Aircraft Spade Apparatus

Abstract

An aileron counterbalance or aircraft spade apparatus disposed to afford optimal drag force, which particularly enhances the capability of an aircraft to spin, turn and dive more quickly and efficiently in aircraft races. The aircraft spade apparatus includes a rectangular shape and which exhibits a greater surface area and higher drag force characteristics.

Claims

1. An aileron counterbalance apparatus comprising: a linearly disposed rectangular structure comprising an under layer of twisted composite material, a laminate top coat and a set of mounting apertures.

2. The aileron counterbalance apparatus of claim 1 wherein the under layer of twisted composite material is visible through the laminate top coat.

3. The aileron counterbalance apparatus of claim 1 wherein the aileron counterbalance apparatus comprises no downwardly-extending spade flanges.

4. The aileron counterbalance apparatus of claim 1 wherein the aileron counterbalance apparatus comprises a uniform thickness.

5. The aileron counterbalance apparatus of claim 1 further comprising a set of mounting apertures.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Advantages of the present system will be apparent from the following detailed description of exemplary embodiments thereof, which description should be considered in conjunction with the accompanying drawings, in which having thus described the system in general terms, reference will now be made to the accompanying drawings, which are not necessarily drawn to scale, and wherein:

[0021] FIG. 1 illustrates a front view of the one embodiment of the instant aircraft spade or aileron counterbalance apparatus layered above a concurrent state of the art aircraft spade.

[0022] FIG. 2 illustrates a front view of the one embodiment of the instant aircraft spade or aileron counterbalance apparatus layered below a concurrent state of the art aircraft spade.

[0023] FIG. 3 illustrates a front view of one embodiment of the aircraft spade apparatus.

[0024] FIG. 4 illustrates a front perspective view of the preferred embodiment of the aircraft spade apparatus.

[0025] FIG. 5 illustrates an environmental side view of the present apparatus during testing.

[0026] FIG. 6 illustrates an environmental side view of the present apparatus at the desired angle for use.

[0027] FIG. 7 illustrates a side view of one embodiment of the aircraft spade apparatus.

[0028] FIG. 8 illustrates top plan view of one embodiment of the aircraft spade apparatus illustrated in FIG. 7.

[0029] FIG. 9 illustrates a spade aerodynamics testing profile for one embodiment of the instant apparatus.

DETAILED DESCRIPTION OF THE SEVERAL EMBODIMENTS

[0030] The detailed description set forth below in connection with the appended drawings is intended as a description of presently preferred embodiments of the system and does not represent the only forms in which the present system may be constructed and/or utilized. The description sets forth the functions and the sequence of steps for constructing and operating the system in connection with the illustrated embodiments.

[0031] In fluid dynamics, drag (sometimes called air resistance, a type of friction, or fluid resistance, another type of friction or fluid friction) is a force acting opposite to the relative motion of any object moving with respect to a surrounding fluid. This can exist between two fluid layers (or surfaces) or a fluid and a solid surface. Unlike other resistive forces, such as dry friction, which are nearly independent of velocity, drag forces depend on velocity. Drag force is proportional to the velocity for a laminar flow and the squared velocity for a turbulent flow. Even though the ultimate cause of a drag is viscous friction, the turbulent drag is independent of viscosity. Drag forces always decrease fluid velocity relative to the solid object in the fluid's path.

[0032] Utilizing these principles, the instant apparatus introduces a novel configuration including a rectangular structure which allows for a greater coefficient of drag for superior maneuverability during aerial acrobatics as illustrated herein.

[0033] FIG. 1 illustrates a front view of one embodiment of the instant spade apparatus 16 or aircraft aileron counterbalance mechanism, layered over a concurrent state of the art embodiment of an aircraft spade apparatus 10 used within the industry, in order to illustrate the greater useful surface area gained by the instant spade apparatus 16. As illustrated, the concurrent embodiment 10 employees a triangular configuration and offers less overall surface area.

[0034] The surface of the aircraft spade apparatus 16 may comprise a laminate top coat 12. The main structure of the aircraft spade apparatus 16 is comprised of an under layer of twisted composite material 13 which is visible through the laminate top coat 12. The aircraft spade apparatus 16 additionally comprises a series or set of mounting apertures 14. Within the set of mounting apertures 14, at least two upper apertures 26, 24 may be located in proximity to upper portion of the aircraft spade apparatus 16 and at least one aperture, which may be located near the center of the apparatus, or a center aperture 28. The center aperture 28 is equidistant from the at least two upper apertures 26, 24.

[0035] FIG. 2 illustrates a front view of one embodiment of the instant aircraft spade 16 or aileron counterbalance apparatus layered below a concurrent state of the art aircraft spade 10 for comparative purposes to further illustrate the greater useful surface area gained by the instant system. Once again, the concurrently employed aircraft spade 10 features a triangular shape and inherently less surface area overall. The instant apparatus 16 is featured directly behind the concurrent embodiment 10 in order to illustrate the difference in shape and surface area.

[0036] FIG. 3 illustrates a front view of one embodiment of the aircraft spade apparatus 16. Upper apertures 26, 24 are illustrated and located below the upper portion 20 of the aircraft spade apparatus 16. In one embodiment, the upper apertures 26, 24 may be located at one-fourth () inch below the upper portion 20 of the present aircraft spade apparatus 16, in order to allow for proper fracture and stress/strain properties surrounding upper apertures 26, 24.

[0037] In one embodiment, each individual upper aperture 26 and 28 may be at a specified distance 22 away from the nearest vertical side of the present apparatus 16. In one embodiment, the specified distance 22 away from the nearest vertical side of the present apparatus 16 may be two and one quarter inches (2) inches.

[0038] The center aperture 28 should be located equidistantly from the vertical sides in order to allow for proper fracture and stress/strain properties. In one embodiment, the center aperture 28 may be located three (3) inches from the vertical sides at in length 32 from the vertical sides of the instant apparatus 16.

[0039] FIG. 4 illustrates a front perspective view of one embodiment of the aircraft spade apparatus 16. In this embodiment, the bottom and top edges 34 are shown to be six and one quarter (6) inches in length. The two vertical sides 30 are shown to be seven and one quarter 7 inches in length. Thus, the aircraft spade apparatus 16 employees a uniform thickness throughout, and in one embodiment may be shown to be inches 46.

[0040] FIG. 5 illustrates a side view of the present apparatus 16 constrained for wind tunnel testing.

[0041] FIG. 6 illustrates a side view of the present apparatus 16 constrained for wind tunnel testing at a desired angle of forty-five degrees (45).

[0042] FIG. 7 illustrates a side view of one embodiment of the aircraft spade apparatus 16 embarked for usage and attached to the lower portion of a fuselage of a plane.

[0043] FIG. 8 illustrates top plan view of the embodiment of the aircraft spade apparatus 16 of FIG. 7.

[0044] FIG. 9 illustrates a spade aerodynamics testing profile for one embodiment of the instant apparatus.