AIRCRAFT FLIGHT CONTROL

• US 20090230252A1
• Filed: 03/12/2009
• Published: 09/17/2009
• Est. Priority Date: 03/13/2008
• Status: Active Grant

• Current Assignee: Airbus Helicopters
• Original Assignee: Eurocopter
• Inventors: DAUNOIS, Stephane, CORRE, Michel
• Granted Patent: US 8,074,941 B2
• Time in Patent Office: Days
• US Class Current: 244/234
• CPC Class Codes: B64C 13/0421 control sticks for primary flight controls
• CPC Class Codes: B64C 27/56 characterised by the control initiating means, e.g. manually actuated
• CPC Class Codes: G05G 2009/04718 with cardan or gimbal type joint
• CPC Class Codes: Y10T 74/20201 Control moves in two planes

Abstract

An aircraft flight control (10) includes a control stick (11) with a handle (14) and a root (13) that are interconnected by an intermediate segment (12) of the control stick (11). The flight control (10) includes a pitch shaft (20) and a roll shaft (30) that are mutually perpendicular, the control stick (11) passing through an oblong orifice (21) formed in the pitch shaft (20), the root (13) being mechanically connected to the roll shaft (30) by a mechanical connection (40), while the intermediate segment (12) is connected to the pitch shaft (20) via a connection pin (70) that passes through the intermediate segment (12) and that is arranged axially in the oblong orifice (21).

Claims

1. An aircraft flight control (10) comprising a pitch and roll control stick (11) suitable for being turned about a pitch axis (AXTANG) and a roll axis (AXROLL) that are mutually perpendicular, said control stick (11) being provided with a handle (14) and a root (13) interconnected by an intermediate segment (12) of said control stick (11), wherein the flight control (10) comprises a pitch shaft (20) and a roll shaft (30) that are mutually perpendicular for controlling the aircraft in pitching and rolling by performing turning movements respectively about said pitch and roll axes (AXTANG and AXROLL) under drive from said control stick (11), said control stick (11) also passing through an oblong orifice (21) formed in said pitch shaft (20), said root (13) is mechanically connected to the roll shaft (30) by a mechanical connection (40) while said intermediate segment (12) is connected to the pitch shaft (20) by a connection pin (70) that passes through said intermediate segment (12) and that is arranged axially in said oblong orifice (21).

2. A flight control according to claim 1, wherein said connection pin is a bar (70) having said roll axis (AXROLL) as its longitudinal axis of symmetry (AXS).

3. A flight control according to claim 1, wherein said flight control (10) comprises a main anchor platform (50) anchoring it to said aircraft, and said roll and pitch shafts (20 and 30) are fastened to said main anchor platform (50) in such a manner as to be capable of performing rotary movements respectively about said pitch and roll axes (AXTANG and AXROLL).

4. A flight control according to claim 1, including at least one primary rod (22) hinged on a primary projection (21) fastened to said pitch shaft (20).

5. A flight control according to claim 1, that is provided with at least one primary sensor (23) for sensing the position of said pitch shaft (20).

6. A flight control according to claim 1, including at least one secondary rod (32) hinged to a secondary projection (31) fastened to said roll shaft (30).

7. A flight control according to claim 1, that is provided with at least one secondary sensor (33) for sensing the position of said pitch shaft (30).

8. A flight control according to claim 1, wherein said mechanical connection (40) includes a compass linkage (41) provided with first and second branches (42, 43), said first branch (42) being hinged to the root (13) of the control stick (11) and to a first end zone (43′

) of the second branch (43).

9. A flight control according to claim 8, wherein a second end zone (43″

) of the second branch (43) of the compass linkage (41) is hinged to the roll shaft (30).

10. A flight control according to claim 8, wherein a second end zone (43″

) of the second branch (43) of the compass linkage (41) is mechanically connected to the roll shaft (30) via transfer means (44) comprising in succession a horizontal first transfer rod (45), a vertical transfer member (46), followed by a horizontal second transfer rod (47), a ball-joint (48) having a large amount of freedom in angular movement being placed between said second branch (43) and said first transfer rod (45).

11. A flight control according to claim 10, wherein said first transfer rod (45) extends along said pitch axis (AXTANG).

12. A flight control according to claim 10, wherein said ball-joint (48) can accommodate a maximum amount of angular movement of plus or minus 20°

.

13. A flight control according to claim 10, including support means (60) for supporting the mechanical connection, said support means (60) being fastened firstly to the second branch (43) and being secured secondly to the pitch shaft (20).

14. A flight control according to claim 10, including a secondary anchor platform (49) anchoring the vertical transfer member (46) to a structure of the aircraft.