The control unit two cursortheme

 

The invention relates to radio engineering, namely, aviation electronics, and can be used for continuous monitoring of the output signals of the two cursortheme at the corners of heading, roll and pitch, as well as to control synchronously rotating shaft, remote transmission, etc., the control Unit two cursortheme contains the output of the sensor signals of the type synchro, out phase-sensitive detectors (PCD) and the comparator, three subchannel control roll, pitch, and rate. In each sub-channel signal processing separate synchro introduced zero-body, two water economy Department, information bus, the bus write/read bus reference voltage, and each sub-channel signal processing entered the microcontroller. The outputs of the sine and cosine windings of the first synchro through the first and second PCD respectively connected with the first and second information inputs of the microcontroller. The outputs of the sine and cosine windings of the first synchro through the first and second water economy Department respectively connected to the fourth and fifth information inputs of the microcontroller. Bus reference voltage (Lev. Board) is connected to the reference inputs of the first and second PCD and the input of the zero-body, the output of which is connected with the third information input is. The outputs of the sine and cosine windings of the second synchro connected to the same microcontroller relevant links, identical to the first synchro. One output of the microcontroller is connected to the scoreboard alarm signals “divergence”. Other outputs of the microcontroller for roll and pitch are connected by a signal “high limit roll left” and “pitch dive”, “the great ultimate roll right and pitch pitch up” respectively. The technical result consists in increasing the reliability of the device, increasing the accuracy of determining the differences in all destabilizing factors, as well as reducing the overall mass of the device and its power. 1 C.p. f-crystals, 3 ill.

The invention relates to radio engineering, namely, aviation electronics, and can be used for continuous monitoring of the output signals of the two cursortheme at the corners of heading, roll and pitch, can also be used, for example, to control synchronously rotating shaft, remote broadcasts, and so on,

Currently, the vast majority of planes of small-and medium-range equipped with two cursortheme (KB) or Gena for angles of roll and pitch, another for of course), and one that produces signals on the horizon (AH), autopilot (AP) and the other customers left the pilot and the other right. During the flight in conditions of sharp changes in temperature (GW are usually unsealed compartment), vibration and other disturbing influences, girovertikal (both or one) may alert rate, roll and pitch, different from the true, i.e., differ among themselves. Can also be breakages feeding wires GW and wires going from HS to AG and other customers can also be large poslevoyennye error. Because AG is the primary flight instrument at hand (shturvalnom) the management and AP in the automatic mode of piloting, the difference signal HS can lead (and lead as practice shows) to the precondition of a flight accident.

Known used on aircraft An-24, An-12, Mi-8, MI-17 and other control unit two GW roll and pitch based on Electromechanical principle. In this block (channel Bank, channel pitch identical to the first additional sine-cosine rotary transformer (synchro-receiver) “testing” is fulfilled tracking system, on the shaft of the gearbox which is the rotor Mo proportional to the angle of misalignment. This voltage is used as a signal to the comparison circuit, and is set as a reference voltage installation allowable angle of misalignment, usually 4-5see “Block comparison and limit roll BSPC”, M, “Engineering”, 1976, page 6-10.

The disadvantages of this unit are: low reliability due to the use of electromechanics, large overall dimensions and mass properties (GMH), lack of accuracy, especially in the course of the channel.

Known control unit roll BCA-18 used, for example, on the Tu-154, Il-86, etc. based on the comparison of the electrical signals of each winding of the synchro (roll and pitch) of the first and second GW between them, i.e., the sine winding of the first GW compared to the sine winding of the second GW, cosine winding of the first GW is compared, and so on, see “Technical description the ABS-154”, M, “engineering”, 1978.

The disadvantages of this unit are: a large number of adjustments when installing the unit on the Board and when changing, about twelve, because of the steepness of the GW signals differ from each other; low accuracy, because in the process of flight of the steepness of the sensors are changed when switching consumers HS, and when ist applied due to the low accuracy.

A device for control of angular position sensors, see A. C. of the USSR №481060 containing amplitude detectors connected to the sine and cosine windings of the angle position sensors, made in the form of sine-cosine rotary transformers, analog-to-digital converters, and the adder, the output of which is connected to a threshold element, it introduced functional dividers, control blocks, blocks allocation cosine and sine voltage and the logical elements, and the outputs of the amplitude detectors connected to the cosine windings of the sensor of angular position, connected with the control inputs of the control modules and analog-to-digital converters through functional divisors and units selection cosine voltages, the outputs of the amplitude detectors sine windings are connected to signal inputs of the control units and through blocks allocation sine voltage is connected to the analog-to-digital converters, the outputs of the control units and the outputs of the analog-to-digital converters connected to the inputs of the block of logic elements whose outputs are connected to the adder - prototype

The disadvantages of the prototype are the following: the operation of the device proem in similar, which leads to excessive circuit complexity, insufficient accuracy and high mass-dimension characteristics (GMH).

An object of the invention is to improve the operational efficiency due to a sharp decline GMH and power consumption; improve reliability; improve the accuracy of determining the differences in all destabilizing factors.

To solve this problem is proposed a control unit two cursortheme that contains the output of the sensor signals of the type synchro, out phase-sensitive detectors (PCD) and the comparator, the control unit has three subchannel control roll, pitch, and rate, and in each sub-channel signal processing separate synchro introduced zero-body, two water economy Department, information bus, the bus write/read bus reference voltage, and each sub-channel signal processing entered the microcontroller, thus the outputs of the sine and cosine windings of the first synchro through the first and second PCD respectively connected with the first and second information inputs of the microcontroller, the outputs of these windings through the first and second water economy Department respectively connected to the fourth and fifth information inputs of the microcontroller, the tire supporting naprajeno with the third information input of the microcontroller, who first bus write/read is connected to control inputs of both the water economy Department, the outputs of the sine and cosine windings of the second synchro, one output of the microcontroller is connected to the scoreboard alarm signals “divergence” and the other outputs of the microcontroller for roll and pitch are connected by a signal “high limit roll left” and “pitch dive”, “the great ultimate roll right and pitch pitch up”, respectively; all subchannels connected with flight-information complex “smart Board” bus serial interface, and subchannels roll and pitch connected with him also input a single command takeoff/landing-route”.

In Fig.1 shows a block diagram of the control unit cursortype, Fig.2 is a chart of conversion of input signals to the microcontroller of Fig.3 is a chart change the envelopes of the output voltage synchro angle of rotation when the destabilizing factors (changing the voltage and/or on/off many consumers synchro signals).

In Fig.1 depicts, I, II and III - subchannels roll, pitch, and rate, respectively, 1 and 2 - angle position sensors-type synchro, 3, 4, 5 and 6 - out phase-sensitive detail the sampling and storage), 13 - the microcontroller (MC); RS232C - bus serial interface of Fig.2 depicts the DCI - voltage winding synchro, converted to 5V, U cost and U sint - voltage retiring cosine and sine windings of synchro.

The sine winding synchro 1 through FCD 3 is connected with the first information input MK 13, and through the water economy Department 10 from the fifth input, the cosine winding of synchro 1 through FCD 4 is connected with the second information input MK 13, and through the water economy Department 9 - with the fourth input bus IEP (Lev. Board) is connected with the control inputs FCD 3 and FCD 4, and with the signal input of the zero-body 7, the output of which is connected with the third information input MK 13, with the eleventh informational input of which is connected one team RK “Takeoff/landing-route, coupled with information AFCS “smart Board”, the outputs MK 13 are: first information output “divergence”, the second “great roll left”, the third “great roll right through going on the scoreboard alarm in the cockpit, bus serial interface RS 232 C, coupled with the information handling complex “smart Board”; output winding of the synchro 2 PA II and the sub-channel course III is identical subchannel roll I, except that in the subchannel course III no output information signals limit angles.

These units control unit can be performed at the following REE and IC. Synchro 1 and 2 on the widely known and commercially used synchro-265 d, see “Sine-cosine rotary transformers”, Technical conditions, S.019.004 TU, M., 1989. CBEMS, FCD 3-6 on the well-known schema, see “Receiving device” Ed. by Fomin N. N., M, P and S, 1996, pp. 326-328, zero-the bodies 7 and 8 on the well-known Schmitt trigger on the IC series 133, the water economy Department of 9-12 on IC 1100, see the Guide “Chip semiconductor integrated analog, T. II, M, VNII, 1976, the microcontroller MC 13, for example, the world-famous company torola type MS with built-in ALU, timing channels, interrupt, ADC, RS232C, etc. or on the PIC16C74 by Microchip.

The control unit operates as follows. Let us first consider the example signal processing synchro 1. The output voltage of the sine winding Sinand cosine Coscome on FCD 3 and FCD 4, respectively, which are used only to determine the sign of the deviation, see Fig.2, which shows an example for the left roll 20. Output voltage FCD 3 and FCD the well-known algorithm determines in which quadrant are the output signals of the synchro. So: if Sin and Cos are both the “ + ” sign (the log.1), the first quadrant, if Sin has a negative sign, a Cos “+”, then the fourth quadrant, and so on, Zero-body 7 converts the frequency of the reference voltage U op (Lev. Board) logic levels, see also Fig.2, which receives the third information input MK 13. On the trailing edge of each pulse of the zero-body 7 timer MC starts counting time in the following way. Because the frequency of the DCI is 400 Hz, and therefore the period is 2.5 MS, the timer is programmed to time of 0.625 MS, i.e., until the middle of the negative log.0) half-U zero-body, after this time, when the amplitude of the frequency of the sine and cosine voltage maximum, given MK 13 command “record” in the form of a log.1, the first bus write/read, which recorded these stresses in the water economy Department 9 and 10, respectively. After the command “record”, immediately log.0 zero-body information with the water economy Department 9 and 10 is read, i.e., arrives at the fourth and fifth informational inputs MK 13, where the internal ADC digitized, i.e. converted into a code of sine and code cosine, then the ALU MK 13 takes their attitude, i.e. receives tg corner, and then arctan, i.e., the code corner in pure form. This operation can be performed prossie or as code, tg, then on the data bus ROM is the information corresponding to the true code of the angle. Similarly, processing of the output signals synchro 2, except that use the DCI (the rights. Board), because usually cursortype are recorded from different sources of alternating voltage. It should be noted that the code point of each synchro unfolds linearly from 0 to 360(with regard to the definition of quadrants), although it is possible to work at angles from 0 to 45and again 90by linearly increasing (0-45and linearly falling (45-90with voltage, but it depends on the taste of the programmer MK. Upon receipt code 1 synchro and synchro 2 MK 13 compares them with each other (subtracts) with account of the sign and if it turns out the difference is higher than the setpoint, usually 2-4produces signal “divergence” on the scoreboard alarm. At the same time MK 13 outputs the signals of the limit angles. For example, during takeoff and landing must not exceed the angles of roll and pitch of the order of 12-13(for heavy vehicles) and 30-35on the route. When exceeding these angles are to be issued is the first reached this corner, it is issued. When signal “Divergence” issue limit angles is blocked. Each sub-channel outputs bus RS232C information about the current angle for each coordinate in-flight-information complex “smart Board”, where it is processed and distributed to consumers. Information about the current angle for each coordinate when no signal “divergence” takes on average two sensors synchro. In the presence of signal “divergence” crew on the testimony of the other devices determines what curculation “lying” (out of order, large angular error, breakage phase, and so on) and disables it. As practice shows, experienced crew (pilot) spends not more than 10 C.

It is easy to see that this scheme can be transformed to compare 3 or 4 cursortheme by comparing each to each by the appropriate reprogramming of the microcontroller.

The serial channel with flight-navigation complex “information Board” can be specified setpoint for the “divergence” and “extreme corners, which may change not only on the single command, but linearly, depending on the flight altitude signal, for example, radioisotop the output sensor signal type synchro, out phase-sensitive detectors (PCD) and the comparator, wherein the control unit has three subchannel control roll, pitch, and rate, and in each sub-channel signal processing separate synchro introduced zero-body, two water economy Department, information bus, the bus write/read bus reference voltage, and each sub-channel signal processing entered the microcontroller, while the outputs of the sine and cosine windings of the first synchro through the first and second PCD respectively connected with the first and second information inputs of the microcontroller, the outputs of these windings through the first and second water economy Department respectively connected to the fourth and fifth information inputs of the microcontroller, bus reference voltage (Lev. Board) is connected to the reference inputs of the first and second PCD and the input of the zero-body, the output of which is connected with the third information input of the microcontroller, which is the first bus write/read is connected to control inputs of both the water economy Department, the outputs of the sine and cosine windings of the second synchro connected to the same microcontroller corresponding connections are identical to the first synchro, one output of the microcontroller is connected to the scoreboard alarm signalsatellite roll left” and “pitch dive”, “great ultimate roll right and pitch pitch up”, respectively.

2. The control unit two cursortheme under item 1, characterized in that all subchannels are connected with flight-information complex “smart Board” bus serial interface and subchannels roll and pitch connected with him also input a single command takeoff/landing-route”.