Heretofore, it has been a common practice to design an inflatable shell to be assembled in the deployed configuration, without regard for the need to fold it into compact form. Typically, the result has been that folding has been a difficult, time-consuming process resulting in a poor stowed configuration. Hence, yet another problem is to design the shell to be assembled in the stowed configuration, bypassing the folding process at the vehicle level.
The problem of weight relief can be summarized as one of securing the stowed shell against shifting under its own weight during transport, without imposing excessive stress on any part of the shell. The weight-relief problem may not be significant in all applications, but launch acceleration makes it so in the original spacecraft application.
To solve these problems, in the improved method, one does more thanmerely choose the sizes and shapes of the gores to obtain the specified deployed shape of a shell. In addition, one chooses the sizes and shapes of the gores and the fold lines, in conjunction with the sequence of incorporation of the gores, to enable assembly of the shell in the stowed configuration, without interference between layers. To make this possible, the fold lines and the shapes of the gores are defined by equations that reflect the aforementioned problems and requirements. These equations incorporate the required modifications for the layers in each gore, accounting for the thicknesses of the layers and providing corresponding margins to prevent interference at fold lines.
The equations also provide for simplification of fold lines in double-curvature regions. For example, in the original application, the basic repeating unit for forming a cylinder with toroidal end caps consists of a gore designated B between two gores designated A/2, as shown in the figure. The B gore contains two straight fold lines that run the entire length, including the toroidal regions at the ends. The seams between the A/2 and B gores constitute a second pair of fold lines that are curved in the end regions, the curvature being such as to enable the flat folded pattern to deploy to the desired toroidal shape at the ends. When repeating units are joined together at vehicle installation, adjacent A/2 gores become a full A gore.
The weight-relief problem is solved by use of straps attached between (1) suitably chosen locations near fold lines and (2) adjacent supporting fixtures on a rigid structure on which the folded shell is to be stowed.
This work was done by Christopher J. Johnson of Johnson Space Center.
This invention is owned by NASA, and a patent application has been filed. Inquiries concerning nonexclusive or exclusive license for its commercial development should be addressed to the Patent Counsel, Johnson Space Center, (281) 483-1003. Refer to MSC-24149-1.