Aircraft and method for removing ice from the relative windshield or for preventing the formation of ice on the windshield itself

Abstract

An aircraft (1) is described comprising a pilot cockpit (10); a windshield (11) delimiting the cockpit (10); a windscreen wiper (14, 15) comprising a plurality of nozzles (16, 17); a first tank (20) filled with a cleaning fluid and fluidically connected with the nozzles (16, 17); and a control unit (30) programmed to determine a flow of cleaning fluid from the first tank (20) towards the windshield (11) and through the nozzles (16, 17); the aircraft (1) further comprises a second tank (35) filled with an anti-icing / de-icing fluid and fluidically connected with the nozzles (16, 17); the control unit (30) determines a flow of anti-icing / de-icing fluid from the second tank (35) towards the windshield (11) and through the nozzles (16, 17).

Description

[0001] AIRCRAFT AND METHOD FOR REMOVING ICE FROM THE RELATIVE

[0002] WINDSHIELD OR FOR PREVENTING THE FORMATION OF ICE ON THE

[0003] WINDSHIELD ITSELF

[0004] Cross-Reference to Related Applications

[0005] This Patent Appl ication claims priority from European Patent Application No . 24152065. 9 filed on January 16 , 2024 , the entire disclosure of which is incorporated herein by reference .

[0006] Technical Field

[0007] The present invention relates to an aircraft and to a method for removing ice from the relative windshield or for preventing the formation of ice on the windshield itsel f .

[0008] The aircraft comprise in a known manner a fuselage defining a pilot cockpit and a windshield engaging an opening of the fuselage frontally to the pilot cockpit .

[0009] Temperature conditions close to or below zero degrees centigrade favour the formation of ice on the windshield . The visibility for the crew is thus reduced and there is therefore a risk to the flight safety of the aircraft .

[0010] Background of the Invention

[0011] In a known way, the windshields of the aircraft have heating systems , which are adapted to prevent the formation of ice on the windshield or remove the ice already formed on the windshield itsel f . With particular reference to the helicopters , these heating systems introduce optical distortions in the field of vision of the pilot i f the windshield is made of polycarbonate . These heating systems , on the other hand, introduce fragilities of the windshield itsel f i f they are made of glass .

[0012] The need to overcome at least one of the aforesaid drawbacks associated with the windshields of known type speci fied above is therefore felt in the sector .

[0013] Summary of the Invention

[0014] Aim of the present invention is to reali ze a helicopter which allows to satis fy the need speci fied above in a simple and economical way .

[0015] US-A-2004 / 045587 and WQ-A-2007 / 046106 disclose an aircraft according to the preamble of claim 1 and a method for removing ice from or for preventing the formation of ice on a windshield for an aircraft according to the preamble of claim 6 .

[0016] US-A-2019 / 375337 discloses a windshield cleaning assembly for a vehicle includes a wiper that is operationally coupled to a wiper motor of a vehicle . A pipe is coupled to the wiper and extends from proximate to opposing ends of a blade of the wiper . The pipe has a first end that is closed .

[0017] A pump is coupled to the vehicle is operationally coupled to an electrical circuit of the vehicle . A tank is coupled to the vehicle and i s fluidically coupled to the pump . The tank is configured to position a fluid . A tube is fluidically coupled to and extends between the pump and a second end of the pipe . The pump is positioned to selectively pump the fluid from the tank through the tube and the pipe . The fluid exits the pipe under pressure through a plurality of holes to clean the windshield .

[0018] According to the invention, this aim is achieved by an aircraft as claimed in claim 1 or 9 .

[0019] The present invention also relates to a method for removing ice from or for preventing the formation o f ice on a windshield of an aircraft , according to what is claimed in claim 7 or 10 .

[0020] Brief Description of the Drawings

[0021] For a better understanding of the present invention, two preferred non-limiting embodiments are described, by way of example only and with the aid of the accompanying drawings , wherein :

[0022] - Figure 1 is a perspective view of a first embodiment of a helicopter reali zed according to the dictates of the present invention;

[0023] - Figure 2 is a schematic front view of some detail s of the helicopter of Figure 1 ; and - Figure 3 is a schematic front view of some detail s of a helicopter according to a second embodiment of the present invention .

[0024] Description of Embodiments of the Invention

[0025] With reference to Figure 1 , 1 denotes a helicopter .

[0026] The helicopter 1 essentially comprises :

[0027] - a fuselage 2 with a nose 3 arranged anteriorly and a tail 4 opposite the nose 3 ;

[0028] - a pilot cockpit 10 arranged at the nose 3 of the fuselage 2 ; and

[0029] - a windshield 11 engaging an opening 9 of the fuselage 2 arranged anteriorly to the pilot cockpit 10 .

[0030] The windshield 11 is divided into two portions 12 , 13 which are flanked with one another sideways .

[0031] The portions 12 , 13 comprise respective end edges 22 , 23 facing and parallel to each other .

[0032] The helicopter 1 further comprises :

[0033] - a tank 20 filled with a cleaning liquid;

[0034] - a pair of windscreen wipers 14 , 15 provided, each one , with a respective plurality of noz zles 16 , 17 fluidically connected to the tank 20 and which can be commanded to supply the cleaning fluid on the windshield 11 ; and a control unit 30 programmed to fluidically connect the tank 20 and the nozzles 16, 17 or to fluidically isolate the tank 20 and the nozzles 16, 17 from each other.

[0035] In particular, each windscreen wiper 14, 15 is provided to distribute the cleaning liquid on the respective portion 12, 13 of the windshield 11.

[0036] In the case shown, the axes A, B are arranged at respective end edges 22, 23 of the portions 12, 13.

[0037] With reference to Figure 2, each windscreen wiper 14, 15 comprises, in turn:

[0038] - a brush 25 adapted to interact with the relative portion 12, 13 of the windshield; and

[0039] - a distributor 26 protruding cantilevered from the brush 25 and provided with nozzles 16, 17.

[0040] The positions of the nozzles 16, 17 along the respective extension axes C are, in the case shown, optimised according to the geometric characteristics of the windshield 11.

[0041] Advantageously, the helicopter 1 further comprises a tank 35 filled with an anti-icing / de-icing liquid and fluidically connected with the nozzles 16, 17; the control unit 30 is programmed to determine a flow of anti-icing liquid from the tank 35 to the windshield 11 through the nozzles 16, 17.

[0042] In greater detail, the helicopter 1 comprises a circuit

[0043] 50 adapted to selectively supply the anti-icing / de-icing liquid from the tank 35 to the nozzles 16, 17 or the cleaning liquid from the tank 20 to the nozzles 16, 17.

[0044] In greater detail, the circuit 50 comprises, in turn: a pair of conduits 51, 52 fluidically connected respectively with the respective tanks 20, 35;

[0045] - a conduit 55 fluidically connected to both conduits 51, 52 at a junction 56; and

[0046] - a pair of conduits 57, 58 fluidically connected with the conduit 55 at a junction 59 and with the nozzles 16, 17 of respective windscreen wipers 14, 15.

[0047] In particular, the conduits 57, 58 comprise, in turn: respective first portions external to the corresponding windscreen wipers 14, 15 and extending starting from the junction 59; and

[0048] - respective second portions fixed to the respective brushes 25 of corresponding windscreen wipers 14, 15, extending between the respective brushes 25 and the corresponding distributors 26, and ending in the respective nozzles 16, 17 of the corresponding distributors 26.

[0049] The circuit 50 further comprises:

[0050] - a valve 60 interposed along conduit 55; and

[0051] - a pump 65 also interposed along the conduit 55.

[0052] More precisely, the valve 60 and the pump 65 are interposed in sequence along the conduit 55 between the j unctions 56 , 59 .

[0053] The control unit 30 controls the valve 60 so as to selectively shi ft it : a first operating configuration wherein it fluidically connects the conduit 55 and the tank 20 full of cleaning liquid, and it fluidically isolates the conduit 55 and the tank 35 full of anti-icing / de-icing liquid; a second configuration wherein it fluidically isolates the conduit 55 and the tank 20 full o f cleaning fluid, and it fluidically connects the conduit 55 and the tank 35 full of anti-icing / de-icing fluid; and a third operating configuration wherein it fluidically isolates both the tank 20 and the tank 35 from the conduit 55 .

[0054] In particular, in the first operating configuration of the valve 60 , the noz zles 16 , 17 ej ect the cleaning liquid onto the windshield 11 .

[0055] In the second operating configuration of the valve 60 , the windscreen wipers 14 , 15 ej ect via the noz zles 16 , 17 the anti-icing / de-icing liquid onto the windshield 11 .

[0056] In the third operating configuration of the valve 60 , the windscreen wipers 14 , 15 do not ej ect either the cleaning liquid or the anti-icing / de-icing liquid onto the windshield 11 . The pump 65 can be commanded to cause the advancement of the anti-icing / de-icing liquid present within the conduit 55 .

[0057] The helicopter 1 further comprises a sensor 85 adapted to detect the presence of ice on the windshield 11 and / or to measure the temperature outside the helicopter 1 , and to generate a signal in the event that ice is detected on the windshield 11 and / or the temperature outside the helicopter 1 is lower than a threshold value .

[0058] The control unit 30 is functionally connected with the sensor 85 and is programmed to shi ft the valve 60 into the second operating configuration when the sensor 85 generates the signal .

[0059] With reference to figure 2 , helicopter 1 further comprises a heating system 80 , which can be commanded by the control unit 30 to heat the windscreen wipers 14 , 15 and the noz zles 16 , 17 and prevent their blocking .

[0060] Heating system 80 comprises , in turn :

[0061] - a power electric generator 87 ;

[0062] - a power electric distributor 86 operatively connected to power electric generator 87 and control unit 30 ; and

[0063] - a plurality of electric resistances 88 embedded inside noz zles 16 , 17 and conduits 57 , 58 , and operatively connected to power electric distributor 86 . Control unit 30 i s programmed to control power electric distributor 86 , so as to cause the flow of electric current through electric resistances 88 , thus heating noz zles 16 , 17 and conduits 57 , 58 and prevent the obstruction thereof .

[0064] It is important to notice that heating system 30 is aimed only to prevent the blocking of noz zles 16 , 17 and conduits 57 , 58 and substantially neither prevents the blocking of wipers 14 , 15 nor clean windshield 11 .

[0065] The operation of the helicopter 1 is described below starting from a condition wherein the control unit 30 places the valve 60 in the third configuration .

[0066] In such a condition, the noz zles 16 , 17 are fluidically isolated from the tanks 20 , 35 . Consequently, the noz zles 16 , 17 do not supply either the cleaning liquid or the anti- icing / de-icing liquid onto the windshield 11 .

[0067] In case it is wished to clean the windshield 11 , the crew operates a special command (not shown) of the pilot cockpit 10 .

[0068] The control unit 30 receives such a command in input and shi fts the valve 60 into the first configuration, wherein the cleaning liquid tank 20 is f luidically connected with the conduit 55 , and the conduit 55 is fluidically isolated from the tank 35 full of anti-icing / de-icing liquid .

[0069] The pump 65 causes the advancement of the cleaning liquid along the conduits 51, 55 and 57, 58 up to the nozzles 16, 17. The nozzles 16, 17 eject the cleaning liquid onto the windshield 11, causing the cleaning thereof.

[0070] Optionally, the crew operates the windscreen wipers 14, 15 to cause the rotation thereof around the relative axes A, B so as to evenly distribute the cleaning liquid on the windshield 11.

[0071] If the sensor 85 generates the signal associated with the presence of ice on the windshield 11 and / or the fact that the temperature outside the helicopter is lower than a threshold value or in case the crew operates a special further command of the pilot cockpit 10, the control unit 30 shifts the valve 60 into the second operating configuration.

[0072] The valve 60 in the second operating configuration fluidically isolates the conduit 55 from the tank 20 full of cleaning fluid, and it fluidically connects the conduit 55 and the tank 35 full of anti-icing / de-icing liquid.

[0073] The pump 65 causes the advancement of the cleaning liquid along the conduits 52, 55 and 57, 58 up to the nozzles 16, 17. The nozzles 16, 17 eject the anti-icing / de-icing liquid onto the windshield 11. The ice is thus removed from the windshield 11 and / or its formation is prevented.

[0074] Also in this case, the crew optionally operates the windscreen wipers 14, 15, to cause the rotation thereof around the relative axes A, B so as to evenly distribute the anti-icing / de-icing liquid on the windshield 11.

[0075] The control unit 30 preferably also commands the heating system 80 so as to heat the windscreen wipers 14, 15 and the nozzles 16, 17 and prevent their blocking.

[0076] In detail, control unit 30 controls power electric distributor 86, so as to cause the flow of electric current through electric resistances 88, thus heating nozzles 16, 17 and conduits 57, 58 and prevent the obstruction thereof.

[0077] Referring to Figure 3, 1' denotes a helicopter according to a second embodiment of the present invention.

[0078] Helicopter 1' is similar to the helicopter 1 and will be described hereinafter only for what differs from the latter; equal or equivalent parts of the helicopter 1, 1' will be marked, where possible, with the same reference numbers .

[0079] Helicopter 1' is similar to helicopter 1 and is hereinafter described only insofar as it differs from it.

[0080] In particular, helicopter 1' differs from helicopter 1 in that it comprises:

[0081] - a single tank 20 filled with anti-icing / deicing fluid only and fluidically connected with nozzles 16, 17; and

[0082] - a control unit 30 programmed to control pump 65 and to determine a flow of the anti-icing / deicing fluid from tank 20 towards windshield 11 and through said nozzles 16, 17, when sensor 85 generates the signal associated with the presence of ice on the windshield 11 and / or the fact that the temperature outside the helicopter is lower than a threshold value or in case the crew operates a special further command of the pilot cockpit 10.

[0083] Helicopter 1' differs from helicopter 1 for not comprising tank 35, conduit 52, junction 56 and valve 60.

[0084] The operation of helicopter 1' is described hereinafter only for what differs from the operation of helicopter 1.

[0085] In particular, in case it is wished to clean the windshield 11, the crew operates the special command (not shown) of the pilot cockpit 10.

[0086] The control unit 30 receives such a command in input and operates pump 65. Pump 65 determines the advancement of the anti-icing / deicing fluid from tank 20 along the conduits 51' , 55 and 57, 58 up to the nozzles 16, 17. The nozzles 16, 17 eject anti-icing / deicing fluid onto the windshield 11, causing both the cleaning thereof and the removal of ice from windshield 11 and / or the prevention of its formation.

[0087] In a similar way, if the sensor 85 generates the signal associated with the presence of ice on the windshield 11 and / or the fact that the temperature outside the helicopter is lower than a threshold value or in case the crew operates a special further command of the pilot cockpit 10 , the control unit 30 operates pump 65 . Accordingly, pump 65 causes advancement of the anti-icing / deicing fluid from tank 20 along the conduits 51 ' , 55 and 57 , 58 up to the noz zles 16 , 17 .

[0088] From an examination of the helicopter 1 , 1 ' according to the present invention, the advantages that it allows obtaining are evident .

[0089] In particular, the tank 35 of helicopter 1 filled with anti-icing / de-icing liquid is fluidically connected with the same noz zles 16 , 17 to which the tank 20 filled with the cleaning liquid is connected .

[0090] It is thus possible to use the same noz zles 16 , 17 and also the same conduit 55 of the hydraulic circuit 50 to channel both the cleaning liquid and the anti-icing / de-icing fluid on the windshield 11 .

[0091] In this way, it is possible to ensure the correct visibility to the crew, reducing the need for additional dedicated devices with respect to the windscreen wipers 14 , 15 and the noz zles 16 , 17 already present in the helicopter 1 , unlike the solutions based on the heating of the windshield 11 of known type and discussed in the introductory part of the present description .

[0092] Moreover, it is possible to use the already normally provided movement of the windscreen wipers 14 , 15 on the windshield 11 to evenly distribute the cleaning liquid on the windshield 11 itsel f .

[0093] Thanks to the fact that the anti -icing / de-icing liquid is ej ected by the noz zles 16 , 17 , it is possible to apply the solution according to the invention to a windshield 11 also made of polycarbonate and without introducing optical distortions in the field of vision of the pilot .

[0094] Moreover, the windscreen wipers 14 , 15 are not only ef fective in distributing the anti-icing / de-icing liquid on the windshield 11 , but they also remove the residues of melted ice and of the aforesaid liquid from the windshield 11 itsel f .

[0095] By providing the noz zles 16 , 17 according to predetermined geometries , it is furthermore possible to :

[0096] - improve the distribution of the anti-icing / de- icing liquid on the windshield 11 ; and / or

[0097] - increase the amount of the surface of the windshield 11 protected from ice formation and / or from which the ice can be removed .

[0098] Heating system 80 allows to prevent the formation of ice and / or to remove ice also from the windscreen wiper 13 , 14 and from the relative movement structures , raising the final safety of the helicopter 1 . Helicopter 1' comprises a single tank 20 filled with anti-icing / deicing fluid only and fluidically connected with nozzles 16, 17.

[0099] In this way, anti-icing / deicing fluid is used for both cleaning windshield 11 and preventing the formation of ice on windshield 11, thus reducing the number of components required and the overall weight oh helicopter 1.

[0100] Furthermore, helicopter 1' does not require any heating system, due to the fact there is not any water mixture inside tank 30' and flowing along conduits 51, 57, 58 and through nozzles 16, 17, and due to the fact anti-icing / deicing fluid prevents the formation of ice inside conduits 51, 57, 58 and nozzles 16, 17.

[0101] It is clear that the helicopter 1, 1' and the method described and shown herein may be subject to modifications and variations without thereby departing from the scope of protection defined by the claims.

[0102] In particular, the helicopter 1 could be an airplane, a convertiplane or another type of aircraft.

[0103] The cleaning liquid and / or the anti-icing / de-icing liquid could be replaced respectively by a cleaning fluid and / or by an anti-icing / de-icing fluid.

Claims

CLAIMS1.- Aircraft (1) comprising:- a pilot cockpit (10) ;- a windshield (11) delimiting said cockpit (10) ;- at least one windscreen wiper (14, 15) comprising a plurality of nozzles (16, 17) ;- a first tank (20) filled with a cleaning fluid and fluidically connected with said nozzles (16, 17) ; and- a control unit (30) programmed to determine, in use, a flow of said cleaning fluid from said first tank (20) towards said windshield (11) and through said nozzles (16, 17) ;- a second tank (35) filled with an anti-icing / de- icing fluid and fluidically connected with said nozzles (16, 17) ; said control unit (30) being programmed to determine, in use, a flow of said anti-icing / de-icing fluid from said second tank (35) towards said windshield (11) and through said nozzles (16, 17) ; said aircraft (1) further comprising:- a first and a second conduit (51, 52) fluidically connected respectively with said first tank (20) and said second tank (35) ;- a third conduit (55) fluidically connected withsaid nozzles (16, 17) ; and- a valve (60) controllable by said control unit (30) and selectively shiftable between: a first operating configuration wherein it fluidically connects said first and third conduit (51, 55) , and fluidically isolates said second and third conduit (52, 55) ; and a second operating configuration wherein it fluidically connects said second and third conduit (52, 55) , and it fluidically isolates said first and third conduit (51, 55) ; characterized in that it comprises a sensor (85) adapted to detect to generate a signal associated to the presence of ice on said windshield (11) and / or in that the temperature of the surrounding environment is lower than a threshold value; said control unit (30) being operatively connected with said valve (60) and said sensor (85) , and being programmed to shift said valve (60) from said first configuration to said second configuration, when said sensor (85) generates said signal; said aircraft being further characterized in that it comprises a heating system (80) , which can be commanded by said control unit (30) to supply heat against saidwindscreen wipers (14, 15) and said nozzles (16, 17) and prevent their blocking.2.- Aircraft according to claim 1, characterized in that said heating system (80) comprises, in turn:- a power electric generator (87) ; a power electric distributor (86) operatively connected to power electric generator (87) and said control unit (30) ; and- a plurality of electric resistances (88) embedded inside said nozzles (16, 17) and said first, second and third conduits (57, 58) , and operatively connected to said power electric distributor (86) .3.- Aircraft according to claim 1 or 2, characterized in that it comprises a pump (65) interposed along said third conduit (55) and which can be commanded to cause the advancement of said cleaning fluid or anti-icing / de- icing fluid present, in use, in said third conduit (55) .4.- Aircraft according to claim 3, characterized in that it comprises:- at least two said windscreen wipers (14, 15) ;- at least two fourth conduits (57, 58) fluidically connected, each one, to a respective said windscreen wiper (14, 15) , and fluidically connected to said third conduit(55) ;said valve (60) and said pump (65) being arranged in sequence along said third conduit (55) in a position interposed between said first and second conduit (51, 52) , and said fourth conduits (57, 58) .5.- Aircraft according to any one of the preceding claims, characterized in that said windshield (11) comprises a first and a second portion (12, 13) ; each windscreen wiper (14, 15) being hinged to said windshield (11) around a relative axis (A, B) so as to be movable on a relative first or second portion (12, 13) of said windshield (11) .6.- Aircraft according to any one of the preceding claims, characterized in that it is a helicopter.7 Method for removing ice from or for preventing the formation of ice on a windshield (11) of an aircraft (1) ; said aircraft (1) comprising:- a pilot cockpit (10) ;- a windshield (11) delimiting said cockpit (10) ;- at least one windscreen wiper (14, 15) comprising a plurality of nozzles (16, 17) ; and- a first tank (20) filled with a cleaning fluid and fluidically connected with said nozzles (16, 17) ; said method comprising steps: i) of channelling a flow of said cleaning fluidfrom said first tank (20) towards said windscreen (11) and through said nozzles (16, 17) ; ii) of channelling a flow of anti-icing / de-icing fluid from a second tank (35) towards said windscreen (11) and through said nozzles (16, 17) ; iii) shifting a valve (60) between: a first operating configuration wherein it fluidically connects a first conduit (51) connected to said first tank (20) and a second conduit (55) fluidically connected to said nozzles (16, 17) , and it fluidically isolates a third conduit (52) connected to said tank (35) and said second conduit (55) ; and a second operating configuration wherein it fluidically isolates said first and second conduit (51, 55) , and it fluidically connects said third and second conduit (52, 55) ; characterized in that it comprises the steps of: iv) generating a signal associated with the presence of ice on said windshield (11) and / or the temperature of the environment surrounding said aircraft (1) is lower than a threshold value; v) shifting said valve (60) from said first configuration to said second configuration, when said signal is generated; andvi) heating said windscreen wipers (14, 15) and said nozzles (16, 17) and prevent their blocking.8.- The method of claim 7, characterized in that said step vi) comprises, in turn, the steps of: vii) generating electric power; viii) distributing said electric power to electric resistances (88) embedded inside said nozzles (16, 17) and said first, second and third conduits (57, 58) .9.- Aircraft (1' ) comprising:- a pilot cockpit (10) ;- a windshield (11) delimiting said cockpit (10) ;- at least one windscreen wiper (14, 15) comprising a plurality of nozzles (16, 17) ;- a sensor (85) adapted to detect to generate a signal associated to the presence of ice on said windshield (11) and / or in that the temperature of the surrounding environment is lower than a threshold value; characterized by comprising:- a single tank (20) filled with anti-icing / deicing fluid only and fluidically connected with said nozzles (16, 17) ;- a fluidic line (51' , 55, 57, 58) , which fluidly connects said tank (20' ) and said nozzles (16, 17) ;- a pump (65) interposed along said fluidic line( 51 ' , 55, 57, 58) , and which can be commanded to cause the advancement of said anti-icing / deicing fluid only through said conduit (55) ; a control unit (30) programmed to control said pump (65) and to determine, in use, a flow of said anti- icing / deicing fluid only from said tank (20) towards said windshield (11) and through said nozzles (16, 17) .10.- A method for removing ice from or for preventing the formation of ice on a windshield (11) of an aircraft ( 1 ' ) ; said aircraft (1' ) comprising:- a pilot cockpit (10) ;- a windshield (11) delimiting said cockpit (10) ;- at least one windscreen wiper (14, 15) comprising a plurality of nozzles (16, 17) ; characterized by comprising the steps of: i) generating a signal associated with the presence of ice on said windshield (11) and / or the temperature of the environment surrounding said aircraft (1) is lower than a threshold value; ii) channelling a flow of anti-icing / de-icing fluid only from said a single tank (20) towards said windscreen (11) and through said nozzles (16, 17) , when said signal is generated.

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