Method and a system for assisting piloting to avoid an obstacle with a rotorcraft

Patent metadata

Field	Value
Publication number	US-9984581-B2
Application number	US-201615162752-A
Country	US
Kind code	B2
Filing date	May 24, 2016
Priority date	May 29, 2015
Publication date	May 29, 2018
Grant date	May 29, 2018

Abstract

A piloting assistance method for avoiding an obstacle with a rotorcraft flying along a current speed vector (Vect 0 ). An alert is generated by using a speed vector of the rotorcraft referred to as a “calculation” speed vector (Vect 1 ) in order to determine whether the rotorcraft might impact an obstacle. During a correction stage and at each calculation iteration, the calculation speed vector (Vect 1 ) is determined using a horizontal component and a vertical component, the vertical component being a function of a current vertical speed of the rotorcraft relative to the ground corrected with a corrective term, the corrective term being a function of a product of a current path speed of the rotorcraft multiplied by the derivative of the path speed.

First claim

What is claimed is:

1. A piloting assistance method for avoiding an obstacle with a rotorcraft flying along a current speed vector (Vect 0 ), an alert being generated by an alert unit of an avionics equipment of the rotorcraft if an obstacle might be impacted by the rotorcraft, wherein a processor of the avionics equipment of the rotorcraft controls the alert unit to generate the alert by using a speed vector of the rotorcraft referred to as a “calculation” speed vector (Vect 1 ) for the processor to determine whether the rotorcraft might impact an obstacle, and during a correction stage (STP 3 ) and at each calculation iteration, the calculation speed vector (Vect 1 ) is determined by the processor using a horizontal component (V 1 ) of the calculation speed vector in a horizontal plane (P 1 ) orthogonal to gravity direction (AX), as determined by the processor, and a vertical component (V 2 ) of the calculation speed vector along the gravity direction (AX), as determined by the processor, the vertical component (V 2 ) being a function of a current vertical speed (Vv) of the rotorcraft relative to the ground, as determined by an inertial unit of the rotorcraft connected to the processor, at the calculation instant corrected with a corrective term (Vvp), the corrective term (Vvp) being a function of a product of a current path speed (Vt) of the rotorcraft, as determined by the inertial unit, multiplied by the derivative of the path speed.

2. The piloting assistance method according to claim 1 , wherein the horizontal component (V 1 ) is equal to a current horizontal speed (Vh) of the rotorcraft relative to the ground.

3. The piloting assistance method according to claim 1 , wherein the vertical component (V 2 ) is determined by the processor using the following relationship:
with

V
⁢

⁢
2

=

Vv
+

Vvp
⁢

⁢
with

Vvp
=

B
*

Vt
g

*

d
⁢

⁢
Vt

d
⁢

⁢
t

where “V 2 ” represents the vertical component, “Vv” represents the current vertical speed relative to the ground, “Vvp” represents the corrective term, “B” represents a constant, “Vt” represents the current path speed,

“

d
⁢

⁢
Vt

d
⁢

⁢
t

”

represents the derivative of the path speed, “g” represents the acceleration due to gravity, “*” represents the multiplication sign, and “+” represents the addition sign.

4. The piloting assistance method according to claim 3 , wherein constant (B) is less than or equal to 1.

5. The piloting assistance method according to claim 1 , wherein the method is initiated when the air speed (TAS, IAS) of the rotorcraft, as detected by an air data computer of the rotorcraft connected to the processor, is greater than a difference between a best rate of climb (Vy) and a margin (Vm).

6. The piloting assistance method according to claim 5 , wherein the margin (Vm) is less than or equal to 20 knots.

7. A piloting assistance method for avoiding an obstacle with a rotorcraft flying along a current speed vector (Vect 0 ), an alert being generated by an alert unit of an avionics equipment of the rotorcraft if an obstacle might be impacted by the rotorcraft, wherein a processor of the avionics equipment of the rotorcraft controls the alert unit to generate the alert by using a speed vector of the rotorcraft referred to as a “calculation” speed vector (Vect 1 ) for the processor to determine whether the rotorcraft might impact an obstacle, and during a correction stage (STP 3 ) and at each calculation iteration, the calculation speed vector (Vect 1 ) is determined by the processor using a horizontal component (V 1 ) of the calculation speed vector in a horizontal plane (P 1 ) orthogonal to gravity direction (AX), as determined by the processor, and a vertical component (V 2 ) of the calculation speed vector along the gravity direction (AX), as determined by the processor, the vertical component (V 2 ) being a function of a current vertical speed (Vv) of the rotorcraft relative to the ground, as determined by an inertial unit of the rotorcraft connected to the processor, at the calculation instant corrected with a corrective term (Vvp), the corrective term (Vvp) being a function of a product of a current path speed (Vt) of the rotorcraft, as determined by the inertial unit, multiplied by the derivative of the path speed;
wherein the current speed vector (Vect 0 ) presents an angle (η) relative to the horizontal plane (P 1 ) and the correction stage is performed by the processor if a plurality of criteria is satisfied, the plurality of criteria comprising at least:
a first criterion that is satisfied if a time derivative of the angle (η) is positive; and
a second criterion that is satisfied if a time derivative of the path speed (Vt) is negative.

8. The piloting assistance method according to claim 7 , wherein the first criterion is satisfied if the time derivative of the angle (η) is greater than a non-zero constant (K).

9. The piloting assistance method according to claim 7 , wherein the plurality of criteria includes a third criterion, the third criterion being satisfied if the current vertical speed (Vv) is positive.

10. The piloting assistance method according to claim 7 , wherein if at least one criterion is not satisfied, it is determined by the processor whether at least one condition is satisfied, the at least one condition comprising a first condition that is satisfied if a time derivative of the path speed (Vt) is negative, and if each condition is satisfied:
if the correction stage (STP 3 ) was implemented in the calculation iteration preceding the current calculation iteration, then the correction stage (STP 3 ) is implemented during the current calculation iteration; and
if the correction stage (STP 3 ) was not implemented in the calculation iteration preceding the current calculation iteration, then a non-corrected stage (STP 6 ) is implemented, during which non-corrected stage and on each calculation iteration the calculation speed vector (Vect 1 ) is determined using the horizontal component (V 1 ) and a vertical component (V 2 ) equal to the current vertical s

Assignees

• Airbus Helicopters

Inventors

• Pire Richard
• Gillet Marianne
• Certain Nicolas

Classifications

• G08G5/0086

  Physics · mapped topic

• G08G5/0021

  Physics · mapped topic

• G08G5/045 Primary

  Physics · mapped topic

• G01C23/005

  Flight directors (indicating arrangements specially adapted for rotary gyroscopes G01C19/32) · CPC title

• G08G5/0052

  Physics · mapped topic