RU2617160C1 - Aircraft air conditioning system control - Google Patents

Abstract

FIELD: ventilation.

SUBSTANCE: aircraft air-conditioning system control device comprises a transformation module and the computing module power command loop control air flow, the module power command temperature control loop mode control unit air conditioning, on-board computer system, and a control bidirectional multiplex bus information exchange. All the modules contain main channel and the control, respectively, and power module and control means.

EFFECT: increase the operational safety of the aircraft, the reliability, and validity of information formed in any configuration of air-conditioning systems.

2 cl, 1 dwg

Description

The invention relates to aircraft and is intended for use in the implementation of the control and monitoring functions of the air conditioning system (SLE) of an aircraft (l.a.).

Air conditioning systems They are used to create normal climatic conditions for the life and work of the crew and passengers, as well as the reliable operation of various aircraft devices.

So, for example, sudden changes in pressure can cause decompression sickness, prolonged exposure to elevated or lowered temperatures leads to serious physiological disturbances, increased humidity leads to the inability of the body to maintain normal body temperature.

By production of modern L.A. more and more often composite materials (composites) are used, the specific strength and rigidity of which surpasses traditional metal structural materials. However, the use of composites imposes higher requirements on air conditioning systems, as during operation, composites may not withstand the high temperatures that may result from depressurization of the air intake subsystem from L.A. engines, which may lead to destruction of structural elements of L.A.

Air conditioning systems for aircraft have recently become much more complicated due to increased speed, altitude and range, and have become more sophisticated - their weight and dimensions have decreased. The use of composites in the production of L.A. makes higher demands on the reliability of hard currency systems, in particular its tightness, and, consequently, on the hard drive control device.

Modern hard currency include numerous sensors, instruments and assemblies that carry out the complex of work necessary to maintain the level of comfort and safety on the L.A.

SLE operate in an automatic control mode, which imposes special requirements for control suitability, reducing the time of overshoot and reducing the time of maintenance.

The requirements for modern SCR are such that it is necessary to carry out comprehensive control and monitoring of all sensors and assemblies that make up the system centrally and universally, assuming the scalability of the functions performed, while at the same time maintaining independence from other general aircraft systems.

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.

In addition to receiving and converting into a digital format information received from sensors and assemblies that are part of the system, generating 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 health signal to the paired equipment, as well as the ability adaptation to various options for completing complexes of airborne equipment.

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

The invention consists in the following.

The task to be solved by the claimed invention is directed is to increase the safety of operation of the air conditioner, increase the reliability, increase the reliability of the generated information, and adapt it to various configuration options for hard currency.

The technical result consists in increasing the safety of the operation of the HP, increasing the reliability, increasing the reliability of the generated information of the inventive device, as well as the possibility of adaptation to various options for the configuration of hard currency.

The specified technical result is achieved by the fact that the control device of the air conditioning system of the aircraft contains a conversion and calculation module, consisting of a main conversion and calculation channel associated with the corresponding power module, and a control conversion and calculation channel associated with the corresponding power module, a power command module air flow control circuit, consisting of the main channel of the power commands of the air flow control circuit, containing ate protection and associated with the corresponding power supply module and the control channel of the power command of the air flow control circuit containing the protection unit and connected to the corresponding power supply module, the power command module of the temperature control circuit, consisting of the main channel of the power command of the temperature control circuit containing the protection unit and associated with the corresponding power supply module, and the control channel of the power commands of the temperature control loop, containing the protection unit and associated with the corresponding power supply module, an air conditioning system mode control module, consisting of a main channel for controlling the air conditioning system modes associated with the corresponding power module, and a control channel for controlling the air conditioning system modes associated with the corresponding power module, the main channel of transformations and calculations of the transform module and calculations, the main channel of the power command module of the air flow control loop, the main channel of the power command module temperature control loop, the main channel of the air conditioning mode control module interact on the main bidirectional multiplex bus for information exchange, and the control channel of transformations and calculations of the conversion and calculation module, the control channel of the power command module of the air flow control circuit, the control channel of the power command module of the temperature control loop , the control channel of the air conditioning system control module interact by Multiplex bidirectional bus control information exchange, and wherein the main control unit changes the channels and computing power module commands air flow control loop, the power module commands the temperature control circuit and the mode control module air conditioning systems contain embedded control means.

The essence of the invention is illustrated by the following drawing.

In FIG. 1 is a structural diagram where

1 - module transformations and calculations, containing

2 - the main channel of transformations and calculations,

3 - power module,

4 - control channel of transformations and calculations,

5 is a power command module air flow control circuit containing

6 - node protection

7 - the main channel of the power commands of the air flow control circuit,

8 - control channel power commands circuit control air flow,

9 - module power commands circuit temperature control, containing

10 - the main channel of the power commands of the temperature control loop,

11 - control channel power commands circuit temperature control,

12 - module management of SLE modes, containing

13 - the main channel for controlling SLE modes,

14 - control channel for controlling SLE modes,

15 - the main bi-directional multiplex bus data exchange,

16 - control bidirectional multiplex bus data exchange,

17 - sensors and assemblies of hard currency,

18 - on-board computer system.

The control device for the air conditioning system of the aircraft performs:

- control and management of units of the air flow control circuit;

- control and management of units of the temperature control loop;

- reception and conversion into a digital code of signals in the form of analog and discrete parameters from SLE sensors;

- logical processing of incoming information according to the specified control algorithms for hard currency;

- information exchange with the onboard computer system;

- protection of actuators and aircraft feeder from all types of overloads;

- control of the SCR of the aircraft, including the control of the sensors of SLE and the control of the tightness of the pipelines of SLE;

- the formation, accumulation, storage in non-volatile memory and the issuance of operational information about the state and failures of SLE of the engine to the ground-based equipment;

- self-control provided by the built-in control tools contained in each channel of each device module.

As noted above, the device is built on a modular basis, so the conversion and calculation module 1 consists of the main and control conversion and calculation channels 2 and 4, respectively, each of which is connected to the corresponding power module 3. Each channel independently and independently performs switching and normalization of analog signals from sensors SLE 17 with their further conversion to digital form, receiving frequency signals, receiving synchronization signals and generating control signals, the formation of reference t Cove for measuring resistances and output control currents, voltage and frequency standards holding own performance control signal from the issuance of serviceability, as well as the logical processing and control reliability of data signals.

Information from the SCR sensors 17, processed in the main channel of transformations and calculations 2, through the main bidirectional multiplex bus of the information exchange 15 and information processed in the control channel of transformations and calculations 4, through the control bi-directional multiplex bus of the information exchange 16 is transmitted to the control module of the SCR 12 , where it is compared with the specified modes of functioning of hard currency.

Power module 3 contains devices for protecting and filtering, limiting and stabilizing voltage, uninterrupted power, a power supply device for SCR sensors, and is designed to combine input power supply voltages from two independent channels of the power supply and filtering system to generate secondary voltages of each channel in the device module and sensors SLE, to control the formation of secondary supply voltages and the issuance of a signal of serviceability of power.

The power command module of the air flow control circuit 5 consists of the main channel of the air flow control circuit 7 and the control channel of the air flow control circuit 8, each of which is connected to the corresponding power module 3. The power command circuit of the air flow control circuit 5 generates power control signals by information received from the mode control module 12 on the main bidirectional multiplex information exchange bus 15 and the control bidirectional multiplex the data exchange bus 16, and generates direct-type control signals by input discrete signals in the event of a failure of the device or the interfaced equipment with the air flow control circuit. Each channel of the air flow control circuit has a protection unit 6, which protects the currents and voltages of the units of the SCR system itself, as well as the aircraft feeder, which provides automatic shutdown when the set protection tripping values are exceeded.

The power command module of the air flow control circuit 5 interacts with other device modules via the main bidirectional multiplex information exchange bus 15 and the control bi-directional multiplex information exchange bus 16, and also controls the units of the air flow control circuit.

The protection unit 6 is designed to automatically determine the permissible values of the current and voltage consumed by the SCR units, and in case of exceeding the permissible values, it turns off the corresponding channel of the control module.

The power command module of the temperature control loop 9 consists of the main channel of the temperature control loop 10 and the control channel of the temperature control loop 11, each of which is connected to the corresponding power module 3. The power command module of the temperature control loop 9 generates power control signals according to information received from the control module modes 12 on the main bidirectional multiplex bus information exchange 15 and the control bidirectional multiplex bus no exchange of information 16 and generates a direct-type control signals from the input discrete signals in the case of a device failure or the counter-temperature control circuit equipment. Each channel of the temperature control loop has a protection unit 6, which protects the current and voltage of the actuators of the SCR system itself, as well as the aircraft feeder, which provides automatic shutdown when the set protection tripping values are exceeded.

The power command module of the temperature control loop 9 interacts with other modules of the device via the main bidirectional multiplex information bus 15 and the control bidirectional multiplex data bus 16, and also controls the units of the temperature control loop.

SLE mode control module 12 consists of a main SLE mode control channel 13 and a SLE mode control channel 14, each of which is connected to the corresponding power module 3. Each channel, independently of the other, implements the specified algorithms for calculating and controlling other device modules, as well as exchanges information on the main bidirectional multiplex bus information exchange 15 and the control bidirectional multiplex bus data exchange 16 with the onboard computer Lex 18.

Independent channels of the SCR 12 mode control module carry out constant channel-by-channel comparison of the converted and calculated information received from the conversion and calculation module 1. Constant channel-by-channel comparison guarantees the absence of false control commands, which ensures the reliability of the received information from the sensors and units of the SCR 17.

The device modules, depending on the purpose and nature of the processed information, form two control loops. This is necessary in order to provide the necessary dynamics for controlling the units of the air flow control circuit and the temperature control circuit, depending on the laws of gas dynamics of the engines.

The air flow control circuit includes a conversion and calculation module and the power command module of the air flow control circuit and provides the necessary dynamics of the control process associated with the gas dynamics of the L.A. engines. and physical properties of air.

The temperature control loop includes a conversion and calculation module, a hard-drive mode control module, and a power command module for the temperature control and hard-drive modes and provides comfortable conditions for the crew and passengers of the aircraft, as well as monitoring the technical condition of all components of the hard-drive system, including integrity and tightness of pipelines, serviceability of sensors, assemblies, etc.

The main bi-directional multiplex bus information exchange 15 is used for the interaction of the main channels included in the modules of this device.

The control bidirectional multiplex bus information exchange 16 is used for the interaction of control channels included in the modules of this device.

SLE sensors 17 are various devices for measuring pressure, temperature, flow, etc., and SLE units are various electromechanical drives.

On-board computer complex 18 is a computer system that ensures the operation and interaction of on-board equipment

The inventive device operates as follows.

When power is supplied, power modules 3 generate secondary power voltages for each of the channels of the conversion and calculation modules 1, power command module of the air flow control loop 5, power command module of the temperature control loop 8 and mode control module 13 and sensors and units of SCR 17, monitoring the formation secondary supply voltages.

Next, the SLE 13 mode control module monitors its own operability and the operability of the sensors and SLE units 17. In the case of an unsatisfactory control result, it stops further actions without setting a sign of serviceability; in 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 health signal in the mode control module 13 and its transmission to the on-board computer complex 18.

Information from SCR sensors 17 in the form of analog signals (voltage, resistance, frequency, current) in the form of discrete signals, packed into words of one-time commands, and their parameters, as well as in the form of a standard serial code, enters the main channel of transformations and calculations 2 and control channel of transformations and calculations 4 module of transformations and calculations 1.

The main channel of transformations and calculations 2 and the control channel of transformations and calculations 4 of the module of transformations and calculations 1 provide normalization, conversion to digital code, calculation of the electrical characteristics of analog signals for transmission on the main bi-directional multiplex bus for information exchange 15 and control bi-directional multiplex bus for information exchange 16 v SLE mode control module 12.

All incoming information is converted and calculated in parallel in the main channel of transformations and calculations 2 and the control channel of transformations and calculations 4 - this is necessary in order to ensure the reliability of the information received in order to ensure the safety of operation of the la

The main channel for controlling the SLE modes 13 and the control channel for controlling the SLE modes 14 of the module for controlling the SLE modes 12 carry out the processing of information received from the conversion and calculation module 1. The received information is checked for reliability. Only reliable information is subject to further processing. The software of the SCR 12 mode control module implements verification of the belonging of the measured parameter value to the allowable measurement range taking into account the measurement error and comparison of information received from the main control channel and the control control channel.

The SCR 12 mode control module, based on the processed information and in accordance with the selected mode, controls the main bidirectional multiplex information exchange bus 15 and the control bidirectional multiplex information exchange bus 16 by the power flow control circuit module 5 and the temperature control circuit power command module 9. Module power commands circuit air flow 5 generates control signals of the units of the circuit air flow, and the module power commands circuit temperature control 9 generates control signals to units of temperature control circuit.

The power module 3 introduced into each channel of each module ensures uninterrupted operation of the device during power failures, which increases the reliability of the device.

Based on the results of self-monitoring by each channel of each device module, the SLE 13 mode control module generates the “Serviceability” integral signal and issues it to the on-board computer complex 18.

Thus, the proposed configuration of the modules and the channel-by-channel construction of each module in the device implies a higher integration of the elements included in the device, sufficient controllability and redundancy, ensuring trouble-free operation of the air conditioning system.

Claims (2)

1. The control device of the air conditioning system of the aircraft, containing a module of analog signals, a module for receiving and transmitting serial codes, a module for controlling and collecting data, characterized in that the module of analog signals, a module for transmitting and transmitting serial codes, a control and data collection module are integrated into a transform and computation module, wherein the transform and computation module consists of a main transform and computation channel associated with the corresponding power supply module, and The control channel of transformations and calculations associated with the corresponding power supply module introduces the power command module of the air flow control circuit, consisting of the main power command channel of the air flow control circuit containing the protection unit and connected to the corresponding power module, and the control channel of the power command of the flow control circuit air containing the protection unit and connected to the corresponding power module, power command module of the temperature control loop, consisting of the basics power channel of the temperature control loop containing the protection node and connected to the corresponding power module, and the control channel of the temperature control loop containing the protection node and connected to the corresponding power module, the air conditioning system control module, consisting of the main mode control channel the air conditioning system associated with the corresponding power supply module and the control channel for controlling the air conditioning system the air connected with the corresponding power supply module, the main channel of transformations and calculations of the conversion and computation module, the main channel of the power command module of the air flow control circuit, the main channel of the power command module of the temperature control loop, the main channel of the air conditioning system control module interact bidirectional multiplex bus of information exchange, and the control channel of transformations and calculations of the module of transformations and subtraction lining, the control channel of the power command module of the air flow control loop, the control channel of the power command module of the temperature control loop, the control channel of the air conditioning system control module interact on a bidirectional multiplex information exchange bus. 2. The control device for the air conditioning system of the aircraft according to claim 1, characterized in that the main and control channels of the conversion and calculation module, the power command module of the air flow control circuit, the power command module of the temperature control loop and the air conditioning system mode control module means of control.

Images