Aircraft probe for measuring total temperature and pressure
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
A63B-053/00
G01P-013/00
출원번호
US-0148875
(2000-12-12)
우선권정보
FR-1999-915998 (1999-12-17)
국제출원번호
PCT/FR00/03489
(2000-12-12)
국제공개번호
WO01/44821
(2001-06-21)
발명자
/ 주소
Collot, Lionel
Choisnet, Joë
l
출원인 / 주소
Thales Avionics S.A.
대리인 / 주소
Oblon, Spivak, McClelland, Maier & Neustadt, P.C.
인용정보
피인용 횟수 :
30인용 특허 :
11
초록▼
A probe for an aircraft, making it possible in particular to measure the total temperature of the air flow surrounding the aircraft. The probe includes a moving vane configured to orientate itself in the axis of an air flow surrounding the moving vane and, fixed to the moving vane, a device for meas
A probe for an aircraft, making it possible in particular to measure the total temperature of the air flow surrounding the aircraft. The probe includes a moving vane configured to orientate itself in the axis of an air flow surrounding the moving vane and, fixed to the moving vane, a device for measuring the total temperature of the air flow.
대표청구항▼
1. A probe for an aircraft, comprising:a moving vane configured to orientate itself in an axis of an air flow surrounding the moving vane; andmeans, fixed to the moving vane, for measuring a total temperature of the air flow,wherein the means for measuring the total temperature comprises:a first cha
1. A probe for an aircraft, comprising:a moving vane configured to orientate itself in an axis of an air flow surrounding the moving vane; andmeans, fixed to the moving vane, for measuring a total temperature of the air flow,wherein the means for measuring the total temperature comprises:a first channel comprising an air inlet orifice substantially facing the air flow and an air outlet orifice;a second channel having an air inlet situated in the first channel; anda temperature sensor fixed in the second channel. 2. The probe as claimed in claim 1, wherein the second channel is substantially perpendicular to the first channel. 3. The probe as claimed in claim 1, wherein the first and second channels comprise a plurality of orifices allowing a boundary layer of air flowing through the channels to be bled off toward an outside of the probe. 4. The probe as claimed in claim 2, wherein the first and second channels comprise a plurality of orifices allowing a boundary layer of air flowing through the channels to be bled off toward an outside of the probe. 5. The probe as claimed in claim 1, further comprising, fixed to the moving vane:means for measuring a total pressure of the air flow;means for measuring a static pressure of the air flow; andmeans for measuring an angle of incidence of the aircraft. 6. The probe as claimed in claim 1, further comprising, fixed to the moving vane:means for measuring a total pressure of the air flow;means for measuring a static pressure of the air flow; andmeans for measuring an angle of incidence of the aircraft. 7. The probe as claimed in claim 2, further comprising, fixed to the moving vane:means for measuring a total pressure of the air flow;means for measuring a static pressure of the air flow; andmeans for measuring an angle of incidence of the aircraft. 8. The probe as claimed in claim 3, further comprising, fixed to the moving vane:means for measuring a total pressure of the air flow;means for measuring a static pressure of the air flow; andmeans for measuring an angle of incidence of the aircraft. 9. The probe as claimed in claim 4, further comprising, fixed to the moving vane:means for measuring a total pressure of the air flow;means for measuring a static pressure of the air flow; andmeans for measuring an angle of incidence of the aircraft. 10. The probe as claimed in claim 5, wherein the means for measuring the angle of incidence of the aircraft comprises two incidence pressure tappings each situated on one of faces of the moving vane substantially symmetrically with respect to a plane of symmetry of the moving vane, and wherein an orientation of the moving vane with respect to a direction of the air flow is feedback controlled with pressures recorded at the two incidence pressure tappings being made substantially equal. 11. The probe as claimed in claim 6, wherein the means for measuring the angle of incidence of the aircraft comprises two incidence pressure tappings each situated on one of faces of the moving vane substantially symmetrically with respect to a plane of symmetry of the moving vane, and wherein an orientation of the moving vane with respect to a direction of the air flow is feedback controlled with pressures recorded at the two incidence pressure tappings being made substantially equal. 12. The probe as claimed in claim 7, wherein the means for measuring the angle of incidence of the aircraft comprises two incidence pressure tappings each situated on one of faces of the moving vane substantially symmetrically with respect to a plane of symmetry of the moving vane, and wherein an orientation of the moving vane with respect to a direction of the air flow is feedback controlled with pressures recorded at the two incidence pressure tappings being made substantially equal. 13. The probe as claimed in claim 8, wherein the means for measuring the angle of incidence of the aircraft comprises two incidence pressure tappings each situated on one of faces of the moving vane substa ntially symmetrically with respect to a plane of symmetry of the moving vane, and wherein an orientation of the moving vane with respect to a direction of the air flow is feedback controlled with pressures recorded at the two incidence pressure tappings being made substantially equal. 14. The probe as claimed in claim 9, wherein the means for measuring the angle of incidence of the aircraft comprises two incidence pressure tappings each situated on one of faces of the moving vane substantially symmetrically with respect to a plane of symmetry of the moving vane, and wherein an orientation of the moving vane with respect to a direction of the air flow is feedback controlled with pressures recorded at the two incidence pressure tappings being made substantially equal.
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이 특허에 인용된 특허 (11)
Beigbeder Grard (Paris FRX) Leblond Henri (Versailles FRX), Aircraft probe for measuring aerodynamic parameters of amient flow.
Seidel, Greg A.; Cronin, Dennis J.; Mette, John H.; Koosmann, Mark R.; Schmitz, James A.; Fedele, John R.; Kromer, Dana A., Multi-function air data sensing probe having an angle of attack vane.
Anderson,Peter; Sanger,Roger R.; Lippold,Timothy J.; Cairns,Paul J., Sensor arrangement having an air inflow pattern for preventing direct debris impact.
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