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Posted
Nov 6, 2026
Nov 22, 2026
High temperature furnace and grips.
Posted
Nov 3, 2026
Nov 17, 2026
Procure launch services through a full and open competition for at least 8 full-mission-assurance launches to the following orbits: 2 high C3 orbit in 2031; 2 lagrange/lunar orbit in 2030; 3 sun synchronous orbit (SSO) in 2030 (2 mission) and 2031 (1 mission); 1 low earth orbit (LEO) in 2030.
Posted
Oct 30, 2026
Nov 13, 2026
Provide enterprise-level development, sustaining engineering, and operations.
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City
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Washington
County
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District of Columbia
Address
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300 E St SW, Suite 5R30
Zip Code
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20546
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IGF::OT::IGF "ARTIFICIAL INTELLIGENCE BASED CONTROL POWER OPTIMIZATION" THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASK REQUIREMENTS: 3.1. DEVELOP FULL WING TIP-TO-WING TIP AEROELASTIC FINITE ELEMENT MODEL THE SYMMETRIC HALF MODEL USED FOR THE PROOF-OF-CONCEPT STUDY SHALL BE EXPANDED TO A FULL AERO-SERVOELASTIC MODEL WING TIP-TO WING-TIP NASTRAN FINITE ELEMENT MODEL TO ANALYZE BOTH SYMMETRIC AND ASYMMETRIC MANEUVERS THROUGHOUT THE FLIGHT ENVELOPE. (DELIVERABLE 4.3: TOOL TO MIRROR NASTRAN HALF MODEL INTO FULL WING TIP-TO-WING TIP MODEL) 3.2. UPDATE WING TIP-TO-WING TIP FEM TO FULL AEROSERVOELASTIC MODEL THIS FULL WING TIP-TO-WING TIP MODEL SHALL ALSO FEATURE MULTIPLE TRAILING EDGE CONTROL SURFACES AND TWO VERTICAL TAILS WITH RUDDERS BASED ON THE BOEING OREIO CONTROL SURFACE GEOMETRY AND DIMENSIONS. DIFFERENT ACTUATOR SIZES AND PROPERTIES SHALL BE USED FOR THE DIFFERENT CONTROL SURFACES TO REPRESENTATIVELY MODEL ACTUATION AND CONTROL POWER REQUIREMENTS. (DELIVERABLE 4.4: FULL WING TIP-TO-WING TIP AEROSERVOELASTIC FINITE ELEMENT MODEL) 3.3. DEVELOP FULL WING TIP-TO-WING TIP AEROELASTIC FINITE ELEMENT MODEL THE PROOF-OF-CONCEPT PROCESS DEVELOPED DURING THE ARMD SEEDLING FUND PHASE I EFFORT SHALL BE EXPANDED TO ACCOMMODATE THE FULL AEROSERVOELASTIC MODEL FROM TASK 1. THIS TASK SHALL INCLUDE CAPTURING THE FULL SPECTRUM OF AVAILABLE CONTROL SURFACES, INCLUDING ALL TRAILING EDGE DE-VICES AND VERTICAL TAILS/RUDDERS. THE SIZE OF THE ANN SHALL BE INCREASED TO CAPTURE THE INCREASED NUMBER OF CONTROL SURFACES AND ADDITIONAL PARAMETERS TO ACCOUNT FOR REFINED ACTUATOR DYNAMICS. TO VALIDATE THE APPROACH, THE SYMMETRIC PITCH MANEUVER EXAMPLE CASE FROM THE PHASE I PROJECT SHALL BE USED AS A VALIDATION CASE. IN THIS CASE, THE FULL ANALYSIS IS EXPECTED TO YIELD SIMILAR RESULTS FOR A SYMMETRIC MANEUVER AS THE PHASE I HALFMODEL. THE TRIM ANALYSIS SHALL BE EXPANDED TO INCLUDE BOTH SYMMETRIC AND ASYMMETRIC MANEUVERS REQUIRING A FULL MODEL LIKE YAW, SIDESLIP, DYNAMIC OVERSWING, OR ENGINE OUT CONDITIONS. THE FIGURE-OF-MERIT FOR THE ANN OPTIMIZATION SHALL BE MODIFIED FROM THE HINGE MOMENT SUM PROXY TO THE ACTUAL ACTUATION POWER, BY INCLUDING SIMPLIFIED ACTUATOR PROPERTIES AND DYNAMICS BASED ON A LITERATURE SEARCH. (DELIVERABLE 4.5: MATLAB BASED NEURAL NETWORK PROCESS FOR ACTUATION POWER OPTIMIZATION) 3.4. NEURAL NETWORK TOPOLOGY TO ACCOMMODATE AN INCREASED NUMBER OF TRAINING DATA SETS AND VARIABLES, THE CRITERIA FOR SELECTING AND IMPLEMENTING THE CURRENTLY DEFINED NEURAL NETWORK FROM THE PHASE I EFFORT SHALL BE REVISITED, SUCH AS COMPUTATIONAL PROPERTIES, PROCESSING UNITS (I.E. THE NUMBER OF INPUTS TO THE NETWORK VS. THE NUMBER OF OUTPUTS), TOPOLOGY OF THE NETWORK, (I.E. THE NUMBER OF INTERCONNECTIONS, NODE CHARACTERISTICS THAT ARE CLASSIFIED BY THE TYPE OF NONLINEAR ELEMENTS USED, AND THE KIND OF LEARNING RULES IMPLEMENTED), ACTIVATION FUNCTION (WHICH DEFINES THE OUTPUT OF A NODE GIVEN AN INPUT OR SET OF INPUTS, EX-AMPLE: STEP FUNCTION, LOG-SIG, TAN-SIG, LINEAR COMBINATION, SOFTMAX ETC.). AND LEARNING ALGORITHMS (I.E. FEED-FORWARD, FEEDBACK ETC.). ALTHOUGH MANY OF THESE ASPECTS HAVE BEEN CONSIDERED DURING THE PHASE I PROJECT, THE INCREASED SIZE AND MORE COMPLEX TOPOLOGY OF THE PRESENT EFFORT WILL REQUIRE REVISITING THEM TO MAKE THE NEURAL NETWORK AS ROBUST AND RELIABLE AS POSSIBLE. CURRENTLY, A GENETIC ALGORITHM IS BEING USED FOR GLOBAL OPTIMIZATION. THE EXPECTED LARGER NUMBERS OF INPUT DATA SETS WILL OFFER THE OPPORTUNITY TO INVESTIGATE OTHER EVOLUTIONARY ALGORITHMS AS WELL. 3.5. EXPAND MANEUVER ANALYSIS AND OPTIMIZATION THE INITIAL QUASI-STEADY APPROACH SHALL BE EXPANDED TO COVER FULL MANEUVERS, E.G. SIMULATING AN ACTUAL PULL-UP FROM A 1.0G CRUISE CONDITION TO A 2.5G MANEUVER. BY COMPUTING A DEFLECTION SCHEDULE FOR SMALL LOAD FACTOR INCREMENTS AND INTEGRATING OVER THE ENTIRE MANEUVER, AN ACCURATE MEASURE OF THE TOTAL ACTUATION ENERGY SHALL BE OBTAINED
"IGF::OT::IGF" OTHER FUNCTIONS TITLE- "WIND-TUNNEL BALANCE CALIBRATION ASSESSMENT" 3.1 INVESTIGATE PREVIOUS WORK COMPLETED IN SUPPORT OF THE BALANCE CALIBRATION ASSESSMENT. THIS INCLUDES CALIBRATION DATA COLLECTED. 3.2 EMPLOY STATISTICAL DESIGN OF EXPERIMENTS TO DEVELOP A COMMON CALIBRATION LOAD SCHEDULE FOR EACH OF THE BALANCE TYPES THAT CAN BE EXECUTED ON THE FOLLOWING BALANCE CALIBRATION SYSTEMS: NASA LARC SVS, NASA LARC MANUAL CALIBRATION SYSTEM, TRIUMPH ABCS, AND THE NASA ARC SANDBERG-SERRELL BALANCE CALIBRATION MACHINE. THE COMMON LOAD SCHEDULE SHALL BE BASED ON A PREDETERMINED CALIBRATION MODEL FORM. THE INITIAL FOCUS OF THIS ASSESSMENT SHALL BE ON THE NASA LARC SVS WITH EACH BALANCE TYPE. 3.3 MODIFY THE CURRENT SVS PROCESSING CODE TO ACCOMMODATE ANY GIVEN CALIBRATION LOAD SCHEDULE. 3.4 EMPLOY STATISTICAL ANALYSIS AND UNCERTAINTY METHODS TO ASSESS THE CALIBRATION DATA FOR A GIVEN BALANCE CALIBRATION TYPE AND CALIBRATION SYSTEM. 3.5 EMPLOY STATISTICAL PROCESS CONTROL TO DEFINE QUANTITATIVE METRICS FOR ASSESSING THE BETWEEN CALIBRATION VARIABILITY FOR A GIVEN CALIBRATION SYSTEM AND BALANCE TYPE. 3.6 EMPLOY RIGOROUS STATISTICAL UNCERTAINTY METHODS FOR QUANTITATIVELY ASSESSING BETWEEN CALIBRATION SYSTEM DISCREPANCIES. THIS SHALL INCLUDE METHODS FOR MITIGATING ANY DISCREPANCIES. 3.7 EMPLOY RIGOROUS STATISTICAL UNCERTAINTY METHODS FOR ASSESSING THE UNCERTAINTY IN USING THE NASA-DEVELOPED IN-SITU LOAD SYSTEM (ILS). 3.8 PRESENT TECHNICAL FINDINGS OF THE ASSESSMENT AT APPROPRIATE FORUMS. THESE MAY INCLUDE AIAA CONFERENCES AND WIND-TUNNEL BALANCE-SPECIFIC SYMPOSIUMS. 3.9 PROVIDE WRITTEN REPORTS ON ANALYSES PERFORMED DETAILING THE TECHNICAL FINDINGS OF THE ASSESSMENT.
IGF::OT::IGF "TRANSPORTATION SYSTEMS ANALYSIS MODEL (TSAM) VI - SHORT HAUL STUDIES AND ENHANCEMENTS" THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 1.1.TSAM MAINTENANCE AND UPGRADES. THE CONTRACTOR SHALL UPDATE, ENHANCE AND FIX BUGS TO THE TSAM MODEL AS NEEDED. THIS WILL INCLUDE IMPORTING AND PROCESSING THE LATEST HISTORICAL DATABASES AND/OR SOCIOECONOMIC PROJECTIONS. THE CONTRACTOR SHALL PERFORM ALL NEEDED RECALIBRATIONS AFTER IMPORTING UPDATED DATABASES. THIS WILL ALSO INCLUDE BUG FIXES AS NEEDED AND INCREMENTAL FEATURE OR ALGORITHM ENHANCEMENTS AS IDENTIFIED. 1.2. TSAM USER GUIDE THE CONTRACTOR SHALL WORK WITH NASA TO CREATE A COMPREHENSIVE USER GUIDE FOR TSAM. THE USER GUIDE SHALL INCLUDE THE FOLLOWING ELEMENTS: 1. TABLE OF CONTENTS 2. DEVELOPMENT HISTORY OF TSAM AND THE MAJOR FEATURES IN TSAM. 3. DESCRIPTION OF TSAM DATA SOURCES AND DATA REQUIREMENTS 4. DESCRIPTION OF TSAM DATA CALIBRATION PROCEDURES 5. TUTORIAL SECTION FOR NEW USERS TO TSAM, INCLUDING INSTALLATION INSTRUCTIONS AND A STEP-BY-STEP DESCRIPTION OF HOW TO RUN A TEST CASE. 6. DESCRIPTION OF EACH FEATURE AND USER INPUT IN THE TSAM USER INTERFACE 7. DESCRIPTION OF ALL OUTPUT FILES PRODUCED BY TSAM 8. COMPREHENSIVE LIST OF RELEASE NOTES FOR ALL PREVIOUS VERSIONS OF TSAM 9. INDEX 1.3. IMPROVE THE TSAM/ACES INTEGRATION CAPABILITY THE CONTRACTOR SHALL WORK WITH NASA TO DEVELOP THE ARCHITECTURE AND ALGORITHMS NECESSARY TO MORE FULLY INTEGRATE TSAM WITH THE AIRSPACE CONCEPT EVALUATION SYSTEM (ACES) SIMULATION. IN PREVIOUS TSAM V TASK ORDER, THE CONTRACTOR CREATED A FRAMEWORK THAT PROCESSED ACES FLIGHT TIMES AND COMPARED THOSE TIMES TO THE TSAM COMMERCIAL AIRLINE TRIP TIMES, AND INCREASED THE TSAM TRIP TIMES TO REFLECT DELAYS CALCULATED BY ACES. TSAM COULD THEN BE RE-RUN WITH THE NEW TRIP TIMES TO PRODUCE A NEW DEMAND SCHEDULE. THIS NEW SUBTASK WILL BUILD UPON THAT FRAMEWORK. IMPROVING THE INTEGRATION CAPABILITY MAY INVOLVE REFINING THE CURRENT PROCESSING OF ACES FLIGHT TIME OUTPUTS INTO TSAM FLIGHT TIMES, AUTOMATING METHODS OF GENERATING ACES FLIGHT DATA SETS FROM TSAM OUTPUTS, AND AUTOMATING THE RUNNING OF TSAM AND ACES IN AN ITERATIVE LOOP. 1.4. DEVELOP TSAM METHODS TO SUPPORT SHORT HAUL CONCEPT STUDIES. THE CONTRACTOR SHALL WORK WITH NASA TO DEVELOP TSAM METHODS TO SUPPORT THE ANALYSIS OF A SHORT HAUL AIRCRAFT CONCEPT. THE SHORT HAUL AIRCRAFT CONCEPT IS A COMMERCIAL AIRCRAFT CAPABLE OF OPERATING ECONOMICALLY ON ROUTES THAT ARE NOT CURRENTLY PROFITABLE FOR AIRLINE OPERATORS. PRELIMINARY STUDIES OF A SHORT HAUL CONCEPT USING TSAM HAVE INVOLVED USING TSAM S AIR TAXI MODEL, WHICH HAS A NUMBER OF SHORTCOMINGS. IMPROVING TSAM S ABILITY TO MODEL A SHORT HAUL CONCEPT MAY INCLUDE MODIFYING THE AIR TAXI MODEL, INCORPORATING THE SHORT HAUL CONCEPT AND ROUTE STRUCTURE INTO THE COMMERCIAL AIR MODEL, AND CREATING NEW ANALYSIS METHODS. 1.5. SHORT HAUL AIRCRAFT STUDY THE CONTRACTOR SHALL WORK WITH NASA TO CONDUCT A PASSENGER DEMAND STUDY FOR A SHORT HAUL AIRCRAFT CONCEPT. THE SHORT HAUL STUDY WILL PREDICT PASSENGER DEMAND AND FLIGHT SCHEDULES FOR ONE OR MORE AIRCRAFT CONCEPTS DESIGNED TO OPERATE IN SHORT HAUL MARKETS. THE CONTRACTOR WILL USE TSAM TO CONDUCT THE STUDY, INCORPORATING NEW/IMPROVED SHORT HAUL ANALYSIS METHODS FROM SUBTASK 3.5. AS PART OF THIS STUDY, THE CONTRACTOR WILL NEED TO ESTIMATE THE FARES ON THE SHORT HAUL ROUTES THAT CURRENTLY HAVE NO AIR SERVICE. NASA WILL PROVIDE THE AIRCRAFT CONCEPT INFORMATION, AND NASA AND THE CONTRACTOR WILL COLLABORATE IN DEFINING THE STUDY PARAMETERS. 1.6. DEVELOP A SIMPLER RELEASABLE VERSION OF TSAM THE CONTRACTOR SHALL WORK WITH NASA TO DEVELOP A SELF-CONTAINED RELEASABLE VERSION OF TSAM THAT CAN BE USED BY NON-EXPERT RESEARCHERS. TSAM IS COMPOSED OF A COMPLICATED ASSORTMENT OF MODELS AND TOOLS, SOME OF WHICH WERE CREATED FOR A SPECIFIC RESEARCH PURPOSE AND ARE NO LONGER ACTIVELY SUPPORTED. NON-EXPERT USERS MAY ATTEMPT TO USE THESE MODULES WITHOUT UNDERSTANDING THEIR LIMITATIONS. TH
NEW TASK TO BILL IDIQ WORK.
IGF::OT::IGF M525 BOWLING ALLEY DEMOLITION
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