Docking structure for spacecraft

Claim 2

A spacecraft having a docking structure at the docking end thereof, said docking structure comprising: a cylindrical wall at said docking end of said spacecraft; a docking section comprising an open-ended receptacle located within said wall and being adapted To receive a corresponding projection on another spacecraft; the end of said receptacle opposite said open end being closed in a gas-tight manner; extendible and retractable supporting means for supporting said receptacle within said wall whereby said receptacle may be extended and retracted longitudinally of said wall; a gas-tight compartment within said wall adjacent said closed end of said receptacle; means for gas pressurizing said compartment and thereby exerting pressure on said receptacle toward the extended position of said receptacle; said compartment comprising flexible means extending around said receptacle for maintaining a gas-tight compartment during extension and retraction movement of said receptacle; means for controllably releasing gas from said compartment.

Claim 3

The invention as defined in claim 1 wherein said receptacle comprises means adapted for engaging latching means of a corresponding docking projection on another spacecraft.

Claim 4

The invention as defined in claim 1 wherein said receptacle is conical in shape and is disposed concentrically within said wall, means including said flexible means for permitting the volume of said compartment to vary in response to variations in gas pressure within said compartment and extension and retraction movement of said receptacle.

Claim 5

The invention as defined in claim 3 wherein said flexible means comprises a gas-tight membrane joined to the convergent end portion of said conical receptacle, a portion of said membrane contacting and conforming to the conical outer surface of said receptacle when said receptacle is in the retracted position while the remaining portion of said membrane extends in an arcuate curvature from the outer surface of said receptacle toward said wall.

Claim 6

The invention as defined in claim 1 wherein said means for supporting said receptacle comprises a plurality of gas-actuated cylinders, each of said cylinders comprising a piston and piston rod, said cylinders being pivotally anchored to said wall, said piston rod being pivotally joined to said receptacle.

Claim 7

The invention as defined in claim 5 wherein means are provided on said pistons of said cylinders for increasing friction between said pistons and the walls of said cylinders.

Claim 8

Docking structure for in-flight docking of a pair of spacecraft comprising: an extendible and retractable docking section carried by the docking end of one of said pair of spacecraft; said docking section comprising an open-ended receptacle; the end of said receptacle opposite said open end being closed in a gas-tight manner; a docking projecting section carried by the docking end of the other of said pair of spacecraft; said projecting section corresponding in shape to said receptacle whereby said projecting section may enter and nest within said receptacle; said one of said spacecraft having a gas-tight compartment in the docking end region thereof inwardly of said receptacle adjacent said closed end thereof; means for gas pressurizing said compartment; said closed end of said receptacle being exposed to gas pressure within said compartment when pressurized whereby such pressure would be applied against said closed end of said receptacle; extendible and retractable means for supporting said receptacle whereby said receptacle may extend and retract under influence of pressure within said compartment and of docking force applied by said other spacecraft through said projection.

Claim 9

Docking structure for in-flight docking of a pair of spacecraft comprising: an extendible and retractable docking section carried by the docking end of one of said pair of spacecraft; said docking section comprising an open-ended receptacle; the end of said receptacle opposite said open end being closed in a gas-tight manner; a docking projecting section carried by the docking end of the other of said pair of spacecraft; said projecting section corresponding in shape to said receptacle whereby said projecting section may enter and nest within said receptacle; said one of said spacecraft having a gas-tight compartment in the docking end region thereof inwardly of said receptacle adjacent said closed end thereof; means for gas pressurizing said compartment; said closed end of said receptacle being exposed to gas pressure within said compartment when pressurized whereby such pressure would be applied against said closed end of said receptacle; extendible and retractable means for supporting said receptacle whereby said receptacle may extend and retract under influence of pressure within said compartment and of docking force applied by said other spacecraft through said projection.

Claim 10

The invention as defined in claim 7 wherein said compartment comprises an extendable and retractable flexible membrane, said membrane being adapted to extend when said receptacle extends and retract when said receptacle retracts.

Claim 11

The invention as defined in claim 8 including means for latching said projection to said receptacle when said receptacle is in the extended position and further means for latching the pair of spacecraft together when the receptacle is in the retracted position.

Claim 12

The Invention as defined in claim 8 wherein said receptacle and said projection are conical in shape, said membrane extending around and being attached to said receptacle, said membrane conforming to the conical shape of said receptacle when said receptacle and said membrane are in the retracted position.