Real time correction of aircraft flight configuration
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-017/13
G06F-017/11
G06F-019/00
출원번호
UP-0066651
(2005-02-22)
등록번호
US-7561946
(2009-07-27)
발명자
/ 주소
Schipper, John F.
출원인 / 주소
The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration
대리인 / 주소
Schipper, John F.
인용정보
피인용 횟수 :
5인용 특허 :
5
초록▼
Method and system for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter. A time-dependent recovery band, defined by first and second recovery band boundaries that are spaced apart at at least one time point, is constructed for a selected flight parameter and
Method and system for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter. A time-dependent recovery band, defined by first and second recovery band boundaries that are spaced apart at at least one time point, is constructed for a selected flight parameter and for a selected time recovery time interval length Δt(FP;rec). A flight parameter, having a value FP(t=tp) at a time t=tp, is likely to be able to recover to a reference flight parameter value FP(t';ref), lying in a band of reference flight parameter values FP(t';ref;CB), within a time interval given by tp≦t'≦tpΔt(FP;rec), if (or only if) the flight parameter value lies between the first and second recovery band boundary traces.
대표청구항▼
What is claimed is: 1. A method for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter, the method comprising: measuring a value FP(t=tp) of a selected flight parameter FP for an aircraft, for a time, t=tp that is equal to or adjacent to a present time; prov
What is claimed is: 1. A method for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter, the method comprising: measuring a value FP(t=tp) of a selected flight parameter FP for an aircraft, for a time, t=tp that is equal to or adjacent to a present time; providing a sequence {FP(tn;ref)}n of FP reference values for at least two time values, t=tn (n=n1, n2), and an available recovery time interval length Δt(FP;rec); providing at least one constrained solution u(t;tn) for the FP on a graph (t, u(t)), with at least one initial constrained solution value u(t=tn;tn) that is displaced from the corresponding value FP(t=tn;ref); for each constrained solution u(t;tn), providing a reference curve-crossing time value, t=tzc(n), at which u(t;tn) crosses at least one trace of the reference values FP(t;ref) on the graph; computing a coordinate pair (t,u)=(tzc(n)-Δt(FP;rec),u(tzc(n)-Δt(FP;rec) ;tn)) on the graph for the at least two time values, t=tn (n=n1, n2), and identifying this coordinate pair with at least one point on a recovery band boundary trace; connecting at least two of the points with the coordinates (tzc(n)-Δt(FP;rec),u(tzc(n)-Δt(FP;rec);t n)) to provide a portion of a recovery band boundary trace; providing at least first and second non-coincident recovery band boundary traces, (t,FP(t;rec;1)) and (t;FP(t;rec;2)), that are spaced apart from each other for at least one time value t on the graph (t, u(t)); displaying the at least first and second recovery band boundary traces, (t,FP(t;rec;1)) and (t;FP(t;rec;2)), and the value FP(t=tp) of the flight parameter at the time t=tp on the graph (t, u(t)); and providing an operator of the aircraft with information which may be used to bring the flight parameter FP within the recovery band defined by the first and second recovery band boundary traces. 2. The method of claim 1, further comprising: providing a value FP(t=tp;φ) of said selected FP parameter in a selected phase φ of a flight; determining if the value FP(t=tp;φ) likes between, or lies on, said first and second recovery band boundary traces; when the value FP(t=tp;φ) lies between said first and second recovery band boundary traces, or lies on at least one of said first and second recovery band boundary traces, interpreting this condition as indicating that said selected flight parameter is likely to be able to recover form the value FP(t=tp;φ) to at least one of said FP reference values within a time interval of length no greater than Δt(FP;rec). 3. The method of claim 1, further comprising: providing a value FP(t=tp;100 ) of said selected FP parameter in a selected phase φ of a flight; determining if the value FP(t=tp;φ) lies between, or lies on, said first and second recovery band boundary traces; when the value FP(t=tp;φ) does not lie between said first and second recovery band boundary traces, and does not lie on at least one of said first and second recovery band boundary traces, interpreting this condition as indicating that said selected flight parameter is unlikely to be able to recover from the value FP(t=tp;φ) to at least one of said FP reference values within a time interval of length no greater than Δt(FP;rec). 4. The method of claim 1, further comprising providing said constrained quantity u(t;tn) for said FP value as a dimensionless ratio FP(t)/FP0, where FP0 is a selected measured or estimated value of said FP value. 5. The method of claim 1, further comprising providing said constrained value u(t;tn) for said flight parameter FP as a solution to a selected constrained differential equation B'≦c2{d2u/dt2 }+c1{du/dt}+c0·u≦B", where the coefficients c0, c1 and c2 are first, second and third numerical constants, at least one being non-zero, and B' and B" are fourth and fifth numerical constants, at least one being non-zero. 6. A method for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter the method comprising: providing a recovery band in a graph of values (t, u(t)) of a measured flight parameter (FP) for an aircraft versus time t, the recovery band being defined by first and second non-coincident recovery band boundary traces that are spaced apart for at least one time value, and providing a recovery time interval length Δt(FP;rec), having a positive temporal value, where the flight parameter, having a value FP(t=tp) at a time t=tp, is likely to be able to recover to a reference flight parameter value FP(t';ref), lying in a band of reference flight parameter values FP(t';ref;CB), within a time interval given by tp≦t'≦tp+Δt(FP;rec), if the flight parameter value lies between, or lies on, the first and second recovery band boundary traces; and displaying at least one of the recovery band on the graph and the recovery time interval length Δt(FP;rec). 7. The method of claim 6, further comprising providing said reference flight parameter band as a curve having a width of substantially 0. 8. The method of claim 6, further comprising providing said quantity w(t) in said graph as a dimensionless ratio FP(t)/FP0, where FP0 is a selected measured or estimated value of said FP value. 9. The method of claim 6, further comprising providing said value w(t) for said flight parameter FP as a solution to a selected constrained differential equation B'≦c2{d2w/dt2 {+c1{dw/dt}+c0·w≦B", where the coefficients c0, c1 and c2 are first, second and third numerical constants, at least one being non-zero, and B' and B" are fourth and fifth numerical constants, at least one being non-zero. 10. A method for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter the method comprising: providing a recovery band in a graph of values (t, u(t)) of a measured flight parameter (FP) for an aircraft versus time t, the recovery band being defined by first and second non-coincident recovery band boundary traces that are spaced apart for at least one time value, and providing a recovery time interval length Δt(FP;rec), having a positive temporal value, where the flight parameter, having a value FP(t=tp) at a time t=tp, is unlikely to be able to recover to a reference flight parameter value FP(t';ref), lying in a band of reference flight parameter values FP(t';ref;CB), within a time interval given by tp≦t'≦tp+Δt(FP;rec), if the flight parameter value does not lie between, and does not lie on, the first and second recovery band boundary traces; and displaying at least one of the recovery band on the graph and the recovery time interval length Δt(FP;rec). 11. The method of claim 10, further comprising providing said reference flight parameter band as a curve having a width of substantially 0. 12. The method of claim 10, further comprising providing said quantity w(t) in said graph as a dimensionless ratio FP(t)/FP0, where FP0 is a selected measured or estimated value of said FP value. 13. The method of claim 10, further comprising providing said value w(t) for said flight parameter FP as a solution to a selected constrained differential equation B'≦c2{d2w/dt2 }+c1{dw/dt}+c0·w≦B", where the coefficients c0, c1 and c2 are first, second and third numerical constants, at least one being non-zero, and B' and B" are fourth and fifth numerical constants, at least one being non-zero. 14. A system for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter, the system comprising a computer that is programmed: to measure a value FP(tp) of a selected flight parameter FP for an aircraft, for a time, t=tp that is equal to or adjacent to a present time; to provide a sequence {FP(tn;ref)}n of FP reference values for at least two time values, t=tn (n=n1, n2), and an available recovery time interval length Δt(FP;rec); to provide at least one constrained solution u(t;tn) for the FP on a graph (t, u(t)), with at least one initial constrained solution value u(t=tn;tn) that is displaced from the corresponding value FP(t=tn;ref); for each constrained solution u(t;tn), to provide a reference curve-crossing time value, t=tzc(n), at which u(t;tn) crosses at least one trace of the reference values FP(t;ref) on the graph; and to compute a coordinate pair (t,u)=(tzc(n)-Δt(FP;rec),u(tzc(n)-Δt(FP;rec) ;tn)) on the graph for the at least two time values, t=tn (n=n1, n2), and to identify this coordinate pair with at least one point on a recovery band boundary trace; to connect at least two of the points with the coordinates (tzc(n)-Δt(FP;rec),u(tzc(n)-Δt(FP;rec);t n)) to provide a portion of a recovery band boundary trace; to provide at least first and second non-coincident recovery band boundary traces, (t,FP(t;rec;1)) and (t;FP(t;rec;2)), that are spaced apart form each other for at least one time value t on the graph (t, u(t)); and to display the at least first and second recovery band boundary traces, (t,FP(t;rec;1)) and (t;FP(t;rec;2)), and the value FP(t=tp) of the flight parameter at the time t=tp on the graph (t, u(t)); and to provide an operative of the aircraft with information which may be used to bring the flight parameter within the recovery band defined by the first and second recovery band boundary traces. 15. The system of claim 14, wherein said computer is further programmed: to provide a value FP(t=tp;φ) of said selected FP parameter in a selected phase φ of a flight; to determine if the value FP(t=tp;φ) lies between, or lies on, said first and second recovery band boundary traces; and wherein the value FP(t=tp;φ) lies between said first and second recovery band boundary traces, or on at least one of said first and second recovery band boundary traces, to interpret this condition as indicating that said selected flight parameter is likely to be able to recover form the value FP(t=tp;φ) to at least one of said FP reference values within a time interval of length no greater than Δt(FP;rec). 16. The system of claim 14, wherein said computer is further reprogrammed: to provide a value FP(t=tp;φ) of said selected FP parameter in a selected phase φ of a flight; to determine if the value FP(t=tp; φ) lies between, or on, said first and second recovery band boundary traces; when the value FP(t=tp;φ) does not lie between said first and second recovery band boundary traces, and does not lie on at least one of said first and second recovery band boundary traces, to interpret this condition as indicating that said selected flight parameter is unlikely to be able to recover from the value FP(t=tp;φ) to at least one of said FP reference values within a time interval of length no greater than Δt(FP;rec). 17. A system for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter the system comprising a computer that is programmed: to provide a recovery band as a graph of values (t, u(t)) of a measured flight parameter (FP) for an aircraft versus time t, the recovery band being defined by first and second non-coincident recovery band boundary traces that are spaced apart at at least one time value, and to provide a recovery time interval length Δt(FP;rec), having a positive temporal value, where the flight parameter, having a value FP(t=tp) at a time t=tp, is likely to be able to recover to a reference flight parameter value FP(t',ref), lying in a band of reference flight parameter values FP(t';ref;CB), within a time interval given by tp≦t'≦tp+Δt(FP;rec), if the flight parameter value lies between, or on, the first and second recovery band boundary traces; and to display at least one of the recovery band on the graph and the recovery time interval length Δt(FP;rec). 18. The system of claim 17, wherein said compute is further programmed to provide said reference flight parameter band as a curve having a width of substantially 0. 19. A system for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter the system comprising a computer that is programmed: to provide a recovery band as a graph of values (t, u(t)) of a measured flight parameter (FP) for an aircraft versus time t, the recovery band being defined by first and second non-coincident recovery band boundary traces that are spaced apart at at least one time value, and to provide a recovery time interval length Δt(FP;rec), having a positive temporal value, where the flight parameter, having a value FP(t=tp) at a time t=tp,is unlikely to be able to recovery to a reference flight parameter value FP(t';ref), lying in a band of reference flight parameter values FP(t';ref;CB), within a time interval given by tp≦t'≦tp+Δt(FP;rec), if the flight parameter value does not lie between the first and second recovery band boundary traces; and to display at least one of the recovery band on the graph and the recovery time interval length Δt(FP;rec). 20. The system of claim 19, wherein said computer is further programmed to provide said reference flight parameter band as a curve having a width of substantially 0.
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이 특허에 인용된 특허 (5)
Bateman,Charles D.; Gover,John H.; Johnson,Steven C., Aircraft autorecovery systems and methods.
Bice Gregory W. (Lancaster CA) Skoog Mark A. (Lancaster CA) Howard John D. (Ft. Lauderdale FL), Aircraft ground collision avoidance and autorecovery systems device.
Mn, Veeresh Kumar; Kushwaha, Dinesh Kumar; Kumar, Chaitanya Pavan, System and method for aircraft performance predictions for descent and approach phases.
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