National Aeronautics and Space Administration
Small Business Innovation Research & Technology Transfer 2004 Program Solicitations
TOPIC T9 Stennis Space Center
[ back to Solicitation ] [ back to Chapter 9 ][ back to Chapter 9.2 ][ back to table of contents ]
T9.01 Rocket Propulsion Testing Systems
T9.02 Integrated Life-cycle Asset Mapping, Management, and Tracking
The John C. Stennis Space Center (SSC) in south Mississippi is NASA's primary center for testing and flight certifying rocket propulsion systems for the Space Shuttle and future generations of space vehicles. Because of its important role in engine testing for four decades, Stennis Space Center is NASA's program manager for rocket propulsion testing with total responsibility for conducting and/or managing all NASA propulsion test programs. Stennis Space Center tests all Space Shuttle Main Engines. These high-performance, liquid-fueled engines provide most of the total impulse needed during the shuttle's eight and one-half-minute-flight to orbit. All shuttle main engines must pass a series of test firings at Stennis Space Center prior to being installed in the back of the orbiter.
The Earth Science Applications Directorate is NASA's Program Manager for Earth Science Applications. The Directorate matches NASA's scientific and technical knowledge with issues of national concern and the needs of our partners. Partners include local, state, and tribal governments, commercial industry, with educational institutions and other non-profit institutions. Through the Directorate's co-funded partnerships, public and private sector decision makers learn how to apply new technologies to critical environmental, resource management, community growth, and disaster management issues. The Directorate also provides the remote sensing community with a comprehensive array of manmade and natural ground targets, measurement systems, and benchmark processes to help test airborne and space remote sensing systems against performance specifications and customer needs.
Stennis Space Center began "re-inventing government" decades ago before the concept became popular. Over the years, SSC has evolved into a multiagency, multidisciplinary center for federal, state, academic and private organizations engaged in space, oceans, environmental programs and the national defense. In addition to NASA, there are 30 other agencies located at Stennis. Of approximately 4,500 employees, about l,600 work in the fields of science and engineering. These agencies work side by side and share common costs related to infrastructure, facility and technical services, thus making it cheaper for each to accomplish its independent mission at SSC.
T9.01 Rocket Propulsion Testing Systems
Proposals are sought for innovative technologies and technology concepts in the area of propulsion test operations. Proposals should support the reduction of overall propulsion test operations costs (recurring costs) and/or increase reliability and performance of propulsion ground test facilities and operations methodologies. As a minor element in a proposal for this topic, the offeror may include specific educational related research, technology advances, or other deliverables that address and support the Agency’s education mission, such as the enhancement of science, technology, engineering, and mathematics instruction with unique teaching tools and experiences. Specific areas of interest in this subtopic include the following.
Facility and Test Article Health-Monitoring Technologies
- Innovative, nonintrusive sensors for measuring flow rate, temperature, pressure, rocket engine plume constituents, and effluent gas detection. Sensors must not physically intrude at all into the measurement space. Low-millisecond to sub-millisecond response time is required. Temperature sensors must be able to measure cryogenic temperatures of fluids (as low as 160R for LOX and 34R for LH2) under high pressure (up to 15,000 psi), high flow rate conditions (2000 lb/s - 82 ft/s for LOX, 500 lb/s - 300 ft/s for LH2). Flow rate sensors must have a range of up to 2000 lb/s (82 ft/sec) for LOX and 500 lb/sec (300 ft/s) for LH2. Pressure sensors must have a range up to 15,000 psi. Rocket plume sensors must determine gas species, temperature, and velocity for H2, O2, hydrocarbons (kerosene), and hybrid fuels.
- Rugged, high accuracy (0.2%), fast response temperature measuring sensors and instrumentation for very high pressure, high flow rate cryogenic piping systems. Temperature sensors must be able to measure cryogenic temperatures of fluids (as low as 160R for LOX and 34R for LH2) under high pressure (up to 15,000 psi), high flow rate conditions (2000 lb/s - 82 ft/s for LOX, 500 lb/s - 300 ft/s for LH2). Response time must be on the order of a few milliseconds to the sub-milliseconds.
- Phenomenology, modeling, sensors, and instrumentation for prediction, characterization, and measurement of rocket engine combustion instability. Sensor systems should have bandwidth capabilities in excess of 100 kHz. Emphasis is on development of optical-based sensor systems that will be nonintrusive in the test article hardware or plume.
Improvement in Ground-Test Operation, Safety, Cost-effectiveness, and Reliability
- Smart system components (control valves, regulators, and relief valves) that provide real-time closed-loop control, component configuration, automated operation, and component health. Components must be able to operate in cryogenic temperatures (as low as 160R for LOX and 34R for LH2 ) under high pressure (up to 15,000 psi) high flow rate conditions (2000 lb/s - 82 ft/s for LOX, 500 lb/sec - 300 ft/s for LH2 ). Components must be able to operate in the elevated temperatures associated with a rocket engine testing environment. Response time must be on the order of a few milliseconds to the sub-milliseconds.
- Improved long-life, liquid oxygen compatible seal technology. Materials and designs suitable for oxygen service at pressures up to 10,000 psi. Both cryogenic and elevated temperature candidate materials and designs are of interest. Typical temperature ranges will be either -320°F to 100°F, or -40°F to 300°F. Seal designs may include both dynamic and static use. Plastic, metal, or electrometric materials, or combinations thereof, are of particular interest.
- Miniature front-end electronics to support embedding of intelligent functions on sensors. Requirements include computational power comparable to a 200 MHz PC with approximately 32 MB of RAM and similar non-volatile storage, analog input/output (I/O) (at least two of each, with programmable amplification and anti-aliasing filters, plus automatic calibration) digital I/O (at least eight), communication port for Ethernet bus protocol (one high speed and one low speed), support for C programming (or other high level language), and a development kit for a PC. The package should occupy a space no larger than 4" x 4" x 2". The system should include an embedded temperature sensor, an embedded stable voltage calibration source, and programmable switching to connect calibration source input and output.
- New and innovative acoustic measurement techniques and sensors for use in a rocket plume environment. Current methods of predicting far-field and near-field acoustic levels produced by rocket engines rely on empirical models and require numerous physical measurements. New and innovative acoustic prediction methods are required which can accurately predict the acoustic levels a priori or using fewer measurements. New, innovative techniques based on energy density measurements rather than pressure measurements show promise as replacements for the older models.
- Development of tools that integrate simple operator interfaces with detailed design and/or analysis software for modeling and enhancing the flow performance of flow system components such as valves, check valves, pressure regulators, flow meters, cavitating venturis, and propellant run tanks.
- New and improved methods to accurately model the transient interaction between cryogenic fluid flow and immersed sensors that predicts the dynamic load on the sensors, frequency spectrum, heat transfer, and effect on the flow field, are needed.
- Modeling of atmospheric transmission attenuation effects on test spectroscopic measurements. Atmospheric transmission losses can be significant in certain wavelength regions for radiometric detectors located far from the rocket engine exhaust plume. Consequently, atmospheric losses can result in over-prediction of the incident radiant flux generated by the plume. Accurate atmospheric transmission modeling is needed for high-temperature rocket engine plume environments. The capabilities should address both the losses from ambient atmosphere and localized environments, such as condensation clouds generated by cryogenic propellants.
Application of System Modeling to Ground Test Operations in a Resource Constrained Environment
- New innovative approaches to incorporating knowledge and information processing techniques (prepositional logic, fuzzy logic, neural nets, etc.) to support test system decision making and operations. A requirement exists to develop, apply, and train intelligent agents, behavioral networks, and logic streams for rocket engine testing modes of operations and practice. Applications must operate statistically well on small and disparate data sources. The resulting products are inferential, representative, and they capture tacit and explicit knowledge. Statistical analysis must be supported.
- Techniques to reduce required sample size to maintain acceptable levels of confidence in cost data. In order to use appropriate models and to manage the cost of data acquisition and maintenance, the minimization of required data sample sizes is critical.
- Measurements and data are the product of ground testing. High accuracy, precision, uncertainty bands, and error bands are important elements of the data that is generated, and this must be quantified. Techniques and models to determine these parameters for active test facilities are required.
[back to top]
T9.02 Integrated Life-cycle Asset Mapping, Management, and Tracking
To support NASA’s need for reliable and low cost asset management in all of its programs including Earth-based activities, robotic and human lunar exploration, and planning for later expeditions to Mars and beyond, the Earth Science Applications Directorate at Stennis Space Center seeks proposals supporting NASA’s requirements for asset management. With proper physical infrastructure and information systems, identification tags should allow any item to be tracked throughout its life cycle. When combined with Earth and Lunar GIS, and related supporting documentation, any significant asset should be located, through time and space, as well as organization. Starting with programmatic requirements and design data, assets would be tracked through manufacture, testing, possible launch, use, maintenance, and eventual disposal. Innovative technology and information architectures should integrate and visually map infrastructure, assets, and associated documentation with the ability to link to program structure, budget, and workflow. Innovative solutions will facilitate information flow between the various NASA Centers and Programs. The system must maintain signature authority and restrict unauthorized moves. Ideally, if fully implemented, any remote item could be actively located throughout the NASA system with minimal delay. Any tagged item should be able to be queried at its location to retrieve associated records, e.g., maintenance, inspection, configuration management, chain-of-custody, engineering specifications, etc. A simple operator interface would provide “finger tip knowledge” about the asset. It should be possible to provide secure access to this information for both domestic and international partners. The proposed solution will minimize capital cost and human work effort required for inventory and tracking of nonconsumable assets, while exceeding the performance of current systems. Note that tagged assets may be subject to extreme environments in space and on Earth.
The innovation may eventually interoperate with a holistic information system, and may not preclude other uses for a terrestrial and lunar GIS such as:
- Operational infrastructure support AM/FM (automated mapping / facilities management)
- Asset and resource management, including waste disposal.
- Lunar landing and facility site selection, and optimization
- Conceptual site infrastructure and layout design
- Surface navigation
- Emergency response information
- A comprehensive portal for Earth and lunar mapping data, both image- and vector-based.
[back to top]
[ back to Solicitation ] [ back to Chapter 9 ][ back to Chapter 9.2 ][ back to table of contents ]