CN212074405U - Cooling controller for airplane brake wheel - Google Patents
Cooling controller for airplane brake wheel Download PDFInfo
- Publication number
- CN212074405U CN212074405U CN201921668348.2U CN201921668348U CN212074405U CN 212074405 U CN212074405 U CN 212074405U CN 201921668348 U CN201921668348 U CN 201921668348U CN 212074405 U CN212074405 U CN 212074405U
- Authority
- CN
- China
- Prior art keywords
- airplane
- wheel
- stage
- air
- signal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Regulating Braking Force (AREA)
Abstract
An air/ground state operation module in the cooling controller respectively collects signals of a left undercarriage landing switch and signals of a right undercarriage landing switch, and performs AND operation on the signal states of the left undercarriage landing switch and the right undercarriage landing switch to jointly determine the air/ground state of the airplane. And the air/ground state operation module is communicated with an input interface of the working end of the delay relay so as to output the determined air/ground state of the airplane to the delay relay. The cooling controller is used for integrating the high/low speed state of the airplane and the air/ground state judgment of the airplane, when the cooling condition is met, the airplane brake wheel cooling controller outputs a wheel cooling system starting signal to cool the brake wheels, the timeliness of cooling the brake wheels is guaranteed, and the labor intensity of ground personnel is reduced. The invention reduces the station passing time of the airplane from 60min to 30min, thereby realizing the rapid takeoff of the airplane.
Description
Technical Field
The invention relates to the field of control of cooling systems for airplane brake wheels, in particular to a cooling controller for the airplane brake wheels.
Background
The airplane of a certain model mostly adopts metal-based powder alloy brake materials, and the airplane can be ensured to move out quickly by adopting a ground forced water cooling or air cooling method.
Modern aircraft have landing weight big, braking energy is big, characteristics such as brake speed height. The C/C composite brake material has the advantages of good friction characteristic, strong heat absorption capacity, small density, long service life and the like, and is widely used. However, the C/C composite brake material has poor oxidation resistance, the brake device cannot be cooled by water, and the C/C composite brake device must be forcibly cooled to ensure that the airplane runs at a high speed, so that the brake cooling control system becomes a necessary airborne device of the brake airplane wheel.
Through retrieval, the existing antiskid brake control box of the airplane collects a left brake airplane wheel speed signal, a right brake airplane wheel speed signal, a left undercarriage landing switch signal and a right undercarriage landing switch signal of the airplane, integrates the four signals and jointly determines the air/ground state of the airplane.
The invention with application number 201811242704.4 creates an airborne brake air cooling system with an automatic control function and a control method thereof. The invention determines the air/ground state of the airplane through a left undercarriage landing switch and a right undercarriage landing switch; acquiring a speed signal output by an airplane wheel speed sensor through an airplane antiskid brake control box, and determining the high/low speed state of the airplane; the automatic control logic of the airborne brake air cooling system is determined according to the high/low speed state and the air/ground state of the airplane, the automatic control of the total working time of the airborne brake air cooling system is realized by using a delay relay, the brake wheels can be timely and reliably cooled after the airplane lands, the take-off and landing period of the airplane can be shortened from 60min to 90min to 30min, the take-off and landing time of the airplane is shortened, and the take-off and landing frequency of the airplane is improved. Meanwhile, the energy is saved, and the labor intensity of ground staff is reduced. However, the aircraft antiskid brake control box and the delay relay in the invention are two separated devices, so that the system has more accessories and low integration level; meanwhile, the landing switch of the left undercarriage and the landing switch of the right undercarriage are connected in series, and the reliability of the system is reduced by the connection mode; the invention is only explained for converting the wheel speed signal into the high/low speed state signal, but the invention does not explain the collection mode of the wheel speed signal and how to convert the speed signal into the wheel high/low speed state signal.
The invention with application number 201811309693.7 creates a cooling system for the main wheel brake of a multi-train airplane. The invention comprises a plurality of brake cooling assemblies and a temperature monitoring control box. The temperature sensors in the brake cooling assemblies are respectively inserted into the temperature sensor mounting holes in the brake shell, the signal input ends of the temperature sensors are connected into the temperature sockets of the temperature monitoring control box, and the power input ends of the brake cooling motors are communicated with the motor sockets of the temperature detection unit. The output bus of the temperature monitoring control box is communicated with an instrument panel of the aircraft cockpit; and an airplane power supply is used as a power supply of the temperature monitoring control box. And two ends of the cooling switch are respectively connected with the input end of the temperature monitoring control box and the airplane power supply. The invention can cool and lower the temperature in advance in the sliding process of the airplane, improves the running frequency of the airplane, reduces the aging speed of the brake device and the components thereof, prolongs the whole service life of the brake device and improves the economic index. The input end of the temperature monitoring control box mentioned in the invention is connected with one terminal of the cooling switch; the other terminal of the cooling switch is connected with an airplane power supply; and the power supply to each brake cooling motor is controlled by a relay. The air/ground state signal of the landing gear of the airplane is communicated with the air/ground state signal input end of the temperature monitoring control box through a data line; the signal of the 'cooling switch' of the aircraft cockpit is communicated with the signal input end of the 'cooling switch' of the temperature monitoring control box through a data line; however, the invention only explains that the starting is carried out when the 'air/ground' state of the landing gear of the airplane is the ground, and if the braking wheels of the airplane are cooled in a high-speed rotating state, certain potential safety hazards exist. Meanwhile, it is not described how "air/ground" is determined, and it is not described in what condition the cooling signal outputted from the temperature monitoring control box is stopped. If the cooling is excessive, energy waste can be caused, incomplete cooling can be caused, and the attendance cycle of the airplane is influenced.
Disclosure of Invention
In order to overcome the defects of multiple system accessories and low integration level and reliability in the prior art, the invention provides an aircraft brake wheel cooling controller.
The cooling controller of the airplane brake wheel comprises a square wave stage, a speed stage, an air/ground state operation module, a left wheel high/low speed threshold circuit, a right wheel high/low speed threshold circuit and a time delay relay. The square wave stage is divided into a left airplane wheel square wave stage and a right airplane wheel square wave stage; the speed stages are divided into a left wheel speed stage and a right wheel speed stage. Wherein:
the signal input end of the left wheel square wave stage is communicated with a left brake wheel speed signal acquisition interface of a left brake wheel speed sensor; the signal output end of the left wheel square wave stage is communicated with the input end of the left wheel speed stage. The output end of the left airplane wheel speed stage is communicated with the input end of the left airplane wheel high/low speed threshold circuit, and a left airplane wheel speed acquisition and processing channel is formed.
The signal input end of the right wheel square wave stage is communicated with a right brake wheel speed signal acquisition interface of a right brake wheel speed sensor; the signal output end of the right wheel square wave stage is communicated with the input end of the right wheel speed stage. The output end of the right airplane wheel speed stage is communicated with the input end of the right airplane wheel high/low speed threshold circuit, and a right airplane wheel speed acquisition and processing channel is formed.
The output end of the left airplane wheel high/low speed threshold circuit and the output end of the right airplane wheel high/low speed threshold circuit are respectively communicated with the input end of the time delay electric appliance.
And the air/ground state operation module is used for respectively acquiring a signal of a landing switch of the left undercarriage and a signal of a landing switch of the right undercarriage, and operating the signal states of the landing switch of the left undercarriage and the landing switch of the right undercarriage to jointly determine the air/ground state of the airplane. And the air/ground state operation module is communicated with an input interface of the working end of the delay relay so as to output the determined air/ground state of the airplane to the delay relay.
The left airplane wheel high/low speed threshold circuit and the right airplane wheel high/low speed threshold circuit both adopt comparison circuits with hysteresis characteristics.
In the invention, a signal input end of a right wheel square wave level is communicated with a speed sensor of a right brake wheel; the signal output end of the right wheel square wave stage is communicated with the input end of the right wheel speed stage. The output end of the right airplane wheel speed stage is communicated with the input end of the right airplane wheel high/low speed threshold circuit, and a right airplane wheel speed acquisition and processing channel is formed. The left airplane wheel speed collecting and processing channel is completely the same as the right airplane wheel speed collecting and processing channel. The output end of the left airplane wheel high/low speed threshold circuit and the output end of the right airplane wheel high/low speed threshold circuit are respectively communicated with the input end of the time delay electric appliance. A right brake wheel speed signal input by a right brake wheel speed sensor is acquired through a signal input end of a right wheel square wave level, and a high-speed threshold V of the right brake wheel of the airplane is set in a cooling controller for the brake wheel of the airplaneSD right 1Low speed threshold V for right brake wheel of airplaneSD right 2. Thereby determining a right wheel speed status signal; a left brake wheel speed signal input by a left brake wheel speed sensor is acquired through a signal input end of a left wheel square wave level, and a high-speed threshold V of the left brake wheel of the airplane is set in a cooling controller for the brake wheel of the airplaneSD left 1Low speed threshold V for left brake wheel of airplaneSD left 2. Thereby determining a left wheel speed status signal; the cooling controller for the aircraft braking wheels logically operates the left wheel speed signal and the right wheel speed signal to determine the high/low speed state of the aircraft.
And an air/ground state operation module in the cooling controller for the aircraft brake wheels respectively collects signals of the landing switch of the left landing gear and signals of the landing switch of the right landing gear, and performs AND operation on the signal states of the landing switch of the left landing gear and the landing switch of the right landing gear to jointly determine the air/ground state of the aircraft. And the air/ground state operation module is communicated with the input interface of the working end of the delay relay so as to output the determined air/ground state of the airplane to the delay relay. The cooling controller for the aircraft brake wheel integrates the high/low speed state of the aircraft and the air/ground state of the aircraft, so that the cooling system starting signal of the cooling controller for the aircraft brake wheel of the aircraft is determined, when the cooling condition is met, the cooling controller for the aircraft brake wheel outputs the wheel cooling system starting signal to cool the brake wheel, the timeliness of cooling of the brake wheel is guaranteed, and the labor intensity of ground service personnel is reduced. The invention reduces the station passing time of the airplane from 60min to 30min, thereby solving the problem of quick takeoff of the airplane.
Drawings
Fig. 1 is a schematic view of a prior art structure.
Fig. 2 is a schematic structural diagram of the present invention.
Detailed Description
The cooling controller for the brake wheel of the airplane comprises a square wave stage, a speed stage, an air/ground state operation module, a left wheel high/low speed threshold circuit, a right wheel high/low speed threshold circuit and a time delay relay. The square wave stage is divided into a left airplane wheel square wave stage and a right airplane wheel square wave stage; the speed stages are divided into a left wheel speed stage and a right wheel speed stage. Wherein:
the signal input end of the left wheel square wave stage is communicated with a left brake wheel speed signal acquisition interface of a left brake wheel speed sensor; the signal output end of the left wheel square wave stage is communicated with the input end of the left wheel speed stage. The output end of the left airplane wheel speed stage is communicated with the input end of the left airplane wheel high/low speed threshold circuit, and a left airplane wheel speed acquisition and processing channel is formed.
The signal input end of the right wheel square wave stage is communicated with a right brake wheel speed signal acquisition interface of a right brake wheel speed sensor; the signal output end of the right wheel square wave stage is communicated with the input end of the right wheel speed stage. The output end of the right airplane wheel speed stage is communicated with the input end of the right airplane wheel high/low speed threshold circuit, and a right airplane wheel speed acquisition and processing channel is formed.
The left airplane wheel speed collecting and processing channel is completely the same as the right airplane wheel speed collecting and processing channel.
And the output end of the left airplane wheel high/low speed threshold circuit and the output end of the right airplane wheel high/low speed threshold circuit are respectively communicated with the input end of the time delay relay.
And the air/ground state operation module is used for respectively acquiring a signal of a landing switch of the left undercarriage and a signal of a landing switch of the right undercarriage, and performing AND operation on the signal states of the landing switch of the left undercarriage and the landing switch of the right undercarriage to jointly determine the air/ground state of the airplane. And the air/ground state operation module is communicated with an input interface of the working end of the delay relay so as to output the determined air/ground state of the airplane to the delay relay.
The air/ground state operation module adopts the prior art to operate a left undercarriage landing switch signal and a right undercarriage landing switch signal, and when the left undercarriage landing switch and the right undercarriage landing switch are both in a ground state, the aircraft is in the ground state; when the landing switch of the left undercarriage and the landing switch of the right undercarriage are both in an air state, the airplane is in the air state; when the landing switch of the left landing gear or the landing switch of the right landing gear is in an air state, the airplane is in the air state.
The time delay relay adopts a sealed hybrid time delay relay, and belongs to the prior art. The performance parameters of the delay relay are shown in a table 1:
TABLE 1 Performance parameters of certain type of sealed hybrid time-delay relay
Note: the 2Z set forth in table 1 is two sets of transitions.
The left airplane wheel high/low speed threshold circuit and the right airplane wheel high/low speed threshold circuit both adopt comparison circuits with hysteresis characteristics.
Both the square wave stage and the velocity stage employ the prior art.
In the embodiment, the output point of the high/low speed state signal of the right airplane wheel and the output point of the high/low speed state signal of the airplane of the left airplane wheel are communicated with the input end of the control contact of the delay relay, and the output end of the air/ground state signal of the airplane is communicated with the input interface of the working end of the delay relay. And integrating the determined high/low speed state of the airplane, the air/ground state of the airplane and the delay relay signal, and outputting a cooling control signal through an output interface of a working end of the delay relay to realize the control of cooling the brake wheel of the airplane.
Claims (2)
1. The cooling controller for the airplane brake wheel is characterized by comprising a square wave stage, a speed stage, an air/ground state operation module, a left airplane wheel high/low speed threshold circuit, a right airplane wheel high/low speed threshold circuit and a time delay relay; the square wave stage is divided into a left airplane wheel square wave stage and a right airplane wheel square wave stage; the speed stages are divided into a left airplane wheel speed stage and a right airplane wheel speed stage; wherein:
the signal input end of the left wheel square wave stage is communicated with a left brake wheel speed signal acquisition interface of a left brake wheel speed sensor; the signal output end of the left airplane wheel square wave stage is communicated with the input end of the left airplane wheel speed stage; the output end of the left airplane wheel speed stage is communicated with the input end of the left airplane wheel high/low speed threshold circuit, so that a left airplane wheel speed acquisition and processing channel is formed;
the signal input end of the right wheel square wave stage is communicated with a right brake wheel speed signal acquisition interface of a right brake wheel speed sensor; the signal output end of the right airplane wheel square wave stage is communicated with the input end of the right airplane wheel speed stage; the output end of the right airplane wheel speed stage is communicated with the input end of the right airplane wheel high/low speed threshold circuit to form a right airplane wheel speed acquisition and processing channel;
the output end of the left airplane wheel high/low speed threshold circuit and the output end of the right airplane wheel high/low speed threshold circuit are respectively communicated with the input end of the time delay relay;
the air/ground state operation module is used for respectively acquiring a signal of a landing switch of a left undercarriage and a signal of a landing switch of a right undercarriage, and operating the signal states of the landing switch of the left undercarriage and the landing switch of the right undercarriage to jointly determine the air/ground state of the airplane; and the air/ground state operation module is communicated with an input interface of the working end of the delay relay so as to output the determined air/ground state of the airplane to the delay relay.
2. An aircraft brake wheel cooling controller as claimed in claim 1 wherein said left wheel high/low speed threshold circuit and said right wheel high/low speed threshold circuit each employ a comparison circuit having hysteresis characteristics.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921668348.2U CN212074405U (en) | 2019-10-08 | 2019-10-08 | Cooling controller for airplane brake wheel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921668348.2U CN212074405U (en) | 2019-10-08 | 2019-10-08 | Cooling controller for airplane brake wheel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212074405U true CN212074405U (en) | 2020-12-04 |
Family
ID=73556903
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921668348.2U Active CN212074405U (en) | 2019-10-08 | 2019-10-08 | Cooling controller for airplane brake wheel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212074405U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114180037A (en) * | 2021-11-30 | 2022-03-15 | 长沙五七一二飞机工业有限责任公司 | Cooling device for airplane brake wheel |
| US11940027B2 (en) | 2020-12-10 | 2024-03-26 | Airbus Operations Limited | Aircraft brake temperature control system |
-
2019
- 2019-10-08 CN CN201921668348.2U patent/CN212074405U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11940027B2 (en) | 2020-12-10 | 2024-03-26 | Airbus Operations Limited | Aircraft brake temperature control system |
| CN114180037A (en) * | 2021-11-30 | 2022-03-15 | 长沙五七一二飞机工业有限责任公司 | Cooling device for airplane brake wheel |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN212074405U (en) | Cooling controller for airplane brake wheel | |
| CN109305147B (en) | Airborne brake air cooling system with automatic control function and control method thereof | |
| CN110562443B (en) | Cooling controller and control method for airplane brake wheel | |
| CN109305148B (en) | Temperature-based aircraft brake air-cooling control system and design method thereof | |
| CN109307025B (en) | Main engine wheel braking and cooling system of multi-wheel system aircraft | |
| CN112483318B (en) | Fan control system with prevent and remove deicing function | |
| CN205450766U (en) | Vehicle control unit integrating battery management and vehicle body control functions | |
| CN104228589A (en) | High-level safety device of pure electric vehicle based on double CPUs | |
| CN210761277U (en) | Temperature controller for airplane brake wheel | |
| CN105620455A (en) | Aircraft brake system and ground protection control method thereof | |
| CN107351823A (en) | A kind of more train brake system and its control method | |
| CN105711423A (en) | High-voltage safety control system of electric vehicle | |
| CN113022514B (en) | Airplane wheel brake cooling control system and control method | |
| CN209258098U (en) | A kind of aircraft airborne brake air cooler control system | |
| CN209112157U (en) | Airborne brake air cooling system with automatic control function | |
| CN208656679U (en) | An in-wheel motor integrated drive control device | |
| CN118299219A (en) | High-voltage switch anti-jump relay and monitoring system thereof | |
| CN214451018U (en) | Rail transit vehicle door data acquisition device | |
| CN109557339A (en) | A kind of three axis accelerometer and impact search switch | |
| CN204355078U (en) | A kind of track traffic signal control convenience | |
| CN211149447U (en) | Multichannel data processing FPGA application module | |
| CN210109596U (en) | Airborne power monitoring circuit of unmanned helicopter | |
| CN202362978U (en) | Intelligent control system for stake examination of drivers | |
| CN114326866B (en) | Heating control method of airborne atmospheric data sensor | |
| CN106873427A (en) | A kind of new stopping implement control system based on CAN |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |