ES2387795A1 - Fixing sustaining surfaces in an unfiltered aircraft. (Machine-translation by Google Translate, not legally binding) - Google Patents

Abstract

Fixing the lifting surfaces in an unmanned aircraft (uav). Said supporting surfaces constitute a wing (4) and a horizontal stabilizer (5) in "canard" configuration. The set of stringers (17) ribs (18) forming the central box (16) of the bearing surfaces include guides that engage with the structural rails (13) that together with the rest of stringers (12) and frames (11) they form the fuselage (1). This connection allows the horizontal sliding in both directions of the supporting surfaces with respect to the fuselage. In this way, an always stable aircraft is obtained, which allows the adaptation of the center of gravity according to the payment letter required for the mission to be carried out. (Machine-translation by Google Translate, not legally binding)

Description

FIXING THE SUSTAINING SURFACES IN AN AIRCRAFT NO

MANNED

Object of the invention.

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The present invention relates to a new design of fixing between

at least one supporting surface with the fuselage. This new design of

fixing of the bearing surfaces applies in particular to a non-aircraft

manned (Unmaned Aerial Vehicle UAV).

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Background of the invention.

They belong to the category of drones or UAVs those

devices that are capable of carrying out missions autonomously and that

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Don't have a pilot on board.

The design of an airplane integrates two main parts: the fuselage and the

sustaining elements. The fuselage or body of the airplane comprises from the

tip or nose to the tail and joins in solidarity with the wings and

stabilizers or aerodynamic surfaces that make up the elements

2nd

Sustainers These elements can be horizontal and / or vertical.

The fundamental problem of conceptual design of an airplane lies in the

weight balance analysis phase. In this analysis it is very important

both the position of the wing and that of the stabilizers. A position

incorrect of the stabilizing elements entails an unstable aircraft or

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excessively stable, undesirable behavior in both cases. The

Instability also reduces aerodynamic performance.

When the mass balance is analyzed in the project of a new

plane the position of the wing and the stabilizers is calculated to place them in

a fixed place of the fuselage. The position of the said stabilizers is

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determined using the calculation of the center of gravity of the plane to

achieve the desired stability margin.

Once the aircraft has been defined and built the supporting surfaces

cannot be moved and with the wing configuration already set, you have the

obligation to place the payload properly distributed on the plane

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To remain stable. This stability is achieved by placing the

center of gravity, which can be modified, ahead of the center of

pressures to a certain extent. The pressure center never modifies its

position.

Mass distribution becomes a complex problem in the

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case of a UAV since these planes are loaded with different components

depending on the mission to which it will be entrusted: recognition,

sea rescue, fire fighting, etc. And the center of gravity

It varies with each mission.

To avoid the complex problem of distributing or limiting the payment burden

1st

because of the design of the aircraft the surface has been developed

sliding support of the present invention.

Description of the invention

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An object of the invention is to provide the aircraft with a wing system and

Sliding stabilizer with respect to the fuselage, so that first it is done

a mass distribution in the aircraft and then both the

wing as the stabilizer in the optimal position to get the margin of

desired stability

2nd

Another object of the invention is to provide a wide range of load of

payment to the same aircraft without the need to redesign its elements

sustainers

In turn, it is another object of the invention to design the fuselage with some

interior rails that give it structural rigidity and allow the wing or

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stabilizer slide over them. On the other hand the wing or stabilizer has

of a central drawer composed of the union of stringers and ribs. He

said central drawer will slide on the rails that are part of the

fuselage stringers allowing displacement in both directions and

Always in a horizontal plane.

3rd

And finally it is another object of the invention to provide the whole with a

fastening system to fix the wing or stabilizer on the rails

with endurance guarantee the bending and cutting efforts received by the

sustaining elements, transmitting these efforts in different ways

   loading

Brief description of the drawings.

In order to explain how the fixation of the elements is constituted

sustainers with the fuselage, as well as the arrangement of the rails and the

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guides, the following figures are accompanied:

Figure 1 shows a complete aircraft viewed in perspective.

Figure 2 shows the final part of the fuselage without its coating and its

fixing with the wing and with the horizontal stabilizer.

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Figure 3 shows in detail the connection between the central drawer of a

sustaining element and the fuselage.

Description of a preferred embodiment

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As shown in figure 1, an aircraft is constituted

by two parts mainly. On the one hand there is the fuselage (1) which is a

elongated body, mainly cylindrical, whose rounded tip

It is known as nose (2) and whose back (3), according to the present

practical realization, integrates the propellant group (14). On the other hand they have

2nd

the sustaining elements that are mainly formed by

wings (4) and a horizontal stabilizer (5). If the stabilizer (5) is found

a known aircraft configuration is formed in front of the wings (4)

like "canard". As it happens in the present invention.

In turn, all the sustaining elements have a part

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front or leading edge (7) where moving elements are included

commonly known as slats and a backside or trailing edge (8)

where mobile elements known as flaps and ailerons (1 0) are included.

In this case the vertical stabilizers (6) are located at the tips of the

at 9).

3rd

Drones have the advantage that they do not incorporate

crew or passage and all the space inside the fuselage

It could be used to include the drive and control mechanisms and

to include different types of cargo depending on the mission that is going to

entrust the aircraft: surveillance, fire fighting, rescue,

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   etc. All the elements included inside the fuselage (1) are known

as a payload and should be placed so that the center of gravity

is positioned in a certain and precise relationship with the center of pressures.

Normally the first will be ahead of the second. He

propeller group (14) is formed by a propeller arranged in the part

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rear (3) of the fuselage (1).

As shown in Figure 2, the inside of the fuselage (1) is a

mainly tubular and hollow body whose walls (not shown in the

figure) are separated by a series of stringers (12) that run

horizontally from the tip (1) to the back (3) intercalating

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periodically with frames (11) that give rigidity to the whole. In the

realization that concerns us, of all existing stringers (12),

corresponding to the sides of the fuselage (1) are rail-shaped (13) and

they link with the existing guides in the central drawer (16) of the elements

Sustainers

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Said supporting elements such as wing (4) and the

stabilizer (5), are formed by a framework of stringers and ribs

which form at one of its ends the central drawer (16) that joins the

fuselage (1).

The stringers (17) and the last rib (18) of the central drawer (16) of the

2nd

corresponding sustaining element make up a set with guides that

They can be located both at the top and bottom. These guides are

they link with the rails (13) that are part of the set of stringers (11)

of the fuselage (1). The union between the guides of the supporting surfaces and

the rails (13) corresponding to the lateral stringers (11) of the fuselage is

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a sliding joint that allows the horizontal movement of said

sustaining surfaces. As shown in figure 3, the drawer

central (16) has guides at the bottom of the last rib (18)

(These guides are not shown in the figure).

Once the optimum point where the surfaces have been established

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sustainers are more stable, these are fixed by screws or other

conventional means of attachment. In the practical embodiment two are arranged

junction points (15) for each central drawer (16) and corresponds to the

corners, both upper and lower, of the last rib (18) that

It forms the aforementioned central drawer (16). The connecting elements (15) are fixed to

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   the stringers (11) of the fuselage through their corresponding holes (19).

According to a second embodiment, the wing can move everything necessary, to the point of achieving a balance such that the use of any type of stabilizer is dispensable, turning the plane into a flying wing. For this, the stringers are configured along their entire length so that there is no limitation on the displacement of the wing along the fuselage.

Similarly, the connection between the rail and the guide of the central wing drawer allows said drawer and the stabilizer to be located on the sides of the fuselage and constitute a medium-wing aircraft. If the union is done by

1 or a group of stringers arranged at the top or bottom, a high wing or low wing aircraft will be constituted. All these configurations are within the scope of the invention.

Claims (4)

1.-Fixing of supporting surfaces for an unmanned aircraft

constituted by a fuselage (1) to which the surfaces are attached

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sustainers formed by the wings and stabilizers forming a

Aircraft with a low, medium or high wing, characterized in that the wings (4) and

the stabilizers (5) have a central drawer (16) where they are located

guides that join the fuselage (1) through rails (13)

structural that extend as stringers (12), so that

1st

there is a horizontal slide between the guides and the rails (13) limited

only because of the physical length of the rail, and because once the

specific point of stability of the aircraft is established the union between

the central drawers (16) and the fuselage (1) with one or more elements of

union (15) that cooperate with the holes (19) of the rail (13).

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2.-Fixing of supporting surfaces according to claim 1a,

characterized in that the rails (13) and the stringers (12) that form the

fuselage (1) are combined with frames (11) to constitute the body of the

aircraft, the rails (13) being arranged on the sides of the fuselage (1) to

2nd

mid-wing and top or bottom aircraft for aircraft

high wing or low wing.

3.-Fixing of supporting surfaces according to claim 1a,

characterized in that both the wing and the different surfaces of

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lift have at one of its ends a central drawer (16) that

they constitute one or several stringers (17) and a rib (18) and form, with the

guide that is arranged in the rib (18), a single sliding assembly.

4.-Fixing of supporting surfaces according to claim 1,

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characterized in that the connecting elements (15) fix the sides

upper and lower of the central drawer (16) with the rails (13) that

they constitute a structural part of the fuselage (1).