Aircraft thrust control scheme for terrain following system

Claim 1

A throttle control system for an aircraft in which thrust is controlled by throttle settings, operating in a terrain following mode using a base throttle setting for a trim value of thrust for a nominal velocity desired for level flight, and having storage means containing predetermined values for maximum and minimum velocity, a predetermined acceleration margin, and given values relating to lift and thrust capabilities of the aircraft, said system comprising: (a) input means to obtain values of the low and high points based on a search of terrain profile ahead of the aircraft from radar instruments, and means to obtain a value of the current velocity; (b) prediction means comprising computation means using the values obtained by the input means of the high and low points, and of the current velocity to predict the maximum and minimum velocities over said profile with said trim value of thrust; (c) first checking means to check for reduced throttle action including first comparison means using values from said prediction means and said storage means to determine whether "yes" the predicted maximum velocity is less than the predetermined maximum velocity or "no" it is not, and means responsive to the result from the first comparison means to set a first intermediate variable to a first or second value for "yes" or "no" respectively; (d) second checking means to check for increased throttle action, including further computation means using values from the prediction means and the given values from the storage means to calculate a projected acceleration margin at the trajectory high point, and second comparison means to determine whether "yes" the projected acceleration margin is greater than said predetermined acceleration margin at said high point or "no" it is not, and means responsive to the result from the second comparison means to set a second intermediate variable to a first or second value for "yes" or "no" respectively; (e) output means effective after operation of the first and second checking means for setting a command variable to a first value, a value of a second set, or a value of a third set, using the values of the first and second intermediate variables, the command variable being set to its first value responsive to the first and second intermediate variables both having their first value, the command variable being set to a value of the second set responsive to the first and second intermediate variables having their second and first values respectively, and the command variable being set to a value of the third set responsive to the first and second intermediate variables having their first and second values respectively, and means for supplying the value of the command variable to throttle control apparatus to maintain said base throttle setting, to provide a decreased thrust increment, or to provide an increased thrust increment, depending upon the command variable having the first, second or third value respectively.

Claim 7

The method of throttle control for an aircraft operating in a terrain following mode over a terrain profile having an altitude at each point including high and low points measured by radar instruments with respect to a current altitude, using a base throttle setting for a trim value of thrust for a nominal velocity desired for level flight, having a current velocity which may differ from the nominal velocity at any particular time; having storage means containing predetermined values for maximum and minimum velocity, a predetermined acceleration margin, and given values relating to lift and thrust capabilities of the aircraft; the aircraft having kinetic and potential energy at each point which are functions of the velocity, altitude, and said given values; wherein said method uses a digital processor operating in repetitive cycles with steps comprising: obtaining and storing values for the low and high points of the terrain profile ahead of the aircraft, and obtaining and storing a value for the current velocity; predicting maximum and minimum velocities at the low and high points respectively with said trim value of thrust by a calculation using the stored values for the high and low points and the current velocity, and using formulas based on predicted kinetic energy being equal to total energy which is the sum of current kinetic energy and potential energy with respect to the low and high points respectively; calculating a projected acceleration margin based on the predicted minimum velocity and given values relating to the aircraft structure and its load; determining by comparison whether the predicted maximum velocity and projected acceleration margin are within predetermined limits, and if so setting the throttle control to a base position for a trim value of thrust; calculating ΔE which is an amount of energy equal to the difference between kinetic energy required and kinetic energy predicted as functions respectively of said predetermined limits and said predicted velocities; and if said predicted maximum velocity and projected acceleration margin are not within the predetermined limits, changing the throttle control from said base position such that the integral of the thrust increment with respect to its trim value over the distance to a profile extreme is greater than or equal to ΔE for climbs and less than or equal to ΔE for dives.

Claim 8

The method of throttle control for an aircraft operating in a terrain following mode over a terrain profile having an altitude at each point including high and low points measured by radar instruments with respect to a current altitude, using a base throttle setting for a trim value of thrust for a nominal velocity desired for level flight, having a current velocity which may differ from the nominal velocity at any particular time; having storage means containing predetermined values for maximum and minimum velocity, a predetermined acceleration margin, and given values relating to lift and thrust capabilities of the aircraft; the aircraft having kinetic and potential energy at each point which are functions of the velocity, altitude, and said given values; wherein said method uses a digital processor operating in repetitive cycles with steps comprising: obtaining and storing values for the low and high points of the terrain profile ahead of the aircraft, and obtaining and storing a value for the current velocity; predicting maximum and minimum velocities at the low and high points respectively with said trim value of thrust by a calculation using the stored values for the high and low points and the current velocity, and using formulas based on predicted kinetic energy being equal to total energy which is the sum of current kinetic energy and potential energy with respect to the low and high points respectively; calculating a projected acceleration margin based on the predicted minimum velocity and given values relating to the aircraft structure and its load; determining by comparison whether the predicted maximum velocity and projected acceleration margin are within predetermined limits, and if so setting the throttle control to a base position for a trim value of thrust; calculating ΔE which is an amount of energy equal to the difference between kinetic energy required and kinetic energy predicted as functions respectively of said predetermined limits and said predicted velocities; and if said predicted maximum velocity and projected acceleration margin are not within the predetermined limits, changing the throttle control from said base position such that the integral of the thrust increment with respect to its trim value over the distance to a profile extreme is greater than or equal to ΔE for climbs and less than or equal to ΔE for dives.