ES2546705B1 - Airplane with groups of fins above and below the fuselage and wings - Google Patents

Abstract

The plane with groups of fins above and below the fuselage and wings, is an aircraft that can get a great lift because of the groups of fins (4, 5) that we installed in the upper area (4) and in the lower area (5) of the fuselage (1), as well as at the ends of the wings (2, 7), both on the front wings (2), as on the rear wings (7), and, also, above ( 12) and below (13) of the two wings (2, 7). With this lift, motors (10) of low power are needed, and, the safety system that is formed in the conical tubes (11) that run along the fuselage on both sides becomes more effective, and, which have, at the exit , a mobile wing that will be oblique, so that the plane can climb high due to the effect of air against this wing.

Description

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DESCRIPTION

Airplane with groups of fins above and below the fuselage and wings.

Object of the invention

The main objective of the present invention is to achieve a great Sustainability for an Airplane of great dimensions and great Weight, such as an Airplane of (80) meters in length. To achieve this objective, above and below its Fuselage (1), as well as above and below the Wings (2, 7), and, at the ends of the Wings (3, 8), a number of Fins Groups (4, 5), (3, 8), (12, 13), against which Air is going to influence against the advance, depending on the alpha angle of inclination that they present in their anterior zone. When this huge Sustainability is achieved, it is very easy to master the Plane in the worst conditions. This Sustainability requires little Force on its Motors (10) to perform the Pushing task, and, at the same time, in case of a possible heat, the Air will enter the Conical Tubes (11) that the Fuselage has (1) to both sides, and, at the exit, the Air stumble against an oblique and upwardly inclined Aleron located there !, which would make it possible for the Plane to rise high, even though this Air, at the exit of the Tubes (11) I didn't have too much strength. This system, therefore, greatly increases flight safety. At the same time, this great Sustainability becomes a considerable fuel saving due to the low power demanded by its Engines (10).

Background of the invention

The main antecedent of this invention is my Patent No. P201200913, entitled: Fins on perpendicular lever arm for the ends of the wings of an airplane, in which an Airplane is presented which has, at the ends of the Wings, an axis vertical that extends downwards, and, at the end of which a Fins Groups are located, thus forming, as indicated by the title, a Perpendicular Lever Arm that greatly increases the Sustaining Force of this Plane. The other antecedent that can be considered, related to the Safety System of the Conical Tubes (11) of the Airplane presented, is that of my other Patent No. P201200690, entitled: Anti-fall system for airplanes with rear wing nozzle, in which it is an Airplane to which two Conical Tubes are placed below the Fuselage, which open at its front end in case of a possible broth. The air that enters inside, multiplies its force due to the narrowing of the cone that forms the Tube, and, the air, at the exit, hits an Aleron located there! obliquely to the effect, which allows the plane to rise immediately.

Description of the invention

The plane with groups of fins above and below the pit / aje and the wings, is an aircraft that can achieve a great sustainability because of the groups of fins (4, 5) that we install in the upper area (4) and in the lower zone (5) of the Fuselage (1), as well as at the ends of the Wings (2, 7), both in the Anterior Wings (2), as in the Posterior Wings (7), and, also, by above (12) and below (13) of the two Wings (2, 7).

The Fin Groups (4, 5) of the upper and lower areas of the Fuselage (1) are wider than the Fin Groups of the ends (3, 8) of the Wings (2, 7), measuring the same as the width of the fuselage (1). And, at the same time, they are shorter in length than those of the ends (3, 8) of the Wings (2, 7) so that many of these Groups (4, 5) can fit over the entire length of the Fuselage (1 ), as shown in Figure 2. In a later section, I will detail measures

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more specific for the Fin Groups (4, 5) of the Fuselage, and, the Fin Groups (3, 8) of the Wings' ends (2, 7). All these groups of fins (4, 5), (3, 8), (12, 13), lean upward through their anterior zone at an alpha angle of (12) degrees, in the same way as the Wings do of all Avion, although they do it with a slightly different inclination. This alpha angle will allow the Air that enters the cavities of the Boxes (14) of all the Fin Groups (4, 5), (3, 8), (12, 13) to go to Push, in at all times, to the surface of the fins above. This is because the Air will enter with a lot of Force, and, it will be pushed after it by the Air that will continue entering the cavity or Box (14) existing between every two layers of Wing (2, 7), or, of Fin (3 , 8), and, as the Wing or Fin layers are inclined with that alpha angle, the Air, throughout its travel through the inside of the Cavity (14) cavity, will be impacting against the Surface of the layer or of the Fin that it has on it, as it is well seen in Figure 3 represented on a scale of (1: 100). At the ends of the Wings (2, 7) other Fin Groups (3, 8) have been placed in Lever's Radius, which further increases the Sustainability of the Plane, because its own Sustaining Force must be multiplied the Radius, or, the Length of the Wings (2, 7). And, in the same way, the Motors (10), are also located at the ends of the Wings (2, 7), in Lever Radius, which greatly increases its Strength, because, to its own Strength, it is necessary multiply, also, the Radius, or, the Length of the Wings (2). The last piece to highlight is an anti-calda safety system, which has only been represented, in part, in figure 1. This security system is formed by two Tubes (11) that are seen in the sides of the Fuselage (1), - behind the Anterior Wings (2) -, which are conical shaped tubes that narrow as the Tube (11) extends towards its rear end. In these Tubes (11) the air would enter it against the broth, and, at the exit through the narrow rear end, it would face an Aleron that, at that precise moment, would turn it obliquely, and, upwards. Take advantage of it, in this way, the great Sustainability of the great Alar Surface of this Airplane, which would make it, with the Force of the Air that entered the Tubes (11), the Airplane, when falling, began to lean upwards immediately, until it is horizontal again, being able to even trace height. In this way, a High Sustainability Aircraft is achieved, which has other practical advantages, such as the possibility of using Low Push Force Motors (10), to achieve the same Performance as the Large Push Force Motors that make missing in the Airplanes that do not carry this system of Fin Groups. In addition, the fuel economy is considerable, depending on the power savings that the engines must develop (10). And, the last practical advantage, already commented, is the great anti-calda security that is achieved, because the Weight that the Aircraft must support for each square meter of Surface, is greatly reduced compared to another Airplane of its same dimensions, which does not it has these groups of fins (4, 5) and (3, 8), (12, 13), and, this means that with a little push force, height can be traced immediately. Date of the invention: (23.03.14).

Description of the figures

Figure 1: Front view of an Airplane that has Anterior and Posterior Wings (2, 7). In them, above and below, some groups of fins (12, 13) formed by several layers of wing are installed, fixed by vertical separators that form isolated cavities. Also in the upper and lower area of the Fuselage (1) we have placed other Fin Groups (4, 5). The width of these Fin Groups (4, 5) is the same as the Fuselage (1) and also the Fin Groups (12, 13) in the Wings (2, 7). In the figure the Fin Groups (12, 13) that will be above and below the Back Wings (7) have not been represented. At the ends of the Wings (2, 7) other Fins Groups (3, 8) are placed, and the Motors (10), both located in Lever Radius.

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Figure 2: Side view of the same Plane of Figure 1, which shows the Groups of Fins (4, 5) above and below the Fuselage (1). These Fins (4, 5), like all the Fins of the Plane (3, 8), and, also, like the Wings (2, 7), are inclined upwards by their previous zone forming an angle of (12) degrees. The number of these Fin Groups (4, 5) is multiplied throughout the entire length of the Fuselage (1). This figure does not show the Motors (10), the Anti-Calda Tubes (11), or the Fin Groups (12, 13) of the upper and lower wings (2, 7).

Figure n ° 3: Lateral view [of a Box (14) of those formed inside a Fin Group (4, 5). It shows the position of the two ends of the upper fin. The rear end coincides in the same horizontal one in which the front end of the lower Flap is located, which implies that, with this disposition, the Air, when entering this Box (14), will be hitting the Upper Fin in all moment, until it comes out the back end of the box (14), which means that it will be pushing up at all times. This determines an alpha angle of inclination of the Fins that will be (12) degrees, if this figure, represented on a scale (1: 100), reminds us of the real dimensions of one of these Boxes (14), to which we assume has a fin length of five meters, and a height of twelve centimeters.

Figures 1-3:

1) Fuselage

2) Wings

3) Fins groups of the ends of the Anterior Wings

4) Fins groups of the Upper Fuselage area with several layers of Fins

5) Fins Groups of the Lower Fuselage area with several layers of Fins

6) Drift rudder

7) Back wings

9) Fixing axes

10) Motors

11) Anti-caldas conical tubes

12) Fins Groups of the upper area of the Anterior Wings

13) Fins Groups of the lower area of the Anterior Wings

14) Box formed between two fins of a group of fins and two vertical separators

Description of a preferred realization mode

The aircraft with groups of fins above and below the fuselage and wings, is characterized by being an aircraft in which a great Sustainability can be achieved with

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the Fin Groups (4, 5) and (3, 8) that we are going to install above and below the Fuselage

(1), as well as above (12) and below (13) of the Wings (2, 7), both on the Previous Wings

(2), as in the Back Wings (7). We also put other Fin Groups (1; 8) at the ends of the Wings (2, 7), forming a Lever Radius, which will further increase the Sustaining Force of these Fin Groups (3, 8 ).

In the same way, by placing the Motors (10) at the ends of the Wings (2), - also forming a Lever Radius -, its Pushing Force will increase greatly depending on the length of the Wings (2, 7). By adding the combined effects of all these elements, a High Sustainability Aircraft is achieved, which requires low power Engines (10), which becomes a good fuel economy and a considerable increase in safety. To increase this safety, Conical Tubes (11) are added to both sides of the Fuselage (1), which extend along the entire length thereof. At the exit end of these Tubes (11) a mobile Aleron is installed, -not represented in the figures-, which will lean upwards through its rear area in case the Plane begins to fall. In this way, the Force that has the Air that travels through these two Tubes (11), will hit the rear Aleron, so that it will cause the Plane to recover the horizontal position in a few seconds, and, which, in addition, can trace height. The latter is allowed by the enormous Sustainability that this Plane has, since, each square meter of Wings and Fins Surface, it will have to support a very small dose of Weight.

One way of calculating the Sustaining Force of these Fin Groups (4, 5), is to calculate, first, the Air Volume that will enter the Fins every second. For this, we only have to measure the Volume of a Fin Group (4, 5), as if it were a parallelepiped with its same dimensions, and, then, we have to multiply the result obtained by the Speed of the Plane because, with this data , we will know how much Air will be entering the Fin Group (4, 5) in every second. When we have this value. we will have to calculate to what mass that volume corresponds. With that Mass we can already obtain the Force that this Air Mass will have, as long as we consider that the Acceleration of the Plane, - which will be equivalent to that of the Air when it enters the Fins -, will be, as a minimum, that of Gravity , since the Plane does not succumb to the Force of Gravity. Either way, the Acceleration of this Plane must be a little greater than that of Gravity. The result obtained in this way will be the Force that this Air Mass will have, as it will be Pushing up all the Fins of a single Fin Group (4, 5). Therefore, the next step will be to multiply that value, by the Number of Fin Groups (4, 5) that we have put on this Plane, to which I will consider that they all have the same Volume. I will proceed, therefore, in the same order provided. I should only indicate that it is an approximate calculation, since the dimensions of the Plane may vary, as well as the Number of Fin Groups (4, 5), (3, 8), (12, 13) that you have installed.

The Volume of a single Fin Group (4, 5) will respond to dimensions of (6 x 5 x 0.6) meters: (6 • 5 • 0.6 = 18 m3).

As the speed of one of these large aircraft can be about

900,000 m

(900) km / h, this value, in meters per second, will be: (------------- = 250 m / s). Therefore the

3,600 ^

Airplane will travel these (250) meters in each second, which will also be the meters that the Fins Groups will travel (4, 5), and, at the same time, the Air will also enter them at this same Speed.

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We multiply, then, the Volume of a single Fin Group, by this Speed, to obtain the Volume of Air that will enter each Fin Group in every second: (18 m3 • 250 m / s = 4,500 m3 / s).

With this Volume of Air, we calculate, now, the Mass: (m = V • 5 = 4,500 • 1'29 = 5,805 kg).

And, with this Mass, we can calculate the Air Force, as it affects the Fins of a single Fin Group (4, 5): (FAire = m • g = 5.805 • 9'81 = 56.947'05 N ).

The next step will be to multiply this result by the Total Number of Fin Groups (4, 5) that we have installed on this Plane: FTotal.Aire = FAjre.Grupo • nGroups = 56.947'05 N • (50 + 20 + 4 ) = 56.947'05 N • 74 = 4.214.081'7 N

With this result of (4,214) Tons of Air Push, and, upwards, on all the Fins of this Airplane, - which will be (80) meters long and weighing (300) Tons -, this Weight will be widely seen compensated, so that its Sustainability will be very high, and, you will hardly need a small Engine (10), of little Push and very low consumption to perform the same Push functions as the large Motors that are put in an Aircraft of these dimensions.

In figure 1 there are two small Motors (10) at the ends of the Anterior Wings (2), which form a Lever Radius, as well as the End Fins (3, 8). Of these, I have not calculated the Force added by this simple fact of being located in Radio de Palanca, which will increase the Air Force against them even more, that is, its Sustainability.

If we divide, now, the value of that Total Air Force, by the Weight of the Plane, we obtain an Index that will help us calculate the Force that the Engines of this Engine will need to have.

Airplane: (

4,214,081'7 N 300,000 N

) = 14'05).

And, if we divide, now, the Total Force that the Engines of an Aircraft of these dimensions need to have, which are at least two Engines of (25) Tons of Push, we will obtain the comparative value that this Airplane with Groups will need of Fins (4, 5), (3, 8), (12, 13), to perform in the same way as an Airplane of the same dimensions

, „. 50,000 N

that does not carry them: (------------

14'05

= 3,559'5 N), which means that, this Plane with Groups of

Fins, you only need to carry a Motor (10) that offers a Push of (35) Tons, or two Motors of (17) Tons each to fulfill its function perfectly.

Claims (1)

ES 2 546 705 A2 1. Airplane with groups of fins above and below the fuselage and wings, characterized by being an aircraft of great sustainability because of the groups of fins (4, 5) that 5 we installed in the upper area (4) and in the lower zone (5) of the Fuselage (1), as well as in the zone upper (12) and lower (13) of the Wings (2, 7), both in the Previous Wings (2) and in the Back Wings (7). In the same way, we put other Groups of Fins (3, 8) at the ends of the Wings (2, 7), both in the Anterior Wings (2), as well as in the Back (7). The Fin Groups (4, 5) of the upper and lower areas of the Fuselage (1) are wider than the 10 Fin Groups (3, 8) of the Wings (2, 7), measuring the same that the width of the Fuselage (1). And, at the same time, they are shorter in length than those of the ends (3, 8) of the Wings (2, 7) so that many of these groups of fins (4, 5) can fit over the entire length of the fuselage (one). All these Fin Groups (4, 5), (3, 8), lean upwards through their anterior zone, at an angle of (11) degrees, in the same way as the Wings of all 15 Aircraft. At the ends of the Wings (2, 7) other Fin Groups (3, 8) have been placed in Lever Radius. And, in the same way, the Motors (10), are also located at the ends of the Wings (2, 7), in Lever Radius. The last pieces to highlight are the two Tubes (11) located on the sides of the Fuselage (1), which are conical shaped tubes that narrow as the Tube (11) extends towards its rear end. The narrow rear end 20 of each Tube (11) faces an Aleron, located obliquely, which has its rear area inclined upwards.