IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0891291
(2010-09-27)
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등록번호 |
US-8527233
(2013-09-03)
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발명자
/ 주소 |
- McIntyre, Melville Duncan Walter
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
2 |
초록
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The different advantageous embodiments provide an apparatus and method for identifying an airspeed for an aircraft. In one advantageous embodiment, an apparatus is provided. The apparatus consists of a plurality of pitot-static probes. The plurality of pitot-static probes generate a first data. The
The different advantageous embodiments provide an apparatus and method for identifying an airspeed for an aircraft. In one advantageous embodiment, an apparatus is provided. The apparatus consists of a plurality of pitot-static probes. The plurality of pitot-static probes generate a first data. The apparatus also consists of a plurality of angle of attack sensor systems. The plurality of angle of attack sensor systems generate a second data. The apparatus also consists of a plurality of light detection and ranging sensors. The light detection and ranging sensors generates a third data. The apparatus also consists of a signal consolidation system configured to detect errors in the first data generated by the plurality of pitot-static probes, the second data generated by the plurality of angle of attack sensor systems, and the third data generated by the plurality of light detection and ranging sensors.
대표청구항
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1. An apparatus comprising: a plurality of pitot-static probes, wherein each of the plurality of pitot-static probes is a first sensor type, and wherein the plurality of pitot-static probes is configured to generate first data, and further wherein the first data comprises a first total pressure valu
1. An apparatus comprising: a plurality of pitot-static probes, wherein each of the plurality of pitot-static probes is a first sensor type, and wherein the plurality of pitot-static probes is configured to generate first data, and further wherein the first data comprises a first total pressure value and a first static pressure value for an environment surrounding an aircraft;a plurality of angle of attack sensor systems, wherein each of the plurality of angle of attack sensor systems is a second sensor type, and wherein the plurality of angle of attack sensor systems are configured to generate second data, and further wherein the second data comprises a second total pressure value and a second static pressure value for the environment surrounding the aircraft;a plurality of light detection and ranging sensors, wherein each of the light detection and ranging sensors are a third sensor type, and wherein the plurality of light detection and ranging sensors are configured to generate third data, and further wherein the third data comprises a third total pressure value and a third static pressure value for the environment surrounding the aircraft; anda signal consolidation system configured to detect errors in the first data generated by the plurality of pitot-static probes, the second data generated by the plurality of angle of attack sensor systems, and the third data generated by the plurality of light detection and ranging sensor systems. 2. The apparatus of claim 1, wherein the signal consolidation system comprises: a processing unit configured to consolidate the first data, the second data, and the third data. 3. The apparatus of claim 1, wherein the signal consolidation system comprises a component selected from a plurality of circuits, a plurality of integrated circuits, and a programmable logic array. 4. The apparatus of claim 1, wherein in detecting the errors in the first data generated by the plurality of pitot-static probes, the second data generated by the plurality of angle of attack sensor systems, and the third data generated by the plurality of light detection and ranging sensors, the signal consolidation system is configured to identify a fourth total pressure value for the environment using the first total pressure value, the second total pressure value, and the third total pressure value; and identify a fourth static pressure value for the environment surrounding the aircraft using the first static pressure value, the second static pressure value, and the third static pressure value. 5. The apparatus of claim 4, wherein in identifying the fourth total pressure value for the environment using the first total pressure value, the second total pressure value, and the third total pressure value, the signal consolidation system is configured to identify a first middle value from the first total pressure value, the second total pressure value, and the third total pressure value to form a consolidated total pressure value for the environment. 6. The apparatus of claim 5, wherein in identifying the fourth static pressure value for the environment using the first static pressure value, the second static pressure value, and the third static pressure value, the signal consolidation system is configured to identify a second middle value from the first static pressure value, the second static pressure value, and the third static pressure value to form a consolidated static pressure value for the environment. 7. The apparatus of claim 6, wherein the signal consolidation system is further configured to identify an airspeed for the aircraft from the first middle value and the second middle value. 8. The apparatus of claim 1, wherein each of the plurality of angle of attack sensor systems comprises: an angle of attack vane sensor associated with a forward fuselage of the aircraft;an inertial sensor system configured to generate inertial data for the aircraft;a global positioning system receiver configured to generate an altitude above a mean sea level for the aircraft and a synthetic static pressure value using a lift model and the inertial data. 9. An apparatus comprising: a plurality of pitot-static probes, wherein each of the plurality of pitot-static probes is a first sensor type, and wherein the plurality of pitot-static probes are configured to generate first data such that the first data comprises a first total pressure value and a first static pressure value for an environment surrounding an aircraft;a plurality of angle of attack sensor systems, wherein each of the plurality of angle of attack sensor systems is a second sensor type, and wherein the plurality of angle of attack sensor systems are configured to generate second data such that the second data comprises a second total pressure value and a second static pressure value for the environment surrounding the aircraft;a plurality of Venturi tubes, wherein each of the plurality of Venturi tubes is a third sensor type, and wherein the plurality of Venturi tubes are configured to generate third data such that the third data comprises a third total pressure value and a third static pressure value for the environment surrounding the aircraft; anda signal consolidation system configured to detect errors in the first data generated by the plurality of pitot-static probes, the second data generated by the plurality of angle of attack sensor systems, and the third data generated by the plurality of Venturi tubes. 10. The apparatus of claim 9, wherein the signal consolidation system comprises a computer readable storage medium, and computer readable program code, stored on a non-transitory computer readable storage medium, for detecting the errors in the first data, the second data, and the third data. 11. The apparatus of claim 9 further comprising: a processing unit configured to run a computer readable program code stored on a non-transitory computer readable storage medium. 12. The apparatus of claim 9, wherein in being configured to correct errors in the first data generated by the plurality of pitot-static probes, the second data generated by the plurality of angle of attack sensor systems, and the third data generated by the plurality of Venturi tubes, the signal consolidation system is configured to identify a fourth total pressure value for the environment using the first total pressure value, the second total pressure value, and the third total pressure value; and identify a fourth static pressure value for the environment surrounding the aircraft using the first static pressure value, the second static pressure value, and the third static pressure value. 13. The apparatus of claim 12, wherein in identifying the fourth total pressure value for the environment using the first total pressure value, the second total pressure value, and the third total pressure value, the signal consolidation system is configured to identify a first middle value from the first total pressure value, the second total pressure value, and the third total pressure value to form a consolidated total pressure value for the environment. 14. The apparatus of claim 13, wherein in being configured to identify the fourth static pressure value for the environment using the first static pressure value, the second static pressure value, and the third static pressure value, the signal consolidation system is configured to identify a second middle value from the first static pressure value, the second static pressure value, and the third static pressure value to form a consolidated static pressure value for the environment. 15. The apparatus of claim 14, wherein the signal consolidation system is further configured to identify an airspeed for the aircraft from the first middle value and the second middle value. 16. A method for identifying an airspeed for an aircraft, the method comprising: generating, using a signal consolidation system receiving input from a plurality of pitot-static probes, a first total pressure value and a first static pressure value for an environment surrounding the aircraft;generating, using the signal consolidation system receiving input from a plurality of light detection and ranging sensors, a second total pressure value and a second static pressure value for the environment surrounding the aircraft;generating, using the signal consolidation system receiving input from a plurality of angle of attack sensor systems, a third total pressure value and a third static pressure value for the environment surrounding the aircraft;detecting, using the signal consolidation system receiving errors in the first total pressure value, the first static pressure value, the second total pressure value, the second static pressure value, the third total pressure value, and the third static pressure value to form a consolidated total pressure value and a consolidated static pressure value; andidentifying, using a computer system implementing the signal consolidation system, the airspeed for the aircraft from the consolidated total pressure value and the consolidated static pressure value.
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