Aircraft tipping alarm system and method using fluid pressure measurement on nose landing gear shock strut
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-025/60
B64D-045/00
B64C-025/34
출원번호
US-0625564
(2015-02-18)
등록번호
US-9522741
(2016-12-20)
발명자
/ 주소
Piroozmandi, Farid
출원인 / 주소
The Boeing Company
인용정보
피인용 횟수 :
0인용 특허 :
10
초록▼
There is provided an aircraft tipping alarm system having a nose landing gear (NLG) shock strut containing hydraulic fluid and having an aperture. The system further has an elongated pressure chamber assembly configured to engage to the aperture. The elongated pressure chamber assembly has an elonga
There is provided an aircraft tipping alarm system having a nose landing gear (NLG) shock strut containing hydraulic fluid and having an aperture. The system further has an elongated pressure chamber assembly configured to engage to the aperture. The elongated pressure chamber assembly has an elongated pressure chamber containing hydraulic fluid and having a pressure sensor device, a first check valve configured to restrict hydraulic fluid flow only into the NLG shock strut, a second check valve configured to restrict hydraulic fluid flow only into the elongated pressure chamber, and a reduced diameter breakable neck section. A potential aircraft tipping back position is indicated when a reduction of pressure of the hydraulic fluid in the NLG shock strut, sensed via the pressure sensor device, is greater than or equal to a pressure reduction threshold.
대표청구항▼
1. An aircraft tipping alarm system for an aircraft, the aircraft tipping alarm system comprising: a nose landing gear (NLG) shock strut containing hydraulic fluid and having an aperture; and,an elongated pressure chamber assembly coupled to the NLG shock strut, the elongated pressure chamber assemb
1. An aircraft tipping alarm system for an aircraft, the aircraft tipping alarm system comprising: a nose landing gear (NLG) shock strut containing hydraulic fluid and having an aperture; and,an elongated pressure chamber assembly coupled to the NLG shock strut, the elongated pressure chamber assembly comprising: an elongated pressure chamber containing hydraulic fluid and having a pressure sensor device;a first check valve positioned at a first end of the elongated pressure chamber, the first check valve restricting hydraulic fluid flow only into the NLG shock strut;a second check valve positioned at a second end of the elongated pressure chamber, the second check valve restricting hydraulic fluid flow only into the elongated pressure chamber; and,a reduced diameter breakable neck section,wherein a potential aircraft tipping back position is indicated when a reduction of pressure of the hydraulic fluid in the NLG shock strut, sensed via the pressure sensor device, is greater than or equal to a pressure reduction threshold. 2. The system of claim 1, wherein the aircraft is a cargo aircraft. 3. The system of claim 1, wherein the NLG shock strut is a nose landing gear (NLG) oleo pneumatic shock strut, and the hydraulic fluid is oleo fluid. 4. The system of claim 1, wherein when the potential aircraft tipping back position is indicated, the pressure sensor device generates and transmits an aircraft tipping alarm signal to produce an aircraft tipping alarm that is sensible to a human being. 5. The system of claim 1, wherein the pressure sensor device comprises a mechanical gauge pressure sensor or a piezoelectric pressure sensor. 6. The system of claim 1, wherein the first check valve is embedded within the NLG shock strut. 7. The system of claim 1, wherein the first check valve is replaced with an open end portion configured to couple with a nose landing gear (NLG) check valve on the NLG shock strut, the NLG check valve being configured to restrict hydraulic fluid flow only into the NLG shock strut. 8. The system of claim 1, wherein the second check valve includes an externally threaded open end portion configured for coupling to a fluid pump and supply assembly. 9. The system of claim 1, wherein the reduced diameter breakable neck section is configured to break away from the NLG shock strut upon impact, and wherein upon breakage of the reduced diameter breakable neck section, only the first check valve remains engaged to the aperture. 10. The system of claim 1, wherein the reduction of pressure of the hydraulic fluid in the NLG shock strut for indicating the potential aircraft tipping back position is adjustable upward or downward. 11. The system of claim 1, wherein the aircraft tipping alarm system further comprises an alarm control system comprising one or more of a controller, a power source, an aircraft tipping alarm apparatus, one or more display units, a system logic, and a cargo handling system deactivator device. 12. The system of claim 1, wherein the potential aircraft tipping back position is indicated when the reduction of pressure of the hydraulic fluid in the NLG shock strut, sensed via the pressure sensor device, is greater than or equal to fifty percent (50%) of a predetermined pressure level of the hydraulic fluid in the NLG shock strut. 13. A cargo aircraft comprising: a nose landing gear (NLG) assembly coupled to a fuselage; and,an aircraft tipping alarm system coupled to the nose landing gear (NLG) assembly, the aircraft tipping alarm system comprising: a nose landing gear (NLG) shock strut containing oleo fluid and having an aperture; and,an elongated pressure chamber assembly configured to engage to the aperture, the elongated pressure chamber assembly comprising: an elongated pressure chamber containing oleo fluid and having a pressure sensor device;a first check valve configured to restrict oleo fluid flow only into the NLG shock strut;a second check valve configured to restrict oleo fluid flow only into the elongated pressure chamber, the second check valve having an externally threaded open end portion configured for coupling to a fluid pump and supply assembly; and,a reduced diameter breakable neck section configured to break away from the NLG shock strut upon impact, and wherein upon breakage of the reduced diameter breakable neck section, only the first check valve remains engaged to the aperture,wherein a potential aircraft tipping back position is indicated when a reduction of pressure of the oleo fluid in the NLG shock strut, sensed via the pressure sensor device, is greater than or equal to fifty percent (50%) of a predetermined pressure level of the oleo fluid in the NLG shock strut. 14. The cargo aircraft of claim 13, wherein the first check valve is embedded within the NLG shock strut. 15. The cargo aircraft of claim 13, wherein the first check valve is replaced with an open end portion configured to couple with a nose landing gear (NLG) check valve on the NLG shock strut, the NLG check valve being configured to restrict oleo fluid flow only into the NLG shock strut. 16. The cargo aircraft of claim 13, wherein the aircraft tipping alarm system further comprises an alarm control system comprising one or more of a controller, a power source, an aircraft tipping alarm apparatus, one or more display units, a system logic, and a cargo handling system deactivator device. 17. The cargo aircraft of claim 13, wherein when the potential aircraft tipping back position is indicated, the pressure sensor device generates and transmits an aircraft tipping alarm signal to produce an aircraft tipping alarm that is sensible to a human being. 18. A method for preventing or alarming against a tipping back position of an aircraft during a loading or unloading of the aircraft on ground, the method comprising the steps of: equipping the aircraft with an aircraft tipping alarm system, the aircraft tipping alarm system comprising an elongated pressure chamber assembly coupled to a nose landing gear (NLG) shock strut via a first check valve, the elongated pressure chamber assembly comprising a pressure sensor device and a reduced diameter breakable neck section;determining a predetermined pressure level of a hydraulic fluid in the NLG shock strut;activating the aircraft tipping alarm system, during the loading or unloading of the aircraft;measuring a reduction of pressure of the hydraulic fluid in the NLG shock strut via the pressure sensor device coupled to an elongated pressure chamber, which is coupled to the NLG shock strut, during the loading or unloading of the aircraft; and,generating and transmitting with the pressure sensor device an aircraft tipping alarm signal, when the reduction of pressure of the hydraulic fluid in the NLG shock strut, sensed via the pressure sensor device, is greater than or equal to fifty percent (50%) of the predetermined pressure level, indicating a potential aircraft tipping back position. 19. The method of claim 18, further comprising a step of producing an aircraft tipping alarm that is sensible by a human being, upon the generating and transmitting of the aircraft tipping alarm signal. 20. The method of claim 18, further comprising a step of partially or fully deactivating a cargo handling system engaged in the loading or unloading of the aircraft, upon the generating of the aircraft tipping alarm signal. 21. The method of claim 18, wherein the step of equipping the aircraft further comprising equipping a cargo aircraft with the aircraft tipping alarm system, and further comprising a step of embedding the first check valve of the aircraft tipping alarm system within the NLG shock strut, where the first check valve is part of the elongated pressure chamber. 22. The method of claim 21, wherein the step of equipping the aircraft further comprising a step of replacing the first check valve of the elongated pressure chamber assembly with an open end portion configured to couple with a nose landing gear (NLG) check valve on the NLG shock strut, the NLG check valve being configured to restrict hydraulic fluid flow only into the NLG shock strut. 23. The method of claim 18, further comprising a step of once the aircraft tipping alarm system is activated and generates and transmits the aircraft tipping alarm signal, resetting the aircraft tipping alarm system to continue loading or unloading the aircraft by increasing a pressure in the elongated pressure chamber to the predetermined pressure level.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (10)
Nance,C. Kirk, Aircraft landing gear kinetic energy monitor.
Gouette, Geoffrey E.; White, Steven B.; Merrick, James M.; Weed, Kristine K.; VanGinhoven, Paul A.; Wehr, Steven L.; Fossen, Ralph E.; Piroozmandi, Farid; Collen, Brian L.; Taneja, Sudershan K., Aircraft tip alarm system.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.