Method and system for determining a recirculation effect from an obstacle on a main rotor induced velocity of a simulated rotorcraft

Patent metadata

Field	Value
Publication number	US-10909875-B2
Application number	US-201815940251-A
Country	US
Kind code	B2
Filing date	Mar 29, 2018
Priority date	Mar 29, 2018
Publication date	Feb 2, 2021
Grant date	Feb 2, 2021

Abstract

A method for determining an effect of a simulated obstacle on a main rotor induced velocity of a simulated rotorcraft in a simulation, comprising: receiving an aircraft airspeed of the simulated rotorcraft and a height above ground for the simulated rotorcraft; generating a line of sight vector having a source position located on the simulated rotorcraft, a direction and a given length; determining a distance between the simulated obstacle and the simulated rotorcraft using the line of sight vector, the distance being at most equal to the given length of the line of sight vector; determining an induced airflow velocity using the distance between the simulated obstacle and the simulated rotorcraft, the aircraft airspeed and the height above ground, the induced airflow velocity being caused by a downwash recirculation flow generated by the simulated obstacle; and outputting the induced airflow velocity.

First claim

We claim:

1. A computer-implemented method for determining an effect of a simulated obstacle on a main rotor induced velocity of a simulated rotorcraft in a simulation, comprising:
receiving an aircraft airspeed of the simulated rotorcraft and a height above ground for the simulated rotorcraft;
generating a line of sight vector having a source position located on the simulated rotorcraft, a direction and a given length;
determining a distance between the simulated obstacle and the simulated rotorcraft using the line of sight vector, the distance being at most equal to the given length of the line of sight vector;
determining a recirculation induced airflow velocity using the distance between the simulated obstacle and the simulated rotorcraft, the aircraft airspeed and the height above ground, the recirculation induced airflow velocity being caused by a downwash recirculation flow generated by the simulated obstacle; and
outputting the recirculation induced airflow velocity.

2. The computer-implemented method of claim 1 , wherein the direction of the line of sight vector corresponds to an azimuth angle.

3. The computer-implemented method of claim 1 , wherein the line of sight vector is parallel to an Earth horizontal plane.

4. The computer-implemented method of claim 3 , wherein the source position is located at least one of along the rotation axis of the main rotor of the simulated rotorcraft and on a hub of the main rotor of the simulated rotorcraft.

5. The computer-implemented method of claim 1 , further comprising varying at least one of an azimuth angle of the line of sight vector and a position of the source position along a rotation axis of the main rotor of the simulated rotorcraft.

6. The computer-implemented method of claim 1 , wherein said generating the line of sight vector comprises generating a plurality of line of sight vectors each having a respective source position located on the simulated rotorcraft, a respective azimuth angle and a respective length.

7. The computer-implemented method of claim 6 , wherein said determining the distance between the simulated obstacle and the simulated rotorcraft comprising determining a respective distance between each respective source position and the simulated obstacle.

8. The computer-implemented method of claim 6 , wherein the respective length is identical for each one of the plurality of line of sight vectors.

9. The computer-implemented method of claim 1 , wherein said determining the distance between the simulated obstacle and the simulated rotorcraft comprises:
accessing a visual database containing a topography of a simulated terrain and simulated physical structures;
identifying the simulated obstacle as being the closest object from the source position along a direction defined by an azimuth angle, the closest object being one of a part of the simulated terrain and one of the simulated physical structures and a distance between the closest object and the source position being at most equal to the given length of the line of sight vector; and
determining a distance between the source position and the closest object, thereby obtaining the distance between the simulated obstacle and the simulated rotorcraft.

10. A system for determining an effect of a simulated obstacle on a main rotor induced velocity of a simulated rotorcraft in a simulation, comprising:
a vector module configured for generating a line of sight vector having a source position located on the simulated rotorcraft, an azimuth angle and a given length;
a calculation module configured for:
receiving a distance between the simulated obstacle and the simulated rotorcraft, an aircraft airspeed of the simulated rotorcraft and a height above ground for the simulated rotorcraft;
determining a recirculation induced airflow velocity using the distance between the simulated obstacle and the simulated rotorcraft, the aircraft airspeed, the height above ground and the distance between the simulated obstacle and the simulated rotorcraft, the recirculation induced airflow velocity being caused by a downwash recirculation flow generated by the simulated obstacle and the distance being at most equal to the given length of the line of sight vector; and
outputting the recirculation induced airflow velocity.

11. The system of claim 10 , wherein the direction of the line of sight vector corresponds to an azimuth angle.

12. The system of claim 10 , further comprising a distance module configured for determining the distance between the simulated obstacle and the simulated rotorcraft using the line of sight vector.

13. The system of claim 10 , wherein the line of sight vector is parallel to an Earth horizontal plane.

14. The system of claim 10 , wherein the vector module is further configured for varying the azimuth angle of the line of sight vector.

15. The system of claim 10 , wherein the vector module is further configured for varying a position of the source position along a rotation axis of the main rotor of the simulated rotorcraft.

16. The system of claim 10 , wherein the vector module is configured for generating a plurality of line of sight vectors each having a respective source position located on the simulated rotorcraft, a respective azimuth angle and a respective length.

17. The system of claim 16 , wherein the distance between the simulated obstacle and the simulated rotorcraft comprising a respective distance between each respective source position and the simulated obstacle.

18. The system of claim 16 , wherein the respective length is identical for each one of the plurality of line of sight vectors.

19. The system of claim 10 , further comprising a distance module configured for:
accessing a visual database containing a topography of a simulated terrain and simulated physical structures;
identifying the simulated obstacle as being the closest object from the source position along a direction defined by the azimuth angle, the closest object being one of a part of the simulated terrain and one of the simulated physical structures and a distance between the closest object and the source position being at most equal to the given length of the line of sight vector; and
determining a distance between the source position and the closest object, thereby obtaining the distance between the simulated obstacle and the simulated rotorcraft.

20. A non-transitory computer program product comprising a computer readable memory storing computer executable instructions thereon that when executed by a computer perform method steps of:
receiving an aircraft airspeed of a simulated rotorcraft and a height above ground for the simulated rotorcraft;
generating a line of sight vector having a source position located on the simulated rotorcraft, a direction and a given length;
determining a distance between a simulated obstacle and the simulated rotorcraft using the line of sight vector, the distance being at most equal to the given length of the line of sight vector;
determining a recirculation induced airflow velocity using the distance between the simulated obstacle and the simulated rotorcraft, the aircraft airspeed and the height above ground, the recirculation induced airflow velocity being caused by a downwash recirculation flow generated by the simulated obstacle; and
outputting the recirculation induced airflow velocity.

Assignees

• Cae Inc

Inventors

• Nadeau Beaulieu Michel
• Tardif Jean

Classifications

• G09B9/46 Primary

  the aircraft being a helicopter · CPC title

• G09B9/44

  providing simulation in a real aircraft flying through the atmosphere without restriction of its path · CPC title

• G09B9/085

  Special purpose teaching, e.g. alighting on water, aerial photography · CPC title