RU2537514C1 - Device to integrate standby instrument integrated system orientation unit with aircraft instrumentation complex - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: device comprises rotary transformer, unit of primary data transducers, ADC, computer, external interface shaper, microcontroller with ADC, null device, galvanic isolation unit, synchroniser, inverter and two conversion channels. Each of aforesaid components incorporates switch buffers connected in series with null device input. Comparator output is connected to microcontroller and switch control input. Switch control unit output is connected to ADC input while its outputs are connected to inverter input and output, said ADC being built in said microcontroller. Note here that buffer input of one channel is connected to sine winding of rotary transformer. Buffer input of the other channel is connected to sine winding of rotary transformer. Galvanic isolation unit input is connected to external reference voltage source which supplies the rotary transformer excitation winding incorporated with aircraft instrumentation complex.

EFFECT: enhanced performances.

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Description

The invention relates to aircraft, in particular to orientation blocks.

Known block orientation of the course system [1], containing a block of primary information sensors, analog-to-digital Converter (ADC), a computer (VM).

The disadvantage of this device is the lack of a converter signal of a rotating transformer into a digital code.

Also known block orientation [2], containing a block of sensors of primary information, ADC, VM.

The disadvantage of this device is the lack of a converter signal of a rotating transformer into a digital code.

The claimed invention is aimed at expanding the functionality of the orientation unit of the integrated system of backup devices.

The task is achieved by the fact that in the device for turning on the orientation unit of the integrated backup instrument system in the flight-navigation complex, which includes a rotating transformer containing a block of primary information sensors, ADC, VM, according to the invention, an external interface shaper, a microcontroller with a built-in ADC, a null-organ connected to the microcontroller, connected in series to the galvanic isolation unit and a synchronizer connected to the microcontroller, output which is connected through a shaper of the external interface to the VM, and two conversion channels, each of which contains a switch and a series-connected buffer connected to the input of the zero-organ, an inverter, a comparator, the output of which is connected to the microcontroller and the control input of the switch, the output of which is connected to the input The ADC built into the microcontroller, and the inputs are connected to the input and output of the inverter, while the input of the buffer of one channel is connected to the sinus winding of a rotating transformer, the input of the buffer of another the voltage is connected to the cosine winding of a rotating transformer, and the input of the galvanic isolation unit is connected to a source of external reference voltage supplying the excitation winding of a rotating transformer, which is part of the flight-navigation complex.

Significant differences of the proposed device include the introduction of an external interface shaper, a microcontroller with an integrated ADC, a zero-organ connected to the microcontroller, connected in series to the galvanic isolation node and a synchronizer connected to the microcontroller, the output of which is connected via a shaper of the external interface to the VM, and two conversion channels, each of which contains a switch and a series-connected buffer connected to the input of a zero-organ, an inverter, a mparator whose output is connected to the microcontroller and the control input of the switch, the output of which is connected to the input of the ADC built into the microcontroller, and the inputs are connected to the input and output of the inverter, while the buffer input of one channel is connected to the sinus winding of a rotating transformer, the buffer input of the other channel is connected to the cosine winding of a rotating transformer, and the input of the galvanic isolation unit is connected to a source of external reference voltage supplying the excitation winding of the rotating transformer, the input main part of the flight-navigation complex.

With this inclusion, the analog signals proportional to the sine and cosine of the rotation angle of the rotating transformer are converted into digital information about the current angle value necessary for transmission to the flight-navigation complex.

The present invention is illustrated in the drawing, which shows a block diagram containing a block of primary information sensors 1, ADC 2, VM 3, external interface driver 4, microcontroller 5, ADC 6, integrated in microcontroller 5, zero-organ 7, galvanic isolation device 8, synchronizer 9, conversion channels 10, 11, switch 12, buffer 13, inverter 14, comparator 15, sine 16 and cosine 17 of the rotary transformer winding, external voltage reference source 18, rotary transformer winding 19, aerobatics o-navigation complex 20.

Block 1 of the primary information sensors is connected through an ADC 2 to VM 3, to which a microcontroller 5 is connected via a former 4 of the external interface, to which a zero-organ 7 is connected and a synchronizer 9 and a galvanic isolation device 8 connected to a voltage reference source 18 and a winding are connected in series 8 19 excitation of a rotating transformer. In each of the conversion channels 10, 11, a buffer 13 connected to the input of the null organ, an inverter 14 and a comparator 15, the output of which is connected to the microcontroller 5 and the control input of the switch 12, the output of which is connected to the input of the ADC 6 built into the microcontroller 5, is connected in series and the inputs are connected to the input and output of the inverter 14, while the inputs of the buffer 13 of one channel 10 are connected to the sine 16 winding, and the other channel 11 to the cosine 17 of the rotating transformer, which is part of the flight-navigation complex 20.

The device operates as follows. Block 1 of the primary information sensors gives the current values of the parameters in the form of analog electrical signals, which are converted using the ADC 2 into a digital code supplied to the VM 3, where the flight parameters are calculated. From the flight-navigation complex 20, analog signals with sine 16 and cosine 17 windings of a rotating transformer are received in the form of sinusoidal voltages, proportional to the sine and cosine of the rotation angle of the aircraft, respectively. These signals are fed to the buffers 13 of the conversion channels 10, 11 for decoupling, are inverted by the inverter 14, and using the comparator 15 are converted into a sequence of rectangular pulses that coincide in phase with the input signal. Due to the fact that the sine and cosine signals have certain phase relationships between themselves in different quadrants of the angle of rotation, then at the output of the comparator 15 channels of the converter 10, 11 there will be a two-bit parallel digital code that contains information about the current quadrant of the angle of rotation. This information is fed to the microcontroller 5. In each channel, the input sinusoidal signals are inverted and fed to the inputs of the analog switch 12, which, through the control input from the comparator 15, connects direct or inverse signals to the inputs of the ADC 6 built into the microcontroller 5. These signals are converted into a digital code are transmitted to the microcontroller 5, where they are processed according to a certain algorithm, a digital code is generated, proportional to the angle of rotation of the rotating transformer, which through the shaper 4 in The current interface is transferred to VM 3. For galvanic isolation and synchronization of signal processing, a galvanic isolation device 8 and synchronizer 9 are connected in series, and a zero-organ 7 is provided to start the duty cycle of the microcontroller 5, which determines the transition point through zero by sine signals 16 and cosine 17 windings of a rotating transformer.

Thus, the formation of a digital code proportional to the sine and cosine of the current value of the rotation angle of the rotating transformer, expands the functionality of the proposed device.

The proposed device is used in the orientation unit of the integrated system of backup devices.

Information sources

1 US Patent No. 4347730, cl. 73 / 1E, 1982

2 Anniversary XV St. Petersburg International Conference on Integrated Navigation Systems. Collection of materials. St. Petersburg 2008, p. 263. Compensation of the magnetic deviation of the integrated backup instrument system, V.M. Samoilov, D.V. Svyazhin (prototype).

Claims (1)

A device for including the orientation unit of the integrated backup instrument system in the flight-navigation complex, which includes a rotating transformer containing a block of primary information sensors, an analog-to-digital converter, a computer, characterized in that an external interface former, a microcontroller built-in analog-to-digital converter, a zero-organ connected to the microcontroller, connected in series galvanic isolation unit a synchronizer connected to a microcontroller, the output of which is connected through a shaper of an external interface to a computer, and two conversion channels, each of which contains a switch and a series-connected buffer connected to the input of a zero-organ, an inverter, a comparator, the output of which is connected to a microcontroller and the control input of the switch, the output of which is connected to the input of an analog-to-digital converter built into the microcontroller, and the inputs are connected to the input and output of the inverter, when that one input channel buffer connected to the sine winding of the rotary transformer, the other channel buffer input connected to the cosine winding of the rotary transformer and the input node is connected to the electrical isolation of the external reference voltage source supplying the excitation winding of the rotary transformer included in the flight control and navigation system.