CN215475822U - Quick heating device for airplane deicing vehicle - Google Patents
Quick heating device for airplane deicing vehicle Download PDFInfo
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- CN215475822U CN215475822U CN202121135371.2U CN202121135371U CN215475822U CN 215475822 U CN215475822 U CN 215475822U CN 202121135371 U CN202121135371 U CN 202121135371U CN 215475822 U CN215475822 U CN 215475822U
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Abstract
The utility model discloses a quick heating device for an airplane deicing vehicle, which comprises a heating pipe, a guide pipe and an adjusting pipe, wherein the guide pipe is fixedly arranged at one end of the heating pipe through a first connecting piece, the adjusting pipe is fixedly arranged at the other end of the heating pipe through a second connecting piece, one end of the adjusting pipe is fixedly provided with a water outlet pipe, the circumferential inner wall of the heating pipe is fixedly provided with a first heating pipe and a second heating pipe, a heating plate is fixedly arranged inside the adjusting pipe, and one end, close to the heating pipe, of the circumferential inner wall of the adjusting pipe is fixedly provided with a temperature sensor. According to the utility model, the first heating pipe and the second heating pipe form two heating structures which work independently, so that the temperature in the heating pipes is more uniform, and when one of the first heating pipe and the second heating pipe breaks down, the other heating pipe can work continuously, so that the situation that the airplane cannot be deiced in emergency is prevented, and the heating of the deicing fluid is completed in two sections, namely the heating pipe and the adjusting pipe.
Description
Technical Field
The utility model relates to the technical field of airplane deicing vehicles, in particular to a quick heating device for an airplane deicing vehicle.
Background
With the rapid development of civil aviation industry in China, the annual throughput of each airport is steadily and rapidly increased, and in order to maximize the flight efficiency on the basis of the existing shelf number, the requirements of civil aircrafts on the ground guarantee and resource support service level of the airports are higher and higher. Accordingly, various vehicles for airport ground support work are increasing. The airplane deicing vehicle is important equipment for ensuring safe flight of airplanes in cold regions in airports or airlines in winter on ice and snow days. In case of ice and snow weather or extremely cold weather with high humidity, in order to ensure the normal operation of the flight, the deicing operation of the surface of the airplane is required to be carried out within a certain time before taking off. The main function of the airplane deicing vehicle is to clean frost, snow and ice on the surfaces of the airframe, the large wing, the flap, the empennage, the landing gear and the like of the airplane to be taken off. The deicing fluid heated to the specified temperature is sprayed to the positions where the airplane is iced and accumulated with snow at a certain pressure by using equipment on the airplane deicing vehicle, so that deicing and anti-icing operations are performed, and the airplane keeps good flight lift.
One way to improve the deicing quality and the deicing efficiency of civil aircraft is to increase the number of aircraft deicing equipment and improve the performance of the deicing equipment. The defects of long heating time, low working efficiency and the like of the deicing fluid heating system of the old deicing vehicle become one of the direct reasons for large-area delay of flights at large-scale hub airports in ice and snow weather, so that a quick heating device for the airplane deicing vehicle is needed.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the defects in the prior art, and provides a quick heating device for an airplane deicing vehicle.
In order to achieve the purpose, the utility model adopts the following technical scheme:
the utility model provides an aircraft is rapid heating device for deicing vehicle, includes heating pipe, stand pipe and control tube, the stand pipe is through first connecting piece fixed mounting in the one end of heating pipe, and the control tube passes through second connecting piece fixed mounting in the other end of heating pipe, the one end of control tube is fixed with the outlet pipe, the circumference inner wall fixed mounting of heating pipe has first heating pipe and second heating pipe, the inside fixed mounting of control tube has the hot plate, and the circumference inner wall of control tube is close to the one end of heating pipe and is fixed with the temperature-sensing ware.
Preferably, the first heating pipe and the second heating pipe are equal in size and are symmetrically wound with each other.
Preferably, four symmetrical mounting blocks are fixed on the circumferential inner wall of the adjusting pipe, and the heating plate is fixedly mounted on the mounting blocks.
Preferably, the spiral piece is fixedly installed on the circumferential inner wall of the guide pipe.
Preferably, one end of the guide pipe is fixedly provided with a reducing pipe, one end of the reducing pipe is fixedly provided with a water inlet pipe, and the water inlet pipe is fixedly provided with a water inlet valve.
Preferably, the circumference inner wall of inlet tube is fixed with the filter screen, and the circumference outer wall of guide pipe, heating pipe, regulating pipe, reducing pipe all wraps up has the heat preservation, and the circumference outer wall of heat preservation is fixed with the controller.
Preferably, the water outlet pipe is fixedly provided with a pressure detector.
Compared with the prior art, the utility model provides a quick heating device for an airplane deicing vehicle, which has the following beneficial effects:
1. the first heating pipe and the second heating pipe are electrified to generate heat through the arranged heating pipe, the adjusting pipe, the first heating pipe, the second heating pipe, the temperature sensor and the heating plate, deicing liquid enters the heating pipe and is heated by the first heating pipe and the second heating pipe, the temperature sensor detects the temperature of the heated deicing liquid, if the temperature does not reach the required minimum temperature, the heating plate is electrified to continuously heat the deicing liquid, so that the deicing liquid can reach the standard temperature range of deicing, the first heating pipe and the second heating pipe form two heating structures which work independently, so that the temperature in the heating pipe is more uniform, when one of the first heating pipe and the second heating pipe breaks down, the other heating pipe can continue to work, the airplane can be prevented from being incapable of deicing under emergency, the heating of the deicing liquid is completed in two intervals of the heating pipe and the adjusting pipe, the deicing liquid is heated to be close to an applicable temperature interval, and then the continuous heating of the deicing fluid is facilitated through the adjustment of the heating plate, the heating temperature is prevented from being difficult to accurately control through one-time heating, the temperature of the deicing fluid is greatly changed, and the use is not facilitated.
2. Through the flight that sets up, back in deicing liquid gets into the stand pipe, through the flight formation speed that prolongs the direction of circumference, in deicing liquid forward rotation gets into the heating tube, the indirect speed that flows that has reduced deicing liquid makes deicing liquid can fully heat in the heating tube, and rotatory deicing liquid that gos forward mixes more evenly, does not have the difference of high low temperature, is favorable to deicing liquid's safe handling.
3. Through the pressure detector who sets up, the pressure of the inside of ability real-time supervision device is known the safe work that is favorable to the guarantee device to the pressure situation in the device immediately.
The part not involved in the device is the same as the prior art or can be realized by adopting the prior art, the utility model has simple and compact integral structure, good economic practicability and more stable and uniform heating of the deicing fluid.
Drawings
Fig. 1 is a schematic overall structural diagram of a rapid heating device for an aircraft deicing vehicle according to the present invention;
FIG. 2 is a schematic view of an internal structure of a heating pipe of the rapid heating device for an aircraft deicing vehicle according to the present invention;
fig. 3 is a schematic perspective view of a rapid heating device for an aircraft deicing vehicle according to the present invention;
FIG. 4 is a schematic view of an internal structure of a regulating tube of the rapid heating device for an aircraft deicing vehicle according to the present invention;
FIG. 5 is a schematic view of the inner structure of a guide tube of the rapid heating device for an aircraft deicing vehicle according to the present invention;
fig. 6 is a schematic structural diagram of a second embodiment of a rapid heating device for an aircraft deicing vehicle according to the present invention.
In the figure: 1-water outlet pipe, 2-heat preservation layer, 3-controller, 4-water inlet valve, 5-water inlet pipe, 6-filter screen, 7-first heating pipe, 8-second heating pipe, 9-guide pipe, 10-first connecting piece, 11-heating pipe, 12-second connecting piece, 13-adjusting pipe, 14-spiral sheet, 15-pressure detector, 16-temperature sensor, 17-mounting block, 18-heating plate and 19-reducing pipe.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
In the description of this patent, it is noted that unless otherwise specifically stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can include, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed. The specific meaning of the above terms in this patent may be understood by those of ordinary skill in the art as appropriate.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Example 1
Referring to fig. 1-5, a rapid heating device for an aircraft deicing vehicle comprises a heating pipe 11, a guide pipe 9 and an adjusting pipe 13, wherein the guide pipe 9 is fixedly installed at one end of the heating pipe 11 through a first connecting piece 10, the adjusting pipe 13 is fixedly installed at the other end of the heating pipe 11 through a second connecting piece 12, one end of the adjusting pipe 13 is fixedly provided with a water outlet pipe 1 through a screw, the circumferential inner wall of the heating pipe 11 is fixedly provided with a first heating pipe 7 and a second heating pipe 8, the adjusting pipe 13 is fixedly provided with a heating plate 18 inside, and one end of the circumferential inner wall of the adjusting pipe 13 close to the heating pipe 11 is fixedly provided with a temperature sensor 16 through a screw, the first heating pipe 7 and the second heating pipe 8 are electrically heated, deicing fluid enters the heating pipe 11 and is heated through the first heating pipe 7 and the second heating pipe 8, the temperature sensor 16 detects the temperature of the heated deicing fluid, if the temperature does not reach the required minimum temperature, electrifying the heating plate 18 and continuing to heat the deicing fluid, enabling the deicing fluid to reach the standard temperature range of deicing, forming two heating structures which independently work by the first heating pipe 7 and the second heating pipe 8, enabling the temperature in the heating pipe 11 to be more uniform, and when one of the first heating pipe 7 and the second heating pipe 8 breaks down, enabling the other heating structure to continue to work, preventing the airplane from being incapable of deicing under emergency, dividing the heating of the deicing fluid into two sections of the heating pipe 11 and the adjusting pipe 13 to be completed, firstly heating the deicing fluid to a temperature section close to the applicable temperature, then adjusting through the heating plate 18, being beneficial to continuous heating of the deicing fluid, preventing one-time heating from being difficult to accurately control the heating temperature, enabling the temperature of the deicing fluid to change greatly, and being not beneficial to use.
In the utility model, the first heating pipe 7 and the second heating pipe 8 have the same size and are symmetrically wound with each other.
In the utility model, four mounting blocks 17 which are mutually symmetrical are fixed on the circumferential inner wall of the adjusting pipe 13 through screws, and the heating plate 18 is fixedly mounted on the mounting blocks 17.
According to the utility model, the spiral piece 14 is fixedly arranged on the circumferential inner wall of the guide pipe 9, after entering the guide pipe 9, the deicing fluid passes through the spiral piece 14 to form a speed along the circumferential direction, and the deicing fluid rotates forwards to enter the heating pipe 11, so that the flowing speed of the deicing fluid is indirectly reduced, the deicing fluid can be fully heated in the heating pipe 11, the deicing fluid which rotates forwards is more uniformly mixed, no high-temperature and low-temperature difference exists, and the safe use of the deicing fluid is facilitated.
According to the utility model, one end of the guide pipe 9 is fixedly provided with the reducing pipe 19, one end of the reducing pipe 19 is fixedly provided with the water inlet pipe 5, the water inlet valve 4 is fixedly arranged on the water inlet pipe 5, and the arranged reducing pipe 19 can reduce the flow velocity of the deicing fluid, so that the deicing fluid slowly enters and is heated subsequently, and the heating is more uniform.
According to the utility model, the filter screen 6 is fixed on the circumferential inner wall of the water inlet pipe 5 through screws, the filter screen 6 can filter out larger impurities in deicing fluid to prevent the impurities from blocking the spray head, the heat preservation layer 2 is wrapped on the circumferential outer walls of the guide pipe 9, the heating pipe 11, the adjusting pipe 13 and the reducing pipe 19 to preserve heat of the device and prevent heat leakage and energy waste, and the controller 3 is fixed on the circumferential outer wall of the heat preservation layer 2 through screws.
The working principle is as follows: when the deicing fluid heating device is used, the first heating pipe 7 and the second heating pipe 8 are electrified to generate heat, deicing fluid enters from the water inlet pipe 5, the flow speed is reduced through the reducing pipe 19, the deicing fluid is made to advance in a rotating mode through the guide pipe 9, the deicing fluid enters the heating pipe 11 and is heated through the first heating pipe 7 and the second heating pipe 8, the temperature of the heated deicing fluid is detected by the temperature sensor 16, if the temperature does not reach the required minimum temperature, the heating plate 18 is electrified to continue heating the deicing fluid, the deicing fluid can reach the standard temperature range of deicing, the heating of the deicing fluid is completed in two intervals, namely the heating pipe 11 and the adjusting pipe 13, the deicing fluid is heated to a temperature range close to the applicable temperature range, then the heating plate 18 is adjusted, continuous heating of the deicing fluid is facilitated, the heating temperature is prevented from being controlled accurately by one-time heating, the temperature of the deicing fluid is greatly changed, and the deicing fluid is not beneficial to use.
Example 2
Referring to fig. 6, the present embodiment further includes a pressure detector 15 fixedly mounted on the water outlet pipe 1, compared to embodiment 1.
The working principle is as follows: through the pressure detector 15 who sets up, the pressure of the inside of ability real-time supervision device is known the safe work that is favorable to the guarantee device to the pressure situation in the device immediately.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and equivalent alternatives or modifications according to the technical solution of the present invention and the inventive concept thereof should be covered by the scope of the present invention.
Claims (7)
1. The utility model provides a quick heating device for aircraft deicing vehicle, includes heating pipe (11), stand pipe (9) and control tube (13), stand pipe (9) are through first connecting piece (10) fixed mounting in the one end of heating pipe (11), and control tube (13) are through the other end of second connecting piece (12) fixed mounting in heating pipe (11), the one end of control tube (13) is fixed with outlet pipe (1), its characterized in that, the circumference inner wall fixed mounting of heating pipe (11) has first heating pipe (7) and second heating pipe (8), the inside fixed mounting of control tube (13) has hot plate (18), and the circumference inner wall of control tube (13) is close to the one end of heating pipe (11) and is fixed with temperature-sensing ware (16).
2. A rapid heating device for aircraft de-icing vehicle according to claim 1, characterized in that said first heating pipe (7) and said second heating pipe (8) are of equal size and are wound symmetrically around each other.
3. A rapid heating device for aircraft deicing vehicle according to claim 1, characterized in that four mounting blocks (17) symmetrical to each other are fixed to the circumferential inner wall of the regulating tube (13), and the heating plate (18) is fixedly mounted on the mounting blocks (17).
4. A rapid heating device for aircraft deicing vehicle according to claim 1, characterized in that the circumferential inner wall of the guide tube (9) is fixedly provided with a spiral sheet (14).
5. The rapid heating device for the aircraft deicing vehicle according to claim 1, wherein one end of the guide pipe (9) is fixedly provided with a reducing pipe (19), one end of the reducing pipe (19) is fixedly provided with a water inlet pipe (5), the water inlet pipe (4) is fixedly arranged on the water inlet pipe (5), and the arranged reducing pipe (19) can reduce the flow rate of deicing liquid, so that the deicing liquid slowly enters and is heated subsequently, and the heating is more uniform.
6. The rapid heating device for the aircraft deicing vehicle according to claim 5, characterized in that a filter screen (6) is fixed on the circumferential inner wall of the water inlet pipe (5), the insulating layer (2) is wrapped on the circumferential outer walls of the guide pipe (9), the heating pipe (11), the adjusting pipe (13) and the reducing pipe (19), and a controller (3) is fixed on the circumferential outer wall of the insulating layer (2).
7. A rapid heating device for aircraft deicing vehicle according to claim 1, characterized in that a pressure detector (15) is fixedly mounted on the water outlet pipe (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121135371.2U CN215475822U (en) | 2021-05-26 | 2021-05-26 | Quick heating device for airplane deicing vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121135371.2U CN215475822U (en) | 2021-05-26 | 2021-05-26 | Quick heating device for airplane deicing vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215475822U true CN215475822U (en) | 2022-01-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121135371.2U Active CN215475822U (en) | 2021-05-26 | 2021-05-26 | Quick heating device for airplane deicing vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215475822U (en) |
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2021
- 2021-05-26 CN CN202121135371.2U patent/CN215475822U/en active Active
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