DE3545943A1 - Aerodynamic lift and propulsion system - Google Patents

Abstract

This completely novel lift and propulsion system is distinguished by a large airflow rate which is deflected organically on the large bell surfaces in order to achieve powerful lifting forces. The airflow rate in kg/s determines the reaction force, that is to say the lift. It is also necessary to take note of its physically small construction, robustness and structural simplicity (cheapness). In addition, the generally hazardous and severely intrinsically hazardous long rotor blades of conventional helicopters are obviated and even a collision in the air need no longer lead to the machines involved crashing if the relatively small lift units remain undamaged. They can additionally be protected by being embedded. The system opens up the possibility of individual air transportation, of the air car, which can take off and land in a very small space. It makes possible a "rucksack lifting apparatus", for example for installers, fire service personnel, and mountain rescue personnel etc. Because of its compactness, it can be used for operational purposes which cannot yet be predicted.

Description

The lift and propulsion of aircraft is carried out according to aerodynamic Principles or isolated according to the recoil principle the rocket.

This rocket principle should not be considered here.

To achieve buoyancy or propulsion are common distinguish three systems:

1. The wing principle, in which a known profiled Surface more or less horizontally using motor power is pulled or pushed through the air mass. Propulsion is in limited speed even without engine power, in gliding to achieve, in which the height of the Aircraft is consumed. Height gain as a result of the thermal is excluded from the consideration.

2. The propeller system, which is aerodynamic Screw profile surfaces into the air masses and adhere to them support, accelerate them backwards or downwards. The best known examples are the classic propeller and the rotor of the helicopter.

3. The jet engine with air mass intake that compresses heated and expressed in volume again. Depending on Direction of movement of the outflowing air mass can propel or hub are generated.

The very few other systems in aviation can be left out will.

The subject of the invention is a new rotating system. Here, centrifuged air alternately creates a suction ( e ) and a pressure zone ( f ) and thus a very compact buoyancy or propulsion system.

In this system, a process takes place in stages comparable to that of an air-circulating wing. It is characterized by a number of bell-shaped elements ( a ) with a central cutout ( c ), which are arranged one above the other on a drive shaft ( b ).

The bells are interconnected - spaced apart - by air - air baffles ( d ) and thin tie rods ( n ), which also represent the connection to the drive shaft via the clamping segment ( i ).

When the system rotates, air is thrown centrifugally outwards via the intake shaft ( c ) between the air baffles ( d ) and glides along the concave surfaces ( f ) of the bells in a constant deflection, generating pressure ( f ), and also over the convex surfaces, so-called generating ( e ), according to the aerodynamic effect of a wing.

At the periphery, the air masses caused by the rotation are expelled in a tangential flow. The first bell shape shields the others ( h ), so it is drawn lower. It has only narrow air baffles ( d ) on the top, but with which an aerodynamic suction effect is achieved by centrifuging the air over the convex surface.

The air passes through the rotation of the bell with very high Rotational energy out and this air rotational energy would be pure loss.

It is converted again into buoyancy ( m ) by means of a guide vane ring ( l, k ) through the action ( g, k ), at the same time it is directed parallel to the axis, that is to say generally downwards.

Due to the majority of floors and the efficiency of the spin effect very large amounts of air are pushed through and on derived and supported the large shaped surfaces of the bells, so that a sum of buoyancy is generated.

The air flow is likely to be a multiple of that of jet engines reach comparable diameter.

Compared to those that are both bulky and at risk of air demolition Rotors of a helicopter or an air screw and the air compressors in jet engines that are at risk of air breakdown the system has the advantage that it is speed independent is and less air can be removed.

It also has the advantage of being robust, structural Simplicity and ease of maintenance.

Using this system is a completely new type of aircraft conceivable. A passenger cabin with double-sided  bilateral rotor bells, which, around their vertical axis slightly swiveling, both stroke, as well as forward or backward travel can generate. When swiveling a rotor on forward, the other on reverse, turns around the own axis causes.

This system is equally as horizontal Propulsion system of aircraft and modified as a hydraulic Drive of watercraft can be used. The water entry would have to be increased, the number of floors reduced. The Guide vane ring was unnecessary.

Claims (7)

Aerodynamic lift and propulsion system, characterized in that 1. a plurality of bell-shaped elements ( a ) are arranged one above the other on a common drive shaft ( b ), by means of which air flowing in via the intake shaft ( c ) due to the rapid rotation of the system under the constraint of rotation and the air baffles ( d ) convex and concave shapes of the bell elements ( a ) is conducted and each creates a suction ( e ) and a pressure zone ( f ). 2. according to claim 1, the kinetic energy of the air expressed at the lower edge of the bell rotating in a guide vane ring ( l, k ) flowing through it is converted into additional buoyancy ( m ). 3. according to claim 1 and 2, the bell elements via the spacing air baffles ( d ) and the tie rods ( n ) with the clamping segment ( i ) and the drive shaft ( b ) are connected. 4. according to claims 1 to 3, the first bell shields the other ( h ) and is also provided on the top with air baffles ( d ). 5. according to claims 1 to 4, such a lifting rotor unit on each side of an aircraft ( j ), vertically slightly individually or jointly pivotable, for the purpose of driving forward, backward and maneuvering. 6. according to claims 1 to 5, the system installed horizontally is and for the sole propulsion generation of air and as hydraulic drive of watercraft is used.