CN113415428B - Thermal foaming type impact force generator for deicing - Google Patents
Thermal foaming type impact force generator for deicing Download PDFInfo
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- CN113415428B CN113415428B CN202110960767.9A CN202110960767A CN113415428B CN 113415428 B CN113415428 B CN 113415428B CN 202110960767 A CN202110960767 A CN 202110960767A CN 113415428 B CN113415428 B CN 113415428B
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- deicing
- heating
- impact force
- liquid medium
- flexible
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- 238000005187 foaming Methods 0.000 title abstract description 12
- 238000010438 heat treatment Methods 0.000 claims abstract description 58
- 239000007788 liquid Substances 0.000 claims abstract description 33
- 239000006260 foam Substances 0.000 claims description 12
- 238000009835 boiling Methods 0.000 claims description 3
- 230000005284 excitation Effects 0.000 abstract description 5
- 230000000694 effects Effects 0.000 description 3
- 230000000670 limiting effect Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 230000006698 induction Effects 0.000 description 2
- 230000000737 periodic effect Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000007650 screen-printing Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pipe Accessories (AREA)
Abstract
The invention is suitable for the technical field of aircraft deicing and provides a thermal foaming type impact force generator for deicing, which comprises an impact force exciter, wherein the impact force exciter comprises a flexible sealed cavity, an electric heater and a liquid medium; the electric heater comprises a heating electrode and a heating device, the heating electrode is electrically connected with the heating device, the heating device is completely arranged in the flexible closed cavity, and the heating electrode extends out of the flexible closed cavity and is connected with an external power supply; the liquid medium is contained within the flexible enclosure and is in direct contact with the heating electrode and/or the heating device. The deicing device has a simple excitation circuit, and eliminates complex external pipelines and control valves with larger weight, so that the deicing device has small volume, light weight, high energy utilization rate and high safety.
Description
Technical Field
The invention relates to the technical field of aircraft deicing, in particular to a thermal foaming type impact force generator for deicing.
Background
When the airplane flies in a low-temperature cloud layer, the icing phenomenon can be generated on the windward side, and the flying safety is influenced.
The anti-icing and deicing technology is used for guaranteeing flight safety. Compared with the traditional thermal type deicing system of gas heating and electric heating, the vibration deicing or coupled vibration deicing system has the obvious advantage of low energy consumption. The vibration exciter adopted at present is a piezoelectric type, an induction type electric pulse coil, an electric repulsion type electric pulse coil and the like. The piezoelectric actuator has the problems of small deformation and heavy weight; the problems of complex excitation circuit of the electric pulse coil, overhigh excitation voltage and the like cause that the deicing modes are still not ideal.
Therefore, there is a need in the art for a deicing device that has a simple excitation circuit, is lightweight, and has a small volume.
Disclosure of Invention
In order to solve the defects of the prior art, the invention provides a thermal foaming type impact force generator for deicing, which is suitable for a vibration deicing or coupled deicing system.
A thermal foam impact generator for deicing comprising an impact force actuator comprising a flexible sealed chamber, an electric heater and a liquid medium;
the electric heater comprises a heating electrode and a heating device, the heating electrode is electrically connected with the heating device, the heating device is completely arranged in the flexible closed cavity, and the heating electrode extends out of the flexible closed cavity and is connected with an external power supply;
the liquid medium is contained within the flexible enclosure and is in direct contact with the heating electrode and/or the heating device.
Further, the aircraft further comprises a mounting bracket, and the mounting bracket fixes the impact force exciter below the aircraft skin.
Further, the mounting frame is provided with an accommodating cavity, the accommodating cavity is opened towards one side of the aircraft skin, and the impact force exciter is arranged in the accommodating cavity.
Further, the mounting bracket is bonded to a mounting seat of the aircraft skin.
Further, the mounting frame further comprises a lug, and the lug is arranged on the outer side wall of the accommodating cavity.
Furthermore, the lug is provided with a mounting hole.
Further, the heating device is a heating wire or a heating film.
Further, the liquid medium fills the flexible sealed cavity.
Compared with the prior art, the thermal foaming type impact force generator for deicing disclosed by the invention has at least the following beneficial effects:
according to the invention, the heated liquid medium is foamed to generate high-temperature and high-pressure gas, and the impact force generated by outward expansion of the cavity of the flexible sealed cavity is used for knocking the skin of the airplane to perform vibration deicing in the sealed space.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic internal view of a thermal foam impact generator according to an embodiment of the present invention;
fig. 2 is a schematic perspective view of a thermal foaming impact generator according to an embodiment of the present invention.
FIG. 3 is a schematic view of an impact force exciter according to an embodiment of the present invention;
FIG. 4 is another schematic view of an impact force exciter according to an embodiment of the invention;
in the figure, 00-impact force generator, 10-impact force actuator, 11-flexible sealed cavity, 12-heater, 121-heating electrode, 122-heating device, 13-liquid medium, 20-mounting frame, 21-containing cavity, 22-lug, 23-mounting hole.
Detailed Description
The following description provides many different embodiments, or examples, for implementing different features of the invention. The particular examples set forth below are illustrative only and are not intended to be limiting.
A thermal foaming impact force generator 00 for deicing, as shown in fig. 1 and 2, comprises an impact force exciter 10, wherein the impact force exciter 10 comprises a flexible closed cavity 11, an electric heater 12 and a liquid medium 13, as shown in fig. 3;
the electric heater 12 comprises a heating electrode 121 and a heating device 122, the heating electrode 121 is electrically connected with the heating device 122, the heating device 122 is completely arranged in the flexible sealed cavity 11, and the heating electrode 121 extends out of the flexible sealed cavity 11 and is connected with an external power supply; the liquid medium 13 is contained in the flexible sealed chamber 11 and is in direct contact with the heating electrode 121 and/or the heating means 122. It will be appreciated by those skilled in the art that the liquid medium 13 surrounds the heating electrode 121 and the heating means 122 such that the heating means is operable to substantially heat the liquid medium 13.
In order to ensure the strength of the impact force, the liquid medium 13 fills the whole closed cavity 11 to avoid attenuation of the pressure wave generated by foaming due to the presence of gas, so that a continuous and stable pressure wave can be ensured.
The flexible closed cavity can be made of materials with better elasticity such as rubber and the like, and has the function of sealing the liquid medium in the flexible closed cavity, so that on one hand, when the impact force exciter works, the liquid medium is prevented from volatilizing under the condition that the liquid medium in the flexible closed cavity is repeatedly boiled, and the service life of the impact force exciter is prolonged; on the other hand, when the liquid medium in the aircraft interior is heated by the heater, the temperature of part or all of the medium is rapidly raised to the boiling point or above, high-pressure and high-temperature bubbles are generated, so that the flexible closed cavity expands outwards, impact force is generated, and vibration force is generated to remove ice on the surface of the aircraft skin.
Further, the liquid medium of this embodiment may be water, and under the heating effect of the heater, when the temperature reaches 100 degrees celsius or above 100 degrees celsius, the water starts to boil to generate high-temperature and high-pressure bubbles, which impact the cavity wall of the flexible sealed cavity to expand outward, so as to generate an impact force for deicing. It can be understood by those skilled in the art that the choice of the liquid medium, such as water, should not be taken as a limitation to the present invention, and theoretically, the present invention can be implemented as long as the liquid medium can be boiled and foamed at a certain temperature, i.e. a liquid medium that generates high-temperature and high-pressure bubbles.
The arrangement mode of the heating device in the flexible sealing cavity can be selected according to the shape and the type of the heating device, and the heating device can be a heating wire or a heating film. The heating device shown in fig. 1 is a patterned arrangement, for example, a heating film may be arranged on the substrate by screen printing, and the whole substrate is placed in the flexible sealed cavity; fig. 3 and 4 show that the heating wires directly adopting the spiral shape are uniformly arranged in the area to be heated. It should be noted that the arrangement of the heating device in the embodiment of the present invention is not intended to limit the present invention.
The flexible closed cavity 11 can be configured to have a certain shape, such as a square shape (as shown in fig. 3) or a spherical or ellipsoidal shape (as shown in fig. 4), wherein the liquid medium is represented by the inner squares in fig. 3 in a liquid state, and the liquid medium is represented by the small dots in fig. 4 in a foaming state.
The impact force exciter 10 needs to be fixed under the aircraft skin to be able to de-ice the aircraft skin, and therefore a thermal foam impact force generator for de-icing according to an embodiment of the invention further comprises a mounting bracket 20, the mounting bracket 20 fixing the impact force exciter 10 under the aircraft skin.
The mounting 20 is provided with a receiving chamber 21, the receiving chamber 21 being open towards a side of the aircraft skin, the impact exciter 10 being placed in the receiving chamber 21. The function of the accommodating cavity 21 is to fix the impact force exciter 10, on one hand, the impact force exciter 10 is fixed under the skin of the airplane to transmit the impact force to the lower part of the skin, and the ice accumulated on the skin is removed; on the other hand, the cavity walls of the accommodating cavities also serve to limit the expansion of the flexible closed cavities in the impact force exciter in directions other than towards the aircraft skin, so that the impact force can be intensively applied to the aircraft skin, thereby improving the deicing effect. It will be appreciated by those skilled in the art that the side of the receiving chamber 21 facing the aircraft skin may be open, and that the side facing the aircraft skin may be provided as a complete opening, or as a partial opening, leaving room for the impact force exciter to be able to transmit an impact force to the aircraft skin.
Fig. 2 is an overall perspective view of a thermal foam impact generator according to an embodiment of the present invention, fig. 1 is an internal structural view of the thermal foam impact generator, and an impact actuator 10 may be directly bonded into a receiving chamber 21 of a mounting bracket 20; at the same time, the thermal foam impact generator can also be directly bonded to the mounting seat of the aircraft skin. As will be appreciated by those skilled in the art, in order to mount the mechanical vibration deicing device, a mounting seat for fixing the vibration deicing device is provided below the aircraft skin, and the mounting bracket of the present application can directly adhere the side facing away from the opening of the accommodating cavity 21 to the mounting seat.
Preferably, the mounting bracket 20 further includes a tab 22, the tab 22 is disposed on an outer side wall of the accommodating cavity 21, the tabs may be disposed on four sides, or may be disposed on two opposite sides, and in order to ensure the overall stability of the mounting base, the accommodating cavity and the tab are integrally formed, and the tab may be provided with a mounting hole 23. Therefore, the mounting rack with the lugs can be directly bonded on the mounting seat below the aircraft skin, and the mounting rack can also be mounted on the mounting seat through the connecting piece, so that the damage of the deicing device to the aircraft skin is avoided.
As will be appreciated by those skilled in the art, the mounting bracket 20 needs to have a certain rigidity in order to limit the expansion and deformation of the impact exciter 10 on the side not facing the skin, and thus, metal, hard plastic, etc. may be used.
When the thermal foaming type impact force generator for deicing disclosed by the invention works, a high-power heater is used for rapidly heating a liquid medium 13 in a sealed cavity 10, the temperature of part or all of the liquid medium 13 is rapidly raised to be above a boiling point, high-temperature and high-pressure bubbles are generated in a flexible sealed cavity 11 through gasification, the flexible sealed cavity is expanded outwards to generate impact force, and the side wall of a containing cavity of an installation frame 20 has a limiting effect on the flexible sealed cavity, so that the impact force exciter 10 is expanded towards one side of an aircraft skin only, and only the impact force is applied to the aircraft skin, and therefore, vibration force is applied to the aircraft skin; after a certain time, the heating is stopped, the bubbles are gradually dissipated along with the stop of the heating, the gasified liquid is changed into liquid again, the pressure in the flexible sealed cavity 11 disappears, and the initial state is recovered. The heating can be also heated and stopped according to a certain time rule, so that the periodic impact force is provided, and the vibration deicing of the aircraft skin is realized.
It is worth to be noted that the heater of the invention needs to adopt a high-power heater, and can rapidly heat the liquid medium within the time range of microsecond to millisecond, so as to realize the effect of periodic vibration deicing.
Compared with the vibration deicing mode adopting piezoelectric type, induction type, electric repulsion type and other modes in the prior art, the thermal foaming type impact force generator for deicing disclosed by the invention is a very novel deicing device, a complex external pipeline and a control valve with larger weight are eliminated, an excitation circuit is simple, the size is small, the weight is light, the energy utilization rate is high, and the safety is high.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (8)
1. A thermal foam impact generator for deicing, characterized in that it comprises an impact force actuator (10), said impact force actuator (10) comprising a flexible closed chamber (11), an electric heater (12) and a liquid medium (13);
the electric heater (12) comprises a heating electrode (121) and a heating device (122), the heating electrode (121) is electrically connected with the heating device (122), the heating device (122) is completely arranged in the flexible closed cavity (11), and the heating electrode (121) extends out of the flexible closed cavity (11) and is connected with an external power supply;
the liquid medium (13) is contained inside the flexible closed cavity (11) and is in direct contact with the heating electrode (121) and/or the heating device (122);
the liquid medium in the flexible closed cavity is heated by the heater, and the temperature of part or all of the liquid medium is quickly raised to the boiling point or above to generate high-pressure high-temperature bubbles, so that the flexible closed cavity expands outwards to generate impact force.
2. The thermal foam impact generator for deicing of claim 1, further comprising a mounting bracket (20), said mounting bracket (20) securing said impact exciter (10) under the aircraft skin.
3. The thermofoam impact generator for deicing according to claim 2, characterized in that the mounting frame (20) is provided with a receiving chamber (21), the receiving chamber (21) opening out to the side of the aircraft skin, the impact force exciter (10) being placed in the receiving chamber (21).
4. The thermal foam impact generator for deicing as claimed in claim 3, characterized in that the mounting frame (20) is adhesively bonded to a mounting seat of an aircraft skin.
5. The thermofoaming impact generator for deicing according to claim 3, characterized in that said mounting frame (20) further comprises tabs (22), said tabs (22) being provided on the outer side walls of said housing cavity (21).
6. The thermal foam impact generator for deicing as claimed in claim 5, characterized in that mounting holes (23) are provided in said tabs (22).
7. Thermal foam impact generator for deicing according to one of claims 1 to 6, characterized in that said heating means (122) are heating wires or heating films.
8. Thermal foam impact generator for deicing according to claim 7, characterized in that said liquid medium (13) fills said flexible hermetic chamber (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110960767.9A CN113415428B (en) | 2021-08-20 | 2021-08-20 | Thermal foaming type impact force generator for deicing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110960767.9A CN113415428B (en) | 2021-08-20 | 2021-08-20 | Thermal foaming type impact force generator for deicing |
Publications (2)
| Publication Number | Publication Date |
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| CN113415428A CN113415428A (en) | 2021-09-21 |
| CN113415428B true CN113415428B (en) | 2021-11-02 |
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| CN202110960767.9A Active CN113415428B (en) | 2021-08-20 | 2021-08-20 | Thermal foaming type impact force generator for deicing |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114162328A (en) * | 2022-02-10 | 2022-03-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Airplane deicing method and deicing device |
| CN114604432A (en) * | 2022-05-11 | 2022-06-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Pulse discharge type bubble impact force generator for deicing |
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