• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The added thrust system for the wings of an airplane, is a balance (4-8) with two arms (5, 7) and two plates (4, 8), which supports its fulcrum in a pivot (6) of the diameter of a metallic circle (9) having another pivot at the other end, where another shaft (11) will be placed, which will have a protector (12) at 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 backward thrust, will be converted into a forward thrust of the wings (1). (Machine-translation by Google Translate, not legally binding)
    公开号:ES2658412A1
    申请号:ES201600788
    申请日:2016-09-09
    公开日:2018-03-09
    发明作者:Fº JAVIER PORRAS VILA
    申请人:Fº JAVIER PORRAS VILA；
    IPC主号:
    专利说明:

    PUSHING SYSTEM ADDED FOR LASVIAS DE UNAVIÓN
    OBJECT OF THE INVENTION
    The main objective of the present invention is to build a balance system (4-8) that harnesses the force of combustion gases, to create a double thrust forward. 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 using the outside of these same gases from the combustion of the reactor, to push forward to the wings (1). The system isolates a device where the fulcrum of the balance (4-8) will be supported, which will convert the thrust force of the gases back against the plate (4), into a force of thrust forward, against the wings (1), in the protector (8). BACKGROUND OF THE INVENTION
    The main antecedent of my invention of the day (08.09.16) .., actually., I don't 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 rectilineum and another curved-, which is located in the rear part 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 it is, in reality, a hole that is introduced into 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 introduce the hollow of another shaft (11) that extends to a guard (12) that is in contact with the wing (1). In the center of this metal circle (9) two other axes (10) are fixed, one on each face, which also extend to the wing (1). The second arm (7) of the balance (4-8) is curved outward, enough that it does not trip over the axis (11) at the point where the end of this axis (11) is inserted into the second pivot of the metal 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 FIGURES
    Figure # 1: Bottom view of an airplane wing (1) that would have the passenger tube in the upper area, next to the reactor (3). On the rear part of the wing (1) is the aidid thrust system, formed by a balance (4-8) whose fulcrum is supported by the first pivot (6) located at the end of the diameter of a metal circle ( 9), which has two axes (10) that are fixed to the wing (1) by one end, and, extend there from the center of the two sides of the circle (6). At the other end of the


    diameter, there is a second pivot on which another axis (1 1) is fixed, which also rests on the wing (1),
    by a protector (12).
    Figure 1:
    1) Wing of an airplane
    5 2) Elevation
    3) Reactor
    4) Receiver balance plate
    5) First balance arm
    6) First pivot of the metal circle
    10 7) Second balance arm
    8) Protector, for the Wing, of the pushing force
    9) Metallic circle
    10) Metal circle fixing shaft
    11) Axis of the second pivot of the metal circle
    fifteen 12) Protector, for the Wing, of the pushing force
    DESCRIPTION OF A PREFERRED REALIZATION MODE
    The added thrust system for the wings of 1111 aircraft is characterized by having a balance
    (4-8) with two arms (5, 7) and two plates (4, 8), - located behind the reactor (2) -, which supports its fulcrum
    in the first pivot (6) located in the diameter of a metallic circle (9) having another pivot in the
    twenty another end, where another shaft (11) will be placed, which will have a protector (12) at the end, which
    support on the wing (1). The second curved arm (7) of the balance (4-8) ends in a protector (8) that
    contact the wing (1). The metal circle (9) has, on both sides, two axes (10) that extend
    to the wing (1). Thus, to the own force of the gases of the reactor (2), these are going to be collected in the
    plate (4), and, its backward thrust, will be converted into a forward thrust of the wings (1). From
    2S this way, when the combustion gases of the reactor (2) are directed against the plate (4) of the first
    arm (5), will push it back, and, the protector (8) of the second curved arm (7), will push towards
    in front of the wing (1), whereby, the plane 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
    30 12) where the fulcrum of the balance will rest (4-8). This device (9-12) will allow the force
    backward that will determine in this same fulcrum, that is, in the hole that is introduced in the first
    pivot (6) of the metal circle (9) -, the thrust of the gases against the plate (4) of the balance (4-8), is
    can cancel, so that the metal circle (9) will be pushed back 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, is the fulcrum and the 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 be compensated for the two forces that try to move it, and, the result of these two forces will be a zero force, which will allow the backward force that the plate (4) of the first arm of the balance (4-8), is directed, with all the value of that same force, towards the second plate that, in fact, is the protector (8) that we have put on the end of the second curved arm (1).
    权利要求:
    Claims (1)
    [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 other curved-, which is located in the rear area of the wing (1). The first (5) of these two
    5 arms (5, 7) is rectilinear and extends from its receiving plate (4) located at the end, just behind the reactor (12), to the fulcrum, which in this case is actually a hole that introduces into 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, into which the hollow of the end of another axis is introduced ( JI) that extends to a guard (12) that is in contact with the wing
    10 (1). In the center of this metal circle (9) two other axes (10) are fixed, one on each face, which also extend to the wing (1) where they will be fixed. The second arm (7) of the balance (4-8) is curved outward, enough that it does not collide with the axis (11) at the point where the end of this axis (1 1) is introduced into the second pivot of the metal circle (9). The end of this second curved arm (7) ends in a protector (8) that will be in contact
    15 continuous with the wing (1)
    - 5
    - 10
    Figure 1
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    同族专利:
    公开号 | 公开日
    ES2658412B1|2019-01-30|
    引用文献:
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    US20140342632A1|2013-05-15|2014-11-20|Tanous Works, Llc|Hovering Toy Figure|
    CN103569359A|2013-10-24|2014-02-12|王金海|Multi-wing-arm multi-feature-membrane spiral arm control fly type wing arm internal-transmission helicopter|
    法律状态:
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    优先权:
    申请号 | 申请日 | 专利标题
    ES201600788A|ES2658412B1|2016-09-09|2016-09-09|Added thrust system for the wings of an aircraft|ES201600788A| ES2658412B1|2016-09-09|2016-09-09|Added thrust system for the wings of an aircraft|
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