CN114291270A - A transmission of electricity structure for paddle anti-icing ice - Google Patents
A transmission of electricity structure for paddle anti-icing ice Download PDFInfo
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- CN114291270A CN114291270A CN202111513890.2A CN202111513890A CN114291270A CN 114291270 A CN114291270 A CN 114291270A CN 202111513890 A CN202111513890 A CN 202111513890A CN 114291270 A CN114291270 A CN 114291270A
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- blade
- power transmission
- deicing
- transmission structure
- induction coil
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Abstract
The invention belongs to the technical field of helicopter deicing and relates to a power transmission structure for blade deicing and ice prevention. The invention discloses a power transmission structure for deicing a helicopter blade, which comprises an iron core (3) and coils (4) wound on the iron core (3), wherein the coils (4) are uniformly distributed along a rotating blade component (1), a blade partition heating control circuit (2), a support framework (6) and a temperature sensor (7) are fixed on the blade component (1), the blade partition heating control circuit (2) is connected with a heating resistor and the temperature sensor which are arranged in the blade, the support framework (6) is wound with an induction coil (5), the induction coil (5) is perpendicular to the coils (4) and is connected with the blade partition heating control circuit (2), and the iron core (3), the coils (4) and the induction coil (5) form a wireless power transmission structure. The invention can solve the meaningless loss of the contact type power transmission structure of the helicopter, and can reversely control the blade zone heating control circuit (2) to avoid overheating, thereby being safe and reliable.
Description
Technical Field
The invention belongs to the technical field of helicopter deicing and relates to a power transmission structure for blade deicing and ice prevention.
Background
The existing on-board blade deicing circuit basically adopts a structure that a collector ring moving part is in contact with a static part to carry out electric energy transmission, an electric brush is an easily-consumed and easily-damaged part in the collector ring and needs to be replaced periodically, and the time occupied by blade deicing is negligible in the whole service life of the helicopter; therefore, the contact type power transmission structure causes more meaningless working conditions, the existing deicing method based on the eddy current effect has the defects that the blades can only be heated in one direction, the measurement and feedback control on the temperature of the blades are not needed, and the blades are easily overheated.
In order to solve the problem of meaningless loss of the contact type power transmission structure of the helicopter and realize feedback control of blade temperature, a wireless feedback type power transmission structure needs to be designed.
Disclosure of Invention
The purpose of the invention is: the paddle wireless deicing and power transmission feedback control structure is simple in structure, easy to maintain and high in reliability.
The technical solution of the invention is as follows:
the utility model provides a transmission of electricity structure for helicopter paddle deicing, its includes iron core 3, twines in iron core 3's coil 4, and 1 symmetric distribution of rotatory paddle part is followed to coil 4, and paddle subregion heating control circuit 2, support skeleton 6, temperature sensor 7 are fixed in paddle part 1, paddle subregion heating control circuit 2 is connected the heating resistor who sets up in the paddle, and support skeleton 6 twines has induction coil 5, induction coil 5 is perpendicular and be connected with paddle subregion heating control circuit 2 with coil 4, iron core 3, coil 4, induction coil 5 form wireless transmission of electricity structure to realize the control to the paddle heating through subregion heating control circuit 2 and temperature sensor 7.
The middle part of the supporting framework 6 is provided with a hollow plastic compression structure which is sleeved on the rotating shaft of the paddle, and the outer circumference of the supporting framework is provided with a plurality of notches for winding the induction coil 5.
The supporting framework 6 and the winding part of the induction coil are made of silicon steel sheets, so that the eddy current effect can be reduced, the energy loss is avoided, and the rest plastic compression parts are made of glass fiber phenolic plastics, so that the plastic compression composite material is light in weight, convenient in process and easy to integrally form, does not generate eddy current, and reduces the energy loss.
The induction coil 5 adopts a staggered winding mode so as to increase the winding quantity of the coil and improve the inductive current.
The iron core 3 is an annular closed structure, four magnetic poles of the iron core for winding the coil are symmetrically arranged on the inner side of the annular structure, a closed magnetic conduction structure is formed, magnetic field leakage can be effectively reduced, the magnetic field of the induction coil is increased, the inductance effect is improved, and meanwhile, the influence on other airborne equipment is avoided.
The blade zone heating control circuit 2 comprises a junction station, a control chip and zone heating switches, wherein after the junction station rectifies and stabilizes the current generated by the induction coil 5, one path supplies power to the control chip, the other path is connected with the zone heating switches, the control chip receives voltage signals transmitted by a temperature sensor 7 arranged on the blade and controls whether the zone heating switches are closed or not and the closing time according to the threshold range of the voltage signals, the zone heating switches are connected with blade heating resistors, and 5 switches of the zone heating switches correspond to 5 zones of the blade; when the voltage transmitted to the control chip by the temperature sensor 7 arranged in the blade is in a reasonable range, the control chip outputs one path of high level to the partition heating switches according to an algorithm, one path of partition switches in the partition heating switches is closed, and the current rectified by the junction station realizes heating of the resistor through the partition heating switches.
The zoned heating switch is an interlocking 5-linked switch, so that the influence on the dynamic performance of the helicopter caused by simultaneous heating of multiple zones in the blade is prevented.
The invention has the advantages that: the power transmission structure for preventing and removing the ice of the blade adopts a wireless induction ice removing method in the technical field of the blade of the helicopter for the first time, can solve the problem of meaningless loss of a contact type power transmission structure of the helicopter, is different from eddy current induction, and can reversely control the blade zone heating control circuit 2 by arranging the temperature sensor on the blade to avoid overheating heating, thereby being safe and reliable.
Drawings
FIG. 1 is a schematic view of a power transmission structure for blade deicing protection of the present invention;
FIG. 2 is a schematic diagram of a blade zone heating control circuit;
the device comprises a 1-junction station, a 2-control chip, a 3-partition heating switch and a 4-temperature sensor.
Detailed Description
The invention is described in further detail below with reference to the drawings.
Example 1
As shown in figure 1, the power transmission structure for preventing and deicing of the helicopter blades comprises an iron core 3 and coils 4 wound on the iron core 4, wherein the coils 4 are symmetrically distributed along a rotating blade component 1, and is characterized in that a blade zone heating control circuit 2 and a support framework 6 are fixed on the blade component 1, the support framework 6 is wound by an induction coil 5, the iron core 3, the coils 4 and the induction coil 5 form a wireless power transmission structure, and the blade zone heating control circuit 2 and a temperature sensor realize control over blade heating. When the deicing system is started, direct current is introduced into the coil 4 to form a magnetic pole and a magnetic circuit shown in fig. 1, magnetic flux in the induction coil 5 changes and generates current, and the current is transmitted to the blade zone heating control circuit 2, the blade zone heating control circuit 2 comprises a junction station, a control chip and zone heating switches, after the junction station rectifies and stabilizes the current generated by the induction coil 5, one path supplies power to the control chip, the other path is connected with the zone heating switches, the control chip receives voltage signals transmitted by a temperature sensor arranged on the blade and controls whether the zone heating switches are closed or not and the closing time according to the threshold range of the voltage signals, the zone heating switches are connected with blade heating resistors, and 5 switches of the zone heating switches correspond to 5 zones of the blade; when the voltage transmitted to the control chip by the temperature sensor arranged in the paddle is within a reasonable range, the control chip outputs one path of high level to the partition heating switches according to an algorithm, one path of partition switches in the partition heating switches is closed, and the current rectified by the junction station realizes heating of the resistor through the partition heating switches.
The iron core 3 is made of electrician pure iron with high magnetic permeability, reduces magnetic circuit reluctance, increases air gap magnetic induction intensity, can reduce magnetic field leakage to a limited extent, and avoids influence on airborne equipment.
The middle part of the supporting framework 6 is provided with a hollow plastic compression structure which is sleeved on the rotating shaft of the paddle, and the outer circumference of the supporting framework is provided with a plurality of notches for winding the induction coil 5.
The supporting framework 6 and the winding part of the induction coil are made of silicon steel sheets, so that the eddy current effect generated by a changing magnetic field can be reduced, the energy loss is avoided, and the plastic compression part is made of glass fiber phenolic plastics, so that the plastic compression part is light in weight, convenient in process and easy to integrally form, and can not generate eddy current and reduce the energy loss.
The blade zone heating control circuit 2 comprises a junction station, a control chip and zone heating switches, wherein after the junction station rectifies and stabilizes the current generated by the induction coil 5, one path supplies power to the control chip, the other path is connected with the zone heating switches, the control chip receives voltage signals transmitted by a temperature sensor arranged on the blade and controls whether the zone heating switches are closed or not and the closing time according to the threshold range of the voltage signals, the zone heating switches are connected with blade heating resistors, and 5 switches of the zone heating switches correspond to 5 zones of the blade;
the zoned heating switch is an interlocking 5-linked switch, so that the influence on the dynamic performance of the helicopter caused by simultaneous heating of multiple zones in the blade is prevented.
The invention provides a deicing and power transmission structure for a helicopter blade, which realizes non-contact power transmission for the blade and prevents the blade from icing through an electromagnetic induction principle, realizes feedback control of blade heating through a temperature sensor and a control circuit, adjusts the heating time according to the temperature and prevents the blade from overheating. The power transmission structure meets the requirement of the whole life of the helicopter, has no consumable part and does not need to be replaced regularly.
Example 2
At present, methods for deicing blades are various, and limited power transmission and wireless power transmission can be adopted according to a power transmission mode.
The wired power transmission structure is complex in structure, easy to break down and frequent in maintenance, the electric brushes in surface contact, first contact and point contact modes are difficult to control pressure, complex in structure and easy to break down, the electric brushes are wearing parts and need to be replaced periodically, the deicing time can be ignored in the service life of the whole helicopter, relatively speaking, the wired power transmission structure greatly increases the failure rate, the maintenance cost and the consumption cost of the wearing parts, and the use value is low.
The wireless power transmission structure can be divided into an electromagnetic induction principle and an eddy current effect according to an electric conversion path, the existing electromagnetic induction type deicing mode is temporarily absent, the eddy current effect is applied, a magnetic field is generated through a coil, induced current is generated by utilizing the change of magnetic flux of metal in the magnetic field, and then the metal is directly heated to realize deicing of the blade, but the heating mode cannot realize zone heating of the blade, so that all regions of the blade where the metal is arranged are heated simultaneously, the power consumption is extremely high, or the deicing effect of all regions of the blade where the metal is arranged is poor due to insufficient helicopter power, and the flight safety of the helicopter is influenced due to high-power consumption or poor deicing effect of the blade; and the eddy current effect can not realize the detection and feedback of the temperature of the paddle, and the paddle can be overheated under the condition of large power consumption, so that potential safety hazards exist.
There are many places where detailed research can be conducted on the electromagnetic induction type power transmission deicing structure, for example, the number of the iron cores 3 and the number of the coils 4 can be 1 pair, 2 pairs, or 4 pairs, and since the conditions on the machine are severe, all exposed devices must be resistant to the environment, and the built-in electronic and structural devices must be resistant to vibration, impact, and the like.
Claims (8)
1. A power transmission structure for deicing a helicopter blade, characterized in that: including iron core (3), twine in coil (4) of iron core (3), rotatory paddle part (1) evenly distributed is followed in coil (4), and paddle subregion heating control circuit (2), support chassis (6), temperature sensor (7) are fixed in paddle part (1), paddle subregion heating control circuit (2) are connected the heating resistor who sets up in the paddle, and support chassis (6) winding has induction coil (5), induction coil (5) are perpendicular and are connected with paddle subregion heating control circuit (2) with coil (4), iron core (3), coil (4), induction coil (5) form wireless power transmission structure.
2. A power transmission structure for deicing a helicopter blade according to claim 1, characterized in that: the middle part of the supporting framework (6) is provided with a hollow plastic compression structure which is sleeved on the rotating shaft of the paddle, and the outer circumference of the supporting framework is provided with a plurality of notches for winding the induction coil (5).
3. A power transmission structure for deicing a helicopter blade according to claim 1, characterized in that: the support framework (6) and the winding part of the induction coil are made of silicon steel sheets, and the rest plastic compression parts are made of glass fiber phenolic plastics.
4. A power transmission structure for deicing a helicopter blade according to claim 1, characterized in that: the induction coil (5) adopts a staggered winding mode so as to increase the winding quantity of the coil and improve the inductive current.
5. A power transmission structure for deicing a helicopter blade according to claim 1, characterized in that: the iron core (3) is of an annular closed structure, and four magnetic poles of the iron core for winding the coil are symmetrically arranged on the inner side of the annular structure to form a closed magnetic conduction structure.
6. A power transmission structure for deicing a helicopter blade according to claim 1, characterized in that: the blade zone heating control circuit (2) comprises a junction station, a control chip, a zone heating switch and a temperature sensor, after current rectification and voltage stabilization are carried out on the current generated by the induction coil (5) by the junction station, one path supplies power to the control chip, the other path is connected with the zone heating switch, the control chip receives a voltage signal transmitted by the temperature sensor (7) arranged on the blade, whether the zone heating switch is closed or not and the closing time length are controlled according to the threshold range of the voltage signal, the zone heating switch is connected with the blade heating resistor, and 5 switches of the zone heating switch correspond to 5 zones of the blade.
7. A power transmission structure for deicing a helicopter blade according to claim 6, characterized in that: the zoned heating switch is an interlocking 5-linked switch, so that the influence on the dynamic performance of the helicopter caused by simultaneous heating of multiple zones in the blade is prevented.
8. A power transmission structure for deicing a helicopter blade according to claim 7, characterized in that: the blade zone heating control circuit (2) is internally provided with a control chip which adjusts the cyclic heating time of each zone of the blade by utilizing an algorithm and a voltage signal transmitted by a temperature sensor (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111513890.2A CN114291270A (en) | 2021-12-10 | 2021-12-10 | A transmission of electricity structure for paddle anti-icing ice |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111513890.2A CN114291270A (en) | 2021-12-10 | 2021-12-10 | A transmission of electricity structure for paddle anti-icing ice |
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| Publication Number | Publication Date |
|---|---|
| CN114291270A true CN114291270A (en) | 2022-04-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111513890.2A Pending CN114291270A (en) | 2021-12-10 | 2021-12-10 | A transmission of electricity structure for paddle anti-icing ice |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB525452A (en) * | 1939-02-21 | 1940-08-28 | British Thomson Houston Co Ltd | Improvements in and relating to means for heating parts of aircraft |
| GB1192364A (en) * | 1966-05-26 | 1970-05-20 | Teddington Aircraft Controls L | Improvements in or relating to Aircraft De-Icing and Anti-Icing Systems |
| CN105857620A (en) * | 2016-05-06 | 2016-08-17 | 武汉航空仪表有限责任公司 | Main paddle distributor for rotor wing anti-icing/deicing system |
| CN109792199A (en) * | 2016-10-03 | 2019-05-21 | 赛峰直升机发动机 | Equipped with the aircraft turbine airscrew engine of motor |
| CN112550730A (en) * | 2019-09-10 | 2021-03-26 | 拉季埃-菲雅克有限责任公司 | Electric motor for a propeller engine |
-
2021
- 2021-12-10 CN CN202111513890.2A patent/CN114291270A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB525452A (en) * | 1939-02-21 | 1940-08-28 | British Thomson Houston Co Ltd | Improvements in and relating to means for heating parts of aircraft |
| GB1192364A (en) * | 1966-05-26 | 1970-05-20 | Teddington Aircraft Controls L | Improvements in or relating to Aircraft De-Icing and Anti-Icing Systems |
| CN105857620A (en) * | 2016-05-06 | 2016-08-17 | 武汉航空仪表有限责任公司 | Main paddle distributor for rotor wing anti-icing/deicing system |
| CN109792199A (en) * | 2016-10-03 | 2019-05-21 | 赛峰直升机发动机 | Equipped with the aircraft turbine airscrew engine of motor |
| CN112550730A (en) * | 2019-09-10 | 2021-03-26 | 拉季埃-菲雅克有限责任公司 | Electric motor for a propeller engine |
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