CN104859846A - Safe automatic control device for undercarriage and undercarriage compartment - Google Patents
Safe automatic control device for undercarriage and undercarriage compartment Download PDFInfo
- Publication number
- CN104859846A CN104859846A CN201410065690.9A CN201410065690A CN104859846A CN 104859846 A CN104859846 A CN 104859846A CN 201410065690 A CN201410065690 A CN 201410065690A CN 104859846 A CN104859846 A CN 104859846A
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- China
- Prior art keywords
- pressure air
- dry ice
- high pressure
- undercarriage
- pipe
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Abstract
The invention discloses a safe automatic control device for an undercarriage and an undercarriage compartment. The safe automatic control device comprises an undercarriage and an undercarriage compartment. A dry ice warehouse, a high pressure air chamber and a control case are arranged in the undercarriage compartment. The dry ice warehouse is provided with a dry ice conveyer pipe. The dry ice conveyer pipe is provided with a dry ice solenoid valve for controlling conduction of the dry ice conveyer pipe. The upper part of the undercarriage is provided with a temperature sensor and a humidity sensor. A high pressure air pipe is arranged at the high pressure air chamber. The high pressure air pipe is provided with a high pressure air solenoid valve for controlling conduction of the high pressure air pipe. The temperature sensor, the humidity sensor, the dry ice solenoid valve and the high pressure air solenoid valve are respectively connected to a control box. The device can detect a temperature and humidity of an undercarriage and the interior of an undercarriage compartment. When the temperature is over high, a dry ice conveyer is used for cooling and when the humidity is over high, a high pressure air conveyer blows to remove accumulated water beside the undercarriage. The device has a simple structure, is convenient for reconstruction, is stable and reliable in work and can be widely used in the field of aviation.
Description
Technical field
The present invention relates to a kind of safe auto-control device, particularly relate to a kind of safe auto-control device for undercarriage and landing gear compartment.
Background technology
Undercarriage is exactly that aircraft is parked on ground, slide, for supporting aircraft gravity during takeoff and anding, bear the device of respective loads, it can consume and absorb the Impact energy of aircraft when landing to a certain extent, and there is good brake equipment, landing gear compartment is exactly the place placing and control alighting gear, frictional heating is the modal state of alighting gear, often cause alighting gear even in landing gear compartment temperature sharply raise, on the airport that ponding is more, aircraft tyre skids than being easier to again, this series of problems all may bring threat to aircraft control system, thus great accident may be caused.
Summary of the invention
Object of the present invention is just to provide to solve the problem a kind of safe auto-control device for undercarriage and landing gear compartment that can carry out corresponding actions according to temperature and humidity.
The present invention is achieved through the following technical solutions above-mentioned purpose:
A kind of safe auto-control device for undercarriage and landing gear compartment, comprise landing gear compartment and alighting gear, dry ice supply chamber is provided with in described landing gear compartment, high pressure air room and control box, described dry ice supply chamber is provided with dry ice delivery pipe, one end of described dry ice delivery pipe is communicated with described dry ice supply chamber inside and is fixed on described dry ice supply chamber side, the other end of described dry ice delivery pipe is connected with dry ice shower nozzle, described dry ice delivery pipe is provided with the dry ice electromagnetic valve controlling its conducting, described alighting gear top is provided with temperature sensor and humidity sensor, described high pressure air room is provided with high-pressure air pipe, one end of described high-pressure air pipe is communicated with described high pressure air chamber interior and is fixed on the side of described high pressure air room, the other end of described high-pressure air pipe is connected with high pressure air jet nozzles, described high-pressure air pipe is provided with the high pressure air electromagnetic valve controlling its conducting, the signal output part of described temperature sensor is connected with the temperature signal input of described control box, the signal output part of described humidity sensor is connected with the moisture signal input end of described control box, the dry ice control signal mouth of described control box is connected with the control signal input end of described dry ice electromagnetic valve, and the high pressure air control signal mouth of described control box is connected with the control signal input end of described high pressure air electromagnetic valve.
Owing to adding dry ice supply chamber, dry ice delivery pipe, dry ice shower nozzle, dry ice electromagnetic valve, temperature sensor, humidity sensor, high pressure air room, high-pressure air pipe, high pressure air jet nozzles, high pressure air electromagnetic valve and control box, so when aircraft long-pending have a landing at the airport of more rainwater time, automatically ponding can be blown open, avoid skidding, when causing landing gear compartment and alighting gear temperature excessively to raise suddenly due to factors such as frictions, automatically can be lowered the temperature by dry ice, avoid too high system down or the other accident of causing of Yin Wendu to occur.
In order to enable dry ice be sprayed onto the active components such as described alighting gear, described dry ice shower nozzle and horizontal angle are 30 degree.
In order to enable the easier position of described high-pressure air pipe, its two end portions is stereoplasm tube, and centre portion is soft pipe, and described high-pressure air pipe is close to described alighting gear.
In order to more effectively blow away the ponding of airport ground, described high pressure air jet nozzles and horizontal angle are 60 degree.
Beneficial effect of the present invention is:
The present invention can carry out temperature and humidity detection in undercarriage and landing gear compartment, when temperature is too high, lowered the temperature by dry ice feedway, when humidity is too high, blow the ponding near alighting gear open by high pressure air feedway, structure is simple, and repacking is convenient, working stability is reliable, can be widely used in aviation field.
Accompanying drawing explanation
Fig. 1 is the structural representation of the safe auto-control device for undercarriage and landing gear compartment of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the invention will be further described:
As shown in Figure 1, safe auto-control device for undercarriage and landing gear compartment of the present invention comprises landing gear compartment 1 and alighting gear 9, dry ice supply chamber 2 is provided with in landing gear compartment 1, high pressure air room 11 and control box 13, dry ice supply chamber 2 is provided with dry ice delivery pipe 3, one end of dry ice delivery pipe 3 is communicated with dry ice supply chamber 2 inside and is fixed on dry ice supply chamber 2 side, the other end of dry ice delivery pipe 3 is connected with dry ice shower nozzle 5, dry ice delivery pipe 3 is provided with the dry ice electromagnetic valve 4 controlling its conducting, alighting gear 9 top is provided with temperature sensor 6 and humidity sensor 10, on high pressure air room, 11 are provided with high-pressure air pipe 8, one end of high-pressure air pipe 8 is communicated with inside, high pressure air room 11 and is fixed on the side of high pressure air room 11, the other end of high-pressure air pipe 8 is connected with high pressure air jet nozzles 7, high-pressure air pipe 8 is provided with the high pressure air electromagnetic valve 12 controlling its conducting, the signal output part of temperature sensor 6 is connected with the temperature signal input of control box 13, the signal output part of humidity sensor 10 is connected with the moisture signal input end of control box 13, the dry ice control signal mouth of control box 13 is connected with the control signal input end of dry ice electromagnetic valve 4, the high pressure air control signal mouth of control box 13 is connected with the control signal input end of high pressure air electromagnetic valve 12, in figure, the connection mode of the control signal end of each several part does not mark, dry ice shower nozzle 5 and horizontal angle theta
1be 30 degree, the two end portions of high-pressure air pipe 8 is stereoplasm tube, and centre portion is soft pipe, and high-pressure air pipe 8 is close to alighting gear 9, high pressure air jet nozzles and horizontal angle theta
2it is 60 degree.
As shown in Figure 1, the principle of work of the safe auto-control device for undercarriage and landing gear compartment of the present invention is as follows:
When aircraft landing, landing gear compartment 1 hatch door is opened, if there is more water on airport, then ponding can be taken to the top of alighting gear 9 by wheel, now humidity sensor 10 detects that humidity is larger, control box 13 controls high pressure air electromagnetic valve 12 and opens, high pressure air is blown out from high pressure air jet nozzles 7, blow off the ponding on airport alighting gear 9, when corresponding failure appears in alighting gear 9, temperature is caused to raise suddenly, temperature sensor 6 detects that temperature is higher, control box 13 controls dry ice electromagnetic valve 4 and opens, dry ice sprays from dry ice shower nozzle 5, thus give other position cooling in alighting gear 9 and landing gear compartment 1.
Claims (5)
1. the safe auto-control device for undercarriage and landing gear compartment, comprise landing gear compartment and alighting gear, it is characterized in that: in described landing gear compartment, be provided with dry ice supply chamber, high pressure air room and control box, described dry ice supply chamber is provided with dry ice delivery pipe, one end of described dry ice delivery pipe is communicated with described dry ice supply chamber inside and is fixed on described dry ice supply chamber side, the other end of described dry ice delivery pipe is connected with dry ice shower nozzle, described dry ice delivery pipe is provided with the dry ice electromagnetic valve controlling its conducting, described alighting gear top is provided with temperature sensor and humidity sensor, described high pressure air room is provided with high-pressure air pipe, one end of described high-pressure air pipe is communicated with described high pressure air chamber interior and is fixed on the side of described high pressure air room, the other end of described high-pressure air pipe is connected with high pressure air jet nozzles, described high-pressure air pipe is provided with the high pressure air electromagnetic valve controlling its conducting, the signal output part of described temperature sensor is connected with the temperature signal input of described control box, the signal output part of described humidity sensor is connected with the moisture signal input end of described control box, the dry ice control signal mouth of described control box is connected with the control signal input end of described dry ice electromagnetic valve, and the high pressure air control signal mouth of described control box is connected with the control signal input end of described high pressure air electromagnetic valve.
2. the safe auto-control device for undercarriage and landing gear compartment according to claim 1, is characterized in that: described dry ice shower nozzle and horizontal angle are 30 degree.
3. the safe auto-control device for undercarriage and landing gear compartment according to claim 1, is characterized in that: the two end portions of described high-pressure air pipe is stereoplasm tube, and centre portion is soft pipe.
4. the safe auto-control device for undercarriage and landing gear compartment according to claim 1 or 3, is characterized in that: described high-pressure air pipe is close to described alighting gear.
5. the safe auto-control device for undercarriage and landing gear compartment according to claim 1, is characterized in that: described high pressure air jet nozzles and horizontal angle are 60 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410065690.9A CN104859846A (en) | 2014-02-26 | 2014-02-26 | Safe automatic control device for undercarriage and undercarriage compartment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410065690.9A CN104859846A (en) | 2014-02-26 | 2014-02-26 | Safe automatic control device for undercarriage and undercarriage compartment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104859846A true CN104859846A (en) | 2015-08-26 |
Family
ID=53906125
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410065690.9A Pending CN104859846A (en) | 2014-02-26 | 2014-02-26 | Safe automatic control device for undercarriage and undercarriage compartment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104859846A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2613227A1 (en) * | 2015-11-23 | 2017-05-23 | Fco. Javier Porras Vila | Air wedge for landing gear hatch (Machine-translation by Google Translate, not legally binding) |
| CN106759015A (en) * | 2016-11-22 | 2017-05-31 | 中国航空工业集团公司上海航空测控技术研究所 | A kind of airborne device for removing runway foreign matter |
| CN113183930A (en) * | 2020-01-14 | 2021-07-30 | 北京福田康明斯发动机有限公司 | Cooling method, cooling device and braking system |
| CN115535277A (en) * | 2022-12-06 | 2022-12-30 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft splash protection system |
-
2014
- 2014-02-26 CN CN201410065690.9A patent/CN104859846A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2613227A1 (en) * | 2015-11-23 | 2017-05-23 | Fco. Javier Porras Vila | Air wedge for landing gear hatch (Machine-translation by Google Translate, not legally binding) |
| CN106759015A (en) * | 2016-11-22 | 2017-05-31 | 中国航空工业集团公司上海航空测控技术研究所 | A kind of airborne device for removing runway foreign matter |
| CN113183930A (en) * | 2020-01-14 | 2021-07-30 | 北京福田康明斯发动机有限公司 | Cooling method, cooling device and braking system |
| CN115535277A (en) * | 2022-12-06 | 2022-12-30 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft splash protection system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150826 |
|
| WD01 | Invention patent application deemed withdrawn after publication |