CN101788305A - Method for rapid field calibration of micro inertial measurement unit - Google Patents

Abstract

The invention relates to a method for calibration of a micro inertial measurement unit, in particular to a method for rapid field calibration of a micro inertial measurement unit, which solves the problems that the operation of the existing method for calibration of the micro inertial measurement unit is complex and time-consuming and the field calibration lacks direction and position criteria. The method for rapid field calibration of the micro inertial measurement unit is realized through the following steps: (1) establishing a calibration model; (2) accurately measuring the local gravitational acceleration of the fixed position point to be calibrated; (3) randomly rotating the micro inertial measurement unit in the fixed position point to be calibrated; (4) fitting an ellipsoid equation; (5) collating the fitted ellipsoid equation into a standard ellipsoid equation; (6) calculating the axial scale factor and null bias of an accelerometer for the micro inertial measurement unit; and (7) compensating the output information of the micro inertial measurement unit. The invention is applicable to the field calibration of the micro inertial measurement unit.

Description

A kind of method for quick field calibration of micro inertial measurement unit

Technical field

The present invention relates to the scaling method of Micro Inertial Measurement Unit, specifically is a kind of method for quick field calibration of micro inertial measurement unit.

Background technology

Micro Inertial Measurement Unit is the core component of micro-inertial measuring system.Before using Micro Inertial Measurement Unit, must carry out test calibration to it, with determine wherein inertia device (accelerometer) zero partially, demarcate parameters such as factor and between centers alignment error angle, so that the output information by Micro Inertial Measurement Unit accurately calculates carrier coordinate system each axial linear acceleration and angular velocity of rotation, and then provide input information really and accurately for the attitude algorithm and the navigation calculating of system.Correlation test shows, as time passes and environmental change, the between centers alignment error angle of the inertia device in the Micro Inertial Measurement Unit can not change, but inertia device zero partially, demarcate factor and can change.Wherein, zero of inertia device changes particularly evident partially, all can be different when working on power at every turn, and As time goes on, zero changes constantly aggravation partially.As everyone knows, zero of the inertia device error effect that changes partially navigation and location increases by secondary and the cube of time respectively.This shows, if the parameter of demarcating in Micro Inertial Measurement Unit testing laboratory is applied in the actual test in later stage, can produce than mistake, reduce the measuring accuracy of Micro Inertial Measurement Unit, and Micro Inertial Measurement Unit, particularly be applied to the Micro Inertial Measurement Unit of conventional weapons such as rocket projectile, shell equipment, need have higher measuring accuracy in a short time, is badly in need of a kind of can be before Micro Inertial Measurement Unit be used the scene method of demarcation quick and precisely.The scaling method of existing Micro Inertial Measurement Unit all needs microtest equipment that directional reference and position reference are provided, leave these accurate experimental facilitiess and carry out accurately demarcation of scene, can only carry out simple on-site and demarcate with regard to directly causing Micro Inertial Measurement Unit before reality is used, to be difficult to have ready conditions.And simple calibrating often lack direction benchmark and position reference, demarcating partially with zero of accelerometer is example, only be seek two fully the positions of symmetry just be difficult to accomplish.In a word, the scaling method of existing Micro Inertial Measurement Unit need rely on laboratory equipment, and complicated operation, time-consuming and stated accuracy is low is difficult to satisfy the application demand of micro-inertial measuring system.Based on this, be necessary to invent a kind of simple to operate, save time and method for quick field calibration of micro inertial measurement unit that stated accuracy is high.

Summary of the invention

The present invention is for the scaling method complicated operation that solves existing Micro Inertial Measurement Unit, time-consuming and on-site proving is lacked direction and position reference and the low problem of simple calibrating precision provides a kind of method for quick field calibration of micro inertial measurement unit.

The present invention adopts following technical scheme to realize: a kind of method for quick field calibration of micro inertial measurement unit, this method are to adopt following steps to realize:

(1) sets up peg model; The concrete form of peg model is as follows:

$\left[\begin{array}{c}{u}_x\\ u_y\\ u_z\end{array}\right]=\left[\begin{array}{ccc}{k}_{\mathrm{xx}}& \widehat{k_{\mathrm{yx}}}& \widehat{k_{\mathrm{zx}}}\\ \widehat{k_{\mathrm{xy}}}& k_{\mathrm{yy}}& \widehat{k_{\mathrm{zy}}}\\ \widehat{k_{\mathrm{xz}}}& \widehat{k_{\mathrm{yz}}}& k_{\mathrm{zz}}\end{array}\right]\left[\begin{array}{c}{a}_x\\ a_y\\ a_z\end{array}\right]+\left[\begin{array}{c}{u}_{x0}\\ u_{y0}\\ u_{z0}\end{array}\right]$

Wherein, k _Ij(i=x, y, z; J=x, y, z; I=j) be the axial constant multiplier of accelerometer,

(i=x, y, z; J=x, y, z; I ≠ j) is an accelerometer between centers coupling constant multiplier; u _I0(i=x, y, z) be x axle, y axle, z direction of principal axis accelerometer zero partially;

(i=x, y, z; J=x, y, z; The value of i ≠ j) is demarcated by Micro Inertial Measurement Unit testing laboratory;

(2) accurately measure local gravitational acceleration in fixed position point to be calibrated;

(3) rotate Micro Inertial Measurement Unit at random in fixed position point to be calibrated, make its attitude angle (angle between the coordinate axis of Micro Inertial Measurement Unit place coordinate system and the coordinate axis of quiet ground coordinate system) span cover Micro Inertial Measurement Unit place three dimensions scope (promptly making the coordinate axis end points motion of Micro Inertial Measurement Unit place coordinate system form the ellipsoid track) as far as possible, and then obtain a series of accelerometer output voltage measured values;

(4) simulate the ellipsoid equation by a series of accelerometer output voltage measured values;

(5) the ellipsoid equation arrangement that simulates is the standard spheroid equation, obtains spheroid-like matrix and ellipsoid centre coordinate;

(6) by spheroid-like matrix and ellipsoid centre coordinate, the axial constant multiplier of accelerometer that calculates Micro Inertial Measurement Unit is inclined to one side with zero;

(7), the output information of Micro Inertial Measurement Unit is compensated with the axial constant multiplier of the accelerometer that calculates and zero substitution peg model partially.

Usually, the general peg model of Micro Inertial Measurement Unit is:

$\left[\begin{array}{c}{u}_x\\ u_y\\ u_z\end{array}\right]=\left[\begin{array}{ccc}{k}_{\mathrm{xx}}& k_{\mathrm{yx}}& k_{\mathrm{zx}}\\ k_{\mathrm{xy}}& k_{\mathrm{yy}}& k_{\mathrm{zy}}\\ k_{\mathrm{xz}}& k_{\mathrm{yz}}& k_{\mathrm{zz}}\end{array}\right]\left[\begin{array}{c}{a}_x\\ a_y\\ a_z\end{array}\right]+\left[\begin{array}{c}{u}_{x0}\\ u_{y0}\\ u_{z0}\end{array}\right]---\left(1\right)$

In the formula (1): u _i(i=x, y z) are x axle, the y axle of Micro Inertial Measurement Unit, the output voltage measured value of z direction of principal axis accelerometer; k _Ij(i=x, y, z; J=x, y, z; I ≠ j) is an accelerometer between centers coupling constant multiplier; k _Ij(i=x, y, z; J=x, y, z; I=j) be the axial constant multiplier of accelerometer; a _i(i=x, y z) are the output accekeration of x axle, y axle, z direction of principal axis accelerometer; u _I0(i=x, y, z) be x axle, y axle, z direction of principal axis accelerometer zero partially.

Consider accelerometer between centers coupling constant multiplier k _Ij(i=x, y, z; J=x, y, z; I ≠ j) itself is very little, and variable quantity is very little in a short time, and consequent influence is very little, so uses recently accurately calibration result during on-site proving

The approximate k that replaces _Ij(i=x, y, z; J=x, y, z; I ≠ j) (promptly

Value demarcate by Micro Inertial Measurement Unit testing laboratory), the only bigger axial constant multiplier k of accelerometer during on-site proving to influence _Ij(i=x, y, z; J=x, y, z; I ≠ j) and zero is u partially _I0(i=x, y z) demarcate, and therefore, the peg model in the described step (1) specifically is expressed as follows for the peg model after approximate, the peg model after being similar to:

$\left[\begin{array}{c}{u}_x\\ u_y\\ u_z\end{array}\right]=\left[\begin{array}{ccc}{k}_{\mathrm{xx}}& \widehat{k_{\mathrm{yx}}}& \widehat{k_{\mathrm{zx}}}\\ \widehat{k_{\mathrm{xy}}}& k_{\mathrm{yy}}& \widehat{k_{\mathrm{zy}}}\\ \widehat{k_{\mathrm{xz}}}& \widehat{k_{\mathrm{yz}}}& k_{\mathrm{zz}}\end{array}\right]\left[\begin{array}{c}{a}_x\\ a_y\\ a_z\end{array}\right]+\left[\begin{array}{c}{u}_{x0}\\ u_{y0}\\ u_{z0}\end{array}\right]---\left(2\right)$

Since the vector of the output accekeration of x axle, y axle, z direction of principal axis accelerometer and be always local gravitational acceleration, that is:

a ^Ta＝[k ^-1(u-u ₀)] ^T[k ^-1(u-u ₀)]＝G ² (3)

In the formula (3): G is a local gravitational acceleration;

Can obtain following second normal form equation by formula (3):

$\frac{u^T{\left(k^{-1}\right)}^T{k}^{-1}u}{G^2}-\frac{{2u}^T{\left(k^{-1}\right)}^T{k}^{-1}{u}_0}{G^2}+\frac{u_0^T{\left(k^{-1}\right)}^T{k}^{-1}{u}_0}{G^2}=1---\left(4\right)$

In the formula (3): $k=\left[\begin{array}{ccc}{k}_{\mathrm{xx}}& \widehat{k_{\mathrm{yx}}}& \widehat{k_{\mathrm{zx}}}\\ \widehat{k_{\mathrm{xy}}}& k_{\mathrm{yy}}& \widehat{k_{\mathrm{zy}}}\\ \widehat{k_{\mathrm{xz}}}& \widehat{k_{\mathrm{yz}}}& k_{\mathrm{zz}}\end{array}\right],u=\left[\begin{array}{c}{u}_x\\ u_y\\ u_z\end{array}\right],u_0=\left[\begin{array}{c}{u}_{x0}\\ u_{y0}\\ u_{z0}\end{array}\right];$

By formula (4) as can be known, the output voltage measured value of x axle, y axle, z direction of principal axis accelerometer satisfies a secondary Ellipsoidal Surface equation, and its geometric meaning is that the coordinate points of the output voltage measured value of x axle, y axle, z direction of principal axis accelerometer is positioned in measurement coordinate system on the Ellipsoidal Surface of being determined by formula (4).

In the described step (4), the process of match ellipsoid equation is based on the least squares theory of ellipsoid constraint, and fit procedure relies on computing machine to finish.

In the described step (5), the standard spheroid equation that the ellipsoid equation arrangement through simulating draws is as follows:

$X^T\mathrm{SX}-2X_0^T\mathrm{SX}+X_0^{T}S{X}_0=1---\left(5\right)$

In the formula (5): S is the spheroid-like matrix; X ₀Center point coordinate for ellipsoid.

Formula (5) can draw with formula (4) comparison:

$\left\{\begin{array}{c}{\mathrm{kk}}^T=S^{-1}/G^2\\ u_0=X_0\end{array}\right.---\left(6\right)$

Centre coordinate X according to spheroid-like matrix S and ellipsoid ₀, can calculate the axial constant multiplier k of x axle, y axle, z direction of principal axis accelerometer _Ij(i=x, y, z; J=x, y, z; I ≠ j) and zero is u partially _I0(i=x, y, z).Concrete computation process is as follows:

If

It is as follows to obtain system of equations according to formula (6):

The group of solving an equation calculates the axial constant multiplier k of accelerometer of Micro Inertial Measurement Unit _Ij(i=x, y, z; J=x, y, z; I ≠ j) and zero is u partially _I0(i=x, y, z) as follows:

With the axial constant multiplier k of the accelerometer that calculates _Ij(i=x, y, z; J=x, y, z; I ≠ j) and zero is u partially _I0(z) peg model in the described step of substitution (1) is in conjunction with the accelerometer between centers coupling constant multiplier of accurately being demarcated by Micro Inertial Measurement Unit testing laboratory in the recent period for i=x, y (i=x, y, z; J=x, y z), promptly finishes the quick field calibration to Micro Inertial Measurement Unit, thereby makes Micro Inertial Measurement Unit obtain measurement result more accurately.Compare with the scaling method of existing Micro Inertial Measurement Unit, that method for quick field calibration of micro inertial measurement unit of the present invention has is easy to operate, save time, need not characteristics such as benchmark location, stated accuracy height, can satisfy the demand of micro-inertial navigation system practical application.

The present invention is according to the Micro Inertial Measurement Unit peg model of setting up, least square fitting theory in conjunction with the ellipsoid constraint, efficiently solve the scaling method complicated operation, time-consuming and on-site proving is lacked direction and position reference and the low problem of simple calibrating precision is widely used in the on-site proving of Micro Inertial Measurement Unit in each field of existing Micro Inertial Measurement Unit.

Embodiment

A kind of method for quick field calibration of micro inertial measurement unit, this method are to adopt following steps to realize:

(1) sets up peg model; The concrete form of peg model is as follows:

$\left[\begin{array}{c}{u}_x\\ u_y\\ u_z\end{array}\right]=\left[\begin{array}{ccc}{k}_{\mathrm{xx}}& \widehat{k_{\mathrm{yx}}}& \widehat{k_{\mathrm{zx}}}\\ \widehat{k_{\mathrm{xy}}}& k_{\mathrm{yy}}& \widehat{k_{\mathrm{zy}}}\\ \widehat{k_{\mathrm{xz}}}& \widehat{k_{\mathrm{yz}}}& k_{\mathrm{zz}}\end{array}\right]\left[\begin{array}{c}{a}_x\\ a_y\\ a_z\end{array}\right]+\left[\begin{array}{c}{u}_{x0}\\ u_{y0}\\ u_{z0}\end{array}\right]$

Wherein, k _Ij(i=x, y, z; J=x, y, z; I=j) be the axial constant multiplier of accelerometer, (i=x, y, z; J=x, y, z; I ≠ j) is an accelerometer between centers coupling constant multiplier; u _I0(i=x, y, z) be x axle, y axle, z direction of principal axis accelerometer zero partially; (i=x, y, z; J=x, y, z; The value of i ≠ j) is demarcated by Micro Inertial Measurement Unit testing laboratory;

(2) accurately measure local gravitational acceleration in fixed position point to be calibrated;

(3) rotate Micro Inertial Measurement Unit at random in fixed position point to be calibrated, make its attitude angle span cover Micro Inertial Measurement Unit place three dimensions scope as far as possible, and then obtain a series of accelerometer output voltage measured values;

(4) simulate the ellipsoid equation by a series of accelerometer output voltage measured values;

(5) the ellipsoid equation arrangement that simulates is the standard spheroid equation, obtains spheroid-like matrix and ellipsoid centre coordinate;

(6) by spheroid-like matrix and ellipsoid centre coordinate, the axial constant multiplier of accelerometer that calculates Micro Inertial Measurement Unit is inclined to one side with zero;

(7), the output information of Micro Inertial Measurement Unit is compensated with the axial constant multiplier of the accelerometer that calculates and zero substitution peg model partially.

Claims (1)

1. method for quick field calibration of micro inertial measurement unit is characterized in that: this method is to adopt following steps to realize:

(1) sets up peg model; The concrete form of peg model is as follows:

$\left[\begin{array}{c}{u}_x\\ u_y\\ u_z\end{array}\right]=\left[\begin{array}{ccc}{k}_{\mathrm{xx}}& \widehat{k_{\mathrm{yx}}}& \widehat{k_{\mathrm{zx}}}\\ \widehat{k_{\mathrm{xy}}}& k_{\mathrm{yy}}& \widehat{k_{\mathrm{zy}}}\\ \widehat{k_{\mathrm{xz}}}& \widehat{k_{\mathrm{yz}}}& k_{\mathrm{zz}}\end{array}\right]\left[\begin{array}{c}{a}_x\\ a_y\\ a_z\end{array}\right]+\left[\begin{array}{c}{u}_{x0}\\ u_{y0}\\ u_{z0}\end{array}\right]$

Wherein, k _Ij(i=x, y, z; J=x, y, z; I=j) be the axial constant multiplier of accelerometer,

(i=x, y, z; J=x, y, z; I ≠ j) is an accelerometer between centers coupling constant multiplier; u _I0(i=x, y, z) be x axle, y axle, z direction of principal axis accelerometer zero partially;

(i=x, y, z; J=x, y, z; The value of i ≠ j) is demarcated by Micro Inertial Measurement Unit testing laboratory;

(2) accurately measure local gravitational acceleration in fixed position point to be calibrated;

(3) rotate Micro Inertial Measurement Unit at random in fixed position point to be calibrated, make its attitude angle span cover Micro Inertial Measurement Unit place three dimensions scope as far as possible, and then obtain a series of accelerometer output voltage measured values;

(4) simulate the ellipsoid equation by a series of accelerometer output voltage measured values;

(5) the ellipsoid equation arrangement that simulates is the standard spheroid equation, obtains spheroid-like matrix and ellipsoid centre coordinate;

(6) by spheroid-like matrix and ellipsoid centre coordinate, the axial constant multiplier of accelerometer that calculates Micro Inertial Measurement Unit is inclined to one side with zero;

(7), the output information of Micro Inertial Measurement Unit is compensated with the axial constant multiplier of the accelerometer that calculates and zero substitution peg model partially.