WATER SCOOPING APPARATUS FOR FORESTFIRE SUPPRESSANT IN NON-AMPHIBIOUS AIRTANKERS

Abstract

A water scooping apparatus for an aircraft comprising an extendible tubular member having a first end and an opposite end, wherein the first end is pivotally attached to the aircraft, a duct for fluidly connecting the extendible tubular member at the first end to a water tank, a floater connected to the opposite end of the extendible tubular member, wherein the floater is provided with an intake opening for taking in water; wherein the intake opening is fluidly connected to the extendible tubular member; wherein the water scooping apparatus is operable between a resting position in which the extendible tubular member is substantially retracted, and an operating position in which the extendible tubular member extends downwards from the aircraft at an angle.

Claims

1. A water scooping apparatus for an aircraft, comprising: an extendible tubular member having a first end and an opposite end, wherein the first end is pivotally attachable to the aircraft; a duct for fluidly connecting the extendible tubular member at the first end to a water tank; a floater connected to the opposite end of the tubular member, the floater having buoyancy for in use remaining buoyed on a water surface; wherein the floater is provided with an intake opening for taking in water, wherein the intake opening is positioned underneath the floater; wherein the intake opening is fluidly connected to the extendible tubular member; wherein the water scooping device is operable between a resting position in which the extendible tubular member is substantially retracted, and in an operating position in which the extendible tubular member extends downwards from the aircraft at an angle.

2. The water scooping apparatus according to claim 1, wherein the floater comprises a V-shaped body having a bow and a stern.

3. The water scooping apparatus according to claim 2, wherein the floater is provided with an airfoil attached to the floater near the bow, wherein the airfoil has an angle of engagement with air, and the angle of engagement is chosen to create a downward force during descent of the floater to the water surface.

4. The water scooping apparatus according to claim 2, wherein the intake opening is arranged facing the bow.

5. The water scooping apparatus according to claim 1, wherein the intake opening is provided with an intake valve.

6. The water scooping apparatus according to claim 1, wherein the floater is provided with a hydrofoil mounted underneath the floater near the stern, wherein the hydrofoil is mounted having an angle of engagement with water, and wherein the angle of engagement is chosen to create a downward force.

7. The water scooping apparatus according to claim 1, wherein the extendible tubular member comprises an extendible tube having at least one extension pipe.

8. The water scooping apparatus according to claim 7, wherein the extendible tube is a telescopic pipe.

9. The water scooping apparatus according to claim 1, wherein the extendible tubular member comprises at least a hose, and wherein the water scooping apparatus further comprises means for releasing and retracting the at least one hose.

10. The water scooping apparatus according to claim 9, wherein the means for releasing and retracting of the hose comprise a reel, the reel being arranged for rolling the hose onto the reel and for unrolling the hose from the reel.

11. The water scooping apparatus according to claim 10, wherein the extendible tubular member further comprises lifting means arranged for moving the floater in and out of the resting position and for keeping the floater in the operating position.

12. An aircraft comprising a fuselage comprising a water tank, wherein the aircraft is further provided with a water scooping apparatus according to claim 1, wherein the water scooping apparatus is attached to a reinforced frame of the aircraft via a hinge member, wherein the water scooping apparatus is fluidly connected to the water tank via the duct.

13. A method for filling water tanks of an aircraft according to claim 12, comprising: flying over a water surface at an altitude in a range of 1-18 meter; extending the extendible tubular member until the floater touches the water surface; taking in water from the water surface via the intake opening.

14. The method according to claim 13, wherein the altitude is in a range of 5-15 meter.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0035] FIG. 1 shows an example of a water scooping apparatus according to an embodiment of the invention mounted underneath an aircraft comprising telescopic pipes.

[0036] FIG. 2 shows another example of a water scooping apparatus according to an embodiment of the invention comprising a hose on a reel and the floater mounted inside an aircraft in a resting position.

[0037] FIG. 3 shows the water scooping apparatus of FIG. 2 in an operating position.

[0038] FIG. 4 shows a side view of a floater of the water scooping apparatus according to an embodiment of the invention.

[0039] FIG. 5 shows a front view of the floater of the water scooping apparatus according to an embodiment of the invention.

[0040] FIG. 6 shows a rear view of the floater of the water scooping apparatus according to an embodiment of the invention.

DETAILED DESCRIPTION OF THE INVENTION

[0041] The water scooping apparatus as shown in FIG. 1 in resting-position 8, can be mounted underneath an aircraft 1 or airtanker, e.g. a conventional non amphibious aircraft 1.

[0042] The aircraft 1 may have installed water tanks 10 which can for example contain 10.000 to 30.000 litres or more of liquid fire suppressant, i.e. water. These water tanks are interconnected by wide-dimensional ducts 12 in order to maintain a steady balance of the aircraft 1 during high-speed filling. An airtanker is able to drop the content of these tanks in a very short time, varying from 4 to 8 seconds, on a forest fire.

[0043] The water tanks 10 are connected to a filling pipe or duct 4 which is connected to an extendible pipe 5. The extendible pipe 5 is connected to a hinge 3. The hinge 3 can be mounted on a frame which is mounted in the aircraft 1. The hinge 3 can also be mounted directly inside the aircraft 1 and connected with the for this purpose reinforced main frame or fuselage 14 of the aircraft 1.

[0044] When the water scooping apparatus 2 is in operating position, the floater 7 being pulled by the aircraft 1 and floating on the water surface 9 will maintain a steady, passive, stable and safe position in the water surface 9, while the aircraft 1 may be varying in altitude with respect to the water surface.

[0045] The main pipe 5 which is connected to the hinge 3, is extendible by at least one extension pipe 6. The extension pipe 6 can have an outer diameter to fit inside the extendible main pipe 5. The extension pipe 6 is attached to a floater 7. The extension pipe 6 is provided with an intake opening (see reference numeral 20 in FIG. 4), which may have an intake-valve. Once the floater 7 with intake-opening enters the water-surface 9 the water will pass through the intake opening and enter the said water tanks under high pressure, as shown in FIG. 1. The intake valve can be gradually opened to allow a controlled inflow of water once the floater 7 has engaged the water surface 9.

[0046] As shown in FIG. 2, the extendible tubular member can alternatively comprise a hose 18. The hose 18 can be made from a reinforced material comprising for example Dyneema™ fibre or a similar material. The hose 18 in resting position in FIG. 2 can be rolled onto a reel 13 which is mounted inside the aircraft 1. The floater 7 can be accommodated on a slide 17. Reel 13 and floater 7, parked on the slide 17 can be accommodated within the fuselage 14 of the aircraft 1.

[0047] The hose 18, or multiple hoses 18, can be accompanied by one or more cables (not shown in FIG. 2) for lifting or hoisting the floater 7 from its resting position to operating position and vice versa. The one or more cables also allow relieving the hose 18 from the tensile force exerted by the aircraft to the floater in operating position.

[0048] In FIG. 3 the hose 18 is shown in rolled off position. The reel 13 causes the hose 18 to be extendible, and also provides the hinge action, as the hose can swing around the reel central axis in a vertical plane extending from the front of the aircraft 1 to the rear. The flexibility of the hose 18 can also contribute to the hinge action. The end of hose 18 at the reel 13 is connected to duct 4 via a water tight bearing, thus connecting the hose 18 to the water tanks 10. At the opposite end of the hose the floater 7 is attached to the hose 18.

[0049] For the scooping sequence to begin, the floater 7 is released from the aircraft 1 by opening hatch 16 and lowering slide 17. In this lowered position, the hose 18 can be unrolled from reel 13. The airflow underneath the airplane will position the floater 7 relative to the airplane 1 as shown in FIG. 3. The moving of the slide 17 can be performed for example by means of a winch with a cable attached to a free side of the slide 17. The slide 17 can be lowered by releasing the cable from the winch 15.

[0050] The hose 18 is pivotally attached to the floater 7 and on the other end the main axle/tube of the reel can freely rotate, which allows the aircraft 1 to fly at an altitude between 6 and 20 meters, while the floater 7 remains in perfect scooping position. The diameters of the hose 18 and the duct 4 from the reel 13 to the holding tanks is chosen to allow high speed-filling and the wide-dimensional ducts in-between the water tanks 10 ensure equal filling and consequently balance and stability to the aircraft 1 during the process.

[0051] In FIG. 4 the floater 7 is shown. The floater 7 preferably has a V-shaped body viewed in a vertical cross section and a high and sharp-constructed bow 22 which will split the water surface 9 and water mass below it, allowing the floater 7 to enter the water surface at high speed and maintain a steady position whilst in operation being pulled by the aircraft through the water as described before without causing too much pressure or stress on the aircraft 1. This is for example achieved with an axe bow as shown in FIG. 4.

[0052] At both sides of the floater 7 spray-spoilers 21 can be mounted to deflect bow-waves and spray sideways in order to reduce the pressure.

[0053] The stern 23 is also designed in a way to lead the water smoothly away from the floater in order to cause less stress on the aircraft 1. The stern 23 can for example also be V-shaped both in a horizontal cross-section as well as in a vertical cross section of the floater 7. The intake opening 20 is connected with the said pipe and the water tanks.

[0054] The floater 7 is provided with an airfoil 24 near its bow 22. The airfoil 24 is positioned to create a downward force, for example by tilting it downward in the forward direction of the floater 7, and forces the floater 7 downwards in a stable way to the water surface 9. After touch-down the airfoil 24 may be collapsed and folded to away, inside the floater 7 or to the sides of the floater 7. The airfoil 24 can be collapsible and foldable into a recess of the floater 7. The airfoil 24 is deployed while lowering the floater 7 from the aircraft 1. When the floater 7 engages the water surface 9, the airfoil 24 is preferable collapsed to prevent waves from damaging the airfoil 24.

[0055] The floater 7 can be provided with a hydrofoil 19 underneath the floater 7 near its stern 23. The hydrofoil 19 creates a downward force, whereas the floater buoyancy creates a upward force when pulled by the aircraft 1 and hose 18 through the water surface 9. The hydrofoil 19 is for example tilted downward in a forward direction of the floater 7. In this way the floater 7 is forced into a passive, stable and safe scooping position at an angle of about 40 degrees relative to the aircraft 1.

[0056] The extendible pipe 5, 6 or hose 18 can extend through the floater 7 to be connected with the intake opening 20. Alternatively, a passage can be made extending through the floater body wherein the passage is pivotally connected to the extendible pipe 5, 6 or hose 18 at its upper end and the intake opening 20 is connected to its lower end. The connection of the extendible pipe 5,6 or hose 18 can also be a flexible connection. The pivotal or flexible connection allows free movement of the floater 7.

[0057] In FIG. 5 is shown the floater 7 in front view of the bow 22 with two pipes 6 or hoses 18 in case of high volume airtankers. The intake-opening 20 is shown in front view as well as the spray-spoilers 21.

[0058] In FIG. 6 the floater 7 is shown from the rear with the stern 13 in front.

[0059] The scooping capacity of the water scooping apparatus 2 is determined by the diameter of the hose 18, by the surplus-power of the engines and loading-capacity of the aircraft 1. An overflow valve can be installed in the water tanks 10 to avoid overloading. After filling the water tanks 10 the overflow valve can be closed, the hose 18 rolled onto the reel 13 and the floater 7 can resume its resting position and the hatch is closed. In case of higher volumes the water scooping apparatus 2 can comprise two or more hoses 18 instead of one.

[0060] The embodiments described above are given by way of example. Variations are possible without departing from the scope of protection provided by the claims below.

REFERENCE NUMERALS

[0061] 1 aircraft

[0062] 2 water scooping apparatus

[0063] 3 pivotal connection

[0064] 4 duct

[0065] 5 extendible pipe

[0066] 6 extension pipe

[0067] 7 floater

[0068] 8 water scooping apparatus in resting position

[0069] 9 water surface

[0070] 10 water tanks

[0071] 11 actuator

[0072] 12 water tank connection duct

[0073] 13 reel

[0074] 14 fuselage

[0075] 15 hatch

[0076] 16 winch

[0077] 17 slide

[0078] 18 hose

[0079] 19 hydrofoil

[0080] 20 intake opening

[0081] 21 spray spoiler

[0082] 22 axe bow

[0083] 23 stern

[0084] 24 airfoil