INNOVATIVE DESIGNS INC

THE INNOVATIVE DESIGN, DEVELOPMENT AND OPERATIONS CONTRACT (IDDOC) WILL CONTINUE TO DEVELOP, MAINTAIN, AND MODERNIZE THE ACCOUNTABLE CARE ORGANIZATION - OPERATIONAL SYSTEM (ACO-OS) AND 4 INNOVATION (4I), AND PROVIDE A MODERN SCALABLE ARCHITECTURE, PL

THIS TO PROVIDES INNOVATIVE, DESIGN, DEVELOPMENT, TESTING, AND EXECUTION OF INNOVATIVE AND EMERGING TECHNOLOGIES WHICH MEET DEPARTMENT OF DEFENSE (DOD) STANDARDS AND DES TRANSFORMATION OBJECTIVES.

THIS TASK ORDER WILL PROVIDE SUPPORT IN THE AREAS OF PROJECT EXECUTION AS WELL AS INNOVATIVE DESIGNING, TECHNICAL MENTORING, AND DEPLOYMENT OF UNMANNED UNDERWATER VEHICLE (UUV) SYSTEMS AND SUBSYSTEMS FOR THE UUV COMPETENCY WITHIN SSC PAC AUTONOMOUS SYSTEMS COMPETENCY GROUP, INCLUDING TECHNOLOGICAL AND OPERATIONAL COMPETENCIES. THE PRIMARY UUV SYSTEMS INVOLVED ARE THE NAVY'S MK 18 FAMILY OF UUVS.

SBIR PHASE II AWARD TO INNOVATIVE DESIGN LABS FOR AN INNOVATIVE, AUTHENTIC, AND ANATOMICALLY-CORRECT FEMALE CASUALLY CARE SIMULATOR WITH MIXED REALITY CAPABILITIES FOR THE ARMY APPLICATIONS LABORATORY (AAL).

PHASE II SBIR, EXERGY ENGINEERING WILL DEVELOP A PUMP TECHNICAL HARDWARE SOLUTION TO DEMONSTRATE THE INNOVATIVE DESIGN ADVANCEMENTS NECESSARY FOR ROBUST PUMP OPERATION WITH LOW LUBRICITY AVIATION TURBINE FUELS.

IGF::OT::IGF SBIR PHASE II RESEARCH&DEV: INNOVATIVE DESIGNS FOR RELIABLE ELECTRO-EXPLOSIVE ORDNANCE DEVICES

IGF::OT::IGF THORLEAF RESEARCH, INC. HAS DEMONSTRATED FEASIBILITY IN PHASE I AND NOW PROPOSES A PHASE II EFFORT TO DEVELOP A MINIATURIZED HIGH FLOW, LOW DEAD-VOLUME PRECONCENTRATOR FOR MONITORING TRACE LEVELS OF CONTAMINANTS IN LIQUID WATER UNDER MICROGRAVITY CONDITIONS. OUR INNOVATIVE DESIGN FOR THE PRECONCENTRATOR COMBINES HIGH WATER SAMPLING FLOW RATES WITH LOW DEAD VOLUME, THUS ENHANCING PRECONCENTRATION. THIS IS DESIGNED TO MEET MONITORING NEEDS FOR NASA'S SPACECRAFT WATER EXPOSURE GUIDELINES (SWEGS) AND ADDRESSES A KEY TECHNOLOGY GAP FOR LONG-DURATION HUMAN SPACEFLIGHT, SINCE STANDARD TECHNIQUES WILL NOT FUNCTION WITHOUT GRAVITATION TO STABILIZE PHASE BOUNDARIES. HUMAN EXPLORATION OF THE SOLAR SYSTEM WILL DEPEND ON SUCH TECHNOLOGY, SINCE WATER MUST BE RECYCLED AND THE OPTION OF RETURNING GRAB SAMPLES TO EARTH FOR ANALYSIS FROM BEYOND LOW-EARTH ORBITS DOES NOT EXIST. DURING PHASE II, WE PLAN TO INCORPORATE THIS TECHNOLOGY INTO A MINIATURIZED WATER PRECONCENTRATOR MODULE. BASED ON OUR PHASE I RESULTS WE PROJECT THAT IT WILL BE POSSIBLE TO DEVELOP THIS MODULE WITH A MASS OF ABOUT 0.5 KG AND AVERAGE POWER CONSUMPTION OF<1 WATT.

THE OVERALL TECHNICAL OBJECTIVE OF THE PHASE II EFFORT IS TO MAKE OVERFUN AS A FULLY MULTI-FUNCTIONAL AEROELASTIC SOFTWARE SYSTEM THAT CAN ESTABLISH EITHER THE DISCRETE TIME STATE-SPACE PLANT MODEL OR THE FREQUENCY-DOMAIN AEROELASTIC EQUATION OF MOTION WITH THREE EMBEDDED UNSTEADY AERODYNAMIC SUB-SYSTEMS; DUE TO THE STRUCTURAL DEFORMATION, THE CONTROL SURFACE DEFLECTION AND THE DISCRETE GUST EXCITATION, RESPECTIVELY. ALL THREE UNSTEADY AERODYNAMIC SUB-SYSTEMS CAN BE OBTAINED BY APPLYING THE EXTENDED COMPLEX VARIABLE DIFFERENTIATION (CVD) TECHNIQUE TO THE COMPLEX VERSION OF FUN3D, REFERRED TO AS FUN3D-CVD, TO GENERATE THE NUMERICALLY EXACT LINEARIZED UNSTEADY AERODYNAMIC FORCES. AS A WRAPPER AROUND THE STEADY NAVIER-STOKES (N-S) SOLVER OF FUN3D FOR TRIM ANALYSIS WITH STATIC AEROELASTIC EFFECTS AS WELL AS A WRAPPER AROUND THE COMPLEX UNSTEADY N-S SOLVER OF FUN3D-CVD FOR GENERATING THE THREE UNSTEADY AERODYNAMIC SUB-SYSTEMS, OVERFUN CAN ESTABLISH A VERY ACCURATE TIME-DOMAIN PLANT MODEL OR FREQUENCY-DOMAIN AEROELASTIC EQUATION OF MOTION THAT CAN CAPTURE ALL ESSENTIAL FLOW PHYSICS ON A STATICALLY DEFORMED AEROELASTIC MODEL. ..TO SHOWCASE THAT THE OVERFUN GENERATED PLANT MODEL CAN BE DIRECTLY ADOPTED BY THE MODERN CONTROL LAW DESIGN SCHEMES FOR CONTROL SYSTEM DESIGN, A CLASSICAL AND A ROBUST FLUTTER SUPPRESSION AND GUST LOAD ALLEVIATION CONTROL SYSTEMS WILL BE GENERATED FOR THE BENCHMARK ACTIVE CONTROLS TECHNOLOGY WING WITH TRAILING EDGE FLAP AS INPUT AS WELL AS WITH THE UPPER SPOILER AS INPUT. A TWIN-ENGINE TRANSPORT FLUTTER MODEL (TETFM) THAT WAS TESTED BY THE BOEING ENGINEERS IN THE TRANSONIC DYNAMICS TUNNEL (TDT) WILL BE SELECTED AS THE TEST CASE TO DEMONSTRATE THE ACCURACY OF THE OVERFUN PREDICTED AEROELASTIC SOLUTION FOR COMPLEX CONFIGURATION BY THE VALIDATION WITH THE TDT MEASURED FLUTTER BOUNDARY OF THE TETFM. ..THE OUTCOME OF THE PHASE II EFFORT WILL BE A PRODUCTION-READY OVERFUN SOFTWARE SYSTEM FOR COMMERCIALIZATION IN PHASE III...THE PROPOSED EFFORT IS HIGHLY RELEVANT TO ON-GOING AND FUTURE NASA FIXED WING PROJECTS, WHICH INVOLVE INNOVATIVE DESIGN CONCEPTS SUCH AS THE TRUSS-BRACED WING, BLENDED WING BODY, AND SUPERSONIC BUSINESS JET. THE PROPOSED WORK WILL OFFER A COMPUTATIONAL TOOL TO THE NASA DESIGNERS FOR EARLY EXPLORATION OF DESIGN CONCEPTS THAT EXPLOIT THE TRADE-OFF BETWEEN THE PASSIVE AND ACTIVE APPROACHES FOR MITIGATING THE POTENTIAL AEROELASTIC PROBLEMS ASSOCIATED WITH THOSE CONFIGURATIONS. ..THE PROPOSED DISCRETE TIME STATE-SPACE PLANT MODEL GENERATION CAN BE APPLIED TO VARIOUS FLIGHT VEHICLES INCLUDING BLENDED WING-BODIES, JOINED WINGS, SUB/SUPERSONIC TRANSPORTS, MORPHING AIRCRAFT, AND SIMILAR REVOLUTIONARY CONCEPTS BEING PURSUED. THE PROPOSED RESEARCH WILL BE NEEDED FOR DESIGNING THE NEXT GENERATION OF CIVIL AND MILITARY AIRCRAFT TO MEET THE STRINGENT FUTURE PERFORMANCE GOALS. .

LIGHTWEIGHT ROBOTIC EXCAVATORS ADDRESS THE NEED FOR MACHINES THAT DIG, COLLECT, TRANSPORT AND DUMP LUNAR SOIL. ROBUST AND PRODUCTIVE SMALL ROBOTS ENABLE MINING RICH AND ACCESSIBLE DEPOSITS OF ICE AND OTHER VOLATILES BURIED NEAR CRATERS AT THE LUNAR POLES, DELIVERING RESOURCES TO PRODUCE PROPELLANT, AND THUS MAKING SPACE EXPLORATION SUSTAINABLE. LIGHTWEIGHT EXCAVATORS BRIDGE THE GAP BETWEEN PROSPECTING AND FULL-SCALE ISRU. A LIGHTWEIGHT ROBOT IS PROPOSED THAT EXCAVATES AND DELIVERS REGOLITH WITH PRODUCTION SO SUPERIOR TO THE STATE OF THE ART AS TO ENABLE REALISTIC LUNAR AND PLANETARY APPLICATIONS. DEMONSTRATION OF LIGHT WEIGHT WILL BE ACHIEVED BY OPERATING A LOW MASS ROBOT IN EARTH GRAVITY REDUCED 5/6 BY OFFLOADING. THE SIGNIFICANCE OF THE PROPOSED INNOVATION IS AN APPROACH THAT NOT ONLY PERFORMS THE REQUIRED TASKS BUT IS LOW IN MASS (30 KG TO 150 KG). MASS CONSTRAINTS MAKE PRODUCTIVE EXCAVATION CHALLENGING. HOWEVER, INNOVATIVE DESIGNS INCORPORATING TRANSVERSE BUCKET-WHEELS, HIGH PAYLOAD COMPOSITE DUMP BEDS, AND HIGH-SPEED DRIVING ARE GAME CHANGERS, ENABLING REGOLITH OPERATIONS IN LOW GRAVITY. PHASE 1 EXPERIMENTAL RESULTS SHOW THAT PAYLOAD RATIO AND DRIVING SPEED GOVERN PRODUCTIVITY OF SMALL ROBOTS. PHASE 2 WILL ELEVATE TRLS FROM 3 AT THE BEGINNING TO AN ESTIMATED 4 OR 5 AT END OF CONTRACT.

FOR A NUMBER OF YEARS WE HAVE DEVELOPED, FABRICATED, AND TESTED HIGHLY MINIATURIZED, HIGH VACUUM PUMPS SPECIFICALLY DESIGNED FOR MASS SPECTROMETERS USED ON MARS MISSIONS. THESE PUMPS WOULD ALSO BE USEFUL ON OTHER MISSIONS TO PLANETS AND SATELLITES WITH ATMOSPHERE, SUCH AS TITAN, AS WELL AS TERRESTRIAL APPLICATIONS ON EARTH. IN ORDER TO ALLOW THESE HIGH VACUUM PUMPS TO OPERATE IN HIGH-PRESSURE ENVIRONMENTS SUCH AS EXIST ON TITAN AND EARTH, THE VACUUM PUMP NEEDS TO BE SUPPLEMENTED WITH A ROUGH PUMP THAT CAN TAKE ITS EXHAUST AND COMPRESS IT TO 1 1.5 ATM. THIS PROJECT AIMS TO DESIGN, FABRICATE, TEST, AND DELIVER SUCH A COMPACT VACUUM PUMP SYSTEM THAT CAN GENERATE A HIGH VACUUM, ON THE ORDER OF 1E-8 TORR, AND EXHAUST DIRECTLY TO AN EARTH OR TITAN ATMOSPHERE. THE PUMP WILL BE ASSEMBLED IN A VERY COMPACT, ROBUST, AND LOW-POWER PACKAGE. OUR PHASE I PROJECT CLEARLY DEMONSTRATED THE FEASIBILITY OF OUR INNOVATIVE DESIGN BY DEMONSTRATING THE PERFORMANCE OF A ROUGH PUMP AND DESIGNING A COMPACT VACUUM SYSTEM FOR USE ON EARTH OR OTHER PLANETARY BODIES WITH ATMOSPHERIC PRESSURE GREATER THAN 1 ATM. DURING PHASE II OF THIS PROJECT, WE WILL BUILD A COMPLETE BENCHTOP PUMPING SYSTEM THAT MEETS THE REQUIREMENTS.