Rate of change of energy indicator

Claim 2

Apparatus for providing a pilot of an airplane with an indication of the rate of change of energy of the airplane comprising: first means for generating a first signal representative of the flight path acceleration of the airplane; second means for generating a second signal representative of the true airspeed of the airplane; third means connected to receive said first and second signals, said third means being operative to generate a third signal indicative of the product of said first and second signals; and output means connected to receive said third signal for producing an indication of the quotient derived by dividing said third signal by a value equal to the acceleration due to gravity.

Claim 3

The apparatus of claim 1 wherein said first means comprises in combination: a means for giving a fourth signal representative of the normal acceleration of the airplane; a means for giving a fifth signal representative of the longitudinal acceleration of the airplane; means for giving a sixth signal indicative of the angle of attack of the airplane; and computing means for deriving from said fourth, fifth, and sixth signals said first signal representative of the flight path acceleration of the airplane.

Claim 4

The apparatus of claim 2 wherein said second means is a true airspeed sensor.

Claim 5

The apparatus of claim 3 wherein sAid third means is a multiplying circuit.

Claim 6

The apparatus of claim 4 wherein said output means comprises: a dividing circuit for giving a seventh signal representative of the quotient of said third signal divided by a value equal to the acceleration due to gravity; and an indicator for producing a visual indication of said seventh signal.

Claim 7

An energy rate indicator comprising, in combination: means giving a first signal representative of the true airspeed v of an aircraft; means giving a second signal representative of the angle of attack Alpha of the aircraft; means giving a third signal representative of longitudinal acceleration aL of the aircraft; means giving a fourth signal representative of normal acceleration aN of the aircraft; computer means connected to receive all said signals for giving an output representative of the following relation therebetween v/g (aL cos Alpha - aN sin Alpha ) where the constant g is the acceleration due to gravity; and indicating means connected to said computer means for displaying said output.

Claim 8

An energy rate indicator comprising, in combination: means giving a first signal representative of the true airspeed v of an aircraft; means giving a second signal representative of the angle of attack Alpha of the aircraft; means giving a third signal representative of longitudinal acceleration aL of the aircraft; means giving a fourth signal representative of normal acceleration aN of the aircraft; computer means connected to receive all said signals for giving an output representative of the following relation therebetween v/g (aL cos Alpha - aN sin Alpha ) where the constant g is the acceleration due to gravity; and indicating means connected to said computer means for displaying said output.