| AU7916775A | 1976-09-23 | |||
| DE1556795A1 | 1970-08-13 | |||
| FR768177A | 1934-08-01 | |||
| US3175785A | 1965-03-30 | |||
| US3285535A | 1966-11-15 |
| 1. | defining the invention are as follows: A HeliHover Amphibious craft of single hull configuration powered by one or more horisontally rotating deck or superstructure mounted helirotor'assemblies set well above deck arrangement of hovercraft, supported on open or closed superstructure being part of or attaching to main hover craft fuselage body structure. Antitorque means provided aft where so required, depending on main helirotor configuration. Main helirotor arrangement can be single rotor or coaxial, counter rotating rotors of various rotor configurations depending on model and application. Main helirotor assemblies have a vertical or near vertical fixed shaft axis in relation to the main hovercraft fuselage body structure. A single hull hovercraft with a corapartmented under base cavity facing down to the surface wherein the divisional and perimeter walls are formed by trunkated skirts and or other air cushion containing means to contain the suspension air supplied by one or more deck mounted fans delivering pressurised air through inbuilt ducting. oused within the hovercraft fuselage body. Helirotor assemblies share common drive system which are directly or remotely linked to drive antitorque tail rotor or jet air thruster assemblies or other antitorque means. |
| 2. | A HeliHover Amphibious craft as in claim 1 where deck or superstructure mounted helirotor assemblies can be arranged in tandem, pairs or quad formation to meet the needs of different models and applications. |
| 3. | A HeliHover Amphibious craft as in claims 1 and 2 where in the helirotor assemblies are supported" as an integerated part of the main superstructure of the single hover craft fuselage body structure. |
| 4. | A HeliHover Amphibious craft as in claims 1 and 2 wherein the helihoverro or assemblies are supported by an open web or formed " streamlined strut superstructure attaching to lower deck or attached superstructure of the single hover craft fuselage body structure. |
| 5. | A HeliHover Amphibious craft as in claims 1, 2, 3 and 4 wherein the HeliRotor assembly or assemblies are mounted well above the main hover craft fuselage body and superstructure,arranged to have fixed rotor shaft axis tilting forward up to a maximum of 10 from perpendicular in.relation to the lower surface area of the craft. This inclination will vary with different models and applications. |
| 6. | A HeliHover Amphibious craft as in claims 1, , 3, 4, and 5 wherein the torque forces created by the main Helirotor are neutralized by the use of a tail rotor or air jet thruster attached to a elevated tail structure on the stern or aft deck of the craft. |
| 7. | 75 A HeliHover Amphibious craft as in claims 1, 2, 3, 4, and 5, wherein the. |
| 8. | torque forces created by the main HeliRotor are neutralized by the use of a orbital open bladed or cowled fan attached to an elevated tail structure on the stern or aft deck of the craft. |
| 9. | A HeliHover Amphibiouscraft as in claims 1, 2, 3, 4, and 5, where in the basic single hull configuration of the main hovercraft fuselage body structure houses the under open mouthed multiple stabilizing plenum chambers 'with their outer periferal and divisional "borders formed by segmented skirts, cones or fingers. •. |
| 10. | A HeliHover Amphibious craft as in claims 1, 2, 3,. 4, 5, and 8 where in the main helirotor blades are protected by the additional fitting to beam deck sponsons, extending up and out past outer most swept position of these rotor blades. |
| 11. | A HeliHover Amphibious craft as in claims 1, 2, 3, 4, 5, 8, and 9 where in a substantial outrigger rail Is incorporated under and at the rear of the tail rotor. |
| 12. | A .HeliHover Amphibious craft as described in the specification and shown as applied specific arrangements in the drawings Figure 1, 2 and 3 wherein the concept of the invention is applied utilizing any of the known hovercraft configurations combined with any of the known helirotor assemblies as applied to known helicopter types. |
The invention relates to a vehicle or craft operating as a hover-craft with a solid closed fuselage with inbuilt lift fan or fans supplying hover lift pressurised air to support fuselage in hover mode. Manoeuvreability and propulsion thrust is supplied by one or more deck mounted horisontally placed rotor or rotors of helicopter configurations, equipted with variable collective and cyclic pitch control. Tail rotor or rotors, control torsional forces onfuselage as well as assisting manoeuvreability of vehicle.
The invention overcomes the inherent problems of manoeuvreability and side drift associated with conventional hovercraft equipted with deck mounted thrusters^ Trim of craft is effectively improved by lift moment of upward pull of horisontally rotating propulsion heli-rotor or rotors. Main rotor collective pitch together with cyclic pitch adjustments in conjunction with tail rotor control, allows for precise manoeuvrability of the craft in all directions at low or high speed providing effective braking and speed control due to main rotor revoluti being maintained and thrust controlled by pitch adjustments. Noise levels are drastically reduced by eliminating the conventional high speed air screw propulsion units. The craft has the ability to climb over obstacles which would otherwise stop a conventional hovercraft propelled by deck mounted airscrew thrusters.
Stability is vastly improved when compared with the conventional aerostatic Hovercraft in so far as the pendulumn support of the overhead rotor tends to eliminate reverse banking of the hull in turns also assisting forward trim by keeping the bow up, thereby preventing bow plough-in and instability of craft. Skirt life is markedly improved by the action of these factors. On land the conventional Hovercraft runs away in an uncontrolable manner on down hill slopes whereas with the present inventions precise control can be maintained under all circum- stances due to thrust control provided by the 360 cyclic movement of thrust and lift vector from the heli-rotor. In the known invention Australian Patent No 79167, 17th March 1975 by Herbert Leonard Dobb, Titled:- "Air Cushion Pontoon Freight Helicopter".
SUBSTITUTE SHEET
From these specifications and claims it will be noted that the present Hell-Hover invention overcomes the necessity for a twin divided pontoon structure to provide stability, by using a single main hull of wide beam and length proportions utilizing the conventional compartmented under cavity sections with segmented skirts attached. The control and load carrying areas are integer-ally built into the main superstructure in conjunction with the Heli-rotor support structure whereas in the known art the hull is composed of two separate portions, each with their own fan or ductions system for the lift air suspension, with the load carried ona movable platform located between the two pontoons. Loading centre of gravity is critical In this known invention whereas with the present invention the aerostatic support area extends well forward, aft and well out each side of loading area with the above mounted Heli-rotor assembly providing the necessary stability in addition to hull surface. The high above deck mounted horisontal or near horisontal rigid mounting of the Heli-rotor assembly in the present invention maintains the extending rotor blade tips well clear of water or land surface when in forward motion, whereas with the before described known invention the rotor blades are tilted forward to provide thrust for forward movement. This angle is described as. up to 45 forward which bring the fast moving rotor tips close to the ground surface causing hazardous operation and the high risk of catastrophic damage occuring in the event of rotor striking an obstruction, also the pendulumn like support for the hull which the heli-rotor provides in the present invention is lost when the rotor assembly is tilted forward at up to 45 . An important factor with the control of Hovercraft, is "side drift, caused by cross winds to the heading direction, by maintaining the rotor in a near horisontal plane as in. the present invention the ability to equalize this drift by adjustment of the cyclic pitch setting is most effective whereas in the known type with the rotor blade tilted down towards the direction of travel of the vehicle this cannot be accomplished to a satisfactory degree. The present invention has a large hover base area compared to the heli-rotor swept area. The proportion would vary rom 1 to 1 , up to 6 to 1, as. compared to the known inventionwhich has a proportion of a much larger rotor swept area than the area of the twin pontoons. This ratio is part of the necessary helicopter flight characteristics which is claimed for this known in¬ vention.
The present invention is not intended to operate out of aerostatic suspension during motion and is not intended to lift into translational flight at any time due to the dead weight of the vessel at any stage of loading being far over the designed vertical lift capacity of the heli- rotor assembly. Propulsion as a hovercraft supported by aerostatic suspension is solely governed by the degree of cyclic pitch influencing the rotor disc incidence and attitude within a 360 rotation adjustment. Rotor shaft remain in a fixed axis in relation to the hull at all times in a near perpendicular axis. With the vehicle being propelled by the heli-rotor fixed in a. near horisontal state the down wash has a flattening effect on the water surface and able to moderate rough sea conditions overcoming- plough-in and at the same time improving aerostatic lift, moment of hover hull by increasing the ambient air pressure over the lift air fan intakes and adjacent to the external skirt areas to contain leakage and so maintain a high pressure within the plenum chamber of the Hover fuselage body. Rotor down wash lessens and disperses normal hover lift air spray well away from the vessel-improving visability and maintaining a dry superstructure and deck surface.
T e invention has been devised to provide a novel form of amphibious craft capable of manoeuvring over inhospital terrain, water, snow, ice, bog or marsh land in an economical and efficient manner.
The device would have wide application of use, providing a completely new concept to the conventional hovercraft for transport needs, tourist, rescue, artic exploration, agriculture, commercial and defence applications. The heli-hover amphibian would have specific military application in the role of, "Troop assault landing craft", and as "Hover Tanks" for use over snow, bog or marshy terrain, able to manoeuvre from ocean going transport to land mass.
The device can be produced in an economical manner and readily put into service. Further advantages will be aparent from the following description. .According to the invention the device consists of a main flat fuselage body of round, oval or oblong shape which forms the main hovercraft section, attached to the uppersurface of this fuselage body are formed the control passenger and cargo superstructure, which supports the heli-rotor or rotors assembly and tail rotor or rotors and
drive engine assembly, deck area may be open with webbed or formed super structure supporting heli-rotor assembly, standing well above and clear of open deck area. Also incorporated within or adjacent to the main hover fuselage are mounted the lift air fan or fans and drives which supply pressurised lift air to the lower air cushion support cavity contained within the periferal flexible segmented skirts with compartmented under cavity sections equipted with stability trunkated skirts attached to the main hover fuselage. In built static bouyancy is incorporated within the main fuselage structure to support craft when at rest on water and not operating in hover mode. Craft can be produced in various configurations depending on application, using single, co-axial contra-rotating hell rotors as single installation or multiple installations, arranged in tandem, dual or quad formation either as meshing or non-meshing assemblies. Various configurations and design of air cushion support systems and skirts can be incorporated on the underside of main fuselage to provide an efficient hover air cushion base. The invention will now be shown in following drawings in which:- Fig 1. show the top view of a craft with single.heli-rotor. with tail rotor arrangement.
Fig 2. shows Fig 1. in elevation.
Fig 3. shows a perspective view of invention applied to a vehicle ferry or transport vehicle.
Detailed description of embodiment with reference to drawings:-
Identification of indexing of drawings:
1. Main skirted Hovercraft fuselage body.
2. Control cabin superstructure where-in, crew and cargo accommodation is provided.
3. Hatchway providing access to areas in 2. 4. Lift air pressure fan for generating suspensing lift, mounted within hover fuselage.
5. Rear tail rotor assembly.
6. Tail rotor or thruster.
7. Main rotor heli-rotor assembly.
8. Main heli-rotor blades.
9. Trunkated skirts or other known skirt type variations.
10. Vehicle embark or disembarking ramps, retractable, hinged or fixed depending on specific application.
11. Storage deck area, vehicles or cargo.
Figure 1 and 2 shows a preferred application of the invention as conceived,applied to a vehicle or vessel to be used over land, water, swamp, snow, ice or in rough formed guideways as a passenger, cargo carrying transporter. The main hovercraft fuselage body 1 houses the under open mouthed multiple plenum-chambers with their outer periferal and divisional borders arranged in the formulation of trunkated skirts 9. Above the roof of these suspension support compartment are the fan chambers and ducting leading to outlets located in the roof of the suspension compartments to so provide the pressurized lift air generated by the lift fan 4, passing into the distributer com¬ partment and then via the ducting to spaced air outlets located in the ceiling of each plenum compartment and the segmented cones or fingers used on the trunkated skirts 9. These skirts may be independently supplied with pressurised air from a separated fan system, depending on model and application. Main fuselage body 1 has inbuilt ' static bouyancy tanks or foam filled compartment to support the craft when not in hover mode while resting on water. Skids or other fixed or retractable structure act as support means on hard surfaces. The control cabin ' superstructure 2 supports the heli-rotor assembly 7 or can have independent support structure integeral with hover fuselage body 1 depending on model and application. The lift fan assembly 4 providing suspension lift air can be located where shown aft or at any other suitable positon on the superstructure depending on model and application. Craft can have a single heli-lift rotor assembly as shown at 7 or can have a multiple of assemblies arranged in tanden or _uad formation of single or multi-rotor configuration depending on model and application. Rotors blades 8 have collective and cyclic pitch functions similiar to the normal helicopter controls^aft is located the anti-torgue tail rotor assembly 5 which is direct coupled to main rotor by mechanical or hydraulic means, ' : rotor 6 is variably pitched. Both the main rotor and the tail rotor variable pitch characteristics are controlled from the main control station. Rear anti-torque mode can be by rotor or pressurised air thruster. Figure 3 of the drawings shows an application of the concept of the invention to a vehicle ferry or cargo transporter. The embarking or dissembarking ramps 10 can set up
as a retractable or hinged action to act as sea doors when the vessel is in operation.
To those skilled in the art to which the invention relates; many changes in construction, design and widely differing embodiments and applications of the invention will suggest themselves without departing from the spirit and scope of the invention. The disclosures and descriptions herein are purely illustrative and are not intended to be in any sense limiting or being restricted to a precise form.