ADVANCED TECHNOLOGIES INC

THIS IS WORK IS FOR THE 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 FACILITY'S MODEL 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. TESTING WILL INCLUDE THE MEASUREMENT OF ROTOR AND WING LOADS AND MOMENTS AS WELL AS STATIC AND DYNAMIC PRESSURE DATA AT A NUMBER OF LOCATIONS AROUND THE MODEL. THIS TEST CAMPAIGN WILL COVER TWO ENTRIES IN THE 14X22, TENTATIVELY SCHEDULED FOR SUMMER 2019 AND LATE SUMMER/EARLY FALL 2020, AND WILL BE CLOSELY COUPLED WITH A COMPUTATIONAL VALIDATION EFFORT. WHILE THIS SOW IS SPECIFICALLY FOR THE HARDWARE FOR THE FIRST ENTRY, IT IS ANTICIPATED THAT THE MAJORITY OF THE HARDWARE WILL BE UTILIZED FOR THE SECOND ENTRY AS WELL. APPROXIMATELY 95% OF THE DESIGN WORK AND 20% OF THE FABRICATION WAS COMPLETED UNDER RECOM IV. THIS SOW OUTLINES THE TASKS REQUIRED TO COMPLETE THE DESIGN AND FABRICATION UNDER RECOM V.

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

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 OF THE 10 PERCENT ACTIVE FLOW CONTROL-HIGH LIFT COMMON RESEARCH MODEL HARDWARE. THE NEW 10 PERCENT COMMON RESEARCH MODEL WILL BE TESTED AT NASA LANGLEYS 14X22 FT. WIND TUNNEL.

DESIGN, ANALYSIS, FABRICATION, AND CALIBRATION OF A MACH SCALED ROTOR BLADE SET AND MODEL SCALE FULLY ARTICULATED ROTOR HUB FOR HIGH SPEED FORWARD FLIGHT IN THE NASA 14X22 FOOT SUBSONIC WIND TUNNEL.

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

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 FACILITYS MODEL 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.

IGF::OT::IGF DESIGN, ANALYSIS, AND FABRICATION OF THE HVAB (HOVER VALIDATION AND ACOUSTIC BASELINE) ROTOR BLADES THE CONTRACTOR SHALL DESIGN, ANALYZE AND FABRICATE ROTOR BLADES TO BE USED FOR HOVER AND ACOUSTIC TESTING. AS A BASELINE, A TOTAL OF SIX (6) BLADES WILL BE MADE. THIS TOTAL CONSISTS OF FIVE (5) PRODUCTION BLADES; THE SIXTH BLADE WILL BE USED AS A PROCESS BLADE. THE PROCESS BLADE WILL BE CUT UP TO DETERMINE BLADE MASS PROPERTIES (I.E. MASS DISTRIBUTION, TORSIONAL MASS MOMENT OF INERTIA AND CENTER OF GRAVITY) AND USED AS A ROOT PULL SPECIMEN. ALL FIVE (5) OF THE PRODUCTION BLADES WILL BE INSTRUMENTED WITH BEAM, CHORD AND TORSION STRAIN GAGES. ALL FIVE (5) OF THE PRODUCTION BLADES WILL BE INSTRUMENTED WITH LED LIGHTS AT THE TIP FOR BLADE TIP TRACKING. ALL FIVE (5) OF THE PRODUCTION BLADES WILL BE EQUIPPED WITH PAINT-BASED HEATING ELEMENTS, AS DESCRIBED IN SECTION 3.7. ONE (1) OF THE BLADES SHALL ALSO BE PRESSURE INSTRUMENTED WITH ELEVEN (11) CHORDWISE ROWS OF DYNAMIC PRESSURE TRANSDUCERS WITH EACH ROW CONTAINING SEVENTEEN (17) PRESSURE TRANSDUCERS, FOR A TOTAL OF 187 PRESSURE TRANSDUCERS ON THIS BLADE. ANOTHER ONE (1) OF THE BLADES SHALL BE PRESSURE INSTRUMENTED WITH A TOTAL OF FIFTY-ONE (51) PRESSURE TRANSDUCERS DISTRIBUTED AMONG 14 RADIAL STATIONS. TO MONITOR TEMPERATURE OF THE HEATER COATING, THREE (3) OF THE BLADES WILL BE INSTRUMENTED WITH RTDS.

IGF::OT::IGF : FABRICATION OF THE 8.0 PERCENT JUNCTURE FLOW MODEL THE CONTRACTOR SHALL FABRICATE THE 8.0 PERCENT JUNCTURE FLOW MODEL IN ACCORDANCE WITH ALL SECTIONS OF THIS STATEMENT OF WORK AND SUPPLIED CONTRACT DRAWINGS AND FILES. THE CONTRACTOR SHALL INSTALL A TOTAL OF 629 STATIC PRESSURE TAPS IN THE BASELINE MODEL. THE PRESSURE TAP TUBING SHALL BE 0.040 O.D X 0.020 I.D. STAINLESS STEEL. ALL TUBES SHALL BE FLOW CHECKED AND FREE OF FOD (FOREIGN OBJECT DEBRIS). THE CONTRACTOR SHALL LABEL ALL STATIC PRESSURE TAPS AS PER I.D. NUMBERING SCHEME ON THE DRAWINGS.

"IGF::OT::IGF" TITLE:DESIGN&ANALYSIS OF FACTORS 3 ROTOR BLADE SECTION THIS STATEMENT OF WORK DESCRIBES THE DESIGN AND ANALYSIS OF THE FACTORS3 ROTOR BLADE SECTIONS. THIS IS A PRELIMINARY BLADE SECTION DESIGN TO AID A FUTURE BLADE DESIGN, ANALYSIS AND FABRICATION EFFORT. THE FACTORS3 BLADE WILL BE USED TO INVESTIGATE TRANSONIC DRAG RISE AND AVOID DYNAMIC STALL USING BOUNDARY LAYER SUCTION ON GENERAL ROTOR MODEL SYSTEM (GRMS) IN THE ROTOR TEST CELL (RTC) AND THE 14X22FT WIND-TUNNEL. THIS PRELIMINARY DESIGN EFFORT, PHASE 1, IS TO HELP THE GOVERNMENT UNDERSTAND THE PRACTICAL LIMITS OF A CONTINUOUS DISTRIBUTION SUCTION BLADE GIVEN THE STRUCTURAL DESIGN REQUIREMENTS. THE DELIVERABLES FROM THIS TASK WILL AID IN THE DEVELOPMENT OF A PHASE 2 STATEMENT OF WORK FOR THE DESIGN, ANALYSIS AND FABRICATION OF MODEL SCALE (6.5 FT. RADIUS) ROTOR BLADES.

FABRICATION OF THE TAIL CONE THRUSTER MODEL

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.

"IGF::OT::IGF" TITLE: DESIGN AND FABRICATION OF THE 5.2% SCALE SEMISPAN COMMON RESEARCH MODEL (CRM) NATURAL LAMINAR FLOW (NLF) THIS STATEMENT OF WORK DESCRIBES THE DESIGN, ANALYSIS, AND FABRICATION OF THE 5.2% SCALE SEMISPAN COMMON RESEARCH MODEL (CRM) NATURAL LAMINAR FLOW (NLF) WING AND FUSELAGE/WING FAIRING TO FIT THE EXISTING BOEING 5.2% SCALE SEMISPAN 777 FUSELAGE. THE NEW CRM NLF CONFIGURATION WILL BE TESTED CRYOGENICALLY IN THE NASA LANGLEY RESEARCH CENTER (LARC) NATIONAL TRANSONIC FACILITY (NTF).

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.

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.

ROTOR VACUUM SPIN STAND DESIGN, ANALYSIS AND FABRICATION OF A NEW VACUUM SPIN STAND SUITABLE FOR TESTING ROTOR BLADES INSIDE THE NASA LANGLEY RESEARCH CENTER'S LANGLEY AEROTHERMODYNAMICS LABORATORY (LAL) 60-FT VACUUM SPHERE TEST CHAMBER (60VSTC).

DESIGN, ANALYSIS,&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.

IGF::OT::IGF DESIGN AND FABRICATION OF SCALED, SEMISPAN CRM WING MODEL FOR THE ONERA F1 WIND TUNNEL.

IGF::OT::IGF 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.

IGF::OT::IGF OTHER FUNCTIONS - RELIANCE CONSOLIDATED MODELS (RECOM) DESIGN, ANALYSIS, AND FABRICATION OF THE SPACE LAUNCH SYSTEMS RIGID BUFFET MODEL AND STING FOR THE TESTING IN THE TRANSONIC DYNAMIC TUNNEL AT NASA LANGLEY RESEARCH CENTER.

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

DESIGN, ANALYSIS,&FABRICATION OF C4 BLADE SET THIS IS FOR THE DESIGN, ANALYSIS, FABRICATION AND CALIBRATION OF A PASSIVE SET OF THE FACTORS3 (F3) ROTOR BLADES FOR HIGH SPEED FORWARD FLIGHT IN THE 14X22 FOOT SUBSONIC WIND TUNNEL. THE NEW BLADE SET WILL BE TERMED C4 TO DISTINGUISH IT FROM THE F3 BLADE SET. THE DESIGNATION FOR THIS MODEL HARDWARE IS YA-19-0008. THE CONTRACTOR SHALL DESIGN, ANALYZE AND FABRICATE A PASSIVE VERSION OF THE FACTORS3 ROTOR BLADES TO BE USED FOR HIGH SPEED FORWARD FLIGHT EXPERIMENTS. A TOTAL OF FIVE (5) PRODUCTION BLADES SHALL BE FABRICATED; A PROCESS BLADE IS NOT REQUIRED BY NASA UNLESS THE MASS TOTAL MASS PROPERTIES OF THE PRODUCTION BLADES DO NOT MATCH PREDICTIONS. THE PRODUCTION BLADES SHALL BE INSTRUMENTED WITH BEAM, CHORD AND TORSION STRAIN GAUGES AT FOUR RADIAL STATIONS PER BLADE. THE PRODUCTION BLADES SHALL BE INSTRUMENTED WITH LED LIGHTS AT THE TIP FOR BLADE TIP TRACKING. THE INTENT IS TO REUSE THE FACTORS3 BLADE TOOLING AND REMAKE THE BLADES WITHOUT THE INTERNAL AIR PASSAGES AND TITANIUM UPPER SURFACE SKIN. THE DRAWINGS OF THE BLADE TOOLING ARE INCLUDED IN THE CONTRACTOR SHALL DESIGN, ANALYZE AND FABRICATE A PASSIVE VERSION OF THE FACTORS3 ROTOR BLADES TO BE USED FOR HIGH SPEED FORWARD FLIGHT EXPERIMENTS. A TOTAL OF FIVE (5) PRODUCTION BLADES SHALL BE FABRICATED; A PROCESS BLADE IS NOT REQUIRED BY NASA UNLESS THE MASS TOTAL MASS PROPERTIES OF THE PRODUCTION BLADES DO NOT MATCH PREDICTIONS. THE PRODUCTION BLADES SHALL BE INSTRUMENTED WITH BEAM, CHORD AND TORSION STRAIN GAUGES AT FOUR RADIAL STATIONS PER BLADE. THE PRODUCTION BLADES SHALL BE INSTRUMENTED WITH LED LIGHTS AT THE TIP FOR BLADE TIP TRACKING. THE INTENT IS TO REUSE THE FACTORS3 BLADE TOOLING AND REMAKE THE BLADES WITHOUT THE INTERNAL AIR PASSAGES AND TITANIUM UPPER SURFACE SKIN. THE DRAWINGS OF THE BLADE TOOLING ARE INCLUDED IN APPENDIX A: FACTORS3 BLADE DRAWINGS, 1273486 AND 1273487. THE CONTRACTOR SHALL HOLD BOTH A PRELIMINARY DESIGN REVIEW (PDR) AND CRITICAL DESIGN REVIEW (CDR) TO REVIEW. FABRICATION SHALL NOT BEGIN WITHOUT WRITTEN APPROVAL FROM NASA. FINAL ACCEPTANCE OF THE FABRICATED BLADES AND DOCUMENTATION WILL OCCUR DURING AN ACCEPTANCE REVIEW BY THE COR AT THE CONCLUSION OF THE PROJECT, 1273486 AND 1273487. THE CONTRACTOR SHALL HOLD BOTH A PRELIMINARY DESIGN REVIEW (PDR) AND CRITICAL DESIGN REVIEW (CDR) TO REVIEW. FABRICATION SHALL NOT BEGIN WITHOUT WRITTEN APPROVAL FROM NASA. FINAL ACCEPTANCE OF THE FABRICATED BLADES AND DOCUMENTATION WILL OCCUR DURING AN ACCEPTANCE REVIEW BY THE COR AT THE CONCLUSION OF THE PROJECT.

IGF::OT::IGF DESIGN AND ANALYSIS OF THE GENERIC ATTACK HELICOPTER SHELL AND STRUT THE CONTRACTOR SHALL PROVIDE THE DESIGN, ANALYSIS, AND FABRICATION SERVICES AS OUTLINED IN THIS DOCUMENT. THE DESIGNATION FOR THIS MODEL HARDWARE IS YA-16-0014. THE FINAL OBJECTIVE OF THIS PROJECT IS THE DELIVERY OF A COMPLETE CRATED WIND TUNNEL MODEL AND SUPPORT SYSTEM HARDWARE, DRAWINGS, CAD FILES, BOLT TORQUES, ASSEMBLY INSTRUCTIONS, AND AN APPROVED MODEL SYSTEMS REPORT (MSR) TO THE REQUIRED SPECIFICATIONS OF LARCS WIND TUNNEL MODEL SYSTEMS CRITERIA (LPR 1710.15J, 26 MAY 2015). THE US GOVERNMENT BUY OFF OF THE CRITICAL DESIGN REVIEW (CDR) AND THE NASA-SIGNED MSR NOT TO EXCEED 55 DAYS FROM AWARD. DETAILED COST BREAKDOWNS OF THE INDIVIDUAL COMPONENTS (NAMELY THE GAH AND C7TP ASA) SHALL BE INCLUDED.

IGF::OT::IGF DESIGN, ANALYSIS,&FABRICATION OF CUSTOM ROTARY UNION THIS STATEMENT OF WORK DESCRIBES THE DESIGN, ANALYSIS AND FABRICATION OF A CUSTOM ROTARY UNION. A ROTARY UNION ALSO REFERRED TO AS A PNEUMATIC SLIP RING IS USED TO TRANSFER FLUID FROM THE ROTATING FRAME TO THE FIXED FRAME. THIS EFFORT WILL COMPRISE OF TWO PHASES, THE FIRST PHASE WILL CONSIST OF THE DESIGN AND ANALYSIS OF THE CUSTOM ROTARY UNION. THE DELIVERABLES FROM THE FIRST PHASE TASK WILL AID IN THE DEVELOPMENT OF A PHASE 2 STATEMENT OF WORK FOR FABRICATION OF THE CUSTOM ROTARY UNION.

IGF::OT::IGF FABRICATION OF MODIFICATIONS OF LEGACY DIAMOND WING TUNNEL MODEL

IGF::OT::IGF DESIGN OF A COAXIAL-ROTOR WIND-TUNNEL TESTBED

RELIANCE CONSOLIDATED MODELS (RECOM) DESIGN AND/OR FABRICATION OF AEROSPACE MODEL SYSTEMS AND DEVELOPMENTAL TEST HARDWARE

RELIANCE CONSOLIDATED MODELS (RECOM) DESIGN, ANALYSIS, AND FABRICATION OF THE HYPERSONIC INFLATABLE AERODYNAMIC DECELERATOR(HIAD) CENTER BODY II TEST ARTICLE HARDWARE

IGF::OT::IGF DESIGN AND FABRICATION OF THE CURVED DUCT TEST RIG THIS STATEMENT OF WORK DESCRIBES THE DESIGN, ANALYSIS, AND FABRICATION OF A NEW LINER TEST SECTION FOR CURVED DUCT TEST RIG (CDTR). THE INTENT IS TO ADD THE CAPABILITY OF TESTING SOFT STATOR VANES AND MODULARIZE THE TEST SECTION FOR IMPROVED PRODUCTIVITY AND REPEATABILITY. THE CDTR HAS TESTED LINED DUCTS SIMULATING AIRCRAFT FAN NACELLES FOR YEARS. IN THIS DESIGN EFFORT THE EXISTING TEST SECTION WILL EVALUATED AS WELL FOR UPGRADING. THE DESIRE IS TO PROVIDE A NEW TEST SECTION THAT ENHANCES THE TESTING THROUGHPUT OF THE CDTR BY ADDING AN INTEGRATED SOFT VANE TEST CAPABILITY.

INNER SHROUD LINER SEGMENTS

200608!600157!2100!W911W6!AVIATION APPLIED TECHNOLOGY !W911W606C0010 !A!N! !N! ! !20060227!20070228!196406730!196406730!196406730!N!ADVANCED TECHNOLOGIES INC !875 MIDDLE GROUND BLVD !NEWPORT NEWS !VA!23606!56000!700!51!NEWPORT NEWS !NEWPORT NEWS (CITY) !VIRGINIA !+000000369210!N!N!000000604337!AC12!RDTE/AIRCRAFT-APPLIED RESEARCH !A1C!OTHER AIRCRAFT EQUIPMENT !000 !NOT DISCERNABLE !541710!A!A!3! ! ! ! ! !99990909!B! ! !A! !D!U!U!1!001!N!1A!Z!Y!Z! ! !N!B!N!N! ! !A! !A!A!000!A!B!N! ! ! ! ! ! !0001! !

FABRICATION OF THE ACOUSTIC BLADE SET FOR THE HOVER VALIDATION AND ACOUSTIC THE FABRICATION OF THE ACOUSTIC SET OF BLADES DESIGNED AS PART OF THE HOVER VALIDATION AND ACOUSTIC BASELINE (HVAB) ROTOR BLADES.

"IGF::OT::IGF" TITLE: DESIGN, ANALYSIS, AND FABRICATION OF CONVENTIONAL AND KRUEGER SLAT MODELS -MODEL#1: MAIN ELEMENT AIRFOIL#1 WITH CONVENTIONAL SLAT. THE FIRST MAIN-ELEMENT WITH SLAT MODEL SHALL FOLLOW THE PROVIDED PROFILE GEOMETRY OF THE 30P30N CONFIGURATION. THE EQUIVALENT STOWED CHORD OF MODEL#1 SHALL BE 16.751 . THE MAIN ELEMENT (2-DIMENSIONAL) SHALL HAVE A SPAN OF 36 . THE MAIN ELEMENT SHALL BE SECURED TO THE QUIET FLOW FACILITY TEST SECTION SIDE WALLS USING AN EXISTING BRACE AND ADAPTOR DEVICE (SEE DRAWING # 1079347 1-E-1 AND # 1079357 1-D-1). THIS BRACE AND ADAPTOR DEVICE IS ALSO USED TO SET THE MAIN ELEMENT ANGLE OF ATTACK. THE CONVENTIONAL SLAT MODEL (2-DIMENSIONAL) SHALL HAVE A 36 SPAN. THE POSITION OF THE CONVENTIONAL SLAT WITH RESPECT TO THE MAIN ELEMENT AIRFOIL SHALL BE ADJUSTABLE. IF COST EFFICIENT THE POSITION OF THE SLAT MAY BE SET WITH AN EXISTING PAIR OF SLAT BRACKETS (SEE DRAWING# 1075230). A CHARACTERISTIC SLAT DESIGN (NOT THE CORRECT OML, BUT OVERALL CORRECT SIZE) THAT WAS PREVIOUSLY USED WITH THE LATTER SLAT BRACKETS IS SHOWN IN DRAWING# 1075229. THE FINAL OML OF THE DESIRED CONVENTIONAL SLAT IS TO BE DETERMINED, BUT WILL BE SIMILAR TO THE PROVIDED GEOMETRY; THUS MODIFICATIONS ARE BEING CONSIDERED WHICH WILL THICKEN AND SMOOTH THE INNER COVE REGION OF THE SLAT COMPARED TO THAT PROVIDED. AT A MINIMUM THE THIN EDGES OF THE PROVIDED GEOMETRY WILL BE THICKENED TO ENSURE STRUCTURAL INTEGRITY. THE SLAT DESIGN SHALL BE EVALUATED FOR STRUCTURAL INTEGRITY AND INSTRUMENTATION INSTALLATION. AS NECESSARY, THE SLAT OML SHALL BE THICKENED ON THE COVE PORTION OF THE SLAT TO ACCOMMODATE THE INSTALLATION OF PRESSURE TAPS AND UNSTEADY SURFACE PRESSURE SENSORS, AS WELL AS ACHIEVE REASONABLE THICKNESS FOR MACHINING PURPOSES. THE SLAT SHALL BE INSTRUMENTED WITH 5 UNSTEADY SURFACE PRESSURE SENSORS DISTRIBUTED IN THE MID-SPAN REGION OF THE SLAT AND 20 PRESSURE TAPS DISTRIBUTED IN A CHORDWISE ROW NEAR THE SLAT MID-SPAN. THE MAIN ELEMENT OF AIRFOIL#1 SHALL BE INSTRUMENTED WITH 5 UNSTEADY SURFACE PRESSURE SENSORS DISTRIBUTED IN THE MID-SPAN/ LEADING EDGE REGION OF THE AIRFOIL. THE MAIN ELEMENT OF AIRFOIL #1 SHALL HAVE 40 PRESSURE TAPS DISTRIBUTED IN A CHORDWISE ROW NEAR THE AIRFOIL MID-SPAN, AND EIGHT ADDITIONAL PRESSURE TAPS LOCATED AT -SPAN AND -SPAN ON THE SUCTION AND PRESSURE SIDES OF THE MAIN ELEMENT. THE MAIN ELEMENT OF AIRFOIL #1 SHALL HAVE A TOTAL OF 48 STEADY PRESSURE TAPS. THE UNSTEADY SURFACE PRESSURE SENSORS SHALL BE KULITE SENSORS THAT WILL BE GOVERNMENT FURNISHED. THE MAIN ELEMENT MODEL AND SLAT MODEL SHALL INCLUDE A MOUNTING SCHEME FOR SIMPLIFIED SLAT BRACKETS AT THE MODEL CENTER SPAN, CONNECTING THE MAIN ELEMENT AND SLAT. THE BRACKET(S) SHALL BE NON-STRUCTURAL, INCLUDED AS NOISE GENERATION MECHANISMS. THE BRACKET DESIGNS ARE NOT COMPLETE. THE BRACKETS ARE PART OF THE STATEMENT OF WORK, ALTHOUGH DO NOT REQUIRE HOLDING TO THE DELIVERY DATE OF THE REST OF THE MODEL HARDWARE. THE MOUNTING SCHEME SHALL ALLOW FOR A FLUSH SURFACE FINISH WHEN NO BRACKET IS USED. THE SURFACE FINISH FOR THE NEW HARDWARE SHALL BE AT LEAST 32 -INCHES AND HAVE A SURFACE CONTOUR TOLERANCE OF 0.003. THE TRAILING EDGES OF THE SLAT AND MAIN ELEMENT MODEL SHALL HAVE A THICKNESS OF 20 THOUSANDTHS OF AN INCH WITH A TOLERANCE OF 0.003. MODEL#2: MAIN ELEMENT AIRFOIL#2 WITH KRUEGER SLAT THE SECOND MAIN ELEMENT WITH SLAT MODEL SHALL FOLLOW A PROFILE GEOMETRY TO BE DETERMINED, WITH A KRUEGER SLAT INSTEAD OF A CONVENTIONAL SLAT. OVERALL DIMENSIONS MATCH THOSE OF MODEL#1, ALTHOUGH THE DETAILS OF THE SLAT GEOMETRY AND LEADING PORTION OF THE MAIN ELEMENT SHALL DIFFER. THIS MEANS THE EQUIVALENT STOWED CHORD OF MODEL#2 SHALL ALSO BE 16.751 . THE MAIN ELEMENT (2-DIMENSIONAL) SHALL HAVE A SPAN OF 36 . IT SHALL HAVE A KRUEGER CAVITY MACHINED OUT OF THE MAIN ELEMENT. THE MAIN ELEMENT SHALL BE SECURED TO THE QUIET FLOW FACILITY TEST SECTION SIDE WALLS USING AN EXISTING BRACE AND ADAPTOR DEVICE (SEE DR

"IGF::OT::IGF" RELIANCE CONSOLIDATED MODELS (RECOM) DESIGN AND/OR FABRICATION SUPPORT. THIS SUPPORT IS A CONSOLIDATION OF DESIGN AND FABRICATION EFFORTS FOR AEROSPACE MODEL SYSTEMS AND DEVELOPMENTAL TEST HARDWARE USED FOR SPACEFLIGHT, SPACE EXPLORATION, FLIGHT AND GROUND-BASED TESTS SUPPORTING AMES RESEARCH CENTER, GLENN RESEARCH CENTER, LANGLEY RESEARCH CENTER, AND MARSHALL SPACE FLIGHT CENTER. THESE PRECISION EXPERIMENTAL RESEARCH MODELS AND HARDWARE MAY CONSIST OF BOTH MECHANICAL AND ELECTRICAL/ELECTRONIC HARDWARE ELEMENTS. THE MECHANICAL HARDWARE ELEMENTS INCLUDE, BUT ARE NOT LIMITED TO, WIND TUNNEL MODELS (INCLUDING, BUT NOT LIMITED TO, FORCE/PRESSURE, PROPULSION SIMULATION, DYNAMICALLY SCALED, AND FREE FLIGHT), ROTORCRAFT MODELS, DROP MODELS, MODEL COMPONENTS, MODEL SUPPORT SYSTEMS, TEST EQUIPMENT, TURBOMACHINERY MODELS (INCLUDING, BUT NOT LIMITED TO, AIR TURBINE MODELS, WATER FLOW PUMP MODELS) AIRCRAFT FLIGHT TEST HARDWARE, SPACE FLIGHT HARDWARE, LARGE WELDED/FORMED STRUCTURAL COMPONENTS USED IN THE DEVELOPMENT AND VALIDATION OF SPACE FLIGHT SYSTEMS, FORCE MEASUREMENT EQUIPMENT (INCLUDING MULTI-COMPONENT WIND TUNNEL BALANCES), AND STRUCTURAL TEST ARTICLES AND INSTRUMENTATION/DEVICES TO MEASURE FORCE, MOMENT, ACCELERATION, ATTITUDE, PRESSURE STRAIN AND TEMPERATURE. THESE RESEARCH MODELS AND HARDWARE MAY BE UTILIZED FOR VARIOUS FACILITIES SUCH AS NASA WIND TUNNELS, AIR/WATER FLOW TURBINE/PUMP FACILITIES, AIRCRAFT, SPACECRAFT, AND OTHER EXISTING AND FUTURE LABORATORY ENVIRONMENTS.

IGF::OT::IGF THE CONTRACTOR SHALL COMPLETE DETAILED DESIGN, STRESS/DEFLECTION ANALYSIS, FABRICATION, AND QUALITY INSPECTION (AS SPECIFIED) OF A 60-INCH SPAN, SWEPT WING MODEL BASED ON THE CRM. THIS MODEL IS APPROXIMATELY 5.8% OF THE SCALE OF THE FULL-SCALE CRM AND HAS HAD THE DIHEDRAL REMOVED FROM THE WING S DESIGN. THE WING RETAINS THE TWIST AND TAPER OF THE CRM. A DIAGRAM OF THE CRM PLANFORM IS SHOWN IN FIG. 1. THE ROOT CHORD IS APPROXIMATELY 27.1 INCHES WITH AN ANGLE OF ATTACK OF 4.4 DEGREES AND THE TIP CHORD IS APPROXIMATELY 6.2 INCHES WITH AN ANGLE OF ATTACK OF -3.8 DEGREES. THE CRM HAS A QUARTER-CHORD SWEEP ANGLE OF 35 AND A LEADING EDGE SWEEP ANGLE OF 37.2 . THE MODEL SHALL BE FABRICATED AS A MAIN ELEMENT WITH A FULL-SPAN REMOVABLE LEADING EDGE. AN ALTERNATE FULL-SPAN LEADING EDGE SHALL ALSO BE FABRICATED. THE ALTERNATE LEADING EDGE WILL SERVE AS A BLANK FOR MOUNTING ICE SHAPES THAT WILL BE FABRICATED BY OTHER CONTRACTORS. A NON-METRIC SPLITTER PLATE HAVING TWO CONFIGURATIONS SHALL ALSO BE DESIGNED AND FABRICATED BASED ON THE GUIDELINES PROVIDED. TWO DIFFERENT SHROUDS FOR USE WITH EITHER SPLITTER PLATE CONFIGURATION SHALL ALSO BE DESIGNED AND FABRICATED. THE MODEL SHALL BE COMPATIBLE WITH THE FLOOR MOUNTED, FORCE BALANCE SYSTEM WITH AND WITHOUT A SPLITTER PLATE INSTALLED.

IGF::OT::IGF DESIGN, ANALYSIS, AND FABRICATION OF UNMANNED AERIAL SYSTEMS UPGRADES FOR THE LOW SPEED AEROACOUSTIC WIND TUNNEL THIS STATEMENT OF WORK DESCRIBES THE DESIGN, ANALYSIS, AND FABRICATION OF UNMANNED AERIAL SYSTEMS UPGRADES TO THE LOW SPEED AEROACOUSTIC WIND TUNNEL. THE INTENT IS TO TEST SMALL UNMANNED AERIAL SYSTEMS OR COMPONENTS FOR AERO PERFORMANCE AND ACOUSTICS. THE HARDWARE IS TO BE TESTED IN THE LOW SPEED AEROACOUSTIC WIND TUNNEL AT LARC.

DESIGN AND FABRICATION FOR REPAIR OF THE LEADING EDGES OF THE HOVER VALIDATION AND ACOUSTIC BASELINE (HVAB) BLADE SET.

DESIGN, ANALYSIS, AND FABRICATION OF NEW HARDWARE FOR ARMY ROTOR TEST STAND. THIS WORK DESCRIBES THE DESIGN, ANALYSIS, AND FABRICATION OF NEW HARDWARE AND MODIFYING EXISTING HARDWARE OF THE ARMY ROTOR TEST STAND. THE NEW AND MODIFIED HARDWARE WILL ENABLE THE ARTS TO BE USED WITH AN EXISTING LANGLEY FOUR BLADED ROTOR HUB, THE GRMS HEAVY HUB, AND TO BE INSTALLED ON ONE OF THE LANGLEY 14X22 MODEL CARTS. THE TEST STAND WILL BE TESTED IN THE LANGLEY ROTOR TEST CELL AND THE 14X22 FOOT SUBSONIC WIND TUNNEL.

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.

IGF::OT::IGF DESIGN OF A COAXIAL-ROTOR WIND-TUNNEL TESTBED THE CONTRACTOR SHALL COMPLETE THE DESIGN, ANALYSIS, AND FABRICATION OF A MULTI-PROPELLER MODEL SYSTEM TO BE INCORPORATED WITH THE EXISTING MOBILE MODEL TEST STAND (MTS) FOR THE LOW SPEED AEROACOUSTIC WIND TUNNEL (LSAWT). A RENDERING OF THE MULTI-PROPELLER SYSTEM

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

MANUFACTURE AND ASSEMBLY OF LOW-EARTH ORBIT FLIGHT TEST OF AN INFLATABLE DECELERATOR (LOFTID)FLIGHT INNER SHROUD

RELIANCE CONSOLIDATED MODELS (RECOM)-- DESIGN AND FABRICATION OF THE CHECK STANDARD NOZZLE HARDWARE

"IGF::OT::IGF" TITLE: FABRICATION OF THE SUPERSONIC TURBULENT DRAG REDUCTION MODEL 1.1 SCOPE THE CONTRACTOR SHALL PROVIDE MANUFACTURING REVIEW, FABRICATION AND MATERIALS FOR THE SUPERSONIC TURBULENT DRAG REDUCTION MODEL AS OUTLINED BELOW. THE DESIGNATION FOR THIS MODEL HARDWARE IS D303-15-0008. GENERAL DESCRIPTION THE CONTRACTOR SHALL COMPLETE THE FABRICATION OF THE SUPERSONIC TURBULENT DRAG REDUCTION MODEL PER THE PROVIDED DRAWINGS AND ELECTRONIC FILES. MODEL FABRICATION REQUIREMENTS (AS PER DRAWINGS WHEN APPLICABLE, OTHERWISE AS DEFINED) FABRICATION THE CONTRACTOR SHALL FABRICATE THE SUPERSONIC TURBULENT DRAG REDUCTION MODEL IN ACCORDANCE WITH ALL SECTIONS OF THIS STATEMENT OF WORK AND SUPPLIED CONTRACT DRAWINGS AND FILES. THE CONTRACTOR SHALL PROVIDE FINAL INSTALLATION OF THE AIR BEARINGS (GOVERNMENT FURNISHED). THE CONTRACTOR SHALL PROVIDE PROVISIONS FOR ALL INSTRUMENTATION. THE GOVERNMENT WILL PROCURE AND INSTALL ALL INSTRUMENTATION. MATERIALS THE CONTRACTOR SHALL PROVIDE THE MATERIALS TO FABRICATE THE SUPERSONIC TURBULENT DRAG REDUCTION MODEL IN ACCORDANCE WITH ALL SECTIONS OF THIS STATEMENT OF WORK AND SUPPLIED CONTRACT DRAWINGS AND FILES.

IGF::OT::IGFDELIVERY ORDER ENTITLED DESIGN OF AN ADVANCED ROTORCRAFT TESTBED. STATEMENT OF WORK DESCRIBES THE REQUIREMENTS FOR THE DESIGN OF AN ADVANCED ROTORCRAFT TESTBED SUITABLE FOR TESTING A VARIETY OF COMPOUND ROTORCRAFT CONFIGURATIONS IN THE 14 BY 22 FOOT SUBSONIC TUNNEL. IN THIS PROJECT, A COMPOUND HELICOPTER IS DEFINED AS AN AIRCRAFT WITH EITHER A CONVENTIONAL ROTOR AND AUXILIARY LIFT AND/OR PROPULSION SYSTEMS, OR A POWERED LIFT WING WITH OR WITHOUT A CONVENTIONAL ROTOR. 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 EFFECTS OF THE FUSELAGE, ROTOR, WING, TAIL, AND ANY AUXILIARY LIFTING AND PROPULSIVE DEVICE INDEPENDENTLY.

VALVE

"IGF::OT::IGF" FABRICATION OF THE 65 DEGREE SWEPT WING MODEL 1.1 SCOPE THE CONTRACTOR SHALL PROVIDE MANUFACTURING REVIEW, FABRICATION AND MATERIALS FOR THE 65 DEGREE SWEPT WING MODEL AS OUTLINED BELOW. THE DESIGNATION FOR THIS MODEL HARDWARE IS D303-15-0003.1.2 GENERAL DESCRIPTION THE CONTRACTOR SHALL COMPLETE THE FABRICATION OF THE 65 DEGREE SWEPT WING MODEL PER THE PROVIDED DRAWINGS AND ELECTRONIC FILES. 2.0 MODEL FABRICATION REQUIREMENTS (AS PER DRAWINGS WHEN APPLICABLE, OTHERWISE AS DEFINED) 3.1 FABRICATION THE CONTRACTOR SHALL FABRICATE THE 65 DEGREE SWEPT WING MODEL IN ACCORDANCE WITH ALL SECTIONS OF THIS STATEMENT OF WORK AND SUPPLIED CONTRACT DRAWINGS AND FILES. THE CONTRACTOR SHALL ASSURE ALL HARDWARE BE RETURNED CLEAN, FREE FROM GREASE AND OIL, NO CHIPS OR FOREIGN OBJECT DEBRIS (FOD). THE COUNTER BORED AND TAPPED HOLES SHALL BE CLEAN AND TAPPED HOLES TAPPED TO PROPER DEPTH. THE CONTRACTOR SHOULD NOTE THE SURFACE FINISH ON LEADING EDGE PARTS, AS THEY EACH HAVE DIFFERENT FINISH REQUIREMENTS. THE CONTRACTOR SHALL PROVIDE PROVISIONS FOR ALL INSTRUMENTATION. INSTRUMENTATION WILL BE GOVERNMENT FURNISHED AND GOVERNMENT INSTALLED. 3.2 MATERIALS THE CONTRACTOR SHALL PROVIDE THE MATERIALS TO FABRICATE THE 65 DEGREE SWEPT WING MODEL IN ACCORDANCE WITH ALL SECTIONS OF THIS STATEMENT OF WORK AND SUPPLIED CONTRACT DRAWINGS AND FILES. 3.3 IDENTIFICATION APPLICABLE DRAWING NUMBERS SHALL BE PERMANENTLY MARKED ON EACH PART IN AN AREA THAT IS NOT IN AN INTERNAL OR EXTERNAL FLOW OR ON A SEALING SURFACE. 3.4 STRUCTURAL WELDING THE CONTRACTOR SHALL PERFORM ANY STRUCTURAL WELDING THAT IS A RESULT OF A DESIGN REQUIREMENT IN ACCORDANCE WITH LPR 1710.15, SECTION 2.5, OR THE WELDING CODE OR SPECIFICATION DESIGNATED BY THE LARC TECHNICAL PROJECT ENGINEER (TPE)/ RESEARCH PROJECT ENGINEER (RPE). ALL WELDING SHALL BE QUALIFIED TO THE APPLICABLE CODE. PRE-QUALIFIED PROCEDURES ARE NOT ACCEPTED AT LARC. THE NASA LARC QUALITY ASSURANCE CERTIFIED WELDING INSPECTOR SHALL REVIEW THE CONTRACTOR S DRAWINGS AND SUBMITTALS. THE CONTRACTOR SHALL PROVIDE DOCUMENTATION TO SHOW THAT ALL WELDING EFFORTS ARE DONE IN ACCORDANCE WITH THE APPLICABLE SECTIONS OF THESE SPECIFICATIONS. THE CONTRACTOR SHALL SUBMIT ONE (1) COPY OF THE WELDING PROCEDURE AND QUALIFICATION DOCUMENTS, TO INCLUDE THE PROCEDURE QUALIFICATION RECORD (PQR), WELDING PROCEDURE SPECIFICATION (WPS), WELDER QUALIFICATION RECORD (WQR) AS REQUIRED BY ASME BOILER&PRESSURE VESSEL CODE, SECTION IX, FOR REVIEW TEN (10) WORKING DAYS PRIOR TO START OF ANY WELDING.

MODEL 1 INCLUDES THE FOLLOWING

AIRFOIL MODEL

GROUND SUPPORT EQUIP RV STAND-IN ASSEMBLY