Summary

Description

NASA is seeking electric propulsion systems capable of producing up to 20mN thrust, input power up to 1000W and specific impulse ranging from 1600-3500 seconds. The target mass is 1kg for the thruster and 2kg for the power processor unit (PPU). The proposed system will be based on a variant of our low power HET family, the NASA in-situ channel replacement technology for thruster life extension, and a simplified PPU based on our patented multi-functional single converter PPU. In Phase I Busek proposes to develop subsystem designs for the thruster/cathode, PPU and XFS and demonstrate through integrated testing a new power processing architecture that replaces the four main DC-DC converters of a typical PPU with a single multi-functional converter. A major activity of the Phase 1 effort will be the design, fabrication and test of a breadboard version of the multi-functional converter using our high efficiency power converter topology. In Phase II we will design and build engineering prototypes of each subsystem and conduct a TRL 6 integrated system demonstration. At the conclusion of the program the system will be delivered to GRC for extended duration testing in NASA facilities.

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The proposed project is complimentary and directly beneficial to NASA's Safe and Efficient Surface Operations (SESO) research. NASA has previously developed a modular architecture for testing airport control concepts and algorithms within the Surface Management System (SMS). However, SMS currently uses live or pre-recorded surveillance data and, therefore, must be connected to a separate simulation environment. We will develop a self-contained, fast-time SMS simulation environment by incorporating an aircraft taxi model. The proposed stand-alone platform would complement NASA's current SMS-ATG environment by providing a fast-time simulation capability that uses the desired SMS plug-in architecture. We will also develop and integrate within the SMS simulation departure scheduling and taxi planning algorithms. These algorithms will supplement NASA's existing work and be independent of external optimization solvers. Lastly, the project will apply the fast-time simulation and integrated planning algorithms to study JFK airport surface traffic management under regular and off-nominal conditions, studies that complement NASA's research. JFK was chosen because of its complex geometry and traffic. We have received permission from the FAA to use JFK data, which is already available to Mosaic ATM as part of our FAA work.

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Based on our success in developing the world first commercial 10 W femtosecond fiber laser system and our leading technology development in ultrashort pulsed fiber laser and nonlinear fiber optics, PolarOnyx proposes, for the first time, a compact all fiber based high power mid-IR OFC source and sensor system. The laser is a specialty fiber based MOPA incorporating our proprietary technology of pulse shaping, spectral shaping and polarization shaping in generation mid-IR pump source and supercontinuum generation. A tabletop experiment will be demonstrated in Phase I time frame for proof of the concept. A hardware will be delivered in Phase II.

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In phase I of the SBIR program, LEEOAT Company will develop, simulate, fabricate and test high-temperature piezoelectric miniature sensors (up to 800<SUP>o</SUP>C), for physical and geophysical measurements of pressure, force, acceleration and vibration on the surface of Venus and other planets. LEEOAT Company efforts will be focused on achieving high figure-of-merit sensors, that can in the long term reliably operate on the surface of Venus. Additionally, we will innovate the technology for the readout and communication of the measured data at shielded relay stations with intermediate temperatures.

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In Phase II SPEC will design, fabricate and flight test a state-of-the-art combined cloud particle probe called the Hawkeye. Hawkeye is the culmination of two decades of innovative instrument development at SPEC. The new probe will measure the size distribution of cloud and precipitation particles, provide high-resolution (2.3 micron pixel) images of cloud particles and remove artifacts from ice particle shattering. This will be accomplished by eclectic combination of technology developed in three existing SPEC optical cloud particle probes: 1) A fast FSSP, that measures size distributions from 1 to 50 microns and records individual particle statistics and remove shattered particles using inter-arrival times, 2) a cloud particle imager (CPI) with upgraded imagery capable of recording up to 500 frames per second, and 3) a 2D-S (Stereo) probe that is configured with one channel to provide full-view images of particles from 10 microns to 1.28 mm, and a second channel configured to provide full-view images of particles from 50 microns to 6.4 mm. Thus, using particle dimensions along the direction of flight will produce particle size distributions from 1 micron to several cm. Hawkeye will be designed for installation and autonomous (unattended) operation on NASA research aircraft, including the Global Hawk unmanned aerial system (UAS), and DC-8, WB-57F and ER-2 piloted research aircraft. Hawkeye will provide vastly improved measurements of particle and precipitation size distributions, particle shape, extinction coefficient, effective particle radius, ice water content and equivalent radar reflectivity. Hawkeye will be ready for installation on NASA aircraft for the upcoming ACE and GPM decadal missions, which are aimed at measurements of the effects of aerosols, clouds and precipitation on global climate change.

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Nuvotronics has developed and optimized the PolyStrata<SUP>TM</SUP> process for the fabrication of intricate microwave and millimeter-wave devices. These devices have primarily been rectangular coaxial transmission lines, although rectangular waveguide and other structures have also been demonstrated. Intricate devices have been demonstrated with insertion loss 5 to 10 times lower than traditional planar circuits; isolation better than 60dB for lines that share separating walls; multiple levels of densely-packed coaxial circuits; and low-parasitic attachment to active devices and traditional circuit boards. In this Phase I project, Nuvotronics is proposing to develop high density low-loss millimeter backplane circuits to package and interconnect components of future NASA millimeter wave (MMW) radars. The significance of the innovation primarily lies in three areas: reduction of system size, weight and loss in MMW radars. The PolyStrata technology is a batch manufacturing process, providing economies of scale and cost reduction for higher volumes, in addition to flexibility in design for various frequencies of interest. Nuvotronics will design and test select Polystrata interconnects at MMW frequencies of interest, with particular attention to performance over temperature and survivability to launch conditions. The result of the Phase I research will prove the feasibilty of utlizing the Polystrata MMW backplane technology in future NASA missions, and provide the foundation for full scale development, testing, and prototype delivery during the Phase II project.

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AlGaN/GaN MMICs on SiC substrates will be utilized to achieve Power Added Efficiencies (PAE) in excess of 60%. These wide band-gap solid-state semiconductors will be used in novel Power Amplifier (PA) topologies such as Current Mode Class D (CMCD) and Class J. The power output goal of a single X-band PA module is 50W, and the power output goal of the Ka-band PA module is 10W. In turn, these power modules will be combined using novel combiner topologies including but not limited waveguide and radial power combiners in order to achieve the high power goal of 1kW at X-Band and greater than150W at Ka-band. Phase I will consist of choosing the devices sizes and topologies for the PA modules, and performing extensive modeling and simulation, especially for the large signal non-linear operation with harmonic terminations required to achieve the high efficiency goals. In addition, various power combiner configurations will be simulated using 2.5D and 3D electromagnetic field solvers. The power combining strategies will be evaluated for overall system efficiency, size, and weight trade-offs.

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Description

In Phase I, NP Photonics has achieved 1.2 kW peak power for 105 ns fiber laser pulses, and successfully demonstrated the feasibility to produce monolithic high SBS threshold narrow linewidth fiber amplifiers for all fiber-based laser transmitters ideally suited to NASA's active remote sensing spectroscopy. In Phase II, NP Photonics proposes to develop prototypes or products of the high SBS-threshold, Single-Mode (SM), polarization maintaining (PM), high power amplifiers operating with sub-microsecond pulses and transform-limited linewidth. This is based on the successful demonstrations in Phase I by using NP's proprietary patented large core SM PM highly Er/Yb co-doped phosphate glass fibers. Furthermore, in order to push the SBS threshold to the 100s kW level and to demonstrate even higher SBS threshold and improved conversion efficiency for 100-500 ns transform-limited fiber laser pulses, a new large core SM PM photonic crystal phosphate fiber 100/400 will be designed and fabricated in Phase II. It will be used to build the 3rd power amplifier stage in order to offer prototype/product services by achieving 10s kW peak power and 5-mJ pulse energy free of SBS effects. This will more fully enable NASA's active remote sensing with fiber laser pulses at 765 nm by using NP's Single Mode phosphate fiber amplifiers.

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A need exists for analyzers that can measure trace contaminants in air on board spacecraft. Toxic gas buildup can endanger the crew particularly during long missions. Some gases are generated by people and emitted through the skin or by exhalation. In addition to carbon dioxide, these anthropogenic gases include carbon monoxide, ammonia, hydrogen sulfide, acetaldehyde, and methanol. Plastics used in the spacecraft cabin can outgas formaldehyde, and heat exchangers can leak ammonia into breathing air. Overheating electronics can release carbon monoxide, hydrogen cyanide, hydrogen chloride and hydrogen fluoride. Thus, continuous air monitoring is required. Mesa Photonics proposes development of a highly miniaturized, highly efficient Fourier Transform (FT) spectrometer for continuous monitoring of contaminant air. The spectrometer will be able to detect a wide range of compounds with response times of about 30 seconds. Our approach combines several innovations that will lead to a rugged and reliable spectrometer capable of space-based operation and having a long shelf life. Spectrometers will be about the size of a lap-top computer, weigh about 4 kg, and consume about 10 W. Most target contaminants will be detectable at part-per-million or lower concentrations.

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An accurate prediction of aero-elastic effects depends on an accurate prediction of the unsteady aerodynamic forces. Perhaps the most difficult speed regime is transonic where the motion of the shock wave and its interaction with the boundary layer are dominant factors. In spite of over 40 years research into the computation of unsteady transonic aerodynamics there still appear to be areas where available technology is inadequate. A research axiom is that if a particular viewpoint fails to resolve an issue then the problem should be viewed differently. The research proposed here is to re-examine some issues in unsteady transonic aerodynamics using some recent theoretical developments. All aspects of unsteady transonic flow, including limit cycles and control strategies will be considered.

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This proposal describes the development of an inflatable and lightweight polymer-fabric structured pressure vessel designed for the containment of cryogenic fluids. Technology Applications, Inc. (TAI) in collaboration with the Thin Red Line Aerospace (TRLA) proposes to develop a cryogen tank design solution with fully determinate load paths that addresses the need for lightweight pressure containment at extremely low temperatures without the reliability issues that exist in composite tank structures. Ultra High Performance Vessel (UHPV) technology that has already been developed for many other applications will be extended for use into the cryogenic temperature operating range. The Phase I feasibility study encompasses the design and critical support elements for creating a robust lightweight cryogenic tank structure that meets NASA mission specifications. The Phase II program will involve fabricating and demonstrating the performance of a prototype cryogen tank based upon the inflatable UVHP architecture.

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Description

NASA sees an increasing role in the near future for small satellites in the 5-100 kg size range. A potentially disruptive technology, small satellites are being eyed as platforms for the rapid demonstration of new technologies and important science missions. Currently, small satellite platforms struggle to balance the three critical tasks of (1) collecting enough power, (2) acquiring data and (3) downlinking that data to ground stations in a way that maximizes mission return. For these small platforms, which usually do not benefit from steer-able solar arrays or gimbaled antennas and instruments, optimally balancing these three tasks strongly depends on the satellite's attitude control agility. Spacecraft agility has to do with rapid retargeting, fast transient settling and low jitter pointing control. Dr. Bong Wie, renowned spacecraft attitude control expert and Professor of Aerospace Engineering at the Iowa State University, has stated that ultimately the "measure of an agile satellite attitude control system is its ability to collect the maximum data from an area on the Earth that is rich in data-collection opportunities". A logical corollary following from this statement would be that to maximize satellite data-collection, system designers should look to increase the satellite's agility. Furthermore, in addition to data-collection, the other two critical tasks of power collection and data downlink are also maximized as agility is increased. Honeybee Robotics proposes to develop a low cost, high torque and low jitter satellite attitude control actuator derived from its Tiny Operationally Responsive CMG (TORC) design. This derivative product would combine two TORC units into a single scissored-pair configuration with SPA compatible interface. The result, TORC-SP, would be an actuator with the simple control interface of a reaction wheel that offers 1-2 orders of magnitude more torque per unit mass at drastically less power than a reaction wheel.

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Makel Engineering, Inc. (MEI) and the Ohio State University (OSU) propose to develop high sensitivity, miniaturized and in-situ operated gas sensors for the real time monitoring of chemical composition of turbine engine combustors and/or exhaust streams for real-time, in-flight propulsion system measurements to improve NASA's aeronautical flight test capabilities. Gas microsensor arrays developed by MEI, OSU and our technical development partners including NASA have been demonstrated for ground test usage to quantify composition of critical constituents in turbine engine exhaust products, e.g., CO, CO2, NOx, O2, HC (unburned hydrocarbons) and H2. These sensor systems provide the basis for the proposed NASA SBIR effort, which will also leverage development of packaging for extractive emissions testing developed for the DoD with support from NASA researchers.

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The objective of the Phase I is to develop, demonstrate and test novel instrumentation based on ultrasensitive laser absorption spectroscopy for sensitive real-time measurements of several important parameters for monitoring and control of oxygen production facilities and for analyses of lunar surface resources. The instrumentation will provide measurements of multiple trace gases and impurities on the lunar surface with a speed, accuracy and sensitivity not possible with current instrumentation.

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This proposal addresses the need for an antenna technology platform that meets the requirements of high-performance materials, exacting dimensional tolerances, and the geometrical design freedom to enable planar antenna array technologies for frequencies greater than 90GHz. The PolyStrata fabrication technology, being developed at Nuvotronics, LCC, Blacksburg, VA., is capable of meeting or exceeding all of the requirements outlined to be a solution for these frequencies. Air-filled copper rectangular coaxial transmission lines are fabricated using a photolithographically defined layer-by-layer process. The resulting transmission lines are extremely broadband, low-dispersion, high-isolation, and low loss compared to other forms of planar transmission lines. These lines are smaller than rectangular waveguides because the transverse cross-sections of the lines are not resonant. Phase II of this work will include the design, fabrication and characterization of prototypes that will enable PolyStrata-based frequency-scanned antenna-array operating from 140-160GHz with +/-16 degree beam steering, a beamwidth of 0.5 degrees and 400MHz per beam bandwidth. An antenna array with this performance would require roughly 24cm by 24cm. This is possible using 4 sub-arrays that each are fabricated on a single wafer and then tied together to achieve the overall system performance. We will develop and deliver prototypes that will be smaller versions of this, but demonstrate all the necessary aspects of the system including the feed network, the antennas, the tiling of subarrays and the connection to the outside world. The approach will offer a high-yield, cost effective product that will meet the NASA needs.

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The objectives of this Phase II project are to develop InGaN photovoltaic cells for high temperature and/or high radiation environments to TRL 4 and to define the development path for the technology to TRL 5 and beyond. The project will include theoretical and experimental refinement of device structures produced in the Phase I, as well as modeling and optimization of solar cell device processing. The devices will be tested under concentrated AM0 sunlight, at temperatures from 100:C to 250:C, and after exposure to ionizing radiation. The results are expected to further verify that InGaN can be used for high temperature / high radiation capable solar cells in NASA space missions.

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We propose to develop and commercialize a new type of low-stress iridium (Ir) X-ray mirror coating technology that can be used for the construction of high-resolution X-ray telescopes comprising thin-shell mirror substrates, such as the Flight Mirror Array (FMA) currently being developed for the IXO mission. The urgent need for low-stress Ir coating technology is driven by the current limitations on telescope angular resolution resulting from substrate distortions caused by conventional reflective Ir coatings that typically have very high stress. In particular, we have measured film stresses in excess of 4 GPa in the case of Ir films deposited by conventional magnetron sputtering. It is thought that the distortions in the thin glass mirror shells (such as those proposed for the IXO FMA) resulting from such extremely large coating stresses presently make the largest contribution to the telescope imaging error budget, of order 10 arcsec or more. Consequently, it will be difficult, if not impossible, to meet the imaging requirements of IXO, or other high-resolution X-ray missions in the future that use thin-shell mirror technology, unless high-quality Ir coatings having significantly lower stresses can be developed. The development of such coatings is precisely the aim of our proposal. Specifically, building on our successful Phase I effort, we propose to complete the development of low-stress Ir/Cr bilayers, and also investigate the use of Ir/Ti bilayers. We also propose to investigate the properties single-layer Ir films, as well as Ir/Cr and Ir/Ti bilayers, prepared by reactive sputtering with nitrogen. Finally, we plan to transfer the low-stress Ir coating technology to our large, production-class sputtering system so that we can coat GSFC-supplied thin-shell mirror substrates and conclusively demonstrate reduced stress-driven substrate distortions.

Summary

Description

As the size of composite parts exceed that of even the largest autoclaves, new out-of-autoclave processes and materials are necessary to achieve the same level of performance as autoclave cured composites. Unfortunately, the quality of composites manufactured with current out-of-autoclave prepreg systems is limited by their short shelf-life at ambient conditions. The resin advancement, due to long lay-up times, commonly causes variations in fiber volume and higher void content in the cured structures. Also, current out-of-autoclave prepreg systems do not provide the same level of performance, especially damage tolerance, as many current autoclave cured prepreg systems. It is the objective of this work to develop a matrix and prepreg system for out-of-autoclave processing that has a year out-time at ambient conditions while also providing an excellent balance of mechanical properties and damage tolerance. As an additional functionality, the out-of-autoclave prepreg system will be developed to have inherent skin-core self-adhesive properties so that film adhesives are not required for designs with honeycomb cores. It is expected that the TRL will be 4 at the end of this Phase I program.

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Description

During Phase I, M4 Engineering integrated a prototype system into OpenMDAO, a NASA GRC open-source framework. This prototype system was a proof-of-concept that M4 physics based modules could be integrated in OpenMDAO. The results generated in OpenMDAO compared well to the results generated in another framework, ModelCenter. Phase II will be a demonstration of enhanced system functionality with the integration of additional modules and design tools. The integrated objects will perform discipline-specific analysis across multiple flight regimes at varying levels of fidelity. The process will also deliver system-level, multi-objective optimization. Phase II will also showcase a refined system architecture that allows the system to be less customized to a specific configuration (i.e., system and configuration separation) as well as additional example problems. By delivering a capable and validated MDAO system along with a set of example applications to be used as a template for future users, this work will greatly expand NASA's high-fidelity, physics based MDAO capabilities and enable the design of revolutionary vehicles in a cost effective manner. This proposed work compliments M4 Engineering's expertise in developing modeling and simulation toolsets that solve relevant subsonic, supersonic, and hypersonic demonstration applications.

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Description

A priority in Environmental Control and Life Support systems for extended space missions is to recover and process wastewater to provide potable water for crew consumption and oxygen generation. Total organic carbon (TOC) indicates the overall quality of reclaimed and stored water and their suitability for crew consumption by indicating the potential presence of hazardous chemicals. For extended missions, water monitoring requires reliable, real-time, online sensors, with limited or no need for resupplied chemicals, and low equivalent system mass (ESM). The goal of this project is to develop a reliable, compact, flight-qualifiable, microgravity-compatible, TOC analyzer (TOCA) for online, real-time water monitoring with an operational lifetime of 5 years with no need to resupply chemicals or water. Key components include an electrochemical unit that eliminates the need to resupply or store chemicals, an effective oxidation processor for TOC conversion to carbon dioxide, a compact, stable inorganic carbon sensing unit, and mesofluidic design for reduced ESM. During Phase I, Lynntech successfully demonstrated the feasibility of the proposed system by designing, fabricating, and testing both the critical components and an integrated breadboard TOCA. During Phase II, an optimized, reliable, compact, flight-qualifiable, microgravity-compatible TOCA prototype will be designed, fabricated, tested, and delivered to NASA.

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The objective of the Phase I is to develop, demonstrate and test a novel instrument based on laser absorption diagnostics for fast, in situ measurements of important parameters (static gas temperature, bulk gas velocity, and gas concentration) in the high speed flows typical in NASA propulsion test facilities. In addition, the instrument will be easy to move (translate) during operation and thus allow measurements at different locations during a test run.

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Description

Cryogenic fluid transfer components using single crystal piezoelectric actuators are proposed to enable low thermal mass, minimal heat leak, low power consumption and fast response for cryogenic fluid transfer and handling systems to support NASA Lunar Lander, Ground Operations, Ares, and Lunar Surface Systems programs. Single crystal piezoelectrics are attractive because they exhibit 3 to 5 times the strain as conventional piezoelectric ceramics, have very low strain hysteresis, and retain excellent piezoelectric performance at cryogenic temperatures. Single crystal piezoelectric actuators including flextensional actuators and piezomotors were developed in Phase I and incorporated into cryogenic valves. The prototyped piezoelectric cryogenic valves were tested showing excellent flow control performance at temperature ranged from room temperature to liquid nitrogen temperature and pressure ranged from 50 psi to 3000 psi. In Phase II PMN-PT single crystal flextensional actuators and piezomotors design, fabrication and integration into cryogenic valves will be optimized, reliability of these piezoelectric cryogenic valves and actuators will be investigated. These advanced cryogenic actuators also hold promise for shape, motion and force controls in NASA, DOD and industrial applications.

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Description

The Next Generation Air Transportation System (NextGen) brings significant advancements to the current management of the National Airspace (NAS). These fundamental changes have significant implications for safety and security, which, in turn, require new, more flexible techniques for the verification and validation of complex, software-intensive systems and systems of systems. To address this need, Barron Associates will develop a demonstration sense-and- avoid application, representative of the kinds of new systems that are possible in NextGen, and a safety case arguing that it is safe to operate in the NAS. The safety case will rely on run-time assurance and formal methods as evidence to support its claims. Run-time assurance continuously monitors system-level safety properties for impending violations to diagnose software faults and allows a simpler, high-criticality reversionary function to provide assurance for a more complex software function; formal methods provide strong design-time assurance of correctness for software that must operate at the highest levels of criticality. A safety-case-based approach citing these two strategies as evidence offers significant cost savings for similar or higher levels of assurance as compared to traditional, process-based approaches.

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Description

FAA predicts that air traffic will double or even triple by 2025 and unless solutions that enable improvements in the use of airspace can be developed and implemented, significant airspace congestion will occur. Advancements in aircraft capabilities via new technologies can enable aircraft to operate more efficiently in the NAS and to operate safely in areas previously restricted. AeroTech proposes to enhance the assessment of Performance Based Operations (PBO) by implementing the Autonomous Weather Hazard Avoidance Model (AWHAM) into ATM simulations providing autonomous guidance for aircraft thru hazardous weather regions. PBO and traffic flow schemes can be assessed for any scenario by varying the detection capabilities of simulation aircraft, regulations, and/or policies, and examining deviation decisions, flight paths, safety impacts, and NAS throughput. Phase II will involve implementing the hazard avoidance model into an operational simulation and performing a proof of concept study that will establish and quantify the benefits of aircraft equipped with particular hazard detection capabilities from the perspective of an aircraft operator. AeroTech also proposes to develop the structure and architecture for integrating the AWHAM with the Autonomous Operations Planner, which provides pilots assistance in determining flight paths that comply with safety constraints and reduce operational costs.

Summary

Description

The Low Energy Mission Planning Toolbox is designed to significantly reduce the resources and time spent on designing missions in multi-body gravitational environments. It provides a means for quickly planning low energy missions that take advantage of multi-body gravitational environments. The high-speed, efficient process will allow rapid comparison between low energy methods (e.g. ballistic lunar capture transfer trajectories) and their direct counterparts (e.g. Hohmann transfers). The tools leverage recent research on low energy mission design methods to produce algorithms that are stable, hold potential for automation in certain situations, and can be easily interfaced with the NASA open source mission planing tool GMAT.