IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0877467
(2007-10-23)
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등록번호 |
US-8209115
(2012-06-26)
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우선권정보 |
FR-06 09408 (2006-10-26) |
발명자
/ 주소 |
- Lucas, Fabrice
- De Menorval, Jean-Louis
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출원인 / 주소 |
|
대리인 / 주소 |
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인용정보 |
피인용 횟수 :
10 인용 특허 :
15 |
초록
Method and device for aiding the guidance of an aircraft along a flight trajectory. The device makes it possible to cause the aircraft to pass at least one particular waypoint of the flight trajectory, at an associated target time, and to do so to within an associated temporal tolerance.
대표청구항
▼
1. A method for providing guidance information of an aircraft (A) along a flight trajectory (TV1, TV2), wherein: a) generating first input parameters, comprising:at least one start point (PD) corresponding to the start of a first segment (S1) on said flight trajectory (TV1);at least one end point (P
1. A method for providing guidance information of an aircraft (A) along a flight trajectory (TV1, TV2), wherein: a) generating first input parameters, comprising:at least one start point (PD) corresponding to the start of a first segment (S1) on said flight trajectory (TV1);at least one end point (PF) corresponding to the end of this first segment (S1) on said flight trajectory (TV1);an arrival time corresponding to the required arrival time of the aircraft (A) at said end point (PF); anda first temporal error margin;b) on the basis of said start point (PD), of said end point (PF), of said arrival time and of said first temporal error margin, automatically:determining at least said first segment (S1) which starts at said start point (PD) and finishes at said end point (PF);integrating this first segment (S1) into said flight trajectory (TV1) in such a way as to obtain a first modified trajectory (TM1);determining a first vertical speed profile, indicating the vertical speed of said aircraft (A) exclusively along said first segment (S1), which allows the aircraft (A) to arrive at said final point (PF) at said arrival time;deducing a target time for at least one waypoint (PP, PF) which is situated on said first segment (S1), from said first vertical speed profile, said target time defining the time at which the aircraft (A) must pass said waypoint (PP, PF);determining a temporal tolerance relating to the compliance with said target time at said waypoint (PP, PF) at least on the basis of said first temporal error margin; andproviding at least first guidance aid information comprising said first modified trajectory (TM1), and, for each waypoint (PP, PF), the target time and the temporal tolerance that are associated with said waypoint. 2. The method as claimed in claim 1, wherein said step b) is implemented for a plurality of different waypoints (PP, PF). 3. The method as claimed in claim 1, wherein in a subsequent step c), the aircraft (A) is guided with the aid of said first guidance aid information, by carrying out a slaving making it possible to cause the aircraft (A) to pass each waypoint (PP, PF) at the associated target time, and within the associated temporal tolerance. 4. The method as claimed in claim 1, wherein in step a), an operator manually inputs at least some of said first input parameters by employing an input unit. 5. The method as claimed in claim 1, wherein in step a), at least some of said first input parameters are automatically received by a data reception unit. 6. The method as claimed in claim 1, wherein said waypoint corresponds to said end point (PF), said associated target time corresponds to said arrival time, and said associated temporal tolerance corresponds to said temporal error margin. 7. The method as claimed in claim 1, wherein: said waypoint corresponds to a point (PP) of said first segment (S1), other than said end point (PF);said associated target time is an intermediate time at which the aircraft (A) must pass said waypoint (PP) in such a way as to arrive at said arrival time at said end point (PF); andsaid associated temporal tolerance is such that it makes it possible to comply with the arrival time at said end point (PF) to within said temporal error margin. 8. The method as claimed in claim 1, wherein at least steps a) and b) are carried out for a plurality of first segments (S1). 9. The method as claimed in claim 1, wherein at least said start and end points (PD, PF) are presented on a navigation screen. 10. The method as claimed in claim 1, wherein: in step a), second input parameters are moreover generated, comprising:a plurality of successive auxiliary points (P1 to P8) of said flight trajectory (TV2), the first (P1) of said successive auxiliary points in the direction of flight (E) of the aircraft (A) corresponding to said end point (PF);associated with at least some of said auxiliary points (P1 to P8) times of passage corresponding to the times at which the aircraft (A) must pass respectively these auxiliary points (P1 to P8); anda second temporal error margin; andstep b) includes, on the basis of said auxiliary points (P1 to P8), of said times of passage and of said second temporal error margin, automatically:determining at least one second segment (S2), which comprises said auxiliary points (P1 to P8), which begins at the first (P1) of said successive auxiliary points, that is to say at said end point (PF) of said first segment (S1), and which finishes at the last (P8) of said auxiliary points;integrating this second segment (S2) following said first segment (S1) into said first modified trajectory in such a way as to obtain a second modified trajectory (TM2), said first and second segments forming a global segment (SG);determining a target time at which the aircraft (A) must pass said auxiliary point for each auxiliary point with which no time of passage is associated, the target time of the other auxiliary points corresponding to the associated times of passage;deducing a second vertical speed profile, indicating the vertical speed of said aircraft (A) exclusively along said second segment (S2), which allows the aircraft (A) to pass said auxiliary points (P1 to P8) at the associated target times;determining an auxiliary temporal tolerance at least on the basis of said second temporal error margin; andproviding second guidance aid information comprising said second modified trajectory (TM2), said auxiliary temporal tolerance and, for each auxiliary point (P1 to P8), the associated target time. 11. The method as claimed in claim 10, wherein in step c), the aircraft (A) is guided with the aid of said second guidance aid information, by carrying out a slaving making it possible to cause the aircraft (A) to pass each auxiliary point (P1 to P8) at the associated target time, and to do so to within said auxiliary temporal tolerance. 12. The method as claimed in claim 10, wherein in step a), an operator manually inputs at least some of said second input parameters by employing an input unit. 13. The method as claimed in claim 10, wherein in step a), at least some of said second input parameters are automatically received by a data reception unit. 14. The method as claimed in claim 10, wherein at least said auxiliary points (P1 to P8) of said second segment (S2) are presented on a navigation screen. 15. A device for aiding the guidance of an aircraft along a flight trajectory, which device comprises: an input unit for inputting into a flight management system first input parameters comprising:at least one start point (PD) corresponding to the start of a first segment (S1) on the flight trajectory (TV1) of the aircraft (A);at least one end point (PF) corresponding to the end of this first segment (S1) on said flight trajectory (TV1);an arrival time corresponding to the required arrival time of the aircraft (A) at said end point (PF); anda first temporal error margin;said flight management system comprising:an integration unit for integrating said first segment (S1) into said flight trajectory (TV1) in such a way as to obtain a first modified trajectory (TM1);a determination unit for determining a first vertical speed profile, indicating the vertical speed of said aircraft (A) exclusively along said first segment (S1), which allows the aircraft (A) to arrive at said final point (PF) at said arrival time;a deducing unit for deducing a target time for at least one waypoint (PP, PF) which is situated on said first segment (S1), from said first vertical speed profile, said target time defining the time at which the aircraft (A) must pass said waypoint (PP, PF); anda determination unit for determining a temporal tolerance relating to the compliance with said target time at said waypoint (PP, PF);a guidance system; anda transmission unit for providing said guidance system with at least first guidance aid information comprising said first modified trajectory (TM1), and, for each waypoint (PP, PF), the target time and the temporal tolerance that are associated with said waypoint (PP, PF), wherein:said guidance system guides the aircraft (A) with the aid of said first guidance aid information, by carrying out a slaving making it possible to cause the aircraft (A) to pass each waypoint (PP, PF) at the associated target time, and within the associated temporal tolerance. 16. The device as claimed in claim 15, wherein: said input unit is formed so as to input, moreover, second input parameters comprising:a plurality of successive auxiliary points (P1 to P8) of said flight trajectory (TV2), the first (P1) of said successive auxiliary points in the direction of flight (E) of the aircraft (A) corresponding to said end point (PF);associated with at least some of said auxiliary points (P1 to P8), times of passage corresponding to the times at which the aircraft (A) must pass respectively these auxiliary points (P1 to P8); anda second temporal error margin;said flight management system moreover comprises:an integration unit for integrating this second segment (S2), following said first segment (S1) into said first modified trajectory (TM1) in such a way as to obtain a second modified trajectory (TM2), said first and second segments forming a global segment (SG), said second segment (S2) comprising said auxiliary points (P1 to P8), beginning at the first (P1) of said successive auxiliary points, that is to say at said end point (PF) of said first segment (S1), and finishing at the last (P8) of said auxiliary points;a determination unit for determining, for each auxiliary point with which no time of passage is associated, a target time at which the aircraft (A) must pass said auxiliary point, the target time of the other auxiliary points corresponding to the associated times of passage;a deduction unit for deducing a second vertical speed profile indicating the vertical speed of said aircraft (A) exclusively along said second segment (S2), which allows the aircraft (A) to pass said auxiliary points (P1 to P8) at the associated target times; anda determination unit for determining an auxiliary temporal tolerance, wherein:said transmission unit is formed so as to provide said guidance system (5) with second guidance aid information, comprising said second modified trajectory (TM2), said auxiliary temporal tolerance and, for each auxiliary point (P1 to P8), the associated target time; andsaid guidance system is formed so as to guide the aircraft (A) with the aid of said second guidance aid information, by carrying out a slaving making it possible to cause the aircraft (A) to pass each auxiliary point (P1 to P8) at the associated target time, and to do so within said auxiliary temporal tolerance. 17. An aircraft, wherein it comprises a device such as that specified under claim 15. 18. A method for providing guidance information of an aircraft (A) along a flight trajectory (TV1, TV2), the method comprising: a) generating first input parameters comprising:at least one start point (PD) corresponding to the start of a first segment (S1) on said flight trajectory (TV1);at least one end point (PF) corresponding to the end of this first segment (S1) on said flight trajectory (TV1);an arrival time corresponding to the required arrival time of the aircraft (A) at said end point (PF); anda first temporal error margin;b) on the basis of said start point (PD), of said end point (PF), of said arrival time and of said first temporal error margin, automatically:determining at least said first segment (S1) which starts at said start point (PD) and finishes at said end point (PF);integrating this first segment (S1) into said flight trajectory (TV1) in such a way as to obtain a first modified trajectory (TM1);determining a first vertical speed profile, indicating the vertical speed of said aircraft (A) exclusively along said first segment (S1), which allows the aircraft (A) to arrive at said final point (PF) at said arrival time;deducing a target time for at least one waypoint (PP, PF) which is situated on said first segment (S1), from said first vertical speed profile, said target time defining the time at which the aircraft (A) must pass said waypoint (PP, PF);determining a temporal tolerance relating to the compliance with said target time at said waypoint (PP, PF) at least on the basis of said first temporal error margin; andproviding at least first guidance aid information comprising said first modified trajectory (TM1), and, for each waypoint (PP, PF), the target time and the temporal tolerance that are associated with said waypoint,wherein:in step a), second input parameters are moreover generated, comprising:a plurality of successive auxiliary points (P1 to P8) of said flight trajectory (TV2), the first (P1) of said successive auxiliary points in the direction of flight (E) of the aircraft (A) corresponding to said end point (PF);associated with at least some of said auxiliary points (P1 to P8), times of passage corresponding to the times at which the aircraft (A) must pass respectively these auxiliary points (P1 to P8); anda second temporal error margin; andin step b), on the basis of said auxiliary points (P1 to P8), of said times of passage and of said second temporal error margin, automatically:determining at least one second segment (S2), which comprises said auxiliary points (P1 to P8), which begins at the first (P1) of said successive auxiliary points, that is to say at said end point (PF) of said first segment (S1), and which finishes at the last (P8) of said auxiliary points;integrating this second segment (S2) following said first segment (S1) into said first modified trajectory in such a way as to obtain a second modified trajectory (TM2), said first and second segments forming a global segment (SG);determining a target time at which the aircraft (A) must pass said auxiliary point for each auxiliary point with which no time of passage is associated, the target time of the other auxiliary points corresponding to the associated times of passage;deducing a second vertical speed profile, indicating the vertical speed of said aircraft (A) exclusively along said second segment (S2), which allows the aircraft (A) to pass said auxiliary points (P1 to P8) at the associated target times;determining an auxiliary temporal tolerance at least on the basis of said second temporal error margin; andproviding second guidance aid information comprising said second modified trajectory (TM2), said auxiliary temporal tolerance and, for each auxiliary point (P1 to P8), the associated target time.
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