Electrical flight control system for an airplane, with attitude protection on takeoff

• US 5,527,002 A
• Filed: 09/29/1994
• Issued: 06/18/1996
• Est. Priority Date: 10/14/1993
• Status: Expired due to Term

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Le Tron, Xavier, Bilange, Thierry
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US08/314,815
• Time in Patent Office: 628 Days
• Field of Search: 244/76 R, 244/181, 244/195, 244/180, 244/177, 244/175
• US Class Current: 244/181
• CPC Class Codes: G05D 1/0661 specially adapted for take-off

Abstract

According to the invention, attenuator means (8) are provided, making it possible to limit the rate of rotation of the airplane on takeoff, so as to avoid the tail of the airplane striking the ground and to reduce the dispersion of the rotation rates.

Claims

1. An electrical system for control of an elevator aerodynamic surface (1) of an airplane in proximity to the ground, of the type including:

a control member (2) actuated by the pilot of the airplane and associated with a position sensor (3) delivering an electrical signal representative of the angle of deflection of said elevator aerodynamic surface on the ground and of the desired attitude (θ

d) for the airplane in flight;

motor means (4) for control of said elevator aerodynamic surface (1); and

calculating means (6) mounted between said position sensor (3) and said motor means (4), receiving said signal delivered by said sensor (3) and delivering a control signal for said motor means (4) in order to impart, to said aerodynamic surface (1), a movement such that said aerodynamic surface, on the ground, reaches an angular position defined by the position of said control member or such that the airplane, in flight, reaches an attitude corresponding to said desired attitude,

which includes;

generator means (7) for delivering an electrical signal representative of the actual rate of rotation of said airplane; and

attenuator means (8,11) for attenuating, in pitch-up, said control signal addressed by said calculating means (6) to said motor means (4), said attenuator means receiving said electrical signal representative of said actual rotation rate and exerting an attenuation as a function of the value of said electrical signal representative of said actual rotation rate.

2. The system as claimed in claim 1, wherein said attenuation grows progressively when said actual rotation rate grows from zero up to a threshold (L) of said actual rotation rate, and is constant beyond said threshold (L).

3. The system as claimed in claim 1, wherein said attenuator means include:

a first function generator (8), receiving, at its input, said electrical signal representative of said actual rotation rate and delivering at its output a first coefficient (k), the value of which, lying between 0 and 1, depends on the value of said actual rotation rate; and

a first multiplier (11) for multiplying said control signal addressed by said calculating means (6) with said first coefficient (k), before this control signal is addressed to said motor means (4).

4. The system as claimed in claim 1, which includes switch means (9,10) making said attenuator means active only during the takeoff of the airplane.

5. The system as claimed in claim 3, which includes means (12,13) inhibiting the action of said attenuator means (8,11) in the event that, during the takeoff, said control member (2) takes up a position corresponding to pitch-down.

6. The system as claimed in claim 5, in which said control member can move on either side of a neutral position, separating the total range of deflection of said control member into a region corresponding to pitch-up and a region corresponding to pitch-down, wherein said inhibition means include:

a second function generator (12), receiving at its input said electrical signal representative of the desired attitude and delivering at its output a second coefficient (g), the value of which, equal to 0 or 1, depends on said region in which said control member is found with respect to said neutral position; and

a second multiplier (13) for multiplying said signal representative of the actual rotation rate addressed by said generator means (7) with said second coefficient (g), before the latter signal is addressed to said attenuator means (8,11).

7. An electrical system for control of an aerodynamic surface of an airplane in proximity to the ground, with attitude protection on take-off to eliminate the risk of striking the ground with the tail of the airplane during take-off, said system comprising:

a control member actuated by a pilot of the airplane and associated with a position sensor delivering an electrical signal representative of the angle of deflection of said aerodynamic surface on the ground;

motor means for control of said aerodynamic surface;

calculating means, coupled between said position sensor and said motor means, for receiving said electrical signal delivered by said position sensor and delivering a control signal for said motor means in order to impart, to said aerodynamic surface, a movement such that said aerodynamic surface, on the ground, reaches an angular position defined by the position of said control member;

generator means for delivering an electrical signal representative of the actual rate of rotation of said airplane;

attenuator means for attenuating said control signal, said attenuator means receiving said electrical signal representative of said actual rotation rate and exerting an attenuation as a function of the value of said electrical signal representative of said actual rotation rate; and

inhibiting means making said attenuator means active only during take-off of said airplane.

8. An electrical system for control of an aerodynamic surface of an airplane in proximity to the ground, with attitude protection on take-off to eliminate the risk of striking the ground with the tail of the airplane during take-off, said system comprising:

a control member actuated by a pilot of the airplane and associated with a position sensor delivering an electrical signal representative of the angle of deflection of said aerodynamic surface on the ground;

motor means for control of said aerodynamic surface;

calculating means, coupled between said position sensor and said motor means, for receiving said electrical signal delivered by said position sensor and delivering a control signal for said motor means in order to impart, to said aerodynamic surface, a movement such that said aerodynamic surface, on the ground, reaches an angular position defined by the position of said control member;

generator means for delivering an electrical signal representative of the actual rate of rotation of said airplane; and

attenuator means for attenuating said control signal, said attenuator means receiving said electrical signal representative of said actual rotation rate and exerting an attenuation as a function of the value of said electrical signal representative of said actual rotation rate.