Method and device for aiding the control of an aircraft during a parabolic flight in order to generate weightlessness in the aircraft

• US 9,321,523 B2
• Filed: 09/10/2014
• Issued: 04/26/2016
• Est. Priority Date: 09/13/2013
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus Operations SAS (Airbus SE)
• Inventors: Delporte, Martin
• Primary Examiner(s): Trammell, James
• Assistant Examiner(s): Malhotra, Sanjeev
• Application Number:
  US14/482,513
• Publication Number:
  US 20150076288A1
• Time in Patent Office: 594 Days
• Field of Search: 701/11, 701/24, 701/69, 244/7.B, 244/46, 244/118.5, 700/91, 703/13, 473/151, 299/1.9, 102/502, 351/206, 359/295, 323/281, 73/120.5, 104/53
• US Class Current: 1/1
• CPC Class Codes: B64C 13/0421 control sticks for primary flight controls
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32
• CPC Class Codes: G05D 1/0607 specially adapted for aircraft

Abstract

A method and device are disclosed for aiding the control of an aircraft during a parabolic flight in order to generate weightlessness in the aircraft. The device includes a unit for automatically calculating a control stick order corresponding to a current optimum position of the control stick for carrying out a parabolic flight, a unit for automatically determining an actual position of the control stick, and a display unit for automatically displaying, on at least one scale that is displayed on a cockpit screen, simultaneously a first indicator corresponding to the control stick order and a second indicator corresponding to the actual position of the control stick.

Claims

1. A method for assisting the piloting of an aircraft during a parabolic flight in order to generate weightlessness in the aircraft, the aircraft comprising a control stick capable of actuation by a pilot to alter its position and configured to act on at least one elevator of the aircraft so as to generate piloting of the aircraft on the aircraft'"'"'s pitch axis according to the position of the control stick, the method comprising a sequence of steps, carried out in an automatic and repeated manner, during a parabolic flight of the aircraft and consisting in real time in:

a) computing a control stick command corresponding to an optimum current position of the control stick for parabolic flight;

b) determining an effective current position of the control stick; and

c) simultaneously showing, on at least one scale of control stick positions which is displayed on a screen of the cockpit;

(i) a first indicator representing the control stick command computed in step a);

(ii) a second indicator representing said effective current position of the control stick, determined in step b); and

(iii) wherein in step a) the control stick command C is computed on the basis of the following equation;

C=k0+k1*cos θ

/V+k2*sin 2θ

/V2

in which;

θ

is a current angle of pitch of the aircraft;

V is a current speed of the aircraft; and

k0, k1 and k2 are predetermined constants.

2. The method according to claim 1, wherein the angle of pitch of the aircraft is measured by means of at least one inertial sensor on board the aircraft.

3. The method according to claim 1, wherein the speed of the aircraft is determined by means of at least one of the following onboard means:

at least one inertial sensor;

at least one receiver of a satellite positioning system; and

at least one pressure or temperature sensor.

4. The method according to claim 1, wherein in step c) the scale is displayed vertically and the first and second indicators are displayed on either side of this vertical scale.

5. The method according to claim 1, further comprising an additional step, which precedes step a) and consists in determining the constants k0, k1and k2 by carrying out the following operations:

determining and recording, in real time, values for the angle of pitch of the aircraft, for the speed of the aircraft and for deflection of the control stick, over the course of at least one parabolic flight performed by means of at least one of the following operations;

at least one simulation and/or at least one flight test; and

computing said constants k0, k1and k2 on the basis of the values for the angle of pitch, for the speed and for deflection of the control stick, thus recorded.

6. A device for assisting the piloting of an aircraft during a parabolic flight of the aircraft to generate weightlessness in the aircraft, the device comprising:

a) a control stick capable of actuation by a pilot to alter its position and configured to act on at least one aircraft elevator so as to generate piloting of the aircraft on the aircraft pitch axis according to the position of the control stick;

b) a computation unit configured for automatically computing a control stick command corresponding to an optimum current position for parabolic flight;

c) a position determination unit configured to automatically determine an effective current position of the control stick;

d) a display unit configured to automatically show on the at least scale of control stick positions which is displayed on a screen of the cockpit, simultaneously;

(i) a first indicator representing the control stick command computed for the computation unit; and

(ii) a second indicator representing the effective current position of the control stick, determined by the position determination unit; and

e) wherein the computation unit is configured to automatically compute the control stick command C on the basis of the following equation;

C=k0+k1*cos θ

/V+k2*sin 2θ

/V2

in which;

θ

is a current angle of pitch of the aircraft;

V is a current speed of the aircraft; and

k0, k1 and k2 are predetermined constants.

7. The device according to claim 6 further comprising a set of information sources comprising at least one of the following information sources:

at least one inertial sensor;

at least one receiver of a satellite positioning system; and

at least one pressure or temperature sensor.

8. A system for manually piloting an aircraft, the system comprising:

a) a control stick capable of actuation by a pilot to alter its position and configured to act on at least one elevator so as to generate piloting of the aircraft on a pitch axis according to the position of the control stick; and

b) a piloting assistance device for assisting the piloting of the aircraft during a parabolic flight of the aircraft to generate weightless ness in the aircraft, the device comprising;

(i) a computation unit configured for automatically computing a control stick command corresponding to an optimum current position for parabolic flight;

(ii) a position determination unit configured to automatically determine an effective current position of the control stick; and

(iii) a display unit configured to automatically show on the at least scale of control stick positions which is displayed on a screen of the cockpit, simultaneously;

a first indicator representing the control stick command computed for the computation unit; and

a second indicator representing the effective current position of the control stick, determined by the position determination unit; and

(iv) the computation unit being configured to automatically compute said control stick command C on the basis of the following equation;

C=k0+k1* cos θ

/V+k2* sin 2θ

/V2

in which;

θ

is a current angle of pitch of the aircraft;

V is a current speed of the aircraft; and

k0, k1 and k2 are predetermined constants.

9. An aircraft comprising a piloting assistance device for assisting the piloting of an aircraft during a parabolic flight of the aircraft to generate weightlessness in the aircraft, the piloting assistance device comprising:

a) a control stick capable of actuation by a pilot to alter its position and configured to act on at least one elevator so as to generate piloting of the aircraft on the pitch axis according to the position of the control stick;

b) a computation unit configured for automatically computing a control stick command corresponding to an optimum current position for parabolic flight;

c) a position determination unit configured to automatically determine an effective current position of the control stick; and

d) a display unit configured to automatically show on the at least scale of control stick positions which is displayed on a screen of the cockpit, simultaneously;

(i) a first indicator representing the control stick command computed for the computation unit; and

(ii) a second indicator representing the effective current position of the control stick, determined by the position determination unit; and

e) the computation unit being configured to automatically compute said control stick command C on the basis of the following equation;

C=k0+k1*cos θ

/V+k2*sin 2θ

/V2

in which;

θ

is a current angle of pitch of the aircraft;

V is a current speed of the aircraft; and

k0, k1 and k2 are predetermined constants.

10. An aircraft comprising a manual pilot system comprising:

a) a piloting assistance device for assisting the piloting of the aircraft during a parabolic flight of the aircraft to generate weightlessness in the aircraft, the piloting assistance device comprising;

(i) a control stick capable of actuation by the pilot to alter its position and configured to act on at least one elevator so as to generate piloting of the aircraft on the pitch axis according to the position of the control stick,

(ii) a computation unit configured for automatically computing a control stick command corresponding to an optimum current position for parabolic flight;

(iii) a position determination unit configured to automatically determine an effective current position of the control stick; and

(iv) a display unit configured to automatically show on the at least scale of control stick positions which is displayed on a screen of the cockpit, simultaneously;

a first indicator representing the control stick command computed for the computation unit; and

a second indicator representing the effective current position of the control stick, determined by the position determination unit; and

(v) the computation unit being configured to automatically compute said control stick command C on the basis of the following equation;

C=k0+k1*cos θ

/V+k2*sin 2θ

/V2

in which;

θ

is a current angle of pitch of the aircraft;

V is a current speed of the aircraft; and

k0, k1 and k2 are predetermined constants.