CN205898445U - Aircraft attachs central oil tank fault detection device - Google Patents
Aircraft attachs central oil tank fault detection device Download PDFInfo
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- CN205898445U CN205898445U CN201620915746.XU CN201620915746U CN205898445U CN 205898445 U CN205898445 U CN 205898445U CN 201620915746 U CN201620915746 U CN 201620915746U CN 205898445 U CN205898445 U CN 205898445U
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Abstract
The utility model discloses an aircraft attachs central oil tank fault detection device, including singlechip (1), sampling bleeder circuit (2), sampling control circuit (3) and keying circuit (4) are connected to the input of singlechip (1), LED display circuit (5), liquid crystal display circuit (6) and buzzing cue circuit (7) are connected to the output of singlechip (1), sampling bleeder circuit (2) connects ventilation valve actuator (21), import valve actuator (22) respectively, refuels valve actuator (23) and air shutoff valve actuator (24), sampling control circuit (3) are connection control output voltage (31) and high oily area sensor (32) respectively. The utility model discloses can accomplish the additional central oil tank fault detection work of aircraft to but wide application.
Description
Technical field
The utility model is related to aerospace field, specifically a kind of supplementary aircraft centre tank failure detector.
Background technology
Except there being big wing fuel tank, big wing fuel tank is used for the required fuel oil of storage flight to aircraft, and Air Passenger company have also developed attached
Plus centre tank (additional center tanks, acts), for storing more fuel oils；Additional center fuel tank is installed
In the aft hold of aircraft, additional center fuel tank can increase the Fuel On Board quantity of aircraft, to improve the flight boat of aircraft
Journey, meets airline to flight demand, optimizes aircraft configuration.
Repeatedly additional center fuel tank Transmission system fault in aircraft equipped with additional center fuel tank, leads to flight to be delayed,
Change planes execution flight, control department to arrange international flight aircraft difficult, aircraft occurs and stops the situation fixed a breakdown in field.
At present, additional center fuel tank Transmission system does not have built-in test equipment (built-in test in itself
Equipment, bite), affect fault removal efficiency；After additional center fuel tank breaks down, aircraft rests on ground and can lead
Cause flight delay, aircraft stops field and fixes a breakdown the occupancy flight time, and aircraft can lead to the fuel oil in additional center fuel tank in the air
Cannot use, the fuel oil leading to aircraft no enough flies up to destination, both of these case all can increase the operation cost of airline,
Meanwhile, follow-up aircraft assignment can be caused difficult.
Content of the invention
In view of this, the utility model provides a kind of supplementary aircraft centre tank failure detector, attached to solve aircraft
Plus centre tank fault causes no enough fuel oils to fly up to destination, flight delay and increase asking of airline operation cost
Topic.
The utility model provides a kind of supplementary aircraft centre tank failure detector, including single-chip microcomputer, described single-chip microcomputer
Input connect sampling bleeder circuit, sampling control circuit and key circuit, the output end of described single-chip microcomputer connects led and shows
Circuit, liquid crystal display circuit and buzzing cue circuit；Described sampling bleeder circuit connects ventilation valve actuator respectively, import is lived
Door actuator, oiling valve actuator and air turn off valve actuator；Described sampling control circuit connects control output respectively
Voltage and high oil surface sensor.
Preferably, single-chip microcomputer described in supplementary aircraft centre tank failure detector is stc12c5a60s2.
The utility model has the advantages that
The utility model provides a kind of supplementary aircraft centre tank failure detector, can be to supplementary aircraft centre tank
In ventilation valve actuator, inlet valve actuator, oiling valve actuator, air turn off valve actuator, control output
Voltage and high oil surface sensor make detection in advance, it is to avoid supplementary aircraft centre tank fault causes no enough fuel oils to fly up to mesh
Ground, flight delay and increase airline operation cost problem.
Brief description
By the description to the utility model embodiment below with reference to accompanying drawing, of the present utility model above-mentioned and other mesh
, feature and advantage apparent, in the accompanying drawings:
Fig. 1 is functional-block diagram of the present utility model；
Fig. 2 is the circuit diagram of the utility model embodiment.
Specific embodiment
Below based on embodiment, the utility model is described, but what deserves to be explained is, the utility model does not limit
In these embodiments.Below in detailed description of the present utility model, detailed describe some specific detail sections.So
And, for the part not having detailed description, those skilled in the art can also understand the utility model completely.
Additionally, it should be understood by one skilled in the art that the accompanying drawing being provided is simply to illustrate that of the present utility model
Objects, features and advantages, accompanying drawing is not actual being drawn to scale；In the following description, " circuit " refers at least one
Individual element or electronic circuit are by the galvanic circle being electrically connected or electromagnetism connects and composes.
Meanwhile, unless the context clearly requires otherwise, otherwise " inclusion " in entire disclosure and claims, "comprising" etc.
Similar word should be construed to the implication comprising rather than exclusive or exhaustive implication；That is, be " including but not limited to "
Implication.
Supplementary aircraft centre tank has 2, is act1 and act2 respectively, and supplementary aircraft centre tank detection project includes
The high pasta detection of act1, the ventilation valve actuator voltage of act1, the inlet valve actuator voltage of act1, the oiling of act1
Valve actuator voltage, the air of act1 turn off valve actuator voltage, the high pasta detection of act2, the ventilation valve work of act2
Dynamic device voltage, the inlet valve actuator voltage of act2, the oiling valve actuator voltage of act2, the air of act2 turn off valve
Actuator voltage and control output voltage.
Fig. 1 is functional-block diagram of the present utility model.As shown in figure 1, supplementary aircraft centre tank failure detector bag
Include single-chip microcomputer 1, sampling bleeder circuit 2, sampling control circuit 3, key circuit 4, led display circuit 5, liquid crystal display circuit 6 and
Buzzing cue circuit 7；The input of single-chip microcomputer 1 connects sampling bleeder circuit 2, sampling control circuit 3 and key circuit 4；Monolithic
The output end of machine 1 connects led display circuit 5, liquid crystal display circuit 6 and buzzing cue circuit 7.
Sampling bleeder circuit 2 connects respectively needs the actuator of detection, ventilation valve actuator 21, inlet valve actuator
22nd, oiling valve actuator 23 and air turn off valve actuator 24, and the operating voltage of actuator needing detection is through over-sampling
After bleeder circuit 2, it is connected at the io mouth having been configured to input of single-chip microcomputer 1, as input signal, single-chip microcomputer 1 is to above-mentioned defeated
Enter the numerical value after signal transacting in the range of 25v～31v then it is assumed that the operating voltage of actuator is normal, otherwise it is believed that making
The operating voltage of dynamic device is abnormal, and supplementary aircraft centre tank has fault；Sampling control circuit 3 connects control output voltage respectively
31 and high oil surface sensor 32, control output voltage 31 and high oil surface sensor 32 after sampling control circuit 3, be also connected to
At the io mouth having been configured to input of single-chip microcomputer 1, as input signal, the normal voltage range controlling output voltage 31 is 25v
～31v, otherwise it is believed that controlling output voltage 31 abnormal；Above-mentioned normal condition and abnormality can pass through led display circuit
5 are shown, each detection project, led display circuit 5) green and red two different colors of lamp shown, red colored lamp
Represent abnormal, green light represents normal；Liquid crystal display circuit 6 can show to the title of the detection project being carried out, and leads to
Cross key circuit 4 detection project can be selected, certain detection project independent can be detected it is also possible to whole examine
Survey project is detected together.
Wherein, control the operating voltage that output voltage 31 provides to valve actuator for aircraft power system；High pasta passes
Sensor 32 is arranged on the top in fuel tank, for measuring whether the oil in fuel tank has been filled it up with.
Further, supplementary aircraft centre tank failure detector also includes buzzing cue circuit 7, effective for button
The warning of the high pasta of prompt tone, act1 and act2, when refueling to two fuel tank act1 and act2, high oil surface sensor 32 detects
When in fuel tank, oil level reach a certain height, buzzing cue circuit 7 carries out alarm, prevents oil spill from going out fuel tank.
Fig. 2 is the circuit diagram of the utility model embodiment, and single-chip microcomputer is stc12c5a60s2 chip, and wherein vcc is monolithic
The chip power supply voltage of machine, gnd is ground, and sw-1 is switch, and after sw-1 closure, service voltage power+ is pow voltage, passes through
Pow voltage conversion is vcc by voltage boosting/lowering circuit/chip v-v.
Meanwhile, in fig. 2, the pin 1～3 of stc12c5a60s2 chip, pin 40～44 are as ad sampling io mouth adc1
～adc8, totally 8 groups of ad samplings, by bleeder circuit of sampling (sampling bleeder circuit is made up of c1～c8 and r1～r16), adopt respectively
The oiling valve of inlet valve actuator voltage vin2, act1 of ventilation valve actuator voltage vin1, act1 of collection act1 is made
The ventilation valve actuator voltage vin5 of air shutoff valve actuator voltage vin4, act2 of dynamic device voltage vin3, act1,
The air of oiling valve actuator voltage vin7, act2 of inlet valve actuator voltage vin6, act2 of act2 turns off valve
The described valve actuator of actuator voltage vin8, act1 and act2 uses 28dc direct current, is all believed that between 25v～31v
It is normal condition, otherwise it is assumed that being malfunction；The pin 4 of stc12c5a60s2 chip is chip reset end, is connected to resistance
R19, resistance r19 is connected to ground；The pin 5 of stc12c5a60s2 chip and pin 7 are connected to terminal j2, and terminal j2 is single-chip microcomputer
Download program serial ports；The pin 6 of stc12c5a60s2 chip is hanging；The pin 9 of stc12c5a60s2 chip and pin 10 are respectively
As the input of the high oil surface sensor of detection act1 and act2, high oil surface sensor is arranged on top of oil-tank, gnd1 and
Gnd2 connects the high oil surface sensor of act1 and act2 respectively, fuel tank less than when, turn on over the ground, optocoupler rq1 and/or rq2 turn on,
The voltage that pin 9 and pin 10 detect is vcc, fuel tank completely when, optocoupler rq1 and/or rq2 is not turned on, pin 9 and pin 10
The voltage detecting is 0v；Pin 39 detection controls output voltage, controls output voltage to be that power-supply system carries to valve actuator
For operating voltage, sw-2 is switch, and detection is opened when controlling output voltage, to be judged by the conducting of optocoupler rq3 and cut-off
Control output voltage whether normal, h represents high voltage, and l represents low level, is all regarded as normal condition between 25v～31v,
Otherwise it is assumed that controlling output voltage to be malfunction；Pin 14 and 15 meets crystal oscillator xtal, and pin 16 is connected to gnd；J4 is terminal
Seat, is connected with vin1～vin8, gnd1, gnd2 and ground respectively.
Further, the utility model also has the function of button, display and buzzing prompting, in fig. 2,
The pin 11～13 of stc12c5a60s2 chip is the io mouth driving led, and 18～25 pins pass through current-limiting resistance rp-1 and rp-2
It is connected to the negative electrode of light emitting diode led1～led24, wherein led21～led24 is standby, supplementary aircraft centre tank detection
Each detection project of purpose carries respective green light and red light so that as prompting, test normally gives a green light, and sends out a warning during fault；
Pin 26～28,30～37 is connected respectively on j3, and j3 is LCD MODULE；Pin 5～8 is key-press input io mouth, button
K1-r, k2-l, k3-qr, k4-st represent respectively move to right, move to left, confirming and detection project select, cooperation liquid crystal display use；Draw
Pin 17 connects buzzer beep, has button buzzing prompting and fuel tank carry out buzzing function when full.
Further, the utility model also has low voltage test function, the pin 29 of stc12c5a60s2 chip
The electric power+ of detection supply, carries out partial pressure using resistance rp1 and resistance rp2 partial pressure, when the voltage after partial pressure is less than 1.33v, single
Piece machine will produce interrupt signal, output low-voltage prompting, and supplementary aircraft centre tank failure detector quits work.
Embodiment described above only expresses embodiment of the present utility model, and its description is more concrete and detailed, but simultaneously
Therefore the restriction to the utility model the scope of the claims can not be interpreted as.It should be pointed out that the ordinary skill people to this area
For member, without departing from the concept of the premise utility, some deformation, equal replacement can also be made, improve etc., these
Broadly fall into protection domain of the present utility model.Therefore, the protection domain of the utility model patent should be defined by claims.
Claims (2)
1. a kind of supplementary aircraft centre tank failure detector is it is characterised in that include single-chip microcomputer (1), described single-chip microcomputer (1)
Input connect sampling bleeder circuit (2), sampling control circuit (3) and key circuit (4), the output of described single-chip microcomputer (1)
End connects led display circuit (5), liquid crystal display circuit (6) and buzzing cue circuit (7)；Described sampling bleeder circuit (2) is respectively
Connect ventilation valve actuator (21), inlet valve actuator (22), oiling valve actuator (23) and air and turn off valve work
Dynamic device (24)；Described sampling control circuit (3) connects control output voltage (31) and high oil surface sensor (32) respectively.
2. supplementary aircraft centre tank failure detector according to claim 1 is it is characterised in that described single-chip microcomputer
(1) it is stc12c5a60s2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620915746.XU CN205898445U (en) | 2016-08-22 | 2016-08-22 | Aircraft attachs central oil tank fault detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620915746.XU CN205898445U (en) | 2016-08-22 | 2016-08-22 | Aircraft attachs central oil tank fault detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205898445U true CN205898445U (en) | 2017-01-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620915746.XU Active CN205898445U (en) | 2016-08-22 | 2016-08-22 | Aircraft attachs central oil tank fault detection device |
Country Status (1)
| Country | Link |
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| CN (1) | CN205898445U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11193810B2 (en) | 2020-01-31 | 2021-12-07 | Pratt & Whitney Canada Corp. | Validation of fluid level sensors |
-
2016
- 2016-08-22 CN CN201620915746.XU patent/CN205898445U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11193810B2 (en) | 2020-01-31 | 2021-12-07 | Pratt & Whitney Canada Corp. | Validation of fluid level sensors |
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| GR01 | Patent grant |