite signal as a function of the roll angle.

Claim 5

A wind shear detection system as recited in claim 1, further including means for providing a signal representative of the flight path angle of the aircraft, said flight path angle representative signal providing means comprising: means for receiving a signal representative of the vertical speed of the aircraft and the airspeed representative signal and for generating the signal representative of the aircraft flight path angle according to the relative values of the airspeed and vertical speed representative signals, the airspeed representing a horizontal component of the flight path angle and the vertical speed representing a vertical component of the flight path angle.

Claim 6

A wind shear detection system as recited in claim 4 wherein said flight path angle representative signal is generated by dividing the signal representative of the vertical speed by the signal representative of the airspeed of the aircraft.

Claim 7

A wind shear detection system for an aircraft comprising: first means for receiving a signal representative of the longitudinal acceleration of the aircraft, A L ; second means for receiving a signal representative of the normal acceleration of the aircraft, A N ; third means for receiving a signal representative of the flight path angle γ of the aircraft; fourth means for receiving a signal representative of the angle of attack α the aircraft; fifth means for providing a signal representative of the airspeed of the aircraft, v; and sixth means responsive to said first, second, third, fourth and fifth means for providing a signal representative of the wind shear according to the following relationship: ##EQU9## wherein s is the LaPlace operator and T is the integration time constant.

Claim 8

A wind shear detection system for an aircraft comprising: first means for receiving a signal representative of the longitudinal acceleration of the aircraft, A L ; second means for receiving a signal representative of the normal acceleration of the aircraft, A N ; third means for receiving a signal representative of the flight path angle γ of the aircraft; fourth means for receiving a signal representative of the angle of attack α the aircraft; fifth means for providing a signal representative of the airspeed of the aircraft, v; and sixth means responsive to said first, second, third, fourth and fifth means for providing a signal representative of the wind shear according to the following relationship: ##EQU9## wherein s is the LaPlace operator and T is the integration time constant.

Claim 11

The method recited in claim 7, further including providing an alert if the difference between the airspeed and composite signals exceeds a predetermined amount.

Claim 12

The method recited in claim 7, further including providing a signal representative of the roll angle of the aircraft and modifying said composite signal as a function of the roll angle.

Claim 13

A wind shear detection system for an aircraft comprising: first means for receiving a signal representative of the longitudinal acceleration of the aircraft, A L ; second means for receiving a signal representative of the normal acceleration of the aircraft, third means for receiving a signal representative of the vertical velocity, h, of the aircraft; fourth means for receiving a signal representative of the angle of attack α the aircraft; fifth means for providing a signal representative of the airspeed of the aircraft, v; and sixth means responsive to said first, second, third, fourth and fifth means for providing a signal representative of the wind shear according to the following relationship therebetween: shear=A L cos α-A N sin α-g(h/v)-v wherein g is the gravitational constant and v is the rate of change of v.

Claim 14

A wind shear detection system for an aircraft comprising: first means for receiving a signal representative of the longitudinal acceleration of the aircraft, A L ; second means for receiving a signal representative of the normal acceleration of the aircraft, third means for receiving a signal representative of the vertical velocity, h, of the aircraft; fourth means for receiving a signal representative of the angle of attack α the aircraft; fifth means for providing a signal representative of the airspeed of the aircraft, v; and sixth means responsive to said first, second, third, fourth and fifth means for providing a signal representative of the wind shear according to the following relationship therebetween: shear=A L cos α-A N sin α-g(h/v)-v wherein g is the gravitational constant and v is the rate of change of v.

Claim 15

A wind shear detection system for an aircraft comprising: first means for receiving a signal representative of the longitudinal acceleration of the aircraft, A L ; second means for receiving a signal representative of the normal acceleration of the aircraft, A N ; third means for receiving a signal representative of the vertical velocity, h, of the aircraft; fourth means for receiving a signal representative of the angle of attack α the aircraft; fifth means for providing a signal representative of the airspeed of the aircraft, v; and sixth means responsive to said first, second, third, fourth and fifth means for providing a signal representative of the wind shear according to the following relationship therebetween: ##EQU10## wherein g is the gravitational constant, s is the LaPlace operator and T is the integration time constant.

Claim 16

A wind shear detection system for an aircraft comprising: first means for receiving a signal representative of the longitudinal acceleration of the aircraft, A L ; second means for receiving a signal representative of the normal acceleration of the aircraft, A N ; third means for receiving a signal representative of the vertical velocity, h, of the aircraft; fourth means for receiving a signal representative of the angle of attack α the aircraft; fifth means for providing a signal representative of the airspeed of the aircraft, v; and sixth means responsive to said first, second, third, fourth and fifth means for providing a signal representative of the wind shear according to the following relationship therebetween: ##EQU10## wherein g is the gravitational constant, s is the LaPlace operator and T is the integration time constant.

Claim 17

A wind shear detection system for an aircraft, comprising: means for providing an accelerometer derived acceleration signal along the velocity vector, A XS , of the aircraft and an airmass derived signal along the velocity vector; and means for comparing the accelerometer derived acceleration along the velocity vector and the airmass derived signal along the velocity vector for providing a shear signal in response to the difference therebetween, indicative of wind shear, wherein said means for providing the accelerometer derived acceleration signal along the velocity vector, A XS , includes means for deriving the accelerometer derived acceleration signal along the velocity vector fror a longitudinal accelerometer signal, A L , a normal accelerometer signal A N , a signal representative of the aircraft angle of attack, α, a signal representative of the aircraft vertical speed h, and a signal representative of airspeed v, and for deriving the airmass derived signal from the airspeed signal v, and wherein the accelerometer derived acceleration signal along the velocity vector, A XS , is derived according to the following relationship: A.sub.XS =A.sub.L cos α-A.sub.N sin α-g(h/v) where g is the gravitational constant.

Claim 18

A wind shear detection system for an aircraft, comprising: means for providing an accelerometer derived acceleration signal along the velocity vector, A XS , of the aircraft and an airmass derived signal along the velocity vector; and means for comparing the accelerometer derived acceleration along the velocity vector and the airmass derived signal along the velocity vector for providing a shear signal in response to the difference therebetween, indicative of wind shear, wherein said means for providing the accelerometer derived acceleration signal along the velocity vector, A XS , includes means for deriving the accelerometer derived acceleration signal along the velocity vector fror a longitudinal accelerometer signal, A L , a normal accelerometer signal A N , a signal representative of the aircraft angle of attack, α, a signal representative of the aircraft vertical speed h, and a signal representative of airspeed v, and for deriving the airmass derived signal from the airspeed signal v, and wherein the accelerometer derived acceleration signal along the velocity vector, A XS , is derived according to the following relationship: A.sub.XS =A.sub.L cos α-A.sub.N sin α-g(h/v) where g is the gravitational constant.

Claim 19

A wind shear detection system for an aircraft, comprising: means for providing an accelerometer derived acceleration signal along the velocity vector, A XS , of the aircraft and an airmass derived signal along the velocity vector; and means for comparing the accelerometer derived acceleration along the velocity vector and the airmass derived signal along the velocity vector for providing a shear signal in response to the difference therebetween indicative of wind shear, wherein said means for providing the accelerometer derived acceleration signal along the velocity vector, A XS , includes means for deriving the accelerometer derived acceleration signal from a longitudinal accelerometer signal, A L , a normal accelerometer signal A N , a signal representative of the aircraft angle of attack, α, a signal representative of aircraft pitch angle, θ, a signal representative of aircraft roll angle, φ, and for deriving the airmass derived signal from a signal, v, representative of airspeed, wherein the accelerometer derived acceleration signal along the velocity vector, A XS , is derived according to the following relationships: ##EQU11## where g is the gravitational constant.

Claim 20

A wind shear detection system for an aircraft, comprising: means for providing an accelerometer derived acceleration signal along the velocity vector, A XS , of the aircraft and an airmass derived signal along the velocity vector; and means for comparing the accelerometer derived acceleration along the velocity vector and the airmass derived signal along the velocity vector for providing a shear signal in response to the difference therebetween indicative of wind shear, wherein said means for providing the accelerometer derived acceleration signal along the velocity vector, A XS , includes means for deriving the accelerometer derived acceleration signal from a longitudinal accelerometer signal, A L , a normal accelerometer signal A N , a signal representative of the aircraft angle of attack, α, a signal representative of aircraft pitch angle, θ, a signal representative of aircraft roll angle, φ, and for deriving the airmass derived signal from a signal, v, representative of airspeed, wherein the accelerometer derived acceleration signal along the velocity vector, A XS , is derived according to the following relationships: ##EQU11## where g is the gravitational constant.