HYDROFOIL WATERCRAFT

Abstract

Disclosed is a fuselage assembly (100) configured to be attached to a mast assembly (50) of a powered hydrofoil watercraft (1). The fuselage assembly (100) comprises a mast assembly fixation section (106) and an outer housing portion (170) which accommodates, in particular surrounds or encases, a propulsion device (200), in particular an impeller (201), and which outer housing portion (170) at least partially limits an outer dimension of a flow channel (161) through which water is transported during operation of the hydrofoil watercraft (1). The outer housing portion (170) comprises an attachment portion (310) on which a tail unit (300), in particular 10 comprising a stabilizing member (301) such as a stabilizing wing (302), is formed or attachable thereto. In addition or alternatively, the propulsion device (200) may be accommodated in the outer housing portion (170) such that a user is prevented from touching the propulsion device (200).

Claims

1. A fuselage assembly (100) configured to be attached to a mast assembly (50) of a powered hydrofoil watercraft (1), wherein said fuselage assembly (100) comprises a mast assembly fixation section (106) and an outer housing portion (170) which accommodates a propulsion device (200), and which outer housing portion (170) at least partially limits an outer dimension of a flow channel (161) through which water is transported during operation of said hydrofoil watercraft (1), wherein said flow channel (161) is formed such that its cross sectional area is reduced towards an outlet side of said flow channel (161), and wherein (I) said outer housing portion (170) comprises an attachment portion (310) on which a tail unit (300), is formed or attachable thereto and/or wherein (II) said propulsion device (200) is accommodated in said outer housing portion (170) such that a user is prevented from touching said propulsion device (200).

2. The fuselage assembly (100) according to claim 1, wherein said outer housing portion (170) is configured for detachably fixing said tail unit (300) to the same, or wherein alternatively said outer housing portion (170) and said tail unit (300) are integrally formed.

3. The fuselage assembly (100) according to claim 1, further comprising a wing attachment section (105) and a front wing (112) attached to said wing attachment section (105), wherein said wing attachment section (105) is provided at a front portion (101) of said fuselage assembly (100) and is configured to detachably mount said front wing (112).

4. The fuselage assembly (100) according to claim 3, wherein said tail unit (300) and/or said front wing (112) mounted on said fuselage assembly (100) are configured to be transferable between a use state in which said tail unit (300) is able to exert a stabilizing function and/or said front wing (112) is positioned to generate a lifting force, and a stowing state, wherein in said stowing state a mast assembly profile and a profile of said tail unit (300) and/or of said front wing (112) are arranged substantially in one plane, wherein said tail unit (300) and/or said front wing (112) are rotatable about a rotational axis, for example a longitudinal middle axis (A1) of said fuselage assembly (110) or an axis parallel to said longitudinal middle axis (A1), such that said tail unit (300) and/or said front wing (112) are rotatable about 90 between said use state and said stowing state.

5. The fuselage assembly (100) according to claim 1, wherein said outer housing portion (170) comprises an upstream end portion (177) defining an inlet opening (178) and wherein said housing portion (170) comprises a downstream end portion (179) which comprises a nozzle section (172) with an outlet opening (191), wherein a cross sectional area of said inlet opening (178) is larger than a cross sectional area of said outlet opening (191), wherein said cross sectional area at said outlet opening (191) is at least 5% smaller than said cross sectional opening of said inlet opening (178) and wherein said cross sectional area at said outlet opening (191) is 90% to 80% the size of said cross sectional area of said inlet opening (178), wherein in addition or alternatively said nozzle section (172) is detachably configured and is made from a plastics material.

6. The fuselage assembly (100) according to claim 5, wherein said outer housing portion (170) and said propulsion device (200) accommodated therein are configured and arranged with respect to each other such that it is not possible to reach said propulsion device (200) with a human extremity, wherein a length of said outer housing portion (170) and/or the size of said inlet opening (178) and/or the size of said outlet opening (191) and/or the position of said propulsion device (200) in said outer housing portion (170) and/or a dimension of said flow channel (161) are adjusted and/or positioned such that said propulsion device (200) cannot be reached by means of a human extremity through said inlet opening (178) and said outlet opening (191) and/or wherein a safety member is provided which blocks an access for human extremities, wherein said safety member is provided downstream or upstream of said propulsion device (200) and is a stator (174), and wherein in addition or alternatively said length of said flow channel (161) between said inlet opening (178) and said propulsion device (200) is at least 30 mm and/or wherein in addition or alternatively a height or width of said inlet opening (178) is equal to or smaller than 30 mm, and/or wherein in addition or alternatively a length of said stator (174) in flow direction of said flow channel (161) is equal to or larger than 5 mm and/or wherein in addition or alternatively said size of said outlet opening is equal to or smaller than 30 mm.

7. The fuselage assembly (100) according to claim 5, wherein said flow channel (161) is formed between said outer housing portion (170) and an inner housing portion (180) which is suitable for supporting said propulsion device (200), and/or wherein said flow channel (161) is formed as a ring channel extending about said longitudinal middle axis (A1) and circumferentially surrounding said inner housing portion (180) with its cross section in a direction perpendicular to said longitudinal middle axis (A1) defining a ring and/or wherein said inlet opening (178) is formed between said upstream end portion (177) and an outer surface section (181) of said inner housing portion (180), and/or wherein said inlet opening (178) is formed as an annular inlet opening or an elliptical inlet opening, and/or wherein said flow channel (161) is configured such that an inlet angle (184) smaller than 20 is realized at said inlet opening (178).

8. The fuselage assembly (100) according to claim 5, wherein said outer housing portion (170) is connected to said inner housing portion (180) via circumferentially distributed struts (190) arranged around said longitudinal middle axis (A1) so that said outer housing portion (170) is held cantilevered on said inner housing portion (180), said struts (190) at least partially extending in the longitudinal direction of said fuselage assembly (110) and bridging said inlet opening (178), wherein said struts (190) are aerodynamically formed so as to reduce turbulences and comprise a wing shape.

9. The fuselage assembly (100) according to claim 8, wherein at least a portion of said outer housing portion (170), and said rear end portion (183) of said inner housing portion (180) are fixedly coupled to each other, thereby defining a propulsion section (160) of said fuselage assembly (100), and wherein in addition or alternatively said propulsion section (160) is detachably coupled to a front portion (101) of said fuselage assembly (100).

10. The fuselage assembly (100) according to claim 5, further comprising a flap mechanism for selectively opening and closing said inlet opening (178), wherein said flap mechanism is designed such that a negative pressure generated by said propulsion device (200) automatically actuates said flap mechanism, wherein said flap mechanism comprises one or more flaps which are pre-biased in the closing direction, and which flaps are moved into an opened position against the pre-biasing force when there is a corresponding negative pressure and are automatically moved into a closed position driven by the pre-biasing force when there is no sufficiently large negative pressure.

11. The fuselage assembly (100) according to claim 1, further comprising a front portion (101) adapted to sealingly receive an electric motor, wherein said electric motor is thermally coupled to a casing (110) of said front portion (101) for cooling purposes, wherein optionally a motor housing of said electric motor also forms a part of said casing (110) of said front portion (101) in such a manner that said motor housing gets in contact with water on its outer side, such that a direct cooling of said electric motor is possible.

12. The fuselage assembly (100) according to claim 11, wherein said front portion (101) is further adapted to receive a controller couplable to said electric motor, said controller being thermally coupled to said casing (110) of said front portion (101) for cooling purposes, wherein said front portion (101) optionally comprises a controller receiving space separated and sealed from an electric motor receiving space.

13. The fuselage assembly (100) according to claim 1, wherein said mast assembly fixation section (106) bels provided on a top side of said fuselage assembly (110), wherein in addition or alternatively said mast assembly fixation section (106) comprises a mounting recess (107) in which a fuselage assembly fixation portion (54) of said mast assembly (50) can be inserted and locked, wherein said mast assembly fixation section (106) is designed for a positive locking or an integral connection of said mast assembly (50) with said mast assembly fixation section (106).

14. An integrated propulsion unit for a powered hydrofoil watercraft, comprising the fuselage assembly (100) according to claim 1, an electric motor provided in said fuselage assembly (110) and a propulsion device (200) provided in said outer housing portion (170), said electric motor being operatively connected to said propulsion device (200) by means of a drive shaft (203) accommodated in said inner housing portion (180), or wherein said propulsion device (200) is directly coupled to an output shaft of said electric motor.

15. A hydrofoil watercraft (1), comprising a board assembly (10), a mast assembly (50) coupled to a lower portion (12) of said board assembly (10), and the integrated propulsion unit according to claim 14, wherein a front wing (112) and the tail unit (300) are attached to said fuselage assembly (100) of said integrated propulsion unit.

16. The fuselage assembly of claim 2, wherein said detachable fixation is achieved by means of positive locking, and wherein said outer housing portion (170) comprises an attachment portion (310) for detachably attaching said tail unit (300).

17. The fuselage assembly of claim 16, wherein the positive locking is a latching plug and socket connection having a dovetail geometry or being realized by pins.

18. The fuselage assembly of claim 16, wherein the tail unit comprises an attachment flange having a threaded opening.

19. The fuselage assembly of claim 4, wherein said wing attachment section (105) and/or said attachment portion (310) are individually rotatable about said rotational axis or wherein said mast assembly fixation section (106) is configured such that said fuselage assembly is rotatably coupled to said mast assembly (50).

20. The fuselage assembly of claim 1, wherein the tail unit a stabilizing member (301) optionally wherein the stabilizing member is a stabilizing wing (302).

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0065] The present invention will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements.

[0066] FIG. 1 shows a perspective view of a hydrofoil watercraft according to an embodiment.

[0067] FIG. 2 shows a perspective view of an integrated hydrofoil assembly according to an embodiment.

[0068] FIG. 3 shows a bottom view of the integrated hydrofoil assembly of FIG. 2.

[0069] FIG. 4 shows a perspective rearview of a rear portion of the integrated hydrofoil assembly according to FIGS. 2 and 3.

[0070] FIG. 5 shows a perspective view of a hull/fuselage of the integrated hydrofoil assembly according to FIGS. 2 to 4.

[0071] FIG. 6 shows a sectional view of the rear portion of the integrated hydrofoil assembly according to an embodiment.

[0072] FIG. 7 shows a sectional view of an aerodynamically formed coupling member according to an embodiment.

[0073] FIGS. 8 and 9 show a further embodiment of a fuselage assembly.

[0074] FIG. 10 shows a hydrofoil watercraft according to a further embodiment.

[0075] FIG. 11 shows possible modifications and embodiments of a hydrofoil watercraft according to further aspects.

[0076] All figures are only schematic depictions of exemplary embodiments in which, in particular, distances and dimensional correlations are not presented to scale.

DETAILED DESCRIPTION OF EMBODIMENTS

[0077] The following detailed description is merely exemplary in nature and is not intended to limit application and uses. Furthermore, there is no intention to be bound by any theory presented in the preceding background or summary or the following detailed description.

[0078] FIG. 1 shows a perspective view of a hydrofoil watercraft 1 according to an embodiment. The hydrofoil watercraft 1 comprises a board assembly 10, a mast assembly 50 and a fuselage assembly 100 coupled to the mast assembly 50.

[0079] The board assembly 10 comprises a hull 11 which is designed to float on water. For that, the hull 11 comprises a lower portion 12 which is specifically designed to contact water and comprises an upper portion 13 which is configured to support a user. The upper portion may comprise a support surface 14 which allows the user to lie prone, sit, kneel or stand on the board assembly 10 when riding the hydrofoil watercraft 1. In the support surface 14, and access panel 15 is detachably provided. The access panel 15 covers an access opening to an interior space of the board assembly 10. The access panel 15 is coupled to the hull 11 in a watertight manner so as to seal the interior space against an intrusion of water. Although not shown in the drawings, the interior space may accommodate electric components such as a power supply, for example an accumulator. Furthermore, a control unit powered by the accumulator and comprising a wireless receiving unit may be provided. The control unit and/or the power supply may be coupled to the fuselage assembly 100 to supply power and/or control signals to the fuselage assembly, in particular to drive an electric motor arranged in the fuselage assembly 100.

[0080] On the lower portion 12 of the hull 11, the mast assembly 50 is fixedly coupled to the board assembly 10. In an embodiment, the mast assembly 50 is detachably fixed to the board assembly 10 in order to allow a space saving stowing of the hydrofoil watercraft 1. For that, the mast assembly 50 may comprise a board assembly fixation portion 51. The board assembly fixation portion 52 is configured to cooperate with a mast assembly coupling portion (not shown) provided on the lower portion 12 of the hull 11. The board assembly fixation portion 52 may comprise a fastening flange which is integrated into the hull 11. The board assembly fixation portion 52 may comprise an insertion portion or protrusion. The mast assembly coupling portion on the board assembly 10 may comprise a mounting recess for receiving the board assembly fixation portion 52. Accordingly, the board assembly fixation portion 52 may be inserted into the mounting recess provided in the lower portion 12 of the hull 11 of the board assembly 10 in order to couple the mast assembly 50 to the board assembly 10. The board assembly fixation portion 52 may be configured to be coupled to the board assembly 10 by means of positive locking. For example, the board assembly fixation portion 52 and the board assembly 10 may be configured to be screwed to each other. For that, the mast assembly coupling portion of the board assembly 10 may comprise a fixation flange which provides a suitable support for fastening devices such as screws.

[0081] The mast assembly 50 further comprises a fuselage assembly fixation portion 54. According to an embodiment, the fuselage assembly fixation portion 54 may be configured to cooperate with a mast assembly coupling portion 106 provided on the fuselage assembly 100. The mast assembly coupling portion 106 may comprise a mounting recess 107 and may be configured to accommodate the fuselage assembly fixation portion 54 therein. According to the embodiment, the mounting recess 107 is provided in an upper portion of the fuselage assembly 100 so that according to the embodiment, the fuselage assembly 100 is coupled to one end portion 53 of the mast assembly 50. Accordingly, the fuselage assembly 100 may be coupled to one end portion 53 of the mast assembly 50 and the board assembly 10 may be coupled to the mast assembly 50 at the other opposite end portion 51 of the mast assembly 50. The fuselage assembly 100 is thus coupled to the board assembly 10 by means of the mast assembly 50.

[0082] The fuselage assembly 100 according to the exemplary embodiment comprises a front portion 101 and a rear portion 140. The rear portion 140 is detachably coupled to the front portion 101. In some embodiments, the rear portion 140 may be fixedly coupled to the front portion 101 and may in particular be non-detachably coupled to the front portion.

[0083] The front portion 101 comprises a front section 102, a middle section 103 and a rear section 104. The front section comprises a wing attachment section 105, the middle section 103 comprises a mast assembly fixation section 106 and the rear section 104 comprises a coupling section 108 for coupling the rear portion 140 to the front portion 101. The front portion 101 may further comprise an accommodating section 109 for internally accommodating further elements such as elements of a drive unit and/or elements of a power supply. The accommodating section 109 may in addition or alternatively be configured to accommodate a portion of the rear portion 140 therein. The front portion 101 may comprise a hull or casing 110. The casing 110 may be formed as a single part and may be aerodynamically formed with a tip end portion at the front section 102. In the middle section 103 and the rear section 104, the casing 110 may be formed tubular, for example hollow cylindrical and/or elliptical. But in general, other shapes and configurations are possible including for example a configuration in which the shape of an outer circumference of the casing differs from the shape of an inner circumference of the casing. For example, the outer circumference may be shaped triangular, in particular with rounded corners, and the inner circumference of the casing may be formed rounded, for example circular.

[0084] The wing attachment section 105 may be formed by a recess provided in the front section 102 so that it is possible to at least partially accommodate a wing 112, in particular a front wing, therein. In this way, it may be prevented that the wing 112 fully protrudes from the casing so that the application of such a wing 112 does not considerably enlarge an outer dimension, for example a height dimension of the fuselage assembly, for instance. In the rear section 104, openings 111 may be provided in the casing 110. The openings 111 may be provided for coupling purposes, for example for the insertion and accommodation of fastening members 150 for coupling the rear portion 140 of the fuselage assembly 100 to the front portion 101 of the fuselage assembly 100. Accordingly, as is shown in the Figures, the fuselage assembly may comprise a two-part construction in which the rear portion 140 and the front portion 101 are detachably couplable to each other.

[0085] The mast assembly fixation section 106 is configured to couple the mast assembly to the fuselage assembly 100. The mast assembly fixation section 106 may comprise a mounting recess 107 for receiving at least a portion of fuselage assembly fixation portion 54 of the mast assembly 50.

[0086] The wing 112 is detachably mountable to the wing attachment section 105 and is configured to generate a lifting force during movement of the hydrofoil watercraft 1 in water. As already indicated before, the wing 112 according to the embodiment may also be referred to as front wing as according to the exemplary embodiment, the wing 112 is provided at the front section 102 of the fuselage assembly 100. The wing 112 may comprise different shapes and sizes depending on the characteristics that are to be achieved. For example, the wing 112 may comprise a shape that generates a high lifting force already at low speeds or may comprise a shape that needs a higher speed for generating a desired lifting force.

[0087] The rear portion 140 comprises a coupling section 141 configured to couple the rear portion 140 to the front portion 101. The coupling section 141 comprises a coupling flange 142 adapted to be coupled to the coupling section 108 of the front portion 101 of the fuselage assembly 100. The coupling flange may comprise a cylindrical portion 143 with an outer circumferential surface 144. The outer circumferential surface 144 may be dimensioned according to an inner circumferential surface in the coupling section 108. Both circumferential surfaces may be provided parallel with respect to each other and may be arranged to extend parallel with respect to a longitudinal middle axis A1 of the fuselage assembly 100. In particular, the outer diameter of the outer circumferential surface 144 may correspond to the inner diameter of the inner circumferential surface. Engaging portions 145 for fastening members may be provided in the coupling flange 142, for example equidistantly about the longitudinal middle axis A1. For example, the engaging portions 145 may be threaded openings suitable for receiving threaded fastening members such as screws which may be used for coupling the front portion 101 and the rear portion 140 by inserting them through the openings 111 and screwing them into the threaded openings 145.

[0088] The coupling section 141 may further comprise an accommodating section 146 which is configured to be accommodated in the front portion 101 of the fuselage assembly 100. The accommodating section 146 may be formed hollow cylindrical with an accommodating space 147 suitable for receiving an element of a drive train, for example a coupling member for coupling an electric motor to a drive shaft. The accommodating section 146 is arranged on and extends from one side of the coupling flange 142. At a free end of the accommodating section 146, a fixation flange 148 is provided which according to the embodiment, provides an annular fixation surface that may extend about the longitudinal middle axis A1 and in a plane which is perpendicular to the longitudinal middle axis A1. The fixation flange 148 provides a support for a drive member such as an electric motor, in particular in such a manner that the drive member can be mounted on an outer side of the accommodating section 146. For that, the fixation flange 148 may comprise fixation openings 149 arranged on the fixation flange 148. In some embodiments, the accommodating section 146 may be omitted. The electric motor may be arranged in and fixed on the front portion 101 of the fuselage assembly 100 so that there needs to be no fixation option such as the above mentioned fixation flange 148 for mounting the electric motor on the coupling section. For example, the electric motor may be pressed into the front portion 101.

[0089] In addition to the above or alternatively, the rear portion 140 may comprise a propulsion section 160. The propulsion section 160 may extend from the above coupling flange 142 on one axial side so that it extends along the longitudinal middle axis A1, for example on the side of the coupling flange which is opposite to the side where the accommodating section 146 is provided.

[0090] The propulsion section 160 may define a flow channel 161 for water, in which water may be accelerated to create a propulsive force. The flow channel 161 may be configured ring-like, in particular with an annular or elliptical inlet and such that water flows therethrough as indicated in FIG. 6 by dashed arrows. The propulsion section 160 may comprise an inlet section 162, an intermediate section 163 and an outlet section 164. The inlet section 162 may be designed such that a radial entry of water into the propulsion section 160 is possible. According to the present disclosure, radial entry is to be understood as a direction in which the flow of water is at least partially directed cross or inclined to the longitudinal middle axis A1 of the fuselage assembly 100, at least upon entering the flow channel 161, and, thus, has a directional component in radial direction, more precisely towards the longitudinal middle axis A1. However, it is also possible to provide an inlet section which is designed such that an axial entry of water into the propulsion section is possible. For example, the ring-like flow channel may be configured such that a radial outer wall and/or a radial inner wall extends or extend in parallel with the longitudinal middle axis, at least at the inlet section. Accordingly, water entering such a flow channel flows in parallel to the longitudinal middle axis, at least at the inlet section.

[0091] The flow channel 161 may be defined between an outer housing portion 170 and an inner housing portion 180.

[0092] The outer housing portion 170 may be defined by a propulsion device accommodating section 171 and a nozzle section 172. The propulsion device accommodating section 171 is configured to accommodate a propulsion device 200, for example to surround or to encase the propulsion device 200. The propulsion device accommodating section 171 may comprise the shape of a hollow rotation body, for example tubular or similar to a hollow cylindrical section with the difference that the inner wall surface and/or the outer surface of the hollow body may at least partially extend inclined with respect to a middle axis and/or may at least partially be curved in longitudinal direction and non-straight.

[0093] The inner housing portion 180 may be at least partially arranged coaxially within the outer housing portion 170. Accordingly, the flow channel 161 may be formed between an outer surface section 181 of the inner housing portion 180 and an inner surface section 173 of the outer housing portion 170. According to the embodiment, an inlet opening 178 is defined between an upstream end portion of the outer housing portion 180 and the outer surface section 181 of the inner housing portion 180. In other words, the inner housing portion 180 is arranged such that a portion of the outer housing portion 170 and a portion of the inner housing portion 180 overlap each other in longitudinal direction (x-direction in the drawings) of the fuselage assembly 100 thereby forming a portion of the flow channel 161 between them.

[0094] The inner housing portion 180 comprises a front end portion 182 and rear end portion 183. The front end portion 182 is coupled to the coupling flange 142 or integrally formed therewith. An outer circumferential dimension, for example the diameter, of the inner housing portion 180 at the front end portion 182 is larger than the outer circumferential dimension at the rear end portion 183. Accordingly, the outer circumference of the inner housing portion 180 between the front end portion 182 and the rear end portion 183 may be tapered, in particular tapered towards the rear end portion 183. The rear end portion 183 is configured to support the propulsion device 200, for example the impeller 201. The rear end portion 183 may be configured to accommodate a rear bearing 202 for rotatably supporting the propulsion device 200 therein.

[0095] The propulsion device 200, in particular the impeller 201, may be operatively connected to a drive device such as an electric motor by means of a drive shaft 203. In an embodiment, the drive shaft 203 may be supported in the rear portion 140 of the fuselage assembly 100 by means of a rear bearing 202 and a front bearing 204 and such that a rear end portion 205 of the drive shaft 203 protrudes from the rear end portion 183. The front bearing 204 may be supported in the coupling flange 142. The rear bearing 202 may be provided in and may be supported by the rear end portion 183. The propulsion device 200 is fixedly and integrally rotatably mounted on the rear end portion 205 of the drive shaft 203.

[0096] The outer housing portion 170 may be coupled to the inner housing portion 180 on an upstream side of the outer housing portion 170, in other words, on the inlet side, by means of struts 190. The struts 190 may be equidistantly arranged about the longitudinal middle axis A1. Each strut 190 may be aerodynamically formed, for example as shown in FIG. 7 which shows a cross section of the struts in a direction parallel to the longitudinal middle axis A1. In this way, disturbances of a water flow passing the struts are reduced.

[0097] The nozzle section 172 may be detachably mounted to a downstream or rear end portion of the propulsion device accommodating section 171. The nozzle section 172 may comprise or define an outlet opening 191 at a downstream portion thereof. The nozzle section 172 may comprise a stator portion or stator 174 comprising multiple stationary guide vanes. However, in some embodiments, the stator 174 may be arranged in the propulsion device accommodating section 171. In other words, the stator 174 does not have to be provided in the nozzle section 172 but may be provided at other suitable positions in the flow channel 161. It is also possible to provide the stator 174 upstream of the propulsion device. Accordingly, an inverse arrangement may also be realized in which water first flows through the stator and then passes the impeller. In the embodiment, the stator 174 is arranged downstream of the propulsion device 200. The stator portion 173 may be configured such that a user may not pass a finger through the space between guide vanes 175. In other words, the distance between adjacent guide vanes 175 may be such that passing of a portion of the human body therethrough is not possible at all or is only possible to an extent in which the propulsion device 200 may not be reached or touched. Accordingly, the distance between the guide vanes 175 may be set depending on a distance between the stator 174 and the propulsion device 200.

[0098] In some embodiments, the fuselage assembly 100 may comprise a tail unit 300. In the embodiment, the tail unit 300 is provided in the rear portion 140 of the fuselage assembly 100. The tail unit 300 may also be referred to as stabilizing portion and according to the embodiment, comprises a stabilizing member 301. According to an example, the stabilizing member 301 comprises a wing 302, more precisely a horizontal wing as is shown in FIG. 2, for instance. In addition or alternatively, a vertical wing may be provided.

[0099] The fuselage assembly 100 may comprise an attachment portion 310 for detachably attaching the stabilizing member 301 thereto. On the other hand, according to a modification, the stabilizing member 301 may be integrally formed in the rear portion 140 of the fuselage assembly 100, for example by casting or injection molding.

[0100] In FIGS. 1 to 6, embodiments are shown in which the rear portion 140 comprises an attachment portion 310 that allows to detachably mount the stabilizing member 301 thereon. In the embodiment, the fuselage assembly 100 comprises two attachment flanges 311 each defining a supporting surface 312. Each attachment portion 310, for example each attachment flange 311, may comprise a threaded opening 313 which is configured to receive a threaded fastener 314 such as a screw. Accordingly, the stabilizing member 301 may be detachably attached by means of screws 314 as shown in FIG. 3. As is shown in the embodiments, the attachment portion 310 may be provided on the outer housing portion 170, for example in the propulsion device accommodating section 171. For that, the attachment portion 310 may be integrally formed in an outer circumferential portion 176 of the outer housing portion 170.

[0101] In some embodiments, the fuselage assembly 100 is configured such that the tail unit 300 is transferable between a use state and a stowing state. The use state may be a state in which the tail unit 300 is arranged to normally exert its predetermined function, for example to provide or add stability during movement of the powered hydrofoil watercraft 1. The tail unit 300 may comprise different configurations depending on the effect that is to be achieved. For example, the tail unit 300 may comprise at least one the above mentioned stabilizing wings 302. For example, the tail unit 300 may comprise a horizontal stabilizing wing mainly extending in horizontal direction during use and/or may comprise a vertical stabilizing wing mainly extending in vertical direction during use. In some embodiments, the stabilizing wing may be curved or may comprise at least two sections angled with respect to each other. The stabilizing wing may comprise a kink or sharp bend. Further configurations are possible. For example, the tail unit may comprise two stabilizing wings forming a V-shape. The tail unit 300 may be arranged rotatable about the longitudinal middle axis A1 of the fuselage assembly 100. The outer housing portion may be arranged rotatable about the longitudinal middle axis A1 of the fuselage assembly 100. Thus, by rotating the outer housing portion, the tail unit may be rotated between the above-mentioned states. The front wing 112 may be attached in a similar manner and may also be rotatable between a stowing state and a use state. The wing attachment section 105 may be rotatable so that the front wing 112 may be rotated by rotating the wing attachment section 105 about the longitudinal middle axis A1. However, as mentioned in the summary, different arrangements are possible including an arrangement in which one of the stabilizing wings and/or the front wing is rotatable about a vertical axis or an axis perpendicular to an outer surface of the portion it is mounted to.

[0102] In some embodiments, a mast assembly profile and a profile of the tail unit and/or of the front wing are arranged substantially in one plane when the tail unit and/or the front wing are in the stowing state. The tail unit and/or the front wing may be rotatable about a longitudinal middle axis of the fuselage assembly, for example such that the tail unit and/or the front wing are at least rotatable about 90 between the use state and the stowing state.

[0103] In the embodiments as shown, the fuselage assembly 100 is coupled to an end portion 53 of the mast assembly 50 so that the fuselage assembly 100 forms an end portion of the hydrofoil watercraft 1. In other words, according to the embodiment as shown in FIG. 1, the mast assembly 50 extends between the fuselage assembly 100 and the board assembly 10. It is however, also possible to couple the fuselage assembly 100 at a middle section 55 between the end portions 51, 53 of the mast assembly 50. In this way, the fuselage assembly 100 may be coupled to the mast assembly 50 at a position between end portion 53 and end portion 51. In this way, end portion 53 may be available for the fixation of a further element, such as a generic hydrofoil assembly or a wing.

[0104] In the embodiments shown in the figures, the fuselage assembly 100 combines a drive assembly and a hydrofoil assembly. In other words, the drive assembly is integrated into the hydrofoil assembly 100. However, it is also possible to provide a separate generic hydrofoil assembly and a separate drive assembly embodied by a fuselage assembly as described before. For example, a configuration may be provided in which the fuselage assembly that does not comprise elements like front wing and tail unit, is coupled to the mast assembly 50 at a portion between a generic hydrofoil assembly and the board assembly 10.

[0105] A modification to the embodiment shown in FIGS. 1 to 7 will be described with reference to FIGS. 8 and 9. As already mentioned before, the propulsion section 160 may be configured such that the stator 174 is arranged upstream of the propulsion device 200. Furthermore, the propulsion section 160 may be provided at the front portion 101 of the fuselage assembly and the mast assembly fixation section 106 may be arranged in the rear portion 140. In the modification as shown in FIGS. 8 and 9, the fuselage assembly 100 is embodied as a drive assembly 400 which does not comprise hydrofoil characteristics and only serves a propulsion purpose. A generic separate hydrofoil assembly 500 corresponding to known generic hydrofoil assemblies including a front wing 502 and a tail unit 510 coupled to each other by means of a fuselage 501 is provided at the lower end portion 53 of the mast assembly 50. The tail unit 510 comprises a stabilizing member 511 in the form of a wing 512. The drive assembly 400 is coupled to the mast assembly at a position between end portions 51 and 53 of the mast assembly 50. An inlet opening 401 allows for an inflow of water in axial direction and an outlet opening 402 also allows for an outflow of water in axial direction. Other features are similar to the features as already described before in connection with the embodiment of FIGS. 1 to 7 with the difference that the inlet opening 401 is provided at a foremost portion of the drive device 400/fuselage assembly 100 and the stator 174 is provided upstream of the propulsion device 200. The mast assembly fixation portion 106 is provided at a rearmost portion of the drive device 400. As is also obvious, further components like the electric motor are accommodated in the rear portion 140 of the fuselage assembly 100 for example at a position between the mast assembly fixation portion 106 and the propulsion section 160. The outlet opening 402 is defined ring-like and surrounds the rear portion 140 of the fuselage assembly 100.

[0106] A further embodiment of a hydrofoil watercraft 1 is shown in FIG. 10. The hydrofoil watercraft 1 may comprise one or more of the features as described before and may be a modification of the hydrofoil watercraft 1 as described before. The board assembly 10 may comprise a control unit 16. The control unit 16 may be coupled to a power source, for example an accumulator 20. The accumulator 20 may be detachably received in an interior space of the board assembly 10 and may be detachable for charging purposes. The board assembly 10 may comprise a first receiving unit 17. The first receiving unit 17 may be coupled to control unit 16. The first receiving unit 17 may be configured to wirelessly receive a control signal from a wireless remote control 21. The remote control may be a handheld remote control 21 held by a user and operated by the user to control the hydrofoil watercraft 1, for example to accelerate and decelerate the same. The board assembly 10 may comprise a second receiving unit 18. The second receiving unit 18 may be coupled to the control unit 16. The second receiving unit 18 may be configured to wirelessly receive a control signal from the remote control 21. Accordingly, a configuration may be provided in which two receiving units 17, 18 are provided. Each receiving unit 17, 18 may be a transceiver. Both receiving units 17, 18 may be configured to receive a signal from the remote control 21. The control unit 16 may be configured to receive the control signal from the remote control 21 via the receiving unit 17, 18 at which the signal strength is highest. In an exemplary configuration, the receiving units 17, 18 may be arranged at a distance from each other. For example, the receiving units 17, 18 may be provided in the board assembly at different longitudinal positions and/or laterally offset, for example on opposite sides of a middle longitudinal extension of the board assembly 10. In the embodiment as shown in FIG. 10, the first receiving unit 17 is provided in a front portion of the board assembly and the second receiving unit 18 is provided in a rear portion of the board assembly. In this way, a configuration may be achieved in which it is less likely that a control signal may not be received by the control unit 16 due to a blocked or covered receiving unit. This may be beneficial in situations in which the board assembly is partially under water since water may have a negative effect on signal transmission. During riding the hydrofoil watercraft, situations may occur in which the front portion of the board assembly 10 dives into water whereas the rear portion of the board assembly stays out of the water or vice versa. In such a situation, signal transmission from the remote control to the control unit 16 may be securely possible via the second wireless receiving unit 18 or the first receiving unit 17, in other words via the receiving unit 17, 18 which is not under water. Accordingly, providing two or more receiving units and distributing them on the board assembly such that they are arranged at a distance from each other secures the signal transmission even in situations in which portions of the board assembly are under water.

[0107] The control unit 16 and/or the power supply 20 may be coupled to the fuselage assembly 100 to supply power and/or control signals to the fuselage assembly, in particular to drive an electric motor 205 arranged in the fuselage assembly 100. For that, an electric line 56 may be provided which, for example, couples the control unit 16 to the fuselage assembly.

[0108] The board assembly 10 may comprise a humidity sensor 19. The humidity sensor 19 may be provided in the above mentioned interior space of the board assembly 10 in which electronic components such as the accumulator 20 and/or the control unit 16 are arranged. In addition or alternatively, a humidity sensor 206 may be provided in the fuselage assembly 100 in a compartment in which the electric motor 205 or an optional controller 207 for the electric motor 205 are provided. Each humidity sensor may be configured to measure the humidity in compartments in which electric components are accommodated. Each humidity sensor 19, 206 may be coupled to a controller, for example to the controller 16. Based on a signal received from a humidity sensor, the controller may perform predefined safety routines and/or may output signals reflecting the detected humidity. The signals may indicate to a user that measures for lowering the humidity should be taken. For example, the controller may be configured to output a warning signal to a user, for example to the remote control 21, when a predetermined humidity threshold value is exceeded. In addition or alternatively, the controller may be configured to cut off electric components from the power supply if a predetermined threshold humidity value is exceeded. Accordingly, the safety of the hydrofoil watercraft 1 may be increased by monitoring one or more electric components regarding humidity in their surroundings.

[0109] In addition or alternatively to the above features, the control unit 16 may be configured to provide an energy efficient driving mode. The driving mode may comprise a gliding mode in which the impeller is actively rotated at a speed which allows a fluid to pass the impeller substantially without being applied with a force from the impeller. According to a further configuration, the impeller may be disconnected from the electric motor such that it may be rotated only by means of fluid passing the impeller. In addition or alternatively, the electric motor 205 may comprise a motor/generator and the control unit may be configured to provide a recovery mode. In the recovery mode, the impeller is actively rotated by fluid passing the same and the rotational force generated is transferred into electric power by the motor/generator which may then by stored in the accumulator. The gliding mode and the recovery mode may be activated in suitable situations, for example a situation in which a user rides a wave and does not need an active motor drive. The recovery mode may also be used during deceleration of the hydrofoil watercraft. According to a configuration, the recovery mode is preset to be normally active so that as much energy as possible is recuperated. The recovery mode may be activated or deactivated depending on the charging level of the accumulator. The recovery mode may be activated if a the charging lever of the accumulator falls below a predetermined threshold charging level.

[0110] Further features of different aspects may be gleaned from FIG. 11. The hydrofoil watercraft 1 may comprise one or more of the features as described before and may be a modification of one of the hydrofoil watercrafts 1 as described before comprising one or more of the features as described below.

[0111] In addition or alternatively to one or more of the above-mentioned features of the hydrofoil watercraft, the hydrofoil watercraft may comprise may comprise a measurement device 22, for example an inertial measurement unit. The measurement device 22 may be configured to detect an angular rate and/or orientation and/or acceleration of the hydrofoil watercraft. The measurement device is accommodated in the board assembly 10. The measurement device 22 may be coupled to control unit 16. The measurement device 22 may be used for controlling the motor 205. Different possibilities regarding use of the measurement device 22 and implementations for controlling the motor 205 on the basis of the output of such measurement device 22 are given above and will not be repeated here.

[0112] The nozzle section 172 of the fuselage assembly 100 may be adjustable. For example, the outlet opening 191 of the nozzle section 172 may be adjustable in that its dimension may be changed, for example the dimension of the cross sectional area of the outlet opening. By changing the outlet opening dimension, in particular the diameter, it is possible to more efficiently generate a thrust needed for propulsion of the hydrofoil watercraft at different speeds. The nozzle section may comprise an outlet opening varying device 192 for changing the dimension, for example the diameter of the outlet opening 191. The outlet opening varying device may comprise length adjustable flexible elongate members 193 for generating a varying force on the edge portion defining the outlet opening. Details regarding such flexible elongate members 193 were already described and are not repeated here. According to a further aspect, the nozzle section 172 may be configured interchangeable so that a user may attach differently shaped nozzle sections to the fuselage assembly. In this way, the user can adapt the fuselage assembly to his needs, in particular to his riding style.

[0113] According to a further aspect, the fuselage assembly 100 may comprise a manipulating device 194 for manipulating the direction of the thrust generated in the propulsion section. In this way, a movement of the hydrofoil watercraft may be controlled or at least assisted. In other words, a thrust vectoring nozzle section 195 may be provided. The nozzle section 195 may comprise movable flaps 196 for directing the water flowing out of the nozzle section.

[0114] According to a further aspect, the hydrofoil watercraft may comprise a wireless signal and/or energy transmission arrangement 197, for example between mast assembly and board assembly 10. A transceiver 198 may be arranged in the board assembly 10 and coupled to the control unit 16. A further transceiver 199 may be provided in the mast assembly 50 and may be coupled to the electric motor 205 provided in the fuselage assembly 100. Further details regarding possible signal and or energy transmission arrangements and benefits were already given above and are not repeated here.

[0115] According to a further aspect, the hydrofoil watercraft may comprise an improved cooling arrangement 600 for cooling heat generating components, for example including but not limited to the control unit 16, motor controller and/or accumulator. The cooling arrangement 600 may be a passive cooling arrangement. The cooling arrangement 600 may comprise a piping system 601 fluid connected to an inlet opening 602 and an outlet opening 603 and allowing water to enter the piping system through the inlet opening and to exit the piping system through the outlet opening. The piping system 600 may be coupled to or may comprise a heat exchanger 604 or heat transfer member thermally coupled to one or more heat generating components. Possible configurations were already described in the general part of the description.

[0116] The hydrofoil watercraft 1 may comprise a maintenance determination unit as described in the general part of this disclosure, which may be integrated into the control unit 16.

[0117] According to an aspect, the hydrofoil watercraft may comprise communication means 700 for wirelessly connecting the same to a radio communication network. For that, the hydrofoil watercraft may comprise a transceiver 701.

[0118] According to a further aspect, the hydrofoil watercraft comprising one or more features as described herein is controllable by a remote control 21. The remote control may be configured as already described in this disclosure and can in addition or alternatively comprise a means for receiving and/or sending information. According to a further aspect, the remote control may be configured to measure health data of the user. The remote control can comprise a heart rate detection means 23 and/or may comprise a temperature detection means 24. In addition or alternatively the remote control 21 may comprise a motion sensor 25. The motion sensor may detect a motion of the user. The detected motion information may be used for controlling the hydrofoil watercraft, for example for acceleration or deceleration and/or steering.

[0119] According to a further aspect, the board assembly of a hydrofoil watercraft as described in the present disclosure may comprise a user detection device 702. The user detection device may comprise one or more sensor devices. Each sensor device may be configured to detect the presence of a user on the board assembly, at least in a specific area on the board assembly.

[0120] According to a further aspect, the hydrofoil watercraft may comprise a position detection unit or an interface for coupling to a mobile device comprising a position detection unit thereto. The position detection unit may comprise one or more GNSS signal receivers and may, for example, be integrated into one of the receiving units 17, 18 as described before.

[0121] The hydrofoil watercraft may comprise a collision prevention unit. The collision prevention unit may comprise a water depth determining device 703 providing a corresponding depth signal which may be used instead of depth information stored in a map.

[0122] According to an aspect, a display 704 may be provided on a front portion of the board assembly 10. The display may be used to display information for a user, such as information regarding current operational information, for example residual range, battery charge, travel speed, travel height, travelled distance or even navigation information.

[0123] According to an aspect, the hydrofoil watercraft may comprise a lighting arrangement 705. The lighting arrangement may comprise different lighting portions, for example a headlight portion, a taillight portion, and/or sidelight portions.

[0124] According to a further aspect, the hydrofoil watercraft remote control 21 may comprise a heating portion 26 (also referred to as heated portion) for at least partially heating a user's hand. The heated portion may be integrated into a gripping portion of the remote control.

[0125] According to a further aspect, the board assembly 10 of a hydrofoil watercraft as described herein may comprise a (foot) heating arrangement or portion 706. A supporting surface of the board assembly on which a user stands may comprise one or more heated sections. Each heated section may be integrated into an upper surface of the board assembly.

[0126] According to a further aspect, one or more loudspeakers 707 may be provided. As described before, a loudspeaker 707 may be part of a signaling device. However, one or more loudspeakers may be provided independent of a presence of a signaling device and/or may be configured couplable to a mobile device of a user or to a receiving unit integrated in the hydrofoil watercraft. The loudspeaker may be used for emitting sounds such as music and/or instructions from a navigation system.

[0127] According to an aspect, a remote control may be provided which is configured to provide navigation functions. The remote control may comprise the features as already mentioned before with respect to other aspects and embodiments. In addition or alternatively, the remote control may comprise a display 27. The display may show a map and/or navigation information. Navigation information may be entered (uploaded) into the remote control or a navigation unit in the board assembly wirelessly coupled to the remote control. The remote control may further comprise an emergency button 28.

[0128] In conclusion, it is pointed out that the terms like comprising or the like are not intended to rule out the provision of additional elements or steps. Let it further be noted that a or an do not preclude a plurality. In addition, features described in conjunction with the different embodiments can be combined with each other however desired. It is also noted that the reference numbers in the claims are not to be construed as limiting the scope of the claims. Moreover, while at least one exemplary embodiment has been presented in the foregoing summary and detailed description, it should be appreciated that a vast number of variations exist.

[0129] It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration in any way. Rather, the foregoing summary and detailed description will provide those skilled in the art with a convenient roadmap for implementing an exemplary embodiment, it being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope as set forth in the appended claims and their legal equivalents.

REFERENCE SIGNS

[0130] 1 Hydrofoil watercraft 162 Inlet section [0131] 10 Board assembly 163 Intermediate section [0132] 11 Hull 164 Outlet section [0133] 12 Lower portion 170 Outer housing portion [0134] 13 Upper portion 171 Propulsion device accommodating [0135] 14 Support surface section [0136] 15 Access panel 172 Nozzle section [0137] 16 Control unit 173 Inner surface section [0138] 17 First wireless receiving unit 174 Stator/Stator portion [0139] 18 Second wireless receiving unit 175 Guide vane [0140] 19 Humidity sensor 176 Outer circumferential portion [0141] 20 Accumulator 177 Upstream end portion [0142] 21 Remote control 178 Inlet opening [0143] 22 Measurement device 179 Downstream end portion [0144] 23 Heart rate detection means 180 Inner housing portion [0145] 24 Temperature detection means 181 Outer surface section [0146] 25 Motion sensor 182 Front end portion [0147] 26 Heating portion 183 Rear end portion [0148] 27 Display 184 Inlet angle [0149] 28 Emergency button 190 Strut [0150] 30 Mast assembly 191 Outlet opening [0151] 51 End portion 192 Outlet opening varying device [0152] 52 Board assembly fixation portion 193 Flexible elongate members [0153] 53 End portion 194 Manipulating device [0154] 54 Fuselage assembly fixation portion 195 Nozzle section [0155] 55 Middle section 196 Flaps [0156] 56 Electric line 197 Signal/Energy transmission [0157] 100 Fuselage assembly arrangement [0158] 101 Front portion 198 Transceiver [0159] 102 Front section 199 Transceiver [0160] 103 Middle section 200 Propulsion device [0161] 104 Rear section 201 Impeller [0162] 105 Wing attachment section 202 Rear bearing [0163] 106 Mast assembly fixation section 203 Drive shaft [0164] 107 Mounting recess 204 Front bearing [0165] 108 Coupling section 205 Electric motor [0166] 109 Accommodating section 206 Humidity sensor [0167] 110 Casing 207 Controller [0168] 111 Opening 300 Tail unit [0169] 112 Front wing 301 Stabilizing member [0170] 140 Rear portion 302 Wing [0171] 141 Coupling section 310 Attachment portion [0172] 142 Coupling flange 311 Attachment flange [0173] 143 Cylindrical portion 312 Supporting surface [0174] 144 Outer circumferential surface 313 Threaded opening [0175] 145 Engaging portion/threaded opening 314 Threaded fastener [0176] 146 Accommodating section 400 Drive device [0177] 147 Accommodating space 401 Inlet opening [0178] 148 Fixation flange 402 Outlet opening [0179] 149 Fixation openings 500 Hydrofoil assembly [0180] 150 fastening member/screw 501 Fuselage [0181] 160 Propulsion section 502 Front wing [0182] 161 Flow channel 510 Tail unit [0183] 511 Stabilizing member 702 User detection device [0184] 512 Wing 703 Water depth determining device [0185] 600 Cooling arrangement 704 Display [0186] 601 Piping system 705 Lighting portion [0187] 602 Inlet opening 706 Heating portion [0188] 603 Outlet opening 707 Loudspeaker [0189] 604 Heat exchanger A1 Longitudinal middle axis [0190] 700 Communication means [0191] 701 Transceiver