CN212921989U - Deicing device for aircraft - Google Patents
Deicing device for aircraft Download PDFInfo
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- CN212921989U CN212921989U CN202021029831.9U CN202021029831U CN212921989U CN 212921989 U CN212921989 U CN 212921989U CN 202021029831 U CN202021029831 U CN 202021029831U CN 212921989 U CN212921989 U CN 212921989U
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Abstract
The utility model provides a deicing device for an aircraft, which is characterized by comprising a detector and a heater, wherein the detector is arranged on the outer surface of an aircraft wing skin and is used for detecting whether the outer surface of the aircraft wing skin is frozen; the heater is located the detector with between the aircraft wing covering, with the detector electricity is connected, the heater includes the zone of heating, the heater is used for detaching ice layer on the aircraft wing covering, has realized carrying out the purpose of fixed point heating to the position that needs the deicing, has avoided the unified heating method in the traditional technique, the very big degree reduction the consumption of aircraft.
Description
Technical Field
The utility model belongs to aircraft deicing field, concretely relates to defroster for aircraft.
Background
When the aircraft is subjected to artificial rainfall operation, the artificial rainfall operation is usually carried out under complex meteorological conditions, correspondingly, the surface of the aircraft is easy to freeze under high humidity or low temperature conditions, the weight of the aircraft body is increased after the aircraft is frozen, the center of gravity of the aircraft body is unstable, unpredictable influence is generated on the flight, action and performance of the aircraft, and even flight accidents are caused; at the same time, the aerodynamic profile of the aircraft is destroyed, increasing the drag and reducing the lift, leading to harmful vibrations.
The existing aircraft mostly adopts a series of deicing methods such as a hot air deicing system to uniformly deice the ice layer on the aircraft, because the aircraft flies and operates under the working condition, the position of icing on the fuselage can be different, the uniform deicing method in the prior art is adopted, a larger large electric system is needed to provide the power required by deicing, for a small aircraft, the effective load is low, the power is small, when a power supply system is additionally added, the weight of the small aircraft is increased, the gravity center of the fuselage can be unstable, and the normal working condition of the small aircraft is influenced.
Disclosure of Invention
Not enough to prior art exists, the utility model aims to provide a defroster for aircraft solves prior art power consumption too big, needs additionally to increase power generation system's problem.
In order to solve the technical problem, the utility model discloses a following technical scheme realizes: a de-icing apparatus for an aircraft, comprising: the detector is arranged on the outer surface of the aircraft wing skin and is used for detecting whether the outer surface of the aircraft wing skin is frozen; the heater is located between the detector and the aircraft wing skin, with the detector electricity is connected, the heater includes the zone of heating, the heater is used for detaching the ice sheet on the aircraft wing skin.
The heater is still including locating respectively the interior heat insulation layer and the outer insulation layer of zone of heating both sides, interior heat insulation layer is located the one side that is close to aircraft wing covering, one side that is close to the detector is located to the outer insulation layer.
The heater still includes the abrasionproof decreases the protective layer, the abrasionproof decreases the protective layer parcel interior heat insulation layer, zone of heating and outer insulating layer.
The heating layer is a metal heating layer.
The heater further comprises an overheating protection layer arranged between the aircraft wing skin and the inner insulation layer.
The deicing device comprises a plurality of pairs of detectors and heaters, the plurality of pairs of detectors and the plurality of pairs of heaters are arranged on the outer surface of the aircraft wing skin at intervals, and the plurality of pairs of detectors and the plurality of pairs of heaters are connected in parallel.
The deicing device further comprises a camera, and the camera is arranged on the outer surface of the aircraft wing skin and close to the aircraft fuselage.
Compared with the prior art, the utility model, following technological effect has:
(I) the utility model discloses a defroster is through setting up the heater on the surface of aircraft wing covering and set up the detector on the heater, the heater includes the zone of heating, the zone of heating is connected with the detector electricity, the detector can obtain the signal of the freezing signal of aircraft surface, and transmit this signal of telecommunication for the zone of heating, the zone of heating can begin to work and carry out the deicing to its place region according to this signal of telecommunication, the fixed point deicing to the aircraft has been realized through zone of heating production of heat, the unified heating method in the traditional technique has been avoided, the reduction of very big degree the consumption of aircraft.
(II) the utility model discloses a defroster is through setting up overheated protective layer, and the temperature that can effectual control aircraft wing covering prevents the damage of high temperature to aircraft wing covering.
(III) the utility model discloses a defroster through set up the camera on the aircraft wing is close to the position of fuselage, and the camera can shoot the freezing position and the deicing effect of aircraft for the staff carries out real-time supervision to the deicing effect, and the staff can be according to the timely unusual heater of discovery deicing of the image information who shoots, and maintains or changes this heater, guarantees the normal clear of deicing work.
(IV) the utility model discloses an aircraft can be through defroster fixed point deicing on the one hand through defroster, reduces the aircraft and freezes the reduction of back aerodynamic characteristic to avoided the complete machine to lead to the focus unstability because of freezing weight increases, this defroster consumption of on the other hand is less relatively, weight and the consumption that can effectual reduction aircraft.
Drawings
Fig. 1 is a schematic view of the overall structure of the deicing device of the present invention;
fig. 2 is a schematic view of the overall structure of the deicing device of the present invention installed on an aircraft.
The meaning of the individual reference symbols in the figures is:
1-detector, 2-aircraft wing skin, 3-heater, 4-ice layer, 5-camera, 6-aircraft fuselage;
301-a heating layer, 302-an inner insulating layer, 303-an outer insulating layer, 304-an anti-wear protection layer, 305-an overheating protection layer.
The following examples are provided to explain the present invention in further detail.
Detailed Description
The following embodiments of the present invention are given, and it should be noted that the present invention is not limited to the following embodiments, and all the equivalent transformations made on the basis of the technical solution of the present application all fall into the protection scope of the present invention.
Example (b):
the embodiment provides a deicing device for an aircraft, which is shown in fig. 1-2 and comprises a detector 1 and a heater 3, wherein the detector 1 is arranged on the outer surface of an aircraft wing skin 2, and the detector 1 is used for detecting whether the outer surface of the aircraft wing skin 2 is frozen; the heater 3 is arranged between the detector 1 and the aircraft wing skin 2 and is electrically connected with the detector 1, the heater 3 comprises a heating layer 301, and the heater 3 is used for removing an ice layer 4 on the aircraft wing skin 2.
When the aircraft is in high altitude, the surface of the aircraft can be frozen under any condition of high humidity or low temperature, and the ice layer can cause the aircraft to be incapable of normal operation and even have potential safety hazard; the utility model discloses a device, through set up the heater on the surface at aircraft wing covering and set up the detector on the heater, the heater includes the zone of heating, zone of heating is connected with the detector electricity, the detector can obtain the freezing signal of telecommunication on aircraft surface, and give the zone of heating with this signal of telecommunication transmission, the zone of heating can be based on this signal of telecommunication beginning to work and carry out the deicing to its place region, the fixed point deicing to the aircraft has been realized to the heat production through the zone of heating, the unified heating method on the traditional technique has been avoided, the reduction of very big degree the consumption of aircraft.
The detector and the heater are responsible for deicing of a position area where the detector and the heater are located, the detector is a model 9732steel, the detector is an optical sensor consisting of a combined spectrometer and an optical switch, non-collimated light is used for monitoring the opacity and the optical refractive index of a substance on a probe, the change of the opacity and the refractive index is recorded as icing, the working principle of the detector is that signals of the change of the opacity and the refractive index are converted into four electrical signals capable of being directly detected through three signal lines with different colors, the output voltage of the detector is greater than 3V and is displayed as 1, and the output voltage of the detector is less than 0.5V and is displayed as 0. The detector outputs an electrical signal of 000 representing no icing state, 100 representing a small icing state, 110 representing a large icing state, and 111 representing an icing saturation state, and when the detector outputs electrical signals of 100, 110, and 111, the detector outputs an icing electrical signal. The heater is arranged on the outer surface of the aircraft wing skin, the detector is arranged on the heater, the heater comprises a heating layer, the heating layer is a conductive metal film, and the conductive metal film is electrically connected with the detector. The aircraft is provided with a power supply system, and the detector and the heater are respectively connected with the power supply system in parallel; when the skin of the aircraft is frozen, the detector can send an icing electric signal, at the moment, the heater receives the icing electric signal and then the power supply system provides electric energy for the heater, the heating layer starts to work after being electrified to generate heat to deice the area where the heating layer is located, and fixed-point deicing of the aircraft is realized.
The aircraft can seriously influence the normal operation of aircraft after ice sheet thickness exceedes 1mm at the flight in-process, when no more than 1mm, the influence to the aircraft production can be ignored, when the electricity signal of detector output is 110 and 111, it is greater than 1mm to show ice sheet thickness, consequently the detector in this embodiment sends the signal of icing electricity to the heater after ice sheet exceedes 1mm, power supply system provides the electric energy for the heater after the heater receives this signal of icing electricity, the zone of heating begins work after the circular telegram and produces the heat and carries out the deicing to its place region.
As a preferable solution of this embodiment, the heater 3 further includes an inner insulating layer 302 and an outer insulating layer 303 respectively disposed on two sides of the heating layer 301, the inner insulating layer 302 is disposed on a side close to the aircraft wing skin 2, and the outer insulating layer 303 is disposed on a side close to the detector 1. Wherein the inner insulation layer 302 is to prevent heat generated by the heating layer from diffusing into the interior of the aircraft wing skin 2; outer insulating layer 303 is to prevent heating layer 301 from conducting electricity.
As a preferable solution of this embodiment, the heater 3 further includes an anti-wear protection layer 304, and the anti-wear protection layer 304 wraps the inner insulation layer 302, the heating layer 301 and the outer insulation layer 303.
The anti-abrasion protective layer 304 can effectively protect the inner insulating layer 302, the heating layer 301 and the outer insulating layer 303 from being damaged by external factors such as air flow and the like in high altitude, and the service life can be prolonged.
As a preferable solution of this embodiment, the heating layer 301 is a metal heating layer.
Wherein, the metal heating layer comprises the electric heat piece of mutual insulation, the operating voltage of heater 3 is 24V, power is 24w, the heating highest temperature is 50 ℃, the metal heating layer is used for producing heat, when the temperature of zone of heating reaches 60 ℃, the heat of production transmits aircraft wing covering 2 through interior heat insulation layer 302, transmit to ice sheet 4 through outer insulation layer 303 and abrasionproof protection layer 304, the material of abrasionproof protection layer 304 is glass fiber, the material of outer insulation layer 303 is insulating heat conduction silica gel, the material of interior heat insulation layer 302 is the resistant high temperature cloth of teflon, the material that this embodiment selected can not only play thermal-insulated and abrasionproof and decrease effect, because of self weight is low, can also reduce the load of aircraft.
As a preferable solution of this embodiment, the heater further includes an overheating protection layer 305, and the overheating protection layer 5 is disposed between the aircraft wing skin 2 and the inner insulation layer 3, and is used for preventing the damage to the aircraft wing skin due to the over-temperature of the heater.
The working principle of the overheating protection layer 5 is as follows: the overheating protection layer comprises a temperature sensor and a heating switch, the heating switch is electrically connected with the heater, when the temperature sensor senses that the temperature of the surface of the aircraft wing skin is higher than 50 ℃, the heating switch is closed, and the metal heating layer stops working.
As a preferable scheme of this embodiment, the deicing device includes a plurality of pairs of detectors 1 and heaters 3, the plurality of pairs of detectors 1 and heaters 3 are arranged on the outer surface of the aircraft wing skin 2 at intervals, and the plurality of pairs of detectors 1 and heaters 3 are connected in parallel.
The icing conditions of the aircraft wing skin 2 at different positions are different due to differences of the operating environments of the aircraft wing skin at different positions when the aircraft operates in high altitude, fixed-point deicing on the aircraft wing skin 2 is realized by arranging a plurality of pairs of detectors 1 and heaters 3, mutual influence is avoided, and the power consumption of the aircraft is effectively reduced.
As a preferable scheme of this embodiment, the deicing device further includes a camera 5, and the camera 5 is disposed on the outer surface of the aircraft wing skin 2 near the aircraft fuselage 6.
The camera can shoot the icing position and the deicing effect of the aircraft, so that a worker can monitor the deicing effect in real time, the worker can find the heater with abnormal deicing according to shot image information in time, the heater can be maintained or replaced, and normal operation of deicing operation is guaranteed.
The deicing principle of the deicing device of the embodiment is as follows:
when the aircraft freezes at the high altitude construction surface, the utility model provides a pair of a defroster for aircraft, through at aircraft wing covering surface detector, the detector is through the signal conversion different electricity signals with the opacity of ice sheet and refractive index change, and then can draw the icing state on aircraft surface, and transmit this electric signal to the heater, the heater can carry out the deicing according to this electric signal to the region in place, produce the heat through the work of zone of heating, and transmit the heat to the ice sheet through outer insulation layer and abrasionproof damage protective layer, and then melt the ice sheet; in the process of deicing operation, the camera arranged on the outer surface of the aircraft wing skin can shoot the thickness of an icing area and an ice layer on the aircraft body, so that the deicing effect is effectively monitored; and when the temperature sensor senses that the temperature of the surface of the aircraft wing skin is higher than 50 ℃, the heating switch is closed, the heating layer stops working, and the deicing work is finished.
Claims (7)
1. De-icing device for an aircraft, characterized in that it comprises:
the detector (1) is arranged on the outer surface of the aircraft wing skin (2), and the detector (1) is used for detecting whether the outer surface of the aircraft wing skin (2) is frozen;
a heater (3) provided between the detector (1) and the aircraft wing skin (2), electrically connected with the detector (1), the heater (3) comprising a heating layer (301), the heater (3) being for removing an ice layer (4) on the aircraft wing skin (2).
2. Deicing device for aircraft according to claim 1, characterized in that said heater (3) further comprises:
locate respectively interior heat insulation layer (302) and outer insulation layer (303) of zone of heating (301) both sides, one side that is close to aircraft wing covering (2) is located in interior heat insulation layer (302), one side that is close to detector (1) is located in outer insulation layer (303).
3. Deicing device for aircraft according to claim 2, characterized in that said heater (3) further comprises:
an anti-abrasion protective layer (304), wherein the inner insulating layer (302), the heating layer (301) and the outer insulating layer (303) are wrapped by the anti-abrasion protective layer (304).
4. Deicing device for aircraft according to claim 3, characterized in that said heating layer (301) is a metallic heating layer.
5. A deicing apparatus for an aircraft as set forth in claim 3, wherein said heater further comprises:
an overheating protection layer (305), the overheating protection layer (305) being provided between the aircraft wing skin (2) and the inner insulation layer (302).
6. Deicing device for aircraft according to claim 1, characterized in that it comprises a plurality of pairs of probes (1) and heaters (3), the pairs of probes (1) and heaters (3) being spaced apart on the outer surface of the aircraft wing skin (2), and the pairs of probes (1) and heaters (3) being connected in parallel.
7. Deicing apparatus for an aircraft as set forth in claim 6, wherein said deicing apparatus further comprises:
the camera (5) is arranged at a position, close to an aircraft fuselage (6), of the outer surface of the aircraft wing skin (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021029831.9U CN212921989U (en) | 2020-06-05 | 2020-06-05 | Deicing device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021029831.9U CN212921989U (en) | 2020-06-05 | 2020-06-05 | Deicing device for aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN212921989U true CN212921989U (en) | 2021-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021029831.9U Active CN212921989U (en) | 2020-06-05 | 2020-06-05 | Deicing device for aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114655443A (en) * | 2021-12-30 | 2022-06-24 | 成都流体动力创新中心 | Deicing device, system and method for airplane |
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2020
- 2020-06-05 CN CN202021029831.9U patent/CN212921989U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114655443A (en) * | 2021-12-30 | 2022-06-24 | 成都流体动力创新中心 | Deicing device, system and method for airplane |
| CN114655443B (en) * | 2021-12-30 | 2023-06-23 | 成都流体动力创新中心 | Deicing device, system and method for airplane |
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