CN113002802B - Airplane wheel speed sensor with state output function - Google Patents
Airplane wheel speed sensor with state output function Download PDFInfo
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- CN113002802B CN113002802B CN202110299152.6A CN202110299152A CN113002802B CN 113002802 B CN113002802 B CN 113002802B CN 202110299152 A CN202110299152 A CN 202110299152A CN 113002802 B CN113002802 B CN 113002802B
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- 238000009434 installation Methods 0.000 claims description 3
- 238000009429 electrical wiring Methods 0.000 claims 1
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- 238000006243 chemical reaction Methods 0.000 description 5
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Aviation & Aerospace Engineering (AREA)
- Regulating Braking Force (AREA)
Abstract
An airplane wheel speed sensor with a state output function comprises an electric motorThe connector, the open/short circuit detection module, the coil, the resistor and the square wave generation module are arranged on an airplane brake wheel and used for outputting stronger anti-jamming capability and peak-peak value V with load for an airplane electronic anti-skid controller P‑P A square wave signal of 6v.dc with a frequency magnitude proportional to the magnitude of the aircraft speed. The invention can monitor the working state of the wheel speed sensor in real time while meeting the requirement of speed acquisition of the brake wheel. And three electrical fault signals of the airplane wheel speed sensor and three mechanism or mechanical connection fault signals can be accurately output to the electronic anti-skid controller, so that the fault of the airplane wheel speed sensor can be found at the first time, the outfield fault can be found and processed early, the problem of reporting the fault of the speed sensor in the process of sliding, taking off or landing of the airplane is solved, partial fault of the airplane wheel speed sensor is eliminated, the outfield fault rate of the airplane wheel speed sensor is reduced by 15%, and the reliability is improved by 6%.
Description
Technical Field
The invention relates to the field of airplane brake systems, in particular to an airplane wheel speed sensor with a state output function.
Background
The aircraft brake system consists of a normal brake system, a static brake system and an emergency brake system. The normal braking system consists of a pressure reducing valve, an electro-hydraulic pressure servo valve, a conversion valve, a batcher, a speed sensor and an electronic anti-skid controller; the emergency brake system consists of an emergency brake valve, a conversion valve and a batcher; the static braking system consists of a hydraulic electromagnetic valve, a conversion valve and a batcher. See in particular table 1 for aircraft brake system accessories.
TABLE 1 aircraft braking System Accessories
| Serial number | Name (R) | Product Properties | Number of | Remarks to note |
| 1 | Pressure reducing valve | |
4 | |
| 2 | Electrohydraulic pressure servo valve | |
2 | Product built-in |
| 3 | Conversion valve | |
4 | |
| 4 | Quantitative device | |
4 | |
| 5 | Emergency brake valve | |
1 | |
| 6 | Speed sensor | Electrical product | 8 | Built-in control coil of product |
| 7 | Electronic anti-skid controller | |
1 | Built-in electronic control circuit of product |
| 8 | Hydraulic electromagnetic valve | |
1 |
HB6761 "airplane wheel brake system design requirements" chapter on airplane anti-skid brake system fault detection and warning requires "brake system fault detection should provide a light or sound fault indication. The fault detection can never affect the normal operation of the system. Warning lights or fault displays in the cabin should be placed in a significant area within the driver's field of view when the aircraft is landing and braking ".
The wheel speed sensor in the prior art is a magnetoelectric wheel speed sensor, outputs an approximate sine wave signal when the wheel speed sensor works, the signal frequency is in direct proportion to the speed of an airplane, and the sensor-free fault detection function is realized. The magnetoelectric machine wheel speed sensor has two types according to the magnetic field forming mode, one type is an excitation machine wheel speed sensor, and the other type is a permanent magnet machine wheel speed sensor.
The airplane wheel speed sensor is mounted on an airplane wheel brake device, is connected with a brake airplane wheel through an airplane wheel speed sensor support, and detects the speed of the brake airplane wheel in real time, namely an externally mounted airplane wheel speed sensor; the other sensor is arranged in a lifting frame shaft and is connected with a brake wheel through a wheel speed sensor shifting fork to detect the speed of the brake wheel in real time, and the sensor is called an internal wheel speed sensor for short.
The antiskid braking system of the airplane has higher and higher requirements on six general quality characteristics, namely safety, reliability, maintainability, testability, supportability and environmental adaptability. The electronic anti-skid controller of the anti-skid brake system of the airplane in the prior art has the functions of detecting and positioning the faults of the speed sensor coil. The fault detection function of the wheel speed sensor in the airplane antiskid braking system is realized by an open/short circuit detection module in an electronic antiskid controller.
When the airplane wheel speed sensor is used, 6 common fault modes are available, specifically, 1, the opening/short circuit fault of a coil of the airplane wheel speed sensor is detected; 2. wheel speed sensor plug seat failure; 3. an on/short circuit fault of the wheel speed sensor electrical line; 4. wheel speed sensor jamming or half-jamming failure; 5. the rotating speed transmission mechanism of the brake wheel breaks down; 6. wheel speed sensor installation failure.
The invention discloses a wheel speed sensor in the invention with the application number of CN201821199740.2, and the invention discloses a screw cap fixed on the inner surface of a shell; the motor mounting seat is fixed on the outer end face of the screw cap, and a cylinder body of the motor mounting seat is arranged in the shell; the internal tooth ring is positioned in the middle part in the shell, and the cylinder of the motor mounting seat is arranged in the shell; the inner tooth ring is positioned in the middle of the shell, and the outer circumferential surface of the inner tooth ring is in clearance fit with the inner surface of the shell; the hollow rotor component is positioned in the middle of the shell, and a fit clearance is formed between the hollow rotor component and the inner circumferential surface of the inner tooth ring and between the hollow rotor component and the end surface of the inner-layer cylinder of the lead magnet; the transmission shaft support sleeve is positioned in the hollow rotor component transmission part and is in transition fit with the inner surface of the hollow rotor component transmission part. However, the invention only describes the structure of the wheel speed sensor, does not describe the speed signal processing mode and requirements, and does not have a state output signal;
an aircraft wheel speed sensor is disclosed in the invention with application number CN201480026828.2, which comprises a pair of conductors coupled between an electromechanical system and a control system. The control system is configured to apply a carrier voltage signal to the pair of conductors and detect a modulated current signal on the pair of conductors. The electromechanical system includes a stator, and a rotor that moves as the aircraft wheel rotates. The stator includes windings disposed around the rotor. The windings are configured to generate a modulated current signal on the pair of conductors in response to movement of the rotor. The modulated current signal has a frequency that depends on the rotational speed of the aircraft wheel. The modulation frequency is determined by demodulation. The peak amplitude of the modulated signal remains constant over the entire range of detected speeds. The rotor may have a plurality of primary teeth around which the stator coil is wound, each primary tooth having a plurality of secondary teeth on an inner periphery. The shape of the teeth provided on the rotor may correspond to the shape of the secondary teeth on the stator. The invention describes the processing and using method of the speed signal in the braking system, but the speed sensor has no state output signal.
The invention with the application number of 201520179855.5 discloses a conversion circuit of a wheel speed sensor, which comprises a voltage comparison circuit and a signal coupling circuit, wherein an input signal is coupled to the voltage comparison circuit through the signal coupling circuit, and the voltage comparison circuit outputs a pulse signal with equal positive and negative time widths. The invention overcomes the defect that the prior speed sensor detection circuit can only output sine wave signals, can directly output square waves and ensure the consistency of high and low level time widths, but the invention creates a speed signal acquisition circuit belonging to an electronic anti-skid controller, the circuit is not integrated in a speed sensor, and the invention does not solve the problem of speed sensor fault detection.
Disclosure of Invention
In order to overcome the defect that the wheel speed sensor in the prior art cannot detect faults in real time due to the fact that the wheel speed sensor does not have a state output function, the invention provides the wheel speed sensor with the state output function.
The invention comprises an electric connector, an open/short circuit detection module, a coil, a resistor and a square wave generation module; after being connected in parallel with one end of the resistor, the power end of the square wave generation module and the power end of the open/short circuit detection module are communicated with the pin A of the electric connector through a lead; the pin A of the electric connector is communicated with the output end of a +28VDC power supply; the other end of the resistor is communicated with one end of the coil, and the signal input end of the square wave generation module is connected with the signal input end of the open/short circuit detection module in parallel and then is connected to a lead connecting the resistor and the coil through a lead.
And the other end of the coil, the power ground wire of the open/short circuit detection module and the power ground wire of the square wave generation module are connected in parallel and then are communicated with a D pin of the electric connector. The D pin of the electric connector is communicated with a power ground wire; the D pin of the connector is connected with the cathode of the wheel speed signal acquisition end of the electronic anti-skid controller; and the D pin of the electric connector is communicated with the ground wire of the electronic anti-skid controller through a lead.
The square wave signal output end of the square wave generating module is communicated with a pin B of the electric connector through a lead; the B pin of the electric connector is connected with the anode of the wheel speed signal acquisition end of the electronic anti-skid controller, and the wheel speed signal acquisition end directly acquires a square wave signal which is consistent with the wheel speed.
The output end of the open/short circuit detection module is communicated with a C pin of the electric connector through a lead; the C pin of the electric connector is connected with an airplane wheel speed state signal acquisition interface of the electronic anti-skid controller; the C pin of the electrical connector outputs a normal operation signal of the wheel speed sensor, an open-circuit fault signal of the wheel speed sensor and a short-circuit fault signal of the wheel speed sensor.
The airplane wheel speed sensor is arranged on an airplane brake wheel and is powered by a direct current power supply, and a square wave signal and a speed sensor state signal which are consistent with the speed are output to the electronic anti-skid controller.
The airplane wheel speed sensor can accurately judge and monitor the working state of the airplane wheel speed sensor in real time.
When the airplane is in a static state and the airplane wheel speed sensor is not in fault, the airplane wheel speed sensor outputs a signal that the airplane wheel speed sensor works normally.
When the airplane is in a static state and three electrical or line faults occur to the airplane wheel speed sensor, the airplane wheel speed sensor outputs three electrical fault signals; the three electrical or line faults include a wheel speed sensor coil on/short circuit fault, a wheel speed sensor plug and a wheel speed sensor electrical line on/short circuit fault.
And II, when the airplane stops on the parking apron, the jack jacks the airplane, and the airplane wheel speed sensor has no fault, the brake airplane wheel is rotated, and the airplane wheel speed sensor outputs a signal that the airplane wheel speed sensor works normally.
When the three mechanisms and mechanical connection faults of the airplane wheel speed sensor occur, the airplane wheel speed sensor outputs corresponding fault signals; the three mechanism and mechanical connection faults comprise a jamming or semi-jamming fault of the airplane wheel speed sensor, a fault of a brake airplane wheel rotating speed transmission mechanism and a fault of the airplane wheel speed sensor installation.
The invention is arranged on the braking wheel of the airplane, the antiskid braking system of the airplane is electrified, and the power is supplied by the direct-current power supply, so that the electronic antiskid controller of the airplane has stronger output anti-jamming capability and carries a peak-peak value V P-P A square wave signal of 6v.dc and frequency magnitude proportional to aircraft speed magnitude. The invention can monitor the working state of the wheel speed sensor in real time while meeting the requirement of speed acquisition of the brake wheel. And three electrical fault signals of the wheel speed sensor and three mechanical or mechanical connection fault signals can be accurately output to the electronic anti-skid controller.
In the invention, the antiskid braking system of the airplane is electrified, the speed sensor of the airplane wheel can realize the function of outputting the state information, and the working state of the speed sensor of the airplane wheel can be accurately judged and monitored in real time.
The invention can output peak-peak value V by adding the open/short circuit detection module 2, the resistor 4 and the square wave generation module 5 on the prior airplane wheel speed sensor P-P The square wave signal of 6V.DC, improves the anti-jamming capability of the airplane wheel speed sensor, simultaneously improves the stability of the speed signal output by the airplane wheel speed sensor, and solves the problem of unstable speed signal in a low-speed state.
The invention can realize the real-time monitoring of the airplane wheel speed sensor, and can accurately monitor the normal working signal, the three electrical fault signals and the three mechanism and mechanical connection fault signals of the airplane wheel speed sensor during the airplane shutdown inspection; the fault of the airplane wheel speed sensor can be found at the first time, so that the outfield fault can be found and processed early, and the problem of reporting the fault of the speed sensor in the process of airplane taxiing, taking-off or landing is solved; the fault of the airplane wheel speed sensor is eliminated, the outfield fault rate of the airplane wheel speed sensor is reduced by 15%, and the reliability of the speed sensor is improved by 6%.
Drawings
FIG. 1 is a prior art electrical block diagram of a wheel speed sensor;
fig. 2 is an electrical block diagram of the wheel speed sensor of the present invention.
In the figure: 1 an electrical connector; 2 an open/short circuit detection module; 3, a coil; 4, resistance; and 5, a square wave generation module.
Detailed Description
The embodiment is a wheel speed sensor of a braking system of an airplane of a certain type. The airplane wheel speed sensor is obtained by adding an open/short circuit detection module 2, a resistor 4 and a square wave generation module 5 on the basis of the existing airplane wheel speed sensor; the airplane wheel speed sensor can realize state signal output and direct output of square wave signals;
the airplane wheel speed sensor of the embodiment is composed of an electric connector 1, an open/short circuit detection module 2, a coil 3, a resistor 4 and a square wave generation module 5; after the power end of the square wave generating module 5, the power end of the open/short circuit detecting module 2 and one end of the resistor 4 are connected in parallel, the power ends are communicated with the pin A of the electric connector 1 through wires; the pin A of the electric connector 1 is communicated with the output end of a +28VDC power supply; the other end of the resistor 4 is communicated with one end of the coil 3, and a signal input end of the square wave generating module 5 is connected in parallel with a signal input end of the open/short circuit detecting module 2 and then is connected to a wire connecting the resistor 4 and the coil 3 through a wire.
And the other end of the coil 3, the power ground wire of the open/short circuit detection module 2 and the power ground wire of the square wave generation module 5 are connected in parallel and then are communicated with the D pin of the electric connector 1. The D pin of the electric connector 1 is communicated with a power supply ground wire; the D pin of the connector 1 is connected with the negative electrode of the airplane wheel speed signal acquisition end of the electronic anti-skid controller; and the D pin of the electric connector 1 is communicated with the ground wire of the electronic anti-skid controller through a lead.
The square wave signal output end of the square wave generating module 5 is communicated with a pin B of the electric connector 1 through a lead; the B pin of the electric connector 1 is connected with the anode of the wheel speed signal acquisition end of the electronic anti-skid controller, and the wheel speed signal acquisition end directly acquires a square wave signal which is consistent with the wheel speed.
The output end of the open/short circuit detection module 2 is communicated with a pin C of the electric connector 1 through a lead; the C pin of the electric connector 1 is connected with an airplane wheel speed state signal acquisition interface of the electronic anti-skid controller; the C pin of the electrical connector 1 outputs a normal operation signal of the wheel speed sensor, an open-circuit failure signal of the wheel speed sensor and a short-circuit failure signal of the wheel speed sensor.
The airplane wheel speed sensor is applied to an airplane antiskid braking system;
the airplane wheel speed sensor with the output state signal is arranged on an airplane brake wheel, and an airplane antiskid brake system is electrified and can directly supply power through a direct-current power supply to output a square wave signal and a speed sensor state signal which are consistent with the speed to an electronic antiskid controller; the airplane wheel speed sensor can monitor the working state in real time while the airplane wheel speed signal acquisition is met. Three electrical faults of the airplane wheel speed sensor and three mechanism or mechanical connection fault signals can be output to the standard electromechanical integrated controller of the electromechanical system accurately.
Claims (3)
1. The airplane wheel speed sensor with the state output function is characterized by comprising an electric connector, an open/short circuit detection module, a coil, a resistor and a square wave generation module; after the power end of the square wave generation module and the power end of the open/short circuit detection module are connected with one end of the resistor in parallel, the power ends are communicated with the pin A of the electric connector through wires; the pin A of the electric connector is communicated with the output end of a +28VDC power supply; the other end of the resistor is communicated with one end of the coil, and a signal input end of the square wave generation module is connected with a signal input end of the open/short circuit detection module in parallel and then is connected to a lead for connecting the resistor and the coil through a lead;
the other end of the coil, a power ground wire of the open/short circuit detection module and a power ground wire of the square wave generation module are connected in parallel and then communicated with a D pin of the electric connector; the D pin of the electric connector is communicated with a power ground wire; the D pin of the connector is connected with the negative electrode of the airplane wheel speed signal acquisition end of the electronic anti-skid controller; the D pin of the electric connector is communicated with the ground wire of the electronic anti-skid controller through a lead;
the square wave signal output end of the square wave generating module is communicated with a pin B of the electric connector through a lead; the B pin of the electric connector is connected with the anode of the airplane wheel speed signal acquisition end of the electronic anti-skid controller, and the airplane wheel speed signal acquisition end directly acquires a square wave signal which is consistent with the speed of the airplane wheel;
the output end of the open/short circuit detection module is communicated with a C pin of the electric connector through a lead; the C pin of the electric connector is connected with an airplane wheel speed state signal acquisition interface of the electronic anti-skid controller; the C pin of the electric connector outputs a normal working signal of the airplane wheel speed sensor, an open-circuit fault signal of the airplane wheel speed sensor and a short-circuit fault signal of the airplane wheel speed sensor;
the airplane wheel speed sensor is arranged on an airplane brake wheel and is powered by a direct-current power supply to output a square wave signal and a speed sensor state signal which are consistent with the speed to the electronic anti-skid controller;
the airplane wheel speed sensor can accurately judge and monitor the working state of the airplane wheel speed sensor in real time;
i, when the airplane is in a static state and the airplane wheel speed sensor has no fault, the airplane wheel speed sensor outputs a signal that the airplane wheel speed sensor works normally;
when the airplane is in a static state and three electrical or line faults occur in the airplane wheel speed sensor, the airplane wheel speed sensor outputs three electrical fault signals;
II, when the airplane stops on the parking apron and is jacked up by using a jack, and the airplane wheel speed sensor has no fault, rotating the brake airplane wheel, and outputting a normal working signal of the airplane wheel speed sensor by the airplane wheel speed sensor;
when the wheel speed sensor has three mechanism and mechanical connection faults, the wheel speed sensor outputs corresponding fault signals.
2. A wheel speed sensor with status output function as claimed in claim 1 wherein said three electrical or wiring faults include a wheel speed sensor coil on/short circuit fault, a wheel speed sensor plug receptacle fault and a wheel speed sensor electrical wiring on/short circuit fault.
3. A wheel speed sensor with status output function as claimed in claim 1 wherein said three mechanism and mechanical connection failures include wheel speed sensor stuck or semi-stuck failure, brake wheel speed transmission failure and wheel speed sensor installation failure.
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| CN202110299152.6A CN113002802B (en) | 2021-03-20 | 2021-03-20 | Airplane wheel speed sensor with state output function |
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| CN202110299152.6A CN113002802B (en) | 2021-03-20 | 2021-03-20 | Airplane wheel speed sensor with state output function |
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| CN113002802B true CN113002802B (en) | 2023-02-07 |
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| US4871993A (en) * | 1987-07-03 | 1989-10-03 | Kanto Seiki Co., Ltd. | Self-diagnostic apparatus for vehicle meter |
| EP0586942A1 (en) * | 1992-09-10 | 1994-03-16 | Eaton Corporation | A wheel speed sensor input circuit with sensor status detection |
| CN104198754A (en) * | 2014-09-11 | 2014-12-10 | 中国人民解放军海军航空工程学院青岛校区 | Aero-engine rotation speed testing system |
| CN109407000A (en) * | 2017-08-17 | 2019-03-01 | 中国航发商用航空发动机有限责任公司 | Alternator failure detection circuit and method |
| CN110488140A (en) * | 2019-09-20 | 2019-11-22 | 无锡麦道电子科技有限公司 | A kind of electromagnet fault detection circuit device and its detection method |
| CN111122908A (en) * | 2019-12-30 | 2020-05-08 | 中国科学院工程热物理研究所 | Circuit design device and method for self-detecting faults of aircraft engine speed sensor |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06160427A (en) * | 1992-11-18 | 1994-06-07 | Sumitomo Electric Ind Ltd | Rotation sensor and failure detection method thereof |
| JP2005249516A (en) * | 2004-03-03 | 2005-09-15 | Toyota Motor Corp | Signal processing circuit and wheel speed signal processing circuit |
| US9720024B2 (en) * | 2014-12-02 | 2017-08-01 | Nxp Usa, Inc. | Sensor circuit, vehicle and method therefor |
| CN109521310B (en) * | 2019-01-10 | 2024-01-12 | 华奥安心技术服务(集团)股份有限公司 | Fault simulation detection analyzer for vehicle braking system and detection method thereof |
-
2021
- 2021-03-20 CN CN202110299152.6A patent/CN113002802B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4871993A (en) * | 1987-07-03 | 1989-10-03 | Kanto Seiki Co., Ltd. | Self-diagnostic apparatus for vehicle meter |
| EP0586942A1 (en) * | 1992-09-10 | 1994-03-16 | Eaton Corporation | A wheel speed sensor input circuit with sensor status detection |
| CN104198754A (en) * | 2014-09-11 | 2014-12-10 | 中国人民解放军海军航空工程学院青岛校区 | Aero-engine rotation speed testing system |
| CN109407000A (en) * | 2017-08-17 | 2019-03-01 | 中国航发商用航空发动机有限责任公司 | Alternator failure detection circuit and method |
| CN110488140A (en) * | 2019-09-20 | 2019-11-22 | 无锡麦道电子科技有限公司 | A kind of electromagnet fault detection circuit device and its detection method |
| CN111122908A (en) * | 2019-12-30 | 2020-05-08 | 中国科学院工程热物理研究所 | Circuit design device and method for self-detecting faults of aircraft engine speed sensor |
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