IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0443727
(2007-10-09)
|
등록번호 |
US-8125352
(2012-02-28)
|
우선권정보 |
FR-06 08869 (2006-10-10) |
국제출원번호 |
PCT/EP2007/060722
(2007-10-09)
|
§371/§102 date |
20090409
(20090409)
|
국제공개번호 |
WO2008/043763
(2008-04-17)
|
발명자
/ 주소 |
- Dubourg, Bernard
- Michel, François
|
출원인 / 주소 |
|
대리인 / 주소 |
Lowe Hauptman Ham & Berner, LLP
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
4 |
초록
▼
The invention pertains to optoelectronic devices for aiding the guidance and taxiing of aircraft, comprising a so-called head-up collimator allowing the presentation of information in the pilot's visual field. It applies notably to large-size civil aircraft of the Boeing 747 or Airbus A380 type. The
The invention pertains to optoelectronic devices for aiding the guidance and taxiing of aircraft, comprising a so-called head-up collimator allowing the presentation of information in the pilot's visual field. It applies notably to large-size civil aircraft of the Boeing 747 or Airbus A380 type. The optoelectronic device comprises means for calculating a deviation factor for the actual trajectory of said aircraft relative to a theoretical trajectory on said traffic way, means for generating symbols and at least one head-up collimator comprising means for displaying and superimposing said symbols on the outside landscape. The deviation factor is calculated on the basis of an angle (PÂ′G) and that the means for generating symbols generate a symbol representing said deviation factor, so as to be superimposed on said traffic way.
대표청구항
▼
1. An optoelectronic device for aiding a guidance of aircraft, said aircraft comprising a landing gear and a nose wheel, the aircraft being situatable on an airport traffic way, said device comprising: means for calculating a deviation factor for an actual trajectory of said aircraft relative to a t
1. An optoelectronic device for aiding a guidance of aircraft, said aircraft comprising a landing gear and a nose wheel, the aircraft being situatable on an airport traffic way, said device comprising: means for calculating a deviation factor for an actual trajectory of said aircraft relative to a theoretical trajectory on said traffic way,means for generating symbols and at least one head-up collimator comprising means for displaying and superimposing said symbols on an outside landscape,wherein the deviation factor is calculated based on a first angle PÂ′G determined by a vertex of a triangle defined by a first point A′ arising from a projection of a central point of the landing gear on the actual trajectory,a second point, called a guidance point G, situated between a projection of a point of the nose wheel of the aircraft and the projection of the central point of a main landing gear on the actual trajectory anda third point P, defined by the projection of the guidance point on the theoretical trajectory and that the means for generating symbols generate a symbol representing said deviation factor, so as to be superimposed on said traffic way. 2. The optoelectronic device as claimed in claim 1, wherein anticipation information is calculated based on a second angle TÂ′T′ determined by a vertex of a triangle comprising a first point, called an anticipation point T, situated between the point of the nose wheel and the guidance point G and a second point T′ obtained by a projection of the anticipation point T on the theoretical trajectory and finally a third point, the vertex A′, defined by the projection of the central point of the main landing gear on the actual trajectory and that the means for generating symbols generate a signal representing said anticipation information, so as to be superimposed on said traffic way. 3. The optoelectronic device as claimed in claim 1, wherein the displayed symbol, representing the deviation factor, moves laterally as a function of the value of the first angle PÂ′G, the position of the symbol corresponding to a zero deviation between the actual trajectory and the theoretical trajectory being referenced by a fixed marker. 4. The optoelectronic device as claimed in claim 3, wherein the display symbol representing the deviation factor is a diamond. 5. The optoelectronic device as claimed in claim 3, wherein the display symbol representing the deviation factor is a circle comprising three axial segments. 6. The optoelectronic device as claimed in claim 3, wherein the marker corresponding to a zero deviation between the actual trajectory and the theoretical trajectory is a rectangle. 7. The optoelectronic device as claimed in claim 2, wherein the signal, representing the anticipation information, is the blinking of a symbol, said blinking being triggered when the second angle TÂ′T′ exceeds a predefined threshold. 8. The optoelectronic device as claimed in claim 7, wherein the blinking symbol is the symbol representing the deviation factor. 9. The optoelectronic device as claimed in claim 7, wherein the blinking symbol is the fixed rectangle on the screen, this symbol being associated with the symbol of the deviation factor. 10. The optoelectronic device as claimed in claim 1, wherein the guidance point G, on wide-body craft, of the A380 or B747 type, is situated at a distance from the nose wheel equivalent to a third of the distance between the nose wheel and the center of the main gear of the aircraft A′. 11. The optoelectronic device as claimed in claim 10, wherein the anticipation point T, on wide-body craft, of the A380 or B747 type, is situated at the level of the nose wheel. 12. The optoelectronic device as claimed in claim 1, wherein the guidance point G, on narrow-body craft, of the A320 type, is situated at the level of the nose wheel. 13. The optoelectronic device as claimed in claim 2, wherein the guidance point G, on wide-body craft, of the A380 or B747 type, is situated at a distance from the nose wheel equivalent to a third of the distance between the nose wheel and the center of the main gear of the aircraft A′. 14. The optoelectronic device as claimed in claim 3, wherein the guidance point G, on wide-body craft, of the A380 or B747 type, is situated at a distance from the nose wheel equivalent to a third of the distance between the nose wheel and the center of the main gear of the aircraft A′. 15. The optoelectronic device as claimed in claim 4, wherein the guidance point G, on wide-body craft, of the A380 or B747 type, is situated at a distance from the nose wheel equivalent to a third of the distance between the nose wheel and the center of the main gear of the aircraft A′. 16. The optoelectronic device as claimed in claim 5, wherein the guidance point G, on wide-body craft, of the A380 or B747 type, is situated at a distance from the nose wheel equivalent to a third of the distance between the nose wheel and the center of the main gear of the aircraft A′. 17. The optoelectronic device as claimed in claim 6, wherein the guidance point G, on wide-body craft, of the A380 or B747 type, is situated at a distance from the nose wheel equivalent to a third of the distance between the nose wheel and the center of the main gear of the aircraft A′. 18. The optoelectronic device as claimed in claim 7, wherein the guidance point G, on wide-body craft, of the A380 or B747 type, is situated at a distance from the nose wheel equivalent to a third of the distance between the nose wheel and the center of the main gear of the aircraft A′. 19. The optoelectronic device as claimed in claim 8, wherein the guidance point G, on wide-body craft, of the A380 or B747 type, is situated at a distance from the nose wheel equivalent to a third of the distance between the nose wheel and the center of the main gear of the aircraft A′. 20. The optoelectronic device as claimed in claim 9, wherein the guidance point G, on wide-body craft, of the A380 or B747 type, is situated at a distance from the nose wheel equivalent to a third of the distance between the nose wheel and the center of the main gear of the aircraft A′.
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