Method and system for providing sideslip envelope protection
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-007/70
G06F-019/00
G06G-007/00
G06G-007/76
출원번호
US-0372863
(2012-02-14)
등록번호
US-8718841
(2014-05-06)
발명자
/ 주소
Cherepinsky, Igor
출원인 / 주소
Sikorsky Aircraft Corporation
대리인 / 주소
Cantor Colburn LLP
인용정보
피인용 횟수 :
0인용 특허 :
9
초록▼
A system for providing sideslip envelope protection includes a processor for obtaining values of a sideslip envelope indicative of operating conditions of the aircraft along an axis and for estimating a sideslip angle along the axis from at least one operating condition; and a comparer for comparing
A system for providing sideslip envelope protection includes a processor for obtaining values of a sideslip envelope indicative of operating conditions of the aircraft along an axis and for estimating a sideslip angle along the axis from at least one operating condition; and a comparer for comparing the sideslip angle with the sideslip envelope to generate an output value, where the processor determines a maximum yaw rate from the output value and scales the maximum yaw rate to generate a scaled yaw rate.
대표청구항▼
1. A method for providing sideslip envelope protection to an aircraft, comprising: obtaining, with a processor, sideslip values from a sideslip envelope, the sideslip envelope defines structural limits of operation of the aircraft along an axis;estimating, with the processor, a sideslip angle along
1. A method for providing sideslip envelope protection to an aircraft, comprising: obtaining, with a processor, sideslip values from a sideslip envelope, the sideslip envelope defines structural limits of operation of the aircraft along an axis;estimating, with the processor, a sideslip angle along the axis from at least one operating parameter of the aircraft;comparing, with the processor, the sideslip angle with the sideslip value and generating an output value;determining, with the processor, a maximum yaw rate from the output value; andscaling, with the processor, the maximum yaw rate to generate a scaled yaw rate; wherein the scaled yaw rate corresponds to a variable yaw rate available to the aircraft that is adjusted for the sideslip envelope that remains from the estimated sideslip angle. 2. The method of claim 1, wherein the scaled yaw rate is a function of the sideslip envelope and the maximum yaw rate. 3. The method of claim 1, wherein scaling the maximum yaw rate is performed by a look-up table indexing the maximum yaw rate with the sideslip envelope. 4. The method of claim 1, wherein the operating conditions includes lateral acceleration, attitude, and angular rate. 5. The method of claim 1, further comprising scaling a pedal input as a function of the scaled yaw rate. 6. The method of claim 1, wherein the sideslip envelope corresponds to a maximum pedal displacement. 7. The method of claim 1, further comprising receiving the at least one operating condition from one or more sensors. 8. The method of claim 1, wherein the axis corresponds to the yaw. 9. A system for providing sideslip envelope protection, comprising: a processor for obtaining sideslip values of a sideslip envelope indicative of structural limits of operation of the aircraft along an axis and for estimating a sideslip angle along the axis from at least one of the operating conditions; anda comparer for comparing the sideslip angle with the sideslip envelope to generate an output value;wherein the processor determines a maximum yaw rate from the output value; andwherein the processor scales the maximum yaw rate to generate a scaled yaw rate;wherein the scaled yaw rate corresponds to a variable yaw rate available to the aircraft, the variable yaw rate being adjusted for the sideslip envelope that remains from the estimated sideslip angle. 10. The system of claim 9, wherein the scaled yaw rate is a function of the sideslip envelope and the maximum yaw rate. 11. The system of claim 9, wherein scaling the maximum yaw rate is performed by a look-up table indexing the maximum yaw rate with the sideslip envelope. 12. The system of claim 9, wherein the operating conditions includes lateral acceleration, attitude, and angular rate. 13. The system of claim 9, wherein a controller scales a pedal input as a function of the scaled yaw rate. 14. The system of claim 9, wherein the sideslip envelope corresponds to a maximum pedal displacement. 15. The system of claim 9, wherein the scaled yaw rate corresponds to an available sideslip envelope. 16. The system of claim 9, wherein the axis corresponds to the yaw.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (9)
Middleton Robin (Bellevue WA), Apparatus and method for warning of a high yaw condition in an aircraft.
Randazzo,Pasquale A.; Butkiewicz,John D.; Miller,David G.; Mossman,David C.; Redkoles,Paul; Morse,Channing S., Heading reference command and control algorithm and cueing systems and methods for aircraft turn-to-target maneuvers.
Perez Ricardo L. (Plantsville CT) Barnum Ronald E. (Trumbull CT) Tefft Franklin A. (Killingworth CT), Helicopter pedal feel force proportional to side slip.
Skonieczny Joseph P. (Madison CT) Fogler ; Jr. Donald L. (Milford CT) Gold Phillip J. (Shelton CT) Keller James F. (Media PA) Dryfoos James B. (Wallingford PA), High speed turn coordination for rotary wing aircraft.
Gold Phillip J. (Shelton CT) Fogler ; Jr. Donald L. (Milford CT) Skonieczny Joseph (Madison CT) Keller James F. (Media PA), Turn coordination inhibit for rotary wing aircraft control system.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.