[특허]Method for securing a ground speed used an algorithm for guiding landing of an aircraft, associated computer program and device

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Method for securing a ground speed used an algorithm for guiding landing of an aircraft, associated computer program and device

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/06 G08G-005/00 G01C-023/00 G08G-005/02
출원번호	US-0592262 (2015-01-08)
등록번호	US-9377783 (2016-06-28)
우선권정보	FR-14 00052 (2014-01-10)
발명자 / 주소	Riedinger, Marc Lissajoux, Sylvain
출원인 / 주소	THALES
대리인 / 주소	Troutman Sanders LLP
인용정보	피인용 횟수 : 0 인용 특허 : 9

초록
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A method for securing a ground speed used for guiding landing of an aircraft by determining a ground speed of the aircraft and determining a landing guidance instruction based on the determined ground speed. Next, estimate the vertical speed of the aircraft and limit, during guidance along a glide path having a descent angle, the determined ground speed as a function of the estimated vertical speed. The guidance instruction is based on the limited ground speed. Further, measure the height of the aircraft and compare it with a threshold height. If the measured height is greater than the threshold height, limit the ground speed as a function of acceleration measurements. If the measured height is below the threshold height, limiting the ground speed as a function of the estimated vertical speed and as a function of acceleration measurements of the aircraft taken once threshold height has been crossed.

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청구항
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1. A method securing a ground speed used in an algorithm guiding landing of an aircraft above a flare portion, comprising the following steps: determining a ground speed of the aircraft, using an inertial sensor;determining, using a computer, at least one landing guidance instruction based on at least said determined ground speed of the aircraft;estimating a vertical speed of the aircraft using a reference system;during guidance along a glide path describing a given descent angle, limiting said determined ground speed of the aircraft as a function of the estimated vertical speed;wherein the guidance instruction being determined based on said limited ground speed;measuring a height of the aircraft; andcomparing the measured height of the aircraft with a threshold height;wherein if the measured height is greater than the threshold height, the limitation of the ground speed comprises the limitation, as a function of the estimated vertical speed, of a ground speed of the aircraft determined as a function of measurements performed by a first sensor of the aircraft;wherein if the measured height is below the threshold height, the limitation of the ground speed comprises the limitation, as a function of the estimated vertical speed, of a ground speed of the aircraft determined as a function of acceleration measurements of the aircraft performed by a second sensor different from the first sensor since the threshold height has been crossed, excluding any measurement taken once the threshold height has been crossed by the first sensor separate from the second sensor, and further as a function of the ground speed of the aircraft as limited in a step for limiting a ground speed of the aircraft determined as a function of measurements performed by said first acceleration sensor before crossing the threshold height; andwherein the first sensor acts independently of the second sensor. 2. The method securing a ground speed used in an aircraft landing algorithm according to claim 1, wherein the ground speed is limited as a function of a ratio between said estimated vertical speed and tan(γ), where the angle γ has a value comprised in the range between 2° and 10°. 3. The method securing a ground speed used in an aircraft landing algorithm according to claim 2, wherein the ground speed is limited as a function of a ratio between said estimated vertical speed and the tangent of the descent angle of the glide path. 4. The method securing a ground speed used in an aircraft landing algorithm according to claim 2, wherein said limited ground speed is equal to the median of the set comprising the determined ground speed, the result of the sum of said ratio and a first, positive constant, and the result of the sum of said ratio and a second, negative constant. 5. The method securing a ground speed used in an algorithm for guiding landing of an aircraft according to claim 1, wherein said measurements done by a first aircraft sensor comprise acceleration measurements. 6. The method securing a ground speed used in an aircraft landing algorithm according to claim 1, wherein the precision level of the determination of the aircraft's ground speed by the first sensor is higher than the precision level of the determination of the aircraft's ground speed by the second sensor, and wherein the aircraft further comprises a third sensor similar to the second sensor such that the accuracy of said aircraft acceleration measurements done by the second sensor is validated based on acceleration measurements done by the third sensor. 7. The method securing a ground speed used in an aircraft landing algorithm according to claim 1, wherein the ground speed is limited as a function of a ration between said estimated vertical speed and tan(γ), where the angle γ has a value comprised in a range from 2.5 to 3.5 °. 8. A computer program that can be installed in a landing guidance device of an aircraft, said program comprising instructions for carrying out the following steps for securing a ground speed used in an algorithm for guiding an aircraft above a flare portion when the program is run by a processor of said landing guidance device: determining a ground speed of the aircraft;using a computer to determine at least one landing guidance instruction based on at least said determined ground speed of the aircraft;estimating a vertical speed of the aircraft;during guidance along a glide path describing a given descent angle, limiting said determined ground speed of the aircraft as a function of the estimated vertical speed;wherein the guidance instruction being determined based on said limited ground speed;measuring a height of the aircraft; andcomparing the measured height of the aircraft with a threshold height;wherein if the measured height is greater than the threshold height, the limitation of the ground speed comprises the limitation, as a function of the estimated vertical speed, of a ground speed of the aircraft determined as a function of measurements performed by a first sensor of the aircraft;wherein if the measured height is below the threshold height, the limitation of the ground speed comprises the limitation, as a function of the estimated vertical speed, of a ground speed of the aircraft determined as a function of acceleration measurements of the aircraft performed by a second sensor different from the first sensor since the threshold height has been crossed, excluding any measurement taken once the threshold height has been crossed by the first sensor separate from the second sensor, and further as a function of the ground speed of the aircraft as limited in a step for limiting a ground speed of the aircraft determined as a function of measurements performed by said first acceleration sensor before crossing the threshold height; andwherein the first sensor acts independently of the second sensor. 9. A landing guidance device for an aircraft, comprising: a ground speed sensor securing a ground speed of the aircraft and determining at least one landing guidance instruction above the flare portion as a function of said at least one determined ground speed;a vertical speed sensor estimating a vertical speed of the aircraft and, during guidance along a glide path describing a given descent angle, determining said determined aircraft ground speed and securing said determined ground speed of the aircraft by limiting it as a function of the estimated vertical speed;a processor determining the guidance instruction as a function of said limited ground speed; anda height sensor measuring a height of the aircraft and comparing the measured height of the aircraft with a threshold height;wherein if the measured height is greater than the threshold height, for limiting said ground speed by limiting, as a function of the estimated vertical speed, a ground speed of the aircraft determined as a function of measurements performed by a first sensor of the aircraft;wherein if the measured height is below the threshold height, for limiting the ground speed by limiting, as a function of the estimated vertical speed, a ground speed of the aircraft determined as a function of acceleration measurements of the aircraft performed by a second sensor different from the first sensor since the threshold height has been crossed, excluding any measurement taken once the threshold height has been crossed by the first sensor separate from the second sensor, and further as a function of the ground speed of the aircraft as limited by the device determined by limiting a ground speed of the aircraft determined as a function of measurements performed by said first acceleration sensor before crossing the threshold height; andwherein the first sensor acts independently of the second sensor. 10. The aircraft landing guidance device according to claim 9, further comprising a limiter limiting the ground speed as a function of a ratio between said estimated vertical speed and tan(γ), where the angle γ has a value comprised in the range between 2° and 10°. 11. The aircraft landing guidance device according to claim 10, further comprising a second limiter limiting the ground speed as a function of a ratio between said estimated vertical speed and the tangent of the descent angle of the glide path. 12. The aircraft landing guidance device according to claim 10, wherein said limited ground speed is equal to the median of the set comprising the determined ground speed, the result of the sum of said ratio and a first, positive constant, and the result of the sum of said ratio and a second, negative constant. 13. The aircraft landing guidance device according to claim 9, wherein said measurements performed by the first sensor comprise acceleration measurements. 14. The aircraft landing guidance device according to claim 9, wherein the precision level of the determination of the aircraft's ground speed by the first sensor being higher than the precision level of the determination of the aircraft's ground speed by the second sensor, and the aircraft further comprising a third sensor similar to the second sensor, said device being suitable for validating the accuracy of said aircraft acceleration measurements done by the second sensor as a function of acceleration measurements done by the third sensor. 15. The aircraft landing guidance device according to claim 9, further comprising a limiter limiting the ground speed as a function of a ration between said estimated vertical speed and tan(γ), where the angle γ has a value comprised in a range from 2.5 3.5°.

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Method for securing a ground speed used an algorithm for guiding landing of an aircraft, associated computer program and device

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Method for securing a ground speed used an algorithm for guiding landing of an aircraft, associated computer program and device

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