The main stages of transition from early samples of Germanium alloy transistors to modern superpower bipolar Silicon transistors are reviewed. The state of theory of the semiconductor device performance and model notion of their output characteristics are analyzed. Perspective types and classes of the transistors on the base of Silicon and wide-band-gap materials are specified. Information about n ondestructive methods and means for measurement of electro physical parameters in bipolar transistor structures aimed at development of controllable technology of the transistors are presented. Analysis of equipment used for measurement output characteristics of the transistors, including super-powerful, and able to itch pulse power up to 1 megawatt is carried out. Basic problems related to the task of creation of power bipolar transistors with qualitatively superior set of output characteristics are formulated, approaches to the problems solutions are envisaged.

Description of linear continuous part of discrete system in phase space with the system output signal being one of the space coordinates is obtained by a linear nondegenerate transformation with observability matrix. The initial description of continuous part in natural phase space is obtained by decomposition of transfer function of continuous part into two functions, in one of which the numerator equals to unity, and in the other – the denominator. Implementation of the transformation makes use of an identity representing the observability matrix in the form of a polynomial in powers of the system matrix (Frobenius matrix) with coefficients of numerator of transfer function of the continuous part. An example demonstrating the proposed method applicability is presented.

Linear object under consideration provides execution of several manufacturing process and at the same time has to maintain a predetermined relation between the controllable variables of the object itself. A special case when the correlation between the controllable variables may be represented as linear manifold is studied. The object model is divided into two parts by using the error vector of deviation from the linear manifold; the first part of the model corresponds to execution of the manufacturing process, while the second part is used to eliminate deviation from the chosen manifold. Control laws for the both components of the model are synthesized independently in the form of difference equations. As an example, the problem of control for two-motor object is analyzed; the control system of the object should provide zero tracking error and maintain a certain ratio between rotation angles of motors’ rotors, which is equivalent to the presence of the mechanical reduction gear between rotors. Results of the control system modeling are presented.

Linear object under consideration provides execution of several manufacturing process and at the same time has to maintain a predetermined relation between the controllable variables of the object itself. A special case when the correlation between the controllable variables may be represented as linear manifold is studied. The object model is divided into two parts by using the error vector of deviation from the linear manifold; the first part of the model corresponds to execution of the manufacturing process, while the second part is used to eliminate deviation from the chosen manifold. Control laws for the both components of the model are synthesized independently in the form of difference equations. As an example, the problem of control for two-motor object is analyzed; the control system of the object should provide zero tracking error and maintain a certain ratio between rotation angles of motors’ rotors, which is equivalent to the presence of the mechanical reduction gear between rotors. Results of the control system modeling are presented.

The necessity of optimal (relative to the speed of action) control angular motion of spacecraft approaching an orbital object, is justified. A spacecraft with propulsion motor fixed stationary on its body and flywheel drives used as execution units of angular motion control system is considered. Dependence of angular speed of on the spacecraft turn angle is derived for the case of optimally fast rotation around the axis directed along the required angular speed. The main moments of inertia of the spacecraft are taken into account as well as gyroscopic moment of forces along the cross axis and restrictions to moment of forces exerting by the flywheel drives. It is shown that under optimally fast control, one of the projections of resulting moment on the axes along which the execution units are mounted, attains its limitation. The algorithms of evaluation of control moments making it possible to turn the spacecraft for the minimum time are developed. The algorithms also allow calculation of position of any axis bounded to the spacecraft body during the turn. The algorithms performance is tested with the use of mathematical modeling of spacecraft body turn through a specified angle, comparison with the known solution is carried out.

Results of development and experimental testing of active gravity compensation system for large-size transformable are presented. The developed system is intended for the use in ground experimental adjustment of transformed deployable umbrella-type reflectors with a diameter of up to 48 meters. Mathematical modeling and experimental testing confirm the system usability and efficiency. The system provides compensation of gravity action on large-size transformable cylindrically symmetric constructions consisting of up to several tens of non-transformable moving parts. A digital control system allows flexible variation of the testing parameters and the tested object configuration. Application of specialized control algorithms can almost completely compensate for the friction forces inherent in kinematic scheme of the gravity compensation system and therefore reduce drastically the time of the system adjustment and preparation for testing. Preliminary experimental studies show that under gravity-compensation action on the non-transformed part weighting up to 10 kg and moving with the linear speed of 2 m/min, the effective average value of residual uncompensated gravity force does not exceed 0.07 N.

A digital method for quantitative control of wave aberrations in optical systems is proposed. The approach is based on the method of izophotometry and involves transformation of a pair of shadow images into geometric models of shadowgrams of a linear grating using transformation function (including the “wedge” function), and the further processing of the models with specially designed software. The analyzed optical system quality is assessed; wavefront deformation map and characteristics of the system image quality are presented.

One of solutions to the problem of improvement of spectral composition of output oscillation of selfoffset phase-locked loop with multiplication implies a variation in feedback path structure. The Vernier feedback path makes it possible to diminish significantly the phase noise level in the self-offset phaselocked loop pass band (in the vicinity of carrying oscillation) while maintaining the specified loop multiplication factor. Analysis of noise filtering is carried out, and modelling in Fastmean 6 environment is performed for digital-to-analog frequency converter in the Vernier feedback path. The resulting oscillations spectra are presented. Recommendations on the method applications are formulated.

The possibility to optimize lens optical surface formation for submillimeter spectrum is considered. The presented analysis is based on image quality criteria and takes into account the manufacturing tolerances (dimensional tolerance, form tolerance, position tolerance, allowable roughness) and the labor costs for materials transparent in the submillimetre range (polyethylene, crystal quartz, polyethylene terephthalate, α –saphire, silicon).

A method for studying damped oscillations of a bellows shell in the presence of internal friction is considered. The logarithmic decrement of the oscillation is taken as a measure of internal friction at static and dynamic loading. Principles of operation of automated complex created for measuring internal friction in bellows sensing elements of control systems are described; the complex affords production of competitive and highly reliable bellows sensing elements. The complex incorporates an apparatus determining the element ability of energy scattering under vibration; a unit used to determine the energy scattering under cyclic loading of the bellows; a setup for studying damping characteristics of the bellows material under transfer vibrations and the element loading by static stretching force. The complex is also provided with an instrument for investigating the damping properties of the bellows sensing element material by damp oscillation method and the method of resonance deepening.