DE3644899A1 - Aircraft - Google Patents

Abstract

The aircraft consists of a round fuselage, a ring, a control and monitoring mechanism and a payload compartment. The aircraft is intended to be used as a novel type of vehicle which enables smooth onward motion through the air by utilising air masses and air flows. The aircraft has the form of an inverted plate with flat edges and a planar base. The cockpit is located in the dome-shaped upper part. The lower part of the vehicle is formed by a ring which rotates vigorously about its axis or its centre point and has a large diameter, this also determining the external shape of the aircraft (Figs. 1 and 2). The outer casing of the apparatus produces its fast lateral onward motion, and rapid descent of the vehicle is prevented by the large lower surface. The technology of the aircraft is based on the fact that the vigorously rotating ring holds the aircraft in the horizontal position (gyro phenomenon) and prevents any abrupt motions. As a result of its rapid rotation, the ring B (Fig. 2) compensates for the weight of the vehicle, and the variation in the angular velocities of the ring produces the easy controllability of this aircraft. <IMAGE>

Description

The flying product consists of a round missile, a ring, a control and engine and usable space. The The product is intended as a new vehicle, with which the Locomotion in airspace by using air masses and -flows is made possible. The flying product counts the aircraft.

Currently, aircraft that are heavier than air are considered Airplanes, helicopters and autogyros. It is high developed vehicles that can be used for various purposes. To replace some of them, and also for the implementation of new ones and larger tasks in the following is the technique of flow presented product.

The flying product maintains its horizontal position due to of the so-called gyro phenomenon. Comparable patents can be found in class B 64 C. The second property that the product self-supporting effect, is due to the centrifugal and zen tripedal forces generated by the ring; there are so far no patents. The third property, the streamlined shape of the Vehicle, is known and calculated according to the experimental values of aircraft wings.

The invention is based on the good sliding properties of a round flat body and insist that the kinetic energy of the violently rotating ring on the influence of gravity is able to compensate for the potential energy of the product.

The moment of inertia of the annular cylinder:

J = _^1/2 × m × r ²
J = moment of inertia m = mass of the ring r = radius of the ring

The kinetic energy of the circular ring:

W = _^1/2 x J × UU

W = kinetic energy J = moment of inertia UU = angular velocity of a rotating body

The size of the air drag caused by the missile stands is due to the experimental coefficients of flight wings predictable; the formulas for those generated by the ring th kinetic energy results from physics.

The flying product is a new type vehicle. The developed for the different purposes Aircraft are largely specialized. The respective Benefits are largely at the cost of significant energy effort has been achieved. The product presented here is economical in energy consumption because its movements the air use currents. While the size of the current air vehicles is largely limited, the flying Er have a very large scope. Some of the hay Aircraft are able to effortlessly move vertically to move: one of the main characteristics of the flying product nisses is the ability to move in the height-depth direction. A standstill in the air is only possible in a few cases real can. The flying product also forms here a new alternative. For this purpose, this vehicle couples its own of an airplane with that of a satellite.

With the help of the flying product you can make a decision de abuses will be remedied. The essential in this regard union specific properties of the invention are in the characteristic part of the patent claims presented.

The greatest advantage can be seen that locomotion in Airspace happens through the use of air currents and wind. Energy is used by the vehicle to be in a horizontal position to be held; in calm weather it will be on the desired height "carried" while during storm fuel only is needed to maintain balance. The movement of the vehicle is generally in the form of curved paths.

In the following the invention is described in detail with Reference to the attached pictures:

Figure 1: Flying product A , the first version, equipped with a ring with a fixed axis;

Image 2: flying product B ; the ring forms a double ring;

Figure 3: Ring A , with a fixed axis, via which the torque is transferred to the ring;

Figure 4: Cross section of ring A ;

Figure 5: Ring A , with a "hollow" axis. The freely rotating wheels above the rim carry the vehicle; when the ring is stationary, the wheels in the lower part of the fuselage carry the ring;

Figure 6: Cross section of ring B ;

Picture 7: Ring C is the second version. Here rings of type A and B attached to the large ring rotate at high angular velocity;

Figure 8: Cross section of ring C.

The shape of the flying product is based on if possible small air resistance, which improves sliding properties is made possible. The outer shape of the ride together with the ring rotating violently in it the specific properties of this invention. By the ring generated energy is here on a previously not ge used way. In its capacity as a body the ring connects the three axes of the coordinate system, and form the forces acting in the respective directions Moments regarding the other axes in this inven systematically used.

The outer shape of the flying product resembles an overturned plate ( Figures 1 and 2) with flattened edges. From changes are made by the light used in each ring, which is either of type A (Figure 3 and 4), Type B (Figure 5 and 6) or Type C (Figure 7 and 8). Support ring C , circular in Figs. 7 and 8, can also have a different surface shape.

Ring B ( Fig. 5 and 6) can be used according to its structure for flying products of all sizes. The intermediate part between the outer ring (Obj. 4 ) and the inner ring (Obj. 5 ) only serves to apply kinetic energy. The inner part of the inner ring ( Fig. 2, Obj. 5 ) is intended for the engine and the usable space. Door openings can be installed on the upper or lower part of the fuselage. The weight of the vehicle rests on the airfield on telescopic ( picture 1 and 2, object 3 ) or other types of supports. In the rest position, the weight of the ring is supported z. T. on freely rotating wheels, which are installed in the vehicle's props ( Figure 2, item 1 ). Ring B receives its kinetic energy via the inner surface of the inner ring ( Figure 5, Obj. 5 ), either through a friction surface or through a rack. Any energy source known today can be used for the engine of the vehicle; even a nuclear reactor in large vehicles. When ring B ( Fig. 2) is working, the support wheels (Obj. 2 ) on the top of the inner ring (Obj. 5 ) turn. When moving, these support wheels carry the entire flying product. The usable space extends from the basic structure through the inner ring B ( Figure 2, item 5 ) to the dome of the vehicle, where the control and control room is located. The outer ring of ring B is a so-called mass ring with high angular speeds.

As an alternative to the ring of the vehicle, a ring with a fixed axle can be used, the vehicle resting solely on the axle. Ring A ( picture 3 and cross-section picture 4) is coupled to the vehicle by means of the axle. The bends between the outer edge and the middle part of the ring become large between the rest and functional phases ( Fig. 1) when the ring is very extensive. Therefore the ring model A ( picture 3) can only be recommended for small flying products. A motor connected directly to the axis ensures that the ring rotates. Ring A fills the entire lower part of the vehicle ( picture 1). Entry and exit take place at the upper part of the vehicle.

The second version of the ring is ring C ( picture 7 and 8). Here forms plastic tube with a diameter of z. B. 1000 mm that the scaffolding for a structure of z. B. 10 rings according to models A and B with a diameter of z. B. 3000 mm. If the angular velocity of an individual ring is reduced, this part is lowered, which results in a lowering of the entire ring system. The support ring does not necessarily have to be circular, other surface shapes can also be considered. The individual rings can e.g. B. be brought into motion by compressed air. Flaps corresponding to the flaps of aircraft surround the frame of the large ring, where they are controlled by the air masses flowing around the vehicle.

Claims (4)

1. Characteristic of the flying product is that it is a flat, round vehicle, looking like an inverted deep plate with wide edges, which moves smoothly in the air space. The exterior is aerodynamically shaped, the cross section of the vehicle is symmetrical in relation to the diameter. From the middle part a narrow fin extends in a radius to the edge; this serves as a rudder. In the lower part of the vehicle there are one or more large diameter rings rotating violently around their axis. The size of the rings determines the size of the entire aircraft ( Figures 1 and 2). The hull of the flying product is self-supporting.
Characteristic of the ring part is its large diameter and the equipment of the ring-shaped cylinder with homogeneous mass. The ring balances statically and dynamically and rotates at high speed. Ring B ( Figure 5, Obj. 5 ): The function of the inner ring consists of
to carry the entire vehicle while moving with the help of wheels rotating on its surface ( Fig. 2, Obj. 2 ), to transfer kinetic energy to the outer ring ( Fig. 5, Obj. 4 ) and in the rest position the ring by means of itself to carry it under the wheels
to maintain the position of the rotating ring with respect to its theoretical center. The length of the ring diameter can vary between 1 m and 1000 m, depending on the application of the flying product. 2. For the flying product according to claim 1 is characterized in that the ring claim 1 (Figure 3 and 4) is equipped with a fixed axis, is transmitted to the mass of the ring arc by means of which kine diagram energy according to the flying product according to claim 1 to wear. 3. For the flying product according to claim 1 characterizing that the ring part of rings according to the claims 1 and 2 is formed in a fixed framework. The ring part can  be circular or have a different surface shape. 4. For the flying product according to claim 1 characteristic that it out in the ring plane with engine is equipped and with control flaps on the edge of the ring.