Aircraft lift arrangement

Abstract: An aircraft lift arrangement that involves giving the fins (10) or vertical elements (4,15), a positive angle slope in relation to their forward edge or transverse axis both on the leading (5) and trailing (6) 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 (D), providing resistance to the advance, and the other a vertical, ascendant or lift component (L).

Description: Field of the invention: On vertical fins or projections. Description of the prior art. Aircraft lift enhancement involving inclined surfaces is for instance known from prior art document EP-A-0 827 905, current fins or vertical elements are inclined against the transversal axis to produce a downward force which reduces aircraft lift, all of which is corrected with the present invention. Brief summary of the invention . The aircraft lift arrangement involves giving the fins or vertical elements, engine pylons and lateral portions of their cowls, fin units, launcher-tank, rocket, floats and skids mounts, struts or brackets, external cables and antennas a positive angle slope in relation to the 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. This provides a twin benefit, on the one hand eliminating the downward force and on the other generating an upward force or lift of the same value. In other cases, the arrangement both generates lift and simultaneously reduces forward resistance. The leading edge of these fins, mounts, etc. creates greater lift that the trailing edge with the same inclination. The lift generated is generally high as such fins or vertical elements require a certain thickness in order to fulfil their aerodynamic profile role as well as to house ducting or control elements, etc., so that their cross-section or front area is greater. It may also be used in sideways sloping fins. Given the foregoing, it is advisable wherever feasible to use vertical fins or elements rather than horizontal types with this arrangement. Advantages: on increasing its lift, its efficiency increases, it is simple and inexpensive. BRIEF DESCRIPTION OF THE DRWINGS Figure 1 shows a partial side view of an aircraft without the arrangement of this invention. Figure 2 shows a schematic, partial, side view of an aircraft with the arrangement of this invention. Figure 3 and 5 show schematic, partial, side views of several variants. DETAILED DESCRIPTION OF THE INVENTION Figure 1 consists of the aircraft fuselage 1, the wing 2, the engine cowl 3, the pylon 4, the downward force F 1 and the resistance D 1 of the leading edge 5 and the downward force F 2 and the resistance D 2 of the trailing edge 6. Downward forces are the present drawbacks. Figure 2 consists of the wing 2, the engine cowl 3, the pylon 4, the lift L 1 and the resistance D 1 of the leading edge 5 and the lift L 2 and resistance D 2 of the trailing edge 6, where the lift L 3 and the resistance D 3 of the side leading edges 7 and the lift L 4 and the resistance D 4 of the cowl trailing edge 8, 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. Figure 3 consists of the fuselage 1, the wing 2, the engine cowl 3, the pylon 4, the lift L 1 and the resistance D 1 of the leading edge 5 and the lift L 2 and the resistance D 2 of its trailing edge 6, it only shows the improvement on the pylon. Figure 4 consists of the wing 2, the engine cowl 3, the rocket mount 4, the lift L 1 and the resistance D 1 of the leading edge 5 and the lift L 2 and the resistance D 2 of the trailing edge 6. This arrangement is also typical with launcher-tank, rocket, floats and skis mounts etc. Figure 5 consists of the fuselage 1, the fin unit 10, the lift L 1 and the resistance D 1 of the leading edge 11 and the lift L 2 and the resistance D 2 of its trailing edge 12 on the rudders 13, the tail 14, and the lift L and the resistance D of the antenna 15. The arrows indicate the airflow.

Claims: A method of providing an aircraft lift arrangement that involves giving the fins or vertical elements (4,7,8 and 10), a positive angle slope in relation to the forward edge or transverse axis both on the leading and trailing edges, both beginning at the upper front (5, 6, 7 and 8) 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 (D1, D2, D3 and D4), providing resistance to the advance, and the other a vertical, ascendant or lift component (L1, L2, L3 and L4). A method as claimed in claim 1, wherein the fins and vertical elements are engine pylons (4 Figure 2). A method as claimed in claim 1, wherein the fins and vertical elements are lateral portions of their cowls (7 and 8). A method as claimed in claim 1, wherein the fins and vertical elements are fin units (10). A method as claimed in claim 1, wherein the fins and vertical elements are rocket mounts (4, figure 4). A method as claimed in claim 1, wherein the fins and vertical elements are launcher-tank mounts. A method as claimed in claim 1, wherein the fins and vertical elements are aircraft float mounts. A method as claimed in claim 1, wherein the fins and vertical elements are aircraft skis mounts. A method as claimed in claim 1, wherein the fins and vertical elements are external cables and antennas (15). A method as claimed in claim 1, wherein the fins are sideways sloping fins.

Inventors: MUNOZ SAIZ MANUEL, MUNOZ SAIZ, MANUEL
Applicants: MUNOZ SAIZ MANUEL, MUNOZ SAIZ, MANUEL
Application year: 2000
Main classification: B64C1
IPC codes: B64D29, B64D27, B64C7