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This document is a summary of the mathematical models that are used in the DARPA TRADES project for the solid rocket motor design challenge. It is hoped that this brief description of these models will be of use to those that are working on the project.
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Propulsion technologies have focused on monopropellant hydrazine systems for the past four decades. However, hydrazine is both highly toxic and highly flammable, requiring expensive cold storage and specialized handling and disposal protocols. Alternative propellant fuels for supporting satellites and spacecraft are required, and greener, on-demand approaches for manufacturing denser, less dangerous rocket fuels are essential. This project will ensure that humans in extreme environments such as space can sustainably access renewable fuel resources from biomass waste streams via continuous biocatalytic manufacturing using microfluidic reactor systems. Demonstration of our sustainable and recyclable processes for manufacturing greener propellants from biomass waste will advance further applications in future space missions. There remains a continued need to develop more sustainable, environmentally-responsible pathways for manufacturing fuels in general and propellants in particular. This project, building upon known biocatalytic processes, will provide astronauts with renewable propellant fuel sources that can be manufactured in situ. Thus, “on-demand” access to propellants that perform more efficiently than hydrazine is enabled by this proposed work.
The Space Nuclear Thermal Propulsion (SNTP) project was an attempt to create a more powerful and more efficient rocket engine utilizing nuclear technologies. As part of this project a zero-power critical assembly referred to as SNTPCX was designed and installed at Sandia National Laboratories. The SNTP-CX was a light water moderated particle bed reactor utilizing highly enriched uranium fuel in the form of UC particles. The SNTP-CX performed 142 runs covering numerous experiments from the year 1989 to 1992. The program was canceled in 1994 as the nation’s priorities shifted. Now these experiments are being evaluated for use as criticality safety benchmarks. Nineteen of the 142 reactor runs were dedicated to a series of experiments to calculate the worth of the boron used in the light water moderator. This series of experiments has been selected for further evaluation as a critical benchmark for the International Criticality Safety Benchmark Evaluation Project (ICSBEP).
The purpose of this paper is to present some aspects regarding the computational model and technical solutions for multistage suborbital launcher for testing (SLT) used to test spatial equipment and scientific measurements. The computational model consists in numerical simulation of SLT evolution for different start conditions. The launcher model presented will be with six degrees of freedom (6DOF) and variable mass. The results analysed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize a small multi-stage launcher, by recycling military rocket motors. From technical point of view, the paper is focused on national project 'Suborbital Launcher for Testing' (SLT), which is based on hybrid propulsion and control systems, obtained through an original design. Therefore, while classical suborbital sounding rockets are unguided and they use as propulsion solid fuel motor having an uncontrolled ballistic flight, SLT project is introducing a different approach, by proposing the creation of a guided suborbital launcher, which is basically a satellite launcher at a smaller scale, containing its main subsystems. This is why the project itself can be considered an intermediary step in the development of a wider range of launching systems based on hybrid propulsion technology, which may have a major impact in the future European launchers programs. SLT project, as it is shown in the title, has two major objectives: first, a short term objective, which consists in obtaining a suborbital launching system which will be able to go into service in a predictable period of time, and a long term objective that consists in the development and testing of some unconventional sub-systems which will be integrated later in the satellite launcher as a part of the European space program. This is why the technical content of the project must be carried out beyond the range of the existing suborbital vehicle programs towards the current technological necessities in the space field, especially the European one.
The purpose of the NETL Project was to develop a diverse combination of distributed renewable generation technologies and controls and demonstrate how the renewable generation could help manage substation peak demand at the ATK Promontory plant site. The Promontory plant site is located in the northwestern Utah desert approximately 25 miles west of Brigham City, Utah. The plant encompasses 20,000 acres and has over 500 buildings. The ATK Promontory plant primarily manufactures solid propellant rocket motors for both commercial and government launch systems. The original project objectives focused on distributed generation; a 100 kW (kilowatt) wind turbine, a 100 kW new technology waste heat generation unit, a 500 kW energy storage system, and an intelligent system-wide automation system to monitor and control the renewable energy devices then release the stored energy during the peak demand time. The original goal was to reduce peak demand from the electrical utility company, Rocky Mountain Power (RMP), by 3.4%. For a period of time we also sought to integrate our energy storage requirements with a flywheel storage system (500 kW) proposed for the Promontory/RMP Substation. Ultimately the flywheel storage system could not meet our project timetable, so the storage requirement was switched to a battery storage system (300 kW.) A secondary objective was to design/install a bi-directional customer/utility gateway application for real-time visibility and communications between RMP, and ATK. This objective was not achieved because of technical issues with RMP, ATK Information Technology Department’s stringent requirements based on being a rocket motor manufacturing facility, and budget constraints. Of the original objectives, the following were achieved: • Installation of a 100 kW wind turbine. • Installation of a 300 kW battery storage system. • Integrated control system installed to offset electrical demand by releasing stored energy from renewable sources during peak hours of the day. Control system also monitors the wind turbine and battery storage system health, power output, and issues critical alarms. Of the original objectives, the following were not achieved: • 100 kW new technology waste heat generation unit. • Bi-directional customer/utility gateway for real time visibility and communications between RMP and ATK. • 3.4% reduction in peak demand. 1.7% reduction in peak demand was realized instead.
Mega-ampere class pulsed power machines drive intense currents into small volumes to study high energy and density environments. Power lost during these events is a difficult and paramount problem to solve. For example, facilities such as Sandia National Laboratories’ Z machine experience meaningful power loss, which can be linked to non-linear ohmic heating at high currents (i.e., 26 MA on Z) leading to thermal desorption of contaminants and subsequent shunt plasma formation. Characterizing and understanding this type of thermal desorption is key to design optimizations necessary to minimize current loss, which will be even more important for next generation pulsed power. This type of characterization requires the ability to identify and determine concentration of analytes with nanosecond resolution given the pulse width of Z is on the order of 100 ns. This report summarizes progress on a small exploratory project focused on investigating options to meet this challenge using mass spectrometry. The main focus of these efforts utilized an Energy and Velocity Analyzer for Distributions of Electric Rockets intending to determine how quickly transient data could be resolved. This probe combines an electrostatic analyzer with a Wien velocity filter (ExB) to obtain ion energy and velocity distributions. Primary results from this exploratory project indicate significant additional work is needed to demonstrate a nanosecond time scale mass spectrometer for this application and also highlight that alternative detection methods such as laser-based diagnostics should be considered to meet the need for ultra-fast detection.
The Press Building was constructed in 1954 with 15,073 ft 2 of floor space. It was built to house a 5000 ton double action Lake Erie hydraulic press and a uranium casting area. Missions included uranium activities associated with the Nuclear Weapons and Rover Rocket programs. At the end of the Rover program, the building continued to support various uranium materials science projects until the building was placed into a cold and dark status in 2013 and then was demolished in 2017. The building interior, the press, and associated systems were radiological contaminated and disposed of as low level waste. The demolition of this building opened up valuable real estate in the TA-3 area for the future construction of an ~11,000 Sq. Ft. Biosafety Level 2 laboratory and office building. This building will support the ongoing Bioscience Division mission at the laboratory.
Bose-Einstein-Condensates (BECs) can be used as a very sensitive tool for experiments on fundamental questions in physics like testing the equivalence principle using matter wave interferometry. Since the sensitivity of these experiments in ground-based environments is limited by the available free fall time, the QUANTUS project started to perform BEC interferometry experiments in micro-gravity. After successful campaigns in the drop tower, the next step is a space-borne experiment. The MAIUS-mission will be an atom-optical experiment that will show the feasibility of experiments with ultra-cold quantum gases in microgravity in a sounding rocket. The experiment will create a BEC of 10{sup 5} {sup 87}Rb-atoms in less than 5 s and will demonstrate application of basic atom interferometer techniques over a flight time of 6 min. The hardware is specifically designed to match the requirements of a sounding rocket mission. Special attention is thereby spent on the appropriate magnetic shielding from varying magnetic fields during the rocket flight, since the experiment procedures are very sensitive to external magnetic fields. A three-layer magnetic shielding provides a high shielding effectiveness factor of at least 1000 for an undisturbed operation of the experiment. The design of this magnetic shielding, the magnetic properties, simulations, and tests of its suitability for a sounding rocket flight are presented in this article.
ABSTRACT Bright-rimmed clouds (BRCs) are ideal candidates to study radiation-driven implosion mode of star formation as they are potential sites of triggered star formation, located at the edges of Hii regions, showing evidence of ongoing star formation processes. BRC 18 is located towards the eastern edge of relatively closer (∼400 pc) H ii region excited by λ Ori. We made R-band polarimetric observations of 17 candidate young stellar objects (YSOs) located towards BRC 18 to investigate any preferred orientation of the discs with respect to the ambient magnetic field and the direction of energetic photons from λ Ori. We found that the discs are oriented randomly with respect to the projected magnetic field. Using distances and proper motions from the Gaia EDR3 of the candidate YSOs, we investigated the possible acceleration of BRC 18, away from λ Ori due to the well-known ‘Rocket Effect’, by assuming that both the candidate YSOs and BRC 18 are kinematically coupled. The relative proper motions of the candidate YSOs are found to show a trend of moving away from λ Ori. We computed the offset between the angle of the direction of the ionization front and the relative proper motion of the candidate YSOs and found it to lie close to being parallel to each other. Additionally, we found 12 sources that are co-moving with the known candidate YSOs towards BRC 18. These co-moving sources are most likely to be young and are missed in previous surveys conducted to identify potential YSOs of the region.
This project was undertaken to assess the feasibility and advantages of utilizing a gas-cooled fast reactor to supply power to an electric propulsion system for deep space exploration to Europa, one of Jupiter's moons. Specifically, the primary objective of this project was to design a 9 MWe gas cooled fast reactor with an accompanying power conversion system to supply electricity to multiple electrically-powered thrusters for a four year mission duration. The thruster design chosen for this analysis is the Variable Specific Impulse Magnetoplasma Rocket (VASIMR). The VASIMR propulsion system, currently being developed by Ad Astra Rocket Company (AARC), is an electric propulsion rocket that uses electric power to accelerate neutral plasma propellant. Advanced electric space propulsion systems such as the VASIMR offer unique capabilities that allow for higher exhaust velocities that are up to ten times that of traditional chemical rockets. Furthermore, the thrust and specific impulse of the VASIMR system can be varied in order to achieve optimal travel times to given destinations for a desired payload. As a result, electric propulsion systems characteristically have lower ratios of system mass to power output than chemical rockets. This ratio is commonly known as the alpha parameter. Alpha parameters of approximately 10 kg/kWe or less make electric propulsion more attractive for deep space exploration missions in terms of resource efficiency and cost. However, the primary challenge with electric propulsion is to develop a high power density source of electricity in order to minimize the total system mass. The alpha parameter is the main benchmark used in this project to test whether or not the proposed coupled gas cooled reactor and power conversion system design is more competitive than other proposed systems. (authors)
Microreactor designs make use of a coreblock for structural stability allowing for these devices to provide powder generation while being portable and inherently safe. In order to maximize energy output of the microreactors, materials must be able to withstand high temperature without melting and without substantial decreases in mechanical properties. As simultaneous projects looking at steels, graphite, and other materials are on-going, this work package will investigate titanium – zirconium – molybdenum alloy (TZM) as it allows for potentially higher microreactor operating temperatures than traditional reactor materials such as stainless steel. Notably, this alloy was developed in the 1960s for use in rockets and has a very high melting point (2623°C) but is difficult to form, machine and join. With limited needs in aerospace, literature is appropriately sparce in looking at the AM of TZM (examples include [1,2]). However, the properties appear to be an excellent match for the needs of the microreactor coreblock leading to the current project. In addition, small washers form the bulk of TZM parts needed in aerospace while the microreactor community was looking at larger, more complex parts. Therefore, AM of TZM is being explored to enable near – net shape of components with the needed complexity to impact the nuclear energy field.
The CSNR NTR Design Team has developed a history of collaboration with NASA Marshall Spaceflight Center (MSFC). First assembled in the summer of 2013 to explore the concept of the Low-Enriched Uranium Nuclear Thermal Rocket (LEU-NTR), the team continued research to find solutions with guiding Nuclear Thermal Propulsion (NTP) technological development and provide design and analysis support for the Space Capable Cryogenic Thermal Engine (SCCTE) Project. The work presented in this report provides a background on the cermet LEU-NTR, summarizes work complete to explore a new design space for NTRs, and describes the SCCTE core that was developed.
This technical report summarizes the work completed by BioLite in fulfilment of the US DOE EERE award. The work plan focused on three key objectives: developing an optimized combustion system that demonstrates high combustion efficiency and low PM 2.5 and CO emissions, integrate the system into popular stove phenotypes – side-fed rocket stove architecture like the BioLite HomeStove, and the Patsari chimney stove in Mexico such that they maintain their important phenotypical characteristics, independently evaluate quantitative fuel and emissions performance of the integrated ‘Turbo-Patsari’ in Mexican households. The project activities were organized into six major tasks: A. Develop, fabricate, and test proof-of-concept prototypes B. Develop field prototypes, assess user feedback and field performance C. Define revised stove design for pre-production model, Identify manufacturing requirements and estimated cost to build, Conduct reliability, emissions, and performance testing of pre-production Turbo-Patsari D. Build pre-production Turbo-Patsari stove combustion cores E. Conduct pre-production field trials F. Summarize field trial results and evaluate Turbo-Patsari for potential volume production. A two-pronged approach was adopted for the above tasks. The first involved building a modular test platform that allowed parametric variation of multiple stove design parameters that directly affect its performance – heat output, thermal efficiency, and emissions. The second part of the approach comprised of building a surrogate Patsari based on GIRA’s specifications that could then be modified or retrofitted for optimum performance based on the learnings from the modular test platform. The following sections of the report will describe the findings of tests on these platform, the subsequent development, design, and installation of the Turbo-Patsari, and finally the in-home field trial.
Rarefied gas-particle two-phase plume in which the phase of particles is liquid or solid flows from a solid propellant rocket of hypersonic vehicle flying at high altitudes, the aluminum oxide particulates not only impact the rarefied gas flow properties, but also make a great difference to plume radiation signature, so the radiation prediction of the rarefied gas-particle two-phase plume flow is very important for space target detection of hypersonic vehicles. Accordingly, this project aims to study the rarefied gas-particle two-phase flow and ultraviolet radiation (UV) characteristics. Considering a two-way interphase coupling of momentum and energy, the direct simulation Monte Carlo (DSMC) method is developed for particle phase change and the particle flow, including particulate collision, coalescence as well as separation, and a Monte Carlo ray trace model is implemented for the particulate UV radiation. A program for the numerical simulation of the gas-particle two-phase flow and radiation in which the gas flow nonequilibrium is strong is implemented as well. Ultraviolet radiation characteristics of the particle phase is studied based on the calculation of the flow field coupled with the radiation calculation, the radiation model for different size particles is analyzed, focusing on the effects of particle emission, absorption, scattering as well as the searchlight emission of the nozzle. A new approach may be proposed to describe the rarefied gas-particle two-phase plume flow and radiation transfer characteristics in this project.
The U.S. Department of Energy, National Nuclear Security Administration Nevada Field Office (NNSA/NFO) has authorized an updated recording and evaluation of Test Cell C. This facility is part of the former Nuclear Rocket Development Station (NRDS) in Area 25 of Nevada National Security Site (NNSS) in Nye County, Nevada (formerly the Nevada Test Site [NTS]). Future alterations to the facility are anticipated to meet current and future National Weapons Science, Global and Homeland Security Programs, and Environmental Management mission requirements. Therefore, this survey was done to comply with requirements of Section 106 of the National Historic Preservation Act and its implementing regulations, 36 C.F.R. Part 800. An architectural survey of 35.75 acres was completed by Desert Research Institute (DRI). This area also represents the potential Test Cell C Historic District and is identified by NNSA/NFO as the Area of Potential Effect (APE) within which the undertaking may directly cause alterations to the character of historic properties. One resource, Building 25-3210 (SHPO Resource No. B2444), within this area was previously surveyed by DRI. It was found eligible for inclusion in the National Register of Historic Places (NRHP or National Register) under Criteria A and C, and Consideration G. Mitigation of this building was completed prior to its demolition. The APE for reasonably foreseeable effects that may indirectly cause alterations later in time, be farther removed in distance, or be cumulative is the unrecorded NRDS historic district. The present survey updates the previous survey to present standards and expands it to include the entire Test Cell C complex. This includes updated recording and evaluation of the remains of 25-3210 and its 32 previously unrecorded and unevaluated Accessory Resources. The entire complex was recorded as the Test Cell C Historic District (SHPO Resource No. D346), which is eligible for the National Register at the National Level under Criteria A, C, and D. All nine architectural resources in the district are recommended as contributing elements of the Test Cell C Historic District (Figure 2). Of these, four (25-3210 Resource No. B2444, 25-3220 SHPO Resource No. B18110, 25-3226 SHPO Resource No. B18111, and 25-3230-32 SHPO Resource No. B18114) are recommended as individually eligible to the National Register under Criteria A and C, and one (KIWI-TNT [Transient Nuclear Test] SHPO Resource No. S2287) is recommended as individually eligible under Criteria A, C, and D. The remaining four resources (25-3214 SHPO Resource No. B18109, 25-3228 SHPO Resource No. B18112, 25-3229 SHPO Resource No. B18113, and 25-3233 SHPO Resource No. 18115) are not recommended as individually eligible. In addition, the Test Cell C Historic District is regarded as a contributor to the potential national significance of the NRDS Historic District. In 2010, the NTS became the NNSS. Because of the nature of the discussion in the Historic Context below, “NTS” is used throughout that section, otherwise “NNSS” is used to refer to the site. The survey area is located in unplatted sections of T13S R51E Mount Diablo Baseline and Meridian (projected) in Area 25 of the NNSS. It is within the NRDS in Jackass Flats, which has long been recognized as a potential historic district. An oblique aerial photo of the Test Cell C complex is shown on the cover of this report.
Presented in this paper is the Space Capable Cryogenic Thermal Engine (SCCTE), a Low Enriched Uranium (LEU) W-UO2 cermet fuel, ZrH1.8 moderated Nuclear Thermal Propulsion (NTP) Concept. The SCCTE project was undertaken by a collaboration with NASA Marshall Space Flight Center (MSFC) and Center for Space Nuclear Research (CSNR) to investigate the applicability of LEU cermet NTP technology for a human Mars mission in the 2030's time frame. This paper focuses on the nuclear design aspects of SCCTE.
LiteBIRD, the Lite (Light) satellite for the study of B-mode polarization and Inflation from cosmic background Radiation Detection, is a space mission for primordial cosmology and fundamental physics. The Japan Aerospace Exploration Agency (JAXA) selected LiteBIRD in May 2019 as a strategic large-class (L-class) mission, with an expected launch in the late 2020s using JAXA’s H3 rocket. LiteBIRD is planned to orbit the Sun–Earth Lagrangian point L2, where it will map the cosmic microwave background polarization over the entire sky for three years, with three telescopes in 15 frequency bands between 34 and 448 GHz, to achieve an unprecedented total sensitivity of $2.2\, \mu$K-arcmin, with a typical angular resolution of 0.5° at 100 GHz. The primary scientific objective of LiteBIRD is to search for the signal from cosmic inflation, either making a discovery or ruling out well-motivated inflationary models. The measurements of LiteBIRD will also provide us with insight into the quantum nature of gravity and other new physics beyond the standard models of particle physics and cosmology. We provide an overview of the LiteBIRD project, including scientific objectives, mission and system requirements, operation concept, spacecraft and payload module design, expected scientific outcomes, potential design extensions, and synergies with other projects.