CN117849383A - Airspeed tube electric heater structure - Google Patents
Airspeed tube electric heater structure Download PDFInfo
- Publication number
- CN117849383A CN117849383A CN202311851435.2A CN202311851435A CN117849383A CN 117849383 A CN117849383 A CN 117849383A CN 202311851435 A CN202311851435 A CN 202311851435A CN 117849383 A CN117849383 A CN 117849383A
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- CN
- China
- Prior art keywords
- heater
- ptc ceramic
- airspeed tube
- airspeed
- tube
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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- 239000000919 ceramic Substances 0.000 claims abstract description 30
- 230000003068 static effect Effects 0.000 claims abstract description 9
- 238000010438 heat treatment Methods 0.000 claims description 21
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 239000012212 insulator Substances 0.000 claims description 3
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 claims description 3
- 239000000395 magnesium oxide Substances 0.000 claims description 3
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 claims description 3
- 239000000843 powder Substances 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 229910001120 nichrome Inorganic materials 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 229910018487 Ni—Cr Inorganic materials 0.000 description 2
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Abstract
The invention belongs to the field of manufacturing of aviation onboard products, and relates to an electric heater structure of a airspeed tube. The structure comprises: armoured heaters and PTC ceramic heaters; the armored heater is arranged at the front edge part of the L-shaped airspeed tube total pressure port, the static pressure hole and the support arm; the PTC ceramic heater is arranged at the rear edge of the L-shaped airspeed tube support arm; the sheathed heater and the PTC ceramic heater are in series connection.
Description
Technical Field
The invention belongs to the field of manufacturing of aviation onboard products, and relates to an electric heater structure of a airspeed tube.
Background
The airspeed tube is a device which is matched with an aircraft and is used for measuring parameters such as total pressure, static pressure, attack angle and the like when the aircraft flies in the air, and the measurement accuracy, reliability and the like of the airspeed tube directly influence the task completion and flight safety of the aircraft. Icing conditions often occur when an aircraft flies in the air through a cloud of sub-cooled water. The detection mechanism of the airspeed tube is generally positioned outside the aircraft skin, and icing phenomenon can occur on the windward side of the airspeed tube under icing meteorological conditions. If the design of the airspeed tube does not meet the requirement of preventing and removing ice, the sensing function of the airspeed tube can be invalid under the icing meteorological conditions, so that the flight safety of the aircraft is affected. At present, a plurality of flying accidents caused by the icing of the airspeed tube occur at home and abroad, and the ice prevention and removal performance of the air data airspeed tube becomes a key performance.
The airspeed tube generally adopts a mode of arranging an electric heater to heat the surface of the product, so that the surface temperature of the product is always above 0 ℃, and the normal use under the air icing meteorological conditions is realized. The airspeed tube generally adopts an armored heater as a heating element, the heating element does not have automatic temperature control capability, and when the airspeed tube does not need to perform ice prevention and removal on the ground, larger power can be wasted, the temperature is extremely high, and people are easy to hurt. The surface temperature of the airspeed tube exceeds 500 ℃ after long-term electrification and use, so that the aging of a heating element can be accelerated, and the service life of a heater is shortened.
Disclosure of Invention
The purpose of the invention is that: aiming at the working mode of the prior airspeed tube heater, the invention realizes the airspeed tube with the automatic power-changing function and solves the problems of high ground working heating power and high temperature of the airspeed tube.
The technical scheme of the invention is as follows:
provided is an airspeed tube electric heater structure, comprising: armoured heaters and PTC ceramic heaters;
the armored heater is arranged at the front edge part of the L-shaped airspeed tube total pressure port, the static pressure hole and the support arm;
the PTC ceramic heater is arranged at the rear edge of the L-shaped airspeed tube support arm;
the sheathed heater and the PTC ceramic heater are in series connection.
The sheathed heater is wound into a spiral shape.
The armoured heater is made up of metal crust, magnesium oxide powder insulator and nickel-chromium wire for heating, which is stretched into wire shape by mould at high temperature.
The PTC ceramic heater is made by firing ceramic.
PTC ceramic heaters are used to provide heat to non-critical ice protection areas.
In the heating process, the heating power of the armored heater accounts for 70% -80% of the total power.
The armored heater is arranged at the total pressure port, the static pressure hole and the front edge part of the support arm of the L-shaped airspeed tube in a welding mode.
The PTC ceramic heater is tightly attached to the inner surface of the rear edge of the L-shaped airspeed tube support arm so as to facilitate heat transmission outwards.
The invention has the beneficial effects that:
the power consumption of a airspeed tube of the aircraft when the aircraft stands by on the ground is reduced, and the power consumption of the aircraft is reduced;
the surface temperature of the airspeed tube during ground test and use is reduced, and the safety of personnel and equipment is improved;
the service life and the reliability of the airspeed tube are improved, and the rejection rate of the airspeed tube is reduced.
Drawings
FIG. 1 is a schematic diagram of a pitot tube heater configuration.
Wherein, 1-total pressure port; 2-armoured heater; 3-static pressure holes; 4-a support arm; 5-L-shaped airspeed tube; 6-PTC ceramic heater.
Fig. 2 is a graph of individual sheathed heater power profiles.
Fig. 3 is a graph of the power of the PTC ceramic heater alone.
Fig. 4 is a power graph of a heater structure provided by the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without making any inventive effort are intended to fall within the scope of the present invention.
Features and exemplary embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by showing examples of the invention. The present invention is in no way limited to any particular arrangement and method set forth below, but rather covers any adaptations, alternatives, and modifications of structure, method, and device without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques have not been shown in detail in order not to unnecessarily obscure the present invention.
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other, and the embodiments may be referred to and cited with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
As shown in fig. 1, the present pitot tube electric heater structure includes: the sheathed heater 2 and the PTC ceramic heater 6 are in a serial structure. The sheathed heater 6 has high power and high efficiency, and is a main generation part of ice control power. The armoured heater 6 is wound into a spiral shape, and is arranged at the front edge parts of the total pressure port 1, the static pressure hole 3 and the support arm 4 of the L-shaped airspeed tube 6 to heat the pneumatic core part of the airspeed tube. The PTC ceramic heater has lower power and is used for providing heat for non-critical ice control areas such as the rear edge of the support arm. The PTC ceramic heater 6 is connected in series with the sheathed heater 2, and the heating power of the product on the ground is reduced by the temperature characteristic of PTC.
The armoured heater is made up of metal crust, magnesium oxide powder insulator and nickel-chromium wire for heating, which is stretched into wire shape by mould at high temperature. Under the condition of normal temperature and no wind, the power of the armored heater is reduced to a certain extent along with the temperature rise of the heater. The power of the armored heater can be correspondingly increased under the condition of high-speed heat dissipation. The armoured heater is wound into a spiral by adopting monofilaments, is arranged at pneumatic core parts such as a total pressure port, a static pressure hole, a front edge part of a support arm and the like according to the deicing requirement of a airspeed tube, and is welded on the inner wall of the metal by a welding method.
The PTC ceramic heater is formed by firing special ceramics, the ceramic heater can design a Curie temperature point, and the resistance increases exponentially after the temperature reaches the Curie temperature point, so that the power is reduced rapidly after the temperature exceeds the temperature, and the heater is maintained at a stable temperature.
The airspeed tube heating function is mainly used for preventing and removing ice of an aircraft in the air, and the icing part of the airspeed tube heating function is mainly positioned on the windward side of the airspeed tube and comprises a total pressure port, a static pressure tube body and the front edge of a support arm. In the icing wind tunnel, according to the icing condition of national army standards, the icing rate of the total pressure port of the airspeed tube can reach 30mm/min, and if effective heating protection is not available in the air, the pressure feeling of the airspeed tube can be invalid. Under the condition of air flight, the surface heat dissipation speed of the airspeed tube is extremely high under the condition of high-speed and low-temperature airflow, the power of the L-shaped airspeed tube tested in the icing wind tunnel exceeds 200W, the windward temperature of the L-shaped airspeed tube can be stabilized to be above 0 ℃, and the normal function of the airspeed tube is ensured. However, besides the air working state, the air speed tube heating function of some aircrafts on the ground can be started, and in addition, the air speed tube is required to work under the normal-temperature windless condition for the ground heating function test of the air speed tube. In the ground working state, the heat dissipation efficiency of the airspeed tube is extremely low, the heating power can generate extremely high temperature, the highest surface temperature of the airspeed tube with the heating power of 100W can exceed 500 ℃, and the temperature inside the airspeed tube can be higher. Therefore, if the ground working state can not effectively control the power, the service life of the airspeed tube is influenced to a certain extent, and personnel injury is easily caused.
The armored heater 2 and the PTC ceramic heater 6 are connected in series to heat together, so that the problem that the service life of the airspeed tube is influenced due to the fact that the temperature is too high during ground working can be effectively solved. For example: the heating power of the single armored heater 2 is 200W in the air, and the ground windless condition is 100W. The heating power of the single PTC ceramic heater 6 used in the air is 80W, and the ground windless condition is 20W. After series use, the airspeed tube has the heating air power of 180W, the ground windless condition of 30W, and the power is greatly reduced compared with the ground working condition under the test condition. Simulation analysis shows that the maximum surface temperature of the airspeed tube designed in series is only about 100 ℃ under the condition of no wind on the ground, which is far lower than 500 ℃ of the armored heater 6, thereby improving the safety. In addition, the PTC ceramic heater 6 is arranged at the rear end of the support arm, and can also protect the rear edge of the support arm to a certain extent, so that the rear edge is prevented from freezing.
The airspeed tube is designed by connecting the armored heater 2 and the PTC ceramic heater 6 in series, the power and the surface temperature of the airspeed tube are greatly reduced under the condition of no wind on the ground, the use safety is ensured, and the service life of the airspeed tube is prolonged. The power curve of the individual sheathed heater is shown in fig. 2, the power of the individual PTC ceramic heater is shown in fig. 3, and the power curve of the heater structure provided by the invention is shown in fig. 4.
The foregoing is merely a detailed description of the invention, which is not a matter of routine skill in the art. However, the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily contemplated by those skilled in the art within the scope of the present invention should be included in the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. An airspeed tube electric heater structure, comprising: armoured heaters and PTC ceramic heaters;
the armored heater is arranged at the front edge part of the L-shaped airspeed tube total pressure port, the static pressure hole and the support arm;
the PTC ceramic heater is arranged at the rear edge of the L-shaped airspeed tube support arm;
the sheathed heater and the PTC ceramic heater are in series connection.
2. The structure of claim 1, wherein the sheathed heater is wound in a spiral shape.
3. The structure of claim 1, wherein the sheathed heater is comprised of a metal sheath, a magnesium oxide powder insulator, and a heat-generating nichrome wire that is drawn into a wire shape at high temperature through a die.
4. The structure of claim 1 wherein the PTC ceramic heater is ceramic fired.
5. The structure of claim 1 wherein the PTC ceramic heater is used to provide heat to non-critical ice protection and removal regions.
6. The structure of claim 1, wherein the sheathed heater has a heating power of 70-80% of the total power during heating.
7. The structure of claim 1, wherein the sheathed heater is mounted on the L-shaped pitot tube total pressure port, the static pressure port, and the front edge portion of the support arm by welding.
8. The structure of claim 1 wherein the PTC ceramic heater is in close proximity to the inner surface of the trailing edge of the L-shaped pitot tube arm to facilitate heat transfer outwardly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311851435.2A CN117849383A (en) | 2023-12-29 | 2023-12-29 | Airspeed tube electric heater structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311851435.2A CN117849383A (en) | 2023-12-29 | 2023-12-29 | Airspeed tube electric heater structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117849383A true CN117849383A (en) | 2024-04-09 |
Family
ID=90547612
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311851435.2A Pending CN117849383A (en) | 2023-12-29 | 2023-12-29 | Airspeed tube electric heater structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117849383A (en) |
-
2023
- 2023-12-29 CN CN202311851435.2A patent/CN117849383A/en active Pending
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| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination |