WO2016113579A1

WO2016113579A1 - Method to prevent aircraft stalling - anti stall equipment

Info

Publication number: WO2016113579A1
Application number: PCT/GR2016/000001
Authority: WO
Inventors: Konstantinos KASTANAS
Original assignee: Kastanas Konstantinos
Priority date: 2015-01-12
Filing date: 2016-01-08
Publication date: 2016-07-21
Also published as: GR1008767B

Abstract

Method of prevention - avoiding aircraft stalling, mostly due to bad weather conditions and minimizing cruising speed, by placing a device that is able to produce and deliver continuously the appropriate amount of smooth air flow to the upper part of the wings and at the junction of the root of the wings with the main body of the aircraft, capable to replace the possible turbulent air flow accompanying the detachment molecules from the wings of the aircraft with smooth analogue like, thus avoiding roaming in a stalling situation. The device shall be connected to the proper air flow detector, and even to the weather detector, which already exist on advanced aircrafts, and whenever required, it will be activated and will produce the appropriate amount of smooth air flow, that of similar density and speed for each time required to maintain the necessary lift, regardless of variable weather conditions or other phenomena, as discussed above, and eventually channel it at the upper part of the wings.

Description

DESCRIPTION

METHOD TO PREVENT AIRCRAFT STALLING - ANTI STALL EQUIPMENT

The invention relates to the prevention of aircraft stalling, and the method by which this can be avoided for industrial application, when undesired emergency stall may occur especially due to extrinsic conditions (wind and/or speed).

More specifically, the invention demonstrates the ability to produce lift, necessary to support the aircraft on the horizon, regardless of its speed.

According to the basic aircraft flight principles, lift - a natural phenomenon - is produced by the wings (in fact it emerges from the combination of aircraft speed, spread of wings, and ground speed), and is based on the smooth flow of air to the wings of the aircraft, degradable to low (upper wing part) and high (bottom wing) air pressure according to the laws of physics, and because of the shape of the wing, combined with the necessary speed, varying from aircraft to aircraft, depending on the data of each manufacturer.

When applying the present invention, specialists place an air generation device based on the main engines of the aircraft (so as not to charge the vessel with additional weight of extra machines) and place it on top of the wing root (wing union with the shaft) .

If required, the device is able to channel a smooth flow of air, of adjustable intensity and quantity, depending on the location, atmospheric conditions, speed and load of the aircraft, heading from the shaft to the tip of the wing, to minimize the existing low pressure, and maximize the high pressure at the bottom of the wing, thus maximizing the necessary lift to support the aircraft on the horizon, achieving support of the aircraft, REGARDLESS OF THE SPEED, THE TEMPERATURE AND THE DENSITY OF THE AIR, OR EVEN THE CORNER OF INCIDENCE.

Studying the attached drawing (1 ) one can clearly observe the exact placement of the device on the aircraft, which is enhanced by the present invention, and furthermore the smooth flow of air, which is channeled towards the wings, so as to produce the necessary lift, when required.

The existing engine turbines of the aircraft, being handled in the cockpit, produce and multiply the air, in order for the aircraft to move on the horizon.

Their direct connection to the proposed device in a state of stand-by for immediate use, when required, can produce the amount of air (which is and will remain of a smooth flow rather than be turbulent, only because it is produced by a controllable machine, and not by unstable weather conditions) in order to be channeled at the same time to the exact point where it is required, so as to contribute to the support of the aircraft on the horizon dynamically and not statically (regardless of the outside air) according to the principles of physics, and to produce the necessary lift.

Have we ever observed stalling on birds? No, really.The answer is negative because birds have the ability to exploit and correct at once and on end, the angle of incidence and the "pace" of their wings (if someone can say so), adjusting their speed according to the direction of the wind, maintaining this way their ability to fly.

If aircraft manufacturers implement and apply this present invention, along with some small adjustments on the constructional blueprints, (i.e. by channeling some air from the existing machines through the shaft to that specific point being described, and by placing the vent of the proposed device externally, to the point recommended), the produced aircraft can be considered extremely SAFE, at least from this perspective, annihilating the possibility of stall, due to bad weather conditions, or a reduction in speed.

A further advantage of the invention is that, if a change of situation occurs in no time, there might be a chance that the new situation cannot be reversed successfully, without the use of the invention, resulting in the fall of the aircraft.

The invention - a new idea to register patent will be called " METHOD TO PREVENT AIRCRAFT STALLING " (ANTI STALL EQUIPMENT - ASE) is based not on how the situation is handled, but mainly on the prevention of the certain situation - and most importantly on its prevention in combination with its industrial production.

Claims

"The protection of the invention from any unauthorized installation by manufacturing aircraft companies is required, roaming avoidance device in stalling situations, according to the description and blueprint of the invention, namely the unauthorized installation of the device which eliminates roaming installing situations. "

The invention relates to the prevention of avoiding aircraft stalling, associated with industrial production, by placing an appropriate device.

The device is placed on the upper part of the wings and their union with the shaft and, in case of speed reduction due to weather conditions, and/or during landing (when speed reduction is required) a smooth flow of air will be channeled, as much as necessary, to the upper part of the wings, in order to ensure the required lift (via maximizing high pressure and minimizing low pressure) according to the principles of physics and alongside with the manufacturer's instructions.

The devise

• produces sufficient quantity of air smooth flow (proportional to the prevailing current situations such as the speed of the aircraft, the temperature - the air density, the address - the wind intensity, angle of incidence) using the main engines of the aircraft as a basis, only with small additions, i.e. by passing the necessary smooth air not only in the thrust turbines under the wings, as in the past, or at the back of the shaft, (depending on the manufacturer), but also for the proposed device -one for each wing- regardless of the prevailing weather conditions.

• Channels the air produced to the upper part of each wing and its root, so that the generated lift remains strong for reasons of safety - airworthiness of the aircraft, and

• is placed at the junction of the "root" of each wing of the aircraft with the main body of the fuselage and at the front of the vessel where this can be possible industrially and,

In order for the produced lift to always remain liable (regardless of weather or other conditions) to support the aircraft and make sure that aircraft stall will not occur.

The device is connected to the proper air flow detector, and even to the weather detector, which already exist in advanced aircrafts, and whenever required, it will be activated and will produce the required amount of smooth air flow, that of similar density and velocity to maintain the necessary lift, regardless of variable weather conditions or other phenomena, and eventually channel it to the upper part of the wings.