AEROJET ROCKETDYNE

TECHNICAL EFFORT - ANALYSIS AND DESIGN ENGINE ASSEMBLY (ADEA) - HYDROCARBON BOOST TO PROVIDE HIGH OPERABILITY AND FLIGHT RELIABILITY AS RELATED TO REUSABLE LIQUID ROCKET ENGINE (LRE)

RESEARCH AND DEVELOPMENT (R&D) - STAGE 2 LARGE CLASS TECH DEMO

MOTOR,ROCKET PART NUMBER: 10242870

DACS SYSTEM DEFINITION & DESIGN (BASIC)

SOLID DACS SYSTEM DEFINITION & DESIGN

LOX METHANE ASCENT MAIN ENGINE TECHNOLOGY DEVELOPMENT

PHASE I - EXERCISED

LIQUID OXYGEN/HYDROGEN DEEP-THROTTLING INJECTOR TECHNOLOGY DEVELOPMENT.

AWARD CONTRACT TO AEROJET TO ENTER INTO THE INTEGRATION AND DEMONSTRATION OF THE AWP AS A RESULT OF RFP W31P4Q-09-R-0002

IGF::OT::IGF THE OVERALL OBJECTIVE OF THE PROPOSED TURBINE-BASED COMBINED-CYCLE (TBCC) LOW MACH RISK REDUCTION DIRECT CONNECT COMBUSTOR (DCC) TESTING IS TO ADVANCE KEY ENABLING TECHNOLOGY FOR TBCC HYPERSONIC PROPULSION SYSTEMS BY EXTENDING LOW MACH AND ALTITUDE OPERATION OF AR S 3RD GENERATION POWERHEAD FOR THE DUAL-MODE SCRAMJET PROPULSION SYSTEM WHILE MAINTAINING MAXIMUM FLIGHT MACH CAPABILITY. THE SPECIFIC OBJECTIVES ARE TO EXPLORE AND CHARACTERIZE IGNITION, OPERABILITY AND PERFORMANCE AT SIMULATED CONDITIONS REPRESENTING COMBINED CYCLE AND RAMJET MODES OF OPERATION OVER THE MODE TRANSITION CORRIDOR. AR WILL CONDUCT A HYDROCARBON FUELED DIRECT CONNECT TEST THAT PROVIDES A FLEXIBLE, LOW COST APPROACH WHICH WILL REDUCE RISK FOR TBCC HYPERSONIC PROPULSION SYSTEMS. THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: (1) TASK PLANNING AND STATUS, (2) INTEGRATED AND COORDINATED PRE-TEST ANALYSES, (3) HARDWARE REFURBISHMENT AND FABRICATION, (4) GROUND TESTS IN A JET BURNER TEST STAND, AND (5) POST-TEST DATA ANALYSIS AND REPORTING TO MEET PROGRAM OBJECTIVES.

ENG & LAB TEST SUPPORT FOR RSLP MMII, STAGE 2 MOTOR

TO 0015, CLINS 8,9,10,11,14,15

ENG & LAB TEST SUPPORT FOR RSLP MMII, STAGE 2 MOTOR

THE SCOPE OF WORK IS TO DEVELOP THE SET OF DOCUMENTS AND INFORMATION NECESSARY TO AWARD CONTRACTS FOR THE DEVELOPMENT OF MODULAR BEAM STATIONS AND RECEIVE ELEMENTS. THE OBJECTIVE(S) OF THIS WORK IS: 1. CONDUCT PARAMETRIC ANALYSES THAT ILLUMINATE THE VALUE OF BEAMED ENERGY MISSION CONCEPTS FOR LAUNCH, POWER PROVISION TO LEO SPACECRAFT ON ORBIT, AND SEP APPLICATIONS BETWEEN LEO AND GEO. 2. CREATE REFERENCE DESIGNS AND EVALUATE THE TRADE SPACE FOR POWER BEAMING MODULES, HEAT EXCHANGERS, AND PHOTOVOLTAIC RECEIVE ELEMENTS (SOLAR, MONOCHROMATIC, AND THERMAL).

TASK ORDER 0011

AWARD CLINS 0008, 0009, 0014 AND 0015

CLINS 4, 5, 6, 7,&12

IGF::OT::IGF ~~ PREFERRED POWER ARCHITECTURE DEMONSTRATION FOR SOLAR ELECTRIC PROPULSION MODULE - DEVELOP AND DEMONSTRATE A POWER SYSTEM ARCHITECTURE FOR AN IN-SPACE TRANSPORTATION SEP-CENTRIC SPACECRAFT THAT MAXIMIZES THE ELECTRICAL AND THERMAL EFFICIENCIES OF THE POWERTRAIN BETWEEN THE SOLAR ARRAYS AND ELECTRIC PROPULSION THRUSTER TO REDUCE MASS, VOLUME AND COST TO THE SPACECRAFT WHILE ALSO TAKING INTO ACCOUNT THE REQUIREMENTS FOR THE OTHER SPACECRAFT SYSTEMS AND SUBSYSTEMS.

REFER TO BASE

ACTUAL INSPECTION IAW START TREATY

AWARD CLINS 0007, 0010, 0011, 0012, 0013

TO 0001

THE CONTRACTOR SHALL DEVELOP AN INJECTION HOLD GEOMETRY THAT IS COMPATIBLE WITHIN THE PHYSICAL CONSTRAINTS OF THE EXISTING 61 ELEMENT THRUSTER HARDWARE. THE CONTRACTOR SHALL PERFORM ALL STRUCTURAL AND FLOW ANALYSIS NEEDED TO VALIDATE THE FUNCTION AND PERFORMANCE OF THE REPLACEMENT FACEPLATE DESIGN. THE CONTRACTOR SHALL FABRICATE, TEST AND DELIVER THREE INJECTOR FACEPLATES WITHIN THE TIME CONSTRAINTS OF THE CONTRACT. THE REPLACEMENT INJECTOR FACEPLATES MUST BE COMPATIBLE WITH EXISTING NASA HARDWARE. THE CONTRACTOR IS RESPONSIBLE FOR ALL DESIGN, FABRICATION, TESTING AND DELIVERY OF THE REPLACEMENT INJECTOR FACEPLATES. NASA WILL PROVIDE ALL TECHNICAL INFORMATION ABOUT EXISTING HARDWARE AND PROPELLANT FLOW CONDITIONS THAT ARE ANTICIPATED FOR OPERATIONAL USE. AN EXISTING INJECTOR ASSEMBLY AND THRUSTER CHAMBER WILL BE USED WITH THE REPLACEMENT INJECTOR FACEPLATES. IN ORDER TO DROP INTO THIS EXISTING LABORATORY HARDWARE, THE REPLACEMENT INJECTOR FACEPLATES SHALL HAVE EXTERIOR MECHANICAL INTERFACES IDENTICAL TO THAT SHOWN IN NASA DRAWING 623862. AN EXISTING 69-ELEMENT OXYGEN INJECTOR WILL BE USED WITH THE REPLACEMENT INJECTOR FACEPLATES. THE INTERIOR MECHANICAL INTERFACES OF THE OXYGEN INJECTOR ARE SHOWN IN NASA DRAWING 623862. THE REPLACEMENT INJECTOR FACEPLATES SHALL ALSO BE COMPATIBLE WITH THE 1/8 INCH PRESSURE TAP TUBE, AND INCLUDE TWO HOLE OPENINGS AT DIAGONALLY OPPOSITE CORNERS. THE REPLACEMENT INJECTOR FACEPLATES WILL BE USED OVER A RANGE OF CHAMBER PRESSURES AND MIXTURE RATIOS UNDER LABORATORY CONDITIONS. THE FUEL INJECTOR HOLES WITHIN THE FACEPLATES SHALL HAVE FLOW CHARACTERISTICS COMPATIBLE WITH INFORMATION SHOW IN FIGURE 1 AND TABLE 1. TYPICALLY, THE FACEPLATES ARE TO OPERATE WITH GASEOUS OXYGEN OXIDIZER AND GASEOUS METHANE FUEL OVER A PC RANGE OF FROM 1.3 TO 4.0 FOR DURATIONS OF APPROXIMATELY 5 SECONDS. IT IS UNDERSTOOD THAT ACTUAL OPERATION AT STOICHIOMETRIC MR IS NOT TO BE USED AS A DESIGN LIMITING PARAMETER. THE DESIGN IS TO UTILIZE THE EXISTING GOX/H2 OPERATIONAL CHARACTERISTICS AS GUIDELINES FOR THERMAL DISTRIBUTION AND MAXIMUM PRESSURE DROP. THERE IS ALSO A DESIRE TO REDUCE OVERALL FACEPLATE FUEL PRESSURE DROP AND IN NO CASE EXCEED THE CURRENT DROP. VERIFICATION OF UNIT PRESSURE DROP SHALL BE BY COLD FLOW. WHILE THE THERMAL DISTRIBUTION OF THE EXISTING INJECTOR FACEPLATES, WHEN TESTED WITH GOX/H2 IS KNOWN TO BE LESS THAN UNIFORM, THE GOAL IS TO PROVIDE NO WORSE DISTRIBUTION. LIMITED ANALYSIS SHALL BE PERFORMED TO ASSESS THIS GOAL; NO FUNCTIONAL VERIFICATION NEED BE PERFORMED.

IGF::OT::IGF, TASK ORDER 0017, ESR19 AGING SURVEILLANCE

NEW TASK ORDER CLIN 0004

TASK ORDER FOR IN-SPACE PROPULSION

NEXT PHASE 2 CLOSEOUT REVIEW SUPPORT

AFT END REPAIR AGING STUDY

PHASE 1 PRELIMINARY DESIGN STUDY FOR THE LUNAR ATMOSPHERE AND DUST ENVIRONMENT EXPLORER (LADEE)

RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY)

GFP, TEST FIXTURE EQUITABLE ADJUSTMENT

DISPOSITION OF GFP

SD-956 LINER MATERIAL

THIS IS A TASK ORDER ENTITLED, "DESIGN OF THE NASA HIGH VOLTAGE HALL ACCELERATOR ENGINEERING MODEL THRUSTER"

FLEXSEAL RUBBER STUDY

SPECIAL STUDY FOR RUBBER AGING EVALUATION

AWARD TASK ORDER 0009, SR-19 LINER KITS

LINER INHIBITOR KITS

ENG & LAB TEST SUPPORT FOR RSLP MMII, STAGE 2 MOTOR

RESEARCH AND TECHNOLOGIES FOR AEROSPACE PROPULSION SYSTEMS TECHNOLOGY AREA 4- SPACE PROPULSION. TASK ORDERS TO BE ISSUED FOR TECHNOLOGY AREA 4. CONTRACT IDIQ TO AEROJET.

IDIQ