IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0558359
(2000-04-26)
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발명자
/ 주소 |
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출원인 / 주소 |
- Hughes Electronics Corporation
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대리인 / 주소 |
Whelen, John T.Sales, Michael
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인용정보 |
피인용 횟수 :
26 인용 특허 :
5 |
초록
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A system and method employing a rate matching algorithm for providing an optimized pattern for puncturing parity bits of a turbo encoded data word of a given rate to produce a turbo encoded data word of a desired lower rate, to thus eliminate bits from said turbo encoded data word to be transmitted
A system and method employing a rate matching algorithm for providing an optimized pattern for puncturing parity bits of a turbo encoded data word of a given rate to produce a turbo encoded data word of a desired lower rate, to thus eliminate bits from said turbo encoded data word to be transmitted by a transmitter. The system and method determine a final amount of bits to be transmitted in the encoded data word, and determine, based on the final amount of bits in relation to the original number of bits in the encoded data word, the number of parity bits to be eliminated from transmission in the encoded data word. Because the parity bits typically have been inserted into the encoded data word by different encoders, the system and method uses a rate matching algorithm to provide an optimized pattern for puncturing the parity bits so that substantially the same number of parity bits provided by each encoder are punctured.
대표청구항
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A system and method employing a rate matching algorithm for providing an optimized pattern for puncturing parity bits of a turbo encoded data word of a given rate to produce a turbo encoded data word of a desired lower rate, to thus eliminate bits from said turbo encoded data word to be transmitted
A system and method employing a rate matching algorithm for providing an optimized pattern for puncturing parity bits of a turbo encoded data word of a given rate to produce a turbo encoded data word of a desired lower rate, to thus eliminate bits from said turbo encoded data word to be transmitted by a transmitter. The system and method determine a final amount of bits to be transmitted in the encoded data word, and determine, based on the final amount of bits in relation to the original number of bits in the encoded data word, the number of parity bits to be eliminated from transmission in the encoded data word. Because the parity bits typically have been inserted into the encoded data word by different encoders, the system and method uses a rate matching algorithm to provide an optimized pattern for puncturing the parity bits so that substantially the same number of parity bits provided by each encoder are punctured. ach angle to runway end; and third computer readable program means for alerting the aircraft flight crew of an approach inconsistency, if the determined aircraft approach angle to runway end is less than a threshold angular value and one or more parameters based on aircraft position and the received glideslope and localizer signals are met. 10. The computer program product of claim 9, wherein the second computer readable program means for determining aircraft approach angle to runway end determines aircraft approach angle to runway end based on aircraft geometric altitude, a vertical figure of merit, a horizontal figure of merit, runway elevation, and aircraft distance to runway threshold. 11. The computer program product of claim 9, wherein one of the one or more parameters comprises valid glideslope and localizer signals. 12. The computer program product of claim 9, wherein one of the one or more parameters comprises the aircraft being on the front course of the ILS approach. 13. The computer program product of claim 9, wherein one of the one or more parameters comprises the aircraft being within a distance range from the selected runway based on distance to selected runway threshold, horizontal figure of merit, and a runway quality factor. 14. The computer program product of claim 9, wherein one of the one or more parameters comprises the aircraft being within an angular range from the selected runway based on aircraft true track and selected runway bearing. 15. The computer program product of claim 9, wherein one of the one or more parameters comprises the aircraft being below a height above runway altitude value based on geometric altitude, a vertical figure of merit, and runway elevation. 16. The computer program product of claim 9, wherein one of the one or more parameters comprises the received glideslope and localizer signals indicating that the aircraft is within threshold values of center of the ILS approach. 17. An apparatus for alerting an aircraft flight crew of an inconsistency during an instrument landing system (ILS) approach to a selected runway, the apparatus comprising: a component configured to receive glideslope and localizer signals; a component configured to determine aircraft approach angle to runway end; and a component configured to alert the aircraft flight crew of an approach inconsistency, if the determined aircraft approach angle to runway end is less than a threshold angular value and one or more parameters based on aircraft position and the received glideslope and localizer signals are met. 18. The apparatus of claim 17, wherein the component configured to determine aircraft approach angle to runway end determines the aircraft approach angle to runway end based on aircraft geometric altitude, a vertical figure of merit, a horizontal figure of merit, runway elevation, and aircraft distance to runway threshold. 19. The apparatus of claim 17, wherein one of the one or more parameters comprises valid glideslope and localizer signals. 20. The apparatus of claim 17, wherein one of the one or more parameters comprises the aircraft being on the front course of the ILS approach. 21. The apparatus of claim 17, wherein one of the one or more parameters comprises the aircraft being within a distance range from the selected runway based on distance to selected runway threshold, horizontal figure of merit, and a runway quality factor. 22. The apparatus of claim 17, wherein one of the one or more parameters comprises the aircraft being within an angular range from the selected runway based on aircraft true track and selected runway bearing. 23. The apparatus of claim 17, wherein one of the one or more parameters comprises the aircraft being below a height above runway altitude value based on geometric altitude, a vertical figure of merit, and runway elevation. 24. The apparatus of claim 17, wherein one of the one or more parameters comprises the received glideslope and localizer signals indicating t hat the aircraft is within threshold values of center of the ILS approach.
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