Abstract: A lifting arrangement for aircraft fuselages that consists of placing longitudinal vertical or slanted fins or plates on the lower and lateral lower part of the whole fuselage, said fins forming a channel with the underside of the fuselage, including nose, fuselage and tail, open on their lower area. Further adding longitudinal horizontal or laterally slanted fins on the lateral middle or middle-to-low area of the fuselage and with a positive slope up to the nose with said fins arranged in such a way that the upper fins are projected increasingly laterally, and because of this arrangement and their slope up to the nose, the air flow is directed downward and backward.

Abstract: A spherical gear pump that comprises two rotors, or geared spheres, with the teeth arranged around them in a circular band at right angles to their axis of rotation: the pump spheres are covered by close-fitting spherical cases or housings except at the central or most internal part of the connection between the gears on the two spheres, the fluid contained in the cavity created between the most external gears and the case or housing is moved during rotation from the intake to the outlet, one sphere is driven by its shaft and the other is dragged by the gearing between the two.

Abstract: A process for the recovery of the energy from the air in pressurised areas of aircraft that involves linking or moving air from the pressurised areas to the lower areas of the fuselage or lower surfaces of the wings, the horizontal stabilisers, and other aerodynamic profiles, along ducting and/or by discharging through multiple slots or openings flowing downward and rearward with a small inclination against the direction of the air flow, to avoid turbulence. The pressure of the pressurised cabin air conditioning is used. In other cases, it is used the pressure produced at the front of the fuselage, on the leading edges of the wings, the horizontal stabiliser or other aerodynamic profiles. Lift is increased in all cases without further energy requirements.

Abstract: The present invention is direct to an aircraft fuselage lift arrangement which includes an elongated vertically flattened oval cross section fuselage having a longitudinal axis; an upper longitudinal axis along the upper most portion of the fuselage and parallel to the longitudinal axis, a lower longitudinal axis parallel to the longitudinal axis and along the length of the bottom of the fuselage. The fuselage having a conical nose portion at one end and a conical tail portion at its opposite end. The nose portion of the fuselage having an upwardly inclined front wall extending upwardly from the bottom of the fuselage to at least the upper longitudinal axis of the fuselage. The tail portion of the fuselage having a downwardly declining rear wall extending from the upper longitudinal axis to the bottom of the fuselage. The fuselage also having a main landing gear.

Abstract: A wind energy catchment device comprising a central vertical shaft that rotates, the bottom end of which is secured by means of bearings to a rigid support fixed to the ground, the upper and lower part of the shaft have radial arms secured to it, evenly spaced one from the other, the outer ends of the upper arms are connected by cables or cords with its contiguous outer ends of the lower arms, between the upper and lower radial arms and the central shaft there are rectangular parallelepiped sails secured at their outer vertices. In all cases the furthest external vertical side of these sails or plates is secured and the sails or plates rotates from 90° to 180° with or around their shafts, cables or ropes that connect the ends of the arms, having both internal vertices loose, between the central shaft and two contiguous arms are arranged some parallel cords or mesh that support the sails or plates when they receive the air on the side of the mesh furthest from the wind.

Abstract: Wind energy catchment device that consists of loops of closed circuits of cables or ropes which go through a succession of parachutes in series, that rotates by means of pulleys among columns, pylons or shafts secured to rigid supports fixed to the ground, the cables go through the parachutes by their asymmetry axis, the cables are secured to the fabric of the parachute by their center zone, having the parachute a hole or holes around said cable, the ends of the strings of the parachute tie or join its periphery with a common point of the cable.

Abstract: The golf ball consists in a ball with diametric holes, perforations or orifices through it, spaced at appropriate distances on the surface and with a hollow center created by the crossing of the through orifices, or by an added spherical chamber, it can use also a central spherical compact zone or a rubber thread ball, using in this case tangential holes to said central zone.

Abstract: An aircraft lift arrangement that consists of fine fins which are parallel among themselves and slightly curved, arranged attached along the sides of the aircraft fuselage, beginning at the front and running downward toward the rear, with a positive angle of attack and with the additional of small thin wings to provide lateral stability and to carry the engines, flaps and ailerons.

Abstract: The wheel and track system comprises conventional rails on which the head cross-section can be also circular, semi-circular or oval, using with these main conventional wheels or pulley wheels, which support most of the wagon weight, having a roughly semi-circular cross-section channel between the web and the skid of the rail on one or both sides, in which inclined wheels rest, which have a peripheral or edge curvature also of semi-circular cross-section, to avoid derailment and support a part of the weight. In this way the rail can be used with mixed type wheels simultaneously or with wheels of just one type, depending on the vehicle used. This rail can also be used by actual trains.

Abstract: The present invention is direct to an aircraft fuselage lift arrangement which includes an alongated constant central cross section fuselage having a longitudinal axis; an upper longitudinal axis along the upper most portion of the fuselage and parallel to the longitudinal axis, a lower longitudinal axis parallel to the longitudinal axis and along the length of the bottom of the fuselage. The fuselage having a nose portion at one end and a tail portion at its opposite end. The nose portion of the fuselage having an upwardly inclined front wall extending upwardly from the bottom of the fuselage to at least the upper longitudinal axis of the fuselage. The tail portion of the fuselage having a downwardly declining rear wall extending from the upper longitudinal axis to the bottom of the fuselage. The fuselage also having a main landing gear.

Abstract: An aircraft lift arrangement that involves giving the fins or vertical elements, a positive angle slope in relation to their forward edge or transverse axis both on the leading and trailing edges, both beginning at the upper front and descending in an incline rearward as far as the base, to produce an inclined force on said vertical element which is broken down into two components, one horizontal and rearward, providing resistance to the advance, and the other a vertical, ascendant or lift component.

Abstract: Wind energy catchment device that consists of loops or closed circuits of cables or ropes which go through a succession of parachutes in series, that rotates by means of pulleys among columns, pylons or shafts secured to rigid supports fixed to the ground, the cables go through the parachutes by their asymmetry axis, the cables are secured to the fabric of the parachute by their center zone, having the parachute a hole or holes around said cable, the ends of the strings of the parachute tie or join its periphery with a common point of the cable.

Abstract: An aircraft lift arrangement that has a fuselage, wings, a nose, a tail and a landing gear and comprises a stretched, flattened fuselage which produces the lift both during forward movement and in side winds, the bottom of which is preferably flat and the top rounded, with narrow lengthened wings used mainly to carry the engines and provide the flight control surfaces, the nose inclined with a positive leading angle, the bottom surface flat and the top rounded, and the tail sloping downward, its lower surface flat and the top rounded, to prevent release of the limit layer in the upper areas, with large leading angles. The landing gear is moved rearward somewhat to allow greater nose pitch up attitude during takeoff and landing.

Abstract: The enhanced aerodynamic profile of the invention consists of a profile consisting of three sections: a front or leading edge of two sides or plates forming an acute dihedral angle with the vertex facing forward, a central section formed by two parallel sides or plates, and a rear section or trailing edge formed by two sides or plates at an acute dihedral angle with the vertex facing rearward, where the unions on the lower or upper surfaces are suitably rounded, where the front section is a fin or cone turning on an axis which divides it into two unequal parts, the rear part being larger, said fin or cone has the lower surface of its rear section inclined, adapting with another which is inclined in the upper front part of the central section, said fin with positive leading angles is automatically oriented with the direction of the slipstream.

Abstract: A spherical gear pump that comprises two rotors, or geared spheres, with the teeth arranged around them in a circular band at right angles to their axis of rotation: the pump spheres are covered by close-fitting spherical cases or housings except at the central or most internal part of the connection between the gears on the two spheres, the fluid contained in the cavity created between the most external gears and the case or housing is moved during rotation from the intake to the outlet, one sphere is driven by its shaft and the other is dragged by the gearing between the two.

Abstract: An automatic wing-flap that consists of the use of each side of the fuselage of additional small wings, which act simultaneously as individual wings and as flaps, fastened and divided with a rotating shaft parallel to the transversal axis of the aircraft in two pieces of different surface, where the front piece is the smaller, said both different pieces of the wing-flap have different resistance to the air ram, creating a rotation torque as a function of the aircraft's speed, when retracted or at high speed with a horizontal flap attitude, creating an independent wing and when they are completely extended with a maximum angle of attack they act like extended flaps, some extend bands or springs assist or complement the action of the smaller portion of the wing-flap whose resistance is such that, at low speed, the wing-flap remain extended, acting like a flap.

Abstract: Lifting arrangement for lateral aircraft surfaces that consists of numerous lateral flutings, grooves, splines, flutes or riblets parallel to each other, arranged on the lateral surfaces of fuselages, fin units, pylons and gondolas of aircraft with a downward slope from the nose to the tail, with the flow of air passing through such flutings, grooves, etc., towards the rear and downwards, generating lifting by reaction, using small planes o fins to support the engines and flight control fins.

Abstract: The device involves the placement of an air pump turbine and the aircraft outflow valve in a duct through which all the air flows, with the turbine shaft attached to that of an electric generator, to a hydraulic pump, and to the N2 and accessory gearbox inside the engine, the air is also sent through a duct to strike inclined against the tips of the fan blades and against the tips of the first stage of the low speed compressor blades of the turbine engine.

Abstract: Flight controls with automatic balance for use in controlling the movement of an aircraft through a fluid system, the control system includes ailerons divided into two parts, which at lower speed adopt the shape of a conventional aileron and rotate in their entirety with the same degree, and at high speeds a first part of the flap rotates or extends to a determinated angle by an actuator while the second part of the aileron, which is hinged or articulated to the first part of the aileron, rotates with reference to the main part, where the amount of rotation is a function of the air speed pressure, and one or more springs oppose the rotation caused by air speed pressure.

Abstract: The device involves the placement of an air pump turbine and the aircraft outflow valve in a duct through which all the air flows, with the turbine shaft attached to that of an electric generator, to a hydraulic pump, and to the N2 and accessory gearbox inside the engine, the air is also sent through a duct to strike inclined against the tips of the fan blades and against the tips of the first stage of the low speed compressor blades of the turbine engine.