DE2201959A1 - Hovercraft - Google Patents

Description

HEI. " \ N.

6 Fti>. '. · -:'. . ,,, j liain 7Ü ckerliu. ';, ·. 27 valley. 51 7079

January 13, 1972 Gzk / pn

William Robert Bertelsen, 2720 31st Avenue, Rock Island,

Illinois, U.S.A.

Hovercraft

The invention relates in the broadest sense to an aircraft and in particular a hovercraft or ground effect vehicle. These vehicles move generally said on a cushion of air or some other compressible gas between the vehicle and the surface is held over which the vehicle is traveling. The vehicles can look over very different surfaces move, for example water, snow, ice, earth or paved road surfaces. The supply of compressible Gas is usually provided by a turbine or a blower motor; the gas is drawn through an opening in the Platform or deck of the vehicle in a collection chamber pressed, which is closed by a flexible apron that hangs down from the vehicle deck and the vehicle essentially surrounds. So far there have been difficulties in the construction and operation of such ground-effect vehicles, mainly due to the fact that the movement of the vehicle could not be properly controlled. the Directional stability and inability to inflate movement around the vertical axis (yaw, e> > dor vehicles are inadequate, because there is no direct frictional contact between the vehicle

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and the surface it travels over. Previous attempts to create a control for such directional stability and orientation made use of a tail unit, swiveling propulsion fans, discharge openings, changes to the apron shape and various combinations of these measures. These attempts led to designs that were complicated in their construction, but not in their mode of operation are satisfactory and expensive to manufacture. If an attempt was made to use the lifting gas for control, for example by means of discharge openings or changes the apron shape, it was generally found that the lifting gas did not exit with sufficient speed to be effective Enable control. The use of a tail unit or swiveling drive fans, also in combination, is likewise unsatisfactory, especially because of the property of the vehicle to act as a wind vane, in particular when the vehicle is hovering or traveling at low speed with a tailwind. In those cases where the jacking is caused by one or more large propellers, which are mounted high above a deck, the propulsive force acts on a long lever arm above the center of gravity and leads to considerable stomping of the vehicle Forces, or in the case of the pivoting propellers, forces that cause pitching and rolling. These forces are trying to push the nose of the vehicle downwards and / or the vehicle to the side at a high point of attack Force so that the vehicle "plows" or rolls. This attribute is particularly undesirable when a conventional hovercraft drives over moving or churned water.

The inherent quality of hovercraft, itself to move in all directions, both horizontally and horizontally with a rotation of the vertical axis, leads to difficult control? »· Problems with sloping surfaces. Considerable force must be applied to the suspended vehicle just to

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in the case of an inclined surface, for example a mountain slope, to maintain the air cushion, is also one additional steering effort required to achieve the desired orientation to maintain the vertical axis of the vehicle on these surfaces. In summary, it follows that at inclined surface, the gravitational forces that act on the vehicle are overcome by larger counteracting control forces must be available to the pilot of the vehicle to drive such a vehicle on an inclined To hold surface and drive up such a surface.

Maintaining the alignment around the vertical axis of the vehicle on uneven terrain also leads to a complex issue Control problem. For example, if the vehicle is driving over an uneven surface, the front end of the vehicle may move on a right sloping surface and the rear of the vehicle on a left sloping surface are located. Such a relationship of the vehicle to these surfaces will cause a right turning moment, that acts on the vehicle around the vertical axis. Therefore, in this example, the pilot must for optimal control in the Be able to move the front end of the vehicle to the right or left regardless of the unevenness of the terrain, and accordingly it must have sufficient counteracting forces to prevent the movement of the rear end of the Control the vehicle under all operating conditions. In another example, the pilot must look for an optimal Control possibility via sufficient counteracting side force at both the front and the rear end of the vehicle to keep the vehicle on a mountain slope. In addition, if a forward or Backward movement along the l.crghange.s is desired, sufficient Propulsion forces required, ebonso wio the one mentioned counteracting forces.

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In accordance with the present invention, the described problems and difficulties of known hovercraft are eliminated substantially overcome and it becomes an effective control for directional stability and the Alignment around the vertical axis (yaw alignment) achieved. A hovercraft according to the invention has one Drive device, which generates a gas flow, and a gimbal-mounted flow guide device, by v / ahlweise directing part of the gas flow into a plenum chamber located below one provided on the vehicle Platform is arranged. Said flow control device can be moved due to its cardanic suspension in such a way that it can unravel part of the gas flow outwardly over the vehicle platform so that the gas flow has a horizontal component in any desired Has direction and thus generates a thrust or a control component in any desired horizontal direction, whereby Gas is used directly by the flow guide device. Thanks to the all-round swivel or cardanic Suspension, the thrust can be sized as desired by changing the strength, in each case Direction around the vertical axis. The vehicle can be turned on the spot or instantly a push if desired Get the size to the front, back or in any side direction as desired. When vehicles according to this invention, the flow guide devices at the front and rear end, drive on a curve, the forces can are controlled around the roll axis in such a way that they at least partially counteract the natural tendency of the vehicle, to roll to the outside of the curve, so that the possibility of rolling over when cornering is reduced will. Even with just a single flow control device grip the forces around the roll axis, those of the operator counteract, on a much shorter lever arm than ii Fall of the high-mounted propellers.

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According to a preferred embodiment of the invention, there are several pivotably suspended flow guide devices provided, for example near the front and rear of the vehicle, in order to have the best possible control of the To reach the vehicle, as will be described in more detail below.

According to another embodiment is a single pivotably suspended flow guiding device is provided. Although the control of this type of vehicle is not as adaptable is like several flow guiding devices, has the design with only a single flow guiding device the advantages of simple construction, easy control and Operation, so / ie the lower cost and the lower weight.

In a particular embodiment according to the invention a hovercraft (ground-effect vehicle) provided with gimbaled motor-fan units, which are close to each End of an elongated base platform are provided. If the discharge direction of the blower is downwards, effect the motor-blower units only have a lifting force for that Vehicle. If the motor-fan units are inclined in the same direction, they can propel the vehicle effect forwards, backwards or sideways to the right or left · If the motor-blower units are opposed are aligned, a controlled turning, yawing and rolling of the vehicle can be achieved. The motor-fan units not only provide the lifting force, but also a partial bypass flow in their cardanic suspensions when inclined, the one horizontal component in a 360 ° selectable direction, while at the same time the one required to lift the vehicle Pressure is maintained by the rest of the flow. Consequently control forces for the vehicle are available to the pilot

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Available equal to half of the total available propulsive force at each end in any horizontal direction while maintaining sufficient lifting capacity for the vehicle.

The drive devices for generating the gas flow can be of different types, for example a motor with a fan, a turbine or other. The drive devices can be carried by the flow guide devices as described below, or they can be arranged separately and, for example, with a flexible line can be provided to guide the gas flow to the flow guide device. In the case of several Flow guiding devices can be provided for each a separate drive device, or a single one Drive device can supply a gas flow for several flow guide devices. The drive devices, which supply gas flows to the flow guiding devices can be provided independently of other devices, that only deliver lifting gas. For example, an or multiple motors can be used to deliver only lifting gas, while one or more additional motors provide a gas flow for gimbal-mounted flow directors.

In a further embodiment of the invention, an eyelid-like device is provided for the flow guide device or spherical shell device to use, so that the lifting gas that flows through a duct into a collecting chamber below the platform is directed, can not escape from the collection chamber if the otrömungsleitvorrichtung so aligned is that otherwise there would be an opening between part of the guide shaft and the environment.

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The aim of the invention is to create an improved hovercraft, in particular with improved control options.

In particular, it is an object of the invention to provide a hovercraft to create, with a platform, drive devices for generating a gas flow, flow guiding devices for controlling and directing the gas flow and with a device to the flow guiding device so hang up so that part of the gas flow above the platform can be diverted in any desired direction, to achieve control and thrust for the vehicle.

It is also an object of the invention to provide a hovercraft with a platform, with a control device to control the vehicle position in relation to the transverse, vertical and longitudinal axes (pitch, yaw and roll axes), and with an all-round pivotable device for fastening the control device to the platform; the vehicle should too Have propulsion devices. According to a further object of the invention, the propulsion devices can also at the same time be the control devices mentioned. The aim of the invention is also to provide a hovercraft with a Platform, a control device and a lifting device to generate a lifting force for the vehicle and the control the vehicle position to effect the transverse, vertical and roll axis, with a cardanic suspension device for the lifting and control device on the platform

Another embodiment of the invention provides a hovercraft with a platform and propulsion formed by a uniform device. ¹ .-, lifting and control device for the vehicle and with a cardanic suspension for two Ivlotor blowers on the platform, whereby the motor blowers in the cardanic device are movable to

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to effect the propulsion and control of the vehicle around the transverse, vertical and longitudinal axes.

Air cushion vehicles are described with a drive device for generating a gas flow and with gimbal-mounted flow guiding devices to selectively the To direct gas flow so that a lifting component and a thrust or control component is created. The thrust or steering component acts directly from the flow directing device and is applied over the surface of a deck or platform directed. Embodiments are described with one or more motors, as well as spherical shell devices that are equipped with the flow directors cooperate to reduce the loss of lifting gas. A hovercraft is in the DOS 1 959 474 described.

Further features, advantages and possible applications of the invention emerge from the following description of exemplary embodiments and the drawing, the same components being provided with the same reference numerals.

Show it:

Fig. 1 is a side view of a preferred embodiment of the invention of an air cushion or Ground effect vehicle,

FIG. 2 shows a plan view of the embodiment according to FIG. 1,

Fig. 3 is a front view of the embodiment according to. 1, .

Fig. 4 is a perspective view of the fuselage of the embodiment form according to FIG. 1,

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Fig. 5 is a partial sectional view taken along the line 5-5 of Fig. 2, parts having been removed for the sake of clarity,

6 shows an enlarged partial view along the line 6-6 in FIG. 2, partially interrupted for a better overview.

7A is a schematic view of a preferred embodiment of the controls shown in FIG Connection with the controls according to Fig. 7J3 can be used to move forwards or backwards of the vehicle according to Fig. 1. to effect,

7B is a schematic view of a preferred embodiment of the controls for rotational movement to effect the vehicle according to FIG. 1,

Fig. 8A is a schematic view from above to explain the operation of the controls according to Fig. 7Λ, to cause the vehicle to move forward according to FIG. 1,

8B is a schematic side view of the vehicle according to FIG. 1, which shows the operation of the controls according to FIG. 7Λ, to a forward movement to effect the vehicle according to FIG. 1,

Fig. 9Λ a schematic plan view of the vehicle according to FIG. 1, wcIc into the operation of the controller according to Fig. 7Λ shows to cause a backward movement of the vehicle,

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Fig. 9B is a schematic side view of the operation the controls according to Fig. 7Λ to cause a backward movement of the vehicle according to Fig. 1,

Fig. 10A is a schematic plan view for explaining the operation of the controller according to FIG To cause the vehicle to turn to the left according to FIG. 1,

10B is a schematic front view for explanation the operation of the controls according to FIG. 7B, to allow the vehicle to turn to the left according to FIG. 1 to. cause,

FIG. 11 is a schematic view for explaining the operation of the controls according to FIG. 7 to cause a lateral movement of the vehicle according to FIG. 1,

Fig. 12 is a schematic view for explaining the operation of the controls of Fig. 7B to to cause a rotary movement on the vehicle according to FIG. 1 about its vertical axis,

13 shows a side view of an embodiment according to the invention a hovercraft with only one engine,

14 shows a plan view of the embodiment according to FIG. 13,

15 shows a side view of a flow guide device with ball socket devices, and

16 shows a side view in section to explain the mode of operation of the device according to FIG. 15.

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Figures 1 and 2 show an air cushion or ground effect vehicle V according to the invention. In Fig. 1, a platform or deck 20 is shown which is a closed Cockpit 22 and a flexible apron 24, open at the bottom, which receives and directs the lifting air. the Apron 24 is attached to deck 20 and surrounds its periphery, as can be seen from FIG.

The forward end of the deck of the vehicle carries an axial motor-fan unit 26 (Fig. 2), and in a similar manner the aft end of the deck 20 carries an axial motor-fan unit 28. The rotor fans 26 and 28 are axial aligned with the longitudinal axis of the deck 20.

The front engine fan 26 is mounted in a gimbal unit 30. Similarly, the rear IJotor fan is 28 fastened in the same cardan unit 32. The cardan assemblies 30 and 32 each have a casing 34 or 36 on. The front shroud 34 is mounted in a pivotable gimbal ring 42 for rotational movement at 38 and 40. The ring 42 is attached for pivotal movement to upright supports 44 and 46 (FIGS. 1 and 7B) that are attached to the deck 20 are connected.

The rear motor fan 28 is mounted in the shroud 36, which in turn is rotatable at 48 and 50 in one Gimbal ring 52 is attached. The gimbal ring 52 is for pivoting movement on upright supports 54 and 56 (Figs. 1 and 7B) connected to the deck.

In accordance with the teachings of the present invention, the two motor fans 26 and 28 bring air downward, as shown by the arrows in solid lines in FIG OII fan blades ¹ and 60 are located in a horizontal plane, as shown by the dje.s shown in full lines Ummantclungen CM and 36 in Fig. 1

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If both the shrouds and the motors are tilted, as indicated by the shrouds shown in dashed lines 34 and 36 illustrated in FIG. 1, a partial fan jet is generated as indicated by the dashed lines in FIG Lines shown by arrow segments is illustrated in Fig. 1, with the beam horizontal and backward is guided, whereby a forward propulsion movement is exerted on the vehicle, while sufficient lifting force along with the remaining air force generated by the engine fans.

Fig. 3 shows in solid lines the motor fan 26 in a horizontal position. Through the dashed Lines in Fig. 3 shows the rotation of the motor fan 26, the shroud 24 and the ring 42 about the longitudinal axis of the Vehicle shown within predetermined limits to provide lateral thrust or propulsion to the vehicle, so that the vehicle is rotated to the left about its vertical axis, as shown in FIG. The motor fan 26, the shroud 34 and the ring 42 can also be rotated about the longitudinal axis of the vehicle in order to effect that the vehicle rotates to the right about its vertical axis, as illustrated in FIG. Such a rotation of the The engine, shroud, and ring separates the air vented from the engine into two components, a buoyancy component directed below deck 20 and one Rotary drive component directed over deck 20. Thus, according to the present invention, both a Vehicle directional control and yaw axis orientation as well as lift forces are provided.

Fig. 4 shows a preferred inner hull 70 of the. Vehicle. The fuselage 70 may be molded from fiberglass in order to to make the weight of the vehicle easy. The Kr nf

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has a peripheral wall 90 and two mounting platforms 72 and 74 which are opened at 76 and 78 to the Cardan units 30 and 32 to be included. Between the platforms 72 and 74 there is a recess 80 which passes through the side walls 82a and 84a and through the platform walls 86 and 88 is limited. The recess 80 is provided to accommodate the cockpit equipment, such as the controls, the The driver's seat, electrical equipment, etc. It is noted that in this construction the recess a storage or load space in a low one The center of gravity in the geometric center creates something results in a lower silhouette, which is especially important for military use cases.

As FIG. 5 shows, the deck 20 is secured in the walls 82 and 84 by means (not shown). the Y / ends 82a and 84a extend the length of the vehicle in parallel to its longitudinal axis. It can be seen that the fuselage 70 has curved surfaces at its front and rear ends is provided

As can be clearly seen from FIGS. 5 and 6, an edge 91 of the flexible skirt 24 is on the deck 20 and the hull v / and 90 is on Attaches to the perimeter of the fuselage and extends down to the bottom edge 93 to form an open-bottomed skirt form. The skirt 24 is connected at 95 to an inner flexible skirt 92 which surrounds and defines the vehicle together with the outer skirt 24 and the fuselage walls 82 and 84 a first air collection chamber 97. The skirt 24 and the inner skirt 92 act with a bottom skirt 96 together to form a second plenum chamber 104 which is divided into lifting air outlet chambers 104a by vertical partitions 104b is subdivided to regulate the exit of lift air from the first plenum 97. The lift air occurs

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as shown by the arrows in FIGS. 5 and 6, from the motor fan 26 into the space 76 a. A part of Air then fills the first plenum 97 and flows from there through the opening 94 to fill the second chamber 104 and to form the lift force for the vehicle. A second portion of the air is distributed from space 76a to the area 77 to fill between the recess 80 and the bottom skirt 96; this air flows through the openings 102 in the Floor skirt 92 to the second chamber 104 and supports the lifting air there. It can be seen that Figs. 1, 2, 3, 5 and 6 show the vehicle under conditions when full lift air force is applied and the apron is inflated * It will also be appreciated that other apron constructions can be used to contain sufficient air so that the air cushion requirements of the vehicle are met.

7A shows an embodiment of the control device for carrying out the simultaneous pivoting movement of the gimbal unit motors 26 and 28 and the casings 34 and 36 about an axis perpendicular to the longitudinal axis of the vehicle in the same directions in order to provide movement control of the vehicle in the axis of rotation and a drive . It will be recognized that other controls can be used to effect movement of the gimbals and uramans either simultaneously or separately. Fig. 7A shows a ¹ control stick 110, which is movable about a pivot point 112. On the joystick 110, one end of a cable 114 is attached at a point 138. The cable 114 runs over a disk 120 and through a protective housing 128 which is carried by the cardan ring 42. At a point 124, the cable 114 is fixedly connected to an arm 126 which is supported fixedly connected by the sheath 34. From the point 124, the cable 114 leads to another housing 122 and returns to the connection point 138 to form an endless loop *

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The control stick 110 is also connected to an endless abrasive ene cable 130 which leads to a pulley 132 by a protective housing 134 which is supported by the rear ring 52nd The cable 130 is fixedly connected at a location 135 with an arm 136 which is fixedly supported on the casing 36th From the point 135, the cable leads into another protective housing 137 which is carried by the ring 52 , and returns for connection to the joystick 110 at the point 138.

Thus, by moving the control stick to the right, as shown in FIG. 7Λ, the cable 114 will move the arm 126 to the right, as shown in FIG. 7Λ. Due to its fixed connection to the casing 34 of the arm 126 causes the sheath 34 to rotate about its horizontal axis in Fig. 8B position. As a result of this rotation , the casing and the motor separate the air released by the motor into two components: 1. A lifting component, which leads into the apron 24, and 2. a second component, which exerts a propulsive force on the vehicle.

Conversely, if the joystick 110 is moved forward or to the left as shown in FIG. 7A, the cable 114 will rotate the arm 126 to the left as illustrated in FIG. 7A and the motor 26 and shroud 34 about their horizontal axis tend to be the position shown in Figure 9B, whereby the air discharge is effected from the motor 26, to form two components. 1. a lift component, which leads into the skirt 24, and 2. a second component which has a rear . exerts forward propulsive force on the vehicle.

If the control stick 110, as shown in FIG. 7A, silt up with the sheaths 34 and 3G, the forward movement of the control stick 110 (see arrows) becomes a movement

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or rotation of the motor 28 and the casing 36 simultaneously. With the motor 26 and the casing 34 to cause to generate an additional forward movement, as shown in Fig. 8Λ. If the joystick is similarly as shown in Fig. 7Λ, via the cable 130 to the rear arm 136, the rear motor 28 and the jacket 36 connected, the rear motor 28 and shroud 36 will rotate simultaneously about their horizontal axis and rotate in the same direction as the motor fan 26 and shroud 34, as shown in FIG. 9B, to point to a opposite movement of the control stick 110 (see arrows) an additional backward drive force on the Vehicle while maintaining adequate air delivery for lifting purposes.

The resolution of the component forces of the motor fans 26 and 28 under the influence of the control system (Fig. 7A) creates sufficient lift for the vehicle and also sufficient forward or reverse propulsion for the Vehicle.

Referring to Figure 7B, one embodiment of the controls for the Pivoting movement of rings 42 and 52 illustrated to accommodate movement of the vehicle about its yaw and roll axes steer. In order to pivot the ring 42 about its horizontal axis, it is, as stated above, pivotable in the carrier 44 and fastened in the carrier 46. The ring 42 is provided with an extension 140 which has a pair of rocker arms or arms 144 and 146 connected. Attached to rocker arms 144 and 146 is a cable 140 which is a drive shaft 150 surrounds. The drive shaft 150 has a Steuo.rrr> 0 152 firmly attached to it.

If the steering wheel 152 is threatened to the right, like pus Fii; ·. 7 ¹ J can be seen, then it is effected, dni.> The ring A ^. to scino

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Horizontal axis rotates to the right and the casing 34 and the motor 26 takes with it. Such a rotary motion causes that, as shown in Fig. 10Λ, the air jet from the Kotor divides into two components: 1. A buoyancy lioiirpononte, which leads into the apron 24 and 2. a rotary component which runs perpendicular to the longitudinal axis of the vehicle around the Rotation of the vehicle to the right to effect its vertical axis, such as. can be seen from Fig. 10A.

In FIGS. 10A and 10B, it is assumed that the gimbal unit 32 is held in a position in which it either exerts lift forces only or both lift and forward or reverse propulsion forces on the vehicle.

To control the movement of the ring 52 (FIG. 7B), the ring is received in a front bracket 54 and a rear bracket 56 which are supported by the deck 20, as previously stated. The ring 52 has an extension 156 which carries two arms Ϊ58 and 160. A cable is attached to the arm 158 and traverses a cable 164 carried by the arm 160. The cable 162 runs under a disk 166 and the cable 164 under a disk 163. The cable 162 also runs over a disk 170 and is connected at 171 to a foot pedal 172 which is rotatably mounted ^{on a rod 174;} and a foot pedal 172 are connected to a spring 176 which is attached to the torso 70 at 178. Similarly, the cable 164 leads from the disk 168 around a disk 180 and is connected to a foot pedal 184 at 1SJ2 which is also independent is rotatably attached to the rod 174. The cable 164 and foot pedal 184 are connected to a spring 186 which is attached to the torso 70 at 188.

The forward movement of the Podr.les 172 causes the arm 158 moves down about the axis of rod 156 and causes ring 52 to move to the left, as in Figure 7B shown i «t. The movement of the ttingßü 52 to the left :; causes that the engine 28 and the Umi.ianteluni; · 3G also :, after

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move to the left, which separates the air discharged from the motor 28 into two components: 1. One component behind left and 2. a drive component.

Conversely, the forward movement of the pedal 184 causes the ring 52 rotates about its horizontal axis to the right, as shown in Fig. 7B, and the motor 28 and the Sheath 36 takes with it. Such movement of the ring 52 causes the air discharged from the engine to split into two Separate components: 1. A lifting component and 2. a driving force component, which move the vehicle to the right as can be seen from Fig. 7B.

It can therefore be seen that when both rings 42 and 52 in pivoted in the same direction, a lateral force is exerted on the vehicle causing the Vehicle moves laterally to the right or left of the longitudinal axis of the vehicle, the same will happen if the Rings 42 and 52 are rotated in opposite directions which cause driving forces generated by motors 26 and 28, that the vehicle moves around its vertical axis either to the right or to the left, depending on the difference in angle of rotation of the rings 42 and 52 in opposite directions.

As can be seen, the controls of FIG. 7B effect both the yaw and roll control of the vehicle. It can also be seen that the controls of FIGS. 7Λ and 7B are combined can be applied to the directional stability of the vehicle with respect to the yaw, roll and roll axis of the same and also simultaneously provide both propulsion in either the forward or reverse direction while the lift forces retained for the vehicle.

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In Figures 13 and 14 is an embodiment of the subject of the invention shown with a single gimbal device. This embodiment is the same in many respects the vehicle shown in Figs. However, there is only a single gimbal assembly 201 near the stern of the Arranged vehicle. The gimbal assembly 201 carries a motor 202 and a fan 203; their way of working is similar in many respects to the devices previously described for a vehicle with two gimbals. The. Gimbal device 201 can be controlled by a control device from the operator's seat 204 are to air over the platform 205 in each direction about a vertical axis through the gimbal device 201 blow out. The amount of air that is blown out over the platform can be changed by the operator are by the gimbal device 201 is controlled so that a propulsion or a steering movement or a Combination of both is achieved while maintaining the necessary lift for the vehicle. In which Shown embodiment, the cardan device is added to supports 206 and 207, so that the first Pivot axis is arranged transversely to the longitudinal axis of the vehicle. Pivoting back and forth around the The first pivot axis for controlling the thrust can be done by hand control, or a servo motor can be used preferably from the operator's seat

t can be actuated off. Pivoting around the second pivot axis to generate a rotation or lateral forces can be effected, for example, by the control wheel 208, wherein a conventional timing gear connection can be used.

As shown in Fig. 13, the edge of one opening is from the platform 205 in the Uubgaskammer forming line.sßchachtei-5 because of the inclined arrangement of the walls 212

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the deck 205 tilted out of the horizontal plane. This serves two different purposes. First, the raised one acts Wall 212 as an air-catching vane during the forward movement of the vehicle, v / o by providing additional lifting gas. Second, the beveled edge creates the ability to that there is a greater horizontal component than that at the initial forward thrust adjustment The case would be with a flat edge.

As shown in Figs. 13 and 14, an operator seat 204 and a control panel 209 are arranged so that that they can slide back and forth on rails 210 and 211 within the vehicle. The timing gear connection and the instrument lines (not shown) can be in a flexible line, also not shown, like an umbilical cord, to be connected to the control panel, around a. To enable movement of the control panel. These Forward and backward movement of the oitzer. 204 for the The operator and the i'.O9 control panel make this possible Trimming in the longitudinal direction around the transverse axis of the vehicle.

The vehicle shown in FIGS. 13 and 14 is not quite as flexible in its control options as Crr. ge,.: According to Figs. 1 and 2. However, it has almost the same advantages as the aur, leading to five. ^r ; fovn according to FIGS. 1 and 2 ; this also includes the ability to steer by means of Ltrömung.sleiteinrichtung that can direct a gas flow over a platform in any direction. In addition, the device has like Fip. 13 and 14 have considerable advantages in terms of practicality, weight, simple construction and simple operation.

It has been shown that the design according to Fir · ;, l.'i and 1Ί with only one Hotor still /, in r j erienstell * -mlcr works, venn the flexible apron an oau *> olkn :::!: ior xuv <<; ■ -au Lna'ime

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has, which extends substantially over the entire length and Extends width of the deck and has a bottom closure as well as a distribution device, which the lifting gas on the collecting duct more or less uniformly distributed over the circumference of the flexible apron.

Another inventive feature aims to reduce the loss of lifting gas from the lifting gas chamber during operation of the vehicle. V / ie shown in FIGS. 15 and 16, the cardan device or swivel device 201 has spherical shell devices 213 and 214 which act like eyelids fit the opening 216; they are shown pivotable about the first pivot axis of the cardan device 201. The spherical shell devices 213 and 214 move with the casing 217 so that they close off those areas which would otherwise constitute an opening from the lifting gas chamber to the atmosphere when the casing 217 is pivoted as shown in FIG. 16 to provide thrust produce. As can best be seen from FIG. 16, the spherical socket 214 has an enlarged hand 219 which can touch the deck 205 and limits the movement of the spherical socket 214 when the casing 217 is pivoted to an extreme extent, with a large section of the duct 216 being closed and loss of ilubgns is avoided. Ball shells 213 and 214 are preferably spring loaded to maintain them in contact with stops 221 and 220 at the top of shell 217 until shell 217 is pivoted and in contact with deck 205 when the shell pivots very far will. A single spherical shell could be used, or an additional one; Pair could be arranged so that it is movable about the second pivot axis and to reduce the lifting gas loss during

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the rotary motion leads. The spherical cup or eyelid device can also be used advantageously in the design according to FIG. 1 with several motors.

The invention has been described in the foregoing described on the basis of exemplary embodiments without, however, being limited to these exemplary embodiments;

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Claims (17)

Claims Hovercraft with a platform, a lifting gas chamber underneath the platform with a circumference thereof delimiting flexible apron and marked with a drive device that delivers a gas flow by controllable flow fluid devices to direct at least part of the flow and one on all sides pivotable device (cardan device), which carries the flow guide device, so doß a desired Part of the gas flow can be directed so that it is above the platform with a horizontal component exits in any direction around a vertical axis through the flow guide device and thus a control allows that uses the gas flow directly from the flow guide device. 2. Hovercraft according to claim 1, characterized in that the vehicle has several spaced apart Has Kardaneinrichtuncen, each having a flow guide device wear. 3. Hovercraft according to claim 1, characterized in that that the platform has upright support devices for receiving the cardan devices. 4. Air cushions! r.hrzeu ", according to claim 1, characterized in that that the. "- trümunr;:". guiding device at least one Kugelr.chalen- (eyelid) Has device, which with the otrömungslfitvorri c ', 1) cr.ve ;; b; u' and is suitable for the Vorlust - ^ n Kubgas only to decrease the liubiinskr.nner. - 24 - 209833/0041 IAD ORIGINAL 5. Hovercraft according to claim 4, characterized in that that the flow guide device has a plurality of spherical shell devices, each of which has a stop to limit the movement of the spherical shell device to a predetermined amount. 6. Hovercraft according to claim 1, characterized in that the platform is elongate and protruding upwards Has support devices for the cardan devices, wherein the first pivot axis of the cardan device is transverse runs to the longitudinal axis of the platform. 7. Hovercraft according to claim 3, characterized in that the platform has an opening and the flow guide device has a sheath disposed at least partially within the opening when the casing and the platform are in a horizontal position. 8. Hovercraft according to claim 7, characterized in that the drive device comprises a motor and a fan which emits a powerful air flow that the motor and the fan inside the casing and with these are arranged connected, whereby a "pivoting the casing to pivot the IJotors and the fan and a corresponding pivoting of the strong air flow. 9. Hovercraft according to claim 1, characterized in that an adjustable £ Jitz is provided to adjust the trim properties to improve the vehicle. 10. Hovercraft according to claim 9, characterized in that that there is a movable; control station to which the seat of the operator, control units and control devices belong, movable as a unit r.iiicl. 209833/0041 BATH ORIGINAL 11. Hovercraft with an elongated platform, a flexible apron that surrounds the platform and is connected to its periphery, characterized by a drive device for lifting, driving and controlling the platform in its position to the transverse, longitudinal and vertical axis and upwardly projecting Gimbals on the platform and gimbals pivotally connected to the girders for attaching the gimbals to the platform. 12. Hovercraft according to claim 11, characterized in that the cardan device has a pair of rings, pivotally connected to the beams with one of the rings adjacent each end of the platform is arranged. 13. Hovercraft according to claim 12, characterized in that the cardan device has a pair of sheaths, wherein one shell is pivotally connected to one of the rings and the second shell is pivotable is connected to the second ring, and wherein the sheaths have a pivot axis on v / iron that is perpendicular to the Pivot axis of the rings is arranged. 14. Hovercraft according to claim 13, characterized in that the platform is a pair of spaced apart Has openings which are arranged adjacent the ends of the platform that the Uramantelungen of the Rings hang down with the lower portion of the sheaths positioned within the openings when the Sheath occupies a horizontal position. 15. Hovercraft according to claim 14, characterized in that the drive unit: has a pair of motors and fans which can emit a powerful air flow, including one of the motors and fans within the - 2G 209833/0041 first casing and connected to this is arranged that the second motor and the fan inside the second casing and is arranged connected to it, whereby a pivoting of the rings and the Sheaths a pivoting of the motors and fans and a corresponding pivoting of the powerful air flow has the consequence. 16. Hovercraft according to claim 15, characterized in that it comprises a control device which is in direct communication with the rings and shrouds to control the movement of the vehicle, and that the control devices can be operated so that the powerful air currents are optionally directed that they have a lifting component directed under the platform and a drive and Control component that extends across the platform. 17. Hovercraft according to claim 16, characterized in that the control devices are separated and are optionally actuated to the air flows in any Direction in a range of 360 ° around the vertical axis. 209833/0041 Blank page