GROUND-EFFECT HOVERCRAFT VEHICLE WITH RETRACTABLE WINGS

Abstract

A ground-effect amphibious hovercraft vehicle having a system of retractable wings (8), which are retracted (parking mode) by retracting arms (17a and 17b) of both wings by a head (19). At the same time, the vehicle acts as a ground-effect hovercraft vehicle when the wings (8) are extended (flight mode), which is done by extending the arms (17a and 17b) of both wings by the head (19). The head (19) is extended/retracted using a cylinder (22) moved by a drive motor (18), which may be an electric motor, a hydraulic motor or a mechanical motor, or manually using cables and pulleys.

Claims

1. An amphibious hovercraft comprising retracted wings (8) (parking mode), collected by retracting the arms of both wings (17a and 17b) by means of the head (19), is in turn a ground effect hovercraft with extended wings (8) (flight mode), extended by extending the arms of both wings (17a and 17b) by means of the head (19) wherein the head (19) is extended/retracted by the cylinder (22), and mobilized by a drive motor (18), which can be: electric, hydraulic, mechanical, or manual motor, cables and pulleys.

2. The amphibious hovercraft vehicle, according to claim 1, carrying a retractable wing system (8) (parking mode), mounted on a wing mechanism box (20), these wing mechanism boxes are installed and retracted between the base plates (15a and 15b), together with the structural reinforcement (14), make up the wing box, under the chassis or fuselage of the hovercraft.

3. A ground effect hovercraft, according to claim 1, having a wing system (8), extender (flight mode), mounted on wing mechanism boxes (20), which are extended by the extender arms (17a and 17b), extended by the head (19), wherein the head (19) is extended by the cylinder (22), receiving its movement through the drive motor (18).

4. The ground effect hovercraft, according to claim 3, having an extender/retractor head (19), which allows extension/retraction through hinge axes (21a and 21b) of right wing and hinge axes (21c and 21d) left wing.

5. The ground effect hovercraft, according to claim 3, having a system of extender/retractor arms (17a and 17b), which allow to constantly maintain the wing loads (8), received from 25, front and 26, rear beam on the head (19), this in turn by means of upper adjustment and rolling rollers (24a and 24b) and the lower adjustment and rolling rollers (24c and 24d), to upper (15a) and lower (15b) base plates, contributing to its structural reinforcement (14).

6. The ground effect hovercraft, according to claim 3, having a system of upper and lower base plates (15a), carrying a structural joint reinforcement (14), for the housing of the head (19) and the wing mechanism boxes (20).

7. The ground effect hovercraft, according to claim 3, having a system of wing mechanism boxes (20), wherein the wing mechanism boxes (20) are the heads of the wings (8), and in said mechanism box (20), the hinge axes of the wing boxes (16), the hinge axes (23a and 23b) of extender/retractor arms (17a and 17b) are housed, giving stability and reinforcement to the wing boxes (20), the upper adjustment and rolling roller (30a) and the lower adjustment and rolling roller (30b).

8. The ground effect hovercraft, according to claim 3, having flaps (12) incorporated in its wings (8), improving the lift, ailerons (11), which together with the rudder (4b), facilitate and have greater control of turns, winglet devices (13) to eliminate the effects of turbulence that could be generated in the wings.

9. The ground effect hovercraft, according to claim 3, having in wing mechanism box (20), a system for improving the leading angle on the wings (8), formed by a drive pinion (27) that is driven by motor and reducer, a receiving pinion (28), which is integrally joined to (25) front beam of the wing (8), which performs its oscillation sliding in a guide (29).

Description

DESCRIPTION OF THE DRAWINGS

[0012] In order to help its understanding, drawings are attached as an integral part of said description with illustrative and non-limiting character, where the figures and their details have been represented in the following order:

[0013] FIG. 1. Shows the profile of the left side, where 1, is the crew/passenger cabin. 2, engine room. 3, is the duct or fairing of the propeller. 4a, is the drift; 4b, is the rudder. 5a, horizontal stabilizer; 5b, is the depth rudder. 6, bag-type mudflap, throughout its perimeter. 7, finger type mudflap, with inward discharge, front and side perimeter. 8, wing retracted and housed in chassis or fuselage.

[0014] FIG. 2. Shows the rear profile, where 3, the duct or propeller fairing. 4b, are the rudders. 5b, are the depth rudders. 6, bag-type mudflap. 9, vertical discharge finger type mudflap, to prevent the mudflap from collecting or accumulating elements or materials in its circulation. 10, two-blade or multi-blade propeller, since this can vary depending on the size and according to the application model.

[0015] FIG. 3. Displays the floor profile, where 1, crew/passenger cabin. 2, engine room. 3, propeller duct or cowl. 5a, is the horizontal stabilizer; 5b, depth rudder.

[0016] FIG. 4. It shows the profile in plan, showing a view where the object of this invention is schematized, the retractable wings. Where 5b, rudder depth. 8, wings, in retracted and anchored positions (parking mode). 11, aileron. 12, flaps or flaps. 13, Wing tip or winglet devices. 14, structural reinforcement between the upper plate 15a and the lower plate 15b, and in turn serves as a stopper of the wing extender/retractor head system. In this reinforcement are installed the sensors, approach/stop and safety, corresponding to 19, extender/retractor head. 15b, lower base plate, made of marine structural grade aluminum where the entire wing system is supported. 16, wing hinge axis. 17a, retracted position arm of front wing beam. 17b, retracted position arm of rear wing beam. 18, head drive motor. 19, retracted position head of the wing extenders. This system has been indicated that it can be mobilized by the following means, electric, hydraulic, mechanical, or manual by means of cables and pulleys. This all depends on the type of model in question.

[0017] FIG. 5. Shows the profile in plan, showing the extended and anchored wings (flight mode), where 1, crew/passenger cabin. 2, engine room. 3, propeller duct or cowl. 5a, horizontal stabilizer; 5b, depth rudder. 8, wings. 11, aileron. 12, flaps or flaps. 13, Wing tip or winglet devices.

[0018] FIG. 6. It shows the profile in plan, showing a view where the object of this invention is schematized, the extended wings, where 3, duct or fairing of the propeller. 5a, horizontal stabilizer; 5b, depth rudder. 8, wings in extended and anchored position (flight mode). 11, aileron. 12, flaps or flaps. 13, Wing tip or winglet devices. 14, structural reinforcement, between the plates 15a and 15b, and in turn serves as a stop of the wing extender/retractor head system. In this reinforcement two sensors are installed, one for approach/stop and the other for safety, corresponding to 19, extender/retractor head. 15b, lower base plate made of marine structural grade aluminum where the entire wing system is supported. 16, wing hinge axis. 17a, extended position arm of front wing beam. 17b, extended position arm of rear wing beam. 18, head drive motor. 19, extended position head of the wing extenders. 20, wing system mechanism box.

[0019] FIG. 7. It shows part of the detail of the extender/retractor head, the wing system mechanism box, wing hinge axis and wing arm extender/retractor hinge axes. Where, 19, extender/retractor head sectioned, looking at a 21a, hinge axis 17a, of the extender/retractor arm of the front beam of the wing; a 21b, hinge axis of the 17b, extender/retractor arm of the rear wing beam. 22, extender/retractor cylinder. A 8, wing. 16, wing hinge axis. 20, mechanism box. 23a, 17a hinge axis, extender/retractor arm of front wing beam; 23b, 17b hinge axis, extender/retractor arm of rear wing beam.

[0020] FIGS. 8 and 9. They show in front and side detail respectively of the extender/retractor head. Where 19, there is the head with arrangement of its corresponding hinge axes and adjustment rollers of the rolling channels. Where 15a, upper base plate and 15b, lower base plate. 21a and b, 17a and b hinge axes, right wing front and rear beam extender/retractor arm; 21c and d, 17c and d hinge axes, left wing front and rear beam extender/retractor arm. 24a and b, upper adjustment and rolling rollers of head; 24c and d, lower adjustment and rolling rollers of head. 22, extender/retractor cylinder.

[0021] FIG. 10. Shows in detail the inner front of 20, wing mechanism box. Where 8, is wing. 16, wing hinge axis. 25, front wing beam. 26, rear wing beam. 27, variator driving pinion of leading angle of the wing. 28, variator receiving pinion of leading angle of the wing. 29, guide channel, for the displacement of the front beam, according to the leading angle. When some variation of the leading angle is made, the 26, rear beam, is the main axis of support for the displacement of the leading angle.

[0022] Between the front beam 25 of the wing and the hinge axis 23a, this joint is constituted by a hinged axis, so that it can allow the oscillation of displacement by 29, guide channel. This takes all the incidence without losing the support point of 25, front wing beam.

[0023] In 20, wing mechanism box, two sensors are also installed, one for approach/stop and one for safety.

[0024] FIG. 11. Shows in inner and outer front detail of 20, wing mechanism box. Where 15a, upper base plate; 15b, lower base plate. 16, wing hinge axis. 30a, upper adjustment and rolling roller of wing box; 30b, lower adjustment and rolling roller of wing box.

[0025] FIG. 12. Shows lower floor profile (flotation base), where 6, bag-type mudflap, throughout its perimeter. 7, finger-type mudflap, on the side and front perimeter, for inward discharge, increasing the rising chamber. 9, finger-type mudflap with vertical discharge, only at the rear, to prevent the mudflap from collecting or accumulating elements or materials in its path. 31, parking skids on firm surface.

PREFERRED EMBODIMENT OF THE INVENTION

[0026] For its construction, in the basic part of the hovercraft, the construction observations and recommendations registered in the manual Maritime and Coastguard Agency's Hovercraft Code The Hovercraft Code, of the Maritime & Coastguard Agency are counted as references, in order to comply with the requirements of the International Maritime Organization (IMO).

[0027] In the construction or manufacture of the chassis or fuselage of this ground effect amphibious hovercraft, the various materials already known by the technique will be used, as well as glass fiber, kevlar fiber, pvc, polystyrene, polyurethane, aluminum, plywood, etc.

[0028] The drive motor or the rising motor that will be adapted will be those available in the current market, those that can be internal combustion, electric or hydraulic will be those of defined applications, according to applications and needs.

[0029] The cabin is designed for a crew of five, including the pilot, all separated in separate seats with their seat belt systems.

[0030] The cabin is equipped with the command-and-control systems, as well as the signaling and lighting elements that correspond to both the hovercraft and the ground effect vehicle, an alert panel of the installed equipment. The navigation system will be the one that corresponds to the navigation area, as well as its telecommunications equipment, in addition to those required by regulations.

[0031] The cabin is equipped with two side doors in the shape and design of a gull wing, one to starboard and one to port, for better access, both entry and exit. Once closed the doors are watertight, carrying installation of air conditioning, heating and cooling power system, in addition to natural filtered and mechanized external entry. With the crew and propulsion cabins being soundproofed.

INDUSTRIAL APPLICABILITY

[0032] With these improvements it has a wide field of application in the aeronautical industry, in which various materials of light construction will be used. And in the field and its application can be civil (coast surveillance, swamps, rivers, civil protection, rescue), commercial (small air taxi between the coast, other services), military (patrols, reconnaissance), recreation, etc.