CN113741392B - Distributed flight control system PBIT mode operation flow method - Google Patents

Distributed flight control system PBIT mode operation flow method Download PDF

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Publication number
CN113741392B
CN113741392B CN202111024745.8A CN202111024745A CN113741392B CN 113741392 B CN113741392 B CN 113741392B CN 202111024745 A CN202111024745 A CN 202111024745A CN 113741392 B CN113741392 B CN 113741392B
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pbit
fcc
mode
art
effective
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CN113741392A (en
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何战斌
周成
刘若凡
张天钧
焦林冠
唐丹丹
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Xian Flight Automatic Control Research Institute of AVIC
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Xian Flight Automatic Control Research Institute of AVIC
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    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B23/00—Testing or monitoring of control systems or parts thereof
    • G05B23/02—Electric testing or monitoring
    • G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
    • G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
    • G05B23/0221—Preprocessing measurements, e.g. data collection rate adjustment; Standardization of measurements; Time series or signal analysis, e.g. frequency analysis or wavelets; Trustworthiness of measurements; Indexes therefor; Measurements using easily measured parameters to estimate parameters difficult to measure; Virtual sensor creation; De-noising; Sensor fusion; Unconventional preprocessing inherently present in specific fault detection methods like PCA-based methods
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
    • Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]

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  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Safety Devices In Control Systems (AREA)

Abstract

The invention belongs to the self-detection technology in an aircraft control system, and provides a PBIT mode operation flow method of a distributed aircraft control system, which is used for detecting the state of the aircraft control system and feeding back the state of the aircraft control system on the premise of ensuring safety. The technical scheme comprises the following steps: the PBIT task of the whole flight control system is started by a Flight Control Computer (FCC), when the FCC meets the PBIT interlocking condition of the FCC, the FCC enters a PBIT mode, simultaneously sends FCC starting mode words to an actuator remote control terminal (ART) according to a special state, the ART enters the PBIT mode when judging the self interlocking condition and receiving a PBIT _ START signal in the FCC starting mode words to be effective, and sends a self working mode to the FCC, when the FCC finishes the PBIT test, the FCC enters a fault comprehensive mode, exits the PBIT mode after waiting for the ART to finish the PBIT test, receives test information sent by the ART, enters a PBIT waiting mode after the FCC synthesizes the faults of the FCC and the ART, and exits the PBIT mode to a period real-time task mode after waiting for the avionic to call the PBIT fault.

Description

Distributed flight control system PBIT mode operation flow method
Technical Field
The invention belongs to the self-detection technology in an airplane control system, and designs a PBIT mode operation method based on a distributed airplane control system.
Background
The PBIT is a self-detection function for providing fault detection, positioning and isolation for a flight control system before flight, is an important system fault self-detection method, and is an important way for improving the test performance and the diagnosis capability of the system. The system is detected by hardware and software with a self-checking function in the flight control system. Aiming at a distributed flight control system based on a 1394b bus and an airplane with a special state function, in order to ensure the safety of the airplane and ground maintenance personnel and the safe operation of the flight control system when the system is subjected to PBIT test, a whole set of operation flow for the starting, quitting and comprehensive fault declaration of a PBIT mode of the distributed flight control system needs to be designed, and a PBIT mode operation method of the distributed flight control system is not retrieved from public data at home and abroad at present.
Disclosure of Invention
The purpose of the invention is:
the invention provides a PBIT mode operation flow method of a distributed flight control system, which is used for detecting the state of the flight control system on the premise of ensuring safety, reporting the detection result to avionics or maintenance equipment, and feeding back the state of the flight control system to a pilot or maintenance personnel.
The technical scheme of the invention is as follows:
a distributed flight control system PBIT mode operation flow method comprises the following steps:
the PBIT task of the whole flight control system is started by a Flight Control Computer (FCC), when the FCC meets the PBIT interlocking condition of the FCC, the FCC enters a PBIT mode, meanwhile, different starting mode words of the FCC are sent to an actuator remote control terminal (ART) according to the special state of the airplane, the ART enters the PBIT mode when judging the self interlocking condition and receiving a PBIT _ START signal in the FCC starting mode words to be effective, and sends a self working mode to the FCC, when the FCC finishes the PBIT test, the FCC enters a fault comprehensive mode, exits the PBIT mode after waiting for the ART to finish the PBIT test, receives test information sent by the ART, enters a PBIT waiting mode after the FCC synthesizes the faults of the FCC and the ART, and exits the PBIT mode to a period real-time task mode after waiting for the avionic to call the PBIT fault.
The method comprises the following steps:
step 1, pressing a PBIT button on a press, enabling an FCC to receive a PBIT starting signal, and enabling the FCC to enter a PBIT mode when the PBIT interlocking condition of the FCC is effective;
step 2, judging whether the plane is in a special state or not when the PBIT starting signal voting value is effective;
step 3, the FCC sends FCC starting mode words to ART through a bus;
step 4, when the PBIT interlocking condition of the ART is effective and the received PBIT _ START is effective, the ART enters a PBIT mode and simultaneously sends a self working mode to the FCC to be the PBIT mode;
step 5, when the FCC is tested in the PBIT, setting the FCC in the starting mode word to be invalid when the PBIT is 0, and entering a fault comprehensive mode;
step 6, ART exits the PBIT mode when PBIT test finishes, and send the test information to FCC;
step 7, entering a PBIT waiting mode after FCC comprehensive FCC and ART fault information is finished;
step 8, if the PBIT fault of the avionic call is effective within the waiting time, responding to the call and exiting the PBIT from the FCC to enter a periodic real-time task mode after the call is finished; if the PBIT fault called by the avionics is invalid, the waiting time is over, the FCC exits the PBIT and enters a periodic real-time task mode, and the FCC sends a starting mode word to the ART.
Step 8 latency is 30s.
The PBIT interlocking conditions of the FCC in step 1 are valid: the wheel bearing state is effective, the wheel bearing voting value is effective, the PBIT is started effectively, the dynamic pressure is allowed to be effective when the dynamic pressure is less than 1215Pa, the BIT software is allowed to be effective, and the BIT interlock signal is effective.
The method for judging the special state in the step 2 comprises the following steps: the special state switch votes the value, the special state lock votes on the left, and the special state lock votes on the right, and when the value is '0', the airplane is in a special state, and if any voted value is '1', the airplane is not special.
The FCC start mode word in step 3 includes: PBIT mode, PBIT _ START, FCC are in PBIT, periodic real-time tasks.
The effective PBIT interlocking condition of ART in the step 4 is as follows: the front wheel bearing voting value is effective; the FCC's PBIT mode (voted value) is valid; the voting value of the special state switch is not special; the left and right special status lock votes are not special.
The test information in the step 6 comprises a PBIT completion mark, a PBIT abnormal exit mark and a PBIT detection result.
The invention has the advantages that:
the distributed flight control system PBIT (self-detection before flight) mode operation flow method is provided, aiming at the distributed flight control system, the flow of PBIT starting, exiting and fault comprehensive declaration of each node is defined, FCC and ART can respectively enter a PBIT mode to test when respective entry conditions are met, and the fault detection, positioning and isolation of the flight control system are ensured on the premise of ensuring the safety of an airplane and the safety of maintenance personnel under the condition that the airplane is in a special or non-special state.
Drawings
Fig. 1 is a schematic view of a PBIT mode operation flow of a distributed flight control system according to the present invention.
Detailed Description
The invention provides a distributed flight control system PBIT mode operation flow method, which comprises the following steps:
aiming at a distributed four-redundancy flight control system based on a 1394b bus, the distributed flight control system takes FCC and ART as control core nodes, a Flight Control Computer (FCC) and an actuator remote control terminal (ART) are taken as different control nodes in the system, and the distributed flight control system has a plurality of operation modes, including a periodic task mode, a PBIT mode and the like, the FCC is the control core of a PBIT task of the flight control system, the PBIT task of the whole flight control system is started by the FCC, a PBIT button on a press is pressed, the FCC receives a PBIT starting signal, when the PBIT interlocking condition of the FCC is effective, the FCC enters the PBIT mode, at the moment, when the PBIT starting signal value is effective, whether an airplane is in a special state is judged, and an FCC starting mode word is sent to the ART through a voting bus, wherein the FCC starting mode word comprises: PBIT mode, PBIT _ START, FCC are in PBIT, periodic real-time tasks. When the PBIT interlock condition of the ART is valid and the received PBIT _ START is valid, the ART enters the PBIT mode and simultaneously sends the self-operation mode to the FCC as the PBIT mode. When the FCC finishes the PBIT test, the ' FCC ' in the word of the startup mode is in PBIT ' and is invalid to ' 0 ', the FCC enters a failure comprehensive mode, the ART exits the PBIT mode when the PBIT test finishes, and sends test information to the FCC, the method mainly comprises a PBIT finish mark, a PBIT abnormal exit mark and a PBIT detection result, the FCC enters a PBIT waiting mode (30 s) after the completion of the comprehensive FCC and ART failure information, when in a special state, the ART can not enter the PBIT mode according to the entry condition, only the FCC carries out the PBIT test, the FCC synthesizes the failure information only in the failure comprehensive mode, the FCC enters the PBIT waiting mode (30 s) after the completion of the FCC, if the local PBIT failure is valid by the avionic call within 30s, the response call and the PBIT exits the PBIT real-time task mode after the call, if the avionic calls the local PBIT failure, the FCC exits the PBIT 30s time finishes, the FCC enters the PBIT enters the real-time period task mode, and the FCC sends the information table of the word of the startup mode to the FCC.
As shown in fig. 1:
step 1, pressing a PBIT button on a press, receiving a PBIT starting signal by FCC, and entering a PBIT mode by FCC when the PBIT interlocking condition of FCC is effective;
wherein, the PBIT interlocking condition of FCC effectively is: the wheel bearing state is effective, the wheel bearing voting value is effective, the PBIT is started effectively, the dynamic pressure is allowed to be effective when the dynamic pressure is less than 1215Pa, the BIT software is allowed to be effective, and the BIT interlock signal is effective.
Step 2, judging whether the airplane is in a special state or not when the PBIT starting signal voting value is effective;
the method for judging the special state of the airplane comprises the following steps: the special state switch votes the value, the special state lock votes on the left, and the special state lock votes on the right, and when the value is '0', the airplane is in a special state, and if any voted value is '1', the airplane is not special.
In order to ensure the safety of the airplane and the safety of personnel, whether the airplane is in a special state or not needs to be judged when the PBIT test is carried out, and the ART does not carry out the PBIT test in the special state so as to prevent the control surface from being damaged due to the movement of a steering engine in the test.
Step 3, the FCC sends FCC starting mode words to ART through the bus;
wherein, the FCC start mode word includes: PBIT mode (FCC sends '1' valid when entering PBIT), PBIT _ START (FCC enters PBIT and sends '1' valid when the airplane is not in special state; FCC enters PBIT and sends '0' invalid when the airplane is in special state), FCC is in PBIT (FCC sends '1' valid when PBIT test is carried out), and periodic real-time task (FCC sends '0' invalid when not in periodic task).
The different states of PBIT _ START are determined based on whether the aircraft is in a particular state.
Step 4, when the PBIT interlocking condition of the ART is effective and the received PBIT _ START is effective, the ART enters a PBIT mode and simultaneously sends a self working mode to the FCC to be the PBIT mode;
wherein, the PBIT interlocking condition of ART is effectively as follows: the front wheel bears the effective voting value; the FCC's PBIT mode (voted value) is valid; the voting value of the special state switch is not special; the left and right special status lock votes are not special.
Different from other distributed systems, whether the ART enters the PBIT mode or not needs to meet self-interlocking conditions, and meanwhile, the ART is jointly determined according to the state of 'PBIT _ START', if any condition is not met, the ART does not enter the PBIT mode, and only FCC carries out PBIT test.
Step 5, when the FCC is tested in the PBIT, setting the FCC in the starting mode word to be invalid when the PBIT is 0, and entering a fault comprehensive mode;
the FCC has different modes of operation and enters a failure mode.
Step 6, the ART exits the PBIT mode when the PBIT test is finished, and sends test information to the FCC, wherein the test information mainly comprises a PBIT finishing mark (1 is finished, 0 is unfinished), a PBIT abnormity exiting mark (1 is abnormal exiting, 0 is normal exiting), and a PBIT detection result (1 is PBIT test has no fault, and 0 is PBIT test fault);
step 7, entering a PBIT waiting mode (30 s) after the FCC comprehensive FCC and ART fault information is finished;
when the aircraft is in a special state, according to the entering conditions, ART cannot enter a PBIT mode, only FCC carries out PBIT test, and FCC only synthesizes FCC fault information in a fault synthesis mode.
And 8, after the fault information is integrated, the FCC enters a PBIT waiting mode (30 s), if the PBIT fault of the current time called by the avionics in 30s is valid, the response call is carried out, the FCC exits from the PBIT entering a periodic real-time task mode after the call is finished, if the PBIT fault of the current time called by the avionics is invalid, the 30s time is finished, the FCC exits from the PBIT entering the periodic real-time task mode, and at the moment, the FCC sends a starting mode word (the PBIT mode is invalid, the PBIT _ START is invalid, the FCC is in the PBIT invalid, and the periodic real-time task is valid) to the ART.
The present invention will be further illustrated by the following examples
Example 1: when the system is in a periodic real-time task, a PBIT button on a press is pressed, when a wheel bearing signal is bearing, dynamic pressure is 1000Pa, and an airplane is not in a special state, FCC enters a PBIT mode after being judged by the PBIT interlocking condition of the press, PBIT test is carried out, meanwhile, FCC starting mode words are sent to an ART through a 1394b bus after being judged by the ART, the ART enters the PBIT mode after being judged by the PBIT interlocking condition of the press and received FCC starting mode words containing 'PBIT _ START' and effective, PBIT test is carried out, after the FCC finishes the PBIT test, a failure comprehensive mode is entered, test information is sent to the FCC through the 1394b bus after the ART finishes the PBIT test, the PBIT mode exits, the FCC enters the PBIT waiting mode after finishing the synthesis of the FCC and the ART failure information, and after the avionic calls the PBIT failure in 30s, the FCC exits the PBIT mode and enters the periodic real-time task mode.

Claims (7)

1. A distributed flight control system PBIT mode operation flow method is characterized by comprising the following steps:
the PBIT task of the whole flight control system is started by a Flight Control Computer (FCC), when the FCC meets the PBIT interlocking condition of the FCC, the FCC enters a PBIT mode, simultaneously sends different FCC starting mode words to an actuator remote control terminal (ART) according to whether the aircraft is in a special state, the ART enters the PBIT mode by judging the self interlocking condition and receiving a PBIT _ START signal in the FCC starting mode words to be effective and sends a self working mode to the FCC, when the FCC finishes the PBIT test, the FCC enters a fault comprehensive mode, exits the PBIT mode after finishing the PBIT test by waiting for the ART, receives test information sent by the ART, enters a PBIT waiting mode after the faults of the FCC comprehensive FCC and the ART, exits the PBIT mode to a periodic real-time task mode after calling the PBIT fault by a avionic,
the method comprises the following steps:
step 1, pressing a PBIT button on a press, receiving a PBIT starting signal by FCC, and entering a PBIT mode by FCC when the PBIT interlocking condition of FCC is effective;
step 2, judging whether the airplane is in a special state or not when the PBIT starting signal voting value is effective;
step 3, the FCC sends FCC starting mode words to ART through the bus;
step 4, when the PBIT interlocking condition of the ART is effective and the received PBIT _ START is effective, the ART enters a PBIT mode and simultaneously sends a self working mode to the FCC to be the PBIT mode;
step 5, when the FCC is tested in the PBIT, setting the FCC in the starting mode word to be invalid when the PBIT is 0, and entering a fault comprehensive mode;
step 6, ART exits the PBIT mode when PBIT test finishes, and send the test information to FCC;
step 7, entering a PBIT waiting mode after FCC comprehensive FCC and ART fault information is finished;
step 8, if the PBIT fault of the avionic call is effective within the waiting time, responding to the call and exiting the PBIT from the FCC to enter a periodic real-time task mode after the call is finished; if the PBIT fault called by the avionics is invalid, the waiting time is over, the FCC exits the PBIT and enters a periodic real-time task mode, and the FCC sends a starting mode word to the ART.
2. The method for operating the flow in the PBIT mode of the distributed flight control system according to claim 1, further comprising: step 8 latency is 30s.
3. The method of claim 1, wherein the FCC PBIT interlocking condition in step 1 is effectively: the wheel bearing state is effective, the wheel bearing voting value is effective, the PBIT is started effectively, the dynamic pressure is allowed to be effective when the dynamic pressure is less than 1215Pa, the BIT software is allowed to be effective, and the BIT interlock signal is effective.
4. The method of claim 1, wherein the method comprises the steps of running the distributed flight control system in PBIT mode,
the method for judging the special state in the step 2 comprises the following steps: the special state switch votes the value, the special state lock votes on the left, and the special state lock votes on the right, and when the value is '0', the airplane is in the special state, and when any voted value is '1', the airplane is not in the special state.
5. The method of claim 1, wherein the method comprises the steps of running the distributed flight control system in PBIT mode,
the FCC start mode word in step 3 includes: PBIT mode, PBIT _ START, FCC are in PBIT, periodic real-time tasks.
6. The method as claimed in claim 1, wherein the method comprises the steps of,
the effective PBIT interlocking condition of ART in the step 4 is as follows: the front wheel bearing voting value is effective; the FCC's PBIT mode (voted value) is valid; the voting value of the special state switch is not special; the left and right special status lock votes are not special.
7. The method as claimed in claim 1, wherein the test information in step 6 includes a PBIT completion flag, a PBIT exception exit flag, and a PBIT detection result.
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