CN108871670B - Fault detection method for pressure sensor of airplane all-electric brake system - Google Patents
Fault detection method for pressure sensor of airplane all-electric brake system Download PDFInfo
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- CN108871670B CN108871670B CN201810742106.7A CN201810742106A CN108871670B CN 108871670 B CN108871670 B CN 108871670B CN 201810742106 A CN201810742106 A CN 201810742106A CN 108871670 B CN108871670 B CN 108871670B
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- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L25/00—Testing or calibrating of apparatus for measuring force, torque, work, mechanical power, or mechanical efficiency
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Abstract
The invention discloses a method for detecting faults of a pressure sensor of an all-electric brake system of an airplane, which is used for solving the technical problem that the existing fault detection method is complex in system. The technical scheme includes that firstly, pressure borne by a braked wheel is collected through a pressure feedback signal collecting circuit through a four-wire system pressure sensor, then the collected pressure feedback signal is filtered and conditioned through a Butterworth low-pass filter to eliminate noise, then the pressure feedback signal is sent to a pressure sensor fault detecting circuit, output voltage of the pressure sensor fault detecting circuit is detected to be positive voltage or negative voltage, and therefore fault diagnosis is conducted on the four-wire system pressure sensor. The method can quickly detect the fault problem when the four-wire system pressure sensor of the airplane electric brake system has a fault, so that corresponding fault-tolerant control can be performed on the fault problem of the four-wire system pressure sensor of the airplane electric brake system, the normal operation of the airplane brake system is ensured, the reliability of the airplane brake system is effectively improved, and the system is simple and reliable.
Description
Technical Field
The invention relates to a fault detection method, in particular to a fault detection method for a pressure sensor of an all-electric brake system of an airplane.
Background
With the development of All-Electric Aircraft (AEA All-Electric-Aircraft) technology, computer technology, and control technology. The airplane electric brake system is one of the core technologies of an all-electric airplane, and depends on the bearing capacity of the airplane to the static weight and the dynamic impact load in the normal landing, forced landing, takeoff emergency stop and other processes of the airplane. Therefore, in order to ensure the safe operation of the airplane, higher requirements are put on the safety, stability and reliability of the airplane electric brake system.
The pressure sensor is the most commonly used sensor in industry, and is widely applied to the fields of aerospace, war industry, ships, railway traffic and the like. As an important component of an airplane electric brake system, the pressure sensor is mainly used for collecting airplane brake pressure in real time and providing pressure feedback signals required by control for the airplane brake system. Therefore, in order to ensure the normal operation of the aircraft electric brake system, the pressure sensor of the aircraft electric brake system must be subjected to fault detection so as to eliminate the fault of the pressure sensor and ensure the safety of the aircraft system.
The document "Chinese invention patent with application publication number CN 106644256A" discloses a method for detecting faults of a pressure sensor. The hardware of the method consists of a machine body and a diagnosis system in the machine body, wherein the diagnosis system comprises an acquisition preprocessing system, a decomposition computing system and a state display system, the method adopts 4 FPGA devices to analyze pressure adopted signals, and the system is too complex and does not meet the requirement of simplifying the system when an airplane all-electric brake system is designed.
Disclosure of Invention
In order to overcome the defect that the existing fault detection method is complex in system, the invention provides a fault detection method for a pressure sensor of an all-electric brake system of an airplane. The method comprises the steps of firstly collecting pressure borne by a braked wheel through a pressure feedback signal collection circuit through a four-wire system pressure sensor, then carrying out filtering conditioning on the collected pressure feedback signal by adopting a Butterworth low-pass filter to eliminate noise, then sending the pressure feedback signal into a pressure sensor fault detection circuit, and detecting that the output voltage of the pressure sensor is positive voltage or negative voltage so as to carry out fault diagnosis on the four-wire system pressure sensor. The method can quickly detect the fault problem when the four-wire system pressure sensor of the airplane electric brake system has a fault, so that corresponding fault-tolerant control can be performed on the fault problem of the four-wire system pressure sensor of the airplane electric brake system, the normal operation of the airplane brake system is ensured, the reliability of the airplane brake system is effectively improved, and the system is simple and reliable.
The technical scheme adopted by the invention for solving the technical problems is as follows: a method for detecting faults of a pressure sensor of an all-electric brake system of an airplane is characterized by comprising the following steps: the fault detection system for the pressure sensor of the airplane electric brake system comprises a four-wire system pressure sensor, a pressure feedback signal conditioning circuit, a pressure sensor fault detection circuit, a fault detection signal conditioning circuit and a CPU. The four-wire system pressure sensor collects the brake pressure of the airplane wheel braked by the airplane through the pressure collecting circuit, outputs the brake pressure value, sends the brake pressure value into the pressure sensor fault detection circuit after passing through the pressure feedback signal conditioning circuit, detects faults of the pressure sensor, and sends fault detection signals into the fault control module CPU after passing through the fault detection signal conditioning circuit. The fault detection method comprises the following steps:
firstly, a four-wire system pressure sensor is adopted to acquire a brake pressure feedback value of an airplane braked wheel through a pressure feedback signal acquisition circuit.
And secondly, sending the brake pressure feedback signal to a conditioning circuit, filtering and conditioning by adopting a second-order Butterworth low-pass filter, and eliminating noise so as to facilitate a later-stage fault detection circuit to carry out fault detection.
And thirdly, collecting the filtered and conditioned pressure feedback signal by a pressure sensor fault detection circuit, and judging that the brake pressure feedback signal is positive voltage or negative voltage. If the pressure feedback signal is negative voltage, the pressure sensor is in fault, and the fault detection circuit outputs a fault signal; if the pressure feedback signal is positive voltage, the pressure sensor is normal, and the fault detection circuit outputs a normal signal.
And fourthly, acquiring output signals of the fault detection circuit by the fault detection signal processing circuit, and conditioning the output signals into voltage signals which can be identified by the AD port of the CPU by adopting an amplitude limiting circuit.
And fifthly, the CPU receives the conditioned fault diagnosis signal, and if the fault detection circuit outputs the fault signal, the CPU performs corresponding fault reporting aiming at the fault signal to perform fault tolerance control.
Further, the pressure feedback signal acquisition circuit is AD620 of Analog Devices.
Further, the second order butterworth low pass filter is an OP07 operational amplifier from Texas Instruments.
Furthermore, the pressure sensor fault detection circuit is composed of two comparison circuits, a brake pressure feedback signal of an airplane braked wheel is compared with a high level signal and a low level signal through the two comparison circuits respectively, and then a fault diagnosis signal is obtained through an AND gate.
Further, the amplitude limiting circuit adopts a BAT54S circuit, so that a subsequent stage fault detection circuit can detect faults.
Further, the CPU employs TMS320F812 from Texas Instruments.
The invention has the beneficial effects that: the method comprises the steps of firstly collecting pressure borne by a braked wheel through a pressure feedback signal collection circuit through a four-wire system pressure sensor, then carrying out filtering conditioning on the collected pressure feedback signal by adopting a Butterworth low-pass filter to eliminate noise, then sending the pressure feedback signal into a pressure sensor fault detection circuit, and detecting that the output voltage of the pressure sensor is positive voltage or negative voltage so as to carry out fault diagnosis on the four-wire system pressure sensor. The method can quickly detect the fault problem when the four-wire system pressure sensor of the airplane electric brake system has a fault, so that corresponding fault-tolerant control can be performed on the fault problem of the four-wire system pressure sensor of the airplane electric brake system, the normal operation of the airplane brake system is ensured, the reliability of the airplane brake system is effectively improved, and the system is simple and reliable.
Specifically, the method comprises the following steps: firstly, when the airplane electric brake system operates, a four-wire system pressure sensor is adopted to collect pressure borne by a braked airplane wheel, a feedback pressure signal is processed by a second-order Butterworth low-pass filter and then is sent to a fault detection circuit, a control chip collects a fault signal output by the fault detection circuit for fault-tolerant control, so that when the pressure sensor fails, a fault problem can be quickly detected, a fault signal is generated, and the reliable operation of the airplane electric brake system is ensured;
secondly, the invention can realize the fault detection of the four-wire system pressure sensor by adopting 1 controller CPU, has simple system structure and accurate measurement, and is also suitable for the fault detection of other four-wire system pressure sensors.
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
Drawings
FIG. 1 is a block diagram of a system for detecting faults of an electric brake pressure sensor of an airplane according to the method of the present invention.
FIG. 2 is a block diagram of a four wire system pressure sensor in the method of the present invention.
Fig. 3 is a schematic diagram of a fault detection circuit in the method of the present invention.
Detailed Description
The following examples refer to fig. 1-3. The method for detecting the faults of the pressure sensor of the all-electric brake system of the airplane comprises the following steps:
the system for the fault detection method of the pressure sensor of the airplane electric brake system comprises a four-wire system pressure sensor, a pressure feedback signal conditioning circuit, a pressure sensor fault detection circuit, a fault detection signal conditioning circuit and a CPU. The four-wire system pressure sensor collects the brake pressure of the airplane wheel braked by the airplane through the pressure collecting circuit, outputs the brake pressure value, sends the brake pressure value into the pressure sensor fault detection circuit after passing through the pressure feedback signal conditioning circuit, carries out fault pressure sensor fault detection, and sends a fault detection signal into the fault control module CPU after passing through the fault detection signal conditioning circuit.
In the embodiment, TMS320F2812 of Texas Instruments is used as a control chip, a permanent magnet brushless direct current motor is used as a servo motor of an airplane all-electric brake system, IR2136 is used as a three-phase bridge circuit driving chip, and a four-wire system pressure sensor is used as a system pressure acquisition device.
The method for detecting the faults of the pressure sensor of the all-electric brake system of the airplane comprises the following specific steps:
firstly, a four-wire system Pressure sensor collects a Pressure signal Pressure borne by a braked wheel of the airplane through a Pressure feedback signal collecting circuit.
And secondly, filtering the Pressure feedback signal by adopting a second-order Butterworth low-pass Filter to reduce the noise of the Pressure feedback signal, wherein the filtered Pressure feedback signal is Pressure _ Filter.
Thirdly, sending the filtered Pressure feedback signal Pressure _ flag to a Pressure sensor Fault detection circuit, wherein if the Pressure sensor fails, the Fault circuit outputs a Fault signal Pre _ Fault which is 1, and the device Fault reports error; if the pressure sensor is normal, the Fault detection circuit outputs a normal signal Pre _ Fault which is equal to 0, and the device is normal.
And fourthly, after the output signal of the fault signal detection circuit passes through a conditioning circuit, conditioning the output signal into a voltage signal which can be identified by an AD port of the CPU of the control chip, and then inputting the voltage signal into the CPU through a filter circuit.
And fifthly, judging whether to carry out fault-tolerant control or not according to corresponding signals after the control chip CPU receives the output signals of the pressure sensor fault detection circuit.
Further, the pressure acquisition circuit in step one is composed of AD620 of Analog Devices.
Further, the second order butterworth low pass filter in step two consists of an OP07 operational amplifier from Texas Instruments.
Furthermore, the fault detection circuit in the third step is composed of two comparison circuits, the brake pressure feedback signal of the airplane braked wheel is compared with a high level signal and a low level signal through the two comparison circuits, and then the fault diagnosis signal is obtained through an AND gate.
Further, the BAT54S is adopted by the amplitude limiting circuit in the fourth step to form an amplitude limiting circuit of ± 3.3V, so that the subsequent fault detection circuit can perform fault detection.
Further, the controller CPU in step five employs Texas Instruments TMS320F 812.
Furthermore, the brake pressure feedback signals of the filtered and conditioned airplane braked wheels are collected, when the four-wire system pressure sensor normally operates, the output signals of the pressure sensor are positive voltages, and when the four-wire system pressure sensor fails, the situation that the sensor outputs negative voltages can occur. Therefore, the brake pressure feedback signal of the airplane braked wheel is compared with a high level signal and a low level signal respectively through two comparison circuits, and then a fault diagnosis signal is obtained through an AND gate. If the pressure sensor is normal, the two comparators output high level, and the AND gate outputs high level pressure sensor which is normal; if the fault occurs, the comparator which is compared with the low level outputs the low level, the fault detection circuit outputs the fault of the low level pressure sensor, and the fault of the device is reported in error.
Claims (6)
1. A method for detecting faults of a pressure sensor of an all-electric brake system of an airplane is characterized by comprising the following steps: the fault detection system for the pressure sensor of the airplane all-electric brake system comprises a four-wire system pressure sensor, a pressure feedback signal conditioning circuit, a pressure sensor fault detection circuit, a fault detection signal conditioning circuit and a CPU (central processing unit); the four-wire system pressure sensor acquires the brake pressure of the airplane braked wheel through the pressure acquisition circuit, outputs a brake pressure value, sends the brake pressure value into the pressure sensor fault detection circuit after passing through the pressure feedback signal conditioning circuit, performs fault detection on the pressure sensor, and sends a fault detection signal into the fault control module CPU after passing through the fault detection signal conditioning circuit; the fault detection method comprises the following steps:
the method comprises the following steps that firstly, a four-wire system pressure sensor is adopted to collect a brake pressure feedback value of an airplane braked wheel through a pressure feedback signal collecting circuit;
secondly, sending the brake pressure feedback signal to a conditioning circuit, and carrying out filtering conditioning by adopting a second-order Butterworth low-pass filter to eliminate noise so as to facilitate a later-stage fault detection circuit to carry out fault detection;
thirdly, the pressure sensor fault detection circuit collects the filtered and conditioned pressure feedback signal and judges whether the brake pressure feedback signal is positive voltage or negative voltage; if the pressure feedback signal is negative voltage, the pressure sensor is in fault, and the fault detection circuit outputs a fault signal; if the pressure feedback signal is positive voltage, the pressure sensor is normal, and the fault detection circuit outputs a normal signal;
fourthly, the fault detection signal processing circuit collects output signals of the fault detection circuit and conditions the output signals into voltage signals which can be identified by an AD port of the CPU by adopting an amplitude limiting circuit;
and fifthly, the CPU receives the conditioned fault diagnosis signal, and if the fault detection circuit outputs the fault signal, the CPU performs corresponding fault reporting aiming at the fault signal to perform fault tolerance control.
2. The method for detecting the fault of the pressure sensor of the all-electric brake system of the aircraft according to claim 1, wherein: the pressure feedback signal acquisition circuit is AD620 of Analog Devices.
3. The method for detecting the fault of the pressure sensor of the all-electric brake system of the aircraft according to claim 1, wherein: the second order butterworth low pass filter is an OP07 operational amplifier from Texas Instruments.
4. The method for detecting the fault of the pressure sensor of the all-electric brake system of the aircraft according to claim 1, wherein: the pressure sensor fault detection circuit is composed of two comparison circuits, a brake pressure feedback signal of an airplane braked wheel is compared with a high level signal and a low level signal through the two comparison circuits respectively, and then a fault diagnosis signal is obtained through an AND gate.
5. The method for detecting the fault of the pressure sensor of the all-electric brake system of the aircraft according to claim 1, wherein: the amplitude limiting circuit adopts a BAT54S circuit so that a subsequent stage fault detection circuit can detect faults.
6. The method for detecting the fault of the pressure sensor of the all-electric brake system of the aircraft according to claim 1, wherein: the CPU employs TMS320F812 from Texas Instruments.
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| CN201810742106.7A CN108871670B (en) | 2018-07-09 | 2018-07-09 | Fault detection method for pressure sensor of airplane all-electric brake system |
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| JPH0847287A (en) * | 1994-08-04 | 1996-02-16 | Mitsuba Electric Mfg Co Ltd | Protection circuit on failure of hall element of motor |
| CN101520468B (en) * | 2009-04-09 | 2011-04-20 | 中国兵器工业集团第七0研究所 | Magnetoelectric sensor adjusting circuit |
| CN202608760U (en) * | 2012-05-31 | 2012-12-19 | 西北工业大学 | Airplane double-redundancy electric-brake device |
| CN202614450U (en) * | 2012-05-31 | 2012-12-19 | 西北工业大学 | Aircraft electric brake pressure transducer redundancy apparatus |
| CN106644256A (en) * | 2016-11-24 | 2017-05-10 | 安徽皖拓自动化有限公司 | Pressure sensor fault diagnosis device and diagnosis method thereof |
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Effective date of registration: 20210419 Address after: 710089 block B, Dier Industrial Park, Yanliang National Aviation high tech industrial base, Xi'an City, Shaanxi Province Patentee after: Xi'an Tiancheng Aviation Technology Co.,Ltd. Address before: 710072 Xi'an friendship West Road, Shaanxi, No. 127 Patentee before: Northwestern Polytechnical University |
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