GIVEN THAT TRANSPORT INTO SPACE IS HIGHLY SIZE AND WEIGHT CONSTRAINED SIGNIFICANT RESEARCH AT NASA HAS BEEN CONDUCTED ON THE DESIGN OF MULTIPURPOSE (RECONFIGURABLE) STRUCTURES. HOWEVER MOST OF THESE STRUCTURES ARE NOT DEPLOYABLE FROM A COMPACTED STATE. IN ADDITION THEY REQUIRE MANUAL ASSEMBLY OF NUMEROUS PARTS AND OFTEN MUST BE PHYSICALLY RECONFIGURED FOR SIGNIFICANT STRUCTURAL CHANGE. HERE I WILL DEVELOP DEPLOYABLE AND RECONFIGURABLE COMPLIANT MECHANISMS BASED ON ORIGAMI AND POP-UP BOOK FOLDING PRINCIPLES THAT WILL BE REALIZED WITH HIGH STRENGTH BULK METALLIC GLASS. TO CREATE THESE STRUCTURES LAMINATE DESIGN AND MANUFACTURING TECHNIQUES AS WELL AS THERMOPLASTIC FORMING WILL BE USED. THESE MANUFACTURING PROCESSES ALLOW FOR THE PROPOSED COMPLIANT STRUCTURES TO BE FABRICATED AT A VARIETY OF SCALES WITH MINIMAL MANUAL ASSEMBLY. TO ACHIEVE THIS GOAL THIS PROJECT WILL BE CARRIED OUT IN THREE PHASES. IN THE FIRST PHASE LAMINATE DESIGN AND MANUFACTURING WILL BE USED TO REALIZE VOXEL (LINKAGE) ARRAYS CONSISTING OF REPEATED LINKAGES TO ACHIEVE UNIQUE OUTPUT MOTION AND GEOMETRY. ADDITIONALLY LOCALLY ALTERING THE MATERIAL THICKNESS OF METALLIC GLASS WILL BE EXPLORED AS AN ALTERNATIVE METHOD FOR CREATING FLEXURES. IN THE SECOND PHASE THE MATERIAL AND STRUCTURAL PERFORMANCE WILL BE CHARACTERIZED ALLOWING FOR THE OPTIMIZATION OF THE DESIGN AND FABRICATION OF THESE COMPLIANT STRUCTURES. FINALLY THESE STRUCTURES WILL BE USED TO DEMONSTRATE THEIR ABILITY TO BE DEPLOYED AND WITHSTAND LARGE PRESSURE DIFFERENCES NECESSARY FOR THEIR DEPLOYMENT IN SPACE. THESE RESULTS WILL YIELD MULTIPURPOSE STRUCTURES FOR A VARIETY OF USES IN SPACE INCLUDING HABITAT DEVELOPMENT AND SOLAR ARRAYS AS WELL AS FOR POTENTIAL USE AS A DEPLOYABLE MANIPULATOR FOR REMOTE MANIPULATION TASKS.