Abstract: The invention relates to high stiffness parabolic structures utilizing integral reinforced grids. The parabolic structures implement the use of isogrid structures which incorporate unique and efficient orthotropic patterns for efficient stiffness and structural stability.

Abstract: A deployable structure that synchronously deploys in both length and width is disclosed which is suitable for use as a structural component for orbiting space stations or large satellites. The structure is designed with maximum packing efficiency so that large structures may be collapsed and transported in the cargo bay of the Space Shuttle. The synchronous deployment feature allows the structure to be easily deployed in space without a complex deployment mechanism. The structure is made up of interconnected structural units, each generally in the shape of a parallelepiped. The structural units are constructed of structural members connected with hinged and fixed connections at connection nodes in each corner of the parallelepiped. Diagonal members along each face of the parallelepiped provide structural rigidity and are equipped with mid-length, self-locking hinges to allow the structure to collapse.

Abstract: A zero-play pin clevis joint for deployable space structures includes a tapered pin and tapered bores extending through a shackle and through a tang such that the tapered pin is received in the tapered bores. Spring washers urge the tapered pin into the tapered bores of the shackle and also urge the tang onto the tapered pin. Deployable truss structures use a plurality of the aforementioned zero play pin clevis joints to connect a plurality of truss tubes. The angle of taper for the various components is preferably about 12.degree. included angle.

Abstract: This invention relates to a coupling device for tubular members (11 and 12), of large truss structures, with a locking collar 20 being the only moving part. Each tubular member is constructed with an end bell section 15 that has a belled flange 17 with a mating face 18, and a necked area 16 which is smaller in diameter than the tubular members to be joined. A split ring 30 is affixed to each tubular member and is constructed so that then two tubular members are laterally moved into axial alignment and collar 20 is rotated thereover, the split ring loads the joint with axial force by pressing the belled flange mating surfaces together, and a preloading force is provided by the collar 20 mating with a taper on the outside of the split rings. All free play is thereby removed by preloaded force. A major object of the invention is to provide an ability to remove and replace individual tubular members without disturbing other structural parts of a truss structure.

Abstract: A deployable geodesic truss structure can be deployed from a stowed state to an erected state. The truss structure includes a series of bays, each bay having sets of battens connected by longitudinal cross members which give the bay its axial and torsional stiffness. The cross members are hinged at their mid point by a joint so that the cross members are foldable for deployment or collapsing. The bays are deployed and stabilized by actuator means connected between the mid point joints of the cross members. Hinged longerons may be provided to also connect the sets of battens and to collapse for stowing with the rest of the truss structure.

Abstract: The disclosure relates to a deployable M-braced truss structure that is efficiently packaged into a compact stowed position and expandable to an operative position at the use site. The M-braced configuration effectively separates tension-compression and shear in the structure and permits efficient structural design. Both diagonals and longerons telescope from an M-braced base unit. They are deployed either pneumatically, mechanically by springs or cables, or by powered reciprocating mechanisms. Upon full deployment, the diagonals and longerons lock into place with a simple latch mechanism.

Abstract: This invention relates to a lattice type structural panel utilizing the unidirectional character of filamentary epoxy impregnated composites to produce stiff lightweight structural panels for use in constructing large area panels for space satellites and the like.

Abstract: This invention relates to a lattice type structural panel utilizing the unidirectional character of filamentary epoxy impregnated composites to produce stiff lightweight structural panels for use in constructing large area panels for space satellites and the like.