Flying vehicle of inverse sustentation (FVIS)

A transport airship of passengers and cargo, that is sustained by a flow of air or gases combustion directed toward a circular wing of the characteristics of an airplane wing. That is, a tear forms in a sectional view and an attack angle regarding the horizontal flow of air or impelled gases. For being generated the sustentation directing the flow of air or gases toward the wing and not on the contrary, the vehicle is denominated “of inverse sustentation.” The flow can be generated by an internal combustion motor in whose axis rotates a screw propeller acting as a fan, or a screw propeller can be moved by a jet engine, when an air current is used, or it can be generated by a jet engine when a current of escape gases are used. In any of these cases, the effects of reaction in these main propellers help the sustentation of the vehicle. According to design necessities, it will be possible to settle one, two, or more main units of propulsion, obtaining in this way;

• personal transport vehicles and heavy transport vehicles or passengers in general. The mentioned circular wing is attached in regard to the flow, but it owns hinge movement according to the unitary circular axis. Being able to move independent or synchronized for each of the four sections in which it is divided, with ends of obtaining the maneuverability and stability of the vehicle changing anytime you wish the angle of attack of each section of the wing. This swinging movement or hinge movement is gotten by means of the use of two hydraulic pistons installed in each one of the four sections of the wing, which receive oil pressure a hydraulic bomb, and which, at the same time, is run by an electric motor whose energy is given by a generator installed in the axis of the motor or turbine. Providing a bigger or smaller attack angle of the same value in the four sections of the wing, a proportional ascencional speed will be obtained. The attack angle of each section of the circular wing could vary until taking a “negative” value, in other words, placing over the horizontal plane at a same angle value in each section, with the purpose of obtaining a stable and quick descent when it is necessary.
• In the case of using a jet engine (turbine), the vehicle has a circular duct, of air entrance, located in a position so that, when it enters into the jet engine, it cools the escape gases directed to the wing and heats the air when it enters into the jet engine.
• The flow of air or gases are directed toward the wing by a circular duct with the characteristics of a nozzle, that is, it narrows toward the border, with the purpose of winning speed of the flow when it exits. Minor speeds than the sound speed for exit of gases are considered because the purpose is to provide sustentation.
• The horizontal displacement of the vehicle is gotten with secondary propulsion units installed on top or side external parts of the structure;
• these secondary units can be motors with screw propellers, jet engines (turbines), depending on the specific application of the vehicle. The location of four jet engines to 90° degrees will provide an unknown maneuverability in existent airships.
• In the event of using a jet engine as a main flow-generating unit, and for smaller vehicles of low displacement speed, the option of deriving part of the main gas flow to four nozzles at 90° exists. In this case, electromagnetic valves from the cockpit will regulate the change to obtain the transfer of speed and direction. This is also applied to the case of using a jet engine as a motor to move a fan, deriving all escape gases toward those mentioned four regulated nozzles.
• The geometry of the wing seen from top, can be modified partially, if it is required to compensate an asymmetric distribution of weights.
• For a bigger vehicle, several circular wings can be used with their main flow-generating unit protective cover joined structurally to elevate a bigger unitary fuselage.
• The general form can be adapted according to each necessity, without being indispensable to adopt the circular geometry. This also includes the geometry of the sustentation circular wing, which, when necessary, can also be separated in more than four parts. Some of them can be firm.
• In the exterior of the vehicle, some wings can be added to the structure replacing the internal circular wing in the sustentation when a minimum speed of sustentation is reached through these wings in horizontal displacement. This configuration includes the option of installing the main flow-generating unit in horizontal position, regulating the flow with electromagnetic valves synchronized toward the sustentation with the circular wing or toward a rear nozzle for the horizontal displacement.
• The principle of the invention can be applied for obtaining vertical takeoff in a conventional airplane directing the flow of sustentation directly to the wings by means of a couple of ducts located in front of them in all their extension.