Systems and methods for velocity profile based approach to point control
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05D-001/00
G05D-001/08
G05D-003/00
G06F-007/00
G06F-017/00
출원번호
US-0917091
(2010-11-01)
등록번호
US-8712607
(2014-04-29)
발명자
/ 주소
Litwinowicz, Anthony
출원인 / 주소
Sikorsky Aircraft Corporation
대리인 / 주소
Cantor Colburn LLP
인용정보
피인용 횟수 :
0인용 특허 :
34
초록▼
A method for velocity profile based approach to point control for an aircraft includes determining a distance from the aircraft to a target point; determining a velocity command based on the distance to the target point and a desired acceleration; and issuing the velocity command. A velocity profile
A method for velocity profile based approach to point control for an aircraft includes determining a distance from the aircraft to a target point; determining a velocity command based on the distance to the target point and a desired acceleration; and issuing the velocity command. A velocity profile based approach to point control module for an aircraft and a computer program product comprising a computer readable storage medium containing computer code that, when executed by a computer, implements a method for velocity profile based approach to point control are also provided.
대표청구항▼
1. A computer-implemented method for velocity profile based approach to point control for an aircraft, the method comprising: determining, by a processor of a computer, a distance from the aircraft to a target point;determining a velocity command based on the distance to the target point and a desir
1. A computer-implemented method for velocity profile based approach to point control for an aircraft, the method comprising: determining, by a processor of a computer, a distance from the aircraft to a target point;determining a velocity command based on the distance to the target point and a desired acceleration, wherein the velocity command is determined based on a square root of a product of two times the distance to the target point and the desired acceleration; andissuing the velocity command. 2. The method of claim 1, further comprising repeating determining the distance to the target point, determining the velocity command, and issuing the velocity command until the aircraft is at a hover at the target point. 3. The method of claim 1, wherein the issued velocity command is used as a reference by a groundspeed controller to control a velocity of the aircraft. 4. The method of claim 1, wherein the desired acceleration is configured by a pilot, or is a default value. 5. The method of claim 1, wherein the distance from the aircraft to the target point is a longitudinal distance, the desired acceleration is a desired longitudinal acceleration, and the velocity command is a longitudinal velocity command. 6. The method of claim 1, wherein the distance from the aircraft to the target point is a lateral distance, the desired acceleration is a desired lateral acceleration, and the velocity command is a lateral velocity command. 7. The method of claim 1, wherein the velocity command is limited by a predetermined velocity limit. 8. A velocity profile based approach to point control computer module for an aircraft, which comprises: a processor configured to: determine a distance from the aircraft to a target point;determine a velocity command based on the distance to the target point and a desired acceleration, wherein the velocity command is determined based on a square root of a product of two times the distance to the target point and the desired acceleration; andissue the velocity command. 9. The approach to point control module of claim 8, further comprising repeating determining the distance to the target point, determining the velocity command, and issuing the velocity command until the aircraft is at a hover at the target point. 10. The approach to point control module of claim 8, further comprising a groundspeed controller configured to use the issued velocity command as a reference control a velocity of the aircraft. 11. The approach to point control module of claim 8, wherein the desired acceleration is configured by a pilot, or is a default value. 12. The approach to point control module of claim 8, wherein the target point is defined by a set of longitudinal and lateral coordinates, and the approach to point control module comprises a longitudinal velocity module and a lateral velocity module. 13. The approach to point control module of claim 12, wherein the longitudinal velocity module determines a longitudinal distance from the aircraft to the target point, a longitudinal desired acceleration, and a longitudinal velocity command, and the longitudinal velocity module issues a longitudinal velocity command. 14. The approach to point control module of claim 12, wherein the lateral velocity module determines a lateral distance from the aircraft to the target point, a lateral desired acceleration, and a lateral velocity command, and the lateral velocity module issues a lateral velocity command. 15. The approach to point control module of claim 8, further comprising a velocity limiter configured to limit the velocity command to a predetermined velocity limit. 16. A computer program product comprising a computer readable storage medium containing computer code that, when executed by a computer, implements a method for velocity profile based approach to point control, wherein the method comprises: determining a distance from the aircraft to a target point;determining a velocity command based on the distance to the target point and a desired acceleration, wherein the velocity command is determined based on a square root of a product of two times the distance to the target point and the desired acceleration; andissuing the velocity command. 17. The approach to point control module of claim 16, further comprising repeating determining the distance to the target point, determining the velocity command, and issuing the velocity command until the aircraft is at a hover at the target point.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (34)
Rogers, Steven P.; Asbury, Charles N., Aircraft future position and flight path indicator symbology.
Bice Gregory W. (Lancaster CA) Skoog Mark A. (Lancaster CA) Howard John D. (Ft. Lauderdale FL), Aircraft ground collision avoidance and autorecovery systems device.
Wright Stuart C. (Milford CT) Adams Don L. (Fairfield CT) Fischer William C. (Monroe CT) Verzella David J. (Guilford CT), Dual inner loop fault inhibit of aircraft outer loop.
Fowler Donald W. (Oxford CT) Lappos Nicholas D. (Milford CT) Edwards Joan A. (Fairfield CT), Helicopter integrated fire and flight control having a pre-launch and post-launch maneuver director.
Nishida Masao,JPX ; Taka Yasuhiro,JPX ; Nakajima Toshikazu,JPX ; Nakaue Keiichiro,JPX ; Otsuka Ryuji,JPX ; Shiomi Kakuichi,JPX ; Kusui Yoichi,JPX, Individual guidance system for aircraft in an approach control area under automatic dependent surveillance.
Baker Donald H. (Phoenix AZ) Bowe Larry J. (Phoenix AZ) Manning Kenzel P. (Phoenix AZ) Post William C. (Scottsdale AZ), Vertical path control for aircraft area navigation system.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.