CN111220814A - Airplane wheel speed acquisition system and fault detection method - Google Patents
Airplane wheel speed acquisition system and fault detection method Download PDFInfo
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- CN111220814A CN111220814A CN201911097665.8A CN201911097665A CN111220814A CN 111220814 A CN111220814 A CN 111220814A CN 201911097665 A CN201911097665 A CN 201911097665A CN 111220814 A CN111220814 A CN 111220814A
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- 238000001514 detection method Methods 0.000 title claims abstract description 71
- 230000007274 generation of a signal involved in cell-cell signaling Effects 0.000 claims abstract description 9
- 238000012423 maintenance Methods 0.000 claims abstract description 8
- 238000006243 chemical reaction Methods 0.000 claims description 22
- 238000000034 method Methods 0.000 claims description 2
- 238000002955 isolation Methods 0.000 abstract description 5
- 230000000694 effects Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 6
- 239000000306 component Substances 0.000 description 4
- 230000007547 defect Effects 0.000 description 2
- 239000008358 core component Substances 0.000 description 1
- 230000003137 locomotive effect Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
- G01P3/42—Devices characterised by the use of electric or magnetic means
- G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
- G01P3/48—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
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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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Abstract
The invention provides an airplane wheel speed acquisition system and a fault detection method, wherein an airplane wheel speed sensor and a speed analog signal generation unit are both connected to the input end of an input switching unit, when detection is started, the input switching unit is communicated with the speed analog signal generation unit and is disconnected with the input switching unit, after detection is finished, the input switching unit is disconnected with the speed analog signal generation unit and the input switching unit through a switching enabling signal, and meanwhile, the airplane wheel speed sensor is communicated with the input switching unit. By adding the input switching unit, interference signals cannot enter the airplane wheel speed acquisition system from the outside through the airplane wheel speed sensor during detection; meanwhile, fault isolation is realized, and the invention realizes quick isolation, shortens maintenance time, improves ground maintenance efficiency and improves the overall detection effect.
Description
Technical Field
The invention relates to the field of airplane braking, in particular to a speed acquisition system and a fault detection method.
Background
The aircraft brake system is an important component of an aircraft electromechanical system, mainly realizes the brake function in the landing and sliding stage of the aircraft, and simultaneously shortens the sliding distance of the aircraft through the self-carried anti-skidding function of the system, thereby avoiding the skidding of the wheels of the aircraft.
At present, the brake system of domestic airplanes is mainly a digital telex antiskid brake system (hereinafter, the brake system is referred to as a digital telex antiskid brake system), and the system comprises a hydraulic source, a hydraulic pipeline, a brake instruction sensor, an airplane wheel speed sensor, a hydraulic servo valve, an antiskid brake control box, a brake device and other components. The antiskid brake control box is used as a core component of the whole brake system, and outputs a current signal to the hydraulic servo valve after comprehensive calculation by collecting signals output by other components, and the hydraulic servo valve outputs corresponding brake pressure to airplane wheels of the airplane according to the magnitude of the current signal, so that the airplane brake is realized. The principle schematic diagram of the aircraft braking system is shown in fig. 1.
The wheel speed signal is a frequency signal generated when the airplane wheel drives the wheel speed sensor to rotate. The antiskid brake control box converts the input wheel speed frequency signal into a corresponding digital quantity through an internal wheel speed acquisition system, and the digital quantity can directly reflect the speed. The wheel speed signal is used as an important input signal of the whole brake system, and plays an important role in judging the current road condition (such as whether water, snow, ice and the like exist on the road surface), the wheel slip state, whether the airplane is grounded and the like by the anti-skid brake control box. When the anti-skid brake control box identifies that the current runway is an ice runway or the wheels skid, the anti-skid brake control box reduces the brake pressure output to the wheels by the hydraulic servo valve by reducing the output current signal, so as to prevent the wheels from entering or releasing the skid state of the wheels; or when the airplane is not grounded, the antiskid brake control box actively inhibits the output of the current signal, and the airplane wheel is prevented from landing under pressure.
It can be seen that the reliability and accuracy of the wheel speed signal is critical to the braking system. Therefore, most of the antiskid brake control boxes can detect the state of the wheel speed acquisition system in the antiskid brake control boxes, and the antiskid brake control boxes are prevented from outputting wrong current signals due to faults of the wheel speed acquisition system.
The basic principle of the state detection of the wheel speed acquisition system is as follows: a speed analog signal generating unit in the anti-skid brake control box outputs a fixed frequency signal similar to an airplane wheel speed signal, namely a speed analog signal, the speed analog signal is connected to an input end of an airplane wheel speed acquisition system, the airplane wheel speed acquisition system firstly converts the frequency signal into a corresponding speed voltage signal through a frequency-voltage conversion unit, the speed voltage signal is converted into a corresponding speed digital signal through an analog-digital conversion unit, the speed digital signal is finally input into a CPU, the CPU compares the speed digital signal with the expected digital quantity, and when the deviation exceeds a threshold value, the speed signal acquisition system is defined to have a fault. At the moment, the anti-skid brake control box gives an alarm through the alarm lamp to remind maintenance personnel to check the anti-skid brake control box. The schematic diagram of the detection principle of the original wheel speed signal acquisition system is shown in fig. 2.
The detection mode of the wheel speed acquisition system is relatively simple, and whether the wheel speed acquisition circuit breaks down or not can be effectively detected. However, in this detection mode, the speed analog signal for detection is directly connected to the wheel speed acquisition circuit. If when carrying out wheel speed and collecting circuit detection, wheel speed sensor has frequency signal or interference signal output, and wheel speed signal and speed analog signal will superpose mutually, lead to the wheel speed voltage signal of wheel speed collection circuit output not to accord with expected voltage, and antiskid brake control box mistake deems wheel speed collection system trouble, forms false alarm, seriously influences braking system's normal work.
Meanwhile, according to the detection method, because the connection between the wheel speed sensor and the anti-skid brake control box is not disconnected, even if the wheel speed acquisition circuit is normal, when the wheel speed sensor is short-circuited, the speed analog signal does not flow into the wheel speed acquisition system any more, but is directly released to the ground wire through a short-circuit point, so that the anti-skid brake control box can also consider that the wheel speed acquisition system or the wheel speed sensor fails, but cannot be accurately positioned.
Therefore, the detection mode cannot carry out accurate fault isolation, namely when the airplane wheel speed acquisition system fails, whether the failure is caused by the self failure of the airplane wheel acquisition system or the failure of the airplane wheel speed sensor cannot be determined; meanwhile, the detection mode has poor anti-jamming capability, and once an interference signal exists on the wheel speed sensor, a false alarm is caused, so that the maintainability and the reliability of a brake system are reduced.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides an airplane wheel speed acquisition system and a fault detection method, aiming at optimizing the detection mode of the original airplane wheel speed acquisition system, ensuring that faults can be isolated to each brake component, improving the anti-jamming capability of a detection circuit and reducing the false alarm of a brake system.
The technical scheme adopted by the invention for solving the technical problems is as follows:
an airplane wheel speed acquisition system comprises a speed analog signal generating unit, an input switching unit, a frequency-voltage conversion unit, an analog-digital conversion unit and a CPU, wherein an airplane wheel speed sensor and the speed analog signal generating unit are connected to the input end of the input switching unit, when detection is started, the input switching unit is communicated with the speed analog signal generating unit and is disconnected from the airplane wheel speed sensor and the input switching unit, the input switching unit converts a signal into a speed voltage signal through the frequency-voltage conversion unit, the speed voltage signal is converted into a speed digital signal through the analog-digital conversion unit, the speed digital signal is input into the CPU, the CPU compares the speed digital signal with the expected digital quantity, and when the deviation exceeds a threshold value, the speed signal acquisition system is defined to be out of order, the anti-skid brake control box is warned by a warning lamp to remind maintenance personnel to check the anti-skid brake control box, meanwhile, a CPU feeds back a detection enabling signal to a speed analog signal generating unit, the speed analog signal generating unit inputs a speed analog signal input value into a switching unit to form a feedback loop, the CPU feeds back a switching enabling signal to an input switching unit to control the input switching unit, and switching of the speed analog signal generating unit and the airplane wheel speed sensor is realized; after detection is finished, the input switching unit disconnects the speed analog signal generating unit from the input switching unit through the switching enabling signal, and meanwhile, the airplane wheel speed sensor is communicated with the input switching unit.
The invention also provides a fault detection method of the airplane wheel speed acquisition system, which comprises the following detailed steps:
step 1: when the detection is started, the CPU sets the detection enable signal and the switching enable signal to be at a high level;
step 2: the speed analog signal generating unit generates a speed analog signal, the speed analog signal is output in a default non-speed analog signal mode, and when the speed analog signal generating unit detects that a detection enabling signal sent by a CPU is in a high level mode, the speed analog signal is output to the input end of the input switching unit;
and step 3: the input switching unit is used for switching an input source of the airplane wheel speed acquisition unit, the output end of the airplane wheel speed sensor is connected with the input end of the input switching unit by default, when the input switching unit detects that a switching enabling signal sent by a CPU is high level, the output end of the airplane wheel speed sensor is disconnected from the input end of the input switching unit, and the output end of the speed analog signal generation unit is connected with the input end of the input switching unit;
and 4, step 4: the frequency-voltage conversion unit outputs the speed analog signal to the airplane wheel speed voltage signal, converts the airplane wheel speed voltage signal into an airplane wheel speed digital signal through the analog-digital conversion unit and transmits the airplane wheel speed digital signal to the CPU through a data bus;
and 5: the CPU compares the airplane wheel speed digital signal with a threshold value, and when the deviation meets the requirement, the airplane wheel speed acquisition system is normal;
step 6: after the CPU finishes the detection of the airplane wheel speed acquisition system, setting the detection enabling signal and the switching enabling signal to be at a low level;
and 7: when the speed analog signal generating unit detects that the detection enabling signal sent by the CPU is at a low level, the speed analog signal is stopped to be output;
and 8: when the input switching unit detects that the switching enabling signal sent by the CPU is low level, the output end of the airplane wheel speed sensor is connected with the input end of the input switching unit, the output end of the speed analog signal generating unit is disconnected with the input end of the input switching unit, and the detection of the airplane wheel speed collecting system is completed.
The invention has the advantages that by adding the input switching unit, the airplane wheel speed sensor and the speed analog signal generating unit are not directly connected with the airplane wheel speed acquisition system any more, but are connected to the input end of the input switching unit together, meanwhile, the output end of the input switching unit is connected with the original airplane wheel speed acquisition system, when the airplane wheel speed acquisition system is detected, the input switching unit connects the speed analog signal generating unit with the airplane wheel speed acquisition system and disconnects the airplane wheel speed sensor from the airplane wheel speed acquisition system; after detection is finished, the input switching unit is disconnected with the speed analog signal generating unit and the airplane wheel speed collecting system, and meanwhile, the airplane wheel speed sensor is communicated with the airplane wheel speed collecting circuit. In this way, when the airplane wheel speed acquisition circuit detects, the interference signal can not enter the airplane wheel speed acquisition circuit from the outside through the airplane wheel speed sensor; meanwhile, the failure of the wheel speed sensor cannot cause the failure of the wheel speed acquisition system, so that the failure isolation is realized. After the detection of the airplane wheel speed acquisition circuit is completed, the airplane wheel speed sensor is connected with the airplane wheel speed acquisition circuit, so that an airplane wheel speed signal can enter the airplane wheel speed acquisition system, and the function of the airplane wheel speed acquisition system is not affected. The system realizes quick isolation during the speed acquisition of the locomotive, shortens the maintenance time, improves the ground maintenance efficiency and improves the overall detection effect.
Drawings
FIG. 1 is a schematic diagram of an aircraft braking system of the present invention.
Fig. 2 is a schematic diagram of a conventional wheel speed detection system.
FIG. 3 is a schematic diagram of the wheel speed detection system of the present invention.
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
The invention provides a detection method of a wheel speed acquisition system, which can avoid the influence of an external interference signal on a detection result when the wheel speed acquisition system is detected; meanwhile, the fault location can be accurate, and the defect that the fault location is inaccurate in the original detection mode is avoided. Therefore, the detection mode of the invention improves the reliability and the maintainability of the brake system.
The existing airplane wheel speed acquisition system causes the failure positioning of an original airplane wheel speed acquisition circuit, and the basic reason of poor anti-interference capability is that the airplane wheel speed acquisition system, a speed analog signal generation unit and an electric appliance of an airplane wheel speed sensor are mutually communicated. Therefore, the core of the present invention is that a schematic diagram of the detection principle of the wheel speed signal acquisition circuit of the present invention is shown in fig. 3.
An airplane wheel speed acquisition system comprises a speed analog signal generating unit, an input switching unit, a frequency-voltage conversion unit, an analog-digital conversion unit and a CPU, wherein an airplane wheel speed sensor and the speed analog signal generating unit are connected to the input end of the input switching unit, when detection is started, the input switching unit is communicated with the speed analog signal generating unit and is disconnected from the airplane wheel speed sensor and the input switching unit, the input switching unit converts a signal into a speed voltage signal through the frequency-voltage conversion unit, the speed voltage signal is converted into a speed digital signal through the analog-digital conversion unit, the speed digital signal is input into the CPU, the CPU compares the speed digital signal with the expected digital quantity, and when the deviation exceeds a threshold value, the speed signal acquisition system is defined to be out of order, the anti-skid brake control box is warned by a warning lamp to remind maintenance personnel to check the anti-skid brake control box, meanwhile, a CPU feeds back a detection enabling signal to a speed analog signal generating unit, the speed analog signal generating unit inputs a speed analog signal input value into a switching unit to form a feedback loop, the CPU feeds back a switching enabling signal to an input switching unit to control the input switching unit, and switching of the speed analog signal generating unit and the airplane wheel speed sensor is realized; after detection is finished, the input switching unit disconnects the speed analog signal generating unit from the input switching unit through the switching enabling signal, and meanwhile, the airplane wheel speed sensor is communicated with the input switching unit.
A detection method of an airplane wheel speed acquisition system comprises the following detailed steps:
step 1: when the detection is started, the CPU sets the detection enable signal and the switching enable signal to be at a high level;
step 2: the speed analog signal generating unit generates a speed analog signal, the speed analog signal is output in a default non-speed analog signal mode, and when the speed analog signal generating unit detects that a detection enabling signal sent by a CPU is in a high level mode, the speed analog signal is output to the input end of the input switching unit;
and step 3: the input switching unit is used for switching an input source of the airplane wheel speed acquisition unit, the output end of the airplane wheel speed sensor is connected with the input end of the input switching unit by default, when the input switching unit detects that a switching enabling signal sent by a CPU is high level, the output end of the airplane wheel speed sensor is disconnected from the input end of the input switching unit, and the output end of the speed analog signal generation unit is connected with the input end of the input switching unit;
and 4, step 4: the frequency-voltage conversion unit outputs the speed analog signal to the airplane wheel speed voltage signal, converts the airplane wheel speed voltage signal into an airplane wheel speed digital signal through the analog-digital conversion unit and transmits the airplane wheel speed digital signal to the CPU through a data bus;
and 5: the CPU compares the airplane wheel speed digital signal with a threshold value, and when the deviation meets the requirement, the airplane wheel speed acquisition system is normal;
step 6: after the CPU finishes the detection of the airplane wheel speed acquisition system, setting the detection enabling signal and the switching enabling signal to be at a low level;
and 7: when the speed analog signal generating unit detects that the detection enabling signal sent by the CPU is at a low level, the speed analog signal is stopped to be output;
and 8: when the input switching unit detects that the switching enabling signal sent by the CPU is low level, the output end of the airplane wheel speed sensor is connected with the input end of the input switching unit, the output end of the speed analog signal generating unit is disconnected with the input end of the input switching unit, and the detection of the airplane wheel speed collecting system is completed.
The embodiment takes a certain antiskid brake control box as an example, and the unit related to the detection of the wheel speed acquisition system comprises: the airplane wheel speed control system comprises an airplane wheel speed acquisition unit, a CPU, a speed analog signal generation unit, an input switching unit and an airplane wheel speed sensor. The method comprises the following specific steps:
step 1: when the detection is started, the CPU sets the detection enable signal and the switching enable signal to be at a high level;
step 2: the speed analog signal generating unit generates a speed analog signal, the speed analog signal is output in a default non-speed mode, and when the speed analog signal generating unit detects that a detection enabling signal sent by a CPU is in a high level mode, the speed analog signal with the preset frequency of 3000Hz is output to the input end of the input switching unit;
and step 3: the input switching unit is used for switching an input source of the airplane wheel speed acquisition unit, the output end of the airplane wheel speed sensor is connected with the input end of the input switching unit by default, when the input switching unit detects that a switching enabling signal sent by a CPU is high level, the output end of the airplane wheel speed sensor is disconnected from the input end of the input switching unit, and the output end of the speed analog signal generation unit is connected with the input end of the input switching unit;
and 4, step 4: the frequency-voltage conversion unit outputs a 4.71V wheel speed voltage signal to a speed analog signal with the frequency of 3000Hz, converts the 4.71V wheel speed voltage signal into a 4710 wheel speed digital signal through an A/D conversion circuit (a circuit for converting the analog signal into a digital signal), and transmits the digital signal to the CPU through a data bus;
and 5: the CPU compares the airplane wheel speed digital signal 4710 with an expected value 4700, and when the deviation is not more than +/-50, the airplane wheel speed acquisition system is normal;
step 6: after the CPU finishes the detection of the airplane wheel speed acquisition system, setting the detection enabling signal and the switching enabling signal to be at a low level;
and 7: when the speed analog signal generating unit detects that the detection enabling signal sent by the CPU is at a low level, the speed analog signal is stopped to be output;
and 8: when the input switching unit detects that the switching enabling signal sent by the CPU is low level, the output end of the airplane wheel speed sensor is connected with the input end of the input switching unit, the output end of the speed analog signal generating unit is disconnected with the input end of the input switching unit, and the detection of the airplane wheel speed collecting system is completed.
Claims (2)
1. An aircraft wheel speed acquisition system characterized in that:
the airplane wheel speed acquisition system comprises a speed analog signal generating unit, an input switching unit, a frequency-voltage conversion unit, an analog-digital conversion unit and a CPU, wherein an airplane wheel speed sensor and the speed analog signal generating unit are connected to the input end of the input switching unit, when detection is started, the input switching unit is communicated with the speed analog signal generating unit and is disconnected from the airplane wheel speed sensor and the input switching unit, the input switching unit converts a signal into a speed voltage signal through the frequency-voltage conversion unit, the speed voltage signal is converted into a speed digital signal through the analog-digital conversion unit, the speed digital signal is input to the CPU, the CPU compares the speed digital signal with the expected digital quantity, and when the deviation exceeds a threshold value, the speed signal acquisition system is defined to be out of order, the anti-skid brake control box is warned by a warning lamp to remind maintenance personnel to check the anti-skid brake control box, meanwhile, a CPU feeds back a detection enabling signal to a speed analog signal generating unit, the speed analog signal generating unit inputs a speed analog signal input value into a switching unit to form a feedback loop, the CPU feeds back a switching enabling signal to an input switching unit to control the input switching unit, and switching of the speed analog signal generating unit and the airplane wheel speed sensor is realized; after detection is finished, the input switching unit disconnects the speed analog signal generating unit from the input switching unit through the switching enabling signal, and meanwhile, the airplane wheel speed sensor is communicated with the input switching unit.
2. A method of fault detection using the aircraft wheel speed acquisition system of claim 1, comprising the steps of:
step 1: when the detection is started, the CPU sets the detection enable signal and the switching enable signal to be at a high level;
step 2: the speed analog signal generating unit generates a speed analog signal, the speed analog signal is output in a default non-speed analog signal mode, and when the speed analog signal generating unit detects that a detection enabling signal sent by a CPU is in a high level mode, the speed analog signal is output to the input end of the input switching unit;
and step 3: the input switching unit is used for switching an input source of the airplane wheel speed acquisition unit, the output end of the airplane wheel speed sensor is connected with the input end of the input switching unit by default, when the input switching unit detects that a switching enabling signal sent by a CPU is high level, the output end of the airplane wheel speed sensor is disconnected from the input end of the input switching unit, and the output end of the speed analog signal generation unit is connected with the input end of the input switching unit;
and 4, step 4: the frequency-voltage conversion unit outputs the speed analog signal to the airplane wheel speed voltage signal, converts the airplane wheel speed voltage signal into an airplane wheel speed digital signal through the analog-digital conversion unit and transmits the airplane wheel speed digital signal to the CPU through a data bus;
and 5: the CPU compares the airplane wheel speed digital signal with a threshold value, and when the deviation meets the requirement, the airplane wheel speed acquisition system is normal;
step 6: after the CPU finishes the detection of the airplane wheel speed acquisition system, setting the detection enabling signal and the switching enabling signal to be at a low level;
and 7: when the speed analog signal generating unit detects that the detection enabling signal sent by the CPU is at a low level, the speed analog signal is stopped to be output;
and 8: when the input switching unit detects that the switching enabling signal sent by the CPU is low level, the output end of the airplane wheel speed sensor is connected with the input end of the input switching unit, the output end of the speed analog signal generating unit is disconnected with the input end of the input switching unit, and the detection of the airplane wheel speed collecting system is completed.
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| CN113428123A (en) * | 2021-07-15 | 2021-09-24 | 西安航空制动科技有限公司 | Tire burst prevention airplane brake system and control method thereof |
| CN113460022A (en) * | 2021-08-21 | 2021-10-01 | 西安航空制动科技有限公司 | Fault detection method for airplane wheel braking system |
| CN114419951A (en) * | 2022-02-24 | 2022-04-29 | 中航贵州飞机有限责任公司 | DDS-based airplane wheel speed simulation system |
| CN117104528A (en) * | 2023-10-19 | 2023-11-24 | 四川腾盾科技有限公司 | Front three-point unmanned aerial vehicle flying off-ground positioning device and test flight calculation method thereof |
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