CN109850160A - A kind of frequency trailing type electrothermal deicing system for unmanned plane - Google Patents
A kind of frequency trailing type electrothermal deicing system for unmanned plane Download PDFInfo
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- CN109850160A CN109850160A CN201711232324.8A CN201711232324A CN109850160A CN 109850160 A CN109850160 A CN 109850160A CN 201711232324 A CN201711232324 A CN 201711232324A CN 109850160 A CN109850160 A CN 109850160A
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- deicing
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- working substance
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- icing
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Abstract
A kind of frequency trailing type electrothermal deicing system for unmanned plane disclosed by the embodiments of the present invention, is related to the hot clearing ice technology of the key positions such as unmanned plane wing, engine inlets, solves the problems, such as unmanned plane energy consumption deficiency deicing.After exciting icing detection module detects icing, valve is opened, fluid working substance drives through transfer tube, it exchanges heat in deicing side liquid working medium inflow heat exchanger with engine side fluid working substance, hot fluid working medium enters in embedded deicing unit after heat exchange, the shell of fluid working substance and embedded deicing unit in embedded deicing unit exchanges heat, carry out deicing, fluid working substance after cooling enters heat exchanger and exchanges heat in embedded deicing unit after deicing, constantly circulation, the system are mainly used for unmanned plane deicing.
Description
Technical field
The present invention relates to the hot clearing ice technology fields of the key positions such as unmanned plane wing, engine inlets, more particularly to
A kind of frequency trailing type electrothermal deicing system for unmanned plane.
Background technique
The key positions such as aircraft wing, engine inlets, which freeze, changes Aerodynamic Configuration of Aireraft or component capabilities, increases not
Safety even jeopardizes flight safety, therefore, periodically most important to maintenance Flight Safety to aircraft deicing in flight course.
Currently, typical unmanned plane clearing ice technology has mechanical deicing, chemical liquid deicing, hydrophobic covering anti-icing technology, heat
Deicing etc., five class clearing ice technologies have application in different aircrafts or aircraft different parts.Mechanical deicing is by electricity, gas, sound wave
Accumulated ice structure is destroyed Deng mechanical force is generated in body surface, so that accumulated ice falls off, pneumatic cover deicing, Electro-Impulse De-icing, electricity reprimand are removed
Ice, the deicing of low frequency piezoelectricity, ultrasonic wave deicing are mechanical deicing；Pneumatic cover deicing structure is complicated, regular visit；Electro-Impulse De-icing
Vulnerable to electromagnetic interference；Electricity reprimand deicing cover is easy to aging, deicing finite thickness；Low frequency piezoelectricity deicing passes through piezoelectricity using inverse piezoelectric effect
Driver causes guard plot material deformation, and deflection is limited；Ultrasonic wave deicing cost is high and expends a large amount of electric energy；Change
The limited increase aircraft weight of liquid deicing efficiency and power consumption are learned, and there are etching problems；Super hydrophobic covering anti-icing technology is not
It can be carried out active deicing and cost be high；Hot deicing has two kinds of electro-thermal deicing and airborne heat deicing, and electro-thermal deicing need to disappear
A large amount of electric energy are consumed, a large amount of energy consumptions influence the flight time of aircraft, restrict aircraft range.
Summary of the invention
It is an object of the invention to overcome the shortage of prior art, provides a kind of frequency trailing type heat for unmanned plane and remove
Ice system, the problem of being able to solve unmanned plane energy consumption deficiency deicing.
Technical solution of the invention:
A kind of frequency trailing type electrothermal deicing system for unmanned plane, the system include embedded deicing unit 1, transfer tube
5, heat exchanger 4, control valve 6, the first pipeline 701, the second pipeline 702, third pipeline 703 and the 4th pipeline 704, engine effluent
Body working medium is flowed out from third pipeline 703, flows through heat exchanger 4, flows back to engine from the 4th pipeline 704, embedded deicing unit 1 according to
It is secondary to be connected into circuit with control valve 6, heat exchanger 4 and transfer tube 5, when unmanned plane is in non-icing condition, control valve 6 and driving
Pump 5 is in closed state；
Wherein, embedded deicing unit 1 includes: shell 108 and the exciting icing detection module being placed in inside shell 108
107, rectangle sides one end for signal conditioning module 106 and conduit partition 105, shell 108 is equipped with fluid working substance entrance
102, the other end is equipped with fluid working substance outlet 101, and conduit partition 105 is for guiding fluid working substance to flow from fluid working substance entrance 102
Enter in embedded deicing unit 1, is carried out from the embedded deicing unit 1 of 101 outflow of fluid working substance outlet and fluid working substance and shell
Heat exchange；
The system work process is as follows: signal conditioning module 106 generates pumping signal, excites exciting icing detection module
107 vibration component generates vibration, and exciting icing detection module 107 detects vibration component vibration frequency and reaches icing frequency
Afterwards, valve 6 is first opened, and then fluid working substance drives through transfer tube 5, in second pipe 702 in fluid working substance inflow heat exchanger 4 with
Engine side fluid working substance exchanges heat, and hot fluid working medium enters embedding through first pipe 701 and fluid working substance entrance 102 after heat exchange
Entering in formula deicing unit 1, the shell 108 of the fluid working substance in embedded deicing unit 1 and embedded deicing unit 1 exchanges heat, into
Row deicing, after deicing in embedded deicing unit 1 fluid working substance after cooling through fluid working substance outlet 101 and second pipe 702
It exchanges heat into heat exchanger 4.
Further alternative, transfer tube 6 receives the control signal of signal conditioning circuit 106, and icing thickness increases, and freeze speed
Rate is accelerated, and control signal increases the output pressure head of transfer tube 6；Icing thickness reduces, and icing rate slows down, and control signal, which is reduced, to be driven
The output pressure head of dynamic pump 6.
Further alternative, the fluid working substance is the anti-freeze cooling liquid with high thermal conductivity ability.
A kind of frequency trailing type electrothermal deicing system for unmanned plane provided in an embodiment of the present invention, including embedded deicing
Unit, transfer tube, heat exchanger, control valve, fluid working substance and pipeline composition.Embedded deicing unit includes shell, fluid working substance
Conduit, exciting icing detection module, signal conditioning module；Exciting icing detection module perceives icing condition, and look-in frequency occurs
Variation, the control signal after signal conditioning module improves as transfer tube and control valve；Transfer tube drives fluid working substance flowing,
Exchange heat in heat exchanger with engine side hot fluid, and after through embedded deicing unit, exchange heat with housing outer surface, remove product
Ice.
Detailed description of the invention
Included attached drawing is used to provide to be further understood from the embodiment of the present invention, and which constitute one of specification
Point, for illustrating the embodiment of the present invention, and come together to illustrate the principle of the present invention with verbal description.It should be evident that below
Attached drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property labour under the premise of, be also possible to obtain other drawings based on these drawings.
Fig. 1 is that the frequency trailing type electrothermal deicing system theory structure provided in an embodiment of the present invention for unmanned plane is illustrated
Figure；
Fig. 2 is embedded deicing unit perspective view in the embodiment of the present invention；
Fig. 3 is embedded deicing unit top view in the embodiment of the present invention；
Fig. 4 is embedded deicing unit front view in the embodiment of the present invention；
The embedded deicing unit of 1-: the outlet of 101- fluid working substance, 102- fluid working substance entrance 103- control valve control signal
Cable, 104- transfer tube control signal cable 105- conduit partition, 106- signal processing circuit, 107- exciting icing detection mould
Block, 108- shell；
2- wing, 3- engine, 4- heat exchanger, 5- transfer tube, 6- control valve；
The embedded deicing unit entrance pipe of 701-, the embedded deicing unit export pipeline of 702-, 703- engine side are changed
Hot device entrance pipe, 704- engine side heat exchanger exit pipeline, 801- control valve service cable, 802- transfer tube control electricity
Cable, 803- signal processing unit cable.
Specific embodiment
Specific embodiments of the present invention are described in detail below in conjunction with attached drawing.In the following description, for solution
Purpose and not restrictive is released, elaborates detail, to help to be apparent from the present invention.However, to those skilled in the art
It is readily apparent that the present invention can also be practiced in the other embodiments departing from these details for member.
It should be noted that only showing in the accompanying drawings in order to avoid having obscured the present invention because of unnecessary details
Gone out with closely related device structure and/or processing step according to the solution of the present invention, and be omitted with relationship of the present invention not
Big other details.
The embodiment of the present invention provides a kind of frequency trailing type electrothermal deicing system for unmanned plane, exciting icing detection module
Icing condition is perceived, look-in frequency changes, and the control after signal conditioning module improves as transfer tube and control valve is believed
Number；Transfer tube drive fluid working substance flowing, in heat exchanger with engine side hot fluid exchange heat, and after through embedded deicing list
Member exchanges heat with housing outer surface, removes accumulated ice.The transfer tube frequency strong and weak with the characterization icing that exciting icing detection module perceives
Signal magnitude and adjust pressure head, change working medium heat exchange, realize from master regulation deicing.Start with the application of the invention, unmanned plane is available
The autonomous deicing of machine waste heat.
Referring to Fig. 1, the system include power supply unit 8, embedded deicing unit 1, transfer tube 5, heat exchanger 4, control valve 6,
First pipeline 701, the second pipeline 702, third pipeline 703 and the 4th pipeline 704；
Engine side fluid working substance is flowed out from third pipeline 703, is flowed through heat exchanger 4, is flowed back to and start from the 4th pipeline 704
Machine, embedded deicing unit 1 are successively connected into circuit with control valve 6, heat exchanger 4 and transfer tube 5, are in unmanned plane and do not freeze
When state, control valve 6 and transfer tube 5 are in closed state；
Wherein ,-Fig. 4 referring to fig. 2, embedded deicing unit 1 include: shell 108 and the exciting that is placed in inside shell 108
Rectangle sides one end for icing detection module 107, signal conditioning module 106 and conduit partition 105, shell 108 is equipped with stream
Body working medium entrances 102, the other end are equipped with fluid working substance outlet 101, and conduit partition 105 is for guiding in embedded deicing unit 1
Fluid working substance flow direction, guidance fluid working substance flows into embedded deicing unit 1 from fluid working substance entrance 102, from fluid work
The embedded deicing unit 1 of 101 outflow of matter outlet and fluid working substance exchange heat with shell；
Power supply unit 8 is for the exciting icing detection module 107 of embedded deicing unit 1, signal processing module 106, drive
The power supply of dynamic pump 5, control valve 6 is powered by cable 802 to transfer tube 5 specifically, being powered by cable 801 to control valve 6,
It is powered by cable 803 to signal processing circuit 106.
106 one side of signal conditioning circuit is produced for generating pumping signal, the vibration component of exciting icing detection module 107
Raw vibration；On the other hand, vibration frequency variation letter caused by exciting detecting module 107 being changed because of icing thickness and icing rate
It number is handled, is converted into the control signal of transfer tube 5 and control valve 6.Control signal after signal processing circuit 106 improves is logical
It crosses signal cable 104 and controls transfer tube, solenoid valve is controlled by signal cable 103.
The system work process is as follows: signal conditioning module 106 generates pumping signal, excites exciting icing detection module
107 vibration component generates vibration, and exciting icing detection module 107 detects vibration component vibration frequency and reaches icing frequency
Afterwards, vibration signal being converted into voltage signal, control valve 6 is first opened, and then transfer tube 5 works, driving fluid working substance circulation,
Fluid working substance drives through transfer tube 5, in second pipe 702 in fluid working substance inflow heat exchanger 4 with engine side fluid working substance into
Row heat exchange, hot fluid working medium enters in embedded deicing unit 1 through first pipe 701 and fluid working substance entrance 102 after heat exchange, embedding
The shell 108 for entering fluid working substance and embedded deicing unit 1 in formula deicing unit 1 exchanges heat, and carries out deicing, embedded after deicing
Fluid working substance after cooling exchanges heat through fluid working substance outlet 101 and second pipe 702 into heat exchanger 4 in deicing unit 1,
Then continue cycling through.
Engine 3, engine side heat exchanger entrance pipeline 703, engine side heat exchanger exit pipeline 704 are also possible to machine
The waste heat source of equipment is carried, but guarantee unmanned plane is met under flying condition when continuing strong icing condition, waste heat source is held at this
The continuous enough heats generated are for removing accumulated ice.
Preferably, transfer tube 6 receives the control signal of signal conditioning circuit 106, and icing thickness increases, and icing rate adds
Fastly, control signal increases the output pressure head of transfer tube 6；Icing thickness increase, icing rate accelerate when, the quality of shell 108 and
Rigidity increases, and the resonance frequency of exciting icing detection module 107 increases, 106 turns of conditioned circuit with the increase of icing thickness
It turns to transfer tube 5 and controls signal increase.The output pressure head of transfer tube 5 increases, to accelerate deicing side interior conduit fluid working substance
Flow velocity, enhance the heat exchange of fluid working substance and shell 108 in embedded deicing unit 1, accelerate to remove speed of icing, to realize autonomous
Regulate and control deicing.
Preferably, the fluid working substance is the anti-freeze cooling liquid with high thermal conductivity ability.
A kind of frequency trailing type electrothermal deicing system for unmanned plane provided in an embodiment of the present invention, does not need active control
Device participate in icing thickness resolving, deicing rate with accumulated ice detecting head caused by accumulated ice rate and accumulated ice thickness frequency variation and
Variation.Icing thickness increase causes the rigidity of the shell of icing detection head to increase, and then the resonance frequency increasing popped one's head in that causes to freeze
Adding, resonance frequency changes the output pressure head from main regulation transfer tube 5, so that the rate of circulating flow of fluid working substance is improved, enhancing heat exchange,
Ice-melt rate increases, and accumulated ice thickness reduces, resonance frequency variation, and then reduces the output pressure head of transfer tube 5, reduces fluid working substance
Rate of circulating flow, and then weaken heat exchange, until accumulated ice completely eliminates.With the advantages of existing anti-clearing ice technology second is that embedded deicing
Inside the embeddable body covering 2 of unit 1, the pneumatic and Stealth Fighter of unmanned plane is not influenced.Using engine waste heat deicing, it is not necessarily to
Consume a large amount of electric energy.
As above it describes for a kind of embodiment and/or the feature that shows can be in a manner of same or similar at one or more
It is used in a number of other embodiments, and/or combines or substitute the feature in other embodiments with the feature in other embodiments
It uses.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, one integral piece, step or component when using herein, but simultaneously
It is not excluded for the presence or additional of one or more other features, one integral piece, step, component or combinations thereof.
The many features and advantage of these embodiments are clear according to the detailed description, therefore appended claims are intended to
Cover all these feature and advantage of these embodiments fallen into its true spirit and range.Further, since this field
Technical staff is readily apparent that many modifications and changes, therefore is not meant to for the embodiment of the present invention to be limited to illustrated and description essence
Really structurally and operationally, but all suitable modifications and the equivalent fallen within the scope of its can be covered.
Unspecified part of the present invention is known to the skilled person technology.
Claims (3)
1. a kind of frequency trailing type electrothermal deicing system for unmanned plane, which is characterized in that the system includes embedded deicing list
Member 1, transfer tube 5, heat exchanger 4, control valve 6, the first pipeline 701, the second pipeline 702, third pipeline 703 and the 4th pipeline 704,
Engine side fluid working substance is flowed out from third pipeline 703, is flowed through heat exchanger 4, is flowed back to engine from the 4th pipeline 704, embedded
Deicing unit 1 is successively connected into circuit with control valve 6, heat exchanger 4 and transfer tube 5, when unmanned plane is in non-icing condition, control
Valve 6 processed and transfer tube 5 are in closed state；
Wherein, embedded deicing unit 1 include: shell 108 and the exciting icing detection module 107 being placed in inside shell 108,
Rectangle sides one end for signal conditioning module 106 and conduit partition 105, shell 108 is equipped with fluid working substance entrance 102, separately
One end is equipped with fluid working substance outlet 101, and conduit partition 105 is embedded in for guiding fluid working substance to flow into from fluid working substance entrance 102
In formula deicing unit 1, from the 101 embedded deicing unit 1 of outflow of fluid working substance outlet；
The system work process is as follows: signal conditioning module 106 generates pumping signal, excitation exciting icing detection module 107
Vibration component generates vibration, and exciting icing detection module 107 detects after vibration component vibration frequency reaches icing frequency, valve
6 first open, and then fluid working substance drives through transfer tube 5, in second pipe 702 in fluid working substance inflow heat exchanger 4 and engine
Side liquid working medium exchanges heat, and hot fluid working medium enters embedded remove through first pipe 701 and fluid working substance entrance 102 after heat exchange
In ice unit 1, the shell 108 of fluid working substance and embedded deicing unit 1 in embedded deicing unit 1 exchanges heat, and carries out deicing,
Fluid working substance after cooling through fluid working substance outlet 101 and second pipe 702 enters heat exchange in embedded deicing unit 1 after deicing
Device 4 exchanges heat.
2. system according to claim 1, which is characterized in that transfer tube 6 receives the control letter of signal conditioning circuit 106
Number, icing thickness increases, and icing rate is accelerated, and control signal increases the output pressure head of transfer tube 6；Icing thickness reduces, and freezes
Rate slows down, and control signal reduces the output pressure head of transfer tube 6.
3. system according to claim 1 or 2, which is characterized in that the fluid working substance is anti-with high thermal conductivity ability
Freeze coolant liquid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711232324.8A CN109850160A (en) | 2017-11-30 | 2017-11-30 | A kind of frequency trailing type electrothermal deicing system for unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711232324.8A CN109850160A (en) | 2017-11-30 | 2017-11-30 | A kind of frequency trailing type electrothermal deicing system for unmanned plane |
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| Publication Number | Publication Date |
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| CN109850160A true CN109850160A (en) | 2019-06-07 |
Family
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| CN201711232324.8A Pending CN109850160A (en) | 2017-11-30 | 2017-11-30 | A kind of frequency trailing type electrothermal deicing system for unmanned plane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110641711A (en) * | 2019-10-30 | 2020-01-03 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202255011U (en) * | 2011-06-30 | 2012-05-30 | 卡特彼勒S.A.R.L公司 | Multi-heat exchanger module and machine with multi-heat exchanger module |
| WO2012095646A1 (en) * | 2011-01-11 | 2012-07-19 | Bae Systems Plc | Turboprop-powered aircraft |
| CN202368791U (en) * | 2011-11-18 | 2012-08-08 | 武汉航空仪表有限责任公司 | Bushing type icing sensitive vibration component |
| US8444093B1 (en) * | 2011-04-18 | 2013-05-21 | Eran Epstein | Airplane leading edge de-icing apparatus |
| CN103557727A (en) * | 2013-11-25 | 2014-02-05 | 张家港市江南锅炉压力容器有限公司 | Heat exchanger |
| CN203572276U (en) * | 2013-11-25 | 2014-04-30 | 张家港市江南锅炉压力容器有限公司 | Heat exchanger |
| CN105383701A (en) * | 2014-08-28 | 2016-03-09 | 波音公司 | Detecting inflight icing conditions on aircraft |
| CN106741968A (en) * | 2016-12-29 | 2017-05-31 | 华中科技大学 | A kind of combined type deicing system based on the detection of ice sheet skin-surface bonding state |
| CN106907192A (en) * | 2015-12-09 | 2017-06-30 | 通用电气公司 | Heat management system |
-
2017
- 2017-11-30 CN CN201711232324.8A patent/CN109850160A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012095646A1 (en) * | 2011-01-11 | 2012-07-19 | Bae Systems Plc | Turboprop-powered aircraft |
| US8444093B1 (en) * | 2011-04-18 | 2013-05-21 | Eran Epstein | Airplane leading edge de-icing apparatus |
| CN202255011U (en) * | 2011-06-30 | 2012-05-30 | 卡特彼勒S.A.R.L公司 | Multi-heat exchanger module and machine with multi-heat exchanger module |
| CN202368791U (en) * | 2011-11-18 | 2012-08-08 | 武汉航空仪表有限责任公司 | Bushing type icing sensitive vibration component |
| CN103557727A (en) * | 2013-11-25 | 2014-02-05 | 张家港市江南锅炉压力容器有限公司 | Heat exchanger |
| CN203572276U (en) * | 2013-11-25 | 2014-04-30 | 张家港市江南锅炉压力容器有限公司 | Heat exchanger |
| CN105383701A (en) * | 2014-08-28 | 2016-03-09 | 波音公司 | Detecting inflight icing conditions on aircraft |
| CN106907192A (en) * | 2015-12-09 | 2017-06-30 | 通用电气公司 | Heat management system |
| CN106741968A (en) * | 2016-12-29 | 2017-05-31 | 华中科技大学 | A kind of combined type deicing system based on the detection of ice sheet skin-surface bonding state |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110641711A (en) * | 2019-10-30 | 2020-01-03 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle |
| CN110641711B (en) * | 2019-10-30 | 2021-08-03 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle |
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