Negative climb rate after take-off warning system with predetermined loss of altitude inhibit

Claim 2

In an aircraft instrument for warning the pilot of an excessive descent following a climb during a takeoff or a missed landing approach maneuver, said instrument having a source of signal representing the vertical motion of the aircraft, improved means establishing a warning criteria, comprising: means responsive to said vertical motion signal for establishing a signal representing the net altitude loss of the aircraft from the high point of the flight path; means for establishing an excessive altitude loss signal; means for comparing said net altitude loss signal with said excessive altitude loss signal, the comparing means output indicating whether the net altitude loss which has occurred is excessive; and means responsive to an output of the comparing means indicating an excessive net altitude loss for initiating a pilot warning.

Claim 3

The aircraft warning instrument of claim 1 in which the instrument includes a source of signal representing the altitude of the aircraft above the ground and the means establishing an excessive altitude loss signal is responsive to the altitutde above ground signal.

Claim 4

The aircraft warning instrument of claim 2 in which the excessive altitude loss signal is directly related to the altitude above the ground signal.

Claim 5

The aircraft warning instrument of claim 1 in which the source of signal representing the vertical motion of the aircraft is a source of barometric altitude rate signal and said means to establish a signal representing the net altitude loss is an integrator.

Claim 6

The aircraft warning instrument of claim 1 in which the means for initiating a pilot warning is connected with said source of vertical motion signal and is enabled when said aircraft is descending.

Claim 7

A negative climb warning system for use in aircraft in a nonlanding configuration comprising: rate means responsive to a barometric altimeter and including an electronic circuit to differentiate the signal from the barometric altimeter with respect to time for generating a signal representing the rate of change in aircraft altitude; configuration means responsive to signals indicating the operative condition of the aircraft flaps and landing gear for generating signals representing the aircraft flight configuration; measuring means responsive to said rate means for measuring the descent of the aircraft; and warning means responsive to said measuring means and said configuration means for generating a warning signal indicating that the aircraft is descending after descending a predetermined distance.

Claim 8

A negative climb warning system for use in aircraft in a nonlanding configuration comprising: rate means responsive to a barometric altimeter and including an electronic circuit to differentiate the signal from the barometric altimeter with respect to time for generating a signal representing the rate of change in aircraft altitude; configuration means responsive to signals indicating the operative condition of the aircraft flaps and landing gear for generating signals representing the aircraft flight configuration; measuring means responsive to said rate means for measuring the descent of the aircraft; and warning means responsive to said measuring means and said configuration means for generating a warning signal indicating that the aircraft is descending after descending a predetermined distance.

Claim 9

The system of claim 6 wherein said measuring means includes an electronic circuit for integrating said differentiated barometric signal and generating a signal representing a net loss of altitude.

Claim 10

The system of claim 7 wherein said warning means is additionally responsive to a radar altimeter signal for generating said warning signal as a function of both said net loss of altitude signal and the aircraft's altitude above ground.

Claim 11

The system of claim 8 wherein said warning means generates said descent warning signal as a linear function of the increase in said net loss signal as compared to increasing aircraft altitude.

Claim 12

A negative climb warning system for an aricraft having a barometric and radio altimeter comprising: means for measuring the aircraft's net loss in barometric altitude; means for comparing said net loss of altitude with the radio altitude; means responsive to said comparing means for generating a warning signal when said net loss exceeds a predetermined amount for a predetermined altitude.

Claim 13

A negative climb warning system for an aricraft having a barometric and radio altimeter comprising: means for measuring the aircraft's net loss in barometric altitude; means for comparing said net loss of altitude with the radio altitude; means responsive to said comparing means for generating a warning signal when said net loss exceeds a predetermined amount for a predetermined altitude.

Claim 14

Th system of claim 10 additionally including means to inhibit said warning signal above a first predetermined altitude and below a second predetermined altitude.

Claim 15

The system of claim 11 additionally including means to inhibit said warning signals during predetermined phases of aircraft operation.

Claim 16

The system of claim 10 additionally including means to inhibit said warning signals when the aircraft is gaining altitude.

Claim 19

An electronic circuit, responsive to rate of change in barometric altitude signals and altitude signals from a radar altimeter, for generating a negative climb warning signal in an aircraft comprising: an integrating amplifier for integrating the rate of change in barometric altitude signal thereby producing a signal representing the descent of the aircraft; a clamp circuit operatively connected to said integrating amplifier for preventing the output of said descent signal from said integrating amplifier; a first comparator circuit responsive to said rate of change in said barometric signal and said descent signal for activating said clamp circuit; a summing junction for combining the radar altitude signal with a biasing signal; a second comparator circuit, operatively connected wtih said integrating amplifier and said summing junction, to generate a logic signal indicating that said descent signal has exceed a predefined value with respect to said biased altitude signal; a first logic circuit, operatively connected to said second comparator circuit and responsive to the altitude signal, to inhibit said logic signal above and below predefined altitudes; to inhibit said logic signal above and below predefined altitudes; and means responsive to said logic signal for generating the negative climb warning.

Claim 20

An electronic circuit, responsive to rate of change in barometric altitude signals and altitude signals from a radar altimeter, for generating a negative climb warning signal in an aircraft comprising: an integrating amplifier for integrating the rate of change in barometric altitude signal thereby producing a signal representing the descent of the aircraft; a clamp circuit operatively connected to said integrating amplifier for preventing the output of said descent signal from said integrating amplifier; a first comparator circuit responsive to said rate of change in said barometric signal and said descent signal for activating said clamp circuit; a summing junction for combining the radar altitude signal with a biasing signal; a second comparator circuit, operatively connected wtih said integrating amplifier and said summing junction, to generate a logic signal indicating that said descent signal has exceed a predefined value with respect to said biased altitude signal; a first logic circuit, operatively connected to said second comparator circuit and responsive to the altitude signal, to inhibit said logic signal above and below predefined altitudes; to inhibit said logic signal above and below predefined altitudes; and means responsive to said logic signal for generating the negative climb warning.

Claim 21

The circuit of claim 15 additionally including: a flip-flop circuit for indicating the phase of flight operation of the aircraft; a second logic circuit, responsive to signals indicating flap, landing gear, and altitude condition of the aircraft, for setting said flip-flop circuit; a third logic circuit responsive to signals indicating the altitude of the aircraft for resetting said flip-flop; and a circuit element for transmitting the logical setting of said flip-flop to said clamp circuit.

Claim 22

The circuit of claim 15 additionally including a circuit element to transmit the logical setting of said flip-flop to said first logic circuit.

Claim 23

The circuit of claim 15 additionally including a third comparator circuit, responsive to the rate of change in barometric altitude signal and operatively connected to said first logic circuit, to inhibit said logic signal in response to an increase in barometric altitude.

Claim 24

An aircraft warning instrument for alerting the pilot of an aircraft to a condition of excessive descent following takeoff or a missed landing approach, comprising: a source of signal representing the rate of change of altitude of the aircraft; a source of signal representing the altitude of the aircraft above the ground; means responsive to the rate signal for generating a signal representing the net loss in aircraft altitude from the high point of the flight path; means for directly comparing the aircraft altitude net loss signal with the altitude above ground signal; and means responsive to said comparing means to actuate a pilot warning device when the net distance which the aircraft has descended is excessive for the aircraft altitude above ground.

Claim 25

An aircraft warning instrument for alerting the pilot of an aircraft to a condition of excessive descent following takeoff or a missed landing approach, comprising: a source of signal representing the rate of change of altitude of the aircraft; a source of signal representing the altitude of the aircraft above the ground; means responsive to the rate signal for generating a signal representing the net loss in aircraft altitude from the high point of the flight path; means for directly comparing the aircraft altitude net loss signal with the altitude above ground signal; and means responsive to said comparing means to actuate a pilot warning device when the net distance which the aircraft has descended is excessive for the aircraft altitude above ground.

Claim 26

The aircraft warning instrument of claim 19 including means responsive to the aircraft rate of change of altitude signal for inhibiting the pilot warning so long as the aircraft is climbing.

Claim 27

The aircraft warning instrument of claim 19 in which the means for generating the aircraft altitude change signal is an integrator having its input connected with the source of altitude rate signal and having an output representing the change of aircraft altitude.

Claim 28

The aircraft warning instrument of claim 21 including means for clamping the integrator output to a reference level.

Claim 29

The aircraft warning instrument of claim 22 in which said integrator clamp means is responsive to the aircraft configuration to unclamp the integrator from the reference level on takeoff.

Claim 30

The aircraft warning instrument of claim 22 in which said integrator clamp means is responsive to the aircraft configuration to unclamp the integrator from the reference level on missed landing approach.

Claim 31

The aircraft warning instrument of claim 22 in which said integrator clamp means is responsive to an extended condition of the aircraft landing gear or flaps to clamp the integrator to the reference level on landing approach.

Claim 32

The aircraft warning instrument of claim 22 in which said integrator clamp means is responsive to a retracted condition of the aircraft landing gear or flaps to unclamp the integrator from said reference level on takeoff or a missed landing approach.

Claim 33

The aircraft warning instrument of claim 22 in which said integrator output clamp means is responsive to a combination of a change of aircraft altitude signal representing a climb of the aircraft and to an integrator output representing no accumulated descent to clamp the integrator to the reference level.