• 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:
    System against accidents, control, and improvement in aircraft. Constituted from a set of wings-helices that can rotate on its longitudinal axis to become one or the other, arranged in different parts of the aircraft such as the nose, wing end, tail, upper area, etc., which are placed in operation so as not to exceed, compensate and control the speed of impact descent of the aircraft in case of emergency and avoid injuries, deaths, damage to cargo and aircraft. (Machine-translation by Google Translate, not legally binding)
    公开号:ES2693899A2
    申请号:ES201800072
    申请日:2018-03-23
    公开日:2018-12-14
    发明作者:Joaquín CROS GOMA
    申请人:Joaquín CROS GOMA；
    IPC主号:
    专利说明:

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    DESCRIPTION
    Anti-accident system, control, and improvement in aircraft.
    Object of the invention
    The present invention relates to a system of wings / propellers designed, mainly, to reduce the speed of impact, eliminating the risk of death, preserving, as far as possible, the cargo and minimizing damage to the aircraft, in cases of flight emergency .
    Despite the large number of systems and mechanisms that airplanes and aircraft have in general, and although it is the safest way to travel, when the situation is limited, it is almost impossible to avoid accidents when the control of the ship is lost, its consequences being terrible for the speed of impact.
    The solution proposed by the present invention consists of an integrated system in the aircraft in question, which consists of a series of wings / propellers to reduce, control and minimize the impact of the ship and avoid serious and insurmountable losses.
    The advantages of this invention will be the following:
    - The descent speed is controlled with a maximum limit in case of emergency or serious failure, in which there is no other alternative, minimizing the risk to the life of people, cargo and damage to the aircraft.
    - It can be applied to any type of aircraft: ultralight, light aircraft, sub- and super-sonic aircraft, rocket aircraft, airships, aerostats, helicopters, etc.
    - While the system is not used for your emergency option, you can arrange your wings / propellers to support and improve sustainability, stabilization or other security improvement options (duplication of functions). Otherwise, they must be folded into the aircraft.
    - If the necessary internal / external power is supplied, allow it to convert a fixed-wing aircraft into a rotating-wing aircraft and vice versa.
    - In certain aircraft, such as take-off and vertical landing rockets, they allow fuel savings on the descent.
    - This same system is applicable to aircraft with rotating wings such as flying cars with propellers, drones, etc. in case of engine failure and emergency landing impossible.
    The industrial application of this invention is within the manufacture and installation of security elements in aircraft, and more specifically the wings-propellers against accidents and speed control in case of emergency.
    Background of the invention
    Although no identical invention has been found to that described, we present below the documents found that reflect the state of the art related to it.
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    Thus, document ES0283128U refers to a safety installation for airplanes and helicopters in flight, whose purpose is to control the equipment's heat in an emergency situation, essentially characterized in that it consists of the provision of aerodynamic parachute-type brakes, conveniently housed in receptacles established within the fuselage of the apparatus or attached externally to it, said aerodynamic brakes being manually operated with the collaboration of a microprocessor that causes activation in the presence of a series of conditions duly established for this purpose. The solution proposed by the aforementioned invention consists of the provision of brakes, while the main invention is part of a system of convertible blades and / or wings from fixed to rotating or vice versa.
    ES2389356A1 describes a passenger aircraft formed by two independent planes that correspond and work together, being a plane with the passenger compartment, coupled, to the top of another plane with the rest of compartments, and in both, its shapes and dimensions together with the arrangement of their flight elements, they understand each other to form the aircraft. This aircraft may proceed to the take-off maneuver of its plane with the passengers on which it is engaged in flight, for emergency or transfer situations. There are planned versions. Where the wings of the passenger plane are hidden in its fuselage. Where the passenger plane is trained to land on which it is attached and is to receive it.
    Where both planes have mobile rooms to transfer passengers between planes. And where both planes have airbags for safety and landing. The aforementioned invention reflects a combination of several aircraft forming the same aircraft, while the main invention corresponds to a system of conversion of fixed to rotating wings or vice versa.
    ES2293818A1 proposes a sustaining and propellant system for take-off and vertical landing aircraft that consists of applying to the aircraft some groups of rotating propeller and sustaining engines around their transverse axes and close to the center of gravity, presenting pairs of propellers, turbines or stabilizing fans against rotation driven by electric motors at the tips of the wings, nose and / or tail stabilizers of said aircraft, the electric motors are powered by batteries, supercapacitors, large power electric generators powered by the engines and by special power units assistant. The system proposed by the main invention, on the other hand, is a system of fixed wings that can be turned into swivels or vice versa to control the flight in broth.
    ES2327987A1 describes an airplane with vertical take-off propellers and, at the same time, forward, with a rotation axis without displacement, an airplane destined for the transport of passengers or cargo. It has at its base, and extended on its sides, a certain number of electric motors and propellers. The helices of the base are fixed to it, they have no mobility. They are protected behind floodgates. The propellers that extend along the sides have mobility. In them there are axes, -which hold the ring in which the propellers are located-, which can rotate on themselves 90 °, and with them the assembly formed by the ring that holds the electric motor and the blades of the propellers. That is to say, the blades will rotate, without moving, over the vertex where said blades intersect. A notch is created on the shaft that holds the ring with the motor and the blades. The notch leaves a square shape on the shaft and continues to extend - already inside the fuselage - as a cylindrical shaft to a cogwheel in contact with the wheel of an electric motor or the gear attached to it. A shaft with a notch in the head, or with two handles that have the same shape as the notch in the shaft, which extends along a toothed shaft after the tooth is added to the mechanism, in its outer part, and in variable contact with the shaft its head and that is in connection with an electric motor above the toothed shaft, and with another gearwheel below it. As in the previous case, the propellers proposed by the invention
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    Main are more oriented to control the descent in case of accident than to the advance and take off of the aircraft (secondary function).
    Conclusions: As can be seen from the investigation carried out, none of the documents found solves the problems raised as the proposed invention does.
    Description of the invention
    The anti-accident, control and improvement system in aircraft object of the present invention is constituted from a set of wing-propellers arranged in different parts of the aircraft such as the nose, wing end, tail, upper area, etc., that are put into operation so as not to exceed, compensate and control the speed of descent and impact of the aircraft in case of emergency and avoid injuries, deaths, damage to cargo and aircraft.
    In addition, it can be complemented with a balancing or balancing system to maintain certain aircraft positions, if necessary, and / or receive the power necessary to create a VTOL (vertical-take-off-landing) system. Or with sufficient internal / external power required, allow it to convert a fixed-wing aircraft into a rotating-wing aircraft and vice versa.
    The wing-propellers can rotate on its longitudinal axis, allowing them to be placed for aerodynamic functions of support and stabilization, without having to hide because of impeding or minimizing the aerodynamics of the aircraft while they are not used in an emergency.
    They can be applied to any type of aircraft: ultralight, light aircraft, sub- and super-sonic airplanes, rocket airplanes, airships, aerostats, helicopters, etc.
    Apart from the speed control system in emergency broth, it could allow shorter and / or smoother takeoffs and landings, or increase the speed of the aircraft by converting it into a fixed-wing aircraft.
    Said system object of the present invention has its own control system and activation of the emergency system that transforms the wing-propellers from one position to another, and its own auxiliary energy system in case it is not provided from the power system. main of the aircraft; Although the main source of energy to moderate the speed in case of emergency, is the wind energy from the incident wind.
    Brief description of the drawings
    For a better understanding of the present description, drawings that represent a preferred embodiment of the present invention are combined:
    Figure 1: Schematic plan view of an aircraft with the anti-accident, control and improvement system in aircraft object of the present invention in normal flight position.
    Figure 2: Schematic plan view of an aircraft with the anti-accident, control and improvement system in aircraft object of the present invention in an emergency position.
    Figure 3: Schematic view in conventional perspective of the transformation from helix to wing.
    Figure 4: Schematic elevational view of an example of a landing-rocket plane and vertical take-off with the anti-accident, control and improvement system in aircraft.
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    The numerical references that appear in said figures correspond to the following constituent elements of the invention:
    1. Rotational wing-helix set
    2. Longitudinal axis of the blades of the wing-propellers
    3. Control system
    4. Own energy system Description of a preferred embodiment
    A preferred embodiment of the anti-accident system, control, and improvement in aircraft object of the present invention, with reference to the numerical references, can be based on a set of wings-helices arranged (1) in different parts of the aircraft such as the nose , end of wings and tail, which are put into operation to control the speed of descent of the aircraft in case of emergency and avoid accidents.
    Said wing wings of (1) the propellers can rotate on their longitudinal axis (2) 180 ° (one wing for each longitudinal axis), allowing them to be placed for aerodynamic functions of support and stabilization, without having to hide.
    The system also has its own control and activation system for the emergency system that transforms the wing-propellers (1) from one position to another, and its own auxiliary energy system (4) if it is not provided from The main power system of the aircraft.
    权利要求:
    Claims (4)
    [1]
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    1. Anti-accident system, control, and improvement in aircraft, consisting of a set of wing-helices (1) arranged in different parts of the aircraft such as the nose, wing end, tail, upper area, etc., characterized in that they are put into operation so as not to exceed, compensate and control the speed of descent and impact of the aircraft in case of emergency and avoid injuries, deaths, damage to cargo and aircraft.
    [2]
    2. Anti-accident system, control, and improvement in aircraft, according to claim 1, characterized in that the wing-propellers (1) can rotate on their longitudinal axis (2), allowing them to be placed for aerodynamic functions of support and stabilization, without having to hide because it hinders or minimizes the aerodynamics of the aircraft while not being used in an emergency.
    [3]
    3. Anti-accident system, control, and improvement in aircraft, according to claims 1 and 2, characterized in that it also comprises its own control system (3) and activation of the emergency system that transforms the wing-propellers (1) of a position to another, and its own auxiliary energy system (4) in case it is not provided from the main power system of the aircraft; and it can be complemented with a balancing or balancing system to maintain certain aircraft positions, if necessary, and / or receive the power necessary to create a VTOL (vertical-take-off-landing) system; or with sufficient internal / external power required, allow it to convert a fixed-wing aircraft into a rotating-wing aircraft and vice versa.
    [4]
    4. Anti-accident system, control, and improvement in aircraft, according to claims 1 to 3, characterized in that it can be applied to any type of aircraft: ultralight, light aircraft, sub- and super-sonic aircraft, rocket aircraft, airships, aerostats , helicopters, etc.
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    同族专利:
    公开号 | 公开日
    ES2693899R1|2018-12-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    ES74322A1|1920-07-01|1920-10-01|Cierva Codorniu Juan De La|New aviation apparatus.|
    ES2275370B1|2004-03-05|2008-05-01|Industria Helicat Y Alas Giratorias, S.L.|METHOD OF OPERATION OF A CONVERTIBLE AIRCRAFT.|
    ES2277476B1|2004-03-05|2008-07-01|Industria Helicat Y Alas Giratorias, S.L.|SUSTAINABILITY SYSTEM FOR A CONVERTIBLE AIRCRAFT AND CONVERTIBLE AIRCRAFT THAT INCLUDES IT.|
    法律状态:
    2018-12-14| BA2A| Patent application published|Ref document number: 2693899 Country of ref document: ES Kind code of ref document: A2 Effective date: 20181214 |
    2018-12-20| EC2A| Search report published|Ref document number: 2693899 Country of ref document: ES Kind code of ref document: R1 Effective date: 20181213 |
    2019-11-21| FC2A| Grant refused|Effective date: 20191115 |
    优先权:
    申请号 | 申请日 | 专利标题
    ES201800072A|ES2693899R1|2018-03-23|2018-03-23|System against accidents, control and improvement in aircraft|ES201800072A| ES2693899R1|2018-03-23|2018-03-23|System against accidents, control and improvement in aircraft|
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