Comparatively, it is known the Propeller for Airships with Vertical Taking off and Landing that are the object of the licence #(110222 C1), published on 01/31/1998 in (BOPI nr.1/1998).

This Invention, is characterised by the fact that it responds only in a little measure to the numerous needs that the humanity has presently in the resolution of the increasing needs of the late-day civilisation.

Thus, the displacement by that method, is limited from the speed point of view of the flight, of the useful loading limited because of the terrestrial gravity, of the stability in the flight in case of a torrential rain or the storm that can lead to the shutting off of the valves and the immediate collapse of those aeroplanes as well as of the danger of the braking, of the vibrating elastic membranes because of the great number of cycles of identical solicitations that have as consequence the rapid decrease of the resistance to the tiredness.

Also comparatively, the propulsion performed by the help of all the models of classic turboreactor engines currently used in the aviation, according to [1 pag.76–79], the combustion chamber of which are always located between the axial compressor in steps and the turbine, where inside a constructively restricted room, the blade of turbine during a rotation, are attacked continuously all simultaneously by the hot gases resulted from the combustion at constant pressure of burning air mixture with the constructively severe restriction – because of the small diameter and of the thermal loading of the blade of turbine, the production of big relations of compression performing them only at very big revolutions, having constructively major involving concerning the smearing and the cooling, the phenomenon of pumping out and resonance, etc.

All those aspects being eliminated and solved by this invention, by the propulsion with two tubo-reactoar engines identical to the new type, respectively with combustion chambers located outside the coaxial compressor system – turbine and supplied with the condensed air from a single centrifugal radial compressor in steps with double result of medium diameter very big (of a meter range) capable to supply particularly big debits of air in the unit of time at superior net compression relation and with directly favourable influence on the attractive force (Ft)

Where:

in which, is the global efficiency,

(Q) is the quantity of the heat obtained through the combustion of mixture of combustible, and () represents the speed of flight at a certain altitude.

From the above mathematics relation we can observe that in the case of the present invention method where the diameter of the compressor is around one meter we can very easily obtain in the unit of time, very big quantities of heat because of the quantity of heat (Q) that is dependent of the debit value of air .

Where:

(S) represents section of passing and (V) is the speed of the air movement through the respective section it clearly follows that, directly proportional very big force of traction can be obtained because of the lack of some constructive restrictions at the sections of passing as it is the case of the classic turboreactor engines mentioned above.

In a different way, knowing the relation of the specific traction  defined by the relation  [daN.s/kg] in which:

-  is the developed force of traction

- and  is the debit of air that passes through the engine in the unit of time
-  is traction developed by one debit of air of 1 Kg, we have the same result:
the force of traction increases directly proportional with the value of the air debit  which moves through the engine in a unit of time where through the process of this invention, the section of moving on which depends the of some debits respectively the very big force of traction, are no more constructively restricted.

Comparatively to the classic turboreactor engines the efficiency of which are presented in the [1].

An other disadvantage of classic turboreactor engines consists in the fact that at the end of the detention phase of burning gas that leave the blade of turbine.

Those one have a pressure bigger than the atmospheric pressure and a temperature relatively higher, respectively a cinetic energy that disappears when, by the method of the present invention that disadvantage is partially constructively eliminated according to the principle of the action and the reaction of force because of that pressure of output > that show themselves as a specific pressure to entire output surface of gas of the chamber of combustion engenders a supplementary force of traction  having direct influences above the global efficiency  respectively and of the consume of combustible according to the relation  (kgf).

An other disadvantage of propulsion by classic turboreactor engines is the fact that the obtention of some higher efficiencies respectively, big relations of compression is severely limited by thermal loading of the lade of turbine.

That phenomenon eliminated by the invention due to the blade rotation of turbine that are no more all simultaneously attacked by the hot gas of combustion that constructively have times of cooling very big and the number of blade by circumference is largely bigger making, in this way, the blade able to work at some medium thermal conditions largely lower with a very good dissipation of heat and being able to take over mechanic solicitations – largely big comparatively.

Concerning the over coming of the gravity and the pulsation on the terrestrial orbit, comparatively, the present carrying rocket used to over come the gravity and the pulsation on the terrestrial orbit of some aeroplanes or satellite presents big disadvantages comparatively to the present invention. Those disadvantages are characterised by the fact that they have a particularly high cost, the material and the technology very complex, the dimension and the total weight are very big at the taking off implying a very big consume of combustible.

The unique use of carrying rocket and of elements that compose them, the limitation of the total weight because of terrestrial gravity, the limited speed of shifting, those disadvantages are solved by this invention - respectively the same flying saucer (that can be standardised) - and independently from the total weight in the standing during the taking off, (including the dimension and the diameter respectively higher size) being able to perform easily issues in the cosmos and with the same facility the return to the earth without a re-feeding with combustible and repeating that cycle, without particular technical involving to the return in the atmosphere (the special thermal protection) due to that method of propulsion by which the entire functional ensemble can be rotated <on the flight> at 180 degrees very easily (independent to the speed or the density atmosphere) face to the direction of the initial shifting, acting in this way very efficiently – in load – as a system of braking, correlate with the more aerodynamic form and the better structure of resistance (compact) that it has – constructively – in exterior, - the entire functional system similar to two saucers, face to face.