CN110182384B - Electrical system display simulator and method and aircraft power system comprehensive test system - Google Patents

Abstract

The present invention provides an electrical system display simulator and method and an aircraft power system comprehensive test system, the electrical system display simulator includes an EPS state information receiving unit, collects the state information of the power system, and transmits the state information of the power system to Simplified diagram page display unit; the status information includes generator power, output voltage and frequency, bus voltage and current acquisition fluctuation range; simplified diagram page display unit, according to the status information of the power system transmitted by the EPS status information receiving unit through logic Calculate and generate a simplified diagram page for display; unit alarm system display unit. The beneficial effects of the invention are as follows: the "three birds" joint debugging condition is created, that is, the ground test requirements of the aircraft power system can be completed only when the power system exists.

Description

Electrical system display simulator and method, and aircraft electrical system comprehensive test system

technical field

The invention belongs to the technology of performing ground test (MC5) in the operating state of an aircraft power system, and in particular relates to an electrical system display simulator and method and an aircraft power system comprehensive test system.

Background technique

In the past, the ground test of my country's aircraft power system was a separate test of the power system, which did not require the cooperation of other systems of the aircraft, such as information cross-linking of avionics, hydraulic systems, etc. This is because in the top-level design of the aviation power system platform, Traditional aircraft are in three mixed energy modes of hydraulic energy, pneumatic energy and electric energy, each of which operates independently, and the electric system can operate normally and meet the test requirements without the need for other systems. With the introduction of "multi-electric/all-electric aircraft" technology, the use efficiency of hydraulic energy and pneumatic energy is low, reliability and vitality cannot be guaranteed, and electric energy tends to gradually replace the other two energy sources. The result is that the power system is normal. The operation must rely on the information cross-linking of avionics, hydraulic systems and other systems, so the test centered on the power system will inevitably require the cooperation of all aircraft systems to complete, resulting in low resource utilization efficiency and slow test progress.

Contents of the invention

The problem to be solved by the present invention is that in the ground test technology of the aircraft electric power system, the actual avionics system (i.e. the electric bird) and the flight control hydraulic system (i.e. Iron bird) cooperation (information cross-linking, that is, the power system needs to receive the signal of the electric bird and the iron bird).

In order to solve the problems in the prior art, the present invention provides an electrical system display simulator, which integrates the signal monitoring and alarm functions of the electric bird to judge the test results of the electric system and the information input function of the cross-linking information of the electric bird, the iron bird and the electric power system , including an EPS status information receiving unit, collecting status information of the power system, and transmitting the status information of the power system to the schematic page display unit; the status information includes generator power, output voltage and frequency, bus voltage and Fluctuation range of current acquisition; the simplified diagram page display unit, which simulates the signal monitoring function of the electric bird, performs logical calculation according to the state information of the power system and generates a simplified diagram page for display; the unit alarm system display unit, which simulates the alarm of the electric bird The function is to compare the status information of the power system with the given threshold value of the status information of the power system, and determine the warning level according to the comparison result and display it in text form; the signal simulation unit simulates the signals of the avionics system and the hydraulic system, It adopts a virtual operation interface and realizes it through the application software running on the computer. When it is triggered, it calculates the operating status of the power system according to the logic relationship defined by AICD and sends it to the remote power management system.

Preferably, it also includes an EPS status information sending unit, which receives the status information of the power system transmitted by the EPS status information receiving unit, and transmits the status information of the power system to the flight control system.

Preferably, the EPS status information receiving unit includes an acquisition circuit and a data acquisition board; the acquisition circuit collects the status information of the power system, and transmits the status information of the power system to the schematic page display unit through logical processing through the data acquisition board.

Preferably, the signal simulation unit includes a relay board; the signals for simulating the avionics system and the hydraulic system include simulating the APU control switch, APU ready to load, APU start enable, left generator fuel cut-off, left generator ignition switch, right generator More than one signal of fuel cutoff, right generator ignition switch, primary electromechanical power controller airspeed, backup electromechanical power controller airspeed, generator N2 speed, landing gear status, left and right fire handle status and current airspeed , transmitting the analog signal to the remote power management system through the relay board.

The invention also discloses an aircraft power system comprehensive test system, which includes a power system and a remote power management system, and also includes the above-mentioned electrical system display simulator, and the electrical system display simulator sends the operating status of the power system to the remote power management system system, the remote power management system receives the operating status of the power system and converts it into a control command and sends it to the power system. The power system operates according to the control command. displayed in the form.

The present invention also discloses a testing method, which is applied to the aforementioned electrical system display simulator, comprising the following steps:

Receive the user operation command to trigger the signal simulation unit, and the generated simulation signal calculates the operating status of the power system according to the logic relationship defined by AICD and sends it to the remote power management system;

Collecting state information of the power system, the state information of the power system includes the power of the generator, output voltage and frequency, bus voltage and current collection fluctuation range;

The status information of the power system is logically calculated and displayed in the form of a simplified diagram page;

The status information of the power system is compared with a given threshold value of the status information of the power system, and the warning level is determined according to the comparison result to generate a text form for display.

Preferably, the operating state of the power system includes: a generator starting state and a non-starting state, and the generator includes a left generator, a right generator, and an APU generator.

Preferably, logical calculations are defined as follows:

When the electrical system displays that the simulator sends the starting status of the generator to the remote power management system, if the electrical system displays that the fluctuation range of the status information of the power system collected by the simulator is less than 3%, the status information of the corresponding power system is in the normal mode;

When the electrical system displays that the simulator sends the starting status of the generator to the remote power management system, if the electrical system displays that the state information of the power system collected by the simulator fluctuates by more than 3%, the state information of the corresponding power system is a failure mode;

Or when the electrical system displays that the simulator sends the generator non-start status to the remote power management system, if the electrical system displays that the generator power, output voltage and frequency collected by the simulator have feedback information, the corresponding generator power and output Voltage and frequency for failure mode;

When the electrical system displays that the simulator sends the generator non-start status to the remote power management system, if the electrical system displays no feedback information on the power, output voltage and frequency of the generator collected by the simulator, the corresponding generator power and output voltage and frequency, bus voltage and current are non-starting modes;

The status information of the power system includes the power, output voltage and frequency of the generator, the temperature, voltage and current of the storage battery, the output voltage and current of the transformer rectifier, and the bus voltage and current.

Preferably, the status information of the power system is compared with a given threshold value of the status information of the power system, and determining the level of the warning according to the comparison result to generate a text form for display includes:

When the comparison result is that there are signals for the given generator power, output voltage and frequency, and the generator power, output voltage and frequency are zero, it is determined that the warning level of the corresponding generator is the highest level, and the warning is generated and displayed in text form;

When the comparison result is that there is no signal for the given generator power, output voltage and frequency, and the generator power, output voltage and frequency have feedback information, it is determined that the corresponding generator warning level is the highest level, and the warning is generated and displayed in text form;

When the result of the comparison is that the power, output voltage and frequency of the given generator have signals, and the fluctuation range of the state information collection of the power system is above 5%, determine the warning level of the state information of the corresponding power system in the form of intermediate warning generation text show;

When the comparison result is that there are signals for the given generator power, output voltage and frequency, and the state information collection of the power system fluctuates in the range of 3% to 5%, it is determined that the warning level of the state information of the corresponding power system is a low-level warning to generate a text form to display;

When the comparison result shows that the power of the given generator and the output voltage and frequency have signals, and the fluctuation range of the state information collection of the power system is less than 3%, it is determined that the warning level of the state information of the corresponding power system is in normal mode to generate a text form for display ;

When the comparison result is that there is no signal for the power, output voltage and frequency of the given generator, there is no feedback information for the power, output voltage and frequency of the generator, and it is determined that the warning level of the corresponding generator is in non-start mode to generate a text form for display;

The status information of the power system includes the power, output voltage and frequency of the generator, the temperature, voltage and current of the battery, the output voltage and current of the transformer rectifier, and the bus voltage and current;

The displayed text forms are sorted according to highest level warning > middle level warning > low level warning > normal mode > no start mode.

The present invention has the following effects:

(1) In the ground test technology of the aircraft power system, power systems such as power generation and distribution (i.e. copper bird) are the test objects, but the normal operation of the power system requires avionics system (i.e. electric bird), flight control hydraulic system (i.e. Iron bird) cooperation (information cross-linking, that is, the power system needs to receive the signals of the electric bird and the iron bird) to operate normally, which requires the "copper bird" of the power system test and the "electric bird" of the avionics system test And the iron bird of the flight control hydraulic system performs information cross-linking, thus forming the analysis, verification, and debugging of the power system level of "three-bird joint debugging"; the signal simulation unit acts as the "electric bird" and "iron bird" system, giving the power system (i.e. "Bronze Bird") signals required for normal operation create conditions for the normal operation of "Bronze Bird" and realize joint debugging of "Three Birds" without actually building avionics systems and flight control hydraulic systems If the system exists, complete the aircraft power system ground test requirements.

(2) Instead of the real schematic page display unit, summarize the relevant status information of the aircraft power system (EPS) (mainly including generator power, output voltage and frequency, bus voltage and current, and power line topology) and other information to simplify The graph page is displayed intuitively, and ground monitoring personnel can monitor the operating status of the power system through the simplified graph page.

(3) Replace the real avionics alarm system, and centrally display and refresh the fault points in the power system, sort the alarm levels, and play the function of prompting alarms.

(4) The present invention is convenient for human-computer interaction, and tests the performance of the power system quickly and conveniently.

Description of drawings

Fig. 1 is a schematic structural diagram of an electrical system display simulator provided by an embodiment of the present invention;

Fig. 2 is a schematic structural diagram of an electrical system display simulator provided by another embodiment of the present invention;

Fig. 3 is a schematic structural diagram of an electrical system display simulator provided by another embodiment of the present invention;

Fig. 4 is a schematic structural view of an aircraft power system comprehensive test system provided by an embodiment of the present invention;

FIG. 5 is a schematic structural diagram of an EPS state information receiving unit provided by an embodiment of the present invention;

Fig. 6 is the human-computer interaction interface of the electrical system display simulator provided by an embodiment of the present invention;

FIG. 7 is an enlarged view of the page shown in the brief page diagram of FIG. 6;

Fig. 8 is an enlarged view of the unit alarm information display page of Fig. 6;

Among them, 1. EPS status information receiving unit; 2. Simplified diagram page display unit; 3. Crew alarm system display unit; 4. Signal simulation unit; 5. EPS status information sending unit; 6. Flight control system; 7. Power system ; 8. Remote power management system.

Detailed ways

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The accompanying drawings are for illustrative purposes only, and represent only schematic diagrams, rather than actual drawings, and should not be construed as limitations on this patent. In order to better illustrate the specific implementation of the present invention, some parts of the accompanying drawings will be omitted or enlarged Or reduced, does not represent the size of the actual product. For those skilled in the art, it is understandable that some known structures and their descriptions in the drawings may be omitted. Based on the embodiments of the present invention, those of ordinary skill in the art do not All other embodiments obtained under the premise of creative work belong to the protection scope of the present invention.

In the description of the present invention, it should also be noted that, unless otherwise clearly specified and limited, the terms "setting" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection, or Integral connection; it can be mechanical connection or electrical connection; it can be direct connection or indirect connection through an intermediary, and it can be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention according to specific situations.

As shown in Figure 1, an electrical system display simulator, including

The EPS state information receiving unit 1 collects the state information of the power system 7, and transmits the state information of the power system 7 to the schematic page display unit 2; the state information includes the power of the generator, output voltage and frequency, busbar Voltage and current acquisition fluctuation range;

The simplified diagram page display unit 2 performs logic calculation and generates a simplified diagram page form for display according to the state information of the power system 7 transmitted by the EPS status information receiving unit 1;

The unit alarm system display unit 3 compares the status information of the power system 7 with a given threshold value of the status information of the power system 7, determines the warning level according to the comparison result and displays it in text form;

The signal simulation unit 4 simulates the signals of the avionics system and the hydraulic system, adopts a virtual operation interface, and realizes it through the application software running on the computer. When triggered, it calculates the operating state of the power system 7 according to the logic relationship defined by AICD through the built-in relay The board is sent to the remote power management system 8 .

Fig. 2 is another structural diagram of the electrical system display simulator. For the unit alarm system display unit 3, it can obtain the status information of the power system 7 from the schematic page display unit 2 as shown in Fig. 1, or it can The status information of the power system 7 is obtained from the EPS status information receiving unit 1 (ie, the power system 7 status information receiving unit).

In this embodiment, the electrical system display simulator, the hardware is mainly composed of a data acquisition card, an industrial control computer with an Ethernet communication interface, and displays the status information of the power system 7 in the form of a simplified diagram page and unit alarm system (CAS) information , and through the signal simulation unit 4 to display the cross-link bus information between the power system 7 and other systems such as avionics and hydraulic pressure.

The realization of the software is completed by the LabVIEW development environment, and the software part is mainly data communication and logic calculation. During the operation of the aircraft, the avionics system and the flight control hydraulic system need to send control commands, that is, to ensure the normal operation of the power system 7, the avionics system and the flight control hydraulic system need to provide it with status signals of other systems of the aircraft, such as the APU control switch , APU ready to load, APU start enable, left generator fuel cutoff, left generator ignition switch, right generator fuel cutoff, right generator ignition switch, primary electromechanical power controller airspeed, backup electromechanical power controller empty Speed, N2 speed signal of the generator, landing gear status, left and right fire control handle status, current airspeed and other signals mean that the signals simulating the avionics system and the hydraulic system are simulating the APU control switch, APU ready to load, and APU start enable , left generator fuel cutoff, left generator ignition switch, right generator fuel cutoff, right generator ignition switch, primary electromechanical power controller airspeed, backup electromechanical power controller airspeed, generator N2 speed, starting More than one signal for landing gear status, left and right fire handle status, and current airspeed. These signals are directly related to what state the power system 7 is working in, whether it is running normally, and the conversion of its working state. Therefore the present invention needs to simulate the operating state of the avionics system and the flight control hydraulic system according to the current specific test requirements and the actual operating conditions of the power system 7, and send them to the power system 7 in real time through the bus according to the given cycle of each signal respectively. The signal is generated by the signal simulation unit 4 of the present invention, and the required operating state of the power system 7 (ie, the control signal) is sent to the remote power management system 8 (hereinafter referred to as "RPDU test system") through the relay board to control the power system 7 runs.

AICD (Avionics Interface Control Document) is the avionics interface control document

As an industry standard, AICD defines the data frequencies sent by the bus as 1Hz, 5Hz, 10Hz and 20Hz respectively, so all functions (data acquisition, analysis, Save, EPS sketch and CAS information status update, etc.) to meet the real-time requirements of the system.

The status information of the electric power system 7 (EPS) (engine power, output voltage and frequency, bus voltage and current, etc.) is monitored by the bus in real time, and the raw data (EPS information) collected from the 429 bus and the PCI bus by the bus monitor is in accordance with Record the order of time, and then carry out logical processing on the collected data, that is, data decomposition and logical calculation. These two parts need to be carried out in strict accordance with the specification requirements given by AICD. Any slight error in data or calculation will cause judgment The serious distortion of the result makes the current judgment on the state of the power system 7 unreliable.

As shown in Figure 5, the EPS state information receiving unit 1 includes an acquisition circuit and a data acquisition board; the acquisition circuit collects the state information of the power system 7, and transmits the state information of the power system 7 through logical processing through the data acquisition board. The sketch page shows unit 2. The power system 7 operates after obtaining corresponding control instructions, and the state information of the power system 7 (that is, the power of the generator, output voltage and frequency, bus voltage and current, and power line topology) enters the data acquisition board through the acquisition circuit (as an example For example, NI’s PCI6224 data acquisition board) collects, records the status information of the power system 7 according to the order of time, performs logical processing and transmits it to the diagram page display unit 2 for display, the working principle of the diagram page display unit 2 Labview stores the state information of the power system 7 in the Labview data reading memory by writing the dynamic link library DLL file, and reads the state information of the power system 7 in the form of a chart on the PC display in real time by calling the Labview waveform chart show. Among them, the collected signal is divided into analog signal and discrete signal according to the type. The analog signal enters the PCI6224 data acquisition board after passing through the signal acquisition circuit (filtering, amplification, differential adjustment, etc.) to ensure the stability and reliability of the collected signal. .

As shown in Figure 3, on the basis of the above-mentioned embodiments, the electrical system display simulator also includes an EPS state information sending unit 5, which receives the state information of the power system 7 transmitted by the EPS state information receiving unit 1, and sends the power system The status information of 7 is transmitted to the flight control system 6.

The status information of the power system 7 will be sent to the flight control system 6 through the EPS status information sending unit 5, and the flight control system 6 is the information fusion center of the aircraft.

As shown in Figure 4, a kind of comprehensive test system of aircraft power system 7, comprises power system 7 and remote power management system 8, also comprises above-mentioned electrical system display simulator, and electrical system display simulator will power system 7 running state Send it to the remote power management system 8, the remote power management system 8 receives the operating status of the power system 7 and converts it into a control command and sends it to the power system 7, the power system 7 runs according to the control command, and the electrical system displays the simulator to collect the power system 7 status information and displayed in the form of sketch page and text.

The electrical system display simulator test method described above includes the following steps:

Accept the user operation instruction to trigger the signal simulation unit 4, and the generated simulation signal calculates the operating status of the power system 7 according to the logic relationship defined by AICD and sends it to the remote power management system 8;

Collect the state information of the power system 7, the state information of the power system 7 includes the power, output voltage and frequency of the generator, the temperature, voltage and current of the storage battery, the output voltage and current of the transformer rectifier, and the bus voltage and current collection fluctuations scope;

The status information of the power system 7 is logically calculated and displayed in the form of a simplified diagram page;

The status information of the power system 7 is compared with a given threshold value of the status information of the power system 7, and the warning level is determined according to the comparison result to generate a text form for display.

As an example, the running state of the power system 7 includes: a generator starting state and a non-starting state, and the generators include a left generator, a right generator, and an APU generator.

As an exemplary illustration, the logic calculation is defined as follows: when the electrical system display simulator sends the generator start-up status to the remote power management system 8, if the electrical system display simulator collects the state information of the power system with a fluctuation range of 3% or less, then The status information of the corresponding power system is normal mode;

When the electrical system displays that the simulator sends the starting status of the generator to the remote power management system 8, if the electrical system displays that the state information of the power system collected by the simulator has a fluctuation range of more than 3%, then the state information of the corresponding power system is a failure mode;

When the electrical system displays that the simulator sends the non-starting state of the generator to the remote power management system 8, if the electrical system displays that the generator power, output voltage and frequency collected by the simulator have feedback information, the corresponding generator power and output Voltage and frequency for failure mode;

When the electrical system displays that the simulator sends the non-starting state of the generator to the remote power management system 8, if the electrical system displays that the generator power, output voltage and frequency collected by the simulator have no feedback information, the corresponding generator power and output The voltage and frequency are in non-start mode;

The status information of the power system includes the power, output voltage and frequency of the generator, the temperature, voltage and current of the battery, the output voltage and current of the transformer rectifier, and the bus voltage and current. Of course, the status information of the power system is not limited to this, and can also be Transformers are included, for example only.

In this embodiment, the generator includes a left generator, a right generator, and an APU generator, and the bus bar includes: a left AC bus bar, a right AC bus bar, a left DC bus bar, a right DC bus bar, a left DC main bus bar, a right DC main bus bar, DC conversion main bus bar, 3-phase AC main bus bar, single-phase AC main bus bar, flight control DC bus bar, etc. The battery includes the main battery, flight control battery and APU battery, and the transformer rectifier includes Left transformer rectifier, medium transformer rectifier, right transformer rectifier, there are three warning levels for these status information, for the convenience of monitoring, they can be displayed in three colors, for example, green represents normal mode, yellow represents fault failure Mode (which can be further subdivided into the highest level warning, medium level warning and low level warning), white means no start mode.

Take the L AC BUS (left AC bus bar) as an example, if the L AC BUS shows yellow, it means that the L AC BUS (left AC bus bar) is a failure mode: if the L AC BUS shows green, it means that the L AC BUS (left AC bus bar) is the normal mode.

As an exemplary illustration, comparing the status information of the power system 7 with a given threshold value of the status information of the power system 7, and determining the warning level according to the comparison result and displaying it in text form includes:

When the comparison result is that there are signals for the given generator power, output voltage and frequency, and the generator power, output voltage and frequency are zero, it is determined that the warning level of the corresponding generator is the highest level, and the warning is generated and displayed in text form;

When the comparison result is that there is no signal for the given generator power, output voltage and frequency, and the generator power, output voltage and frequency have feedback information, it is determined that the corresponding generator warning level is the highest level, and the warning is generated and displayed in text form;

When the result of the comparison is that the power, output voltage and frequency of the given generator have signals, and the fluctuation range of the state information collection of the power system is above 5%, determine the warning level of the state information of the corresponding power system in the form of intermediate warning generation text show;

When the comparison result is that there are signals for the given generator power, output voltage and frequency, and the state information collection of the power system fluctuates in the range of 3% to 5%, it is determined that the warning level of the state information of the corresponding power system is a low-level warning to generate a text form to display;

When the comparison result shows that the power of the given generator and the output voltage and frequency have signals, and the fluctuation range of the state information collection of the power system is less than 3%, it is determined that the warning level of the state information of the corresponding power system is in normal mode to generate a text form for display ;

When the comparison result is that there is no signal for the power, output voltage and frequency of the given generator, there is no feedback information for the power, output voltage and frequency of the generator, and it is determined that the warning level of the corresponding generator is in non-start mode to generate a text form for display;

The status information of the power system includes the power, output voltage and frequency of the generator, the temperature, voltage and current of the battery, the output voltage and current of the transformer rectifier, and the bus voltage and current;

The displayed text forms are sorted according to highest level warning > middle level warning > low level warning > normal mode > no start mode.

Take the left generator test as an example, if there are signals for the given left generator power, output voltage and frequency, and the collected generator power, output voltage and frequency are zero, it is determined that the warning level of the left generator is the highest level Warnings are generated as text for display. When the comparison result is that there is no signal for the power, output voltage and frequency of the given left generator, and there is feedback information (not zero) for the power, output voltage and frequency of the left generator, it is determined that the warning level of the left generator is the highest warning Generate a text form for display; when the comparison result is that there are signals for the given power, output voltage and frequency of the left generator, and if the collected fluctuation range of the collected power, output voltage and frequency of the left generator is above 5%, determine the left The warning level of the generator is medium-level warning. Generate a text form for display. If the collected fluctuation range of left generator power, output voltage and frequency is between 3% and 5%, it is determined that the left generator warning level is low-level warning. Generate a text form for display. If the collected fluctuation range of left generator power, output voltage and frequency is below 3%, make sure the warning level of the left generator is in normal mode. Generate a text form for display. If the collected battery temperature And when the voltage and current and/or the output voltage and current of the transformer rectifier and/or the fluctuation range of the bus voltage and current collection are above 5%, determine that the warning level of the battery and/or the transformer rectifier and/or the busbar is a medium-level warning and generate text If the collected temperature, voltage and current of the battery and/or the output voltage and current of the transformer rectifier and/or the fluctuation range of bus voltage and current collection are between 3% and 5%, it is determined that the battery and/or transformer The warning level of the voltage rectifier and/or the bus bar is displayed in the form of an intermediate warning generated in text form. When below %, it is determined that the battery and/or transformer rectifier and/or bus bar warning level is medium level warning generation and display in text form. The right alternator and APU alternator tests are the same.

The fluctuation ranges of 3% and 5% of the power system state information collected above can also be re-determined according to actual test needs. Such as 4%, 8% and so on.

As an exemplary illustration, the human-computer interaction interface of the electrical system display simulator may be as shown in FIG. 6 .

The function of this part of ELECTRICAL SYSTEM SYNOPTIC (simplified page diagram display page) is actually the function of status display, that is, the current status of the electric system 7 is displayed in the form of a simplified page diagram after data collection and data processing, and the power system is intuitively displayed 7 The operating status of each part. The specific state information display is shown in Figure 7, and the terminology in Figure 7 is explained: LAC BUS: left AC bus bar; R AC BUS: right AC bus bar; TRU: Transformer Rectifier Unit, transformer rectifier; L\E\R TRU: Left\middle\right TRU; L DC BUS: left DC bus bar; R DC BUS: right DC bus bar; LDCESS BUS: left DC main bus bar; R DC ESS BUS: right DC main bus bar; DC ESS XFER BUS: DC conversion main bus bar; 3PH AC ESS BUS: 3-phase AC main bus bar; 1PH AC BUS: single-phase AC main bus bar; INV: converter; MAIN BATT: main battery; FC BATT: flight control battery; FC DC BUS : flight control DC bus bar; APUBATT: APU battery; yellow represents the failure mode, white represents the non-start mode; green represents the normal state, in Figure 7, the failure mode of the left engine (displays yellow); ); normal starting mode of the right engine (shown in green); other components (except generator) such as E TRU, R DC ESS BUS, MAINBATT feedback values are not within the normal fluctuation range (3%) (shown in yellow), because Figure 7 is black and white The color cannot be seen.

The status information of the power system 7 performs the CAS early warning function through the display unit 3 of the unit alarm system. When some status information of the power system 7 in the simplified diagram page is displayed in yellow, it means that the status information is faulty, and the unit alarm system display unit 3 will extract Faulty component information, compare the parameters of the faulty component with the given threshold, and display the warning information of EPS three levels according to the following categories: Warning, Caution and Advisory, so as to form the unit alarm system (CAS) information display in the interface, and the alarm The information plays the role of reminding the ground monitoring personnel. Here, Warning, Caution and Advisory all belong to "Warning", and the level relationship of warning is Warning>Caution>Advisory. Generator failure to start normally belongs to the highest level warning (Warning), the power and output voltage and frequency of the left generator, the power and output voltage and frequency of the right generator, the power and output voltage and frequency of the APU generator, the temperature and If the voltage and current, the output voltage and current of the transformer rectifier, and the bus voltage and current collection fluctuation range are above 5%, it is a medium-level warning (Caution), and if it is above 3% to 5%, it is a low-level warning (Advisory). CAS, that is, the unit alarm information display page is shown in Figure 8, the CAS information with high alert level is arranged at the top of the page, and the CAS information with low alert level is arranged at the bottom. Explanation of terms in Fig. 8: LGEN FAULT: left generator fault; MAIN BATT FAULT: main battery fault; E TRU FAULT: medium transformer rectifier fault; APU GEN FAULT: APU fault; R GEN FAULT: right generator fault; in Fig. 8 L GEN is in the failure mode and belongs to the highest level of warning, so it is at the top and displays Warning; MAIN BATT and E TRU are in the middle level of warning when the fluctuation range is above 5%, and they are sorted in order to display Caution; L DC BUS fluctuates within 3 If the fluctuation is above %, the Advisory is displayed.

The signal simulation unit 4 is to simulate the avionics system, hydraulic system and other systems, and provide the normal signals required for the normal operation of the power system. Here, the power system 7 refers to the copper bird, the avionics system refers to the electric bird, and the hydraulic system refers to the It is an iron bird, so that it is easy to realize the "three birds" joint test only under the condition that the electric system 7 exists through the electrical system display simulator.

The signal simulation unit 4 can provide the signal needed for the normal operation of the power system, that is, the "copper bird", thus providing an effective means for the ground test of the aircraft power system 7 . The fault source in the power system 7 is simulated by the signal simulation unit 4 (because the normal operation of the power system 7 needs to output signals from the signal simulation unit 4), and the power system 7 obtains some necessary operation signals, which can be controlled artificially. Running, while the power system 7 is running according to the instructions, the sensor will collect the running status of each component (all the status information displayed on the sketch page) in real time, and display it intuitively on the sketch page, and at the same time the electrical system will display The simulator will display the failure of the power system 7 on the CAS page.

The specific test method of the electrical system display simulator is as follows:

Now assume a simulation test: the left engine (L GEN) is in failure mode (yellow), the APU is in non-start mode (white), and the right engine (R GEN) is in normal state (green). Under such artificial settings, the fault verification of the power system 7 can be realized, so as to test the power normality of the system.

Signal simulation (here the electrical system shows that the simulator can simulate signals, and all the required signals can be simulated) contains the following signals:

APU Master Switch: APU control switch; APU RTL: APU ready to load;

APU Start Enable: APU start enable;

L Engine fuel cutoff: left engine fuel cut off; L Engine fire switch: left engine ignition switch;

R Engine fuel cutoff: right engine fuel cut off; R Engine fire switch: right engine ignition switch;

CAL_AIRSPEED1_EMPC(<=80knots): Main electromechanical power controller airspeed (less than or equal to 80 knots)

CAL_AIRSPEED2_EMPC(>170knots): backup electromechanical power controller airspeed (greater than 170 knots)

The main function of the signal simulation is to simulate the signals of the avionics system and hydraulic system, etc. The simulated signals are used as control commands. In order to ensure the normal operation of the power system 7, other systems need to provide it with the status of other systems of the aircraft, such as the N2 speed of the engine. Signals, landing gear status, left and right fire control handle status, current airspeed, etc., use the LabVIEW development environment to perform signal simulation, which belongs to the prior art and will not be repeated here. These signals are directly related to what state the power system 7 is working in, whether it is running normally, and the conversion of its working state. In the ground test technology of the aircraft power system 7, the signal of the signal simulation unit 4 can complete the function of controlling the state of the power system 7, and the signals here are calculated according to the logic relationship defined by AICD to calculate the operating status of the power system 7.

Example: (logical relationship defined by AICD)

Table 1 APU startup mode logic relationship defined by AICD

Table 1 explains: APU auxiliary power unit generally outputs power for the aircraft power system 7 before the aircraft takes off, so when the APU Master Switch, APU RTL, and APU Start Enable are all turned on, and CAL_AIRSPEED1_EMPC (<=80knots) is 1. CAL_AIRSPEED2_EMPC (>170knots) is 0 (representing the aircraft speed is less than or equal to 80 knots), so that the APU is in the start mode, and the rest of the states are in the off mode.

Table 2 Logical relationship of the left engine starting mode defined by AICD

Table 2 explains: the left engine outputs power for the aircraft power system 7 after the aircraft takes off, so when the LEnginefuel cutoff and L Engine fire switch are both turned on, and CAL_AIRSPEED1_EMPC(<=80knots) is 0, CAL_AIRSPEED2_EMPC(>170knots ) is 0 or 1 (representing that the aircraft speed is greater than 80 knots), so that the left engine is in the starting mode, and the rest of the states are in the non-starting mode.

Table 3 Logical relationship of the right engine starting mode defined by AICD

Table 3 explains: the right engine outputs power for the aircraft power system 7 after the aircraft takes off, so when the REnginefuel cutoff and R Engine fire switch are both turned on, and CAL_AIRSPEED1_EMPC(<=80knots) is 0, CAL_AIRSPEED2_EMPC(>170knots ) is 0 or 1 (representing that the aircraft speed is greater than 80 knots), so that the right engine is in the starting mode, and the rest of the states are in the non-starting mode.

The signal simulation function sends the control signal (that is, the operating state of the power system 7) to the RPDU (RemotePowerDistribution Unit) test system, that is, the remote power management system 8, and the RPDU controls the generator operating state of the power system 7 (starting or not starting mode).

The aircraft power system 7 operates according to the control command, and feeds back the analog and digital quantities to the display unit 2 on the schematic page in real time, and performs AICD logic calculation for display. The calculation method: green means normal operation; white means non-start mode; yellow means Failure failure, the AICD calculation of failure failure refers to the normal starting state (the signal simulation unit 4 controls the generator to start), and the sensor returns to an abnormal state (the generator does not start) under the actual power system 7 operation; or the fluctuation range of other components is out of range A yellow reminder is displayed within the normal fluctuation range (3%).

The aircraft power supply system operates according to the control instructions, and feeds back the analog and digital quantities in real time to the display unit on the simplified page of the electrical system display simulator, which also needs to perform AICD logic calculations for display. The calculation method: green means normal operation; white Represents non-start mode; yellow represents fault failure, the AICD calculation of fault failure refers to the normal start state (the signal simulation unit controls the generator to start), and the sensor returns to an abnormal state when the actual power supply system is running (the generator does not start); or If the nominal value of other components is not within the normal fluctuation range (3%), a yellow reminder will be displayed.

Although the embodiments of the present invention have been shown and described, those skilled in the art can understand that various changes, modifications and substitutions can be made to these embodiments without departing from the principle and spirit of the present invention. and modifications, the scope of the invention is defined by the appended claims and their equivalents.

Claims (2)

1. An electrical system display simulator, characterized in that: comprising EPS state information receiving unit, the EPS state information receiving unit includes an acquisition circuit and a data acquisition board; the acquisition circuit collects the state information of the power system, and transmits the state information of the power system to the schematic page through logical processing through the data acquisition board Display unit; the status information includes generator power, output voltage and frequency, bus voltage and current acquisition fluctuation range; The schematic page display unit, which is logically calculated according to the status information of the power system and generated in the form of a schematic page for display; The unit alarm system display unit compares the status information of the power system with a given threshold value of the status information of the power system, determines the warning level according to the comparison result, and displays it in text form; The signal simulation unit simulates the signals of the avionics system and the hydraulic system. It adopts a virtual operation interface and realizes it through the application software running on the computer. The signal simulation unit includes a relay board. When triggered, the power is calculated according to the logical relationship defined by AICD. The system running status is sent to the remote power management system; the signals of the simulated avionics system and hydraulic system include the simulated APU control switch, APU ready to load, APU start enable, left generator fuel cut-off, left generator ignition switch, right generator More than one signal of fuel cutoff, right generator ignition switch, primary electromechanical power controller airspeed, backup electromechanical power controller airspeed, generator N2 speed, landing gear status, left and right fire handle status and current airspeed ; The EPS status information sending unit receives the status information of the power system transmitted by the EPS status information receiving unit, and transmits the status information of the power system to the flight control system; Specifically include the following steps: Receive the user operation command to trigger the signal simulation unit, and the generated simulation signal calculates the power system running state according to the logic relationship defined by AICD and sends it to the remote power management system; the power system running state includes: generator start state and non-start state, so Said generator comprises left generator, right generator, APU generator; Collecting the state information of the power system, the state information of the power system includes the power, output voltage and frequency of the generator, the temperature, voltage and current of the storage battery, the output voltage and current of the transformer rectifier, and the collection fluctuation range of the bus voltage and current; The logic calculation is defined as follows: When the electrical system display simulator sends the generator start-up status to the remote power management system, if the electrical system display simulator collects the state information of the power system with a fluctuation range of less than 3%, then the state of the corresponding power system The information is in normal mode; When the electrical system displays that the simulator sends the starting status of the generator to the remote power management system, if the electrical system displays that the state information of the power system collected by the simulator fluctuates by more than 3%, the state information of the corresponding power system is a failure mode; When the electrical system displays that the simulator sends the generator non-start status to the remote power management system, if the electrical system displays the generator power, output voltage and frequency collected by the simulator with feedback information, the corresponding generator power and output voltage and frequency for the failure mode; When the electrical system displays that the simulator sends the generator non-start status to the remote power management system, if the electrical system displays no feedback information on the power, output voltage and frequency of the generator collected by the simulator, the corresponding generator power and output voltage and frequency, bus voltage and current are non-starting modes; The status information of the power system is logically calculated and displayed in the form of a simplified diagram page; Comparing the status information of the power system with a given threshold of status information of the power system, and determining the warning level according to the comparison result to generate a text form for display; specifically including: when the comparison result is a given power and output of the generator The voltage and frequency have signals, the power of the generator and the output voltage and frequency are zero, and the warning level of the corresponding generator is determined to be the highest level, and the warning is generated and displayed in text form; When the comparison result is that there is no signal for the given generator power, output voltage and frequency, and the generator power, output voltage and frequency have feedback information, it is determined that the corresponding generator warning level is the highest level, and the warning is generated and displayed in text form; When the result of the comparison is that the power, output voltage and frequency of the given generator have signals, and the fluctuation range of the state information collection of the power system is above 5%, determine the warning level of the state information of the corresponding power system in the form of intermediate warning generation text show; When the comparison result is that there are signals for the given generator power, output voltage and frequency, and the state information collection of the power system fluctuates in the range of 3% to 5%, it is determined that the warning level of the state information of the corresponding power system is a low-level warning to generate a text form to display; When the comparison result shows that the power of the given generator and the output voltage and frequency have signals, and the fluctuation range of the state information collection of the power system is less than 3%, it is determined that the warning level of the state information of the corresponding power system is in normal mode to generate a text form for display ; When the comparison result is that there is no signal for the power, output voltage and frequency of the given generator, there is no feedback information for the power, output voltage and frequency of the generator, and it is determined that the warning level of the corresponding generator is in non-start mode to generate a text form for display; The displayed text forms are sorted according to highest level warning > middle level warning > low level warning > normal mode > no start mode. 2. A comprehensive test system for an aircraft electrical system, comprising an electrical system and a remote power management system, characterized in that: it also includes an electrical system display simulator as claimed in claim 1, and the electrical system display simulator sends the operating status of the electrical system to To the remote power management system, the remote power management system receives the operating status of the power system and converts it into a control command and sends it to the power system. Presentation in the form of diagram pages and text.

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