Takeoff and go-around climb-out profile pitch command formulation for aircraft专利检索-飞行计划空中管制专利检索查询-专利查询网

Takeoff and go-around climb-out profile pitch command formulation for aircraft

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专利汇可以提供Takeoff and go-around climb-out profile pitch command formulation for aircraft专利检索，专利查询，专利分析的服务。并且A pitch command signal formulation using angle-of-attack as basic reference provides improved noise abatement takeoff and goaround aircraft climb profiles. A stall margin reference angleof-attack, as modified by flap position provides an angle of attack rundown profile based on flap change schedules. Rundown is effected in response to first flap reductions during the climbing phase in either mode such that common signal formulation circuitry is employed to command the same profile for either flight mode.，下面是Takeoff and go-around climb-out profile pitch command formulation for aircraft专利的具体信息内容。

权利要求

1. In an angle of attack referenced aircraft pitch command signal generation system, means for generating an angle-of-attack command signal defined by a predetermined profile for each of takeoff and go-around computation command mode capabilities comprising, first means responsive to measured aircraft flap position to generate a reference angle-of-attack signal corresponding to a predetermined speed margin over the stall speed corresponding to that flap position for a particular aircraft, signal synchronizing means receiving said reference angle-of-attack signal and developing an output angle-of-attack command signal corresponding to said reference angle-of-attack, altitude responsive means for decreasing said reference angle-ofattack by a predetermined angular decrease over a predetermined period of time initiated at the attainment of a predetermined aircraft altitude, reference angle-of-attack signal processing means, the output of said signal processing means comprising said angle-of-attack command signal, said signal processing means comprising means responsive to said takeoff mode and to predetermined flap deployment to reduce said angle-of-attack command signal to a predetermined reference level over a predetermined period of time initiated at the first reduction in flap deployment from that flap deployment existing at aircraft lift-off, said signal processing means being additionally responsive to said go-around mode and to predetermined flap deployment to reduce said angle-of-attack command signal to said predetermined reference level over said predetermined period of time in response to flap deployment angles less than a predetermined angular deployment.

2. A command signal generation system as defined in claim 1 further including means for increasing said reference angle of attack signal by a predetermined angular increase in response to said go-around mode being effected.

3. A command signal generation means as defined in claim 1 wherein said altitude responsive means comprises a first signal combining means to which said reference angle-of-attack signal is applied as a first input, a first bias signal source of magnitude corresponding to said first predetermined angular decrease, altitude responsive switching means through which said first bias signal source is applied as a subtractive second input to said first signal combining means for altitudes equal to and greater than said predetermined altitude, the output of said first signal combining means comprising said reference angle-of-attack input signal to said signal synchronizing means.

4. Command signal generation means as defined in claim 3 wherein said signal synchronizing means comprises a signal integrator, a second signal combining means receiving said reference angle of attack signal as a first input thereto, a second switching means, the output of said second signal combining means being selectively connected as input to said signal integrator through a first position of said second switching means, the output of said signal integrator being applied as a subtractive second input to said second signal combining means, the output of said signal integrator comprising said angle-of-attack command signal; said signal processing means comprising a further angle-of-attack bias source corresponding to said predetermined angle-of-attack command signal reference level, means for subtractively combining said further bias source with said angle of attack command signal, means responsive to an output signal in excess of zero from said means for subtractively combining to generate a substantially constant reference signal of predetermined mangitude, and means for selectively applying said reference signal as input to said signal integrating means in lieu of said reference angle-of-attack signal through a second position of said second switching means.

5. Command signal generation means as defined in claim 4 wherein said means for subtractively combining comprises a third signal combining means receiving said further bias source and said angle-of-attack command signal as respective mutually subtractive inputs thereto, said means for generating said reference signal comprising signal amplifying means receiving the output of said third signal combining means, signal limiting means receiving the output of said amplifying means, and the output of said signal limiting means comprising said reference signal.

6. Command signal generation means as defined in claim 4 wherein said first and second positions of said second switching means are effected by flap schedule logic means; said flap schedule logic means comprising means to position said second switching means from the first position thereof to the second position thereof during takeoff mode at the time corresponding to said first flap reduction from the flap angle deployment existing a the insTant of aircraft takeoff, said logic means further comprising means to position said second switching means from the first position thereof to the second position thereof during go-around mode at the time corresponding to falp reduction to said predetermined angular deployment angle.

7. Command signal generation means as defined in claim 6 wherein said logic means comprises means to generate an outut signal logic level to effect said second switching means second position in response to said predetermined flap deployment angle and go-around mode being simultaneously effected, and means to further generate an output signal logic level to effect said further switching means second position in response to said first flap angle deployment being less than that angle existing at aircraft takeoff.

8. Command signal generation means as defined in claim 7 wherein said means to further generate comprises strut switch responsive means to memorize the flap angle deployment existing at aircraft lift-off, an means for comparing said memorized flap angle with the instantly existing flap angle and generating said output signal logic level upon said existing flap angle being less than said takeoff flap angle.

9. Command signal generation means as defined in claim 8 wherein said memorizing means comprises a further signal synchronizer responsive to said strut switch to produce an output signal corresponding to flap angle deployment at takeoff, said means for comparing comprising a signal comparator receiving the output signal from said further signal synchronizer and a signal proportional to existing aircraft flap deployment and producing said output signal logic level upon said existing flap angle signal being less than the output signal from said further signal synchronizer.

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Takeoff and go-around climb-out profile pitch command formulation for aircraft

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