ES2658412B1 - Added thrust system for the wings of an aircraft - Google Patents

Description

ADJUSTABLE PUSH SYSTEM FOR A VINTAGE

OBJECTIVE OF THE INVENTION

The main objective of the present invention is to build a balance system (4-8) that takes advantage of the force of the combustion gases, to create a double forward thrust. One of these two thrusts will be created by the force of the reactor, and the second will be created by the balance (4-8), when it takes advantage of the force of these same gases from the combustion of the reactor, to push the wings forward (1 ). The system adds a device where the fulcrum of the balance (4-8) will rest, which will convert the thrust force backwards of the gases against the plate (4), in a pushing force forward, against the wings (1 ), on the protector (8).

BACKGROUND OF THE INVENTION

The main antecedent of my invention of the day (08.09.16) .., in fact, I do not know if there is any antecedent.

DESCRIPTION OF THE INVENTION

The added thrust system for the wings of an airplane is formed by the wing (1) of an airplane, where a reactor (2) is installed, and a balance (4-8) with two arms (5, 7). ), -one rectilinear and one curved-, which is located in the rear area of the wing (1). The first (5) of these two arms (5, 7) is rectilinear and extends from its receiving plate (4) located at the end, -exactly behind the reactor (12) -, to the fulcrum, which in this case is, in reality, a hole that is inserted in the first pivot (6) of one of the ends of the diameter of a metal circle (9), which has a second pivot at the other end of that same diameter, in which introduces the hollow of another shaft (11) that extends to a protector (12) that is in contact with the wing (1). In the center of this metallic circle (9) are fixed two other axes (10), one on each face, which are extended, also, to the wing (1). The second arm (7) of the balance (4-8) is curved outwards, sufficiently so that it does not trip on the axis (11) at the point where the end of this shaft (11) is inserted into the second pivot of the metallic circle (9). The end of this second curved arm (7) ends in a protector (8) that will be in continuous contact with the wing (1).

DESCRIPTION OF THE FIG UPAS

Figure No. I: Bottom view of an aircraft wing (1) that would have the passenger tube in the upper area, next to the reactor (3). The added thrust system is located on the rear part of the wing (1), formed by a balance (4-8) whose fulcrum rests on the first pivot (6) located at the end of the diameter of a metal circle (9) , which has two axes (10) that are attached to the wing (1) at one end, and, extend there from the center of the two faces of the circle (6). At the other end of the diameter, there is a second pivot in which another shaft (11) is fixed, which also rests on the wing (1), by means of a protector (12).

Figure n ° 1:

1) Wing of an airplane

2) Elevón

3) Reactor

4) Balance receiving plate

5) First arm of the balance

6) First pivot of the metal circle

7) Second arm of the balance

8) Protector, for the wing, of the pushing force

9) Metallic circle

10) Metal circle fixing shaft

11) Shaft of the second pivot of the metal circle

12) Protector, for the wing, of the pushing force

DESCRIPTION OF A PREFERRED EMBODIMENT

The added thrust system for the wings of an airplane, is characterized by having a balance (4-8) with two arms (5, 7) and two plates (4, 8), -situated behind the reactor (2) - , which supports its fulcrum in the first pivot (6) located in the diameter of a metal circle (9) that has another pivot in the other end, where another shaft (11) will be placed, which will have a protector (12) in the end, which will rest on the wing (1). The second curved arm (7) of the balance (4-8) ends in a protector (8) that contacts the wing (1). The metal circle (9) has, on both faces, two axes (10) that extend to the wing (1). Thus, to the own force of the gases of the reactor (2), these will be collected in the plate (4), and, its push back, will be converted into a forward thrust of the wings (1). In this way, when the combustion gases of the reactor (2) are directed against the plate (4) of the first arm (5), they will push it backwards, and, the protector (8) of the second arm (7) curved, it will push forward the wing (1), with which, the airplane will be pushed forward in two ways: one by the force of the reactor gases (2), and, another, by the added thrust force of the protector ( 8) of the second arm (7) of the balance (4-8). The system, therefore, adds to the reactor (2), a device (9 12) on which the fulcrum of the balance (4-8) will rest. This device (9-12) will allow the backward force that will determine in this same fulcrum, that is, in the hole that is introduced in the first pivot (6) of the metallic circle (9) -, the thrust of the gases against the plate (4) of the balance (4-8), it can be canceled, so that the metal circle (9) will be pushed backwards by the axes (10) that they fix it to the wings (1), and, at the same time, it will be pushed forward by the axes (11), because they are at the other end of the diameter of the circle (9), in which, at the other end, the fulcrum is there! first pivot (6) that are pushed, with the same force, backwards by the combustion gases of the reactor (2). In this way, the metallic circle (9) will see compensated the two forces that try to move it, and, the resultant of these two forces will be a zero force, which will allow the backward force that receives the plate (4) of the first arm of the balance (4-8), is directed, with all the value of that same force, to the second plate that, in reality, would be the protector (8) that we have put on the end of the second curved arm (7).

Claims (1)

1) Added thrust system for the wings of an airplane , it is characterized by being formed by the wing (1) of an airplane, where a reactor (2) is installed, and, a balance (4-8) with two arms (5, 7), -one rectilinear and one curved-, which is located in the rear area of the wing (1). The first (5) of these two arms (5, 7) is rectilinear and extends from its receiving plate (4) located at the end, just behind the reactor (12), the fulcrum is enough, which in this case is, in reality, a hole that is inserted in the first pivot (6) of one of the ends of the diameter of a metallic circle (9), which has a second pivot at the other end of that same diameter, in which the hollow of the end of another axis (11) that extends until a protector (12) that is in contact with the wing (1). In the center of this metal circle (9) are fixed two other axes (10), one on each face, which are extended, also, to the wing (1) where they will be fixed. The second arm (7) of the balance (4-8) is curved outwards, sufficiently so that it does not trip on the axis (11) at the point where the end of this shaft (11) is inserted into the second pivot of the metallic circle (9). The end of this second curved arm (7) ends in a protector (8) that will be in continuous contact with the wing (1)