Device for controlling angular orientation system of aircraft

FIELD: aircraft engineering, in particular, systems for controlling angular orientation systems.

SUBSTANCE: device has sensors of banking angle, course, pitch and angular speeds of course, banking, pitch, three differentiation blocks, connected to appropriate angular speed indicators, subtracter, first input of which is connected to angular speed indicator of banking, and second one is connected to output of appropriate differentiating block, subtracter output, and also outputs of angular speed indicators for course, pitch and outputs of two other differentiating blocks are connected to existing squarers, and outputs of squarers respectively to adding, subtracting, adding, subtracting, adding inputs of adder, output of which is connected to first input of comparator, second input is supporting, output of which is output of device.

EFFECT: higher reliability of angular orientation system and higher control trustworthiness.

1 dwg

 

The invention relates to the field of aviation technology and can be used for complex control systems of the angular orientation of planes, helicopters, spacecraft. It can also be used to improve the reliability of the angle detection rate, pitch, and roll angular velocities of the object in the platform and strapdown inertial navigation systems. For strapdown inertial navigation systems and their means of flight information display, it can be used for the flight control accuracy of the representation of the orientation angles of the aircraft pilot. In automatic control systems it can businessone discover a flight failures of the main measures of the angular velocity sensors without hardware redundancy.

A device of the day gyroscopic control systems orientation type of detector malnutrition (SNP) [Altuhov V.Y., Stadnik centuries Gyroscopic devices, automatic onboard control systems of aircraft and their maintenance. M: engineering, 1991, p.42]. It contains three input transformer, rectifiers, threshold elements and schema OR so, which verifies that the supply voltages AC and DC their nominal values. Controlled gyroscopic the Skye system is considered healthy if the supply voltage is out of the field of tolerance. The advantage of this sort of control devices are: simplicity, reliability, low weight, size and cost. The main disadvantage of the DPR is their inability to detect the failure signal, corrective, and other low voltage circuits. The control is indirect, because the accuracy of the system orientation is not evaluated.

A device for system control of the angular orientation of the block type control rotation of the gyroscopes (BCUG) [Altuhov V.Y., Stadnik CENTURIES Gyroscopic devices, automatic onboard control systems of aircraft and their maintenance. M: engineering, 1991, p.14], with three sensor angular velocity of the gyroscopic type. It contains three pulse transformer and transistor circuit matches the output of which is through the transistor connected to the relay. If the speed of rotation of gyromotion all three sensors are angular velocities are equal, the pulses from the secondary windings of the transformers arrive simultaneously at the inputs of schema matching. Opens the transistor and closed alarm relay contacts, which produces a signal "Serviceability". If the speed of rotation of at least one gyrometer differs from the other speeds, the pulses arrive at the scheme matches simultaneously. Transistor C is kryvaetsja, which leads to the removal of the signal "Serviceability". The device only monitors the rotation of gyromotion, and the output signals of the angular velocity sensors are not checked. Control also has an indirect nature, and its implementation requires a threefold increase in the number of sensors of angular velocities of the aircraft.

A device control system of the angular orientation of the aircraft, built on two identical Aviagorodok first and second pilot block type comparison and limit roll (BSPC) [Bondarchuk IE, Kharin Century. And. Aviation and avionics of aircraft YAK-40. M: Transport. 1982, p.205]. The device contains two servo systems with selsyns - sensors Aviagorodok and relay amplifier that performs the functions of the Comparators. Misalignment same signals selsyns - sensors Aviagorodok failure causes the relay amplifier and to inform the pilot about the fault. The device has a relatively low reliability of control due to the presence of Electromechanical servo systems. Day it requires an excessive number of similar controlled Aviagorodok that affects the weight, dimensions and cost parameters of the equipment.

A device control system angular orientation for sine-cosine of transformate the [Vorobjev V.G., Deaf CENTURIES, Kadyshev I.K. Aircraft instruments, information-measuring systems and complexes. M.: Transport, 1992. C.376]. The device contains an adder, two schemes of calculation modules signals sine, cosine windings of the transformer and the comparison circuit. Check the condition: the sum of the moduli of signals sine and cosine windings of the transformer must be less than the nominal output voltage sine-cosine transformer is not more than the tolerance. The detection of system failures here is determined by the reliability of the sine-cosine transformer, which is the only part of the system. The device does not check the validity of the entire system angular orientation.

A device control system of the angular orientation of the aircraft type control unit roll (BCA) [Altuhov V.Y., Stadnik CENTURIES Gyroscopic devices, automatic onboard control systems of aircraft and their maintenance. M: engineering, 1991, .38] or basic course and vertical (BSCW) [Vorobjev V.G., deaf CENTURIES, Kadyshev I.K. Avicennia devices, information-measuring systems and complexes. M.: Transport, s]built on three identical sensors of the angular orientation of girovertikal or cursortheme. The device contains a quorum of the elements, the majority of scheme e or e is astromechanics type, where is the averaging of the signals from all three sensors and the comparison in the comparator output signal of each of the three sensors of the angular orientation of the averaged signal. The reliability of the control system of the angular orientation here is great, but the size, weight, power consumption and cost of the equipment is three times larger than necessary. Control with a three-fold structure of the system angular orientation on light, maneuverable aircraft is not appropriate for the operational and economic considerations.

A device for control of the Builder cursortype and sensors of angular velocity [U.S. Pat. 2122230 RF, G 05 B 23/02. Device for control of the Builder cursortype and sensors of angular velocity / Vouchered // B. I. 1998, No. 32], containing the outputs of the Builder cursortheme proportional to the sines and cosines of the angles of roll, heading and pitch on the sine-cosine transformer (CT), structurally included in the audited curculation platform type, the block guides of the cosines of the twelve multipliers, two adders and two schemes subtraction unit projections on twelve multipliers, six adders and six differentiator, inverter. The control device uses the relationship of the projection of absolute angular velocity measured by the angular velocity sensors and calculated on the show is the second of the outputs of the sine-cosine transformer cursortype. Its implementation on an aircraft is determined by platform type it with sine-cosine transformer sensor roll rate and pitch. For common platform systems angular orientation this option from the control device is preferred. However, its implementation in digital systems, where the sine-cosine transformers, as basic information converters sensors are missing, causing additional difficulties.

The closest one of the known technical solutions is a device for the control system of the angular orientation of the aircraft [Belgorod S.L., automation control and landing of aircraft. M; Transport, 1972, s]. It contains sensors angular velocity of the object along the axes X, Y, Z, three blocks differentiation, the sensor roll angle, heading and pitch of the aircraft, three schemes of the subtractor and comparator. Thus the axis of sensitivity of the first sensor of angular velocity along the X-axis parallel to the longitudinal axis of the aircraft. The axis of sensitivity of the second sensor of angular velocity along the Y-axis perpendicular to the plane of the wings. The axis of sensitivity of the third angular rate sensor Z-axis perpendicular to the plane of symmetry of the aircraft. The output of the sensor roll angle is connected to the input of the first block of differentiation, access to the which is connected with the first subtractive input of the first circuit subtraction. The second input of the first circuit of the subtractor is connected to the output of the first sensor of angular velocity along the X axis and the output to the input of the first comparator. The output of the angle sensor of course is connected to the input of the second block of differentiation, the output of which is connected to the first subtractive input of the second circuit subtraction. The second input of the second circuit subtracting connected to the output of the second sensor of angular velocity along the Y-axis, and the output to the input of the second comparator. The sensor output of the pitch angle is connected to the input of the third block of differentiation, the output of which is connected to the first subtractive input of the third circuit subtraction. The second input of the third circuit subtraction is connected to the output of the third sensor of angular velocity along the Z axis, and the output to the input of the third comparator. Signals an error proportional to the respective differences of the angular velocities measured first, second, third sensors of angular velocities along the axes X, Y, Z, and their estimates obtained by dierentiating the sensor roll rate and pitch in the first, second and third blocks differentiation obtained at the outputs of the first, second and third circuits of the subtraction is compared with a tolerance in the first, second and third Comparators. System failure angular orientation, consisting of sensors, roll, heading, pitch, and sensors of angular velocity along the axes X, Y, Z are indicated by the device con is playing at substantial misalignment of the signals at the outputs of the subtraction schemes.

A disadvantage of the known device the prototype is the inability to control the orientation system at arbitrary spatial easy maneuvers of the aircraft, when the roll rate and the pitch have an arbitrary value [Buesgens G.S., Studni W. Aerodynamics of the aircraft. Dynamics of longitudinal and lateral movement. M: mechanical engineering, 1979, s; Aerodynamics, stability and control of a supersonic aircraft, Ed. Gsena. M.: Nauka. Fizmatlit, 1998, s]. When this equality:

underlying the control device of the prototype are violated. This follows from the exact ratios [Buesgens G.S., Studni W. Aerodynamics of the aircraft. Dynamics of longitudinal and lateral movement, Meters: machinery, 1979, p.21, 22; Aerodynamics, stability and control of a supersonic aircraft, Ed. Gsena M.: Nauka. Fizmatlit, 1998, s] angular velocity:

or

where ωXthat ωYthat ωZ- the angular velocity of the aircraft, measured first, second, and third sensors of angular velocities, X, Y, Z coupled system of coordinates; γ, Ψ, υ,- angles, roll, heading, pitch, and their angular velocity.

The technical result achieved when the wasp is the implementation of the claimed invention, is to improve the accuracy of the control system of the angular orientation at arbitrary spatial maneuvers of the aircraft. The relation (2), (3) the angular velocities are taken into account in the inventive device. It is in the most compressed form establishes the relationship of the angular velocities of the aircraft without restrictions on its mobile properties (heavy or light machine) and apply it to angle sensors roll, heading and pitch. This is especially important for future systems angular orientation with strapdown systems and discrete code information reading about the angles and angular velocities of the apparatus in a fully digital avionics. The device can improve the accuracy of control for the detection of failures and malfunctions of the sensors of angular velocity and angle sensors.

The main challenge we address the claimed device object for system control of the angular orientation of the aircraft, is to increase the reliability of the system angular orientation and the reliability of its control with minimum weight, the dimensions, the cost of the equipment easy maneuvering object. Additionally solved the problem of the hardware nonredundant, businessing control with a simple algorithm. The control device does not impose additional requirements when pairing apparatus is atural system orientation platform or strapdown type. Its implementation is simple as the minimum software and circuit means.

This technical result is achieved in that in the device control system of the angular orientation of the aircraft, containing three sensor angular velocity of the object along the X, Y, Z, three blocks differentiation, the sensor roll angle, heading and pitch of the aircraft, the schema subtraction and the comparator, and the axis of sensitivity of the first sensor of angular velocity along the X axis parallel to the longitudinal axis of the aircraft, the axis of sensitivity of the second sensor of angular velocity along the Y-axis perpendicular to the plane of the wings, and the axis of sensitivity of the third angular rate sensor Z-axis perpendicular to the plane of symmetry of the aircraft, the output of the sensor roll angle connected to the input of the first block of differentiation, the output of which is connected to the first subtractive input schema subtraction, the second input of which is connected to the output of the first sensor of angular velocity along the X axis, the output of the angle sensor of course is connected to the input of the second block of differentiation, the sensor output of the pitch angle is connected to the input of the third block of differentiation, introduced five Quad, the adder five inputs, and the output of the circuit subtracting, via the first squarer connected to the first summing input of the adder five whodo is, the second subtractive input of which, through the second squarer connected to the output of the second block of differentiation, the third summing input of the adder five inputs, through the third squarer connected to the output of the second sensor of angular velocity along the Y-axis, the fourth subtractive input of the adder at the five gates of the fourth Quad splitter, coupled to the output of the third block of differentiation, the fifth summing input of the adder at the five gates of the fifth Quad splitter, coupled to the output of the third sensor of angular velocity along the Z axis, and the output of the adder five inputs connected to the input of the comparator.

The essential features of the invention provides the technical result achieved by carrying out the invention devices for system control of the angular orientation of the aircraft. When this is implemented by comparison of the signals is proportional to the square of the modulus of the angular velocity vector of the aircraft, measured through orthogonal projection of the angular velocity sensors along the axes of the associated coordinate system and through the oblique projection of this vector on the axes roll rate and pitch, measured respectively by the sensors of the angular orientation, at an arbitrary position of a light maneuverable object. By kinematic relations (2), we can determine the expression for kV is dratha module of the angular velocity vector of the aircraft, erected in the square right and left parts of the equations and summing them, then

Making the substitution in (4) ratioand from the first equation (2), we get

or after transfer to the left side and grouping

Expression (6) is the ratio, which is implemented by the device control system of the angular orientation of the aircraft.

Conducted by the applicant's analysis of the level of technology found that analogs characterized by the sets of characteristics is identical for all features of the claimed device for system control of the angular orientation of the aircraft, are not available, therefore, the claimed invention meets the condition of "novelty."

Search results known technical solutions in this and related areas of technology in order to identify characteristics that match the distinctive features of the prototype of the characteristics of the claimed invention, have shown that they do not follow explicitly from the prior art.

Of certain of applicant's prior art there have been no known impact provided the essential features of the claimed invention transformations on the achievement of the technical result and the invention is not based on:

- the replacement of any part of the device is similar to another well-known part to achieve a technical result, in respect of which it is the effect of such additions;

- the exclusion of any part of the device is analog while the exclusion of its functions and the achievement of the usual result of such exclusion;

- increase the number of identical elements day gain technical result due to the presence of the device is of such elements;

- the execution of the known device is analog or part of a known material to achieve a technical result due to the known properties of the material;

- creating device, consisting of well-known parts, the choice of which and the relationship between them is carried out on the basis of known rules, and achievable technical result is due only to the known properties of the parts of this device and connections between them;

- the change of the quantitative characteristic (s) of the device and the provision of such evidence in the relationship or change the form of the relationship, if known the Yong the fact that the influence of each on the technical result, and new values for these characteristics or their relationship could be obtained from the known dependencies, therefore, the claimed invention meets the "inventive step".

The invention is illustrated in the drawing, which shows a block diagram of a device for the control system of the angular orientation of the aircraft and the following notation:

1 - sensor roll angle;

2 - the angle sensor rate;

3 - sensor pitch angle;

4 - the first angular rate sensor on the X-axis,

5 - second angular rate sensor on the Y-axis;

6 - the third angular rate sensor Z-axis;

7, 8, 9 - the first, second, and third blocks differentiation;

10 is a diagram of the subtraction;

11, 12, 13, 14, 15 - the first, second, third, fourth, fifth Quad;

16 - adder five inputs;

17 comparator.

The device control system of the angular orientation of the aircraft contains the sensor 1 Bank angle sensor 2 angle rate sensor 3 pitch angle, the first angle sensor 4 speed on the X-axis, the second sensor 5 of the angular velocity along the Y-axis, the third sensor 6 angular velocity along the Z axis so that the first input unit 7 differentiation is connected with the output of the sensor 1, Bank angle, the input of the second block 8 of differentiation is connected with the output of the sensor 2 angle of the course, the input of the third block 9 of differentiation is connected with the output of the sensor 3 angle that is of plaster. First subtractive input circuit 10 of the subtractor is connected to the output of the first block 7 of differentiation, its second input connected to the output of the first sensor 4 angular velocity on the axis X, and the output to the input of the first Quad 11. The inputs of the second Quad 12, the third Quad 13, the fourth Quad 14 and the fifth Quad 15 are connected respectively to the outputs of the second block 8 of differentiation, the second sensor 5 of the angular velocity along the Y-axis, the third block 9 of differentiation, and the third sensor 6 angular velocity on the axis Z. the First summing input of the adder 16 to five inputs connected to the output of the first Quad 11, the second subtractive input - output of the second Quad 12, the third summing input - output of the third Quad 13, the fourth subtractive input - output of the fourth Quad 14, the fifth summing input - output fifth Quad 15, and the output to the input of the comparator 17, the output of which is an output device for system control of the angular orientation of the aircraft.

Practical implementation of the device for a control system of the angular orientation of the aircraft is possible on analog and digital circuit basis. It should be noted that the sensor 1 Bank angle sensor 2 angle rate sensor 3 pitch angle are part of the system angular orientation flight-navigation complex (NCP) is for as separate sensors, for example AGB-98, AGR-29, ISS-1, SBCV-P, "Ridge", etc. or jointly in the platform inertial navigation system for example, And-11, And 21, etc. or in commercially available strapdown intercalary navigation systems (bins) And-42, bins-85 and other First sensor 4 angular velocity along the X-axis, the second sensor 5 of the angular velocity along the Y-axis, the third sensor 6 angular velocity along the Z axis are the main measure of the automatic control system (ACS) of the aircraft, for example, type DUSU-AU DUSU-M, BDG-25, BDG-26, FAP-14 AM, etc. or are part of the same beans as CH-2, CRS-500, VCS-700, and others [avionics Russia. Encyclopedic Handbook / edited amended Sudborough. SPb.: National Association of avionics producers, 1999, s, 128, 64, 77, 78, 119, 126, 127]. In the latter case, the inventive device performs control and built-in transmitter beans. When the circuit implementation device blocks differentiation 7, 8, 9, scheme 10 subtraction, Quad 11, 12, 13, 14, 15, the adder 16 five inputs and a comparator 17 are implemented on integrated circuits [Alexenko A.G., particularly E.A., Starodub GI Application of precision analog ICS. M.; Chapman and hall, 1981, p.75, 82, 98, 101, 94, 174]. The preferred implementation of the inventive device software on-Board computer in a fully digital system, the angular orientation of the plane on the CVM 80, DCM 90 [avionics Russia. Enciclop the legal Handbook / edited edit Sudborough. SPb.: National Association of avionics producers, 1999, s] or the microprocessor signal processing [Digital processing of signals. Guide / Agustina, Siewierski, Abbasov and other edited Agustina. M.: Radio and communication, 1994, p.69; Tin, Avenoso, Oppologize. The design of digital devices on a single chip microprocessors. M.: Energoatomizdat, 1990].

The device control system of the angular orientation of the aircraft operates as follows. The signal from the sensor 1, Bank angle, proportional to the roll γ aircraft, is differentiated in the first block 7 of differentiation, and is supplied to the first subtractive input circuit 10 subtraction. On the second summing input circuit 10 subtraction signal from the first sensor 4 angular velocity on the X-axis, proportional to the angular velocity ωXan aircraft. The output signal of the circuit 10 subtraction proportional tothrough a squarer 11 is supplied to the first summing input of the adder 16 to five inputs. Simultaneously, the signal from the sensor 2 angle rate proportional to the rate of ψ aircraft, is differentiated in the second block 8 of differentiation, and to the input of the Quad 12. The output signal of Quad 12, proportionallysupplied to the second subtractive input of the adder 16 to five inputs on the third summing input of which receives a signal proportional to. It is obtained at the output of the Quad 13, to which input signal, proportional ωYwith the release of the second sensor 5 of the angular velocity on the y axis. Simultaneously, the signal from the sensor 3 pitch angle, is proportional to the pitch υ aircraft, is differentiated in the third block 9 of differentiation, and to the input of the Quad 14. The output signal of the Quad 14, is proportional tocomes on the fourth subtractive input of the adder 16 to five inputs on the fifth summing input of which receives a signal proportional to. It is obtained at the output of the Quad 15, to which input signal, proportional ωZ,with an output of the third sensor 6 angular velocity on the axis z At the output of the adder 16 to five inputs produces a signal proportional towhich is fed to the input of the comparator 17. The output signal of the adder 16 to the five inputs to the system angular orientation different from zero is not more than a value determined by the errors of its sensors and computing in the control device. The morning value equal to the threshold comparator 17 compares the output with what galom adder 16 to five inputs. In the event of a system failure the angular orientation of the signal at the input of the comparator 17 exceeds its threshold, and the control device detects this failure by issuing an output signal of the comparator 17.

As follows from the above, the technical achievement of the control system of the angular orientation of the aircraft is provided by the comparison of the projections of the angular velocity vector of the object on the orthogonal axis of the associated coordinate system and the oblique projection of this vector on the axes roll rate and pitch, as in the prototype, and when the comparison signal is proportional to the square of the modulus of the angular velocity vector of orthogonal projections and oblique squares of the projections of this vector. Orthogonal projections are derived from the signals of the first, second and third sensors of angular velocities in the X, Y, Z, and oblique projection on the sensor signals of the roll rate and pitch. The device does not contain converters trigonometric functions of the angles of roll, heading and pitch, and therefore, its implementation in the computer, based on the shortest time elementary arithmetic operations. This provides him with the best performance in comparison with all known algorithms for control systems angular orientation. Its accuracy does not depend on the arbitrary orientation of the aircraft and the parathas, what is not in the prototype. The inventive control device operates almost businessone, as there is no statistical signal processing. Its information-operational quality analysis [Gorelik A.L., Butko GI, Belousov Y.A. Onboard digital computers. M: mechanical engineering, 1975, p.106] gives approximately the length of the algorithm - 34 units of short-term operations on-Board computer. A similar assessment of the quality of the prototype - 24 units, and similar to U.S. Pat. No. 2122230 RF - 110 units with control sensors, roll, heading, pitch with SKT and 528 units under their control for discrete code signals. Implementation of the proposed algorithm is the lowest with the highest accuracy. The device has a high noise immunity due to the quadratic nonlinear dependence of all incoming signals. At the same time it provides increased sensitivity to system failures angular orientation when one or more signals differ significantly from their normal values. The realization of a device in the computer does not impose any additional conditions to design the circuit, the output signals of the angular orientation of the platform or strapdown type. Check the signals are not trigonometric functions of angles, eliminating the need for additional transformations on the inputs of the computer, and the additional error is to time and cost from this. The device can be used in isolation in the strapdown system as a software control ratio to determine errors and failures [Mats VI, Belousov Y.A., et al H.E. Onboard digital computers and systems. M.: Vysshaya SHKOLA, 1988, s] embedded computer system. The absence of inertia ratio allows for the quantum solution of the main tasks of the system angular orientation - definitions of angles of Bank, rate, pitch, according to the signals of the speed sensors to determine the correctness of that decision, simultaneously computing the claimed relation (6). Software implementation of the device according to the number of steps and the volume control program may have a minimum complexity. This ensures a high accuracy of control and opportunities to its embedding in the local solvers integrated avionics object. In particular, for remote display of flight information that can contribute not only to control these sensors, but also the detection of violations in indicators and channels of communication equipment.

Thus, the above information proves that when carrying out the claimed invention, the following conditions are true:

- a means of embodying the device of the invention in its implementation, is to use the Oia in aeronautical engineering and in particular, for complex control systems the angular orientation of the aircraft. It can be used on light and maneuverable objects without hardware redundancy in order to detect failures of sensors and protection against failures in the system;

for the claimed invention in the form as it is described in the independent claim, confirmed the possibility of its implementation using the described or other known prior to the filing date of the funds;

the tool embodying the claimed invention in its implementation, is able to obtain the technical result.

Therefore, the claimed invention meets the condition of patentability "industrial applicability".

The device control system of the angular orientation of the aircraft, containing three sensor angular velocity of the object along the X, Y, Z, three blocks differentiation, the sensor roll angle, heading and pitch of the aircraft, the schema subtraction and the comparator, and the axis of sensitivity of the first sensor of angular velocity along the X axis parallel to the longitudinal axis of the aircraft, the axis of sensitivity of the second sensor of angular velocity along the Y-axis perpendicular to the plane of the wings, and the axis of sensitivity of the third angular rate sensor Z-axis perpendicular to plose the spine of symmetry of the aircraft, the output of the sensor roll angle is connected to the input of the first block of differentiation, the output of which is connected to the first subtractive input schema subtraction, the second input of which is connected to the output of the first angular rate sensor X, the output of the angle sensor of course is connected to the input of the second block of differentiation, the sensor output of the pitch angle is connected to the input of the third block of differentiation, characterized in that it introduced five Quad, the adder five inputs, and the output of the circuit subtracting, via the first squarer connected to the first summing input of the adder five inputs, the second subtractive input of which, through the second squarer connected with the release of the second block of differentiation, the third summing input of the adder five inputs, through the third squarer connected to the output of the second sensor of angular velocity along the Y-axis, the fourth subtractive input of the adder at the five gates of the fourth Quad splitter, coupled to the output of the third block of differentiation, the fifth summing input of the adder at the five gates of the fifth Quad splitter, coupled to the output of the third sensor of angular velocity along the Z axis, and the output of the adder five inputs connected to the input of the comparator.



 

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FIELD: electric measurements, applicable in check-up of tram and trolleybus electric apparatuses in the process of manufacture and in service.

SUBSTANCE: current in the current source is fed to the current winding of the current relay from the rectifier via a key, choke, shunt. The device uses a pulse-width modulator that controls the keys, slowly varying voltage is applied to the modulating input of the pulse-width modulator that is preliminarily modulated by the rectifier ripple voltage. Besides, use is made of a sample-release circuit of operate (release) currents and voltages. The signals from these circuits are fed to indicators via analog-to-digital converters.

EFFECT: reduced error of determination of operate and release current and voltage relays, enhanced capacity of check-up in the device due to reduced ripples of the source of smoothly varying current.

2 cl, 4 dwg

FIELD: mechanical engineering.

SUBSTANCE: method comprises determining variations of the parameter during acceleration and deceleration of the actuator. The device comprises generator and OR-NOT unit, the inputs of which are connected with the outputs of the relay. The output of the relay is connected with the input of the generator.

EFFECT: enhanced accuracy of the method and simplified device.

3 dwg

FIELD: instrumentation engineering; serviceability check of multichannel communication systems.

SUBSTANCE: proposed equipment includes personal computer, multiplexing switch, circuit checkup unit, control unit, multichannel comparison unit, virtual standard, switching unit, output signal shaper, multiplexer, and normalizing unit that has voltage meter and circuit meter.

EFFECT: enlarged functional capabilities of device.

3 cl, 1 dwg

FIELD: measuring equipment.

SUBSTANCE: as a source of standard signal not separate generator of test signal according to known code structure is used, but a component of modem, to provide for substantial simplification of process under unfavorable conditions.

EFFECT: higher efficiency.

1 dwg

FIELD: automated control and diagnostics systems.

SUBSTANCE: first variant of complex includes control computer, mating block, commutator, local data exchange main, tests forming block, logical analyzer, signature analyzer, synchronization block, digital oscillographs block, special form signals programmed generators block, programmed power-sources block. Second variant of complex additionally includes block for forming high-frequency test signals and block for measuring high-frequency signals.

EFFECT: broader functional capabilities, higher efficiency, higher reliability.

2 cl, 2 dwg

FIELD: automatic control.

SUBSTANCE: device has first and second analog-digital converters, first and second coefficients forming blocks, first and second multiplication blocks, counter, first and second integrator, control effect forming device, division block, buffer and registering block, while coefficients forming blocks are made in form of digital filters and all remaining blocks of device are made digital.

EFFECT: higher precision, higher resistance to interference.

1 dwg

FIELD: measuring equipment.

SUBSTANCE: device has block for forming control and stimulation signals, block for forming standard signals, multiplication blocks, frequency transformer, phase rotator, commutator, frequencies grid generator, integrators, blocks for square involution, adder, normalization block, key, analog-digital converter, comparison circuits, memory blocks, registers, information output block, interval estimation block (for setting lower and upper limits of trust range for each measured value of mutual difference coefficient of distorted and standard signals) and block for analysis of number of support values of mutual difference coefficient (to exclude from further processing results of measurements, for which within limits of trust interval number of support values of coefficient exceeds allowed limit).

EFFECT: higher precision.

2 cl, 2 dwg

FIELD: technical diagnostics.

SUBSTANCE: method includes, for each set of input test signals, forming of prior matching response signals for intermediate points of controlled device. Received response signals at outputs of product are compared to parameters of standard response signals and level of their match is determined, in case of mismatches broken branch of functional circuit is determined and diagnostics is repeated by substituting all formed combinations of input signals, after that diagnostics of erratic portions is started.

EFFECT: simplified method.

3 dwg

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