We consider the motion of two asynchronous drivers mounted on an elastic base. A mathematical model is presented by the following system of widely cited differential equations [10, 11]

;

(1) ;

,

where is the mass of the base, modeled as a rigid body with one degree of freedom, characterized by a linear horizontal displacement , is the coefficient of elasticity of the platform, is the damping coefficient, are the small masses of eccentrics with the eccentricities (radii of inertia), are the moments of inertia of rotors in the absence of imbalance, stands for the driving moments, denotes the resistance moment of the rotor. There is installed the pair of asynchronous drivers (unbalanced rotors) on the platform, whose rotation axes are perpendicular to the direction of base oscillation. The angles of rotation of the rotor are measured from the direction of the axis counter-clockwise. Assume that the moment characteristics of each driver and torque resistance have a simplest form, i. e. , . Here are the constant parameters, respective for the starting points, and stand for the drag coefficients of the rotors. Respectively, the subscript “1” refers to the first driver, while “2” to the second one. If we assume this simple linear model of the moment of static characteristics of the devices, the dimensionless form of eqs. (1) can be rewritten such as follows:

;

(2) ;

,

where appears in the role of the-small parameter of the problem. The parameters and are of order of unity such that and , where and . We introduce new notations: , , (). Here is the oscillation frequency of the base in the absence of the devices, is the dimensionless damping coefficient, is the new dimensionless linear coordinate measured in fractions of the radius of inertia of the eccentrics. The set (2), in contrast to the original equations, depends now on the dimensionless time.

The problem (2) admits an effective study by the method of a small parameter. In order to explore this one, we should transform the system (2) to a standard form of the six equations resolved for the first derivatives. The intermediate steps of this procedure are the follows ones. Firstly, we introduce the new variables, , , , associated with the initial dependent variables by differential relations: , , . Assume that in the set (2). Then one defines the transform to the new dependent variables based on the method of varied constants: , , , , , where , , and are the partial angular velocities of devices. Here , , , , , are the six new variables of the problem. The sense of these new variables: , are the amplitude and phase of base oscillations, respectively, , are the angular accelerations and , are the angular velocities of the rotors. The standard form suitable for further analysis is ready. Because of large records this standard form is not given, but the interested reader can trace in detail the stages of its derivation [12].

Solution of the system in a standard form is solved as transform series in the small parameter :

;

;

(3) ;

;

;

.

Here, the kernel expansion depends upon the slow temporal scales , which characterize the evolution of resonant processes. The variables with superscripts denote small rapidly oscillating correction to the basic evolutionary solution.

Then it is necessary to identify the resonant conditions in the standard form. The resonance in the system (2) occurs within the first-order nonlinear approximation theory, when and when or if the both parameters are close to unity, . All these cases require a separate study. Now we are interested in the phenomenon of the phase synchronization in the system (2). This case, in particular, is realized when, though the both partial angular velocities should be sufficiently far and less than unity, in order to overcome the instability predicted by the Sommefeld effect, since the first-order approximation resonance is absent in the system (2) in this case. Such a kind of resonance is manifested in the second approximation only.

In addition to the resonance associated with the standard phase synchronization in the system (2) there is one more resonance, when , which apparently has no practical significance, since its angular velocities fall in the zone of instability.

Note that other resonances in the system (2) are absent within the second-order nonlinear approximation theory. The next section investigates these cases are in detail.

Synchronization

After the substitution the expressions (3) into the standard form of equations and the separation between fast and slow motions within the first order approximation theory in the small parameter one obtains the following information on the solution of the system. In the first approximation theory, the slow steady-state motions (when) are the same as in the linearised set, i. e. , ; , ; ; . This means that the slowly varying generalized coordinates , , and , и do not depend within the first approximation analysis upon the physical time nor the slow time . Solutions to the small non-resonant corrections appear as it follows:

(4)

.

This solution describes a slightly perturbed motion of the base with the same frequencies as the angular velocities of rotors, that is manifested in the appearance of combination frequencies in the expression for the corrections to the amplitude and the phase . Amendments to the angular accelerations , and the velocities, also contain the similar small-amplitude combination harmonics at the difference and sum.

Now the solution of the first-order approximation is ready. This one has not suitable for describing the synchronization effect and call to continue further manipulations with the equations along the small-parameter method. Using the solution (4), after the substitution into eqs. (3), one obtains the desired equation of the second-order nonlinear approximation, describing the synchronization phenomenon of a pair of drivers on the elastic foundation. So that, after the second substitution of the modified representation (3) in the standard form and the separation of motions into slow and fast ones, we obtain the following evolution equations.

(5)

,

where is the new slow variable (), denotes the small detuning of the partial angular velocities, . The coefficients of equations (5) are following:

;

;

;

.

Let the detuning be zero, then these equations are highly simplified up to the full their separation:

(6)

.

Equations (5) represent a generalization of the standard basic equations of the theory of phase synchronization [10], whose structure reads

.(7)

Formally, this equation follows from the generalized model (5) or (6), if we put . The equation (7) has the general solution

,

where is an arbitrary constant of integration. This solution implies the criterion of the stable phase synchronization:

(8) ,

which indicates that in the occurrence of the stable synchronization the phase detuning must be small enough, compared with the phase modulation parameter. If this condition is not satisfied, then the system can leave the zone of synchronization.

On the other hand the refined model (6) says that for the stable synchronization the performance of the above conditions (8) is not enough. It is also necessary condition that the coefficient of the resonant excitation of vibrations in the base should not exceed the rate of energy dissipation , i. e. . The last restriction significantly alters the stability zone of synchronization in the space system parameters that is demonstrated here on the specific computational examples.

Examples of stable and unstable regimes of synchronization

The table below shows the calculation of the different theoretical implementations of stable and unstable regimes of the phase synchronization. The example 1 (see the first line in the table) demonstrates a robust synchronization with a small mismatch between the angular velocities of drivers . The example 2 (see, respectively, the second line in the table, etc.) displays an unstable phase-synchronization regime at the same small difference between the angular velocities, i. e. . One can reach a stable steady-state synchronization pattern in this example by adding a damping element with the coefficient . The example number 3. This is a robust synchronization for the small differences in eccentrics () and equal angular velocities. The example number 4. This is an unstable synchronization mode with the same small differences in eccentrics () and small mismatch in angular velocities, i. e. . One can reach a stable regime in this example by adding a dissipative element with the damping coefficient. The example number 5. This is an unstable synchronization regime. One cannot reach any stable synchronization regime in this example, it is impossible, even when adding any damping element. The example number 6. This is an unstable regime of synchronization at different angular speeds. It is also impossible to achieve any sustainable sync mode in this case.

Table. Parameters of stable and unstable regimes of synchronization.

The matching condition .

Synchronous rotations of drivers are almost idle and required no any high-powered energy set in this dynamical mode. Most responsible treatment for the drivers is their start, i. e. a transition from the rest to steady-state rotations [14]. So that, the utilizing vibration absorbers for high-powered electromechanical systems has advantageous for the two main reasons. On the one hand it provides a control tool for substantially mitigating the effects of transient shocking loads during the time of growth the acceleration of drivers. This contributes to integrities of the electromechanical system and save energy. On the other hand there is an ability to configure the appropriate damping properties of vibration absorbers to create a stable regime of synchronization when it is profitable, or even get rid of him, to destroy the synchronous movement, creating conditions for a dynamic interchange of drivers.

Acknowledgments