RU152839U1 - INFORMATION TRANSFORMATION DEVICE FOR INFORMATION MANAGEMENT SYSTEM - Google Patents

Abstract

An information conversion device for an information management system, comprising an analog signal receiving module, consisting of n functional logic blocks, and an integrated computing module, consisting of k functional logical blocks, interacting with each other via a code line, characterized in that the receiving module analog signals contains n control units, each n functional-logical unit of the module for receiving analog signals is associated with a corresponding n control unit, the calculator module The integrated one contains k control units, each k functional-logical unit of the computational integrated module is connected to the corresponding k control unit, and the power command module consisting of m functional-logical units and m control units, each of which is associated with the corresponding m control unit, a temperature compensator associated with the analog signal receiving module, a power module associated with the analog signal receiving module, an integrated computing module and mod power command, and the analog signal receiving module, the integrated computing module and the power command module interact with each other via a code line, and the integrated computing module interacts with the aircraft’s information and control system via the primary and backup information exchange channels.

Description

The utility model relates to information-measuring equipment and can be used to collect and process flight data, save this information in case of flight accidents, form control commands, as well as for operational control of aircraft systems and equipment.

A device for collecting and processing information is described in RF patent No. 2349878, IPC G01D 9/00, 06/05/2007, which includes an analog module, a module for one-time commands, a module for receiving and transmitting serial codes, a control module, and a control and data collection module that interact between each other on the working and backup highways, in addition, in the control module and in the control and information collection module there are internal data exchange highways.

Continuously increasing requirements for the degree of automation of flight, the level of reliability of instruments and systems of modern and promising aircraft suggest a higher level of integration of onboard equipment, redundancy of its individual paths for receiving, processing and issuing signals.

The trend towards the integration of airborne equipment involves integrated information processing, increased control over the operation of airborne systems, the identification of dangerous flight conditions and, if necessary, reconfiguration of airborne equipment, as well as the formation of indication and control information for control and display systems.

In addition to receiving and converting information received from on-board equipment into digital format, forming control commands, it is necessary to ensure the maximum reliability of the information, for which it is necessary to monitor their own operability in flight with the issuance of a service signal to the interfaced equipment, as well as the ability to adapt to various options for assembling complexes onboard equipment.

However, the known device does not fully satisfy the increasing requirements for such devices in terms of reliability, controllability, the level of reliability of the processed information and the possibility of reconfiguration.

The essence of the utility model is as follows.

The task to which the claimed utility model is directed is to increase the reliability, increase the reliability of the information generated, the ability to adapt to various versions of on-board radio equipment (avionics).

The technical result consists in increasing the reliability, reliability of the generated information of the claimed device, as well as the ability to adapt to various options of avionics.

The specified technical result is achieved by the fact that the information conversion device for the information management system contains an analog signal receiving module, consisting of n-functional logic blocks, each of which is connected to the corresponding n-control block, an integrated computing module, consisting of k-function -logical blocks, each of which is associated with the corresponding k-control block, a power command module consisting of m-functional logical blocks, each of which is associated with a corresponding a m-control unit, as well as a temperature compensator associated with the analog signal receiving module, a power module connected to the analog signal receiving module, an integrated computing module, a power command module, the analog signal receiving module, the integrated computing module, and the power command module interact among themselves on a code line of communication, and a computing module integrated on the primary and backup channel of information exchange interacts with the information management system th aircraft.

The essence of the proposed utility model is illustrated in the drawing.

In FIG. 1 is a structural diagram where

1 - module receiving analog signals MPA,

2 - n-functional-logical blocks of the module receiving analog signals MPA,

3 - n-blocks of control of the functional logical blocks of the module for receiving analog signals MPA,

4 - CT temperature compensator,

5 - integrated computing module MVI,

6 - k-functional-logical blocks of the module computing integrated MVI,

7 - k-control blocks of the functional-logical blocks of the computing module integrated MVI,

8 - power command module MSC,

9 - m-functional-logical blocks of the power command module MSC,

10 - m-blocks of control of the functional logical blocks of the power command module MSC,

11 - power module MP,

12 - code line communication CLS,

13 - multiplex channel information exchange MKIO.

14 - backup multiplex channel information exchange MKIO,

15 - information management system IMS aircraft.

The information conversion device for the information management system performs:

- receiving signals in the form of one-time commands, analog signals and a standard serial code,

- processing information on the program,

- issuing signals in the form of control signals and a serial code;

- storage and operation of special software in the unit;

- monitoring their own operability in ground conditions and in flight with the issuance of a service signal to the mating equipment.

As noted above, the device is built on a modular principle, so the module for receiving analog signals MPA 1 consists of n-functional logic blocks 2, each of which is connected to the corresponding n-block control 3, carrying out switching and normalization of analog signals with their further conversion into digital form, receiving frequency signals, receiving synchronization signals and generating control signals, generating reference currents for measuring resistances and output control currents, voltage and frequency standards, rovedenie own performance control signal from the issuance of serviceability, as well as providing communication with other modules of the device according to the code link 12 KLS.

The temperature compensator KT 4 provides compensation for the temperature of the cold junction of the device.

The integrated computing module MVI 5 consists of k-functional logic blocks 6, each of which is connected to the corresponding k-control block 7, implementing the specified algorithms for calculating and controlling other device modules, receiving and issuing one-time commands, receiving and issuing information via CLS 12, the exchange of information on the multiplex channel of information exchange MKIO 13 and the backup multiplex channel of information exchange MKIO 14 with the information management system IMS 15.

The power command module of MSC 8 consists of m-functional logic blocks 9, each of which is connected to a corresponding m-control block 10, which generate power control signals according to the information received from MVI 5 via CLS 12, and to generate direct type control signals on input discrete signals in the event of a failure of a device or paired equipment.

The MP 11 power supply module contains protection and filtering devices, voltage limiting and stabilization, uninterruptible power supply, a sensor powering device and is designed to combine the input voltage of the on-board DC 27 V network from two independent channels of the power supply and filtering system, to generate secondary power supply voltages of the MPA modules 1, MVI 5, MSC 8 devices and sensors on-board equipment, to control the formation of secondary supply voltages and the issuance of a signal of serviceability of power.

The KLS 12 code line of communication is a channel uniting the MPA 1, MVI 5, and MSC 8 modules of the device.

The multiplex channel of information exchange MKIO 13 serves to interface the device with the information management system IMS 15.

The backup channel of information exchange MKIO 14 serves to interface the device with the information management system IMS 15 in the event of failure of the MKIO 13.

The information and control system 15 of the aircraft includes an integrated electronic display and alarm system, a control system for general aircraft equipment, on-board maintenance system, etc.

The inventive device operates as follows.

When power is supplied, the MP 11 module generates secondary supply voltages of the MPA 1, MVI 5, MSC 8 and onboard equipment sensors, monitoring the formation of secondary supply voltages.

Further, the device monitors its own operability and the on-board equipment connected to the device included in the ICM 15. In the case of an unsatisfactory control result, it stops further actions without setting a sign of serviceability; in the case of a successful control result, it switches to the normal operation mode.

In the process of functioning, the device periodically monitors its own operability with the formation of a serviceability signal in MVI 5 and its transmission via ICIE 13 and ICIE 14 to ICS 15.

Information from the sensors of on-board equipment in the form of analog signals (voltage, resistance, frequency, current) comes in MPA 1, and in the form of discrete signals, packed into words of one-time commands, and their parameters and in the form of a standard serial code in MVI 5.

N-functional logic blocks 2 each of which is connected to the corresponding n-control block 3 of the MPA 1 module provide normalization, conversion to digital code, calculation of the electrical characteristics of analog signals for transmission via CLS 13 to the MVI module 5.

The temperature compensator KT 4 compensates for the increased temperature of the cold junction of the device that occurs during operation and protects the device from overheating, thereby increasing its performance and reliability.

M-functional-logical blocks 6 each of which is connected to the corresponding m-control block 7 of the MVI module 5 process the digital code received from the MPA 1 on KLS 12, including checking the bits characterizing the completion of the conversion process, and the bits characterizing the correctness of the conversion, and also provide the ability to correct the digital code in order to compensate for errors in the measuring channel from the onboard equipment sensor to the device.

M-functional-logical blocks 6 of the MVI module 5 process discrete signals, packed into words of one-time commands, and their parameters.

The digital information received by MVI 5 is checked for reliability. Only reliable information is subject to further processing. The software of the MVI 5 module implements verification of the membership of a physical quantity value in the allowable measuring range taking into account the measurement error.

The processed information from MVI 5 via CLS 12 enters the power command module of MSC 8. MSC 8 generates control signals in the form of discrete commands to actuators of onboard equipment sensors.

The MP 11 power supply module receives, filters, and limits the input supply voltage of +27 V, supports the supply voltage during power failures for up to 200 ms of the device, and also forms the supply voltage of the sensors of the onboard equipment included in the ICS 15.

MP 11 is equipped with a protection and filtering channel with support for a supply voltage of up to 200 ms for supplying MPA 1, MVI 5, MSC 8 and a channel without support for supply voltage during dips for powering the output stages of relay power commands in the MSC 8 module.

The introduced MP 11 module ensures uninterrupted operation of the device during power failures, which increases the reliability of the device.

According to the results of self-monitoring, MVI 5 generates an integral signal “Serviceability” and issues it to IMS 15 according to MKIO 13 and MKIO 14.

Thus, the proposed configuration of the modules in the device provides higher integration of the elements included in the device, sufficient controllability and redundancy, guaranteeing trouble-free operation of the information management system.

Claims (1)

An information conversion device for an information management system, comprising an analog signal receiving module, consisting of n functional logic blocks, and an integrated computing module, consisting of k functional logical blocks, interacting with each other via a code line, characterized in that the receiving module analog signals contains n control units, each n functional-logical unit of the module for receiving analog signals is associated with a corresponding n control unit, the calculator module The integrated one contains k control units, each k functional-logical unit of the computational integrated module is connected to the corresponding k control unit, and the power command module consisting of m functional-logical units and m control units, each of which is associated with the corresponding m control unit, a temperature compensator associated with the analog signal receiving module, a power module associated with the analog signal receiving module, an integrated computing module and mod power command, and the analog signal receiving module, the integrated computing module and the power command module interact with each other via a code line, and the integrated computing module interacts with the aircraft’s information and control system via the primary and backup information exchange channels.

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