ADVANCED TECHNOLOGIES, INC.

DESIGN, ANALYSIS AND FABRICATION OF C4 BLADE SET 2 - DESIGN, ANALYSIS, FABRICATION AND CALIBRATION OF A HIGHLY INSTRUMENTED C4 ROTOR BLADE SET FOR HIGH SPEED FORWARD FLIGHT IN THE 14X22 FOOT SUBSONIC WIND TUNNEL.

DESIGN OF A MODEL-SCALE COAXIAL ROTOR AEROELASTIC TESTBED (MSCRAT) WITH THE INCLUSION OF THREE OPTION PERIODS TO ALLOW FOR FABRICATION OF THE TESTBED, HOVER STAND MODIFICATIONS, AND A MODULAR TAIL CONE, IF EXERCISED.

DESIGN, ANALYSIS, AND FABRICATION OF MOUNTING HARDWARE TO TEST AN EXISTING 11.8% SCALE SEMISPAN TRANSONIC TRUSS BRACED WING MODEL (TTBW) IN NASA'S 14X22 SUBSONIC TUNNEL.

DESIGN OF A MODEL-SCALE COAXIAL ROTOR AEROELASTIC TESTBED (MSCRAT) WITH THE INCLUSION OF THREE OPTION PERIODS TO ALLOW FOR FABRICATION OF THE TESTBED, HOVER STAND MODIFICATIONS, AND A MODULAR TAIL CONE, IF EXERCISED.

DESIGN OF A MODEL-SCALE COAXIAL ROTOR AEROELASTIC TESTBED (MSCRAT) WITH THE INCLUSION OF THREE OPTION PERIODS TO ALLOW FOR FABRICATION OF THE TESTBED, HOVER STAND MODIFICATIONS, AND A MODULAR TAIL CONE, IF EXERCISED.

FABRICATION OF THE 2.7% SCALE FULL SPAN AND SEMI-SPAN HIGH LIFT COMMON RESEARCH MODEL FOR TESTING IN THE NASA LANGLEY NATIONAL TRANSONIC FACILITY. IT WILL HAVE MODULAR COMPONENTS TO ENABLE THE MODEL TO BE TESTED IN TAKEOFF AND LANDING CONFIGURATIONS.

ELECTRICAL FLANGE PLATE WORK ORDER

DESIGN OF A MODEL-SCALE COAXIAL ROTOR AEROELASTIC TESTBED (MSCRAT) WITH THE INCLUSION OF THREE OPTION PERIODS TO ALLOW FOR FABRICATION OF THE TESTBED, HOVER STAND MODIFICATIONS, AND A MODULAR TAIL CONE, IF EXERCISED.

FLOOR BASEPLATE QUOTE

FABRICATION OF THE 2.7% SCALE FULL SPAN AND SEMI-SPAN HIGH LIFT COMMON RESEARCH MODEL FOR TESTING IN THE NASA LANGLEY NATIONAL TRANSONIC FACILITY. IT WILL HAVE MODULAR COMPONENTS TO ENABLE THE MODEL TO BE TESTED IN TAKEOFF AND LANDING CONFIGURATIONS.

DESIGN OF A MODEL-SCALE COAXIAL ROTOR AEROELASTIC TESTBED (MSCRAT) WITH THE INCLUSION OF THREE OPTION PERIODS TO ALLOW FOR FABRICATION OF THE TESTBED, HOVER STAND MODIFICATIONS, AND A MODULAR TAIL CONE, IF EXERCISED.

DESIGN OF A MODEL-SCALE COAXIAL ROTOR AEROELASTIC TESTBED (MSCRAT) WITH THE INCLUSION OF THREE OPTION PERIODS TO ALLOW FOR FABRICATION OF THE TESTBED, HOVER STAND MODIFICATIONS, AND A MODULAR TAIL CONE, IF EXERCISED.

FABRICATION OF THE 2.7% SCALE FULL SPAN AND SEMI-SPAN HIGH LIFT COMMON RESEARCH MODEL FOR TESTING IN THE NASA LANGLEY NATIONAL TRANSONIC FACILITY. IT WILL HAVE MODULAR COMPONENTS TO ENABLE THE MODEL TO BE TESTED IN TAKEOFF AND LANDING CONFIGURATIONS.

DESIGN AND FABRICATION WORK FOR SWASHPLATELESS PROTOTYPE ROTOR HUB FOR MODEL-SCALE ROTOR TESTING.

STATIC PIPE ASSEMBLLY

DESIGN, ANALYSIS, AND FABRICATION OF COMPOUND TEST HARDWARE. THIS EFFORT COVERS MULTIPLE ASPECTS WHICH INCLUDE REPAIRING THE LANGLEY ROTOR TEST STAND (LRTS), UPGRADING COMPONENTS OF THE LRTS, AND INTEGRATING EXISTING HARDWARE TO THE LRTS.

FEASIBILITY STUDY - SWASHPLATELESS HUB DESIGN FOR A COAXIAL ROTOR.

WINGED COMPOUND ROTORCRAFT WIND TUNNEL TESTBED. DETAILED DESIGN AND FABRICATION OF AN ADVANCED ROTORCRAFT TESTBED SUITABLE FOR TESTING A VARIETY OF WINGED COMPOUND ROTORCRAFT CONFIGURATIONS IN THE 14 BY 22 FOOT SUBSONIC TUNNEL BY WAY OF A TRAVERSING ASSEMBLY MOUNTED BELOW A NEW FALSE FLOOR MOUNTED ON ONE OF THE FACILITIESMODEL CARTS. IN THIS PROJECT A WINGED COMPOUND HELICOPTER IS DEFINED AS AN AIRCRAFT WITH A CONVENTIONAL ROTOR LIFTING WINGS AND CONVENTIONAL TAIL SURFACES. THE ULTIMATE PURPOSE OF THIS TEST EFFORT IS TO GAIN AN UNDERSTANDING OF THE DIFFERENT CONFIGURATION EFFECTS ON THE PERFORMANCE OF COMPOUND ROTORCRAFT TO DRIVE FUTURE ARMY DESIGNS AND AS SUCH THE DESIGN SHALL INCORPORATE THE ABILITY TO MEASURE THE INTERACTIONAL EFFECTS OF THE ROTOR WAKE ON THE WING LOCATED AT VARIOUS LOCATIONS AS WELL AS DIFFERENT TAIL CONFIGURATIONS AND TAIL PROPULSOR CONFIGURATIONS.

RELIANCE CONSOLIDATED MODELS VI MINIMUM GUARANTEE DELIVERY ORDER.

WIND TUNNEL STATIC PRESSURE MEASURE PIPE

DESIGN, ANALYSIS, AND FABRICATION OF COMPOUND TEST HARDWARE. COVERS MULTIPLE ASPECTS WHICH INCLUDE REPAIRING THE LANGLEY ROTOR TEST STAND, UPGRADING COMPONENTS AND INTEGRATING EXISTING HARDWARE TO THE LANGLEY ROTOR TEST STAND.

FABRICATION OF THE 2.7% SCALE FULL SPAN AND SEMI-SPAN HIGH LIFT COMMON RESEARCH MODEL FOR TESTING IN THE NASA LANGLEY NATIONAL TRANSONIC FACILITY. IT WILL HAVE MODULAR COMPONENTS TO ENABLE THE MODEL TO BE TESTED IN TAKEOFF AND LANDING CONFIGURATIONS.

CONCEPT DESIGN FOR A COMMON TAIL STAND (CTS) FOR PROVIDING POWER FOR THREE (3) DIFFERENT TAIL ROTOR CONCEPTS. THE TEST STAND CONCEPTS WILL BE TESTED IN THE NASA LANGLEY RESEARCH CENTER 14X22 FOOT SUBSONIC TUNNEL.

MODAL DESIGN AND ANALYSIS OF ROTOR TEST STAND. IMPROVE MODEL PREDICTIONS AND REDUCE IN-PLANE HUB RESPONSE. VALIDATE MODAL ANALYSIS PREDICTIONS BY COMPARISON TO EXPERIMENTAL TEST DATA AND PERFORM PARAMETRIC STUDY TO ACHIEVE LOWER HUB RESPONSE OF LRTS

MODAL DESIGN AND ANALYSIS OF THE LANGLEY ROTOR TEST STAND (LRTS). FOLLOW-ON EFFORT TO IMPROVE THE MODEL PREDICTIONS AND REDUCE THE IN-PLANE HUB RESPONSE. VALIDATE MODAL ANALYSIS PREDICTIONS AND PERFORM A PARAMETRIC STUDY.

FABRICATION OF THE 5.2% SCALE SEMISPAN HIGH LIFT COMMON RESEARCH MODEL FOR TESTING IN THE NASA LANGLEY RESEARCH CENTER NATIONAL TRANSONIC FACILITY. THE 5.2% SEMISPAN CRM-HL WILL HAVE MODULAR COMPONENTS THAT WILL ENABLE MODEL TO BE TESTED.

FABRICATION OF THE HYPERSONIC INTERNATIONAL FLIGHT RESEARCH EXPERIMENT 5A (HIFIRE-5A) MODEL MADE OF 15-5 STAINLESS STEEL.

CHASSIS THERMAL ISOLATOR

FABRICATION OF 5.2% SCALE SEMISPAN HIGH LIFT COMMON RESEARCH MODEL AT NASA LANGLEY NATIONAL TRANSONIC FACILITY. 5.2% SEMISPAN CRM-HL WILL HAVE MODULAR COMPONENTS THAT WILL ENABLE THE MODEL TO BE TESTED IN TAKEOFF, LANDING AND CRUISE CONFIGURATIONS

DESIGN AND ANALYSIS OF THE ORNITHOPTER WING AN ORNITHOPTER FLAPPING WING WILL BE USED TO INVESTIGATE FLAPPING WING LIFT, THRUST AND POWER CONSUMPTION IN THE EITHER THE NASA LANGLEY 14X22FT WIND-TUNNEL, LOCATED AT NASA LANGLEY RESEARCH CENTER, HAMPTON, VA OR THE ARMY 7X10FT WIND-TUNNEL, LOCATED AT NASA AMES RESEARCH CENTER, MOFFETT FIELD, CA. THE DEVELOPMENT OF A WIND TUNNEL MODEL OF AN ORNITHOPTER FLAPPING WING WILL BE DIVIDED INTO TWO (2) PHASES. THE FIRST PHASE, PHASE I, WILL CONSIST OF THE DESIGN AND ANALYSIS OF A WIND TUNNEL MODEL OF AN ORNITHOPTER FLAPPING WING. THE SECOND PHASE, PHASE II, WILL CONSIST OF THE FABRICATION AND CALIBRATION OF A WIND TUNNEL MODEL OF AN ORNITHOPTER FLAPPING WING.

PROCURE DESIGN, FABRICATION, AND INSTALLATION SERVICES FOR THE MOTORIZED ROLL COUPLER.

PROCURE DESIGN, FABRICATION, AND INSTALLATION SERVICES FOR THE MOTORIZED ROLL COUPLER.

DESIGN, ANALYSIS, FABRICATION, AND TESTING OF A MACH SCALED ROTOR STAND, THE LANGLEY ROTOR TEST STAND (LRTS).

FULL RV VIBE TEST FIXTURES - ITEMIZED DIMENSIONAL INSPECTION REPORT