CN113636085A - Unmanned aerial vehicle and control method of anti-icing and deicing system of unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle and control method of anti-icing and deicing system of unmanned aerial vehicle Download PDFInfo
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- CN113636085A CN113636085A CN202010345314.0A CN202010345314A CN113636085A CN 113636085 A CN113636085 A CN 113636085A CN 202010345314 A CN202010345314 A CN 202010345314A CN 113636085 A CN113636085 A CN 113636085A
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- 238000000034 method Methods 0.000 title claims abstract description 12
- 239000012530 fluid Substances 0.000 claims abstract description 88
- 239000007789 gas Substances 0.000 claims description 20
- 230000000694 effects Effects 0.000 claims description 15
- 238000001514 detection method Methods 0.000 claims description 13
- 230000001965 increasing effect Effects 0.000 claims description 8
- 238000002347 injection Methods 0.000 claims description 7
- 239000007924 injection Substances 0.000 claims description 7
- 238000005507 spraying Methods 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 5
- 230000002708 enhancing effect Effects 0.000 claims description 3
- 230000001419 dependent effect Effects 0.000 claims 1
- 230000002265 prevention Effects 0.000 description 8
- 239000000243 solution Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 239000000126 substance Substances 0.000 description 5
- 239000007921 spray Substances 0.000 description 4
- 230000002528 anti-freeze Effects 0.000 description 3
- 230000008014 freezing Effects 0.000 description 3
- 238000007710 freezing Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
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- 239000000470 constituent Substances 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000009969 flowable effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
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- 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
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
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- 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
- B64D15/20—Means for detecting icing or initiating de-icing
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- Engineering & Computer Science (AREA)
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Abstract
The invention relates to an unmanned aerial vehicle and an anti-icing system control method of the unmanned aerial vehicle, wherein the unmanned aerial vehicle comprises an engine and an anti-icing system, the engine comprises an engine main body and an exhaust funnel (10), exhaust gas of the engine main body is discharged through the exhaust funnel (10), the anti-icing system is used for providing fluid capable of preventing icing and/or removing ice blocks for an area to be anti-icing of the unmanned aerial vehicle, and the anti-icing system is configured to enable the fluid to be in heat exchange with the exhaust gas. The fluid for preventing and removing ice provided by the ice preventing and removing system can exchange heat with the exhaust gas flowing through the exhaust funnel, and the fluid absorbs heat from the exhaust gas, so that the ice preventing and removing can be effectively carried out on an area to be prevented and removed of the unmanned aerial vehicle, and the flight safety of the unmanned aerial vehicle is improved.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle and a control method of an anti-icing and deicing system of the unmanned aerial vehicle.
Background
The ice prevention and the ice removal of the airplane are important functions for guaranteeing the safety of the airplane. Deicing is the prevention of icing on aircraft surfaces and deicing is the removal of ice that has condensed on aircraft surfaces. There are four more common ways of protecting an aircraft from ice: gas-heated anti-icing, electric-heated anti-icing, mechanical de-icing and chemical liquid anti-icing.
The gas-heat anti-icing is to guide a hot gas source to the front edge of a wing, a tail wing and other parts needing anti-icing so as to prevent icing. The electrothermal ice-proof is to embed a strip, wire or film heating element into the easy-to-freeze part of the airplane and to use the electric heating mode to prevent and remove ice. The mechanical deicing means that a layer of expandable rubber pipe belts is arranged on the front edge of the wing, the pipe belts are attached to the wing in normal times, after the wing is frozen, the pipe belts are inflated and deflated to generate periodic expansion and contraction, and the ice layer on the surface can be broken and blown away by airflow. The chemical solution deicing is to spray an antifreeze solution on the icing surface of the airplane for deicing and preventing freezing, the antifreeze solution is a chemical liquid with a very low freezing point, and the antifreeze solution lowers the freezing point of water to melt an formed ice layer.
At present, for a medium-sized fixed wing unmanned aerial vehicle, an aviation piston gasoline engine is generally adopted as a power device, and due to the power limitation of a piston engine, the power requirement of an airplane wing in an electrothermal ice prevention and removal mode cannot be met; meanwhile, the piston engine does not have a large-flow high-temperature gas source to maintain the work of the ice preventing and removing system, so that the piston engine is not suitable for adopting the traditional gas heat ice preventing mode; the adoption of mechanical deicing requires the addition of a complex mechanical structure, so that the overall weight of the unmanned aerial vehicle is increased, and the cost is higher; chemical liquid anti-icing is not suitable for use in air flight. Based on this, at present, there is no anti-icing and deicing measure on the wings of small and medium-sized unmanned aerial vehicles, and the high-altitude flight safety of the small and medium-sized unmanned aerial vehicles is seriously influenced.
It is noted that the information disclosed in this background section is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information constitutes prior art already known to a person skilled in the art.
Disclosure of Invention
The embodiment of the invention provides an unmanned aerial vehicle and a control method of an anti-icing and deicing system of the unmanned aerial vehicle, which are used for performing anti-icing and deicing on an ice area to be prevented and deiced of the unmanned aerial vehicle and improving the flight safety of the unmanned aerial vehicle.
According to an aspect of the invention, there is provided a drone comprising:
the engine comprises an engine main body and an exhaust cylinder, wherein exhaust gas of the engine main body is exhausted through the exhaust cylinder; and
an anti-icing and de-icing system for providing a fluid capable of preventing icing and/or removing ice to an area of the drone to be de-iced, the anti-icing and de-icing system being configured to enable the fluid to exchange heat with the exhaust air.
In some embodiments, an anti-icing system includes a heat exchange device and a spray device in fluid communication, the heat exchange device disposed on an exhaust stack, the spray device disposed proximate to an area to be anti-iced.
In some embodiments, a heat exchange apparatus includes a skin disposed outside an exhaust stack and an outer flow passage formed between the skin and an outer wall of the exhaust stack, a fluid in the outer flow passage exchanging heat with exhaust gas flowing through the exhaust stack.
In some embodiments, the inner wall of the chimney is provided with fins for enhancing heat exchange.
In some embodiments, the injection device comprises:
the first conveying pipe is communicated with the outlet of the heat exchange device;
the connecting pipe is communicated with the first conveying pipe; and
and the second conveying pipe is communicated with the connecting pipe and is provided with a plurality of through holes arranged along the axis direction of the second conveying pipe, and the through flow of the second conveying pipe is smaller than that of the first conveying pipe so as to increase the jet pressure of the fluid sprayed out from the through holes.
In some embodiments, the orifice of the connecting tube connected to the second delivery tube is offset from the through-hole.
In some embodiments, the plurality of through holes are arranged in a circumferential direction of the second delivery pipe.
In some embodiments, the unmanned aerial vehicle further comprises a wing, the area to be protected from ice comprises a leading edge of the wing, and the first delivery pipe and the second delivery pipe are both disposed inside the wing and near the leading edge.
In some embodiments, the first duct and the second duct are both arranged along the extension direction of the leading edge.
In some embodiments, the first and second ducts are arranged in parallel.
In some embodiments, the interior of the airfoil is provided with a fluid passage through which fluid exits the airfoil, the fluid passage communicating with the inlet of the heat exchange device.
In some embodiments, the anti-icing system further comprises a power drive for driving the flow of fluid.
In some embodiments, the anti-icing system further comprises a controller, a first temperature detection device and a second temperature detection device which are in signal connection with the controller, wherein the first temperature detection device is used for detecting the temperature T of the fluid at the outlet of the heat exchange device1A second temperature detection means for detecting the temperature T of the fluid flowing out of the area to be ice-removed2The controller is based on the temperature T of the fluid1And fluid temperature T2The power of the power driving device is adjusted.
According to another aspect of the present invention, there is provided an anti-icing and deicing system control method for an unmanned aerial vehicle, including:
when T is1<T11And T2<T21When the power is needed, the power of the power driving device is increased;
when T is1>T12And T2>T21Or when T is1>T11And T2<T21When the power is needed, the power of the power driving device is reduced;
wherein, T11Is the maximum withstand temperature, T, of the heat exchange device12<T11，T21The minimum temperature at which the deicing effect can be achieved.
In some embodiments, the anti-icing system control method further comprises:
when T is1>T11Or T2<T21And then sending out an alarm signal.
Based on the technical scheme, the fluid for preventing and removing ice provided by the anti-icing and deicing system in the embodiment of the invention can exchange heat with the exhaust gas flowing through the exhaust funnel, and the fluid absorbs heat from the exhaust gas, so that effective anti-icing and deicing can be performed on an area to be prevented and deiced of the unmanned aerial vehicle, and the flight safety of the unmanned aerial vehicle in a cold and humid environment is improved; the deicing system overcomes the defect that the conventional engine of the unmanned aerial vehicle does not have a large-flow high-temperature gas source to maintain the work of the deicing system, improves the traditional gas-heat deicing mode, and is more suitable for popularization and use on the light unmanned aerial vehicle.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
fig. 1 is a schematic structural diagram of an exhaust funnel and a heat exchange device in an embodiment of the unmanned aerial vehicle of the invention.
Fig. 2 is a schematic structural diagram of a wing and a spraying device in an embodiment of the unmanned aerial vehicle.
FIG. 3 is a partial schematic structural diagram of the embodiment of FIG. 2.
Fig. 4 is a schematic structural diagram of an injection device in an embodiment of the unmanned aerial vehicle of the invention.
Fig. 5 is a schematic diagram of the flow of fluid in an embodiment of the drone of the present invention.
In the figure:
10. an exhaust funnel; 11. ribs; 12. an inner flow passage;
21. covering a skin; 22. an outer flow passage; 23. an inlet; 24. an outlet;
30. an airfoil; 31. a leading edge; 32. a fluid channel;
41. a first delivery pipe; 42. a connecting pipe; 43. a second delivery pipe; 44. and a through hole.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "central," "lateral," "longitudinal," "front," "rear," "left," "right," "upper," "lower," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings for convenience in describing the invention and for simplicity in description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the scope of the invention.
Referring to fig. 1, in some embodiments of the drone provided by the present invention, the drone comprises an engine comprising an engine body and an exhaust stack 10, exhaust from the engine body being exhausted through the exhaust stack 10, and an anti-icing system for providing a fluid capable of preventing icing and/or removing ice to an area of the drone to be protected from ice, the anti-icing system being configured to enable the fluid to be in thermal communication with the exhaust.
In the embodiments, the fluid for preventing and removing ice provided by the anti-icing and de-icing system can exchange heat with the exhaust gas flowing through the exhaust funnel 10, and the fluid absorbs heat from the exhaust gas, so that the anti-icing and de-icing of the area to be prevented and removed of the unmanned aerial vehicle can be effectively carried out, and the flight safety of the unmanned aerial vehicle in a cold and humid environment is improved; the deicing system overcomes the defect that the conventional engine of the unmanned aerial vehicle does not have a large-flow high-temperature gas source to maintain the work of the deicing system, improves the traditional gas-heat deicing mode, and is more suitable for popularization and use on the light unmanned aerial vehicle.
In some embodiments, the anti-icing system includes a heat exchange device disposed on the chimney 10 and a spray device disposed proximate to the area to be anti-iced in fluid communication.
By providing heat exchange means, heat exchange of the fluid with the exhaust gas flowing through the exhaust stack 10 is facilitated. By arranging the spraying device, the fluid can be sprayed on the ice area to be controlled, and the spraying mode is favorable for increasing the coverage area of the fluid.
In some embodiments, the heat exchange apparatus includes a skin 21 disposed outside the exhaust stack 10 and an outer flow passage 22 formed between the skin 21 and an outer wall of the exhaust stack 10, and a fluid is heat exchanged with exhaust gas flowing through the exhaust stack 10 in the outer flow passage 22.
The exhaust pipe 10 is provided with an inner flow passage 12 therein, and exhaust gas generated from the engine body is discharged through the inner flow passage 12. The outer flow passage 22 is located at the outer side of the inner flow passage 12, the inner flow passage 12 and the outer flow passage 22 are separated by the outer wall of the exhaust funnel 10, when the fluid for preventing ice flows through the outer flow passage 22, the fluid can exchange heat with the exhaust gas flowing through the inner flow passage 12, the fluid absorbs the heat of the exhaust gas, the temperature of the fluid can be increased, and the ice preventing and removing effect is achieved; meanwhile, the exhaust transfers partial heat to the fluid, so that the temperature of the exhaust gas discharged into the atmosphere can be reduced, the environment is protected, and meanwhile, the waste heat utilization is realized.
In some embodiments, the inner wall of the chimney 10 is provided with fins 11 for enhancing heat exchange. By arranging the fins, the efficiency of heat exchange can be remarkably improved. The ribs 11 are in a strip shape, are mounted on the inner wall of the exhaust funnel 10, and extend along the axial direction of the exhaust funnel 10. The inner wall of the exhaust funnel 10 is provided with a plurality of uniformly arranged fins 11 along the circumferential direction.
As shown in fig. 2 and 3, in some embodiments, the injection device includes a first delivery pipe 41, a connection pipe 42, and a second delivery pipe 43, the first delivery pipe 41 communicating with the outlet 24 of the outer flow passage 22, the connection pipe 42 being connected between the first delivery pipe 41 and the second delivery pipe 43, the second delivery pipe 43 being provided with a plurality of through holes 44 arranged in an axial direction thereof, a flow rate of the second delivery pipe 43 being smaller than that of the first delivery pipe 41 to increase an injection pressure of the fluid ejected from the through holes 44. The flow rate here is the volume of the first duct 41 or the second duct 43.
By setting the flow rate of second delivery pipe 43 to be smaller than the flow rate of first delivery pipe 41, fluid can be accumulated in first delivery pipe 41, and when flowing to second delivery pipe 43, the flow rate becomes small, the fluid pressure increases, and the ejection effect is facilitated.
The plurality of through holes 44 are arranged along the axial direction of the second conveying pipe 43, so that the fluid coverage area can be increased, the ice prevention and removal efficiency is improved, and the dead angle of ice prevention and removal is avoided.
As shown in fig. 4, the first conveying pipe 41 and the second conveying pipe 43 are both circular pipes, and the pipe diameter of the first conveying pipe 41 is larger than that of the second conveying pipe 43.
In some embodiments, the orifice of the connecting tube 42 connected to the second delivery tube 43 is offset from the through hole 44.
If the nozzle of the connection pipe 42 connected to the second delivery pipe 43 is disposed opposite to the through hole 44, the fluid flowing through the connection pipe 42 to the second delivery pipe 43 is directly ejected through the through hole 44, so that the fluid in the first delivery pipe 41 may not reach the end of the first delivery pipe 41 far from the inlet end, and correspondingly, the fluid in the second delivery pipe 43 may not reach the distal end, thereby causing non-uniform ejection range, and the end far from the inlet end of the fluid may not obtain the anti-icing and de-icing effects. In the above embodiment, the nozzle of the connecting pipe 42 connected to the second conveying pipe 43 is staggered with the through hole 44, so that the fluid is prevented from being directly sprayed out of the through hole 44, more fluid flows to the far end, uniform spraying of each through hole 44 is facilitated, and the anti-icing effect is greatly improved.
In some embodiments, the plurality of through holes 44 are arranged in the circumferential direction of the second delivery pipe 43.
In the embodiment shown in fig. 4, a plurality of rows of through holes 44 are provided in the axial direction of the second conveyance pipe 43, and each row of the plurality of through holes 44 is arranged in the circumferential direction.
In some embodiments, the drone further comprises a wing 30, the area to be protected from ice comprises a leading edge 31 of the wing 30, the first duct 41 and the second duct 43 are both disposed inside the wing 30 and proximate to the leading edge 31. The ice protection and removal system described above can be used to protect the leading edge 31 from ice and prevent the leading edge 31 from icing.
In some embodiments, first duct 41 and second duct 43 are both arranged along the direction of extension of leading edge 31. The leading edge 31 extends from the end of the wing 30 close to the fuselage to the end remote from the fuselage, i.e. from the root to the tip of the wing 30. This arrangement can increase the coverage of the leading edge 31 as much as possible, and improve the deicing prevention effect.
In some embodiments, first delivery tube 41 and second delivery tube 43 are arranged in parallel. The connection pipe 42 is perpendicular to the first and second transfer pipes 41 and 43.
In some embodiments, the airfoil 30 is provided with a fluid passage 32 therein, and fluid exits the airfoil 30 through the fluid passage 32, the fluid passage 32 communicating with the inlet 23 of the outer flow passage 22. This has the advantage that the outer flow passage 22 and the injection device form a closed-loop circulation system, and the fluid can circularly flow in the outer flow passage 22 and the injection device, so that the circulation of the fluid for preventing ice can be realized, and the configuration of the ice preventing system can be simplified.
As shown in fig. 3, the fluid from the outer flow passage 22 first enters the first delivery pipe 41, then enters the second delivery pipe 43 through the connection pipe 42, and finally is sprayed on the inner side wall surface of the leading edge 31 of the airfoil 30 through the through hole 44, if ice cubes are condensed on the outer side wall of the leading edge 31, the fluid can melt the ice cubes, so that the deicing effect is achieved, the continuous supply of the fluid after the deicing effect is achieved, and the effect of preventing the continuous icing can also be achieved. The fluid sprayed on the inner sidewall surface of the leading edge 31 can flow out through the fluid channel 32 in the airfoil 30, and then enter the outer flow passage 22 through the inlet 23 of the outer flow passage 22 to continue heat exchange, and then enter the first delivery pipe 41, so as to form a closed-loop circulation system.
In some embodiments, the anti-icing system further comprises a power drive for driving the flow of fluid. By providing the power driving device, the flow efficiency of the fluid can be improved. The power driving device can adopt a power component such as an electric pump.
In some embodiments, the anti-icing system further comprises a controller, a first temperature detection device and a second temperature detection device which are in signal connection with the controller, wherein the first temperature detection device is used for detecting the temperature T of the fluid at the outlet of the heat exchange device1A second temperature detection device for detecting the flow out of the area to be ice-removedBody temperature T2The controller is based on the temperature T of the fluid1And fluid temperature T2The power of the power driving device is adjusted.
By arranging the controller, the first temperature detection device and the second temperature detection device, the temperature T of the fluid at the outlet of the heat exchange device can be measured1And the temperature T of the fluid flowing out of the ice zone to be protected2Performing real-time monitoring by monitoring the fluid temperature T1The temperature T of the fluid at the outlet of the heat exchange device can be prevented1Too high to damage the constituent parts of the heat exchange device, such as the skin 21; by monitoring the fluid temperature T2Whether the temperature of the fluid sprayed to the ice prevention and removal area can achieve the ice prevention and removal effect or not can be judged.
In some embodiments, the fluid temperature T at the outlet of the heat exchange device1The temperature T of the fluid flowing out of the region to be ice-controlled, which is the temperature of the fluid at the outlet of the outer flow passage 222Is the fluid temperature at the outlet of the fluid channel 32.
In each of the above embodiments, the engine may be a piston engine. The engine may be suspended from the wing 30.
In each of the embodiments described above, the fluid may be water, air, or other flowable substance.
Through the description of the multiple embodiments of the unmanned aerial vehicle, it can be seen that the embodiments of the present invention use the exhaust gas in the exhaust funnel 10 of the engine as a heat source to heat the fluid for preventing ice, and the heated fluid for preventing ice is sent to the leading edge 31 of the wing 30 through the first delivery pipe 41, the connecting pipe 42 and the second delivery pipe 43, so that the effects of preventing ice and removing ice can be achieved on the leading edge 31, the wing is prevented from being frozen, and the flight safety of the unmanned aerial vehicle is improved.
Based on the unmanned aerial vehicle, the invention also provides an anti-icing and deicing system control method for the unmanned aerial vehicle, which comprises the following steps:
when T is1<T11And T2<T21When the power is needed, the power of the power driving device is increased;
when T is1>T12And T2>T21Or when T is1>T11And T2<T21When the power is needed, the power of the power driving device is reduced;
wherein, T11Is the maximum withstand temperature, T, of the heat exchange device12<T11，T21The minimum temperature at which the deicing effect can be achieved.
T11For the highest withstand temperature of the various components of the heat exchange device, in some embodiments, T11The highest withstand temperature of the skin 21.
In some embodiments, the anti-icing system control method further comprises:
when T is1>T11Or T2<T21And then sending out an alarm signal. Through sending alarm signal, can send the warning to ground control personnel, make ground control personnel can master unmanned aerial vehicle deicing system's behavior in real time.
In one embodiment, the highest withstand temperature T of skin 2111At 90 ℃ T12Set to 50 ℃ and a minimum temperature T at which an anti-icing effect can be achieved21Is 10 ℃. Accordingly, the control strategy of the controller is: when T is1<90 ℃ and T2<The power of the power driving device is improved at 10 ℃; when T is1>At 50 ℃ and T2>10 ℃ or T1>90 ℃ and T2<And when the temperature is 10 ℃, reducing the power of the power driving device. When T is1<90 ℃ and T2Not less than 10 ℃ or T1>At 50 ℃ and T2When the temperature is less than or equal to 10 ℃, the power of the power driving device does not need to be adjusted. In addition, when T is1>90 ℃ or T2<And when the temperature is 10 ℃, an alarm signal is sent out.
The positive technical effects of the unmanned aerial vehicle in the above embodiments are also applicable to the control method of the deicing system of the unmanned aerial vehicle, and are not described herein again.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made without departing from the principles of the invention, and these modifications and equivalents are intended to be included within the scope of the claims.
Claims (15)
1. An unmanned aerial vehicle, comprising:
an engine including an engine main body and an exhaust stack (10), exhaust gas of the engine main body being discharged through the exhaust stack (10); and
an anti-icing and de-icing system for providing a fluid capable of preventing icing and/or removing ice to an area of the drone to be protected from ice, the anti-icing and de-icing system being configured to enable the fluid to be in thermal communication with the exhaust air.
2. An unmanned aerial vehicle according to claim 1, wherein the anti-icing and de-icing system comprises a heat exchange device and a spraying device in fluid communication, the heat exchange device being provided on the exhaust funnel (10), the spraying device being provided in proximity to the area to be de-iced.
3. The drone of claim 2, wherein the heat exchange means comprise a skin (21) arranged outside the chimney (10) and an outer flow channel (22) formed between the skin (21) and an outer wall of the chimney (10), the fluid being in heat exchange with the exhaust gases flowing through the chimney (10) inside the outer flow channel (22).
4. Unmanned aerial vehicle according to claim 2, characterized in that the inner wall of the chimney (10) is provided with fins (11) for enhancing heat exchange.
5. The drone of claim 2, wherein the injection device comprises:
a first duct (41) communicating with the outlet (24) of the heat exchange means;
a connection pipe (42) communicating with the first delivery pipe (41); and
a second delivery pipe (43) communicating with the connection pipe (42), the second delivery pipe (43) being provided with a plurality of through holes (44) arranged in an axial direction thereof, a flow rate of the second delivery pipe (43) being smaller than a flow rate of the first delivery pipe (41) to increase an ejection pressure of the fluid ejected from the through holes (44).
6. A drone according to claim 5, characterised in that the mouth of the connecting pipe (42) connected to the second duct (43) is staggered from the through hole (44).
7. A drone according to claim 5, characterised in that the through holes (44) are arranged in a circumferential direction of the second duct (43).
8. A drone according to claim 5, characterised in that it further comprises an airfoil (30), the area to be protected from ice comprising a leading edge (31) of the airfoil (30), the first duct (41) and the second duct (43) being both arranged inside the airfoil (30) and close to the leading edge (31).
9. A drone according to claim 8, characterised in that the first duct (41) and the second duct (43) are both arranged along the extension direction of the leading edge (31).
10. A drone according to claim 8, characterised in that the first duct (41) and the second duct (43) are arranged in parallel.
11. A drone according to claim 8, characterised in that the wing (30) is internally provided with a fluid passage (32) through which the fluid exits the wing (30), the fluid passage (32) communicating with the inlet (23) of the heat exchange device.
12. A drone according to claim 2, wherein the anti-icing and de-icing system further comprises a power drive for driving the flow of the fluid.
13. An unmanned aerial vehicle according to claim 12, wherein the anti-icing and de-icing system further comprises a controller, and first and second temperature detection devices in signal connection with the controller, the first temperature detection device being configured to detect a fluid temperature T at the outlet of the heat exchange device1And the second temperature detection device is used for detecting the temperature T of the fluid flowing out of the area to be controlled with ice2Said controller being dependent on said fluid temperature T1And the temperature T of the fluid2The power of the power driving device is adjusted.
14. An anti-icing system control method based on the unmanned aerial vehicle as claimed in claim 13, characterized by comprising:
when T is1<T11And T2<T21When the power is required to be increased, the power of the power driving device is increased;
when T is1>T12And T2>T21Or when T is1>T11And T2<T21When the power is not available, reducing the power of the power driving device;
wherein, T11Is the maximum withstand temperature, T, of the heat exchange device12<T11，T21The minimum temperature at which the deicing effect can be achieved.
15. The method for controlling an anti-icing system according to claim 14, further comprising:
when T is1>T11Or T2<T21And then sending out an alarm signal.
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| CN202010345314.0A CN113636085A (en) | 2020-04-27 | 2020-04-27 | Unmanned aerial vehicle and control method of anti-icing and deicing system of unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114789793A (en) * | 2022-03-08 | 2022-07-26 | 重庆交通大学绿色航空技术研究院 | Tail gas recycling system for fixed-wing unmanned aerial vehicle |
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