METHOD FOR PILOT ASSISTANCE FOR THE LANDING OF AN AIRCRAFT IN RESTRICTED VISIBILITY

• US 20120314032A1
• Filed: 05/25/2012
• Published: 12/13/2012
• Est. Priority Date: 05/27/2011
• Status: Abandoned Application

• Current Assignee: Airbus Defence and Space GmbH
• Original Assignee: EADS Deutschland GmbH (Airbus SE)
• Inventors: MUENSTERER, Thomas, KIELHORN, Peter, WEGNER, Matthias
• Application Number:
  US13/480,798
• Publication Number:
  US 20120314032A1
• Time in Patent Office: Days
• US Class Current: 348/46
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32
• CPC Class Codes: G01S 13/935 for terrain-avoidance
• CPC Class Codes: G01S 7/062 in which different colours are used
• CPC Class Codes: G01S 7/22 Producing cursor lines and indicia by electronic means
• CPC Class Codes: G01S 7/24 the display being orientated or displaced in accordance with movement of object carrying the transmitting and receiving apparatus, e.g. true-motion radar
• CPC Class Codes: G01S 7/51 Display arrangements
• CPC Class Codes: G05D 1/0676 specially adapted for landing

Abstract

Method for pilot assistance in landing an aircraft with restricted visibility, in which the position of a landing point is defined by at least one of a motion compensated, aircraft based helmet sight system and a remotely controlled camera during a landing approach, and with the landing point is displayed on a ground surface in the at least one of the helmet sight system and the remotely controlled camera by production of symbols that conform with the outside view. The method includes one of producing or calculating during an approach, a ground surface based on measurement data from an aircraft based 3D sensor, and providing both the 3D measurement data of the ground surface and a definition of the landing point with reference to a same aircraft fixed coordinate system.

Claims

1. A method for pilot assistance in landing an aircraft with restricted visibility, in which the position of a landing point is defined by at least one of a motion-compensated, aircraft-based helmet sight system and a remotely controlled camera during a landing approach, and with the landing point being displayed on a ground surface in the at least one of the helmet sight system and the remotely controlled camera by production of symbols that conform with the outside view, the method comprising:

one of producing or calculating during an approach, a ground surface based on measurement data from an aircraft-based 3D sensor; and

providing both the 3D measurement data of the ground surface and a definition of the landing point with reference to a same aircraft-fixed coordinate system.

2. The method according to claim 1, further comprising calculating, both in the aircraft-fixed coordinate system and in a local, ground-fixed relative coordinate system, geometric position data of landing point symbols,

wherein an instantaneous position in space and an instantaneous position of the aircraft are used for converting between the two coordinate systems, in which the instantaneous position of the aircraft results from relative position changes of the aircraft with respect to its position at a selected reference time.

3. The method according to claim 1, wherein the landing point is defined by finding a bearing of the landing point in the helmet sight system and subsequent marking by a trigger.

4. The method according to claim 1, further comprising correcting, via a control element, the position of the landing point symbol displayed in the helmet sight system.

5. The method according to claim 2, wherein the landing point symbols comprise at least one of an H, a T and an inverted Y.

6. The method according to claim 1, further comprising displaying at least one additional visual orientation aid, which conforms with an outside view and comprises a 3D object in the helmet sight system,

wherein the at least one additional visual orientation aid is derived from a real object within an area around the landing point.

7. The method according to claim 6, wherein the 3D data of the real object is produced by the 3D sensor during the approach.

8. The method according to claim 6, wherein the orientation aid comprises an envelope of the real object.

9. The method according to claim 6, wherein the orientation aid assumes a geometric basic shape comprising at least one of a cuboid, cone or cylinder, or combinations thereof.

10. The method according to claim 6, wherein, when there is a plurality of real objects within the landing zone, the method further comprises determining the suitability of the plurality of real objects as an orientation aid via of an assessment algorithm, and displaying the objects that are most suitable as orientation aids.

11. The method according to claim 1, further comprising displaying an additional, synthetic orientation aid, which conforms with the outside view and comprises a virtual wind sock in the helmet sight system.

12. The method according to claim 1, further comprising an additional synthetic orientation aid, which conforms with the outside view and comprises a virtual glide angle beacon in the helmet sight system, in order to assist the approach at the correct glide-path angle.

13. The method according to claim 12, wherein the virtual glide angle beacon comprises at least one of VASI (Visual Approach Slope Indicator) or PAPI (Precision Approach Path Indicator).

14. A method to assist landing an aircraft in an area of limited visibility comprising:

focusing on a landing point via one of a helmet system and a camera;

measuring a line of sight to the landing point;

3 dimensionally measuring an area that includes the landing point;

displaying symbols corresponding to an intersection of the line of sight and the 3 dimensionally measured area in the one of the helmet system and the camera.

15. The method according to claim 14, wherein measurement of the line of sight to the landing point is triggered by a pilot.

16. The method according to claim 14, further comprising correcting a location of the displayed the symbols according to additional measurements of the line of sight to the landing point and the area including the landing point.

17. The method according to claim 14, wherein the symbols comprise at least one of an H, a T and an inverted Y.