Abstract: A spacecraft berthing mechanism for coupling spacecraft is provided which has minimal effect on the maximum size an associated spacecraft hull may have. The berthing mechanism includes a flange member which defines a hatchway and which is adapted for attachment to a spacecraft port. The flange member has a forwardly facing interface surface through which the hatchway passes and an outer peripheral surface extending rearwardly from the interface surface. The peripheral surface has a plurality of beveled portions spaced substantially evenly about the peripheral surface. A plurality of alignment guides are arranged on the flange member such that several of the alignment guides are positioned adjacent one of the beveled portions and the remaining alignment guides are positioned adjacent an opposing beveled portion.

Abstract: A structural latch is provided for mechanically joining vehicle coupling mechanisms such as spacecraft coupling and berthing mechanisms. The structural latch is manually operable to join the coupling mechanisms. Each structural latch is configured to be readily removable from the joined coupling mechanisms in the event the latch becomes inoperable so as to effect coupling mechanism separation.

Abstract: A method and apparatus for joining vehicles such as spacecraft is disclosed that utilizes a capture and berthing technique. The coupling apparatus comprises a first coupling unit having a generally rigid extensible structure that is mountable to a first spacecraft and a second coupling unit having a probe-like structure mountable to a second spacecraft which is cooperable with the extensible structure to effect vehicle coupling. The first and second spacecraft are maneuvered so as to generally align the coupling apparatus thereon, after which the extensible structure is extended to engage and capture the probe-like structure. Following capture of the second coupling unit by the extensible structure, the extensible structure is subsequently retracted to effect berthing of the first and second spacecraft. Once the spacecraft coupling units have been captured and berthed in the foregoing manner, they can be structurally joined by appropriate coupling apparatus.

Abstract: A spacecraft berthing mechanism comprises a peripheral flange adapted for attachment to a spacecraft port, an impact receiving member pivotably attached to the peripheral flange, and a motion damping device connected between the impact receiving device and the peripheral flange. Edge-on berthing between two such berthing mechanisms allows for placement of the impact receiving members and damping devices along only a minor portion of the circumference of the berthing interface, thereby minimizing both the weight and complexity of the structure. The motion damping devices are of the non-rebound type and reset automatically after absorbing berthing impacts.

Abstract: A docking apparatus for coupling two spacecraft comprises a rigid pressure vessel having an interior passage, and first and second docking ports communicating with said interior passage. The planes of the docking ports form an oblique angle with respect to each other, causing the docked spacecraft to assume a canted or inclined relationship. The cant angle eliminates mechanical interference between the adjoining structures of the docked spacecraft. Methods for carrying out docking between spacecraft are also disclosed.

Abstract: A modular spacecraft system adapted for orbital flight is capable of expansion by the connection of at least two substantially identical spacecraft modules, each of which is capable of independent operation. Each spacecraft module comprises a spacecraft body, at least one solar array extendible outwardly from the spacecraft body, and at least one structural interface means for connecting one spacecraft module to another spacecraft module. Methods for deployment of a spacecraft module and for assembly of a modular spacecraft system utilizing a reusable space vehicle are also disclosed.

Abstract: A spacecraft is disclosed which comprises a spacecraft body, at least one solar array extendible outwardly from the spacecraft body, and articulation means for adjusting the position of the solar array relative to the spacecraft body independently about three axes, each of which is orthogonal to the axis adjacent to it. Each articulation means comprises a first rotatable coupling for permitting rotation of the solar array about a first axis substantially parallel to the surface of the spacecraft body, a second rotatable coupling for permitting rotation of the solar array about a second axis normal to the first axis, and a third rotatable coupling for permitting rotation of the solar array about a third axis normal to the second axis and parallel to the longitudinal axis of the array.

Abstract: A spacecraft is adapted for orbital flight in two alternative modes, referred to as the earth-oriented and quasi sun-oriented modes. The spacecraft comprises a spacecraft body, at least one solar array extendible outwardly from the spacecraft body, passive attitude control means utilizing gravity gradient stabilization means which is extendible and retractable relative to the spacecraft body, and active attitude control means. The gravity gradient stabilization means is effective when extended to stabilize the spacecraft in the earth-oriented mode, and the active attitude control means is effective to stabilize the spacecraft in the quasi sun-oriented mode.