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Southwest Sciences proposed the development of a rugged, compact, and automated instrument for the high sensitivity measurement of tropospheric carbon monoxide (CO). The application of recently developed room temperature vertical cavity diode lasers operating near 2300 nm permits the development of sensitive and rugged instrumentation for measurement of atmospheric CO with high precision. Phase I efforts will address the feasibility of measuring CO to a precision of 10 parts-per-billion or better over a range of tropospheric temperatures, pressures, and humidities. Phase II will emphasize development of prototype instrumentation for field testing.

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Many large-scale numerical simulations can be broken down into common mathematical routines. While the applications may differ, the need to perform functions such as matrix solves, Fourier transforms, or eigenvalue analysis routinely arise. Consequently, targeting fast, efficient implementations of these methods will benefit a large number of applications. Graphics Processing Units (GPUs) are emerging as an attractive platform to perform these types of simulations. There FLOPS/Watt and FLOPS/dollar figures are far below competing alternatives. In previous work, EM Photonics has implemented dense matrix solvers using a hybrid GPU/multicore microprocessor approach. This has shown the ability to significantly outperform either platform when used independently. In this project, we will develop a complimentary library focused on performing routines on sparse matrices. This will be extremely valuable to a wide set of users including those doing finite-element analysis and computational fluid dynamics. Using GPUs, users are able to build single workstations with an excess of four teraFLOPS of computational power as well as create large, high-performance computing systems that are efficient in terms of both cost and power. By leveraging libraries such as the ones we will develop for this project, the user is shielded from the intricacies of GPU programming while still able to access their computational performance.

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Global Science & Technology, Inc. (GST) proposes to investigate information processing and delivery technologies to provide near-real-time Web-based access to satellite data from the National Polar-Orbiting Environmental Satellite System (NPOESS) Preparatory Project (NPP). We will investigate computing hardware and software requirements for serving data products acquired through NPP Direct Broadcast to modelers, forecasters, and decision-makers, via industry-standard Web services, within minutes of sensor acquisition. This effort will fill in a notable gap in the transition between current observational systems and the future NPOESS (National Polar-Orbiting Environmental Satellite System.

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Deployable Space Systems (DSS), in partnership with ATK Space and EMCORE, will focus the proposed SBIR program on the optimization and design development of the most promising advanced space photovoltaic subsystem now available: EMCORE's ultra-thin 33% BOL-efficient Inverted Metamorphic Multijunction (IMM) solar cell that is interconnected and integrated onto an advanced flexible blanket; specifically for implementation on the lightest solar array structural system currently in use, ATK's UltraFlex. The proposed innovative and synergistic solutions will produce a near-term, low-risk solar array system that provides breakthrough performance in terms of highest specific power (>500 W/kg BOL), light weight, scalability to large (>15 kW) wing sizes, high deployed stiffness, high deployed strength, compact stowage volume (>50 kW/m3 BOL), high voltage operation capability, reliability, affordability, and rapid commercial readiness. The proposed effort will focus on increasing the design fidelity (TRL) of promising IMM-integrated onto UltraFlex blanket solutions configured to meet key high-voltage SEP / deep space science mission requirements. The development of feasible ultra-lightweight integrated IMM PV UltraFlex solar array technology will enable future missions, including near-to-medium term NASA Discovery and New Frontiers-class interplanetary, planetary orbital, comet rendezvous and Solar Electric Propulsion (SEP) science missions as well as future Orion/CEV Lunar sortie missions.

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The availability of small, low power atomic clocks is now a reality for ground-based and airborne navigation systems. Kernco's Low Power Precision Time Source (LPPTS) is based on Coherent Population Trapping (CPT) technology. Several of these units were recently delivered to the Air Force Research Laboratory (AFRL) at Kirtland Air Force Base and have demonstrated the performance and robustness of the matured design. Since CPT technology has been demonstrated as a viable solution to providing low-power, high-performance atomic clocks, it makes sense to explore the potential for deploying these units for space operations. Size, Weight and Power (SWAP) rank among the highest of the critical parameters in the design and fabrication process of a satellite system. However, the single most critical parameter is perhaps the radiation tolerance of any electronic system. By using the LPPTS design as a point of departure, Kernco proposes to implement a radiation tolerant design of its CPT-Based Atomic Clock to satisfy the need for Low Cost, High Accuracy Timing Signals for small satellite flight opportunities. This SBIR Phase I proposal will focus on the design of a Radiation Tolerant Low Power Precision Time Source (LPPTS-R) suitable for integration into the Space Plug-and-Play Architecture (SPA).

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Vescent Photonics proposes to design and build significantly improved laser frequency locking and control systems that will be suitable for ASCENDS and other NASA sensing needs. Precision laser frequency control (absolute frequency to better than 1 MHz with rapid tuning over 10's to 100's of GHz) for lasers in both the 1.57 CO2 overtone region for direct CO2 detection and around 1.53 m, which may be doubled to reach the O2 A-band spectral-trough feature at 764.7 nm, will be developed and provided. The laser locking and control will employ either calibrated sweep techniques or high-speed frequency offset phase locking. Absolute wavelength references will be maintained to better than 2 MHz via either direct locking to a CO2 line or locking to the HCN R(22) line at 1529.38 nm, which when doubled is directly at the 764.7 nm O2 spectral trough feature. Prototype locking and control systems will be delivered at the end of phase I (TRL will transition from 4 to 5 during phase I) and a complete, ready to use laser system will be delivered at the end of phase II (TRL 6 or 7 at end of phase II).

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One of the CO2 reduction technologies currently being developed by NASA is the CO2 and Moisture Removal Amine Swing-bed System (CAMRAS). One of the disadvantages of the CAMRAS for long duration missions is that it removes moisture in addition to CO2. One way to minimize the water loss from the atmosphere, yet still be able to implement the highly desirable CO2 removal function of the CAMRAS, is to implement a membrane water exchanger, or recuperator, at the inlet of the CAMRAS system. The water exchanger passes humidified, CO2 laden air on one side of a membrane. The water vapor passes through the membrane leaving the CO2 laden air to be treated by the amine system. The air returning from the amine system is dry and CO2 free, as its remaining moisture and CO2 have been absorbed by the amine beads. This dry air passes on the second side of the membrane. Its low dew point provides the driving force for the moisture that passes through from the inlet stream. The CO2 free air becomes re-humidified, thus conserving water in the overall system mass balance. The membrane is highly selective for water, and not for CO2. The amount of carbon dioxide passing through the membrane and returning to the cabin is negligible; therefore the functionality of the CAMRAS as a CO2 removal system will not be impeded. The improvement over the current state-of-the-art is a reduction in power and the elimination of moving parts.

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NASA's Vision for Space Exploration advocates a return to the moon and involves a plan of using the moon as a base of for missions to other planets. Early return missions to the moon will involve lunar exploration with robotic spacecrafts with instrumental payloads for scientific measurements of lunar surface features such as rocks, soil, and minerals. These instrument payloads will be helpful in identifying lunar resources that can be used in establishing extended human presence. Raman spectroscopy has been actively investigated as a lunar as well as a Mars surface robotic investigative tool for minerals. Current Raman instruments for space exploration utilize a single excitation wavelength, with a laser in the near-infrared (IR) to minimize fluorescence background. However, even with the near-IR Raman excitation, background emissions such as fluorescence, F-center luminescence, and blackbody emission can still be a problem. The goal of this project is to employ a dual excitation (visible and near-IR lasers) Raman instrument to minimize background emission. To achieve this goal, a dual excitation wavelength fiber optically coupled Raman probe head and a compact wide spectral range echelle spectrograph will be developed.

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Maxion Technologies and Physical Sciences Inc. (PSI) propose to jointly develop a compact, rugged, highly reliable, and autonomous sensor for in-situ monitoring of CO in spacecraft crew areas for fire warning. Our innovation is to combine a custom fabricated Quantum Cascade Laser (QCL) with PSI's proprietary single board electronics package that incorporates both a high sensitivity optical detection technique and all system control functions, to create a laser spectrometer for CO. The advent of QCLs enables the development of a very compact and highly sensitive monitor. This technical approach will result in a sensor that has the requisite dynamic range of 1 to 500 ppmv with a precision of 1 ppmv CO, in a physically robust and compact package. The Phase I program will demonstrate the feasibility of a breadboard sensor and create a detailed conceptual design for an advanced prototype. The TRL at the beginning of Phase I is level 2 and the TRL at the end of Phase I will be level 4. The Phase II program will fabricate a prototype that can be demonstrated at a relevant simulator. The TRL at the end of Phase II will be level 6. Successful completion of Phases I and II will result in a rigorously validated prototype sensor that can monitor ambient CO with high speed and precision. The sensor architecture can be easily modified to measure other species.

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ORBITEC proposes to develop the Advanced Carbothermal Electric (ACE) reactor to efficiently extract oxygen from lunar regolith. Unlike state-of-the-art carbothermal reactors that use concentrated solar energy or laser energy to heat the regolith, the ACE reactor uses new innovative electric resistant elements to heat the regolith. The ACE reactor eliminates the problems encountered with traditional carbothermal hot-wall reactors and offers significant advantages over current carbothermal reactor approaches. By eliminating the need for a solar energy collection and delivery system, the ACE reactor offers a significantly lowers system mass and eliminates the need to keep optical surfaces clean. The ACE reactor approach can also produce the processed regolith in a form that can be directly used as a structural material. This proposal directly meets the needs of Subtopic X3.01, specifically "Advanced reactor concepts for carbothermal reduction or molten oxide electrolysis." The proposed Phase 1 Effort will define requirements, develop the heating elements, perform performance tests in a sub-scale ACE reactor, and create a preliminary design for a prototype ACE reactor that would be built and tested in Phase 2. The Phase 2 Effort will include fabrication and performance testing of the prototype ACE reactor before it is delivered to NASA.

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In this Phase I SBIR project, Synkera proposes to develop and commercialize solid-state neutron detectors of a unique architecture that will enable sensor modules for a variety of operating environment. The neutron detectors are based around nanoporous anodic aluminum oxide, and will be fabricated using a combination of gas-phase and solution-based deposition methods. The detectors will incorporate a schottky junction surrounding a neutron-conversion material. As part of this development effort we will develop the deposition methods required for the various components of the detector and use modeling to evaluate the feasibility of the design. Our solid-state neutron detectors are expected to have much larger neutron sensitivity toward fast neutrons than conventional detectors at a lower weight and much lower power requirements. These features will enable solid state neutron spectrometers meeting all the NASA requirements on weight, volume, and power. We anticipate that large detector areas can be manufactured at costs below those of conventional neutron detectors.

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Today, memory and payload processing systems for space applications are typically designed for a specific application for a specific mission. Many of these systems do not employ a commercial standard which adversely affects the development costs, risks, and schedule while minimizing effective reuse of capabilities. Traditional commercial standards such as PCI are limited in bandwidth and reliability and do not meet the needs of advanced space payloads. New standards, like VPX, do show promise. VPX supports module to module datarates of 10 Gbps. VPX supports multiple switch architecture, so redundancy is supported. With newer large capacity memory components, a high capacity modular architecture is achievable which opens the door for adoption of a commercial standard for space payload and memory systems.

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FTT proposes development of a magnetically actuated dynamic seal. Dynamic seals are used throughout the turbopump in high-performance, pump-fed, liquid rocket engines for a variety of purposes. The most common applications are in the lift-off seal (LOS), inter-propellant seal (IPS), and balance piston seals ? high-pressure orifice (HPO), low-pressure orifice (LPO), and inner diameter impeller shroud seal (eye seal). The system solution for conventional seals represents a compromise between the turbopump mechanical design, primarily flowpath, and secondary flowpath design that results in increased leakage, increased seal wear, and reduced balance piston load capacity that reduces performance, throttle-ability, thrust-to-weight, reliability, and operability. The magnetically actuated seal eliminates this compromise and provides significant improvement in performance, throttle-ability, thrust-to-weight, reliability, and operability. Phase 1 will advance the technology from TRL 2 to 3. Phase 2 will advance the technology from TRL 3 to 6. The technology is applicable to booster engines, in-space engines, and lunar engines.

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Design, manufacture and test a flat segmented mirror made of optical grade AlBeMet 162 material and fusion bonded through the use of E Beam welding to demonstrate the feasability of manufacturing much larger segmented optics that perform as monlithic optics.

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Flight deck systems, like many safety critical systems, often involve complex interactions between multiple human operators, automated subsystems, and physical structures. Individual components are extensively evaluated and are often redundantly deployed, so catastrophic failures predominately arise not through component failure but as the result of a sequence of failures that cascade because of some unforeseen combination of off-nominal conditions. Such sequences may involve human operators, control algorithms, software implementations, physical structures, and other components of the system. Analyzing the potential for these failure scenarios is extremely difficult, not only because of the inherent complexity of such systems but also because of the multidisciplinary nature of the system itself. While many development tools exist to conduct deep analyses within individual disciplines, there is a lack of tools available for deep analysis of complex multidisciplinary designs. The goal of this proposed research project is thus to create a new class of development tool that allows designers to specify, design, integrate, and conduct analyses of complex systems across disciplinary boundaries. Through this new tool, the dynamic interactions between system components in the presence of off-nominal conditions can be explored to uncover systemic vulnerabilities, precursory conditions, and likely outcomes.

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This SBIR Phase I proposal describes a method of fabrication of far IR and THZ range multilayer metal-mesh filters. This type of filter consists of alternative layers of polymer material and structured thin metal films. The proposed filters are radiation hard and lightweight. The fabrication process proposed will increase the availability of such filters and expand the market while reducing the cost and delivery time. In Phase I, it is proposed to develop a process for incorporating the dielectric film in between the metal mesh and to maintain the mechanical integrity over the wide temperature range (from below 4K to 300K). In Phase II, optimized filters will be fabricated and their properties compared with design predictions. Phase III will involve product design, fabricating filter structures to meet customers' physical as well as optical needs, and marketing and sales investments.

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The objective of this proposal is to create new gas chromatographs (GCs) for contaminant monitoring in spacecraft air that do not require any reagents or special carrier gases. Under DARPA support, Cbana has created a new class of microGCs that are smaller than ever before and yet show performance similar to those of full scale commercial GCs. In the proposed work we will redesign the GCs so that they can use air as a carrier gas. Key to the device is a very low pressure drop adsorbent bed that can capture the contaminants for analysis and produce a very pure air stream as a carrier gas. Phase I tests will be performed to optimize the performance of the adsorption bed and to verify that the GC columns work with air. The result will lead to a cabin air monitoring system that can detect all of the contaminants listed in the NASA report NASA report "Spacecraft Maximum Allowable Concentrations For Airborne Contaminants" and not require special carrier gases or reagents.

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The proposed Phase 1 program will demonstrate that sapphire viewports are feasible for use in Venus probes. TvU's commercial viewport products have demonstrated that the pressure and temperature constraints will be met, while the use of materials appropriate to the atmospheric conditions will satisfy the overall physical constraints. The viewport system will be shown to be adaptable to overall NASA use constraints. A prototype viewport system will be designed for fabrication and testing, and application in Phase 2. Task work will detail the design of both the window and the fixture, test a sample, and emphasize the most important aspects of the design and specification. Phase 1 work will lay out the foundation for a Phase 2 program that will integrate these viewports into the NASA Venus probe program.

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NASA Exploration vehicles require improved technologies for passive thermal insulation for zero boil-off of cryopropellants during extended LEO and lunar surface missions. Vehicles such as the Earth Departure Stage and Orion must be capable of multi-day orbital operation with minimal cryopropellant loss, and the Altair Lunar Lander must have minimal cryopropellant loss over a six month mission on the lunar surface. Quest Product Development, teaming with Ball Aerospace, proposes an innovative advanced insulation system, Wrapped-IMLI, which could provide high performance thermal insulation for cryogenic feed lines. Wrapped-IMLI is a multi-layer system using proprietary micromolded polymer spacers to precisely control layer spacing and reduce inter-layer heat conduction. IMLI versions of this concept, for cryotanks, have been proven with a measured thermal conductivity of 8.8*10-5 W/m-K, 37% lower heat leak than conventional MLI. Preliminary research indicates W-IMLI could provide excellent thermal insulation for cryo-feed lines. Propellant boil-off losses are directly influenced by the MLI, which is the biggest heat leak in cryogenic propellant storage. It is known that MLI insulation for cryogenic propellant feed lines is much less effective than MLI for tank insulation. A Ball Defense Program study indicates the heat leak through spiral-wrapped MLI into lines is up to 10 times worse per area than tank MLI. Better insulation for cryo-feed lines is an important enabling technology for NASA Exploration vehicles. In this Phase I project we would model, conduct a trade study on thermal requirements for NASA spacecraft cryogenic feed lines, design W-IMLI, fabricate a prototype and measure thermal performance.

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Many of the most challenging categories of propulsion system development are related to the prediction of interacting effects between the fluid loads, thermal loads, and the structural deflection. In practice, the interactions between technical disciplines are often not fully explored analytically, and the analysis in one discipline often uses a simplified representation of other disciplines as an input or boundary condition. For example, the fluid forces in an engine generate static and dynamic rotor deflection, but the forces themselves are dependent on the rotor position and its orbit. A typical design practice might involve predicting the fluid and thermal loads for various conditions and passing those estimates along for inclusion with the structural model. This practice ignores the interaction between the physical phenomena where the outcome of each analysis can be heavily dependent on the inputs (i.e., changes in flow due to deflection, changes in deflection due to fluid forces). Such a rigid design process also lacks the flexibility to employ multiple levels of fidelity in the analysis of each of the components. In this project, Mechanical Solutions, Inc. (MSI) proposes to extend two existing software tools to develop a design environment with both breadth (to cover multiple disciplines) and depth (to cover multiple levels of fidelity).

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Thermal analysis is increasingly used in thermal engineering of spacecrafts in every stage, including design, test, and ground-operation simulation. Current high-fidelity modeling and simulation tools are computationally prohibitive and not fully compatible to integrated, multi-physics (e.g., thermal-structural-optical) analysis of spacecrafts, particularly in a single model topology currently being pursued at NASA. NASA engineers are challenged with developing innovative reduction algorithms and models that enable rapid analysis while retaining adequate accuracy. To address this need, we propose to develop and demonstrate innovative Model Order Reduction (MOR) software to automatically generate nonlinear reduced thermal models for spacecraft analysis. The underlying principle is to project the original large models onto a characteristic, low-dimensional subspace (SVD or Krylov subspace), yielding reduced models with markedly low computational orders. In Phase I, a MOR engine encapsulating carefully selected algorithms, a reduced model solver, and a verification module, along with facile data export interfaces will be developed in an integrated software environment. Proof-of-concept will be established by broad case studies, in which reduced models will be analyzed and compared against large model analysis using CFDRC-developed multi-physics simulation tool CFD-ACE+ in terms of accuracy, speed, and resource use. Phase II will focus on enhancing the MOR engine, optimizing the software structure, and expanding interfaces to other NASA-relevant tools.

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We propose a microplate heat exchanger for cryogenic cooling systems used for continuous flow distributed cooling systems, large focal plane arrays, multiple cooling locations, and very low vibration cooling systems. Any DC cryogenic flow system such as turbo Brayton, Joule-Thomson (JT), or remote cooling applications require very high effectiveness heat exchangers to reduce input power. The parasitic loads from heat exchangers are a significant fraction of the overall load, and high effectiveness heat exchangers lead directly to improved system efficiencies across a broad range of cryogenic applications. Microplate heat exchangers have a demonstrated effectiveness over 98% (Marquardt, Cryocoolers 15). While performance is high, they will be difficult to use for larger cryogenic flow systems due to parasitic conduction losses inherent in the materials available for the manufacturing process. A material change will allow more compact heat exchangers with lower parasitic losses. Other limitations of the manufacturing process make yields low, and while it may be possible to push the effectiveness higher, it may be difficult to consistently produce high performing exchangers using the current approach. We propose a new bi-metal microplate heat exchanger which is unique in that it uses the manufacturing process to control critical heat exchanger dimensions that are inherently similar across all parts, allowing high effectiveness without the need for close inspection of every part and the low yield which results from hand inspection. We further include additional features within the flow channels that automatically balance the mass flows within the heat exchanger to push the effectiveness even higher. This is accomplished in the most compact cryogenic heat exchangers theoretically possible to build using parallel plate flow channels.

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Future manned space exploration missions will require space suits with capabilities beyond the current state of the art. Portable Life Support Systems for these future space suits are extremely challenging, since they must maintain healthy and comfortable conditions inside the suit for long-duration missions while minimizing weight and venting no consumables. We propose an innovative system for thermal and humidity control in a space suit that is simple, rugged, lightweight, and nonventing. In Phase I we will prove the feasibility of our approach by analysis and laboratory testing of a proof-of-concept unit to identify the optimum configuration. We will produce a conceptual design for a full-size system. In Phase II we will develop fabrication methods to produce a full-size prototype, then demonstrate operation in a prototypical environment.

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In Sub-topic X4.01, NASA has identified a need for advanced radiation-shielding materials and structures to protect humans from the hazards of galactic cosmic radiation (GCR) on long-duration lunar missions. The radiation species of greatest interest are light ions (particularly protons), heavy ions (such as iron-56) and neutrons. International Scientific Technologies, Inc., in conjunction with the College of William and Mary, proposes the development of lightweight, multi-layered, polymeric shielding against GCR. Phase I Technical Objectives include selection, design and fabrication of materials tailored to shield against hazardous radiation, and measurement and test of individual and layered materials using available radiation sources. The anticipated result of the Phase I and Phase II programs is the development of multi-layered shields with an outer layer of hydrogenous polymeric material for significant dose reduction of incident GCR ions and inner layers of polymeric composites containing additives chosen to moderate and absorb neutrons resulting from fragmentation of incoming heavy ions and to absorb short wavelength electromagnetic radiation resulting from the slowing of the GCR particles and capture of neutrons. The Technology Readiness Level (TRL) at the beginning of Phase I is 3. At the end of Phase I, the TRL will be 4 or higher.

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Trajectory-based operations constitute a key mechanism considered by the Joint Planning and Development Office (JPDO) for managing traffic in high-density or high-complexity airspace in the Next-Generation Air Transportation System (NextGen). With this concept applied to surface operations at major airports, NASA's NextGen-Airportal Project is exploring the use of surface 4-dimensional (4D) trajectories, which use required times of arrival (RTAs) at selected locations along the route. Observing these RTAs as constraints along the taxi route, the flight still has many degrees of freedom in adjusting its state profiles (i.e., position, velocity, etc. as functions of time) to achieve the timing constraints. This research will investigate whether and how these degrees of freedom in trajectory control may be used to achieve desirable behaviors for the taxi operations. Previous research has applied the trajectory control freedom to assure passenger comfort by keeping the accelerations and decelerations within pre-specified limits, and yet there is still untapped flexibility in designing the trajectories. The proposed research will explore this trajectory design problem to achieve additional desirable behaviors, beginning with the consideration of fuel burn, emissions, and noise. A flight-deck automation experimental prototype will provide the platform for simulating the designs, augmented by models developed to evaluate environmental benefits. The findings will benefit future designs of flight-deck automation systems, as well as tower automation systems which rely on accurate understanding of the flight deck's operational behaviors to plan efficient and safe operations for the entire surface traffic.