IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0336543
(2003-01-03)
|
발명자
/ 주소 |
- Tichenor, Clyde L.
- Ginsburgh, Irwin
|
인용정보 |
피인용 횟수 :
16 인용 특허 :
3 |
초록
▼
An aircraft fuel tank ullage safety system (10) that is designed to maintain the fuel tank ullage (94) of an aircraft fuel tank (90) filled with nitrogen. The nitrogen prevents the fuel tank ullage (94) from becoming filled with flammable fuel fumes which can cause an explosion. The system (10) cons
An aircraft fuel tank ullage safety system (10) that is designed to maintain the fuel tank ullage (94) of an aircraft fuel tank (90) filled with nitrogen. The nitrogen prevents the fuel tank ullage (94) from becoming filled with flammable fuel fumes which can cause an explosion. The system (10) consists of at least one flexible, resilient, air-enclosing container (12) having a container ullage (50) that is dimensioned to substantially occupy the space of the fuel tank ullage (94), a differential pressure sensor (30) that determines the internal pressure of the aircraft's fuel tank (90) and a microcontroller (64) that controls and maintains the volume of the air-enclosing container (12) as determined by the differential pressure sensor (30).
대표청구항
▼
An aircraft fuel tank ullage safety system (10) that is designed to maintain the fuel tank ullage (94) of an aircraft fuel tank (90) filled with nitrogen. The nitrogen prevents the fuel tank ullage (94) from becoming filled with flammable fuel fumes which can cause an explosion. The system (10) cons
An aircraft fuel tank ullage safety system (10) that is designed to maintain the fuel tank ullage (94) of an aircraft fuel tank (90) filled with nitrogen. The nitrogen prevents the fuel tank ullage (94) from becoming filled with flammable fuel fumes which can cause an explosion. The system (10) consists of at least one flexible, resilient, air-enclosing container (12) having a container ullage (50) that is dimensioned to substantially occupy the space of the fuel tank ullage (94), a differential pressure sensor (30) that determines the internal pressure of the aircraft's fuel tank (90) and a microcontroller (64) that controls and maintains the volume of the air-enclosing container (12) as determined by the differential pressure sensor (30). s] NASA Conference Publication 3027, 1988 C. Darden, et al, Status of Sonic Boom Methodology and Understanding. AIAA Report 91-3103, 1991, G. Haglund and Boeing Commercial Airplane Group, HSCT Designs for Reduced Sonic Boom. AIAA-98-2956, 1998, R. Seebass and B. Argrow, Sonic Boom Minimization Revistied. 1952, G. Whitham, The Flow Pattern of a Supersonic Projectile (from Communications on Pure and Applied Math, vol. V, 301-348). 1955, G. Whitham, On the Propagation of Weak Shock Waves. AIAA 68-159, 1968, A. George, Reduction of Sonic Boom by Azimuthal Redistribution of Overpressure. NASA Technical Note D-1494, 1962, H. Carlson, The Lower Bound of Attainable Sonic-Boom Overpressure and Design Methods of Approaching This Limit. NASA Technicla Report TR-213, 1964, H. Carlson, Correlation of Sonic-Boom Theory With Wind-Tunnel and Flight Measurements. NASA Technical Note TN D-2877, F. McLean, Some Nonasymptotic Effects on the Sonic Boom of Large Airplanes. NASA Technical Note TN D-5148, 1969, R. Barger, Investigation of a Class of Bodies that Generate Far-Field Sonic-Boom Shock Strength and Impulse Independent of Body Length and Volume. NASA Technical Note TN D-7218, 1973, H. Carlson, Application of Sonic-Boom Minimization Concepts in Supersonic Transport Design. NASA Technical Note TN D-7842, 1975, C. Darden, Minimization of Sonic-Boom Parameters in Real and Isothermal Atmospheres. NASA Technical Paper 1348, 1979, C. Darden, Sonic-Boom Minimization With Nose-Bluntness Relaxation. NASA Technical Paper 1421, 1979, R. Mack, Wind-Tunnel Investigation of the Validity of a Sonic-Boom-Minimization Concept. NASA Technical Note TN D-7160, 1973, L. Hunton, Some Effects of Wing Planform on Sonic Boom. NASA Technical Note TN D-6832, 1972, C. Thomas, Extrapolation of Sonic Boom Pressure Signatures by the Waveform Parameter Method. Paper, K. Plotkin, Wyle Laboratories, Sonic Boom Minimization: Myth of Reality. NASA SP-147, 1967, A.R. Seebass, Sonic Boom Research. NASA SP 180, 1968, Edited by I. Schwartz, Second Conference on Sonic Boom Research. NASA SP-255, 1971, Edited by I. Schwartz, Third Conference on Sonic Boom Research. United States Co-Pending Application Ser. No. 10/060,656 filed Jan. 30, 2002 and entitled Supersonic Aircraft With Spike For Controlling And Reducing Sonic Boom.
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