CALIBRATION METHOD OF THE POSITIONING OF AN ONBOARD DEVICE FOR THE ACQUISITION AND THE REMOTE TRANSMISSION OF DATA RELATING TO MOTION AND DRIVING PARAMETERS OF MOTOR VEHICLES AND MOTORCYCLES

Abstract

A calibration method of the positioning of an onboard device of a vehicle with axes (x, y, z), wherein the device comprises at least one accelerometric sensor (S) which detects the accelerations to which the vehicle is subjected along axes (x, y, z), angularly arranged with respect to the axes (x, y, z) of the vehicle with rotation angles (x, y, z). The accelerometric sensor (S) acquires the acceleration values generated by the force of gravity G acting on the vehicle when the vehicle is stopped. A transformation matrix (R) is determined, wherein a first rotation angle (x) and a second rotation angle (y) are derived on the basis of acceleration values of the force of gravity detected along the axes (x, y, z) when the vehicle is stopped, and a third rotation angle (z) is derived on the basis of the determined travel direction of the vehicle.

Claims

1. A calibration method of the positioning of an onboard device for the acquisition and the remote transmission of data relating to motion and driving parameters of a vehicle having a first plurality of axes of a reference coordinate system of the vehicle (x, y, z), wherein said onboard device comprises at least one accelerometric sensor (S) adapted to detect the accelerations to which the vehicle is subjected along a second plurality of axes of a reference coordinate system of the accelerometric sensor (x, y, z), the second plurality of axes (x, y, z) of the accelerometric sensor (S) being angularly arranged with respect to the first plurality of axes (x, y, z) of the reference coordinate system of the vehicle with a plurality of rotation angles (.sub.x, .sub.y, .sub.z) respectively; said method being characterized in that it comprises: when the vehicle is stopped in a substantially horizontal position, acquiring the acceleration values generated by the force of gravity, G, acting on the vehicle along the second plurality of axes of the reference coordinate system of the accelerometric sensor (x, y, z), by means of said accelerometric sensor (S); acquiring, by means of said accelerometric sensor (s), the acceleration values generated by a plurality of events suffered by the vehicle along the second plurality of axes of the reference coordinate system of the accelerometric sensor (x, y, z), whose acceleration exceeds a predetermined threshold value; determining a travel direction of the vehicle on the basis of a prevailing direction in which the accelerations generated by a plurality of events suffered by the vehicle along the second plurality of axes of the reference coordinate system of the accelerometric sensor (x, y, z) have been acquired; said method determining a transformation matrix (R), adapted to put in relation the accelerations measured along the second plurality of axes of the coordinate system of the accelerometric sensor (x, y, z) with corresponding accelerations along the first plurality of axes in the coordinate system of the vehicle (x, y, z), wherein a first rotation angle (.sub.x) and a second rotation angle (.sub.y) are derived on the basis of acceleration values of the force of gravity detected along the second plurality of axes of the reference coordinate system of the accelerometric sensor (x, y, z) when the vehicle is stopped in a substantially horizontal position, and a third rotation angle (.sub.z) is derived on the basis of the determined travel direction of the vehicle.

2. A calibration method according to claim 1, wherein the step of acquiring by means of said accelerometric sensor (S) the accelerations generated by a plurality of events suffered by the vehicle along the second plurality of axes of the reference coordinate system of the accelerometric sensor (x, y, z), the value of which exceeds a predetermined acceleration threshold value, takes place in a first phase of motion of the vehicle.

3. A calibration method according to claim 1, wherein both the first plurality of axes of the reference coordinate system of the vehicle (x, y, z) and the second plurality of axes of the reference coordinate system of the accelerometric sensor (x, y, z) comprise three axes respectively.

4. A calibration method according claim 1, wherein the plurality of events suffered by the vehicle along the second plurality of axes of the reference coordinate system of the accelerometric sensor (x, y, z), acquired by said accelerometric sensor (S), comprises abrupt acceleration events and abrupt braking events suffered by the vehicle.

5. A method according to claim 1, wherein the accelerometric sensor (S) is a three-axis accelerometer.

6. An onboard device of a vehicle, comprising an elaboration module programmed to implement a method according to claim 1.

7. A computer program executable by an elaboration module of an onboard device of a vehicle, adapted to implement a calibration method of the invention according to claim 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Further features and advantages of the invention will appear more clearly from the following detailed description of an embodiment thereof, given by way of non-limiting example with reference to the accompanying drawing, in which:

[0026] FIG. 1 shows an exemplary arrangement of a vehicle and an onboard device and the respective detection axes;

[0027] FIG. 2 shows a left-handed reference system for the purposes of mathematical discussion of the calibration method;

[0028] FIG. 3 shows the mathematical notation used to describe a rotation of a plane about an axis in the conversion from a first to a second reference system;

[0029] FIG. 4 shows a vector of gravity in plane xy in the particular case in which the vehicle is a motorcycle; and

[0030] FIG. 5 shows a vector of gravity in plane yz in the particular case in which the vehicle is a motorcycle.

DETAILED DESCRIPTION

[0031] Before explaining a plurality of embodiments of the invention in detail, it should be noted that the invention is not limited in its application to the construction details and to the configuration of the components presented in the following description or shown in the drawings. The invention can take other embodiments and be implemented or practically carried out in different ways. It should also be understood that the phraseology and terminology are for descriptive purpose and are not to be construed as limiting. The use of include and comprise and variations thereof are intended as including the elements cited thereafter and their equivalents, as well as additional elements and equivalents thereof.

[0032] The calibration method of the positioning of an onboard device for the acquisition and the remote transmission of data relating to motion and driving parameters of a vehicle, wherein the device has a first plurality of axes of a reference coordinate system of the vehicle x, y, z and comprises at least one accelerometric sensor S adapted to detect the accelerations to which the vehicle is subjected along a second plurality of axes of a reference coordinate system of the accelerometric sensor x, y, z angularly arranged with respect to the first plurality of axes x, y, z of the reference coordinate system of the vehicle with a plurality of rotation angles .sub.x,.sub.y,.sub.z, respectively, comprises the following steps:

[0033] In the embodiment described herein, each plurality of axes of the reference coordinate system of the vehicle x, y, z and the plurality of axes of a reference coordinate system of the accelerometric sensor x, y, z is composed by three axes respectively. The calibration method, although based on the same basic mathematical considerations, differs in the 2 cases of positioning calibration on motor vehicles and motorcycles.

[0034] Calibration of the Positioning on Motor Vehicles

[0035] A first step consists in acquiring the acceleration values generated by the force of gravity G acting on the vehicle along the axes of the reference coordinate system of the accelerometric sensor x, y, z, when the vehicle is stopped in a substantially horizontal position, by means of the accelerometric sensor S.

[0036] A second step consists in acquiring, by means of said accelerometric sensor S, the acceleration values generated by a plurality of events suffered by the vehicle along the axes of the reference coordinate system of the accelerometric sensor x, y, z, whose value exceeds a predetermined acceleration threshold value. This acquisition step takes place in the initial motion phases of the vehicle and the plurality of events consists of a series of abrupt acceleration and braking of the vehicle having a sufficiently high strength to be considered as significant events.

[0037] A further step consists in determining the travel direction of the vehicle on the basis of a prevailing direction in which the accelerations generated by the plurality of events suffered by the vehicle along the axes of the reference coordinate system of the accelerometric sensor x, y, z have been acquired. The plurality of events includes abrupt acceleration, abrupt braking, abrupt turns and vertical stresses suffered by the vehicle.

[0038] The method ends with the determination of a transformation matrix R, which puts in relation the accelerations measured along the axes of the coordinate system of the accelerometric sensor x, y, z with corresponding accelerations along the axes in the coordinate system of the vehicle x, y, z. The matrix comprises the values of the rotation angles .sub.x,.sub.y,.sub.z, wherein the first rotation angle .sub.x and the second rotation angle .sub.y are derived on the basis of acceleration values of the force of gravity detected along the axes of the reference coordinate system of the accelerometric sensor x, y, z when the vehicle is stopped in a substantially horizontal position, and the third rotation angle .sub.z is derived on the basis of the determined travel direction of the vehicle in the step described above.

[0039] .sub.x indicates the rotation angle about the x axis; .sub.y indicates the rotation angle about the y axis; .sub.z indicates the rotation angle about the z axis.

[0040] Below is a detailed description of a preferred embodiment of the invention.

[0041] In order to detect impact or accident events, or acceleration variation events of a vehicle, it is necessary to consider a reference system integral with the vehicle, of left-hand type, using the vehicle point of view (inertial).

[0042] A left-handed system integral with the vehicle is illustrated in FIG. 2.

[0043] A three-axis accelerometric sensor is included or at least connected to the onboard device. Said accelerometric sensor has a triad of axes, normally right-handed, which must be reversed one by one to move to the inertial point of view as in the reference system integral with the vehicle.

[0044] The reference system integral with the vehicle contemplates the following arrangement of three axes: [0045] x axis arranged longitudinally to the vehicle, with positive direction that comes out in the direction of the front part of the vehicle; [0046] y axis arranged transversely to the vehicle, with positive direction that comes out from the left side of the vehicle (driver's side according to Italian vehicles); [0047] z axis arranged vertically, with positive direction that comes out from the lower side of the vehicle, downwards.

[0048] A series of equations must be illustrated to achieve a change of the reference system in space.

[0049] Considering the left-handed three-dimensional coordinate space in FIG. 2, a rotation about the z axis by a positive angle (counterclockwise rotation) is equivalent to the rotation of plane xy by an angle . Point P(P.sub.x, P.sub.y) in the new reference system has coordinates (P.sub.x, P.sub.y).

[0050] Said rotation is shown in FIG. 3.

[0051] Expressing the Cartesian coordinates in polar form:

[00001]$\begin{array}{cc}\{\begin{array}{c}{P}_x=.Math..Math.\cos .Math..Math.\\ P_Y=.Math..Math.\sin .Math..Math.\end{array}& \left(1\right)\end{array}$

[0052] The new coordinates (P.sub.x, P.sub.y) are given by:

[00002]$\begin{array}{cc}\{\begin{array}{c}{P}_{x^{}}=.Math..Math.\cos .Math..Math.\left(+\right)\\ P_{Y^{}}=.Math..Math.\sin .Math..Math.\left(+\right)\end{array}& \left(1.2\right)\\ \{\begin{array}{c}{P}_{x^{}}=.Math.\left[\cos .Math..Math..Math..Math.\cos .Math..Math.-\sin .Math..Math..Math..Math.\sin .Math..Math.\right]=P_x.Math..Math.\cos .Math..Math.-P_y.Math..Math.\sin .Math..Math.\\ P_{Y^{}}=.Math.\left[\sin .Math..Math..Math..Math.\cos .Math..Math.+\cos .Math..Math..Math..Math.\sin .Math..Math.\right]=P_y.Math..Math.\cos .Math..Math.+P_x.Math..Math.\sin .Math..Math.\end{array}& \left(1.3\right)\end{array}$

[0053] In matrix form, these relationships become:

[00003]$\begin{array}{cc}\left(\begin{array}{c}{P}_{x^{}}\\ P_{y^{}}\end{array}\right)=\left(\begin{array}{cc}\cos .Math..Math.& -\sin .Math..Math.\\ \sin .Math..Math.& \cos .Math..Math.\end{array}\right).Math..Math.\left(\begin{array}{c}{P}_x\\ P_y\end{array}\right)& \left(2\right)\end{array}$

[0054] By extending the matrix found in the three-dimensional space:

[00004]$\begin{array}{cc}\left(\begin{array}{ccc}\cos .Math..Math.& -\sin .Math..Math.& 0\\ \sin .Math..Math.& \cos .Math..Math.& 0\\ 0& 0& 1\end{array}\right)& \left(3\right)\end{array}$

[0055] Likewise, the transformation matrices for the other elementary rotations are determined: rotation about the y axis and a rotation about the x axis.

[0056] Any transformation of a three-dimensional Cartesian reference system that has no translational or deforming components can be traced back to a combination of 3 rotations about the axes, composed in a sequential manner. The rotation matrices for each rotation, are: [0057] 1. counter clockwise rotation about axis x by an angle .sub.x:

[00005]$\begin{array}{cc}{R}_x=\left(\begin{array}{ccc}1& 0& 0\\ 0& \cos .Math..Math.{}_x& -\sin .Math..Math.{}_x\\ 0& \sin .Math..Math.{}_x& \cos .Math..Math.{}_x\end{array}\right)& \left(4\right)\end{array}$ [0058] 2. counter clockwise rotation about axis y by an angle .sub.y:

[00006]$\begin{array}{cc}{R}_y=\left(\begin{array}{ccc}\cos .Math..Math.{}_y& 0& \sin .Math..Math.{}_y\\ 0& 1& 0\\ -\sin .Math..Math.{}_y& 0& \cos .Math..Math.{}_y\end{array}\right)& \left(5\right)\end{array}$ [0059] 3. counter clockwise rotation about axis z by an angle .sub.z:

[00007]$\begin{array}{cc}{R}_z=\left(\begin{array}{ccc}\cos .Math..Math.{}_z& -\sin .Math..Math.{}_z& 0\\ \sin .Math..Math.{}_z& \cos .Math..Math.{}_z& 0\\ 0& 0& 1\end{array}\right)& \left(6\right)\end{array}$

[0060] A method for verifying the correctness of the identified matrices using considerable angles is illustrated hereinafter.

[0061] Considering a null rotation, the rotation matrix about the x axis must be the identity and this is actually achieved:

[00008]$\begin{array}{cc}{}_x=0.Math.R_x=\left(\begin{array}{ccc}1& 0& 0\\ 0& 1& 0\\ 0& 0& 1\end{array}\right)& \left(6.1\right)\end{array}$

[0062] If the rotation is instead by /2, a simple transformation of the unit vectors must be obtained:

[00009]$\begin{array}{cc}{}_x=\frac{}{2}.Math.R_x=\left(\begin{array}{ccc}1& 0& 0\\ 0& 0& -1\\ 0& 1& 0\end{array}\right)& \left(6.2\right)\end{array}$

[0063] (1, 0, 0).sup.T becomes (1, 0, 0).sup.T, i.e. the unit vector x.sub.0 remains unchanged, (0, 1, 0).sup.T becomes (0, 0, 1).sup.T, i.e. the unit vector y.sub.0 becomes z.sub.0 in the new reference system, (0, 0, 1).sup.T becomes (0, 1, 0).sup.T, i.e. the unit vector z.sub.0 becomes y.sub.0; these transformations correspond to what expected, the matrix R.sub.x is therefore correct.

[0064] Considering a null rotation, the rotation matrix about axis y must be the identity and this is actually achieved:

[00010]$\begin{array}{cc}{}_y=0.Math.R_y=\left(\begin{array}{ccc}1& 0& 0\\ 0& 1& 0\\ 0& 0& 1\end{array}\right)& \left(6.3\right)\end{array}$

[0065] If the rotation is instead by /2, a simple transformation of the unit vectors must be obtained:

[00011]$\begin{array}{cc}{}_y=\frac{}{2}.Math.R_y=\left(\begin{array}{ccc}0& 0& 1\\ 0& 1& 0\\ -1& 0& 0\end{array}\right)& \left(6.4\right)\end{array}$

[0066] (1, 0, 0).sup.T becomes (0, 0, 1).sup.T, i.e. the unit vector x.sub.0 becomes z.sub.0, (0, 1, 0).sup.T becomes (0, 1, 0).sup.T, i.e. y.sub.0 remains unchanged, (0, 0, 1).sup.T becomes (1, 0, 0).sup.T, i.e. the unit vector z.sub.0 becomes x.sub.0; these transformations correspond to what expected, the matrix R.sub.y is therefore correct.

[0067] Considering a null rotation, the rotation matrix about axis z must be the identity and this is actually achieved:

[00012]$\begin{array}{cc}{}_z=0.Math.R_z=\left(\begin{array}{ccc}1& 0& 0\\ 0& 1& 0\\ 0& 0& 1\end{array}\right)& \left(6.5\right)\end{array}$

[0068] If the rotation is instead by /2, a simple transformation of the unit vectors must be obtained:

[00013]$\begin{array}{cc}{}_z=\frac{}{2}.Math.R_z=\left(\begin{array}{ccc}0& -1& 0\\ 1& 0& 0\\ 0& 0& 1\end{array}\right)& \left(6.6\right)\end{array}$

[0069] (1, 0, 0).sup.T becomes (0, 1, 0).sup.T, i.e. the unit vector x.sub.0 becomes y.sub.0, (0, 1, 0).sup.T becomes (1, 0, 0).sup.T, i.e. y.sub.0 becomes x.sub.0, (0, 0, 1).sup.T becomes (0, 0, 1).sup.T, i.e. the unit vector z.sub.0 remains unchanged.

[0070] As mentioned above, a generic rotation in space such as to make a passage between 3 Cartesian reference systems can be obtained as a composition of simple rotations.

[0071] Proceeding to the composition of R.sub.x and R.sub.y, we get:

[00014]$\begin{array}{cc}{R}_x.Math.R_y=\left(\begin{array}{ccc}\cos .Math..Math.{}_y& 0& -\sin .Math..Math.{}_y\\ \sin .Math..Math.{}_x.Math.\sin .Math..Math.{}_y& \cos .Math..Math.{}_x& -\sin .Math..Math.{}_x.Math.\cos .Math..Math.{}_y\\ -\cos .Math..Math.{}_x.Math.\sin .Math..Math.{}_y& \sin .Math..Math.{}_x& \cos .Math..Math.{}_x.Math.\cos .Math..Math.{}_y\end{array}\right)& \left(6.7\right)\end{array}$

[0072] Instead, the composition of the three single rotations that represents any rotation in space xyz is given by the following rotation matrix

[00015]$.Math.\left(7\right)$$R=R_x.Math.R_y.Math.R_z=\left(\begin{array}{ccc}\cos .Math..Math.{}_y.Math.\cos .Math..Math.{}_z& -\cos .Math..Math.{}_y.Math.\sin .Math..Math.{}_z& \sin .Math..Math.{}_y\\ \sin .Math..Math.{}_x.Math..Math.\sin .Math..Math.{}_y.Math.\cos .Math..Math.{}_z+& -\sin .Math..Math.{}_x.Math.\sin .Math..Math.{}_y.Math.\sin .Math..Math.{}_z+& -\sin .Math..Math.{}_x.Math.\cos .Math..Math.{}_y\\ \cos .Math..Math.{}_x.Math.\sin .Math..Math.{}_z& \cos .Math..Math.{}_x.Math.\cos .Math..Math.{}_z& \\ -\cos .Math..Math.{}_x.Math.\sin .Math..Math.{}_y.Math.\cos .Math..Math.{}_z+& \cos .Math..Math.{}_x.Math.\sin .Math..Math.{}_y.Math.\sin .Math..Math.{}_x+& \cos .Math..Math.{}_x.Math.\cos .Math..Math.{}_y\\ \sin .Math..Math.{}_x.Math.\sin .Math..Math.{}_z& \sin .Math..Math.{}_x.Math.\cos .Math..Math.{}_z& \end{array}\right)$

[0073] Calculating R as R.sub.x.Math.R.sub.y.Math.R.sub.z means applying in a sequence: [0074] rotation about the z axis by an angle .sub.z [0075] rotation about the y axis by an angle .sub.y [0076] rotation about the x axis by an angle .sub.x.

[0077] The composition of the single rotations is not a commutative operation and to switch from the ideal reference system xyz, integral with the vehicle, to the real reference system zyz, integral with the accelerometric sensor, the following relationship applies:

[00016]$\begin{array}{cc}\left(\begin{array}{c}{x}^{}\\ y^{}\\ z^{}\end{array}\right)=R\left(\begin{array}{c}x\\ y\\ z\end{array}\right)& \left(8\right)\end{array}$

[0078] It should be noted that both triads are left-handed.

[0079] In addition, to perform the opposite operation, that is, to convert the measured values in the values integral with the vehicle, the inverse must be calculated. The rotation in space is an isometry (i.e. it preserves angles and modules), therefore R is orthogonal, and then the inverse coincides with the transposed.

[00017]$.Math.\left(9\right)$$R^{-1}=R^T\left(\begin{array}{ccc}\cos .Math..Math.{}_y.Math.\cos .Math..Math.{}_z& \sin .Math..Math.{}_x.Math.\sin .Math..Math.{}_y.Math.\cos .Math..Math.{}_z+& -\cos .Math..Math.{}_x.Math.\sin .Math..Math.{}_y.Math.\cos .Math..Math.{}_z+\\ & \cos .Math..Math.{}_x.Math.\sin .Math..Math.{}_z& \sin .Math..Math.{}_x.Math.\sin .Math..Math.{}_z\\ -\cos .Math..Math.{}_y.Math.\sin .Math..Math.{}_z& -\sin .Math..Math.{}_x.Math.\sin .Math..Math.{}_y.Math.\sin .Math..Math.{}_z+& \cos .Math..Math.{}_x.Math.\sin .Math..Math.{}_y.Math.\sin .Math..Math.{}_z+.Math.\\ & \cos .Math..Math.{}_x.Math.\cos .Math..Math.{}_z& \sin .Math..Math.{}_x.Math.\cos .Math..Math.{}_z\\ \sin .Math..Math.{}_y& -\sin .Math..Math.{}_x.Math.\cos .Math..Math.{}_y& \cos .Math..Math.{}_x.Math.\cos .Math..Math.{}_y\end{array}\right)$

[0080] Starting from the rest position of the sensor, it is possible to determine the plane in which it moves, i.e. derive two of the three rotation angles.

[0081] At rest, we have: (x.sub.0, y.sub.0, z.sub.0).sup.T=R(0, 0, 1).sup.T, whereby:

x.sub.0=sin .sub.y(10)

y.sub.0=sin .sub.x cos .sub.y(11)

z.sub.0=cos .sub.x cos .sub.y(12)

[0082] The following simple reverse formulas find solutions in the range +/90:

[00018]$\begin{array}{cc}{x}_0^{}=\sin .Math..Math.{}_y.Math.{}_y=\mathrm{arc}.Math..Math.\sin .Math..Math.x_0^{}& \left(13\right)\\ y_0^{}=-\sin .Math..Math.{}_x.Math.\cos .Math..Math.{}_y.Math.{}_x=-\mathrm{arc}.Math..Math.\sin .Math..Math.\frac{y_0^{}}{\cos .Math..Math.{}_y}& \left(14\right)\end{array}$

[0083] The following formulas, instead, do not have this limitation: by simultaneously using equations (11, 12) dividing member by member, we obtain

[00019]$\frac{y_0^{}}{z_0^{}}=-\tan .Math..Math.{}_x$
whereby:

.sub.x=arctan 2(y.sub.0,z.sub.0)(15)

[0084] using equations (11) and (12), we calculate:

y.sub.0.sup.2+z.sub.0.sup.2=sin.sup.2 .sub.x cos.sup.2 .sub.y+cos.sup.2 .sub.x cos.sup.2 .sub.y=cos.sup.2 .sub.y

[0085] from the previous one and from (10), it follows that:

[00020]$\frac{x_0^{}}{\sqrt{y_0^{{}^2}+z_0^{{}^2}}}=\tan .Math..Math.{}_y$
and so:

.sub.y=atan 2(x.sub.0,{square root over (y.sub.0.sup.2+z.sub.0.sup.2)})(16)

[0086] In the preferred embodiment described herein, the steps of search of plane xy integral with the vehicle and of search of the travel direction are set out in detail.

[0087] The search step of plane xy integral with the vehicle occurs when the instrument panel of the vehicle is turned off, and in turn comprises the steps of: [0088] 1a) identifying the rest condition: the last 4 average triads of the accelerometric data are analyzed every 15 s (the average is on 20 s recording); if in a certain moment these averages triads differ by less than 100 mg on each axis, then the vehicle is considered in rest conditions and the last average triad is a potential new rest vector. [0089] 2a) calculating the rest position (i.e. the gravity vector at rest): if there is no gravity vector at rest already registered in a non-volatile memory associated with the onboard device, the last average triad of the previous step is selected as gravity vector at rest; otherwise, only if the new candidate rest position differs significantly from the current rest position, the current rest position is replaced with the new candidate rest position, as it is assumed that a disassembly and subsequent reassembly of the accelerometric sensor (and consequently of the onboard device, if the sensor is integrated therein) in a different position occurred. [0090] 3a) calculating .sub.x and .sub.y, using equations (15, 16). The new rest position thus calculated, along with the values of .sub.x and .sub.y is saved in the non-volatile memory.

[0091] The search step of the travel direction includes the steps of: [0092] 1b) considering the accelerometric data (x, y, z) net of the rest vector, calculated in the steps described above; [0093] 2b) applying a moving average on 30 samples; [0094] 3b) searching the peaks of module R that should correspond to abrupt braking and accelerations, and thus events with predominant component longitudinal to the motion of the vehicle, as follows: with a threshold on R of 120 mg in input at the peak and 180 mg in output (thus with a hysteresis of 30 mg around 150 mg) and a minimum and maximum threshold on the duration (1.5 and 8 seconds, respectively); in the identification step of a peak, calculating also 0 and (polar coordinates) of all the acceleration vectors during the peak; [0095] 4b) at the end of acceleration peak event, considering it valid and then going to the next step only if: [0096] a) the acceleration vector step during the peak period is almost constant, that is if the variations of and of are both within 0.8 radians, equal to 45; [0097] b) in the case of devices equipped with GNSS receiver, there is a condition of 3D navigation and the following condition is satisfied:

2.sub.v=|v.sub.iv.sub.f|>max(R)*durata*35/2,

[0098] where 35=9.8 m/s.sup.2*3.6 and the duration is expressed in seconds; c) projecting max(x, y, z) during the peak in plane xy, namely by applying the rotation with angles .sub.x and .sub.y already calculated, component z is less than 60 mg. [0099] 5b) collecting a number of significant peaks (20 in case of devices with GNSS, otherwise 30) and starting from these peaks (abrupt acceleration and braking), determining the prevailing direction on plane xy as follows: [0100] a) grouping the events in two different ways based on the angle with respect to the x axis of plane xy, both based on 24 circular sectors of 15; group A: one starts from 0 and goes in steps of 15; group B: one starts from 7.5 and goes in steps of 15; [0101] b) counting the events in each subgroup and ordering the subgroups by the sum of the resulting modules; [0102] c) if the sum of the modules of the first subgroup of the list is greater than the sum of the modules of the second subgroup by a scale factor of at least 1.1, it means that there is a dominant subgroup; [0103] i. if there is no dominant subgroup on any of its groups, the calculation of angle .sub.z is considered NOT SOLVED and new peaks are collected again; [0104] ii. if only one group has determined a dominant subgroup, the calculation of angle .sub.z is considered SOLVED and the only dominant subgroup determined is selected for the last step; [0105] iii. if both groups have determined a dominant subgroup, only if one of the 2 is dominant with respect to the other by a factor of 1.1, the calculation can be considered SOLVED and such a dominant subgroup is considered thereafter, otherwise case i) applies; [0106] d) .sub.z is given by the weighted average of the vectors that fall in the dominant range determined, where module xy is considered as weight.

Calibration of the Positioning on Motorcycles

[0107] In the particular case in which the vehicle is a motorcycle, all the foregoing considerations are applied up to formula (16), but then one proceeds in a different way to calculate a, as described hereinafter.

[0108] By measuring the gravity vector with the motorcycle inclined laterally by an angle : (x, y, z).sup.T (0, j, k).sup.T.

[0109] j and k may be derived taking into account that the triangle formed by the gravity vector before and after the tilting is isosceles in both reference systems.

[0110] FIG. 4 shows the gravity vector in plane xy.

[0111] In particular, considering the measurement system x, y, z by the accelerometric sensor, the base of the triangle measures:

B={square root over ((x.sub.1x.sub.0).sup.2+(y.sub.1y.sub.0).sup.2+(z.sub.1z.sub.0).sup.2)}(17)

[0112] On the other hand, it is known that

[00021]$\begin{array}{cc}\frac{B}{2}=\sin .Math..Math.\frac{}{2}.Math.=2.Math..Math.\arcsin .Math..Math.\frac{B}{2}=2.Math..Math.\arcsin .Math..Math.\frac{\sqrt{{\left(x_1^{}-x_0^{}\right)}^2+{\left(y_1^{}-y_0^{}\right)}^2+{\left(z_1^{}-z_0^{}\right)}^2}}{2}& \left(18\right)\end{array}$

[0113] Therefore, j is sin and k equal to cos .

[0114] FIG. 5 shows the gravity vector in plane yz.

[0115] From relationship

[00022]$\begin{array}{cc}\left(\begin{array}{c}{x}_1^{}\\ y_1^{}\\ z_1^{}\end{array}\right)=R\left(\begin{array}{c}0\\ j\\ k\end{array}\right)& \left(19\right)\end{array}$

[0116] it follows that x.sub.1=j cos .sub.y sin .sub.z+k sin .sub.y, from which we derive

[00023]${}_z=\mathrm{arc}.Math..Math.\sin .Math..Math.\frac{-x_1^{}+\sin .Math..Math.{}_y.Math.k}{\cos .Math..Math.{}_y.Math.j}.$

[0117] To summarize: [0118] measurement in the rest position (x.sub.0, y.sub.0, z.sub.0) from which we derive:

[00024]$\begin{array}{cc}{}_z=\mathrm{arc}.Math..Math.\sin .Math..Math.x_0^{}& \left(19.2\right)\\ {}_x=\mathrm{arc}.Math..Math.\sin .Math..Math.\left(\frac{-y_0^{}}{\cos .Math..Math.{}_y}\right)& \left(19.3\right)\end{array}$ [0119] measurement with motorcycle inclined laterally by an angle (x.sub.1, y.sub.1, z.sub.1) from which we derive:

[00025]$\begin{array}{cc}=2.Math..Math.\mathrm{arc}.Math..Math.\sin .Math.\frac{\sqrt{{\left(x_1^{}-x_0^{}\right)}^2+{\left(y_1^{}-y_0^{}\right)}^2+{\left(z_1^{}-z_0^{}\right)}^2}}{2},& \left(19.6\right)\\ j=\sin .Math..Math.,k=\cos .Math..Math.& \end{array}$
and then:

[00026]$\begin{array}{cc}{}_z=\mathrm{arc}.Math..Math.\sin .Math..Math.\left(\frac{-x_1^{}+\sin .Math..Math.{}_y.Math.k}{\cos .Math..Math.{}_y.Math.j}\right)& \left(19.5\right)\end{array}$ [0120] calculation of the complete matrix R to convert the data integral with the motorcycle in the measured data.

[0121] It should be noted that the proposed embodiment for the present invention in the foregoing discussion has a purely illustrative and non-limiting nature of the present invention. A man skilled in the art can easily implement the present invention in different embodiments which however do not depart from the principles outlined herein and are therefore included in the present patent.

[0122] Finally, the invention also relates to a computer program, in particular a computer program on or in an information medium or memory, adapted to implement the method of the invention. This program can use any programming language, and be in the form of source code, object code, or intermediate code between source code and object code, for example in a partially compiled form, or in any other desired form in order to implement a method according to the invention.

[0123] The information medium may be any entity or device capable of storing the program. For example, the medium may comprise a storage medium, such as a ROM, for example a CD ROM or a microelectronic circuit ROM, or a magnetic recording medium, such as a floppy disk or a hard disk.

[0124] On the other hand, the information medium may be a medium that can be transmitted, such as an electrical or optical signal, which can be routed through an electrical or optical cable, by radio signals or by other means. The program according to the invention may in particular be downloaded over an Internet type network.

[0125] Of course, the principle of the invention being understood, the manufacturing details and the embodiments may widely vary compared to what described and illustrated by way of a non-limiting example only, without departing from the scope of the invention as defined in the appended claims.