Aircraft comprising a display device for the attitude of an aircraft with respect to a fixed direction in space

• US 10,435,172 B2
• Filed: 03/11/2016
• Issued: 10/08/2019
• Est. Priority Date: 03/13/2015
• Status: Active Grant

• Current Assignee: Leonardo S.p.A.
• Original Assignee: Leonardo S.p.A.
• Inventors: Nour, Pierre Abdel, Brughera, Paolo, Monti, Fabio
• Primary Examiner(s): Seo, Justin
• Assistant Examiner(s): Courson, Tania C
• Application Number:
  US15/555,928
• Publication Number:
  US 20180037335A1
• Time in Patent Office: 1,306 Days
• CPC Class Codes: B64D 2045/007 Indicators or signs in the cabin, e.g. exit signs or seat numbering
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G01C 5/005 altimeters for aircraft G01C5/02, G01C5/06 take precedence
• CPC Class Codes: G01C 9/005 specially adapted for use in aircraft
• CPC Class Codes: G01C 9/02 Details
• CPC Class Codes: G01C 9/10 by using rolling bodies , e.g. spheres, cylinders, mercury droplets
• CPC Class Codes: G08B 7/062 indicating emergency exits

Abstract

A display device for displaying the attitude of an aircraft with respect to a fixed direction in space is described, said device comprising: a first element that can be fastened to the aircraft; and a second element, which is free to move with respect to the first element, following a change in position of first element with respect to the fixed direction; the second element in turn comprising: a mass, which is designed to return the second element to the same stable position with respect to the fixed direction when the first element changes its position with respect to the fixed direction; and a visual indication, which is representative of the position of the fixed direction, as the position of the first element changes.

Claims

1. An aircraft (1) comprising:

a fuselage (2);

a first and a second lateral side (11a and 11b) opposite to each other;

a first emergency exit (9a) defined by said first side (11a);

a second emergency exit (9b) defined by said second side (11b); and

at least one display device (8a, 8b) for displaying the attitude of said aircraft (1) with respect to a fixed direction (V) in space;

wherein the at least one display device (8a, 8b) comprises;

a first element (15), which can be fastened to said aircraft (1); and

a second element (16), which is free to move with respect to the first element (15), following a change in position of said first element (15) with respect to said fixed direction (V);

said second element (16) in turn comprising;

a mass (14), which is designed to return said second element (16) to the same stable position with respect to said fixed direction (V), when said first element (15) changes, in use, its position with respect to said fixed direction (V); and

a visual indication (18), which is representative of the position of said fixed direction (V), as the position of said first element changes (15);

in the event of said aircraft (1) ditching with said first side (11a) positioned below or resting on the waterline (13), said second emergency exit (9b) being usable and positioned at a higher level than said first emergency exit (9a), which is unusable;

said visual indication (18) of said display device (8a or 8b) displaying an exit path (P), pointing from said unusable first emergency exit (9a) towards said usable second emergency exit (9b);

wherein the at least one display device comprises;

at least one first display device (8a) that is located adjacent to one of said first emergency exit (9a) and said second emergency exit (9b) and mounted on one of said first lateral side (11a) and said second lateral side (11b); and

/or

at least one second display device (8b) is housed inside said fuselage (2) of said aircraft (1) in a position set apart from said first lateral side (11a) and said second lateral side (11b).

2. An aircraft according to claim 1, characterized in that said first element (15) and second element (16) are rotatable with respect to each other.

3. An aircraft according to claim 1, characterized in that said first and second elements (15, 16) have at least one common axis of symmetry.

4. An aircraft according to claim 3, characterized in that said first and second elements (15, 16) are delimited by respective portions of spherical surfaces (28, 29) concentric to each other.

5. An aircraft according to claim 1, characterized in that said second element (16) is placed inside said first element (15);

said first element (15) being transparent to allow said visual indication (18) to be visible from outside the first element (15).

6. An aircraft according to claim 5, characterized in that said first element (15) is made in two separate portions (26, 27) connected together.

7. An aircraft according to claim 1, characterized in that said visual indication (18) is at least partially made of a photoluminescent material.

8. An aircraft according to claim 1, characterized in that said visual indication (18) comprises a segment (23) shaped substantially like a triangle;

said segment (23) in turn comprising a base (25) and a vertex (24 opposite to each other, and having, in said stable position of said second element (16), a height substantially parallel to said fixed direction (V);

said vertex (24) being located, in said stable position of said second element (16), above said base (25).

9. An aircraft according to claim 1, wherein the at least one display device (8a, 8b) further includes a liquid film (17), which is interposed between said first and second elements (15, 16).

10. An aircraft device according to claim 9, characterized in that said liquid film (17) is transparent.

11. An aircraft according to claim 1, characterized in that said mass (14) is positioned below the centre of gravity of said second element (16), so as to stably return said second element (16) to the same position with respect to said fixed direction (V), as the position of said first element (15) changes.

12. An aircraft according to claim 1, wherein a border (35) of at least one window (12) of said first lateral side (11a) and said second lateral side (11b) is at least partially made of or painted with a photoluminescent material.

13. An aircraft according to claim 1, further including at least one handle (36) adjacent to said emergency exit (9a, 9b) and made of or painted with a photoluminescent material.