DE1947944A1 - Vertical takeoff aircraft - Google Patents

Description

PATENT LAWYERS DIPL-ING. CURT WALLACH DIPL.-ING. GÜNTHER KOCH 1947944 DR. TINO HAIBACH

8 Munich 2, September 22, 1969

OUR SIGN:

Rolls-Royce Limited, Derby, Derbyshire, England vertical take-off aircraft

The invention relates to a plug tool which is able to take off and land vertically and is equipped with an engine system for this purpose, the lift forces on the Plug stuff exerts independently of those lift forces generated by the aerodynamic wings of the plug stuff during forward flight be generated.

According to the invention is a twin-fuselage aircraft in which the Hulls side by side are rigidly connected in designed in such a way that each fuselage is provided with an outwardly directed wing, the lift forces on the plug stuff exerted during forward flight while engines in the Space between the hulls are mounted so that they are movable between positions in which the drive thrust in either Horizontal direction and / or directed downwards, the engines being mounted so that when the thrust is downwards is directed, the shear vector runs through the center of mass of the plug tool.

The two fuselages are preferably connected to one another by an aerodynamic body which, during the forward flight of the

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" ² " 19A7944

Plugzeuges generated aerodynamic lift forces. The hulls can can also be connected to one another by a component that forms the horizontal stabilizer of the aircraft.

The thrust generating means are preferably mounted on a component, which extends between the hulls and is streamlined is so that lift forces are exerted on the plug stuff while it flies forward.

The thrust propulsion means preferably consist of at least three jet thrust gas turbine engines which are centered around the center of mass of the Plugzeuges are arranged around so that their thrust vector through passes through this center of mass. The gas turbine jet engine can be a turbofan engine or it can have a gas generator that is drivingly connected to a fan that is wrapped around the housing of the gas generator.

Means are preferably provided for the longitudinal inclination movements, to control the rolling movements and the movements around the vertical axis.

An exemplary embodiment of the invention is described below with reference to the drawing. In the drawing show:

Fig. 1 is a plan view of one formed according to the invention

Aircraft,
FIG. 2 is a perspective view of a taken along line II according to FIG

Fig.l sectioned aircraft,
Flg. j3 a perspective view corresponding to FIG. 2, in which the thrusters are arranged with their axes in the horizontal direction and not in the vertical direction, as in FIG. 2.

With the reference numerals 10 and 12, the two fuselages of the double-fuselage aircraft designed according to the invention are designated, which are parallel., Mutually spaced so that a space remains between them.

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~ ^? ~ 19A794A

The fuselages are connected to one another by a wing 14, which is located in front of the center of mass of the two hulls IO and 12 and also the connection of the two hulls at the tail end is made by the horizontal stabilizer 16. Each hull carries on its outside also has an airfoil 18 and the two airfoils 18 are connected to one another by a through the airfoil 14 extending Spar 20 connected, wherein the central wing section .14 is fixed at both ends of the spar 20, which the wing on the hulls 10 and 12.

The middle wing 14 is provided with port sets 22 at each end, which extend to the rear of the hull and define a space between the hulls. A pivotable one Shaft 24 extends to port sets 22. A streamlined housing 26 surrounds and supports shaft 24 four gas turbine jet engines 28, which are arranged so that when they are in their lift position shown in Pig. 1 and 2, its thrust vector through the center of mass JO of the plug tool runs through, so that the engines on the plug stuff lift forces that are independent of those created by the aerodynamic surfaces during forward flight.

Means, not shown, are provided to cause the shaft 24 to rotate so that the thrusters 28 are out of position according to Pig. 2 can be transferred to the position according to FIG.

The thrusters 2δ. Can either be pure jet engines, but they are preferably turbofan engines or fan engines in which a fan is driven by a gas generator.

If the aircraft is to take off from the ground, then the engines can be started while they are still in the position according to Fig. 3, i.e. with their air inlets facing forward, while the thrusters point backwards. Then the instinctual

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plants run up until they almost generate take-off thrust, thus reducing the soil erosion that would occur if the Engines with their thrusters would be directed downwards.

The engines can then be moved into the position shown in FIG and when the take-off thrust is generated by the engines, the plug stuff lifts itself off vertically while it moves with its Longitudinal axis is still parallel to the ground. When a predetermined height of the plug stuff is reached at which the transition from Vertical flight is to be performed on the forward flight, then the shaft 24 is rotated so that the engines from the Move position according to Fig.2 in the position according to FigO.

During this movement, the thrust jets of the engines are released from a Position in which they are only directed downwards into a position in which they are directed downwards and backwards and at this point the aircraft begins to move forward and it is supported by the airfoils 18 and the airfoil sections 14 and 14 26 creates an aerodynamic lift. Then the thrusters are moved progressively into a position in which their propulsion jets follow are directed rearward, the lift on the aircraft being caused solely by its aerodynamic surfaces.

When the aircraft lands, the shaft 24 is rotated so that the engines move from the position shown in FIG. 3 into the position according to FIG. 2 and hears during this movement the aerodynamic lift and the aircraft is only carried by the lifting forces generated by the engines.

In order to support the stability control ^{4 of} the aircraft during the vertically downward flight, nozzles are provided at the tips of each wing and also in the nose and tail of the aircraft and these nozzles are supplied with air drawn from the compressor of the engines 20. In addition, laterally directed nozzles can be provided in order to effect control around the vertical axis of the aircraft.

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Claims (1)

Patent claims: 1. Double-fuselage aircraft with two side by side at a distance lying hulls that are rigidly connected to each other and have outward-pointing wings that generate aerodynamic lift during forward flight, characterized, that thrust drive means are so stored in the space between the hulls are that they can move between positions in which the drive thrust is horizontal and / or vertical, and that the thrust generating means are arranged so that at downward thrust, the thrust vector runs through the center of mass of the plug tool. 2. Plug stuff according to claim 1, characterized , that the connecting means of the two hulls from an aerodynamic There are wing that generates lift forces on the plug stuff during forward flight. J>. Plug stuff according to claim 1, characterized , that the thrust generating means are mounted on a component which extends between the two hulls and is streamlined is designed so that it has lift forces during forward flight generated. 4. plug stuff according to claims 1 to 2,
characterized, that the thrust means have at least three Oasturbinenjetkraftwerke, which around the center of mass of the Plugzeuges around are arranged that their thrust vector passes through this. 5 plug stuff according to claims 1 to 4,
characterized, that the Oas turbine jet engines are turbofan engines or engines with an Oasgenerator, which drives with 009816/041 7 19479U a fan is connected, which is arranged around the housing of the gas generator. 009816/0417