METHOD FOR DETERMINING A ROTOR POSITION OF A THREE-PHASE MACHINE WITHOUT USING A ROTARY ENCODER AND DEVICE FOR CONTROLLING A THREE-PHASE MOTOR WITHOUT USING A ROTARY ENCODER

Abstract

In a method for determining the rotor position of a three-phase machine without using a rotary encoder, and to a device for controlling a three-phase motor without using a rotary encoder, the three-phase machine is fed by a converter that can be operated by pulse-width modulation, and the converter has model variables for the rotor angle and the current indicator of the three-phase machine, and the converter has device(s) by using which, in control operation, at least two values are measured which represent a measure of the local inductances of the machine which represent a measure of the local inductances of the machine, the error of the model rotor angle is determined in that, depending on the model rotor angle and the model current indicator, at least two weighting factors are determined, and in that a weighted sum is formed from the at least two measured values and the at least two weighting factors, and in that a further offset value is substracted from the sum, which is likewise determined on the basis of the model rotor angle and the model current indicator.

Description

FIELD OF THE INVENTION

The present invention relates to a method for identifying the rotor position of an electrical three-phase machine having a rotor and a stator, the three-phase machine being driven by pulsed clamping voltages in accordance with the pulse width modulation method.

The present invention also relates to a device for controlling a three-phase machine in open and/or closed loop, a controller being adapted and designed for implementing the described method.

Additionally, the present invention relates to a three-phase machine having a stator, a rotor, and a device for the open and/or closed-loop control thereof. In general, the present invention relates to encoderless control of a three-phase machine in open and/or closed-loop, the rotor position or the rotor angle being derived from the rotor position dependency of the differential, respectively local inductances.

Evaluating the identified local inductances in accordance with example embodiments of the present invention with regard to the rotor position optimally eliminates the stability problem of certain conventional methods. The subject matter hereof is not determining local inductances. For this, reference is made to conventional methods that are suited for continuously determining local inductances during operation of the three-phase machine using suitable injection voltages. Due to the increased use of three-phase motors instead of direct-current motors, there is considerable interest in high-quality closed-loop control systems for three-phase motors. With the aid of rotor position encoders, such as rotary pulse encoders or resolvers, dynamic and efficient closed-loop control systems of three-phase machines can be obtained in conjunction with pulse-controlled inverters. Disadvantageous in this context is that using rotary position encoders entails a rise in costs and in cabling outlay, and makes failure more likely.

BACKGROUND INFORMATION

The rotor position is determined during operation by what are generally referred to as encoderless, rotary encoderless or sensorless methods. The rotor position is determined continuously on the basis of the applied voltages and measured motor currents. A component of the fundamental wave methods is the integration of the voltages induced by the rotation of the rotor. However, it is disadvantageous that these methods fail due to vanishing voltages at low rotational speeds. Injection methods utilize the rotor position-dependent inductances of the machine by evaluating the rotor position-dependent current response to a high-frequency voltage excitation, for example. Generally, the high-frequency voltage excitation is additively superimposed on the fundamental voltage indicator.

The disadvantage associated with conventional injection methods is that they do not use the full information content of the rotor position-dependent local inductance matrix, as only the anisotropic component or even only the direction of the anisotropic component of the entire local inductance matrix is used, for example. Moreover, conventional methods make simplified assumptions about the anisotropy. This easily leads to unstable behavior, as soon as the machine exhibits more complicated anisotropic properties that deviate from the assumption.

The publication, Operating Point Dependent Anisotropies and Assessment for Position-Sensorless Control, European Conference on Power Electronics and Applications, Karlsruhe, Sep. 5-9, 2016 by W. Hammel et. al. indicates that the parameters of the local inductance matrix not only depend on the rotor position and the instantaneous torque, but, in particular are also directly influenced by the direction of the fundamental current indicator. For conventional injection-based, rotary encoderless, closed-loop control methods, which are based on simplified assumptions, the result is the condition they formulate for a stable operation with respect to the properties of the anisotropy used for the motors to be operated. If conventional methods are used for motors that do not fulfill this condition, this leads to an unstable operation.

Conventional injection methods can be differentiated by the type of injection. For example, in certain injection methods, an alternating one-dimensional injection voltage is additively superimposed on the fundamental voltage indicator. A simple evaluation based thereon assumes that, in the case of a permanently excited synchronous machine, the orientation of the anisotropy coincides with the direction of the d-axis of the rotor. The alternating injection voltage is selected in parallel to the assumed model d-axis. A correct orientation results in the injection-induced a.c. components in parallel to the injection voltage, and thus the injection is torque-free even at high injection amplitudes. On the other hand, if the assumed model d-axis deviates from the actual d-axis, injection-induced a.c. components result that have an additional component orthogonally to the direction of the injection voltage. As a function of this orthogonal current component, the model angle can be adjusted using the correct preceding sign. Thus, an especially simple manner for adjusting the model angle can be attained as long as an anisotropy having the assumed properties is present. In the case of real machines, however, the anisotropy also depends on the magnitude and direction of the fundamental current indicator and leads to the stability problems mentioned.

Among conventional injection methods, there are those which, per evaluation interval, superimpose injection voltages in different directions on the fundamental voltage indicator.

German Patent Document No. 10 2015 217 986, for example, describes an injection method where the trajectory of the injection voltage indicator tip forms a square. On the basis thereof, a calculation rule, which entails very little computational outlay, is presented to determine the anisotropy as a two-component variable. However, even the method it presents does not resolve the difficulty of possible instability caused by the dependency of the anisotropy on fundamental current, as described by W. Hammel et al. in the publication Operating Point Dependent Anisotropies and Assessment for Position-Sensorless Control, European Conference on Power Electronics and Applications, Karlsruhe, Sep. 5-9, 2016. However, in contrast to an injection voltage having an alternating voltage indicator, it is possible to determine the complete differential inductance matrix using this injection scheme.

SUMMARY

Example embodiments of the present invention an improved method for identifying the rotor position of an electrical three-phase machine that permits a rotor-position identification that is stable and noise-immune in all operating points, for three-phase machines having any type of properties of the entire local inductance matrix.

Example embodiment of the present invention also relate to a corresponding device for controlling a three-phase machine in closed or open loop.

Example embodiment of the present invention are based on the realization that rotor positions may only be optimally identified when all rotor position-dependent parameters of the entire local inductance matrix are used in accordance with the manner described herein. To achieve a stable operation, the dependency of the parameters of the local inductance matrix on the orientation of the fundamental current indicator in the closed-loop control system is utilized along the lines described herein.

Example embodiment of the present invention presuppose that the complete differential inductance matrix is continuously determined by a preceding method. For example, the injection method described in the German Patent Document No. 10 2015 217 986, which is expressly incorporated herein in its entirety by reference thereto, may be used.

In a method for rotary encoderless determination of the rotor position of a three-phase machine, the three-phase machine is fed by a converter is operable with pulse width modulation, a model rotor angle and a model current indicator of the three-phase machine is determined, in closed-loop controlled operation, in particular, a first measured value of a measure of a first local inductance of the machine is determined, in closed-loop controlled operation, in particular, a second measured value of a measure of a second local inductance of the machine is determined, a function, in particular a function table that is especially determined offline, of differentials of the measures assigns values of the model rotor angle and of the model current indicator to function values, an error, in particular angle deviation, of the model rotor angle is determined by at least two weighting factors being determined by at least two weighting factors being determined as function values of the function, in particular function table, as a function of the model rotor angle and of the model current indicator, and a sum of the measured values weighted by the weighting factors is produced, and, to determine the error, another offset value is subtracted from the sum, which is likewise determined as a function of the model rotor angle and the model current indicator, the further offset value is determined by the further offset value is determined as a function value of the function, in particular function table as a function of the model rotor angle and of the model current indicator by the function, in particular the function table, the model rotor angle is adjusted by a control loop controlling the error toward zero.

According to example embodiments the local admittances may be used as a measure of the local inductances.

According to example embodiments, the function may be determined, in particular set offline, in particular one time in a step preceding the positional determination, thus, in particular prior to the closed-loop controlled operation, so that the weighting factors and the offset value are assigned by the function to the values of the two model variables online, in particular when the position is determined.

According to example embodiments, to determine the function, the local inductances are determined as a function of values of the rotor position and of the current indicator, in particular, these values of the current indicator representing a trajectory.

According to example embodiments, the weighting factors and the offset value are assigned to the model variables as a function of the differential of the local inductances or local admittances that is specific to the rotor position.

According to example embodiments, each of the at least two weighting factors is produced as a quotient of the differential of one of the measures and of the square sum of all of the differentials of the measures.

According to example embodiments, the assignment for the offset value to be subtracted is set to conform there to this weighted sum when the actual rotor angle of the machine conforms to the model angle.

According to example embodiments, the weighting factors are selected in such a way that that measure which has the greatest manufacturing tolerances is provided with a lower weight or is not considered in the weighted sum.

In the case of the device that includes a converter and a three-phase motor, in particular a rotary encoderless three-phase motor, the three-phase motor is fed by a converter, in particular a pulse-controlled inverter, which is suitably designed for implementing a method described herein.

Example embodiments of the present invention are explained in greater detail below with reference to the appended Figures.

BRIEF DECRIPTION OF THE DRAWINGS

FIG. 1 illustrates the correlation in terms of signal engineering between the model variables known to the converter, the actual rotor position unknown to the converter, and the measurable admittance parameters derived as a function of these variables.

FIG. 2 is a signal flow diagram of an exemplary embodiment of the method.

DETAILED DESCRIPTION

The differential inductance matrix describes the relationship between current variations and the corresponding injection voltage u_c. This matrix is symmetrical and, therefore, includes three independent parameters.

$\begin{array}{cc}{u}_c=\left(\begin{array}{cc}{L}_a& L_{\mathrm{ab}}\\ L_{\mathrm{ab}}& L_b\end{array}\right)·\frac{d}{\mathrm{dt}}{i}_c& \left(1\right)\end{array}$

Conversely, the current rise in response to an applied injection voltage u_c is determined by the inverse matrix.

$\begin{array}{cc}\frac{d}{\mathrm{dt}}{i}_c={\left(\begin{array}{cc}{L}_a& L_{\mathrm{ab}}\\ L_{\mathrm{ab}}& L_b\end{array}\right)}^{-1}·u_c& \left(2\right)\end{array}$

Inverse Y of inductance matrix L is often referred to as the admittance matrix here as well in the following. This is likewise symmetrical and determined by the three parameters Y_a, Y_b, and Y_ab).

$\begin{array}{cc}Y=L^{-1}={\left(\begin{array}{cc}{L}_a& L_{\mathrm{ab}}\\ L_{\mathrm{ab}}& L_b\end{array}\right)}^{-1}=\left(\begin{array}{cc}{Y}_a& Y_{\mathrm{ab}}\\ Y_{\mathrm{ab}}& Y_b\end{array}\right)& \left(3\right)\end{array}$

Thus, the relationship between the applied injection voltage u, and the corresponding current rise is expressed as follows:

$\begin{array}{cc}\frac{d}{\mathrm{dt}}{i}_c=\left(\begin{array}{cc}{Y}_a& Y_{\mathrm{ab}}\\ Y_{\mathrm{ab}}& Y_b\end{array}\right)·u_c=Y·u_c& \left(4\right)\end{array}$

Using the substitutions (5a)-(5c), the admittance matrix may be reduced as illustrated in (6).

$\begin{array}{cc}{Y}_{\sum }=\frac{Y_a+Y_b}{2}& \left(5a\right)\\ Y_{\Delta a}=\frac{Y_a-Y_b}{2}& \left(5b\right)\\ Y_{\Delta b}=Y_{\mathrm{ab}}& \left(5c\right)\\ Y=\left(\begin{array}{cc}{Y}_a& Y_{\mathrm{ab}}\\ Y_{\mathrm{ab}}& Y_b\end{array}\right)=Y_{\sum }·\left(\begin{array}{cc}1& 0\\ 0& 1\end{array}\right)+Y_{\Delta a}·\left(\begin{array}{cc}1& 0\\ 0& -1\end{array}\right)+Y_{\Delta b}·\left(\begin{array}{cc}0& 1\\ 1& 0\end{array}\right)& \left(6\right)\end{array}$

In this reduction, Y_Σ represents the isotropic component of the admittance matrix. On the other hand, the anisotropic component is a variable having magnitude and direction that is represented in (6) by Cartesian components Y_Δa, and y_Δb thereof.

The exemplary embodiment may apply to a permanently excited synchronous machine. For such a machine, the local inductance matrix, respectively the local admittance matrix may be determined in the reduction thereof in accordance with (6) with the aid of a square injection, for example. In German Patent Document No. 10 2015 217 986, isotropic component Y_Σ may be ascertained from the first component of equation (31) as follows:

$\begin{array}{cc}{Y}_{\sum }=\frac{{\Delta i}_{\sum x}}{u_c·\Delta t}=\frac{1}{4·u_c·\Delta t}·\left({\Delta i}_{u\mathrm{\alpha 0}}+{\Delta i}_{u\mathrm{\beta 1}}-{\Delta i}_{u\mathrm{\alpha 2}}-{\Delta i}_{u\mathrm{\beta 3}}\right)& \left(7\right)\end{array}$

This may be simplified to (8), whereby isotropic component Y_Σ may be determined directly from the measured current rises.

$\begin{array}{cc}{Y}_{\sum }=\frac{1}{4·u_c·\Delta t}·\left({\Delta i}_{\mathrm{\alpha 0}}+{\Delta i}_{\mathrm{\beta 1}}-{\Delta i}_{\mathrm{\alpha 2}}-{\Delta i}_{\mathrm{\beta 3}}\right)& \left(8\right)\end{array}$

Apart from measurement errors, second component Δi_Σy of equation (31) in the German Patent Document No.10 2015 217 986 is zero.

The anisotropic components Y_Δa, and K_Δb are derived from the components of indicator equation (43) in German Patent Document No. 10 2015 217 986 as follows:

$\begin{array}{cc}{Y}_{\Delta a}=\frac{1}{4·u_c·\Delta t}·\left({\Delta i}_{\mathrm{\alpha 0}}-{\Delta i}_{\mathrm{\beta 1}}-{\Delta i}_{\mathrm{\alpha 2}}+{\Delta i}_{\mathrm{\beta 3}}\right)& \left(9\right)\\ Y_{\Delta b}=\frac{1}{4·u_c·\Delta t}·\left({\Delta i}_{\mathrm{\alpha 0}}+{\Delta i}_{\mathrm{\beta 1}}-{\Delta i}_{\mathrm{\alpha 2}}-{\Delta i}_{\mathrm{\beta 3}}\right)& \left(10\right)\end{array}$

Admittance components Y_Σ, Y_Δa and Y_Δb may also be determined using other characteristics of the injection voltage, such as of a rotating injection, for example, as described, for example, in the publication A Comparative Analysis of Pulsating vs. Rotating Indicator Carrier Signal Injection-Based Sensorless Control, Applied Power Electronics Conference and Exposition, Austin, Feb. 24-28, 2008, pp. 879-885 by D. Raca et. al.

The method according to an example embodiment of the present invention for rotor position identification is based on determining the three parameters of the admittance matrix. The implementation of the method is not bound to the selected form, respectively reduction in (6). Rather, any other form of representation of the information contained in the admittance matrix may be used as the basis for this.

In particular, to implement the method, it is possible to acquire any three linear combinations from admittance components Y_a, Y_b, and Y_ab, respectively Y_Σ, Y_Δa, and Y_Δb to the extent that they are mutually linearly independent.

A component hereof is appropriately utilizing the realization that the three parameters Y_Σ, Y_Δa, and Y_Δb of the local admittance matrix depend not only on rotor position θ_r but, as a function of the operating points, also on components i_d and i_q of the instantaneous fundamental current indicator, thus they are influenced by the magnitude and direction thereof.

Y _Σ =Y _Σ(θ_r,i_d,i_q)   (11)

Y _Δn =hd Δa(θ_r,i_d,i_q)   (12)

Y _Δb = _Δb(θ_r,i_d,i_q)   (13)

θ_r representing the electric angle of the rotor position and i_d respectively i_q the components of the fundamental current indicator.

The following considerations are limited to the base speed range. Here, the machine is typically operated using a torque-generating current on the q-axis, i.e., i_d=0 or along an MTPA (maximum torque per ampere) trajectory, which indicates a fixed association of the d-current as a function of the q-current. This is described by D. Schröder, for example, in Elektrische Antriebe—Regelung von Antriebssysteme [Electrical Drives—Closed-Loop Control of Drive Systems] 3rd edition, Berlin, Springer 2009. Thus the machine is operated in accordance with (14) or (15).

i _d=0   (14)

respectively

i _d =i _d,MTPA(i_q)   (15)

In selecting the operating points, the converter is hereby limited to two remaining degrees of freedom, namely to electric rotor angle θ_r and q-current i_q, while associated d-current i_d results from the q-current from a fixed association in accordance with (14) or (15), for example. For operating points in accordance with this selection, the dependency of admittance parameters Y_Σ, Y_Δa and Y_Δb is also reduced to just two independent variables θ_r and i_q:

Y _Σ =Y _Σ(θ_r, i_d(i_q),i_q)=Y_Σ(θ_r,i_q)   (16)

Y _Δa =Y _Δa(θ_r,i_d(i_q),i_q)=Y_Δa(θ_r,i_q)   (17)

Y _Δb =Y _Δb(θ_r,i_d(i_q),i_q)=Y_Δb(θ_r,i_q)   (18)

In the case of rotary encoderless operation of the motor on a converter, deviations also inevitably arise between actual electric rotor angle θ_r and corresponding model rotor angle θ_r,mod in the converter. However, even when these ideally turn out to be very small, unstable operation may result in conventional rotary encoderless methods, as described by W. Hammel et. al. in Operating Point Dependent Anisotropies and Assessment for Position-Sensorless Control, European Conference on Power Electronics and Applications, Karlsruhe, Sep. 5-9, 2016.

To orient the fundamental current indicator to be applied, the converter will only be able to revert to model rotor angle θ_r,mod. If this does not conform to actual electric rotor angle θ_r, the result is that the actual d- and q-current components no longer conform with the corresponding model variables. The d- and q-current components i_d and i_q actually flowing in the motor are dependent at this stage on the model variables in converter i_d,mod and i_q,mod as well as on the error of rotor angle model {tilde over (θ)}_r, as follows:

i _d =i _d,mod·cos({tilde over (θ)}_r)−i_q,mod·sin({tilde over (θ)}_r)   (19)

i _q =i _q,mod·cos({tilde over (θ)}_r)+i_d,mod·sin({tilde over (θ)}_r)   (20)

{tilde over (θ)}_r=θ_r,mod−θ_r   (21)

If there is an error of model rotor angle {tilde over (θ)}_r, the assignment according to (14), respectively (15) between the actual q- and d-current components does not take place, rather model d-current i_d,mod is generated as a function of the model q-current i_q,mod:

i _d,mod=0   (22)

respectively

i _d,mod =i _d,MTPA(i_q,mod)   (23)

Since, in accordance with (11)-(13), the admittance parameters are dependent on actual d- and q-currents i_d and i_q, in comparison to (16)-(18), they will have an additional dependency on the error of model rotor angle {tilde over (θ)}_r respectively on model rotor angle θ_r,mod:

Y _Σ =Y _Σ(θ_r,i_q,mod,{tilde over (θ)}_r)   (24)

Y _Δa =Y _Δa(θ_r,i_q,mod,{tilde over (θ)}_r)   (25)

Y _Δb =Y _Δb(θ_r,i_q,mod,{tilde over (θ)}_r)   (26)

respectively

Y _Σ =Y _Σ(θ_r,i_q,mod,θ_r,mod)   (27)

Y _Δa =Y _Δa(θ_r,i_q,mod,θ_r,mod)   (28)

Y _Δb =Y _Δb(θ_r,i_q,mod,θ_r,mod)   (29)

Thus, measurable admittance parameters Y_Σ, Y_Δa and Y_Δb are dependent on the two model variables i_q,mod and θ_r,mod known in the converter as well as on a further variable, namely actual rotor angle θ_r unknown in the converter.

FIG. 1 shows the internal interaction of the relevant equations, which collectively lead to dependencies (27)-(29). The numbers of the equations, which represent the respective relationships, are indicated in parentheses here.

Model d-current i_d,mod is generated from model q-current i_q,mod in accordance with selected MTPA characteristic 103 as expressed by equations (22) respectively (23). Actual motor current components i_d and i_q are derived from model current components i_d,mod and i_q,mod by the transformation of model rotor coordinates into actual rotor coordinates 102 in accordance with equations (19) and (20) using phase angle error {tilde over (θ)}_r. In accordance with (21), the error of model rotor angle {tilde over (θ)}_r is the difference between model rotor angle θ_r,mod and actual rotor angle θ_r. Finally, within the three-phase machine, measurable admittance parameters Y_Σ, Y_Δa and Y_Δb are generated as a function of actual current components i_d and i_q as well as of actual rotor position θ_r in accordance with equations (11)-(13).

Overall, this results in a mapping 100 of the model variable of q-current i_q,mod and of model rotor angle θ_r,mod as well as of actual rotor angle θ_r onto measurable admittance parameters Y_Σ, Y_Δa, and Y_Δb in accordance with equations (27)-(29).

What is decisive is the realization that an error of the model rotor angle does, in fact, influence the admittance parameters, but they may nevertheless be measured, unaltered, using an injection process.

Based on this realization, it is fundamentally possible to use the measured admittance parameters to identify the rotor position. This would be very simple to realize if one of the relationships (27)-(29) could be uniquely solved for rotor angle 74_r in a reversible process. Generally, however, this is not the case for any of the three variables.

In any case, however, it is necessary to know the dependencies of the admittance parameters on the operating point in accordance with (11)-(13). These may be ascertained, for example, by a preceding offline measurement, it being possible for measurement devices to also be used to determine the rotor position. However, there is no need for this to be determined over the entire d-q current plane to realize the method hereof. If the machine is operated on a current trajectory in accordance with (22), respectively (23), and it is also assumed that the phase angle errors occurring during operation remain small, it suffices to determine the admittance parameters on the current trajectory and in the vicinity thereof.

In accordance with example embodiments of the present invention, the stability problem described by W. Hammel et al. in Operating Point Dependent Anisotropies and Assessment for Position-Sensorless Control, European Conference on Power Electronics and Applications, Karlsruhe, Sep. 5-9, 2016 is overcome by a converter internal error signal δ_F initially being generated from variables θ_r,mod and i_q,mod , and which are available to the converter, as well as from measured admittance parameters Y_Σ, Y_Δa, and Y_Δb, whereby this error signal itself again depends only on model q-current i_q,mod and model rotor angle θ_r,mod as well as on unknown rotor angle θ_r:

δ_F=δ_F(θ_r,i_q,mod,θ_r,mod)   (30)

In accordance with example embodiments of the present invention, this signal is generated to represent a measure of the deviation of model rotor angle θ_r,mod from actual rotor angle θ_r, and this signal is fed to a controller which adjusts model angle θ_r,mod to the actual rotor angle. This may be accomplished by a simple PLL control loop, for example. Alternatively, error signal δ_F may be used as a correction intervention in a fundamental wave model, which may thereby also be used in the low speed range and at standstill.

In accordance with example embodiments of the present invention, error signal δ_F is generated in accordance with FIG. 2 by a composite signal F which is a weighted sum of the three measured admittance parameters:

F=G _Σ ·Y _Σ +G _Δa ·Y _Δa +G _Δb ·Y _Δb   (31)

A quantity F₀ is subtracted from this composite signal F, resulting in error signal δ_r:

δ_F=F−F₀   (32)

Weights G_Σ, G_Δa and G_Δb as well as quantity F₀ are typically not constants, but rather operating point-dependent values. Significant thereby is that there is no need to use actual operating point θ_r, i_d and i_q to determine these quantities. Rather, the use of the possibly faulty model operating point θ_r,mod and i_q,mod leads nevertheless in the result to a stable operation and, in fact, even in the case of a non-vanishing phase angle error.

Thus, variables G_Σ, G_Δa, G_Δb and F₀ are general functions of the model variables:

G _Σ =G _Σ(i_q,mod,θ_r,mod)   (33)

G _Δa =G _Δa(i_q,mod,θ_r,mod)   (34)

G _Δb =G _Δb(i_q,mod,θ_r,mod)   (35)

F ₀ =F ₀(i_q,mod,θ_r,mod)   (36)

As a function of the form of these functions G_Σ, G_Δa, G_Δb and F₀, a tabular or functional mapping or a combination of both is practical for the storing or calculation thereof in the converter. The following assumes a tabularly stored dependency of values G_Σ, G_Δa, G_Δb and F₀ on the model operating point.

Thus it follows for error signal δ_F, which is dependent on model variables i_q,mod and θ_r,mod as well as on actual rotor angle θ_r, that:

δ_F=δ_F(θ_r,i_q,mod,θ_r,mod)   (37)

It is possible to form functions G_Σ, G_Δa, G_Δb and F₀ , and, in fact, solely in dependence upon the model variables such that error signal δ_F acquires the following properties

$\begin{array}{cc}\frac{\partial }{\partial {\theta }_r}{\delta }_F\left({\theta }_r,i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right){|}_{{\theta }_{r,\mathrm{mod}}={\theta }_r}=1& \left(38\right)\\ \frac{\partial }{\partial {\theta }_{r,\mathrm{mod}}}{\delta }_F\left({\theta }_r,i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right){|}_{{\theta }_{r,\mathrm{mod}}={\theta }_r}=-1& \left(39\right)\\ {\delta }_F\left({\theta }_r,i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right){|}_{{\theta }_{r,\mathrm{mod}}={\theta }_r}=0& \left(40\right)\end{array}$

and this permits a stable operation because of the properties mentioned.

Thus, in accordance with equation (38), the required property indicates how error signal δ_F is to respond to a change in actual rotor angle θ_r namely with a slope 1 in response to a change in actual rotor angle θ_r proceeding from corrected operating point θ_r,mod=θ_r in the case of set model angle θ_r,mod.

Additionally, the required property in accordance with equation (39) indicates how error signal δ_F is to respond to a change in model angle θ_r,mod, proceeding from adjusted operating point θ_r,mod=θ_r in the case of set actual rotor angle θ_r namely with a slope −1 in response to a change in model angle θ_r,mod.

Consequently, in the vicinity of corrected operating point θ_r,modθ_r error signal δ_F is proportional to phase angle error {tilde over (θ)}_r=θ_r,mod−θ_r and is thus suited for adjusting the model angle to the actual motor angle with the aid of a closed-loop control circuit.

Moreover, from required properties (38) and (39) of error signal δ_F, it follows that the value of error signal δ_F is constant, for example, as selected in (40), constantly zero for all corrected operating points θ_q,mod=θ_r independently of rotor position θ_r and model q-current i_q.

In another step, G_Σ, G_Δa, G_Δb and F₀ are formulated at this stage as a function of model variables i_q,mod and θ_r,mod provide error signal δ_F in accordance with (31) and (32) with the required properties according to (38)-(40).

This is accomplished by executing G_Σ, G_Δa, G_Δb and F₀ as follows:

$\begin{array}{cc}{G}_{\sum }\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)=\frac{D_{\sum }\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)}{D_{\sum }^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+D_{\Delta a}^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+D_{\Delta b}^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)}& \left(41\right)\\ G_{\Delta a}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)=\frac{D_{\Delta a}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)}{D_{\sum }^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+D_{\Delta a}^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+D_{\Delta b}^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)}& \left(42\right)\\ G_{\Delta b}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)=\frac{D_{\Delta b}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)}{D_{\sum }^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+D_{\Delta a}^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+D_{\Delta b}^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)}& \left(43\right)\\ F_0\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)=\frac{\begin{array}{c}{D}_{\sum }\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)·Y_{\sum }\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+\\ D_{\Delta a}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)·Y_{\Delta a}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+\\ D_{\Delta b}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)·Y_{\Delta b}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)\end{array}}{D_{\sum }^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+D_{\Delta a}^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)+D_{\Delta b}^2\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)}& \left(44\right)\end{array}$

D_Σ, D_Δa, and D_Δb thereby represent the differentials of local admittance parameters Y_Σ, Y_Δa and Y_Δb in accordance with rotor position θ_r. If the dependencies of local admittance parameters according to (27)-(29) are determined in the above described manner, then differentials D_Σ, D_Δa and D_Δb thereof in accordance with rotor position θ_r may also be indicated for the corrected operating point:

$\begin{array}{cc}{D}_{\sum }\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)=\frac{\partial }{\partial {\theta }_r}{Y}_{\sum }\left({\theta }_r,i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right){|}_{{\theta }_r={\theta }_{r,\mathrm{mod}}}& \left(45\right)\\ D_{\Delta a}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)=\frac{\partial }{\partial {\theta }_r}{Y}_{\Delta \alpha }\left({\theta }_r,i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right){|}_{{\theta }_r={\theta }_{r,\mathrm{mod}}}& \left(46\right)\\ D_{\Delta b}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)=\frac{\partial }{\partial {\theta }_r}{Y}_{\Delta b}\left({\theta }_r,i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right){|}_{{\theta }_r={\theta }_{r,\mathrm{mod}}}& \left(47\right)\end{array}$

If the alternative representation according to (24)-(26) is used for the description of the admittance parameters, thus as a function of actual rotor angle θ_r, of model q-current i_q,mod and of error angle {tilde over (θ)}_r, the relevant differentials present themselves as follows:

$\begin{array}{cc}{D}_{\sum }\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)={\left[\frac{\partial }{\partial {\theta }_r}{Y}_{\sum }\left({\theta }_r,i_{q,\mathrm{mod}},{\tilde{\theta }}_r\right)-\frac{\partial }{\partial {\tilde{\theta }}_r}{Y}_{\sum }\left({\theta }_r,i_{q,\mathrm{mod}},{\tilde{\theta }}_r\right)\right]}_{{\theta }_r={\theta }_{r,\mathrm{mod}},{\tilde{\theta }}_r=0}& \left(48\right)\\ D_{\Delta a}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)={\left[\frac{\partial }{\partial {\theta }_r}{Y}_{\Delta a}\left({\theta }_r,i_{q,\mathrm{mod}},{\tilde{\theta }}_r\right)-\frac{\partial }{\partial {\tilde{\theta }}_r}{Y}_{\Delta a}\left({\theta }_r,i_{q,\mathrm{mod}},{\tilde{\theta }}_r\right)\right]}_{{\theta }_r={\theta }_{r,\mathrm{mod}},{\tilde{\theta }}_r=0}& \left(49\right)\\ D_{\Delta b}\left(i_{q,\mathrm{mod}},{\theta }_{r,\mathrm{mod}}\right)={\left[\frac{\partial }{\partial {\theta }_r}{Y}_{\Delta b}\left({\theta }_r,i_{q,\mathrm{mod}},{\tilde{\theta }}_r\right)-\frac{\partial }{\partial {\tilde{\theta }}_r}{Y}_{\Delta b}\left({\theta }_r,i_{q,\mathrm{mod}},{\tilde{\theta }}_r\right)\right]}_{{\theta }_r={\theta }_{r,\mathrm{mod}},{\tilde{\theta }}_r=0}& \left(50\right)\end{array}$

The setting of values G_Σ, G_Δa, G_Δb and F₀ selected in accordance with (41)-(44) in conjunction with (45)-(47) or with (48)-(50) not only fulfills conditions (38)-(40) for the error signal, but also yields the best possible signal-to-noise ratio for error signal δ_F, assuming that the measured values of the admittance parameters Y_Σ, Y_Δa and Y_Δb generate noise in an uncorrelated and normally distributed manner and with the same standard deviation.

Example embodiments of the present invention also include settings that deviate herefrom. Thus, for example, there may be a deviation from the above setting in the following variants:

• • 1. A setting of G_Σ, G_Δa, G_Δb and F₀ that is not optimal for the signal-to-noise ratio, so that properties (38)-(40) are nevertheless fulfilled for error signal δ_F.
  • 2. A setting, so that error signal δ_F becomes noise-optimal for different noise characteristics of the measured admittance parameters. The measured admittance parameters may, for example, generate noise with different standard deviations, or the individual admittance parameters generate noise not in an uncorrelated, but in a mutually correlated manner, or the admittance parameters generate noise in accordance with a distribution that differs from the normal distribution. Under these conditions as well, the dependency of values G_Σ, G_Δa, G_Δb and F₀ on the model variables for which error signal δ_F has an optimal signal-to-noise ratio, is set in each case.
  • 3. A setting so that the derivatives in (38)-(39) are not constantly +/−1, but deviate therefrom or even vary as a function of the operating point. In this case, an operating point-dependent control loop gain and thus an operating point-dependent transiet response results for the control loop which adjusts the modeled rotor position.
  • 4. A setting in accordance with which an individual weight, for example, G_Σ is selected to be lower in terms of absolute value or even down to zero. This would be beneficial, for example, if the associated admittance parameter has significant manufacturing tolerances, and different specimen from an ensemble of same motors are to be operated using one single set of parameters. The individual specimen of the ensemble thereby differ with respect to the respective admittance parameter on the basis of manufacturing tolerances.
  • 5. A setting of values G_Σ, G_Δa, G_Δb and F₀ as a function of three model variables instead of the two model variables described here, for example, as a function of the model rotor angle and both model current components. This would be advantageous if the machine were to be operated not only along a fixed current trajectory, but in a larger range of the d-q current plane or in the entire d-q current plane, as is used, for example, in the field weakening range.

In summary, the following steps are to be implemented to execute the method. The following steps are first performed in a preceding offline process:

• • 1. Determination of the operation point dependency of local admittance parameters Y_Σ, Y_Δa and Y_Δb along the set current trajectory and in the vicinity thereof. This may be done offline for a single specimen of a motor type on a test stand having a rotor position measuring device.
  • 2. Determining the differentials of admittance parameters measured offline in accordance with the rotor position.
  • 3. Setting of the table contents for weighting factors G_Σ, G_Δa and G_Δb as well as of term F₀ for all operating points.

The subsequent rotary encoderless determination of the rotor position includes the following steps in online operation, as shown in FIG. 2:

• • 1. Measuring local admittance parameters Y_Σ, Y_Δa and Y_Δb using a suitable high frequency injection voltage.
  • 2. Determining the current values for weighting factors G_Σ, G_Δa and G_Δb by accessing the previously set tables as a function of instantaneous model variables i_q,mod and θ_r,mod.
  • 3. Generating a weighted sum of the measured admittance parameters using the current weighting factors.
  • 4. Determining the current value for term F₀ to be subtracted as a function of the instantaneous model variables.
  • 5. Generating error signal δ_F by subtracting term F₀ from the weighted sum.
  • 6. Feeding error signal δ_F to a control circuit or a fundamental wave machine model.
  • 7. Adjusting model rotor angle θ_r,mod by controlling error signal δ_F toward zero.
  • 8. Cyclically repeating online steps 1-7.

For the described exemplary embodiment, FIG. 2 depicts the signal flow diagram for controlling a rotary encoderless three-phase machine 111 using the method hereof. Three-phase machine 111 is fed by power output stage 109 of an inverter. The currents flowing to the three-phase machine are measured by a two-phase or three-phase current acquisition 110.

Corresponding setpoint d-current i_d,soll is determined as a function of setpoint q-current which is dependent on the desired torque, in accordance with (14) or (15), via MTPA characteristic curve 103, and the setpoint current indicator derived therefrom is fed in model rotor coordinates i_soll^r to setpoint-actual comparison 104. The actual current indicator in model rotor coordinates i_mod^r is formed by inverse transformation 107 from the actual current indicator in stator coordinates i^s using model rotor angle θ_r,mod.

Current controller 105 generates the fundamental wave voltage in model rotor coordinates u_f^r and thus adjusts actual current indicator i_mod^r to setpoint current indicator i_soll^r. Transformation device 106 transforms the fundamental wave voltage from model rotor coordinates into stator coordinates, for which purpose, model rotor angle θ_r,mod is used, in turn.

Injection voltage u_c^s is additively superimposed in stator coordinates u_f^s on fundamental voltage indicator by summation 108, whereby the entire motor voltage is generated in stator coordinates u_m^s which is [(sic.) are] amplified by power output stage 109 and fed to machine 111. The injection voltage may also be alternatively added already before transformation 106 into model rotor coordinates.

The currents flowing in the machine are measured by current acquisition 110. Determined herefrom in separation unit 112 are both the fundamental wave current in stator coordinates i^s as well as, from the high-frequency current components, admittance parameters Y_Σ, Y_Δa and Y_Δb.

Weights G_Σ, G_Δa and G_Δb used for generating weighted sum F are formed via tables, respectively functional mappings 113-115 as a function of model rotor position θ_r,mod and of model q-current i_q,mod.

Weights G_Σ, G_Δa and G_Δb used for generating weighted sum F are formed via tables, respectively functional mappings 113-115 as a function of model rotor position θ_r,mod and of model q-current i_q,mod.

Finally, offset F₀, which is likewise formed as a function of model rotor position θ_r,mod and of model q-current i_q,mod in the table, respectively functional mapping 116 is subtracted from generated weighted sum F. Error signal δ_F is ultimately hereby formed and is fed in the present exemplary embodiment to a PLL controller 119. This is usually composed of the series connection of a PI element 117 and of an I-element 118. The PLL controller adjusts model rotor angle θ_r,mod formed at the output thereof to actual rotor angle θ_r so that, in the corrected state, it ultimately agrees with the actual rotor angle, and error signal δ_F then becomes zero. Additionally available at the output of PI element 117 is a model value of electric angular velocity ω_mod which may be used, for example, as the actual value for a superimposed speed control loop.

LIST OF REFERENCE NUMERALS

100 generation of the admittance parameters as a function of the model variables and the actual rotor position

101 generation of the admittance parameters as a function of the actual motor sizes

102 transformation of model rotor coordinates into actual rotor coordinates

103 MTPA characteristic (maximum torque per ampere)

104 setpoint-actual comparison of the current control circuit

105 current controller

106 transformation of model rotor coordinates into stator coordinates

107 inverse transformation of stator coordinates into model rotor coordinates

108 additive application of the injection voltage

109 power output stage

110 current measurement

111 three-phase machine

112 means for determining the admittance parameters and the fundamental wave current

113 producing the weight factor for the isotropic admittance component

114 producing the weight factor for the anisotropic a-admittance component

115 producing the weight factor for the anisotropic b-admittance component

116 producing the offset to be subtracted

117 PI controller of the PLL controller for forming the model speed

118 I-controller of the PLL controller for forming the model rotor angle

119 PLL controller (phase-locked loop)

LIST OF SYMBOLS

D_Δa differential of the anisotropic admittance a-component in accordance with the rotor position

D_Δb differential of anisotropic admittance b-component in accordance with the rotor position

D_Σ differential of the isotropic admittance component in accordance with the rotor position

F weighted sum of the measured admittance components

F₀ offset to be subtracted

G_Δa weighting factor for the a-component of the anisotropic admittance component

G_Δb weighting factor for the b-component of the anisotropic admittance component

G_Σ weighting factor for the isotropic admittance component carrier current indicator

i_d, i_q actual fundamental wave current components in rotor coordinates

i_d,mod, i_q,mod actual fundamental wave current components in model rotor coordinates

i_mod^r actual fundamental wave current indicator in model rotor coordinates

i^s actual fundamental wave current indicator in stator coordinates

i_d,soll,i_q,soll setpoint current components of the fundamental wave current

i_soll^r setpoint current indicator of the fundamental wave current in model rotor coordinates

Δi_αn, Δi_βn components of the current rises in stator coordinates

Δi_uαn, Δi_uβn components of current rises in voltage coordinates

Δ_Σx,y current rises due to the isotropic admittance component

L inductance matrix in stator coordinates

L_a a-component of the inductance matrix in stator coordinates

L_b b-component of the inductance matrix in stator coordinates

L_ab coupling inductance in stator coordinates

Δt time interval

u_c amplitude of the injection voltage

u_c injection voltage indicator

u_c^s injection voltage indicator in stator coordinates

u_f^r fundamental wave current indicator in model rotor coordinates

u_f^s fundamental wave current indicator in stator coordinates

u_m^s machine voltage in stator coordinates

y admittance matrix in stator coordinates

Y_a a-component of the admittance matrix in stator coordinates

Y_b b-component of the admittance matrix in stator coordinates

Y_ab coupling admittance in stator coordinates

Y_Δa a-component of the anisotropic admittance component in stator coordinates

Y_Δb b-component of the anisotropic admittance component in stator coordinates

Y_Σ isotropic admittance component

δ_F error signal

θ_r rotor position

θ_r,mod model rotor position

{tilde over (θ)}_r error of the model rotor position

Claims

1. A device adapted for rotary encoderless determination of a rotor position of a three-phase motor, comprising: a converter, adapted to feed the three-phase motor, operable with pulse width modulation, and including model variables for a rotor angle and a current indicator of the three-phase motor, the converter including a device adapted to measure, in closed-loop controlled operation, at least two values that represent a measure of local inductances of the three-phase motor, the converter adapted to determine an error of the model rotor angle by determining at least two weighting factors as a function of the model rotor angle and the model current indicator, to form a weighted sum from the at least two measured values and the at least two weighting factors, and to subtract, from the sum, another offset value that is determined as a function of the model rotor angle and the model current indicator.

2. The device according to claim 1, wherein the three-phase motor is arranged as a rotary encoderless three-phase motor.

3. The device according to claim 1, wherein the converter is arranged as a pulse-controlled inverter.

4. The device according to claim 1, wherein the converter is adapted to use local admittances as a measure of the local inductances.

5. The device according to claim 1, wherein the function is determined offline.

6. The device according to claim 1, wherein the function is set one time preceding a positional determination.

7. The device according to claim 1, wherein the function is determined prior to the closed-loop controlled operation.

8. The device according to claim 7, wherein the weighting factors and the offset value are assigned by the function to the values of the two model variables online.

9. The device according to claim 7, wherein the weighting factors and the offset value are assigned by the function to the values of the two model variables during position determination.

10. The device according to claim 1, wherein the function is based on local inductances determined as a function of values of a rotor position and a current indicator.

11. The device according to claim 10, wherein the current indicator represents a trajectory.

12. The device according to claim 1, wherein the weighting factors and the offset value are assigned to the model variables as a function of a differential of the local inductances that is specific to rotor position.

13. The device according to claim 1, wherein the weighting factors and the offset value are assigned to the model variables as a function of a differential of local admittances that is specific to rotor position.

14. A system, comprising: a three-phase motor; anda device adapted for rotary encoderless determination of a rotor position of the three-phase motor, including a converter, adapted to feed the three-phase motor, operable with pulse width modulation, and including model variables for a rotor angle and a current indicator of the three-phase motor, the converter including a device adapted to measure, in closed-loop controlled operation, at least two values that represent a measure of local inductances of the three-phase motor, the converter adapted to determine an error of the model rotor angle by determining at least two weighting factors as a function of the model rotor angle and the model current indicator, to form a weighted sum from the at least two measured values and the at least two weighting factors, and to subtract, from the sum, another offset value that is determined as a function of the model rotor angle and the model current indicator.

15. The system according to claim 14, wherein the three-phase motor is arranged as a rotary encoderless three-phase motor.

16. The system according to claim 14, wherein the converter is arranged as a pulse-controlled inverter.

17. The system according to claim 14, wherein the converter is adapted to use local admittances as a measure of the local inductances.

18. The system according to claim 14, wherein the function is determined offline.

19. The system according to claim 14, wherein the function is set one time preceding a positional determination.

20. The system according to claim 14, wherein the function is determined prior to the closed-loop controlled operation.

21. The system according to claim 20, wherein the weighting factors and the offset value are assigned by the function to the values of the two model variables online.

22. The system according to claim 20, wherein the weighting factors and the offset value are assigned by the function to the values of the two model variables during position determination.