The EXA UMPPT Solar Panel Joiner/Adder Module is a sub-EPS module to connect up to four (4) independent solar panel and joins/adds their power yield. The module works irrespective of their orientation and state of illumination, providing a unified multiple power point track service.Unlike common MPPT modules, the EXA UMPPT module adds the power yield of all solar panels, not only the ones in full illumination or with the maximum power point, but all at once, providing the maximum power yield possible by the solar panel configuration, boosting the power production in orbit and securing the best possible positive power budget for the mission. It also provides telemetry output for each solar panel connected to the module.

As thin as 7 millimeters, the EXA BA0x High Capacity Battery Array is a family of power store/delivery devices designed to provide the highest energy density and redundancy for your cubesat mission

The EXA KRATOS 1U spacecraft bus is a 1-step CubeSat solution that allows developers to focus on their payload and mission: it includes everything needed for the spacecraft to work and is VTV tested, allowing developers to simply integrate their payload and fly.The KRATOS SCB is completely configurable. From a modest, standard CubeSat to a powerful SpaceTaxi in a 1U that can host up to 6 standard payload boards and 3 cameras delivering up to 100W of power, and LASER communications at 10Mbps, it offers satellite builders the ability to configure the system based on what they need to fly their payload.Specifically, the spacecraft bus includes:Onboard computer with pre-installed librariesSDR Radio with integrated power amplifierPowerful EPS with 4 power railsUMPPT Solar management coupled to a fast battery chargerDeployable Multifunction Solar ArraysAutomated deploy/release control to up to 4 devicesEmbedded monopole and dipole antennas from VHF to L bandEmbedded magnetorquersTemperature and sun sensors in all wallsADCS control with integrated Z axis magnetorquerHigh power batteriesRadiation hardened SSD storageLASER communications at 10Mbps minimumCustomers can add or subtract features and expand capabilities accordingly to their project budget. The core principle of the KRATOS 1U spacecraft bus is that customers focus on their mission, and EXA focuses on the spacecraft.KRATOS 1U spacecraft bus is shipped in a Pelican 1300 Case and includes:Full engineering supportTest reportsEUDP, ICDUN38.3, CoO, MSDS

The EXA SSA03 is a S-band patch antenna with high gain and a bandwidth of up to 30 MHz. The system is suitable for missions that need greater speed and/or bandwidth separation capabilities and great flexibility on the final frequencies selection.Integrated user selectable choice between LCHP and RHCP and center frequency choice between 2220 and 2260 MHz is available. The frequency can be requested within SSA03’s ample center frequency range after the approval from the telecommunication authority and at least 6 months of red tape time can be saved.

The EXA TITAN-1 is a 1U-sized power bank module built from 7 battery arrays designed to provide the highest energy capacity and redundancy: Its power capacity is 50 Whr per battery module, giving a total of 350 Whr. For missions from 3U CubeSats to microsatellites. TITAN enables your system to perform longer and better and pack as much power as a microsatellite configuration. All our batteries are fully customizable to your mission’s need in terms of output, cable, connectors or interfaces and options are available as integrated Carbon Nanotubes Thermal Transfer Bus (CN/TTB) shield which allows missions to reuse the spacecraft self-generated heat, and integrated thermal sensor. Availability: 6 to 8 weeks

The EXA ICEPS is designed to be the central operational heart of CubeSats, enabling modular use of higher performance hardware and features. ICEPS compresses the functions of many cards into a single, 25mm-thick system, using modularity for fully customizable hardware that can range from being simply an EPS or including a range of features.ICEPS can interface and work with any compatible USB hardware, but it is designed to optimally operate in conjunction with EXA-developed hardware, like BA03 Battery Arrays, DMSAs (Deployable Solar Panel), and SEAM/NEMEA shielding. ICEPS is also the system core of the EXA's KRATOS spacecraft bus, including all of these components. Although initially designed to handle requirements for a 1U CubeSat, ICEPS is ready and able to handle all these requirements for larger CubeSat missions.ICEPS is set to launch on IRVINE03 onboard the NASA ELaNa launch in Q4/2021, on IRVINE04 onboard ELaNA also in 2022, on K'OTO onboard HTV for Q3/2021, and onboard INSPIREFLY for 2022. It is also the system core of an upcoming lunar mission onboard the Astrobotic Peregrine Lander, set to land on the moon in Q3/2021.The central features of the system core include:Embedded laser communicationsIntegrated Epik Z2 OBC with 2 SDR radiosUSB and I2C busSSD storage up to 512GBAutomatic control of deployables100W capable EPS6-axis IMUITAR free productICEPS is delivered with:Full engineering supportTest reports and ICDInterface custom cablesChoice of aluminum spacers M2.5

The EXA DMSA/1 (Deployable Multifunction Solar Array for 1U) is the upgraded version of the latest DSA 1/A, it is EXA's entry level product of a family of deployable solar arrays based on artificial muscles for CubeSats in the range of 1U to 6U. The arrays fold into a panel attached to the CubeSat structure just as another solar panel and once in orbit it deploys to full extension, it includes deploy and release contact sensors and its own deploy control board.It includes embedded antennas that range from VHF to L band. The DMSA antennas are embedded in its structure as 2 monopoles or 1 dipole and they deploy with the solar array.The DMSA also has an embedded magnetorquer, sun and temperature sensors. It is possible to configure different solar cells like EXA low-cost solar cells or AzurSpace 3G-30 for very high-power missions. The maximum folded thickness is 6.25 mm for the 3-panel array.Every array is tested and qualified in EXA's facilities and it is shipped with full reports.

The EXA GCA01 is a one-stage, compact GNSS active patch antenna solution that works with GNSS cards and links to GPS, Galileo, BeiDou and GLONASS constellations. The antenna is suitable for space-grade GNSS devices to achieve good sensitivity across all bands in a small form factor.The active patch antenna, by means of a double resonance design, has a wide-band operation over GPS/GLONASS/Galielo/BeiDou systems from 1561MHz to 1606MHz. It includes a one-stage LNA and front-end SAW filter to reduce out of band noise.Main features:Flight heritage since 2018Active antenna, LNA integratedSAW filter integratedCustom choice of connectorsDesigned for LEO missions and requirementsManufactured according to NASA and ESA space standards and materialsFunctional, performance, thermal bake out and vibration tests provided w/documentationCompatible and compliant with standard deployers and CubeSat Standard

As thin as 7 millimetres thick, the EXA BA0x High Energy Density Battery Array is a family of power store/delivery devices designed to provide the highest energy capacity and redundancy: From a minimum of 22.2Whr to a maximum of 44.4Whr per bank. For missions like 1U Cubesats, the BA0x enables your system to perform longer and better and pack even more power than a 3U configuration, the double-sided arrays are user-configurable to output 3.7V or 7.4V. All our batteries are fully customizable to your mission’s need in terms of output, cable, connectors or interfaces and options are available as integrated Carbon Nanotubes Thermal Transfer Bus (CN/TTB) shield which allows missions to reuse the spacecraft self-generated heat, integrated MT01 Magnetorquer and integrated thermal sensor.

The EXA SSA01 is a wide bandwidth S-band antenna than can accommodate a bandwidth of up to 195 MHz for missions that need great speed and/or bandwidth separation capabilities and great flexibility on the final frequencies selection.SSA01 is designed to work between 2025 and 2120 MHz and 2200 and 2300 MHz without sacrificing gain. This provides flexibility for customers so they can minimize or avoid having to wait for the final bands and frequency approval. EXA's goal is to enable customers to accelerate their process of getting to space by reducing the typical bottleneck associated with obtaining approval from the relevant telecommunications authority. Customers can file for a frequency use within SSA01’s broad range, helping to potentially save 6 months in the approval process.Main features:Flight heritage since 2020Custom configurable choice of connectors and/or cablesDesigned for LEO missions and requirementsManufactured according to NASA and ESA space standards and materialsFunctional, performance, thermal bake out and vibration tests provided withdocumentationCompatible and compliant with standard deployers and CubeSat Standard

The EXA Deployable Multifunction Solar Array (DMSA) is designed for microsatellite missions. The array is available in configurations from 75W to 600W.It consists of an embedded magnetorquer, sun and temperature sensors. The arrays also include embedded antennas that range from VHF to L bands. These antennas are embedded in their structure as 2 monopoles or 1 dipole and are designed to deploy with the solar array.The arrays fold into a panel attached to the structure just as another solar panel and once in orbit it deploys to full extension, it also includes deploy and release contact sensors and its own deploy control board.

The EXA SSA02 is the power-amplified version of the SSA01 wide bandwidth S-band antenna than can accommodate a bandwidth of up to 195 MHz for missions that need great speed and/or bandwidth separation capabilities and great flexibility on the final frequencies selection.SSA02 is designed to work between 2025 and 2120 MHz and 2200 and 2300 MHz without sacrificing gain. This provides flexibility for customers so they can minimize or avoid having to wait for the final bands and frequency approval. EXA's goal is to enable customers to accelerate their process of getting to space by reducing the typical bottleneck associated with obtaining approval from the relevant telecommunications authority. Customers can file for a frequency use within SSA02’s broad range, helping to potentially save 6 months in the approval process.SSA02 enhances the link budget for missions through an onboard amplifier tied directly to the antenna, working alongside a RF switch chip that allows safe transceiver capability for the customer's radio. The total ERP delivered by the SSA02 is 34 dB allowing the use of very low power radios, thus saving power without sacrificing link budget. This also means that 2 radios can share the same antenna.Main features:Flight heritage since 2020ERP of 34 dBOn board RF-switch for safe transceiver capabilityAllows the use of very low power radiosAllows 2 radios to operate the same antennaCustom configurable choice of connectors and/or cablesDesigned for LEO missions and requirementsManufactured according to NASA and ESA space standards and materialsFunctional, performance, thermal bake out and vibration tests provided with documentationCompatible and compliant with standard deployers and CubeSat Standard

With only 7.5 grams and 3.2 millimeters thickness, the MT01 Compact Magnetorquer is a vacuum core magnetic coil designed fo ADCS control in cubesat mission from 1U to 3U that boast an impressive performance compared to its small footprint over the mass, power and area budget of the spacecraft. Even with that small dimensions the MT01 is capable of greater magnetic moments, turn speeds and angular accelerations than comparable products on the market, yet the power usage is kept to a minimum: It can turn a 1U mass 90 degrees in 60 seconds using only 0.2 Watts at a LEO orbit of 500kms.MT01 can be integrated in to our BA0x family of high capacity compact batteries and our DSA Deployable Solar Array family too, the biggest advantage of the MT01 is that it can be easily affixed anywhere on your spacecraft using a minimal area.Every coil is tested and qualified in our own facilities and shipped with full reports and packed with additional match connectors interfaces.

This Phase II SBIR project deals with the design, development, and testing of a "Plasma Fairing" to reduce noise on the Gulfstream G550 landing gear. The plasma fairing will use single dielectric barrier discharge (SDBD) plasma actuators to reduce flow- separations and impingement around the landing gear, which are the dominant sources of landing gear noise. The Phase I project successfully demonstrated the feasibility of the plasma fairing concept on a generalized tandem cylinder configuration that shared important features of key sections of the G550 landing gear, specifically the relationship between the strut and the torque arm. The Phase II extends the concept to a more complex geometry: G550 landing gear. We will develop aeroacoustic simulations using University of Notre Dame's state-of-the-art plasma actuator model and Exa Corporation's flow solver PowerFLOW, coupled with experiments in an anechoic wind tunnel with both aerodynamic and acoustic measurements on a scaled G550 nose gear model to design and optimize a Plasma Fairing configuration that provides significant noise reduction on the G550 landing gear. We anticipate a technology readiness level (TRL) of 5 at the end of the Phase II project.

The Advanced Computational Center for Entry System Simulation (ACCESS) is a comprehensive team of world-leading experts from five U.S. universities (Colorado, Illinois, Kentucky, Minnesota, New Mexico) and three international collaborators (Oxford University, National Research Center-Bari, Instituto Superior Tecnico-Lisbon). Our vision for ACCESS is to radically advance the analysis and design of entry systems through development of a tightly integrated interdisciplinary simulation framework employing high-fidelity validated physics models, driven by quantified uncertainty and reliability, and enabled by innovative algorithms and high-performance computing.A NASA Entry System (ES) involves the Thermal Protection System (TPS), including both the heat shield and backshell, along with the supporting structure. An ES is essential to many of NASA’s highest priority space exploration missions, including lunar return to Earth (Artemis), Titan entry (Dragonfly), sending people to Mars (Mars Human Lander), and return of Mars samples to Earth (Earth Entry Vehicle, EEV). Based on the key attributes of these missions, the critical physical processes that drive ES design involve flow phenomena (e.g., chemistry, radiation, turbulence), material response (e.g., ablation) and structural response (e.g., fracture). The ACCESS research plan includes analysis of Dragonfly, Mars Human Lander, and the EEV.Entry System analysis and design capabilities currently employed by NASA and its contractors are workable for Artemis, but have critical limitations for the more challenging environments of future missions. A first significant limitation with state-of-the-art (SOA) analysis capabilities is that the uncertainties associated with predicting key quantities of interest are so large that it is not always possible to close on a design cycle. For example, a margin of 100% for turbulent surface heating augmentation is typically employed for Mars entry, and a margin of 40% was used for radiative surface heating for lunar return. Such large uncertainties arise directly from limitations in the accuracy of modeling the key physical phenomena and represent a significant challenge for meeting design requirements, e.g., EEV has a reliability requirement of less than 1 in 106 that cannot be met by SOA analysis capabilities.A second significant challenge for the design of ES for NASA reference missions concerns the currently available analysis tools. NASA and the contractors employ a number of computational codes for analysis of ES. However, these tools are labor intensive to apply, their computational performance is limited in part by not taking advantage of emerging computer architectures, and they do not integrate uncertainty and reliability.To address these challenges, the ACCESS research plan involves four tightly coupled tasks:Task 1: Kinetic Rate and Physical ProcessesTask 2: Integrated Simulation FrameworkTask 3: High Fidelity Modeling of TPS Features, Damage, and FailureTask 4: Uncertainty Quantification and Reliability.ACCESS will drive down design margins and quantify uncertainty through an innovative, multidisciplinary research approach. The entry missions targeted involve an enormous number of gas-phase and radiative processes. For example, an ablating hydrocarbon TPS can require chemistry mechanisms with about 40 species and 150 reactions. Backshell heating from radiation can also be significant. To reduce the margin, rates for all key reactions must be estimated using reliable experimental data and scalable statistical inference techniques, and the resulting uncertainty must be quantified. In Task 1, theoretical chemistry will identify the key reactions and determine new rates as needed including those for production of electronically-excited states that radiate. The overall kinetics mechanism, including both ground-state and excited-state reactions, will be evaluated through direct comparisons with experimental data generated in world-class facilities. The quantification of uncertainty associated with the rates will be established in collaboration with Task 4. The rates, along with the quantified uncertainty, will be integrated into the overall simulation tool in Task 2. In Task 3, models for gas-surface kinetics, constructed from molecular beam experimental data, must first be applied at the mesoscale for material response modeling. Our novel approach uses simulations of representative volume elements (RVEs). The RVE simulations will use detailed kinetics information (Task 1) and specific meso-structures (Task 3) as inputs, and will quantify each of the mesoscale modeling components required by the material response model; namely, oxidation evolution, porous flow trends, and thermal, structural, and radiative properties. The RVE simulations will provide natural variability in these models and associated parameters (distribution functions), which is crucial to model a full TPS including uncertainty and reliability. The novel stochastic material response framework (Task 3) will be directly coupled to the overall simulation tool (Task 2) and will be developed within the proposed UQ framework (Task 4). This comprehensive approach spans all of the Tasks and all of the ACCESS universities. Such innovative and multidisciplinary integrated research is absolutely essential to achieving the Vision of ACCESS of reducing the overall margins and improving the reliability for the analysis and design of an ES.The primary product of ACCESS is the Integrated Simulation Framework (ISF) that will completely change the paradigm in comparison to SOA capabilities for the analysis and design of ES. The ISF will be developed in Task 2, will integrate the key products of all other Tasks, and will take as its starting point the widely used US3D computational fluid dynamics code. As a fundamental construct in its design, US3D allows the integration of simulation capabilities for a broad range of physical phenomena through specification of plugins. The use of plugins with well-defined interfaces makes it possible to transfer capabilities developed in ACCESS for US3D into other simulation frameworks of NASA and its contractors. Task 4 addresses UQ at the level of individual phenomena in the flow and TPS areas (Tasks 1 and 3) and for overall simulations through the ISF (Task 2). The UQ for Tasks 1 and 3 will break new ground for detailed quantification of uncertainty through close coupling between modeling and experiments. Instead of “validating” the physics models, the contribution of inaccuracy and uncertainty of individual processes to overall risk in the ES design will be quantified and transmitted through the system level simulation. One significant challenge in Task 4 for UQ and reliability is the high computational cost of each full ISF simulation, which may limit the number of sensitivity data points that are generated. To address this challenge, novel algorithms will be explored, such as Discontinuous Galerkin methods and meshless techniques, that have the potential to significantly reduce the time to set up and execute large-scale simulations. Also, key ISF algorithms will be adapted for execution on Peta/Exa scale computer architectures to reduce run time. Emerging UQ approaches will be employed that make careful use of lower fidelity physical models to achieve results consistent with more expensive higher fidelity models but at drastically reduced cost. The successful outcome of the overall Vision for ACCESS will deliver an integrated simulation framework for the comprehensive and affordable design of ES with quantified uncertainty and reliability estimates that will be ready for adoption by NASA and its contractors.

This is a Co-I proposal for the Antarctic Impulsive Transient Antenna (ANITA) mission (P. Gorham, Hawaii, PI). We propose to fly a significantly improved version of the Antarctic Impulsive Transient Antenna (ANITA) long-duraction balloon payload, with a goal of discovering and characterizing ultra-high energy (UHE) neutrinos and cosmic rays in the EeV (Exa-electronvolt) energy range and above. This will be the fifth flight of ANITA payloads, and should achieve the a milestone of 100 days of integrated livetime on orbit, proposed in the earliest flight as a goal for the application of ANITA's novel methodology. Each payload in the series has yielded improved sensitivity, and unexpected results, both in the form of upper limits that excluded long-held predictions for the isotropic neutrino flux from various models, and in the form of serendiptious detections of UHE cosmic rays via radio pulses that were not well understood when ANITA first flew. Moreover, ANITA's ability to perform precision measurements of the pulse shape and polarization properties of the UHE cosmic ray events led to the discovery of candidates for tau-lepton-generated air showers, one in the ANITA-I flight, and most recently, a second candidate in the ANITA-III flight. These events signal the possible appearance of a flux of UHE tau neutrinos, appearing with unexpected properties, in tension with other measurements. ANITA-V will provide an opportunity to elucidate these new potential signals in a compelling way with far-reaching implications for fundamental physics.

This is a Co-I proposal that should be cross-referenced to the University of Hawaii proposal titled "Ultra-high Energy Particle Astrophysics with ANITA-V", for which Peter Gorham is the Principal Investigator. We propose to fly a significantly improved version of the Antarctic Impulsive Transient Antenna (ANITA) long-duration balloon payload, with a goal of discovering and characterizing ultra-high energy (UHE) neutrinos and cosmic rays in the EeV (Exa-electron-volt) energy range and above. This will be the fifth flight of ANITA payloads, and should achieve the a milestone of 100 days of integrated livetime on orbit, proposed in the earliest flight as a goal for the application of ANITA's novel methodology. Each payload in the series has yielded improved sensitivity, and unexpected results, both in the form of upper limits that excluded long-held predictions for the isotropic neutrino flux from various models, and in the form of serendiptious detections of UHE cosmic rays via radio pulses that were not well understood when ANITA first flew. Moreover, ANITA's ability to perform precision measurements of the pulse shape and polarization properties of the UHE cosmic ray events led to the discovery of candidates for tau-lepton-generated air showers, one in the ANITA-I flight, and most recently, a second candidate in the ANITA-III flight. These events signal the possible appearance of a flux of UHE tau neutrinos, appearing with unexpected properties, in tension with other measurements. ANITA-V will provide an opportunity to elucidate these new potential signals in a compelling way with far-reaching implications for fundamental physics.

This is the lead proposal on a multi-institutional proposal. We propose to fly a significantly improved version of the Antarctic Impulsive Transient Antenna (ANITA) long-duration balloon payload, with a goal of discovering and characterizing ultra-high energy (UHE) neutrinos and cosmic rays in the EeV (Exa-electron-volt) energy range and above. This will be the fifth flight of ANITA payloads, and should achieve a milestone of 100 days of integrated live-time on orbit, proposed in the earliest flight as a goal for the application of ANITA's novel methodology. Each payload in the series has yielded improved sensitivity, and unexpected results, both in the form of upper limits that excluded long-held predictions for the isotropic neutrino flux from various models, and in the form of serendipitous detections of UHE cosmic rays via radio pulses that were not well understood when ANITA first flew. Moreover, ANITA's ability to perform precision measurements of the pulse shape and polarization properties of the UHE cosmic ray events led to the discovery of candidates for tau-lepton-generated air showers, one in the ANITA-I flight, and most recently, a second candidate in the ANITA-III flight. These events signal the possible appearance of a flux of UHE tau neutrinos, appearing with unexpected properties, in tension with other measurements. In addition to these unexpected anomalous cosmic-ray like events, ANITA-III analysis has yielded one potentially interesting neutrino candidate from a possible in-ice shower, a total of two possible candidates from the 2014-2015 flight of ANITA-III. ANITA-IV analysis is well underway, with about 3 times the expected sensitivity of ANITA-III, but could not be completed prior to this proposal. Depending on ANITA-IV results, ANITA-V will provide an opportunity to elucidate these new potential signals in a compelling way with far-reaching implications for fundamental physics, or to bring to fruition the strongest world limits on cosmogenic neutrino fluxes from the combination of all of the flights, with over 100 days of expected exposure.