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US 8,006,937 B1Granted
Spacecraft docking interface mechanism
AssigneeThe United States of America as represented by the Secretary of the Navy
InventorsMarcello Romano, Paul Oppenheimer
Life of this patent
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Abstract
A demountable docking interface mechanism and method for docking and undocking two spacecraft utilizing the demountable docking interface mechanism.
Claims19
A docking interface mechanism for spacecraft comprising:
- a frame;
- at least one alignment pin extending outward from the frame, the at least one alignment pin comprising:
- a sleeve;
- a shape memory alloy coupling mounted within the sleeve, the shape memory alloy coupling formed of a shape memory alloy;
- an alignment pin pipe located within the sleeve;
- and
- at least one heater mounted within the sleeve, the heater for controlling the temperature of the shape memory alloy coupling,
- wherein the at least one alignment pin is configured for insertion within a corresponding alignment cup of another docking interface mechanism when the shape memory alloy coupling is below an associated austenitic temperature of the shape memory alloy,
- wherein the at least one alignment pin is further configured to form a rigid mechanical connection with an alignment cup pipe in the corresponding alignment cup when the temperature of the shape memory alloy coupling increases to an associated austenitic temperature of the shape metal alloy,
- wherein the at least one alignment pin is further configured to release the rigid mechanical connection when the temperature of the shape memory alloy coupling decreases to an associated martensitic temperature of the shape metal alloy;
- and
- at least one alignment cup set in the frame, the at least one alignment cup configured to receive a corresponding alignment pin, the at least one alignment cup including an alignment cup pipe.
9 more elements
A method comprising:
- obtaining a first spacecraft, the first spacecraft having a first demountable docking interface mechanism, the first demountable docking interface mechanism comprising:
- a frame;
- a plurality of first alignment pins extending outward from the frame, each of the plurality of first alignment pins comprising:
- a sleeve;
- a shape memory alloy coupling mounted within the sleeve, the shape memory alloy coupling formed of a shape memory alloy;
- an alignment pin pipe located within the sleeve;
- and
- at least one heater mounted within the sleeve, the heater for controlling the temperature of the shape memory alloy coupling;
- and
- a plurality of first alignment cups set in the frame, each including an alignment cup pipe;
- obtaining a second spacecraft, the second spacecraft having a second demountable docking interface mechanism, the second demountable docking interface mechanism comprising:
- a frame;
- a plurality of second alignment pins extending outward from the frame, each of the plurality of alignment pins comprising:
- a sleeve;
- a shape memory alloy coupling mounted within the sleeve, the shape memory alloy coupling formed of a shape memory alloy;
- an alignment pin pipe located within the sleeve;
- and
- at least one heater mounted within the sleeve, the heater for controlling the temperature of the shape memory alloy coupling;
- and
- a plurality of second alignment cups set in the frame, each including an alignment cup pipe;
- inserting each of the plurality of first alignment pins into corresponding second alignment cups, and each of the plurality of second alignment pins into corresponding first alignment cups, when each of the shape memory alloy couplings is below an associated austenitic temperature until a soft mate condition is achieved;
- and
- increasing the temperature of each of the shape memory alloy coupling to an associated austenitic temperature to form a rigid hard mate demountable docking connection between the first spacecraft and the second spacecraft.
20 more elements
Dependencies are inferred from the claim text.