Lift arrangement for lateral aircraft surfaces

Abstract: Lifting arrangement for lateral aircraft surfaces that consists of numerous lateral flutings, grooves, 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 orfins to support the engines and flight control fins.

Description: BACKGROUND OF THE INVENTION FIELD OF THE INVENTION On lateral surfaces of fuselages, fin units, pylons and gondolas of aircraft. DESCRIPTION OF THE RELATED ART. The lateral surfaces of existing aircraft are smooth, and if they are wave-shaped, they are parallel to the centre line of the aircraft and, as a result, do not produce a lifting effect. Other like EP-A-1 104 741 (state of the art according to Article 54(3)EPC or US-A-338538) use lateral fine fins arranged on the lateral surfaces of the fuselages. DESCRIPTION OF THE INVENTION. The lifting arrangement for lateral aircraft surfaces consists of lateral flutings, grooves 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. The flutings, grooves, etc., can be straight or curved with their convexity in an upward direction. The front area of the flutings, grooves, etc., can have a negative or upward slope from the nose up to approximately one-fifth of the length of the flutings, grooves, etc. The horizontal tail assemblies should be larger. In a variant of the invention, part of the lift is obtained by means of the wings and the rest by means of the flutings, grooves, etc. The flutings and grooves can be rounded or wave-shaped or with flanges or edges or sawtooths, horizontal or sloped upward or downwards. In a variation of the invention, the flutings, grooves, etc., are arranged in several stretches in series. The total drag to forward movement is less than that of aircraft with wings. BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 through 7 show partial side schematic views of different fuselages with the lifting arrangement of the invention. Figures 8 through 12 show schematic different cross-section views with the lifting arrangement of the invention. DETAILED DESCRIPTION OF THE INVENTION LIST OF REFERENCE NUMERALS The drawing shows the fuselage (1), the flutings, grooves, etc., (2 and 2'), the input of a portion of the flow (3), and its output (4), the relative air flow (5), the horizontal stabiliser (6), the fin unit (7), the small plane or fin (8) and the front of the flutings, grooves, etc., (9) with a negative or upward slope from the nose up to approximately one-fifth of the length of the flutings, grooves, etc. Figure 1 shows an aircraft whose fuselage has lateral flutings, grooves, etc., (2) of the straight type, where the air arrives at the area (3) of the flutings, grooves, etc., zone and descends leaving the area (4), having the flutings, grooves, etc., 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 L by reaction and the induced drag D. Figure 2 shows an aircraft whose fuselage has flutings, grooves, etc., of the curved type with the front of the flutings, grooves, etc., (9) with a negative or upward slope from the nose up to approximately one-fifth of the length of the flutings or grooves. Figure 3 shows a variant with the grooves of the curved type more spaced out. Figure 4 shows another variant that adds the smaller plane or fin (8). Figure 5 shows the grooves arranged in several stretches in series (2). Figure 6 and 7 show two arrangement with a variant of fuselage. Figure 8 shows the cross-section fuselage (1), with the rounded or wave-shaped grooves (2). Figure 10 shows the cross-section fuselage (1), with the flanges, or sawtooths (2) sloped outwards and downwards. Figure 11 shows the cross-section fuselage (1), with the flutings (2). Figure 12 shows the cross-section fuselage (1), with the flanges (2) sloped outwards and upwards.

Claims: An aircraft comprising a lifting arrangement on its lateral surfaces that consists of numerous lateral flutings, grooves or riblets parallel to each other, arranged on lateral surfaces of one or more of the fuselages, fin units, pylons and gondolas of the aircraft, having a downward slope from the nose to the tail, with the flow of air passing through said flutings, grooves or riblets, etc., towards the rear and downwards, generating lifting by reaction. An aircraft according to claim 1, wherein the flutings, grooves, etc., are straight. An aircraft according to claim 1, wherein the flutings, grooves, etc., are curved with their convexity in an upward direction. An aircraft according to claim 1, wherein the front area of the flutings, grooves, etc., have a negative or upward slope from the nose up to approximately one-fifth of the length of the flutings, groves, etc. An aircraft according to claim 1, wherein part of the lift is obtained by means of the wings and the rest by means of the flutings, grooves, etc. An aircraft according to claim 1, wherein the grooves are rounded or wave-shaped. An aircraft according to claim 1, wherein the flutings have horizontal flanges or edges or sawtooth. An aircraft according to claim 1, wherein the flutings have flanges or groves or sawtooth sloped upwards. An aircraft according to claim 1, wherein the flutings have flanges or groves sawtooth sloped downwards. An aircraft according to claim 1, wherein the flutings, grooves, etc., are arranged in several stretches in series.

Inventors: MUNOZ SAIZ MANUEL, MUNOZ SAIZ, MANUEL
Applicants: MUNOZ SAIZ MANUEL, MUNOZ SAIZ, MANUEL
Application year: 2001
Main classification: B64C3
IPC codes: B64C3, B64C39