Inflatable Wing

This invention relates generally to inflatable structures and more specifically to such structures used for aerodynamic surfaces. Inflatable aerodynamic surfaces have been used previously, but such structures are quite different in construction from the inflatable wing of the present invention. Previous devices involve the use of two panels of treated cloth one of which forms the upper surface of the wing and the other of which forms the lower wing surface. These air tight surfaces are joined together at the edges with a pressure tight seal so that the edges form the leading edge, trailing edge, and wing tip. Surface shape is maintained by joining the upper and lower surface with multitude of threads of varying length. These threads, which number approximately 100 to the inch are run in rows and permit the surfaces to separate only to the length of the threads. The threads function only to keep the fabric spaced at the predetermined distance and do not compartmentalize the volume in any manner. The entire wing volume is one air container and a leak in any portion of the surface will deflate the entire structure.

The present invention uses a compartmentalized structure to increase the structural strength and to minimize the danger of loss of air pressure.

The wing structure is constructed of a series of circular cross section cylindrical chambers whose axial length runs essentially traverse to the airstream direction. Each inflatable structure is composed of a number of these cylinders butted and bonded together at their tangents which give the structure its basic shape when inflated. Flexible membranes are used to cover the ridges formed by the abutting cylinders and are bonded to the tangents of the cylinders to form aerodynamically smooth surfaces on the tip and bottom of the wing. The cylinders may be inflated from common or independent manifolds, but simplicity suggests the use of the common manifold. Simple check valves on each individual cylinder are then used to prevent a leak in one cylinder from deflating the whole structure. Since inflatable structures tend to inflate to a membrane or circular geometry, the basic geometry of the cylinders matches the membrane state of stress and yields a stronger structure which is less subject to distortion from external forces. Moreover, because of the initial tube shape, the cylinder structure is exceptionally stable with variations in pressure beyond the initial pressurization required for inflation. This is a particular advantage for aerodynamic surfaces where shape is critical since variations in airspeed and altitude change the effective pressure differential to which such structures are subjected. The present invention, therefore, makes available a superior inflatable aerodynamic structure with higher structural strength, greater stability and less danger of deflation.

FIG. 1 is a sectional perspective view of the structure of the invention.

FIG. 2 is a sectional perspective view of an alternate embodiment of the invention.

FIG. 3 is a cross section view of the deflated wing folded for storage.

The basic structure of the invention is shown in FIG. 1. Inflatable wing 10 is constructed of air tight fabric cylinders 12, 14, 16, 18, and 22 of the same cross sectional size whose axis are all parallel. In this embodiment, the cylinders are oriented so that their lines of tangency 24, 26, 28, 30, and 32, at which they abut and are bonded for essentially their entire length, all fall in a single plane. This configuration yields a basic flat wing surface when upper cover 34 which is bonded to the uppermost tangent lines of the cylinder and lower cover 36 which is bonded to the lower tangent lines of the cylinders are stretched taut by the inflation of the air tight cylinders. Inflatable wing 10 is made to terminate at edge 38 in a section which is not perpendicular to the axis of the cylinder by varying the length of each cylinder and sealing the cylinders at edge 38. As shown in FIG. 1 the cylinder lengths are made progressively longer between cylinder 12, the shortest length, and cylinder 22, the longest.

FIG. 2 depicts the configuration of the invention which results in a curved aerodynamic surface. For such a configuration enclosures 42, 44, 46, 48, 50, 52, 54, 56, and 58 progressively vary in cross sectional diameter. Furthermore, the abutting tangency lines of these cylinders are varied to adjust the shapes of upper wing surface 40 and lower wing surface 60. The locus 62 of the tangency lines of the cylinders 42 through 58 is a curved surface rather than a flat plane. The lengths of cylinders 42 through 58 are all equal resulting in an end section 64 of the surface which is perpendicular to the axis of the cylinders. The diameters of enclosures 42, 44, 46, 54, 56, and 58 are also shown to decrease as the axial distance increases. This taper of the essentially conical configuration results in a decrease in the width of the aerodynamic surface as the length increases. FIG. 2 thus shows a practical configuration for a typical airfoil. It is to be understood that this shape of enclosure can also be used in an arrangement where all of the enclosures are tapered.

FIG. 3 depicts an end view of the wing in cross section in which a single cylinder 70 of the inflatable wing can be seen compressed into a storage compartment 72 of a vehicle body 74. For such an arrangement, cylinder 70 is deflated and placed into compartment 72 in folds 76, being held in place by bonding at surface 71. For deployment of the inflatable wing, air pressure is applied through common manifold 78 to all cylinders of a wing. This causes air flow through check valve 80 which permits air flow only in the direction from common manifold 78 toward cylinder 70. Since no air will flow in the opposite direction through check valve 80, cylinder 70, once inflated, cannot be deflated by a single leak in one of the other cylinders. Also, as shown in FIG. 3, cylinder 70 may be held in place in compartment 72 by being clamped into space 83 between surface 82 and holding block 84, by clamping screw 86.

It is also to be understood that the forms of the invention herein shown are merely preferred embodiments. Various changes may be made in shape, size, or arrangement of parts; equivalent means may be substituted for those illustrated and described; and certain features may be used independently from other features without departing from the spirit and scope of the invention. For example, cylinder cross section may be varied while keeping the tangency points in a single plane to yield identical curves on both the upper and lower surface of the wing. Moreover, the check valve may be omitted from FIG. 3 if little likelihood of accidental deflation exists.