AU2001281468A1

AU2001281468A1 - Fluid loading system

Info

Publication number: AU2001281468A1
Application number: AU2001281468A
Authority: AU
Inventors: Alan B. Macdonald; Rory D. Parker; Lee Ramage
Original assignee: ERICKSON AIR-CRANE Inc
Current assignee: ERICKSON AIR-CRANE Inc
Priority date: 2000-03-10
Filing date: 2001-03-09
Publication date: 2001-12-06
Anticipated expiration: 2021-03-09

Description

i

FLUID LOADING SYSTEM

Cross-Reference This application claims priority from U.S. Provisional Patent Application Serial No 60/188,547, filed March 10, 2000. Field of the Invention

The invention relates to pump devices for loading fluid into a tank. In particular, the invention involves conduit devices that can load fluid onto an aircraft, either fixed wmg or rotocraft, from a fluid source such as a lake, river, reservoir, or ocean while remaining airborne Background of the Invention

For many years, special aircraft have been designed and used to carry and deliver water to a fire Helicopters or "hehtankers" may be equipped with fire suppression systems that are capable of loading water from a source such as a lake or an ocean, into an onboard tank, and then transporting and dispensing the water onto a fire. Recently, the world-wide demand for hehtanker fire fighting services has expanded. Hehtanker fire fighting operations are now often required in areas where fresh water sources are scarce and salt water sources are abundant Therefore, hehtankers must be able to utilize sea water as a retardant without damaging aircraft components or compromising safety.

Conventional FAA approved hose or "snorkel" devices are unsatisfactory for use with salt water because these snorkels require the helicopter to hover at a level that results in rapid loss of power due to salt accumulation in the engines. For example, U.S.

Patent No. 3,897,829 discloses a helicopter equipped with a suction conduit that is designed to hang vertically below a hovering helicopter to load water from a source into an onboard tank. A significant problem with this type of water suctionmg device is that downwash generated by the rotor causes water from the source to splash onto the underside of the helicopter This can be a serious problem when the source contains salt water because the salt may cause parts of the helicopter to rust and corrode. Salt spray ingested into the engines can cause internal damage and result in a loss of power and eventually may cause total failure of one or both engines. Another problem with use of dangling hoses in ocean water is that the hose may bounce m and out of the water if the ocean is wavy or turbulent. Accordingly, an object of the invention is to provide a system for loading fluid onto an aircraft from a salt water source without ingesting fluid into the aircraft engines

Another object of the invention is to provide a conduit device for loading fluid into a tank on board an aircraft, in which the conduit device can remain partially stabily submerged m the fluid source while the aircraft flies over the source at a ground speed sufficient to stay ahead of the spray generated by the rotor wash

Another object of the invention is to provide a fluid loading system that may be versatily employed to load fluid from different types of sources, for example, oceans, lakes, rivers, and reservoirs, in varying shapes, depths, and degrees of salinity Summary of the Invention

The invention provides a fluid loading and transport system for an aircraft A substantially rigid tube member is connected to the aircraft m communication with the tank The tube member is movable into a downward orientation for accessing a fluid source while the aircraft flies over the source and may be retracted in times of non-use One aspect of the invention relates to a fluid conduit device having a distal end equipped with a divmg device, preferably m the form of an inverted hydrofoil, that substantially maintains the distal end of the conduit device below a surface of the water source while the aircraft flies over the water source

Another aspect of the invention provides a fluid conduit device in which a tube member has a strut running along at least a portion of the length of the tube member The strut is configured to stabilize a submerged distal end of the tube member while the aircraft moves over a fluid source

Still another aspect of the invention involves a fluid conduit device m which a tube member is connected to an aircraft in communication with an onboard tank so that the tube member maintains a substantially rearward angular orientation when the aircraft translates over the fluid source and the distal end of the tube member is submerged

The invention also provides a method of loading water onto a moving aircraft Fluid is transferred from a source through a tube member into a tank on an aircraft by a pump or ram pressure generated by the forward velocity of the aircraft as it moves over the source In a preferred procedure, the tube member is directed rearward relative to the aircraft's direction of travel A distal portion of the tube member is maintained below the surface of the fluid source by providing a diving device near the distal portion.

Brief Description of the Figures Figure 1 is a side view of a helicopter equipped with a tank and associated fluid conduit device for loading water in to the tank

Figure 2 is a side view of a helicopter equipped with a tank and a fluid conduit device consisting of the upper portion of the tube member shown in the system of Figure 1.

Figure 3 is a side view of a helicopter equipped with a tank and fluid conduit device retracted against the underside of the helicopter in its non-use position.

Figure 4 is a partial, side view of the junction between the tube member and the tank of the system shown in Figure 1.

Figure 5 is a partial, cut-away view of a central portion of the tube member shown in the system of Figure 1 Figure 6 is a partial, side view of the distal portion of the tube member in the system of Figure 1.

Figure 7 is a partial, front view of a preferred embodiment of the invention suspended from a tank on the underside of a helicopter.

Figure 8 is a perspective view of the diving device that is mounted on the distal end of the conduit device shown in Figure 7

Figure 9 is a partial, side view of an alternative embodiment of the invention showing a modified intake design.

Figure 10 is a cross-sectional view through the conduit device of Figure 9. Figure 11 is a partial front view of the distal end of the conduit device shown in Figure 9.

Description of the Invention

The invention provides a system for loading fluid into a tank on an aircraft while the aircraft translates over the surface of the fluid source. Tests have demonstrated that a helicopter can fly at a loading level, for example, withm about 10 feet of the water surface, at a speed of approximately 25 knots or greater, and thereby substantially avoid the mgestion of water into the engines. The m-flight loading system can be operated stabily and safely m a turbulent or wavy salt water source such as an ocean without splashing significant amounts of salt water onto the underside of the aircraft. In a preferred application of the invention, a divmg device such as a hydrofoil structure is used to stabilize a submerged distal end of a conduit while loading Figures 1-6 illustrate details of a first embodiment of the invention. Figure 1 shows helicopter 20 which is a conventional helicopter in many respects, except that it has been equipped with a fluid loading and containing system according to the invention Tank 22 is connected to a central portion of the helicopter substantially directly below the mam rotor 23. A front view of a similar tank is shown in Figure 7. Substantially rigid tube member 24, also referred to as conduit structure or snorkel, is connected to the front end of tank 22. A distal end of tube member 24 is submerged m fluid source 30. Tube member 24 is connected to tank 22 by horizontal rotating union 32 and a \ ertical swivel joint 34, further details of which are shown in Figure 4 and discussed below Upper and lower portions of tube member 24 are connected in a central portion 36. The distal end of tube member 24 has a divmg device in the form of an inverted hydrofoil structure or other divmg device 40 which helps to maintain tube member 24 in the fluid source. A streamlined strut 42 is formed in the front face of tube member 24 for decreasing drag when helicopter 20 is moving forward, and also to at least partially stabilize lateral movement of tube member 24. Helicopter 20 is equipped with an altimeter device 46 for monitoring the relative height of helicopter 20 over the surface of fluid source 30 Information from the monitoring device is reported to the pilot/copilot m an appropriate instrument.

As shown in Figure 1 , tube member 24 is directed rearward at a preferred angle θ of approximately 40°. Divmg device 40 is configured to stabilize the distal end of tube member 24 in the fluid at angle θ while helicopter 20 translates forward at approximately 40 knots. The system shown m Figure 1 substantially avoids splashmg of water on the underside of the helicopter by moving forward at a sufficient velocity, preferably about 25 knots or higher, so that water that is splashed up by rotor downwash occurs primarily behind the moving helicopter. Figure 2 shows a different application of the invention. Helicopter 20 and tank 22 are the same as illustrated and described in relation to Figure 1. Tube member 24 has been shortened by detaching the bottom portion so that upper portion 48 of tube member 24 directly connects tank 22 to fluid source 50 Fluid source 50 may be a lake or reservoir that has a substantially calm or flat surface The application shown m Figure 2 may be appropriate when fluid source 50 is relatively fresh water (negligible salt content) so that fluid loading may be performed while helicopter 20 hovers

Figure 3 shows the same system of Figure 1 in its retracted position. Tube member 24 is pulled up and secured against the underside of tank 22 by a wmch (not shown) onboard helicopter 20.

An enlarged view of the joinder mechanism between tube member 24 and tank 22 is shown in Figure 4 Horizontal rotating union 32 allows tube member 24 to rotate around an axis that is substantially perpendicular to the surface of the fluid source, and perpendicular to the direction of travel Vertical swivel joint 34 permits tube member 24 to rotate around axis AA which is perpendicular to the figure Vertical swivel joint 34 permits movement of tube member 24 between the use position, as shown in Figure 1, and the non-use position, as shown in Figure 3. Outer skm 60 of vertical swivel joint 34 is flexible to permit movement of the joint.

In Figure 5 the drawing is cut-away in central portion 36 of tube member 24 to show an optional pump device 64 that is contained inside tube member 24 When the helicopter translates forward with tube member 24 submerged in a water source, even without any assistance from pump device 64, a ram effect is observed which naturally pressures water from the fluid source up through tube member 24 into tank 22 Pump device 64 may be used to increase the rate of fluid loading

Figure 6 shows the distal end of tube member 24. Divmg device 40 is configured to retain and stabilize the desired orientation of tube member 24 in the fluid source as the helicopter translates forward. Water mlet 66 is provided on the front face of tube member 24 for receivmg and channeling water into tube member 24. Internal volutes 68 are shown in dashed lmes, and is provided to smoothly redirect in-flowing fluid up into tube member 24 toward tank 22.

A preferred embodiment of the invention is illustrated in Figure 7. Helicopter 100 has a tank 102 for carrying water from a source such as an ocean, to a fire. Two different conduit devices are connected to the front end of tank 102. Rigid conduit 104 is connected to tank 102 on one side of the front end of tank 102. Conduit 104 is designed primarily for accessing fluid from a salt water or a fresh water source while m forward motion. Flexible hose conduit 106 is connected to the other side of the front end of tank 102, and is used primarily for accessing fluid from a fresh water source while helicopter 100 hovers. Rigid conduit 104 is substantially the same as the one described in relation to Figure 1, except that conduit 104 has no internal pump device located in mid-portion 110. When the distal end of conduit 104 is submerged and moving forward in the water at a velocity of, for example, 25 knots, a substantial ram effect pressures water up through conduit 104 into tank 102 without any additional pump mechanism Experiments have shown that conduit 104 can load water into tank 102 at a rate of approximately 2,000 gallons in 28 seconds while translating forward at a velocity of approximately 35 knots, without any additional pumping mechanism.

The front view of conduit 104 in Figure 7 also illustrates the narrow front profile of lower portion 112 of conduit 104. The narrow front profile streamlines the portion of conduit 104 that is submerged m the water and minimizes drag or water resistance during loading. Intake 114 channels fluid into two internal tubes which extend on up through conduit 104. Diving device 116 is connected to the distal tip of conduit 104 m an orientation that maintains submersion of conduit 104 at a desired angle and depth while loading water into tank 102. It is advantageous to provide two types of conduits or snorkels for maximum versatility. The rigid conduit is most desirable when loading fluid from a salt water source when it is particularly important to avoid mgestion of salt water into the helicopter engines. Other times it may be desirable to use the flexible conduit, for example, when loading from a fresh water source or a source that is not large enough to fly over while loadmg.

Figure 8 shows a perspective view of divmg device 116. Divmg device 116 has a pair of substantially planar shoulder members 120 which taper as they extend down and generally outward on opposite sides of conduit 104. Shoulder members 120 are then connected to lateral wing members 122. Three fastenmg flanges 124 may be provided on the top side of divmg device 116 for connecting divmg device 116 to conduit 104. Figures 9-11 illustrate another embodiment of the invention m which the outer shape of the intake portion of the conduit is modified. Lower conduit portion 140 has a distal intake portion 142. A divmg device 144 is connected to conduit 140 substantially as previously described. Internal tubes 146a and 146b present openings for receiving oncoming fluid as lower conduit portion 140 is submerged and translating forward. Figure 10 shows a cross-section through lower conduit portion 140 and internal tubes 146a and 146b. Figure 11 shows a front view of intake portion 142 where the openings of tubes 146a and 146b can be seen, in addition to the front profile of divmg device 144. Although the invention has been disclosed in its preferred forms, the specific embodiments thereof as disclosed and illustrated herein are not to be considered m a limiting sense, because numerous variations are possible. Applicants regard the subject matter of their invention to include all novel and nonobvious combinations and subcombmations of the various elements, features, functions, and/or properties disclosed herein. No single feature, function, element or property of the disclosed embodiments is essential. The following claims define certain combinations and subcombmations of features, functions, elements, and/or properties that are regarded as novel and nonobvious. Other combinations and subcombmations may be claimed through amendment of the present claims or presentation of new claims in this or a related application. Such claims, whether they are broader, narrower, equal, or different m scope to the original claims, also are regarded as included withm the subject matter of applicants' invention.

Claims

WE CLAIM

1. A fluid conduit de\ ice comprising a tube member having a proximal end and a distal end, the proximal end being configured for connection to an aircraft m communication with an onboard tank, the distal end having a divmg device that substantially maintains the distal end of the tube member below a surface of a fluid source while the aircraft translates over the fluid source.

2 The device of claim 1 , wherein the tube member is substantially rigid

3 The device of claim 1 , wherein the tube member has an upper portion and a detachable lower portion

4. The device of claim 1 , wherein the tube member has a front face, and a strut structure formed on the front face for reducing drag when the aircraft translates over the fluid source.

5. A fluid conduit ice comprising a tube member having a proximal end, and a front face, the proximal end being configured for connection to an aircraft in communication to an onboard tank, the front face having a strut structure configured to stabilize a submerged distal end of the tube member, and to reduce drag, while the aircraft moves over a fluid source.

6. The device of claim 5, wherein the tube member has a divmg device located near the distal end for substantially maintaining the distal end of the tube member below a surface of the fluid source.

7 The device of claim 5, wherein the tube member is substantially rigid.

8 The device of claim 5, wherein the tube member has an upper portion, and a detachable lower portion.

9. The device of claim 5 further comprising a pump device substantially contained mside the tube member for increasing the pump capacity of the fluid conduit device.

10. A pump system compnsmg an aircraft havmg an underside, a tank onboard the aircraft for containing fluid, and a substantially rigid tube member, connected to the aircraft in communication with the tank, wherein the tube member is movable to a downward orientation for accessing a fluid source below the aircraft.

11. The pump system of claim 10, wherein the aircraft is a helicopter.

12. The pump system of claim 10, wherein the aircraft is an airplane.

13 The pump system of claim 10, wherein the tube member is directed rearward relative to the aircraft when the tube member is in the downward orientation

14 The pump system of claim 13, wherem the tube member forms an angle of approximately 40° with the underside of the aircraft when the tube member is in the downward orientation

15 The pump system of claim 10, wherein the tube member has a distal end and a divmg device near the distal end for maintaining the distal end of the tube member in the fluid source while the aircraft moves over the source

16 The pump system of claim 10, wherein the tube member has a front face and a strut structure formed on the front face of the tube member for reducing drag when the aircraft moves over the source

17 The pump system of claim 10 further comprising an altimeter device onboard the aircraft for monitoring the height of the aircraft over the water source

18. The pump system of claim 10 further comprising a pump device substantially contained in the tube member for increasing the loading capacity of the pump system.

19. The pump system of claim 10 further comprising a flexible tube member connected to the tank for loading fresh water while the aircraft hovers over a source

20. A fluid conduit device compπsmg a substantially rigid tube member having a proximal end configured for connection to an aircraft in communication with an onboard tank, wherein the tube member is movable into a downward orientation for accessing a fluid source below the aircraft.

21. The device of claim 20, wherein the tube member has a distal end equipped with a divmg device that substantially maintains the distal end of the tube member below a surface of a water source while the aircraft translates over the water source.

22. The device of claim 20, wherein the tube member has a front face, and a strut structure formed on the front face for decreasing drag when the aircraft translates over the fluid source.

23. The device of claim 20, wherem the aircraft is a helicopter.

24. The device of claim 20, wherem the fluid source contains salt water.

25 A fluid conduit de\ ice comprising a tube member having a proximal end and a distal end, the proximal end being configured for connection to an aircraft m communication with an onboard tank so that the tube member maintains a substantially rearward linear orientation when the aircraft translates over the fluid source and the distal end of the tube member is submerged

26 The device of claim 25, wherem the tube member forms an acute angle with the direction of aircraft translation when the tube member is being used to load fluid into the onboard tank

27 The device of claim 26, wherem the tube member forms an angle of approximately 40° with the direction of aircraft translation when the tube member is being used to load fluid into the onboard tank

28 The device of claim 25, wherein the distal end of the tube member has a divmg device configured to substantially maintain the rearward linear orientation of the tube member relative to the aircraft when the aircraft translates over the fluid source

29 A method of loading water onto an aircraft comprising pumping fluid from a source through a tube member onto a tank on an aircraft, while the aircraft moves over the source

30. The method of claim 29 further comprising the step of directing the tube member rearward relative to the aircraft's direction of travel.

31 The method of claim 29 further comprising the step of maintaining a distal portion of the tube member below the surface of a fluid source by providing a divmg device near the distal portion.

32. The method of claim 29 further comprising the step of providing a pump device m a middle portion of the tube member for increasing the pumping rate through the tube member.