• 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 vertical takeoff system with balanced and duplicated force, is a system that duplicates in the upper and lower areas of an aircraft. Each system starts in two coils (2, 3) facing each other. The two above produce repulsion, and, the two below, produce attraction. The system tries to eliminate the unwanted forces that are directed in the opposite direction from the one needed, that is, downwards, what it does by forming a balance with an oblique axis (5-7) that supports the fulcrum at one end of the horizontal diameter of a wheel (9). At the other end of the wheel (9) is located a vertical axis (10) that will push up the roof of the fuselage (1), when the pivot (6) of the oblique axis (5-7) is pushed downwards by effect of the repulsion that will be exerted on the coil (3). (Machine-translation by Google Translate, not legally binding)
    公开号:ES2656588A1
    申请号:ES201600728
    申请日:2016-08-23
    公开日:2018-02-27
    发明作者:Fco. Javier Porras Vila
    申请人:Fco. Javier Porras Vila；
    IPC主号:
    专利说明:

     Its voltage will be high voltage - ten thousand or twenty thousand volts, or, more, perhaps - and, its intensity will have a minimum of one amp. The two coils (2, 3) will face the same polarity, which will cause repulsion between them. The lower coil (3) is held on a pivoted support (4), to which the right end of an oblique axis (5-7) formed by two sections, a short section (5) and a long section ( 7). Between the two sections (S, 7) the shaft (6) is crossed, which will be placed in a hole located at the right end of the horizontal diameter of the wheel (9). At the left end of this same horizontal diameter of the wheel (9), a vertical axis (10) is placed that ends, in the former upper row, in a mobile support (8) that rests on the upper and inner zone of the fuselage (1), without being fixed to it. The center of the wheel (9) has two other vertical axes (11), -one in each of its 10 faces-, which end, in the upper end, in another fixed support (12), which is the same as the support (10), but, which is fixed to the fuselage (1). The system just described, is then duplicated in the lower area of the fuselage (1), and will have the same elements that I have described, although, located in the opposite direction. Between the two magnetic fields of the two coils (2, 3) of the lower zone, attraction will now occur because they face different polarities. We just have to keep in mind that the support (8) of the oblique axis (5-7) of the system that we install in the lower area of the fuselage (1), will have to be fixed and now screwed to the fuselage (1), just like that will be the support (12) of the vertical axes (11) of the wheel (9). DESCRIPTION OF THE FIGURES Figure # J: Side view of the vertical take-off system, of which only the part 20 corresponding to the upper part of the fuselage (1) of the aircraft or spacecraft, in which a repulsive force between the two coils. In the lower area of the fuselage (1), another system will be installed practically the same as the previous one, but, turned upside down, in which an attractive force will be played between the respective magnetic fields of the two coils. Figure # J: 25 1) Fuselage 2) Upper coil 3) Lower coil 4) Pivot support 5) First short section of the oblique axis 30 6) Pivot attached to the wheel (9) 7) Second short section of the oblique axis 8) Mobile stand 9) Wheel5 10) Vertical axis 11) Vertical axis of the wheel axle (4) 12) Fixed support DESCRIPTION OF A PREFERRED MODE OF REALIZATION The vertical take-off system with the balanced and duplicated force is characterized by being a double system that forms a kind of balance that eliminates much of the unwanted forces that are directed downwards, as created by the repulsion between the two coils (2, 3) of the upper system, such as the attraction of the two coils (2, 3) of the lower system. Naturally, these two forces affect both coils (2, 3) equally, which will subtract thrust force up 10 in the total result that is intended for the plane to take off vertically, because, in repulsion , the coil (3) will be pushed down, while the coil (2) is pushed up. To avoid this problem, a balance system is presented that supports the fulcrum of its axis (5-7), - be the pivot (6) attached to the wheel (9) -, at one end of the horizontal diameter of the wheel (9), at whose other end we place a shaft (10) that rises vertically, and, is fixed to a mobile support (8) that rests freely on the roof of the fuselage (1). In this way, when the repulsion between the two coils (2, 3) pushes the coil down (3), this force will affect the fulcrum or pivot (6), which will also be pushed down. But, as at the other end of the wheel (9) we have put the vertical axis (10), the force that will be exerted downwards on the pivot (6), will push upwards, at the same time, to the vertical axis (10) , and, therefore, also to the roof of the fuselage 20 (1), where the two vertical axes (11) that start from the center of the wheel (9) are fixed at the same time. The result of this pair of forces of opposite direction, will be that the two vertical axes (JI) of the center of the wheel (9), will not receive any force, or, will receive a resultant of forces of zero value, because the force that pushes down to the pivot (6), it will be exactly the same that will push the fuselage roof up (1), through the vertical axis (10). We will have annulled, in this simple way, the downward thrust of the repulsion between the two coils (2, 3), and, at the same time, we will have made this force down, then go up, and, with a value greater than that which had reached the pivot support (4), because the second long section (7) of the oblique axis (5-7) is longer than the short section (5), which implies that, according to the beginning of the Archimedes lever radius, the force will increase in the support (8), depending on the increase in the radius of the 30 axis (7) of the balance. As regards the lower floor system of the fuselage (1), I must say that it will be exactly the same as the upper one, except for two small differences. It is not necessary to present another figure, because it is enough to invert the sheet of figure 1 to clearly visualize what is happening. The first difference is that the magnetic fields that will be faced now will be attractive,because the two coils (2, 3) will have the same polarity. And, the second difference refers to you small detail that has all its importance, as is the fact that the support (8) of the end of the long section (7) of the oblique axis (5-7), this time will have to be well fixed with screws to the ground of the fuselage (1), so that the force that will affect the other end of the short section (5) that is fixed to the pivot support (4) through the coil (3), -that now it will be the one that is located above the coil (2) -, tends to rise to the support (8) of the long section (7) when the force of attraction causes the coil (3) above, tends to go towards below, towards the coil (2) which, by itself my mother, will tend to rise, and, to drag with it to the ground of the fuselage (l). For the rest, it will also happen that the two vertical axes (11) of the wheel (9) will receive only a force of zero value, because the two forces that affect the two ends of their horizontal diameter will be subtracted, of the pivot (6), which will now also push down, and, that of the vertical axis (10) which will also now push upward. In the same way, we have to take into account that, if we place the two systems, the upper and the lower ones, at the ends of the wings of the plane. Of course, their strength will be much greater than if we install them inside of the fuselage of the central tube of the plane. In a space rocket, we can also beat the same, placing the systems described at the ends of two or four axes, which will extend radially horizontally from the central tube of the cobete, which will also form a lever radius of Archimedes , which will increase the strength of vertical take-off systems, or, of artificial satellite UD acceleration, depending on the length of those radial axes. twenty 
    权利要求:
    Claims (4)
    [1]
    CLAIMS 1) Vertical take-off system with balanced and duplicated force, characterized by being a system for airplanes, boats, and all mobile vehicles, formed by two separate coils (2, 3), facing their ends with the same polarity ; the coils (2, 3) are made with a wire two and a half centimeters in diameter, for a high voltage current, and an intensity not less than one ampere; The lower coil (3) is supported on a support plate that has a pivot (4), to which the right end of an oblique shaft (5-7) formed by two sections, a short section (5) and a long section (7); Between the two sections (5, 7) the axis (6) is traversed, which will be located in a hole located at the right end of the horizontal diameter of the wheel (9); At the left end of the same 10 horizontal diameter of the wheel (9), there is a vertical axis (10) that ends, at the upper end, in a mobile support (8) that rests on the upper and inner zone of the fuselage (1), without being attached to it; the center of the wheel (9) has two other vertical axes (11), -one on each of its faces-, which end, at the upper end, in another fixed support (12), which is the same as the support ( 10), but, which is fixed to the fuselage (1); The described system is installed both in the upper zone and in the lower zone of the interior of the fuselage (1) of one of the rooms of an aircraft; The system, therefore, is duplicated in the lower area of the fuselage (1), and has the same elements described, although located in the opposite direction; the opposite ends of the two coils (2, 3) in the lower zone now face different polarities; In this lower system, it must also be taken into account that, the support (8) of the oblique axis (5-7) of the system that we installed in the lower area of the fuselage (l), will have to be fixed and now well screwed to the fuselage (1), as will the support (12) of the vertical axes (11) of the wheel (9); The described system is located inside a special room of the airplane, spacecraft, ship, helicopter, or, in other movement mechanisms.
    [2]
    2) Vertical take-off system with balanced and doubled force, -according to the first claim-, characterized by the current that will pass through the coils (2, 3), which, in the variant, will be alternating, instead of being continuous.
    [3]
    3) Vertical take-off system with the balanced and doubled force, -according to the first claim-, characterized by the variant in which we place the two systems described, at the ends of the wings of an airplane, which will thus form! a lever radius.
    [4]
    4) Vertical take-off system with balanced and doubled force, -according to third claim 30-, characterized by the variant for a space rocket, in which we also place the described systems, at the ends of at least two axes , which will extend radially horizontally from the central tube of the rocket, which will also form a lever radius.
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    同族专利:
    公开号 | 公开日
    ES2656588B1|2018-12-17|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6404089B1|2000-07-21|2002-06-11|Mark R. Tomion|Electrodynamic field generator|
    US20060273666A1|2005-02-03|2006-12-07|Miodrag Mihajlovic|Permanent magnet flux module reciprocating engine and method|
    CN102152853A|2008-07-28|2011-08-17|李晓亮|Self-supply power warplane|
    ES2445217A1|2012-08-29|2014-02-28|Fº JAVIER PORRAS VILA|Accelerator of artificial satellites with electromagnet and shaft |
    CN105471323A|2014-10-06|2016-04-06|福州耕耘专利开发有限公司|Magnetic traction power machine|
    法律状态:
    2018-12-17| FG2A| Definitive protection|Ref document number: 2656588 Country of ref document: ES Kind code of ref document: B1 Effective date: 20181217 |
    优先权:
    申请号 | 申请日 | 专利标题
    ES201600728A|ES2656588B1|2016-08-23|2016-08-23|Vertical lift-off system with balanced and duplicated force|ES201600728A| ES2656588B1|2016-08-23|2016-08-23|Vertical lift-off system with balanced and duplicated force|
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