Boeing

NASA HUMAN LANDING SYSTEM (HLS) DESCENT STUDY ELEMENT

program · Award ID: 80MSFC19C0022

ORION ALTERNATE BLOCK 2 TPS MATERIALS AND HEAT SHIELD SYSTEMS ADVANCED DEVELOPMENT

program · Award ID: NNA07BC30C

IGF::OT::IGF "OTHER FUNCTIONS" WIND TUNNEL TESTING SERVICES IN THE BOEING ST. LOUIS, POLYSONIC WIND TUNNEL (PSWT) FOR THE SPACE LAUNCH SYSTEMS (SLS) PROGRAM

program · Award ID: NNL12AE68P

THREE DIMENSIONAL (3D) SIMULATIONS, MODELS, TOOLS, SCANNING AND SUPPORT OPERATIONS, AND ANALYSIS PACKAGES IN SUPPORT OF THE EXPLORATION GROUND SYSTEMS (EGS) PROGRAM'S BASELINE, MOBILE LAUNCHERS 1 AND 2, MOBILE LAUNCHER SUBSYSTEMS.

program · Award ID: 80KSC025F0011

IGF::OT::IGF 2.0 POWER AND PROPULSION ELEMENT -PPE- STUDY THE POWER AND PROPULSION ELEMENT -PPE- STUDY CONSISTS OF THE OVERALL ARCHITECTURE DEFINITION AND PERFORMANCE OF THE INDIVIDUAL STUDIES INCLUDING THE TECHNICAL AND MANAGEMENT EFFORTS OF DIRECTING AND CONTROLLING THE INTEGRATED ENGINEERING EFFORT. BOEING SHALL PERFORM THE INDIVIDUAL STUDIES AS FOLLOWS. 2.1 INDIVIDUAL STUDIES 2.11 DEFINE AN APPROACH FOR THE PPE DESIGN AND VERIFICATION TO PROVIDE THE REQUIRED FUNCTIONALITY WITH SUFFICIENT RELIABILITY, FAULT PROTECTION AND AVAILABILITY TO OPERATE AS PART OF A HUMAN-RATED SYSTEM FOR ALL CREWED MISSION PHASES. THIS COULD INCLUDE THE USE OF RELEVANT DATA FROM ON-ORBIT OPERATION OF SUBSYSTEMS IF THE PPE USE CASE IS APPLICABLE, SUFFICIENT NUMBER OF UNITS AND CUMULATIVE OPERATING HAVE BEEN ACHIEVED, AND FAILURE MODES ARE SUFFICIENTLY WELL UNDERSTOOD TO ESTABLISH THE CONFIDENCE AND MARGIN NEEDED FOR USE AS PART OF A HUMAN-RATED SYSTEM. 2.1.2 DEFINE AN APPROACH TO THE USE OF STANDARDS, SPECIFICATIONS, AND ENGINEERING PROCESSES TO ASSURE A PPE DESIGN THAT COST-EFFECTIVELY MINIMIZES THE PROBABILITY OF THE OCCURRENCE OF FAILURE MODES THROUGH THE APPLICATION OF SELECTIVE REDUNDANCY, FACTORS OF SAFETY, OR OTHER DESIGN MARGINS AS NECESSARY FOR OPERATION AS PART OF A HUMAN-RATED SYSTEM. 2.1.3 DEFINE AN APPROACH TO PERFORMING PROPULSIVE ORBITAL MAINTENANCE MANEUVERS FOR ENTIRE DSG INTEGRATED WITH A RANGE OF POSSIBLE STACK CONFIGURATIONS. 2.1.4 DEFINE AN APPROACH FOR PPE OPERATION DURING THE RENDEZVOUS AND DOCKING OF CREWED AND UNCREWED VISITING VEHICLES INCLUDING ORION WITH A DSG. 2.1.5 DEFINE AN APPROACH FOR THE PPE TO PROVIDE A DSG WITH UNCREWED AUTONOMOUS ORBIT-TRANSFER CAPABILITY. 2.1.6 DEFINE AN APPROACH FOR THE DESIGN, DEVELOPMENT, AND OPERATION OF A HIGH-RELIABILITY PPE POWER GENERATION AND POWER TRANSFER CAPABILITY AS PART OF A DSG. 2.1.7 DEFINE AN APPROACH TO HOSTING TWO IDSS PASSIVE INTERFACES AND ASSESSMENT FOR HOW THIS DRIVES SYSTEM TECHNICAL RISK, COST, AND SCHEDULE. 2.1.8 DEFINE AN APPROACH TO ADDRESSING THE MINIMAL 15 YEAR PPE OPERATIONAL LIFETIME REQUIREMENT. 2.1.9 DEFINE AN APPROACH TO LONG-TERM AUTONOMOUS OPERATION IN THE CIS-LUNAR ENVIRONMENT INCLUDING FAULT MONITORING, DETECTION, AND HANDLING. 2.1.10 DEFINE AN APPROACH FOR THE PPE TO PROVIDE HIGH-RELIABILITY COMMUNICATIONS FOR A DSG. 2.1.11 PERFORM AN ASSESSMENT OF ACCOMMODATING AN OPTICAL COMMUNICATION DEMONSTRATION ONBOARD THE PPE. 2.1.12 PERFORM AN ASSESSMENT, INCLUDING REVIEWING AND PROVIDING COMMENTS, OF NASA DEFINED ENGINEERING DESIGN&CONSTRUCTION STANDARDS, INTEROPERABILITY STANDARDS, AND-OR SAFETY AND MISSION ASSURANCE STANDARDS THAT MAY BE PROPOSED FOR THE PPE IN A HUMAN RATED DSG. 2.1.13 IDENTIFY AREAS OF SIGNIFICANT POTENTIAL SYNERGIES BETWEEN THE PPE SPECIFIC CAPABILITIES AND BOTH THE CURRENT AND FUTURE CAPABILITIES FOR THE COMMERCIAL MARKET. THIS INCLUDES IDENTIFICATION OF PPE SPECIFIC CAPABILITIES THAT MAY BE BEYOND CURRENT OR PLANNED COMMERCIAL CAPABILITIES. THIS COULD ALSO INCLUDE A VARIETY OF TOPICS SUCH AS BUT NOT LIMITED TO THE USE OF ADVANCED SOLAR ELECTRIC PROPULSION AND INNOVATIVE IDEAS FOR PARTNERSHIP BUSINESS MODELS INCLUDING OPTIONS FOR POTENTIAL COST SHARE OR COST CONTRIBUTIONS THAT ADDRESSES INTELLECTUAL PROPERTY, ASSET OWNERSHIP, AND TIMING OF DELIVERY OF THE ASSET AND-OR SERVICES TO THE GOVERNMENT. 2.1.14 PERFORM AN ASSESSMENT OF ACQUIRING HIGH POWER, HIGH THROUGHPUT ELECTRIC PROPULSION STRINGS AS PART OF THE COMMERCIAL BUS, RATHER THAN THROUGH A GOVERNMENT FURNISHED EQUIPMENT ROUTE. 2.1.15 DEFINE AN APPROACH TO PROVIDING ACCOMMODATIONS OF POTENTIAL -INTERNATIONAL OR DOMESTIC PARTNER PROVIDED- HARDWARE SUCH AS ROBOTIC FIXTURES, SCIENCE AND TECHNOLOGY DEMONSTRATION AND UTILIZATION AND OTHER POSSIBLE ELEMENTS. 2.1.16 DEFINE AN APPROACH TO ADDRESSING ABILITY TO MANAGE BATTERIES CHARGE AND DISCHARGE DURING DIFFERENT ECLIPSE DURATIONS

program · Award ID: 80GRC018C0005

THREE DIMENSIONAL (3D) SIMULATIONS, MODELS, TOOLS, SCANNING AND SUPPORT OPERATIONS, AND ANALYSIS PACKAGES IN SUPPORT OF THE EXPLORATION GROUND SYSTEMS (EGS) PROGRAM'S BASELINE.

program · Award ID: 80KSC026F0002

IGF::CT::IGF PROGRAM: ASTEROID REDIRECT MISSION (ARM). PROJECT: ADAPTING COMMERCIAL SPACECRAFT FOR THE ARM. THIS PROJECT WILL STUDY THE FEASIBILITY OF ADAPTING AND LEVERAGING COMMERCIAL SPACECRAFT DESIGN, MANUFACTURE, INTEGRATION, AND TESTING CAPABILITIES FOR DEVELOPING THE ASTEROID REDIRECT VEHICLE. TO REDUCE DEVELOPMENT COSTS, NASA IS INTERESTED IN STUDYING THE FEASIBILITY OF ADAPTING AND LEVERAGING EXISTING COMMERCIAL SPACECRAFT DESIGN, MANUFACTURE, INTEGRATION, AND TESTING CAPABILITIES FOR DEVELOPING THE ARV AND ITS MAIN COMPONENTS SUCH AS THE SOLAR ELECTRIC PROPULSION (SEP) MODULE. THE MAJOR ELEMENTS OF THE ARV CONFIGURATION ARE THE SEP MODULE, THE MISSION MODULE, AND THE ASTEROID CAPTURE SYSTEM. THE CURRENT BASELINE CONCEPTUAL SEP MODULE CONSISTS OF THE SOLAR ARRAYS AND A HIGH-VOLTAGE POWER MANAGEMENT AND DISTRIBUTION SUBSYSTEM; A PROPULSION SUBSYSTEM INCLUDING HALL THRUSTERS, POWER PROCESSING UNITS (PPUS), TANKS FOR XENON STORAGE, AND A PROPELLANT DISTRIBUTION AND CONTROL SUBSYSTEM; A THERMAL CONTROL SUBSYSTEM; A REACTION CONTROL SUBSYSTEM; AND A MECHANICAL SUBSYSTEM. THE MECHANICAL SUBSYSTEM INCLUDES MECHANISMS FOR LAUNCH VEHICLE SEPARATION AND FOR DOCKING WITH THE ORION SPACECRAFT. THE MISSION MODULE CONTAINS THE ARV ATTITUDE CONTROL SYSTEM, A COMMAND AND DATA HANDLING SYSTEM, A COMMUNICATIONS SUBSYSTEM, AN ENERGY STORAGE SUBSYSTEM, A LOW-VOLTAGE POWER DISTRIBUTION SUBSYSTEM, A THERMAL CONTROL SUBSYSTEM, ALL THE INSTRUMENTATION REQUIRED FOR NAVIGATION, ASTEROID CHARACTERIZATION, AND ASTEROID CAPTURE, AND A SEPARATION MECHANISM TO ENABLE EJECTION OF THE CAPTURE SYSTEM IF NECESSARY. THE CAPTURE SYSTEM COULD BE EITHER AN INFLATABLE OR DEPLOYABLE STRUCTURE THAT CAPTURES THE ASTEROID IN A BAG OR ROBOTIC MANIPULATORS THAT CAPTURE A BOULDER FROM THE ASTEROID S SURFACE. ALTERNATIVELY, THE CAPTURE SYSTEM MAY ALSO CONTAIN THE NAVIGATIONAL SENSORS USED DURING ASTEROID RENDEZVOUS, PROXIMITY OPERATIONS, AND CAPTURE. IN THIS CASE, A CONTROL AND DATA SYSTEM INTERFACE WOULD EXIST BETWEEN THE MISSION MODULE AND CAPTURE SYSTEM. THE MISSION MODULE INTERFACES WITH THE SOLAR ELECTRIC PROPULSION MODULE AND THE ASTEROID CAPTURE SYSTEM. A DOCKING MECHANISM ATTACHED TO AFT END OF THE ARV WILL ALLOW IT TO DOCK WITH THE ORION SPACECRAFT. EXISTING COMMERCIAL CAPABILITIES CAN BE USED TO REDUCE THE DEVELOPMENT COST OF THE ARV SOLAR ELECTRIC PROPULSION MODULE, THE MISSION MODULE, OR A COMBINED PROPULSION AND MISSION MODULE. A STANDALONE HIGH-POWER SEP TUG WITH AN END-OF-LIFE CAPABILITY OF APPROXIMATELY 40 KW MAY PERMIT DIRECT APPLICATION AS A COMPONENT OF THE ARV, AND ALSO EXTEND TO OTHER COMPELLING GOVERNMENT AND COMMERCIAL MISSION APPLICATIONS. BLOCK UPGRADE APPROACHES TO ACCOMMODATE HIGHER POWER (50-300 KW) SEP SYSTEMS FOR FUTURE EXPLORATION MISSIONS ARE ALSO OF INTEREST. A FEASIBILITY STUDY ON THE USE OF EXISTING COMMERCIAL DESIGNS FOR THE ARV AND/OR MISSION MODULE SHALL BE PREPARED, INCLUDING ANY MODIFICATIONS REQUIRED TO EXISTING COMMERCIAL DESIGNS, THE LEVERAGING OF COMMERCIAL DEVELOPMENT AND FABRICATION CAPABILITIES, AND INTEGRATION AND TESTING FACILITIES. THE STUDY SHALL INCLUDE CONCEPTUAL SYSTEMS DESIGN, ANALYSIS, AND ENGINEERING, AND AN ESTIMATE THE COST AND SCHEDULE REQUIRED FOR FLIGHT SYSTEMS DEVELOPMENT. INNOVATIVE IDEAS FOR MINIMIZING COST TO THE GOVERNMENT ARE ENCOURAGED.

program · Award ID: NNH14CL76C

DESIGN VISUALIZATION (DV) SERVICES SUPPORT FOR ORION, ARES, INTEGRATED OPS, AND ALTAIR.

program · Award ID: NNK09EA02T

STATEMENT OF WORK (SOW): TASK TITLE: FULL SCALE LEAK RATE CHARACTERIZATION TESTS OF THE NASA ENGINEERING AND SAFETY CENTERS COMPOSITE CREW MODULE. 1.0 INTRODUCTION/BACKGROUND: THE NASA ENGINEERING AND SAFETY CENTER (NESC) COMPOSITE CREW MODULE (CCM) PROJECT WAS A TECHNOLOGY DEMONSTRATION TASK TO DESIGN, DEVELOP, MANUFACTURE, AND TEST A FULL SCALE COMPOSITE CREW MODULE PRIMARY STRUCTURE BASED ON THE CONSTRAINTS ASSOCIATED WITH THE ORION ELEMENT OF THE NASA CONSTELLATION PROGRAM. SINCE THE NESC COMPOSITE CREW MODULE PROJECT WAS PERFORMED ON A SCHEDULE THAT WAS ACCELERATED FROM THE ORION PROJECT, LOADS AND INTERFACES WERE INCORPORATED AND FROZEN IN JUNE 2007. THUS SOME OF THE LOADS AND INTERFACES ON CCM TODAY ARE NOT CONSISTENT WITH TODAYS VERSION OF THE ORION CREW MODULE. DURING THE DESIGN PHASE OF THE CCM PROJECT, THE ORION PROJECT OFFICE EXPRESSED CONCERNS WITH THE NESC RATIONALE FOR MANAGING LEAKAGE THROUGH THE COMPOSITE MATERIAL SYSTEM. AT THAT TIME, THE TECHNICAL SOLUTION WAS TO USE AUTOCLAVE CURED SANDWICH SKINS WITH UN-VENTED CORE, PROVIDING TWO UNIQUE BARRIERS TO LEAKAGE THROUGH THE SANDWICH SYSTEM. THERE WERE CONCERNS IDENTIFIED WITH THAT RATIONALE IN THAT UNDETECTABLE DAMAGE COULD CAUSE MICRO-CRACKING OF THE LAMINATE IN THE SKINS, RESULTING IN A COMPROMISED FIRST LAYER. COINCIDENT DAMAGE ON THE SECOND LAYER WOULD RESULT IN AN UNDETECTABLE LEAK PATH. GIVEN THE SIGNIFICANT NUMBER OF ATTACHMENTS ON BOTH THE INTERIOR AND EXTERIOR OF THE CREW MODULE STRUCTURE, THE POSSIBILITY OF UNDETECTED DAMAGE IS PRESENT, AND THEREFORE THE LEAK MANAGEMENT RATIONALE AS ORIGINALLY PROPOSED WAS NOT ACCEPTED. DURING THE MANUFACTURING PHASE OF THE CCM, A HIGHLY FLEXIBLE MEMBRANE WAS IDENTIFIED THAT COULD BE INSTALLED ON THE INTERIOR OF THE CCM USING A PRESSURE SENSITIVE ADHESIVE. THIS MEMBRANE HAS A CAPACITY FOR LARGE ELONGATION SO THAT IT CAN BE STRETCHED OVER IRREGULAR SHAPES, SUCH AS BOLTS, AS WELL AS CONFORM TO ODD SHAPES AND SURFACES. THE MEMBRANE FILM WAS ALSO SHOWN TO BE DAMAGE TOLERANT THROUGH IMPACT TESTING THAT RESULTED IN A CRACKED LAMINATE SKIN WHILE THE FILM WAS UNAFFECTED. THIS FILM/LAMINATE SKIN WAS EVALUATED IN A PERMEABILITY TEST FIXTURE BOTH WITH AND WITHOUT DAMAGE AND INDICATES A POSSIBLE SOLUTION TO A DAMAGE TOLERANCE LEAK PREVENTION MEMBRANE. FOR THE PURPOSES OF THIS STATEMENT OF WORK, THIS FILM/LAMINATE SKIN/MEMBRANE WILL BE IDENTIFIED AND CALLED A LINER IN THESE TEST PROCEDURES. 2.0 SCOPE / OBJECTIVE(S): THE SCOPE OF THIS TASK ORDER IS TO CHARACTERIZE THE LEAK RATE THROUGH THE COMPOSITE SHELL SYSTEM OF THE NESC COMPOSITE CREW MODULE IN ITS AS MANUFACTURED STATE AND WITH A POST MANUFACTURE INSTALLED LEAK PREVENTION MEMBRANE, HEREAFTER CALLED A LINER. PERMEABILITY TESTING OF COMPOSITE MATERIAL COUPONS IS ALSO INCLUDED AS PART OF THE UNDERSTANDING OF THE COMPOSITE MATERIALS USED IN THE CCM. THE OBJECTIVE(S) OF THIS TASK ORDER ARE TO 1. DEVELOP A TEST METHOD FOR CHARACTERIZING THE PERMEABILITY OF SELECTED COMPOSITE MATERIAL COUPONS; 2. PERFORM AND REPORT RESULTS OF PERMEABILITY TESTING OF THE COMPOSITE MATERIAL COUPONS WITH AND WITHOUT DAMAGE AND WITH AND WITHOUT AN APPLIED MEMBRANE FILM; AND 3. PERFORM AND REPORT TEST RESULTS OF LEAK TESTING OF THE COMPOSITE CREW MODULE (CCM) IN EIGHT (8) DIFFERENT CONFIGURATIONS IN THE MARSHALL SPACE FLIGHT CENTER (MSFC) VACUUM CHAMBER V20. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL SERVE AS THE TEST CONDUCTOR FOR ALL TESTS DESCRIBED IN TASKS 3.1 AND 3.2. MARSHALL SPACE FLIGHT CENTER (MSFC) PERSONNEL OR EXISTING ON-SITE NASA CONTRACTOR PERSONNEL, WILL PROVIDE FACILITY SUPPORT INCLUDING OPERATION OF THE MSFC V20 VACUUM CHAMBER, SUPPORT EQUIPMENT, OVERHEAD CRANES, FORKLIFTS, AND OTHER NECESSARY EQUIPMENT. THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 COMPOSITE COUPON CHARACTERIZATION TESTS 3.1.1 THE CONTRACTOR SHALL DEVELOP THE CHARACTERIZATION TEST METHOD AND DISCUSS METHOD DURING A

program · Award ID: NNL12AQ02T

C-17 ORION AIRWORTHINESS ANALYSIS

program · Award ID: NNJ08HD57D