Aiming system

• US 8,955,749 B2
• Filed: 12/07/2012
• Issued: 02/17/2015
• Est. Priority Date: 12/09/2011
• Status: Active Grant

• Current Assignee: Selex ES S.p.A. (Leonardo S.p.A.)
• Original Assignee: Selex ES S.p.A. (Leonardo S.p.A.)
• Inventors: Elefante, Alessandro
• Primary Examiner(s): TRAIL, ALLYSON NEEL
• Application Number:
  US14/363,017
• Publication Number:
  US 20140319217A1
• Time in Patent Office: 802 Days
• Field of Search: 235/407, 235/404, 235/409, 340/980, 348/158
• US Class Current: 235/407
• CPC Class Codes: F41G 3/16 Sighting devices adapted for indirect laying of fire
• CPC Class Codes: F41G 3/165 using a TV-monitor
• CPC Class Codes: F41G 3/225 Helmet sighting systems

Abstract

An aiming system for portable weapons comprising pairs of inertial sensors of gyroscopic, accelerometer and magnetometric type arranged respectively on a weapon and on an helmet with Head Up Display, so as to determine both the relative orientation and the relative position in space of the weapon and of the helmet, with consequent display of the line of fire on the Head Up Display.

Claims

1. An aiming system for portable weapons comprising:

a first pair of inertial sensors and a second pair of inertial sensors, said first part of inertial sensors and said second pair of inertial sensors to be arranged respectively on a portable weapon defining a firing trajectory, and on a display device to be worn on a head of a user comprising a visor that can be viewed by the user, said first pair of inertial sensors comprising first inertial sensors adapted to detect an orientation in space and said second pair of inertial sensors comprising second inertial sensors adapted to detect an orientation of a terrestrial magnetic field, said first pair of inertial sensors and said second pair of inertial sensors being adapted to determine, in cooperation with reference means adapted to define at least one initial orientation for said weapon and said display device in space, a relative orientation in space for the weapon and the display device;

an electronic means for managing information received from said first pair of inertial sensors and said second pair of inertial sensors and adapted to place in mutual relation the orientation in space of said weapon and of said display device and to represent in said visor, on a basis of said orientation relation, at least part of the firing trajectory of the weapon;

a third pair of inertial sensors respectively arranged on said weapon and on said display device, said third pair of inertial sensors comprising third inertial sensors adapted to determine a linear displacement in space of said weapon and of said display device, said electronic means for managing information being adapted to place in mutual relation positions in space of said weapon and of said display device and to represent in said visor at least part of the firing trajectory of the weapon both on a basis of said position relation, and on the basis of said orientation relation.

2. A system according to claim 1, wherein said third inertial sensors are accelerometers adapted to determine, in cooperation with said electronic managing means, a value of translations of said weapon and of said display device associated with the head of the user for using a translation value in a calculation and representation of said at least part of the firing trajectory of the weapon in the visor.

3. A system according to claim 1, wherein said first pair of inertial sensors, said second pair of inertial sensors and said third pair of inertial sensors are arranged on two MEMS-type inertial platforms.

4. A system according to claim 1, wherein on said portable weapon and on said display device are three inertial sensors said three inertial sensors comprising a magneto-metric sensor, a gyroscopic sensor and an accelerometer sensor.

5. A system according to claim 4, wherein said gyroscopic sensor and said accelerometer sensor comprise sets of three detection directions to determine Cartesian components of an angular velocity and of an acceleration in space.

6. A system according to claim 1, wherein one or more of said gyroscopic sensors and said accelerometer are formed by three “

sub-sensors”

respectively in a form of gyroscopes and linear accelerometers, arranged orthogonal to one another, said gyroscopes being sensitive to rotations, said accelerometers being sensitive to accelerations and form a reference to the set of three gyroscopes, said magnetometric sensor forming a reference to the set of three gyroscopes.

7. A system according to claim 1, wherein said electronic means for managing information coming from the inertial sensors comprises an electronic unit physically associated with the display device, said electronic unit being designed to place in mutual relation the orientation and the position in space of the weapon and of the display device and to represent in the visor, on the basis of said relations of orientation and of position, at least part of the firing trajectory of the weapon.

8. A system according to claim 1, wherein said display device is associated with a helmet.

9. A system according to claim 1, further comprising data communication means, of wireless type, between sensor means of said weapon and said electronic managing means.

10. A system according to claim 1, further comprising reference means for defining an orientation and an initial position in space for the weapon and the display device (12) which must be known to the system in such a manner as to have initial data from which to carry out variations in orientation and position detected by the sensors useful for projection in the visor of said at least one firing trajectory.

11. A system according to claim 10, wherein said reference means comprises a positioning area between the weapon and the display device such that when the weapon is positioned on said display device in said positioning area, the position and the relative orientation of the weapon and the display device are unequivocally determined.

12. A system according to claim 11, wherein said reference area is implemented by a pocket defined in a helmet inside which a counter-shaped part of the weapon is inserted, in such a manner that in coupling thereof a mutual orientation and a mutual position are unequivocally defined, wherein a control is present on said pocket such that when the weapon is coupled with said pocket, said control being necessarily activated and the system initializes the mutual position and orientation of the weapon and of the display device.

13. A system according to claim 1, further comprising an initialization step in which the position and relative orientation in space of the weapon and of the display device are defined, so that at a time t=0, the weapon and the display device are at a known mutual distance and angular position, said initialization step comprising:

measurement of a drift of the gyroscopes;

calculation of a gravity acceleration component on each of three accelerometers appropriately filtered and measurement of drift of the three accelerometers, having subtracted the gravity acceleration;

setting of initial position and velocity values of the weapon and of the display device.

14. A system according to claim 1, wherein said electronic managing means calculates, by a specific algorithm, on the basis of values of acceleration, angular velocity and magnetic angle, the position in space of the weapon and of the display device, an output of said specific algorithm providing a relative distance and relative orientation between the weapon and the display device by means of difference of Cartesian components of position in an Earth reference system and by means of difference of respective Pitch, Roll and Heading angles.

15. A system according to claim 1, wherein determination of one or more of the position of said weapon and of said display device is implemented by integrating twice an acceleration measured by an acceleration sensor.

16. A system according to claim 15, wherein before the integrating, said acceleration measured by said acceleration sensor is corrected by subtracting one or more of gravity acceleration and centripetal force.

17. A system according to claim 16, wherein before correction by means of subtraction of one or more of the gravity acceleration and of the centripetal acceleration, said acceleration measured by said acceleration sensor is corrected by means of subtraction of a drift effect measured in an initialization step.

18. A system according to claim 15, wherein the centripetal acceleration is calculated using angular velocity data measured by a gyroscopic sensor after having subtracted a value of the drift calculated in the initialization step.

19. A system according to claim 1, wherein determination of Pitch, Roll and Heading angles defining the orientation of one or more of said weapon and of said display device is implemented starting from values of angular velocity measured by a gyroscopic sensor and after having subtracted a value of drift calculated in an initialization step.

20. A system according to claim 1, wherein determination of Pitch, Roll and Heading angles defining the orientation of one or more of said weapon and of said display device can be implemented by means of operations performed on the following relations

21. A system according to claim 1, wherein determination of Pitch, Roll and Heading angles defining the orientation of one or more of said weapon and of said display device can be implemented by means of the following relations, where A_mx, A_my and A_mz are components along orthogonal axes x, y, z and H_x, H_y components of the terrestrial magnetic field measured by a magnetometer along the axes x and y:

P=s<sup>−

1</sup>(A_mx), R=t<sup>−

1</sup>(A_my/A_mz), H=t<sup>−

1</sup>(H_y/H_x).

22. A system according to claim 20, wherein said determination of the Pitch, Roll and Heading angles defining the orientation of one or more of said weapon and of said display device is implemented by means of an algorithm, called sensor fusion, adapted to substantially compare values of variations {dot over (R)}, {dot over (P)}, {dot over (H)} of the angles R, P, H, calculated through gyroscopic sensors, with the values of R, P, H calculated with relations, starting from values measured by accelerometer sensors.

23. A system according to claim 22, wherein determination of the Pitch, Roll and Heading angles takes place iteratively, at a first step the algorithm subtracts from the Pitch/Roll/Heading derivative calculated, a parameter k, a value of which is appropriately initialized, after which the Pitch/Roll/Heading derivative with the parameter k subtracted is integrated and provided as output as a final Pitch/Roll/Heading value, instead, starting from a second step, the value of k which is one of added to and subtracted from the Pitch/Roll/Heading derivative, varies according to a difference between P_gyro, calculated starting from a measurement at gyroscopes, and P_acc, calculated starting from measurement at accelerometers, in such a manner that said difference is reduced iteratively, simultaneously changing the Pitch/Roll/Heading value.