Electronic apparatus for determining the attitude of a weapon and operating method thereof

• US 9,038,900 B2
• Filed: 04/12/2011
• Issued: 05/26/2015
• Est. Priority Date: 04/12/2010
• Status: Active Grant

• Current Assignee: Selex Galileo SPA (Leonardo S.p.A.)
• Original Assignee: Selex Galileo SPA (Leonardo S.p.A.)
• Inventors: Galanti, Marco, Mattonai, Luca, Santini, Nicola
• Primary Examiner(s): Frech, Karl D
• Application Number:
  US13/640,840
• Publication Number:
  US 20130091754A1
• Time in Patent Office: 1,505 Days
• Field of Search: 235/400, 235/404, 235/407, 235/417
• US Class Current: 235/400
• CPC Class Codes: F41G 1/44 Spirit-level adjusting means, e.g. for correcting tilt; Means for indicating or correcting tilt or cant
• CPC Class Codes: F41G 1/48 for firing grenades from rifles
• CPC Class Codes: F41G 3/14 Indirect aiming means

Abstract

An embodiment of an apparatus for determining the attitude angles of a weapon includes a number of accelerometers for measuring the components of the acceleration of the weapon along the axes of a first reference system integral with weapon; a number of gyroscopes configured in such a way to measure the components of the angular speed of the weapon along the axes of the reference body; and a processing unit configured to compute a number of actual attitude angles of the weapon under dynamic conditions based on the components of the angular speed; determine a number of static attitude angles of the weapon under static conditions of the weapon based on the components of the acceleration; and correct the components of angular speed according to static attitude angles and to the actual attitude angles.

Claims

1. An apparatus configured to determine the attitude angles of a weapon, comprising:

acceleration measuring means configured to measure the weapon acceleration components along axes of a first reference system integral with the weapon;

angular speed measuring means configured to measure weapon angular speed components along the axes of said reference system; and

processing means configured to;

compute actual attitude angles of the weapon in dynamic conditions based on the weapon angular speed components;

determine static attitude angles of the weapon in static conditions of the weapon itself based on said weapon acceleration components, by filtering at a low frequency said weapon acceleration components;

correct said weapon angular speed components based on said static attitude angles and of said actual attitude angles;

determine a first static weapon attitude angle corresponding to a static pitch angle of the weapon based on a first component of the weapon acceleration along a first axis of said reference system at a computing time;

said first axis being arranged coaxially to a longitudinal axis of a barrel of said weapon;

determine a second static attitude angle corresponding to a static roll angle of the weapon based on a second component of the weapon acceleration along a second axis of said reference system and said determined said static pitch at a computing time;

said second axis being oriented towards the right side of a support frame of the weapon; and

determine a third actual attitude angle corresponding to the actual heading angle of the weapon based on said weapon angular speed components, the actual roll and pitch angles determined a computing time preceding the current computing time;

receive, at a computing time, the actual attitude angles comprising the pitch, the roll, and the heading determined at a computing time preceding the current computing time;

determine a first correction factor of said angular seed components as a function of a difference between the static pitch and the dynamic pitch determined at the computing time preceding the current computing time; and

determine a second correction factor of said angular speed components as a function of a difference between the static roll and the dynamic roll determined at the computing time preceding the current computing time.

2. The apparatus according to claim 1, wherein said processing means are configured to determine the first static weapon attitude angle corresponding to the static pitch (Psc(t_i)) by implementing the following mathematical relation:

Psc(t_i)=arcsin(Ax(t_i));

wherein Ax(ti) is a first component of the weapon acceleration along a first axis of said reference system at a computing time t_i.

3. The apparatus according to claim 1, wherein said processing means are configured to determine the second static attitude angle corresponding to the static roll (Rso(t_i)) by implementing the following mathematical relation:

Rso(t_i)=arcsin(Ay(t_i))/cos(Psc(t_i);

wherein Ay(ti) is a second component of the weapon acceleration along a second axis of said reference system.

4. The apparatus according to claim 1, wherein said electronic processing means are configured to:

determine a first correction factor computing the difference between said actual Pitch angle computed at the time preceding the current computing time, and the static pitch angle computed at the current computing time;

compute a pitch differential dP(t_i) through the relation;

dP(t_i)=Gy(t_i)*cos(Rro(t_i-1)−

Gz(t_i)*sin(Rro(t_i-1));

compute a corrected pitch differential by subtracting said first correction factor from said pitch differential; and

integrate said corrected pitch differential over time so as to determine the actual pitch angle.

5. The apparatus according to claim 1, wherein said electronic processing means are configured so as to:

determine a second correction factor computing the difference between said actual roll angle computed at the time preceding the current computing time, and said static roll angle computed at the current computing time;

compute the roll differential dP(t_i) through the following relation;

dR(t_i)=Gx(t_i)+Gy(t_i)*sin(Rro(t_i-1)*tan(Prc(t_i))+Gz(t_i-1)*cos(Rro(t_i-1))*tan(Prc(t_i-1))

compute a corrected roll differential by subtracting the correction factor from the roll differential;

integrate the corrected roll differential to determine the actual Roll angle.

6. The apparatus according to claim 1 wherein said processing means are configured to:

compute a heading differential dP(t_i) through the following mathematical relation;

dH(t_i)=H1+H2;

wherein

H1=Gy(ti)*sin(Rro(t_i-1))/cos(Prc(t_i-1));

H2=Gz*cos(Rro(t_i-1)/cos(Prc(t_i-1); and

integrate the heading differential over time to determine the actual heading angle.

7. A method for determining the attitude angles of a weapon, comprising:

measuring components of acceleration of the weapon along axes of a first reference system integral with the weapon;

measuring components of angular speed of the weapon along the axes of said reference system; and

computing actual attitude angles of the weapon in dynamic conditions based on the components of the angular speed;

determining static attitude angles of the weapon in static conditions of the weapon based on said components of the acceleration, by filtering at a low frequency said acceleration components;

correcting said angular speed components based on of said static attitude angles and said actual attitude angles;

determining a first static weapon attitude angle corresponding to the static pitch angle of the weapon based on a first component of the weapon acceleration along a first axis of said reference system at a computing time;

said first axis being arranged coaxially to a longitudinal axis of a barrel of said weapon;

determining a second static attitude angle corresponding to the static roll angle of the weapon based on a second component of the weapon acceleration along a second axis of said reference system and said determined said static pitch angle at a computing time;

said second axis being oriented towards a right side of a support frame of the weapon;

determining a third actual attitude angle corresponding to the actual heading angle of the weapon based on said weapon angular speed components, the actual roll and pitch angles determined a computing time preceding the current computing time;

receiving at a computing time, the actual attitude angles comprising the pitch, the roll and the heading determined at a computing time preceding the current computing time;

determining a first correction factor of said angular speed components as a function of a difference between the static pitch and the dynamic pitch determined at the computing time preceding the current computing time; and

determining a second correction factor of said angular speed components as a function of a difference between the static roll and the dynamic roll determined at the computing time preceding the current computing time.

8. The method according to claim 7, further comprising the step of determining the first static attitude angle of the weapon corresponding to the static pitch Psc(t_i) by implementing the following mathematical relation:

Psc(t_i)=arcsin(Ax(t_i));

wherein Ax(ti) is a first component of the acceleration of the weapon along a first axis of said reference system at a computing time t_i.

9. The method according to claim 7, further comprising the step of determining the second static attitude angle corresponding to the static roll Rso(t_i) by implementing the following mathematical relation:

Rso(t_i)=arcsin(Ay(t_i))/cos(Psc(t_i);

wherein Ay(ti) is a second component of the acceleration of the weapon along a second axis of said reference system.

10. The method according to claim 7, further comprising the step of:

determining a first correction factor by computing the difference between said actual pitch angle computed at the time preceding the current computing time, and the static pitch angle computed at the current computing time;

computing a pitch differential dP(t_i) through the relation;

dP(t_i)=Gy(t_i)*cos(Rro(t_i-1))−

Gz(t_i)*sin(Rro(t_i-1));

computing a corrected pitch differential by subtracting said first correction factor from said pitch differential; and

integrating said corrected pitch differential over time so as to determine the actual pitch angle.

11. The method according to claim 10, further comprising the step of:

determining a second correction factor computing the difference between said actual roll angle computed at the time preceding the current computing time, and said static roll angle computed at the current computing time;

computing the roll differential dR(t_i) through the following relation;

dR(t_i)=Gx(t_i)+Gy(t_i)*sin(Rro(t_i-1)*tan(Prc(t_i))+Gz(t_i-1)*cos(Rro(t_i-1))*tan(Prc(t_i-1))

computing a corrected roll differential by subtracting the correction factor from the Roll differential;

integrating the corrected roll differential to determine the actual Roll angle.

12. The method according to claim 7, further comprising the steps of:

computing a heading differential dH(t_i) through the following mathematical relation;

dH(t_i)=H1+H2;

wherein

H1=Gy(ti)*sin(Rro(t_i-1))/cos(Prc(t_i-1));

H2=Gz*cos(Rro(t_i-1)/cos(Prc(t_i-1); and

integrating the heading differential over time to determine the actual Heading angle.

13. A computer product loadable on a memory of a computer and configured to implement, when running, the method according to claim 7.