CN118113079A - Control device and method for pressure regulating system of cabin of branch civil passenger plane - Google Patents
Control device and method for pressure regulating system of cabin of branch civil passenger plane Download PDFInfo
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- CN118113079A CN118113079A CN202311767612.9A CN202311767612A CN118113079A CN 118113079 A CN118113079 A CN 118113079A CN 202311767612 A CN202311767612 A CN 202311767612A CN 118113079 A CN118113079 A CN 118113079A
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- 238000007689 inspection Methods 0.000 claims abstract description 3
- 238000004891 communication Methods 0.000 claims description 119
- 238000013523 data management Methods 0.000 claims description 27
- 238000012423 maintenance Methods 0.000 claims description 26
- 238000012545 processing Methods 0.000 claims description 9
- 238000001514 detection method Methods 0.000 claims description 4
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D16/00—Control of fluid pressure
- G05D16/20—Control of fluid pressure characterised by the use of electric means
- G05D16/2006—Control of fluid pressure characterised by the use of electric means with direct action of electric energy on controlling means
- G05D16/2013—Control of fluid pressure characterised by the use of electric means with direct action of electric energy on controlling means using throttling means as controlling means
- G05D16/2026—Control of fluid pressure characterised by the use of electric means with direct action of electric energy on controlling means using throttling means as controlling means with a plurality of throttling means
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Abstract
The invention provides a control device and a control method for a pressure regulating system of a cabin of a branch civil passenger plane, which structurally comprise an automatic control channel A, an automatic control channel B and a manual control channel, and structurally comprise two control single plates and other related components which are completely consistent in design. The automatic control channel A and the automatic control channel B have the same structure and are mutually redundant, the automatic redundancy wheel inspection control is carried out on the pressure regulating system of the cabin of the branch civil passenger aircraft, the manual control channel is independent of the two automatic control channels, and the pressure regulating system of the cabin of the branch civil passenger aircraft can be controlled manually according to an override instruction. The two automatic control channels perform data interaction through CCDL to realize the fault state identification and channel switching functions. The control device calculates and outputs the front exhaust valve and the rear exhaust valve instructions through the control logic according to the received information from the control panel of the cockpit and the avionic system, and uploads the states of the control device and the system to the avionic system to provide warning and indicating signals for pilots, so that the avionic system has high safety and high reliability, and simultaneously has economy and compactness.
Description
Technical Field
The invention relates to the technical field of control devices of cabin pressure regulating systems of branch civil airliners, in particular to a control device and a control method of a cabin pressure regulating system of a branch civil airliner.
Background
Branch civil airliners are usually small airliners below 100, mainly responsible for short distance passenger transportation in local areas or between small and medium cities, and have high requirements on economy and applicability.
The cabin pressure regulating system has the main functions of realizing the conditions of cabin pressure, cabin pressure difference and cabin pressure change rate by controlling the exhaust amount discharged outwards in the cabin of the aircraft, namely controlling the opening degrees of the front exhaust valve and the rear exhaust valve of the aircraft, so as to meet the physiological requirements of passengers, ensure the comfort and safety of the passengers and also ensure the safety of the aircraft structure.
The cabin pressure regulating system control device is a core control unit in the system, and the system control functions are all completed by the participation of the control device. At present, in the cabin pressure regulating system of the domestic branch civil airliner, the cabin pressure regulating system control device and method which are applicable to the branch civil airliner and have high safety and high reliability and simultaneously have economical efficiency and compactness are not available.
Disclosure of Invention
The purpose of the invention is that: based on the problems existing in the background technology, a control device and a control method for a pressure regulating system of a cabin of a branch civil passenger plane are provided. The invention improves the safety and reliability of the control device through the architecture design of the automatic and manual control channels with redundancy, and simultaneously takes into account the requirements of the branch civil airliner on economy and compactness in the form of a structure formed by two completely consistent control single boards.
The technical scheme of the invention is as follows: according to a first aspect of the present invention, a control device for a pressure regulating system of a cabin of a branch civil passenger aircraft is provided, wherein the control device is composed of an automatic control channel A, an automatic control channel B and a manual control channel in a structure; structurally consists of two control single boards and other related components which are completely consistent in design. The control board A comprises an automatic control channel A and a part of manual control channel circuits, the control board B comprises an automatic control channel B and a part of manual control channel circuits, and the manual control channel circuits on the control board A and the control board B form a manual control channel together; the automatic control channel A and the automatic control channel B are mutually redundant, the automatic redundancy wheel inspection control is carried out on the pressure regulating system of the cabin of the civil passenger aircraft on the branch line, and the manual control channel is independent of the two automatic control channels and can carry out manual control on the pressure regulating system of the cabin of the civil passenger aircraft on the branch line when the two automatic control channels simultaneously fail or the unit is switched to the manual control through the operation panel.
Further, the automatic control channel A comprises a power supply module, a CPU small system, a discrete input module, an analog input module, a 429 communication module, a CCDL communication module, a 422 communication module and a ground maintenance function module. The power supply module provides a processing power supply and a secondary power supply for each module; the discrete input module and the analog input module respectively receive a switching value signal and an analog value signal from a control panel of the cockpit, the 429 communication module receives system data from an avionics system, the 422 communication module receives state information from a front exhaust valve and a rear exhaust valve, and the CCDL communication module receives state information from another automatic control channel; the CPU small system receives external signals processed by the discrete input module, the analog input module, the 429 communication module and the 422 communication module, and sends a control instruction to the 429 communication module, sends a control instruction to the 422 communication module and sends state information to the CCDL communication module through logic operation and information storage; the ground maintenance function module is used for data communication with ground maintenance equipment during external maintenance.
Further, the automatic control channel B comprises a power supply module, a CPU small system, a discrete input module, an analog input module, a discrete output module, a 429 communication module, a CCDL communication module, a 422 communication module and a ground maintenance function module. The power supply module provides a processing power supply and a secondary power supply for each module; the discrete input module and the analog input module respectively receive a switching value signal and an analog value signal from a control panel of the cockpit, the 429 communication module receives system data from an avionics system, the 422 communication module receives state information from a front exhaust valve and a rear exhaust valve, and the CCDL communication module receives state information from another automatic control channel; the CPU small system receives external signals processed by the discrete input module, the analog input module, the 429 communication module and the 422 communication module, and sends a control instruction to the 429 communication module, sends a control instruction to the 422 communication module and sends state information to the CCDL communication module through logic operation and information storage; the ground maintenance function module is used for data communication with ground maintenance equipment during external maintenance.
Further, the manual control channel comprises a front exhaust valve manual control module and a rear exhaust valve manual control module; the front exhaust valve manual control module receives a manual control instruction signal from a control panel of the cockpit and sends a driving signal to the front exhaust valve; the manual control module of the rear exhaust valve receives a manual control command signal from a control panel of the cockpit and sends a driving signal to the rear exhaust valve.
Further, the automatic control channel A and the automatic control channel B are mutually redundant, the rear wheel is powered on each time of the control device to enter a main control state, the automatic control channel in the main control state is the main control channel, system data sent by a data management computer and a remote sensing unit of an avionics system and control instructions from a control panel of a cockpit are received, driving power sources are provided for a front exhaust valve and a rear exhaust valve through a discrete output module through logic operation, and the control instructions for the front exhaust valve and the rear exhaust valve are output in a 422 communication mode, so that the automatic control of the cockpit pressure regulating system is realized; the automatic control channel which is not in the main control state is a backup channel, and enters a hot backup state, namely, still receives data and performs logic operation, but does not output a control instruction unless a fault indication signal from the original main control channel is received through CCDL, and the automatic control channel is switched to the main control state. The manual control channel is independent of the two automatic control channels, only receives manual control instructions from a control panel of the cockpit, sends driving signals to the front exhaust valve and the rear exhaust valve according to the instructions, and manually controls the pressure regulating system of the cabin of the branch civil passenger aircraft.
Further, the automatic control channel A power supply module is connected with an external 28V power supply A and processes a secondary power supply required by the automatic control channel A, and the automatic control channel B power supply module is connected with an external 28V power supply B and processes a secondary power supply required by the automatic control channel B. The manual control channel is not provided with a power supply module, and the two automatic control channels are used for processing the combined 28V power supply and outputting the combined secondary power supply.
Further, the CPU small systems of the automatic control channel A and the automatic control channel B comprise a microprocessor, a clock circuit, a watchdog circuit and a storage circuit, wherein the microprocessor receives signal data processed by a discrete input module, an analog input module, a 429 communication module, a CCDL communication module and a 422 communication module, and sends out state information and control instructions through the 429 communication module, the CCDL communication module and the 422 communication module after logic operation; the clock circuit provides an external clock source for the microprocessor; the watchdog circuit is used for monitoring whether the microprocessor works normally or not, and when the microprocessor fails, the watchdog circuit can reset the microprocessor; the memory circuit is used for storing key signal data received and sent by the microprocessor.
Further, discrete input modules of the automatic control channel A and the automatic control channel B collect switching value signals from the operation panel of the cockpit.
Further, analog input modules of the automatic control channel A and the automatic control channel B collect analog quantity signals from the operation panel of the cockpit.
Further, the discrete output modules of the automatic control channel A and the automatic control channel B output driving power supplies for the front exhaust valve and the rear exhaust valve respectively.
Further, the 429 communication module of the automatic control channel A collects two paths of communication data from the first data management computer and the second data management computer, and one path of communication data from the first remote sensing unit and sends communication data related to the control device and the system to the first data management computer. The 429 communication module of the automatic control channel B collects two paths of communication data from the first data management computer and the second data management computer, and one path of communication data from the second remote sensing unit and sends communication data related to the control device and the system to the second data management computer.
Further, the 422 communication modules of the automatic control channel A and the automatic control channel B are simultaneously in communication connection with the front exhaust valve and the rear exhaust valve of the airplane, send valve control instructions and receive valve state information.
Further, the CCDL communication module of the automatic control channel A is connected with the CCDL communication module of the automatic control channel B, and is used for exchanging channel state information.
Further, the ground maintenance function modules of the automatic control channel A and the automatic control channel B are in communication connection with ground maintenance equipment.
Further, a front exhaust valve control module of the manual control channel is positioned on the control panel A, acquires switching value signals from the cockpit operation panel, and outputs corresponding direct current motor driving signals to the front exhaust valve of the aircraft according to the switching value signal state.
Further, a rear exhaust valve control module of the manual control channel is positioned on the control panel B, acquires switching value signals from the cockpit operation panel, and outputs corresponding direct current motor driving signals to the rear exhaust valve of the aircraft according to the switching value signal state.
According to a second aspect of the present invention, a control method for a pressure regulating system of a cabin of a branch civil passenger aircraft is provided, and the control device for the pressure regulating system of the cabin of the branch civil passenger aircraft is adopted, comprising the following steps:
Step 1: after the control device is electrified each time, the automatic control channel A and the automatic control channel B enter a main control state according to the previous state round. The automatic control channel in the main control state is the main control channel, receives the system data from the data management computer of the avionic system and the remote sensing unit and the control instruction from the control panel of the cockpit, obtains the opening of the target exhaust valve through logic operation, uses 422 communication mode, outputs the control instruction to the front exhaust valve and the rear exhaust valve, and simultaneously sends the state information of the channel to the backup channel through CCDL communication.
Step 2: the state information comprises a reset instruction of a channel, a mode state and a BIT self-checking result, wherein the reset instruction is sent by a watchdog circuit when a microprocessor in a CPU small system of the channel fails; the mode state indicates whether the channel is in a master control state; the self-checking result is an indication signal for judging whether the channel has faults or not according to BIT detection; when the self-checking result indicates a fault, the main control channel will go out of the main control state and send out a changed mode state; if the channel cannot rotate out of the master control state due to the failure of the microprocessor, the watchdog circuit will send out a reset instruction.
Step 3: the automatic control channel which is not in the main control state is a backup channel, and enters a hot backup state, namely, system data sent by a data management computer and a remote sensing unit of the avionics system is still received, the opening degree of the target exhaust valve is obtained through logic operation, but a control instruction is not output, a reset signal, a mode state and a self-checking result from the main control channel are received through CCDL, and when the reset signal of the main control channel is valid or the mode state is switched and the self-checking result indicates a fault, the backup channel is transferred into the main control state.
Step 4: the automatic control channel A and the automatic control channel B both send state indication signals to a data management computer of the avionics system through a 429 communication module, and the data management computer sends an alarm prompt after not receiving the state indication signals or receiving signals indicating that the state is faulty, so that the manual control needs to be switched.
Step 5: the manual control channel is independent of the two automatic control channels, and only receives a manual control selection signal, a front/rear exhaust valve opening instruction signal and a front/rear exhaust valve closing instruction signal from a control panel of the cockpit, wherein the manual instruction is sent by a crew member, and the manual control channel is activated after receiving the manual control selection signal, so that a driving signal is sent to the front exhaust valve and the rear exhaust valve according to a switching instruction; after receiving the manual control selection signal, the automatic control channel is switched into a hot standby state so as to realize the override function of manual control.
The invention has the beneficial effects that:
The invention provides a control device and a control method for a pressure regulating system of a cabin of a civil passenger aircraft on a branch line, wherein two control single boards which are completely consistent are arranged in the control device, so that the pressure regulating system of the cabin can realize double-redundancy automatic control and independent manual control override, and according to the received related information from a control panel of the cabin and an avionic system, the control device and the system state are uploaded to the avionic system through calculating and outputting a front exhaust valve command and a rear exhaust valve command through control logic, and an alarm and an indication signal are provided for a pilot. The control device has high safety and high reliability, and simultaneously has economical efficiency and compactness.
Drawings
FIG. 1 is an external cross-linked view of a control device to which the present invention is applied
FIG. 2 is a schematic block diagram of a control board of a control device to which the present invention is applied
Detailed description of the preferred embodiments
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1, a control device and a control method for a pressure regulating system of a cabin of a branch civil passenger aircraft mainly have the following functions:
a) The pressure state of the cabin and the input signals from the operation panel of the cockpit and avionic electricity are automatically collected, and the command signals of the valve are output through the calculation of the control logic to automatically control the pressure of the cabin and the pressure difference of the cabin.
B) And outputting a valve command signal according to an override command from the cockpit operation panel to manually control the pressure of the cockpit.
C) And automatically acquiring an emergency pressure release instruction signal from the operation panel of the cockpit, and sending an emergency pressure release related control instruction to the valve through control logic calculation.
D) The control method comprises the steps of automatically collecting a water forced landing command signal from a cockpit operation panel, and sending a water forced landing related control command to a valve through control logic calculation.
E) And monitoring faults in the cabin pressure regulating system and the control device through CCDL communication and sending indication and alarm signals to the avionics system.
In order to meet the requirements of high safety and high reliability of the cabin pressure control system, the control device adopts automatic dual redundancy control and independent manual control. Under normal conditions, the two automatic control channels are in a main control state, and the other automatic control channel which is not in the main control state works in a backup state; when one automatic control channel fails, the other automatic control channel takes over the main control and continues to work; when two automatic control channels simultaneously fail, the unit is switched to manual control through an operation panel, and the manual control channels output driving signals of the exhaust valves.
In order to meet the requirements of economy and compactness of the branch civil airliner, the control device consists of two control single boards which are completely consistent with each other and other related components, the control board A comprises an automatic control channel A and a part of manual control channel circuits, the control board B comprises an automatic control channel B and a part of manual control channel circuits, and the manual control channel circuits on the control board A and the control board B jointly form a manual control channel.
As shown in fig. 2, the automatic control channel a includes a power module, a CPU small system, a discrete input module, an analog input module, a 429 communication module, a CCDL communication module, a 422 communication module, and a ground maintenance function module. The automatic control channel B comprises a power supply module, a CPU small system, a discrete input module, an analog input module, a discrete output module, a 429 communication module, a CCDL communication module, a 422 communication module and a ground maintenance function module. The power supply module provides a processing power supply and a secondary power supply for each module; the discrete input module and the analog input module respectively receive a switching value signal and an analog value signal from a control panel of the cockpit, the 429 communication module receives system data from an avionics system, the 422 communication module receives state information from a front exhaust valve and a rear exhaust valve, and the CCDL communication module receives state information from another automatic control channel; the CPU small system receives external signals processed by the discrete input module, the analog input module, the 429 communication module and the 422 communication module, and sends a control instruction to the 429 communication module, sends a control instruction to the 422 communication module and sends state information to the CCDL communication module through logic operation and information storage; the ground maintenance function module is used for data communication with ground maintenance equipment during external maintenance.
The manual control channel comprises a front exhaust valve manual control module positioned on the control panel A and a rear exhaust valve manual control module positioned on the control panel B. The front exhaust valve manual control module receives a manual control instruction signal from a control panel of the cockpit and sends a driving signal to the front exhaust valve; the manual control module of the rear exhaust valve receives a manual control command signal from a control panel of the cockpit and sends a driving signal to the rear exhaust valve.
The power supply module of the automatic control channel A is connected with an external 28V direct current power supply 1, and the non-isolated secondary power supply required by the manual control channel is processed and output. The power supply module of the automatic control channel B is connected with an external 28V direct current power supply 2, and the non-isolated secondary power supply required by the manual control channel is processed and output, and in addition, the isolated secondary power supply required by the automatic control channel B is processed and output through isolation. The manual control channel is not provided with a power supply module, and the two automatic control channels are used for processing the combined 28V power supply and outputting the combined non-isolated secondary power supply. Besides the power supply conversion circuit, the power supply module also comprises an anti-reverse, surge suppression, filtering and power failure maintaining circuit for processing an external 28V direct current power supply.
The CPU small systems of the automatic control channel A and the automatic control channel B comprise a microprocessor, a clock circuit, a watchdog circuit and a storage circuit. The microprocessor receives signal data processed by the discrete input module, the analog input module, the 429 communication module, the CCDL communication module and the 422 communication module, and sends out state information and control instructions through the 429 communication module, the CCDL communication module and the 422 communication module after logic operation; the clock circuit provides an external clock source for the microprocessor; the watchdog circuit is used for monitoring whether the microprocessor works normally or not, and when the microprocessor fails, the watchdog circuit can reset the microprocessor; the memory circuit is used for storing key signal data received and sent by the microprocessor.
The discrete input modules of the automatic control channel A and the automatic control channel B collect switching value signals from the operation panel of the cockpit, wherein the switching value signals comprise emergency pressure release indication signals, water forced landing indication signals, manual control selection signals and landing airport altitude manual input selection signals. The module transmits these switching value signals to the microprocessor GPIO port of the CPU subsystem.
The analog input modules of the automatic control channel A and the automatic control channel B collect analog quantity signals from the operation panel of the cockpit, wherein the analog quantity signals are landing airport altitude input signals. The module demodulates the analog quantity signal and transmits the analog quantity signal to a microprocessor ADC interface of the CPU small system.
The discrete output modules of the automatic control channel A and the automatic control channel B respectively provide driving power for the front exhaust valve and the rear exhaust valve. The module outputs according to the instruction from the microprocessor, and when the channel receives the manual control selection signal, the module cuts off the output of the driving power supply to the exhaust valve.
The 429 communication module of the automatic control channel A collects two paths of communication data from a first data management computer and a second data management computer of the avionics system, one path of communication data from a first remote sensing unit, and sends communication data related to a control device and the system to the first data management computer. The 429 communication module of the automatic control channel B collects two paths of communication data from the first data management computer and the second data management computer of the avionics system, one path of communication data from the second remote sensing unit, and sends communication data related to the control device and the system to the second data management computer. The modules of each channel exchange information with the CPU small system microprocessor thereof through a serial transmission data bus.
The front exhaust valve control module of the manual control channel collects switching value signals from the cockpit operation panel, the switching value signals comprise a manual control selection signal, a front exhaust valve opening command signal and a front exhaust valve closing command signal, and the module outputs corresponding direct current motor driving signals to the front exhaust valve of the airplane according to the state of the switching value signals.
The rear exhaust valve control module of the manual control channel collects switching value signals from the operation panel of the cockpit, wherein the switching value signals comprise a manual control selection signal, a rear exhaust valve opening command signal and a rear exhaust valve closing command signal. The module outputs a corresponding direct current motor driving signal to the rear exhaust valve of the aircraft according to the state of the switching value signal.
In order to realize automatic dual-redundancy control and independent manual control of the control device, the control device needs to carry out redundancy allocation design of external signals, and the allocation principle is as follows:
a) The emergency pressure release indication signal, the water forced landing indication signal and the landing airport altitude manual input selection signal from the control panel of the cockpit are dual-redundancy switching value signals, and are respectively connected into an automatic control channel A of the control panel A and an automatic control channel B of the control panel B. After the two automatic control channels are processed, data interaction is carried out through CCDL.
B) The manual control selection signal from the control panel of the cockpit is a dual-redundancy switching value signal, and is respectively connected with an automatic control channel A of a control panel A, a manual control module of a front exhaust valve, an automatic control channel B of a control panel B and a manual control module of a rear exhaust valve. After the two automatic control channels are processed, data interaction is carried out through CCDL, the back-up state is carried out, and after each module of the manual control channel receives the signal, each module of the manual control channel respectively enters the enabling state.
C) The front exhaust valve opening command signal and the front exhaust valve closing command signal from the control panel of the cockpit are single redundancy switching value signals, and are connected to the front exhaust valve manual control module of the control panel A, and the module outputs corresponding direct current motor driving signals according to the received commands.
D) The rear exhaust valve opening command signal and the rear exhaust valve closing command signal from the control panel of the cockpit are single redundancy switching value signals, and are connected to the rear exhaust valve manual control module of the control panel B, and the module outputs corresponding direct current motor driving signals according to the received commands.
E) The maintenance signals are respectively connected into the automatic control channel A and the automatic control channel B by adopting a dual redundancy design, so that false triggering of a maintenance state is prevented. The manual control channel is not provided with a microprocessor, and maintenance is not required.
F) Each automatic control channel receives a dual redundancy transmission signal from a data management computer of the avionics system; the receiving end of the data management computer from the avionics system and the remote sensing unit are in one-to-one correspondence with the automatic control channel.
The automatic control channel switching and manual control channel override logic of the control device is as follows:
a) After the control device is powered on and initialized, the control device enters an automatic control mode, and two automatic control channels are a main control-hot backup framework. Under normal conditions, two automatic control channels enter a main control state according to ground state rounds, and the other control channel which is not in the main control state works in a hot standby state. The two control channels all receive relevant system data from a data management computer of the avionics system and a remote sensing unit and control instructions from a control panel of the cockpit, the current target cabin pressure is obtained through logic operation, then the opening of a target exhaust valve is calculated according to the target flow, and the control instructions of a front exhaust valve and a rear exhaust valve are output in a 422 communication mode.
B) And information interaction is carried out between the two control channels through CCDL, and interaction information comprises reset indication, mode state and BIT self-checking result. The reset instruction is sent by a watchdog circuit when a microprocessor in a CPU small system of the channel fails; the mode state indicates whether the current channel is in a master control state; the BIT self-checking result indicates the self-checking condition of the power supply module, the CPU small system, the discrete input module, the analog input module, the discrete output module, the 429 communication module, the CCDL communication module and the 422 communication module of the channel, and when the automatic control channel of the main control state is judged to be a fault according to BIT detection, the channel will transfer out of the main control state, update the mode state signal and send out. If the channel fails to go out of master due to a microprocessor failure, the watchdog circuit will issue a reset indication.
C) The automatic control channel in the hot standby state does not output a control command, but still carries out information interaction with the avionics system through the 429 communication module and the automatic control channel in the main control state through the CCDL. When the automatic control channel in the hot standby state receives the valid reset signal of the main control channel through the CCDL or the mode state of the main control channel is switched and the self-checking result indicates a fault, the automatic control channel will be switched to the main control state, and the control command is output through the 422 communication module, so that the control device is ensured to work continuously.
D) The automatic control channel A and the automatic control channel B both transmit a state indication signal to a data management computer of the avionics system through a 429 communication module, and after the data management computer does not receive the state indication signal or receives a signal indicating that the state is faulty, the data management computer prompts a crew member through a crew member alarm system, and the crew member can operate a control panel of the cockpit to switch to manual control.
E) After the crew sends out manual control selection signals through the control panel of the cockpit, the automatic control channel is switched into a hot standby state, the control command is stopped being output through the 422 communication module, the input of the driving power supply of the respective exhaust valve is cut off, the information interaction is still carried out with the avionics system through the 429 communication module, and the fault detection and alarm functions are reserved.
F) When the crew sends out manual control selection signals through the control panel of the cockpit, the manual control channel is activated, and the manual control channel is independent of the two automatic control channels and only receives the manual control selection signals, the front/rear exhaust valve opening command signals and the front/rear exhaust valve closing command signals from the control panel of the cockpit, so that driving signals are sent to the front exhaust valve and the rear exhaust valve according to the switching commands, and the override function of manual control is realized.
Claims (8)
1. A control device of a pressure regulating system of a cabin of a branch civil passenger plane is characterized in that the control device is structurally composed of an automatic control channel A, an automatic control channel B and a manual control channel; the structure is composed of two control single boards A and B which are completely consistent in design; the control single board A comprises an automatic control channel A and a part A manual control channel circuit, the control single board B comprises an automatic control channel B and a part B manual control channel circuit, and the part A manual control channel circuit and the part B manual control channel circuit form a manual control channel; the automatic control channel A and the automatic control channel B are mutually redundant, the automatic redundancy wheel inspection control is carried out on the pressure regulating system of the cabin of the civil passenger aircraft on the branch line, and the manual control channel is independent of the two automatic control channels and can carry out manual control on the pressure regulating system of the cabin of the civil passenger aircraft on the branch line when the two automatic control channels simultaneously fail or the unit is switched to the manual control through the operation panel.
2. The control device of the pressure regulating system of the cabin of the branch civil passenger aircraft according to claim 1, wherein the automatic control channel A comprises a power supply module, a CPU small system, a discrete input module, an analog input module, a 429 communication module, a CCDL communication module, a 422 communication module and a ground maintenance function module; the power supply module provides a processing power supply and a secondary power supply for each module; the discrete input module and the analog input module respectively receive a switching value signal and an analog value signal from a control panel of the cockpit, the 429 communication module receives system data from an avionics system, the 422 communication module receives state information from a front exhaust valve and a rear exhaust valve, and the CCDL communication module receives state information from another automatic control channel; the CPU small system receives external signals processed by the discrete input module, the analog input module, the 429 communication module and the 422 communication module, and sends a control instruction to the 429 communication module, sends a control instruction to the 422 communication module and sends state information to the CCDL communication module through logic operation and information storage; the ground maintenance function module is used for data communication with ground maintenance equipment during external maintenance.
3. The control device of the pressure regulating system of the cabin of the branch civil passenger aircraft according to claim 1, wherein the automatic control channel B comprises a power supply module, a CPU small system, a discrete input module, an analog input module, a discrete output module, a 429 communication module, a CCDL communication module, a 422 communication module and a ground maintenance function module; the power supply module provides a processing power supply and a secondary power supply for each module; the discrete input module and the analog input module respectively receive a switching value signal and an analog value signal from a control panel of the cockpit, the 429 communication module receives system data from an avionics system, the 422 communication module receives state information from a front exhaust valve and a rear exhaust valve, and the CCDL communication module receives state information from another automatic control channel; the CPU small system receives external signals processed by the discrete input module, the analog input module, the 429 communication module and the 422 communication module, and sends a control instruction to the 429 communication module, sends a control instruction to the 422 communication module and sends state information to the CCDL communication module through logic operation and information storage; the ground maintenance function module is used for data communication with ground maintenance equipment during external maintenance.
4. The control device of the pressure regulating system of the cabin of the branch civil passenger aircraft according to claim 1, wherein the manual control channel comprises a front exhaust valve manual control module and a rear exhaust valve manual control module; the front exhaust valve manual control module receives a manual control instruction signal from a control panel of the cockpit and sends a driving signal to the front exhaust valve; the manual control module of the rear exhaust valve receives a manual control command signal from a control panel of the cockpit and sends a driving signal to the rear exhaust valve.
5. The control device of the pressure regulating system of the cabin of the branch civil passenger aircraft according to claim 1, wherein the power supply module of the automatic control channel A is connected with an external 28V power supply A and processes a secondary power supply required by the automatic control channel A, and the power supply module of the automatic control channel B is connected with an external 28V power supply B and processes a secondary power supply required by the automatic control channel B; the manual control channel is not provided with a power supply module, and the two automatic control channels are used for processing the combined 28V power supply and outputting the combined secondary power supply.
6. A control device for a pressure regulating system in a cabin of a branch civil passenger aircraft according to any one of claims 2 or 3, wherein the CPU subsystem of the automatic control channel a and the automatic control channel B comprises a microprocessor, a clock circuit, a watchdog circuit and a memory circuit, the microprocessor receives signal data processed by a discrete input module, an analog input module, a 429 communication module, a CCDL communication module and a 422 communication module, performs logic operation, and sends status information and control instructions through the 429 communication module, the CCDL communication module and the 422 communication module; the clock circuit provides an external clock source for the microprocessor; the watchdog circuit is used for monitoring whether the microprocessor works normally or not, and when the microprocessor fails, the watchdog circuit can reset the microprocessor; the memory circuit is used for storing key signal data received and sent by the microprocessor.
7. The control device of a pressure regulating system of a cabin of a branch civil passenger aircraft according to claim 1, wherein a front exhaust valve control module of a manual control channel is positioned on a control single board A, collects switching value signals from an operation panel of the cabin, and outputs corresponding direct current motor driving signals to a front exhaust valve of the aircraft according to the state of the switching value signals; the rear exhaust valve control module of the manual control channel is positioned on the control single board B, acquires switching value signals from the cockpit operation panel, and outputs corresponding direct current motor driving signals to the rear exhaust valve of the aircraft according to the switching value signal state.
8. A control method of a pressure regulating system of a branch line civil passenger aircraft cabin, characterized in that a pressure regulating system control device of a branch line civil passenger aircraft cabin according to any one of the preceding claims 1-7 is used, comprising the steps of:
Step 1: after the control device is electrified each time, the automatic control channel A and the automatic control channel B enter a main control state according to the previous state round; the automatic control channel in the main control state is a main control channel, receives system data sent by a data management computer and a remote sensing unit of an avionic system and a control instruction from a control panel of a cockpit, obtains the opening of a target exhaust valve through logic operation, outputs control instructions for a front exhaust valve and a rear exhaust valve in a 422 communication mode, and simultaneously sends state information of the channel to a backup channel through CCDL communication;
Step 2: the state information comprises a reset instruction of a channel, a mode state and a BIT self-checking result, wherein the reset instruction is sent by a watchdog circuit when a microprocessor in a CPU small system of the channel fails; the mode state indicates whether the channel is in a master control state; the self-checking result is an indication signal for judging whether the channel has faults or not according to BIT detection; when the self-checking result indicates a fault, the main control channel will go out of the main control state and send out a changed mode state; if the channel cannot rotate out of the main control state due to the fault of the microprocessor, the watchdog circuit sends out a reset instruction;
Step 3: the automatic control channel which is not in the main control state is a backup channel, the system data sent by a data management computer and a remote sensing unit of the avionics system is still received, the opening degree of the target exhaust valve is obtained through logic operation, but a control instruction is not output, a reset signal, a mode state and a self-checking result from the main control channel are received through CCDL, and when the reset signal of the main control channel is valid or the mode state is switched and the self-checking result indicates a fault, the backup channel is switched into the main control state;
step 4: the automatic control channel A and the automatic control channel B both send state indication signals to a data management computer of the avionics system through a 429 communication module, and the data management computer sends an alarm prompt after not receiving the state indication signals or receiving signals indicating that the state is faulty, so that the manual control needs to be switched;
Step 5: the manual control channel is independent of the two automatic control channels, and only receives a manual control selection signal, a front/rear exhaust valve opening instruction signal and a front/rear exhaust valve closing instruction signal from a control panel of the cockpit, wherein the manual instruction is sent by a crew member, and the manual control channel is activated after receiving the manual control selection signal, so that a driving signal is sent to the front exhaust valve and the rear exhaust valve according to a switching instruction;
After receiving the manual control selection signal, the automatic control channel is switched into a hot standby state so as to realize the override function of manual control.
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| CN202311767612.9A CN118113079A (en) | 2023-12-21 | 2023-12-21 | Control device and method for pressure regulating system of cabin of branch civil passenger plane |
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| CN202311767612.9A CN118113079A (en) | 2023-12-21 | 2023-12-21 | Control device and method for pressure regulating system of cabin of branch civil passenger plane |
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