National Aeronautics and Space Administration
Small Business Innovation Research 2001 Program Solicitation

TOPIC H3 Space Utilities and Power

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H3.01 Thermal Control Systems for Human Space Missions
H3.02 Spaceport and In-Space Cryogenic Fluids, Handling, and Storage Technologies
H3.03 Spaceport/Range Instrumentation and Control Technologies
H3.04 Electromagnetic Physics Measurements, Control, and Simulation Technologies
H3.05 Space Solar Power For Human Missions
H3.06 Propellant Depots
H3.07 Space Nuclear Power For Human Missions

A key goal of the HEDS space utilities and power topic includes working with appropriate NASA and external organizations to identify and establish robust sources for abundant power for in-space and surface exploration systems for science discovery and the commercial development of space. A key objective is to drive down the cost of human/robotic exploration missions and campaigns. Some specific objectives include the following: (1) Development and validation of technology for a range of power levels and/or requirements, such as large space platforms, space transportation systems, including mobile, piloted or human-supporting lunar or planetary surface systems, and various other HEDS systems (e.g., habitats, extravehicular activity (EVA) systems, etc.). (2) Developing a foundation for the future testing and validation of key technologies and demonstrate innovative new human exploration and development of space systems concepts in space. (3) Establishing a foundation for profitable commercial development of space applications of these technologies in the mid- to far-term. Some of the specific technical objectives targeted by this topic include space solar power systems, space nuclear power systems for surface and in-space power applications, wireless power transmission systems, cryogenic propellant depots, and energy storage systems.

H3.01 Thermal Control Systems for Human Space Missions
Lead Center: JSC
Participating Center(s): MSFC

Thermal control is an essential part of any space vehicle as it provides the necessary thermal environment for the crew and equipment to operate efficiently during the mission. The requirements for human-rating and the specified temperature range (275 K - 310 K) drive the development of enabling active thermal control technologies to support human space exploration. A primary goal is to provide advanced thermal system technologies which are highly reliable and possess low mass, size and power requirements (i.e., reduced cost). Areas in which innovations are solicited include the following:

• Fault tolerant fluid-to-fluid heat exchangers that cannot fail in a way that permits leakage between fluid loops.
• Heat pumps to acquire waste heat at near 273 K and reject the heat above 300 K.
• Internal heat pumps or alternative technologies to provide cabin dehumidification on-orbit with a fluid heat sink of 288 to 298 K.
• Lightweight, flexible radiators which can be stowed compactly for transport and deployed for use.
• Micro-meteoroid tolerant and freeze/thaw tolerant radiators.
• Environmentally friendly, non-toxic single and two-phase working fluids that either freeze below 75 K or do not significantly change density upon freezing or thawing.
• Two-phase transport loops and associated controls which require low power for operations. Thermal energy storage systems.
• Controllable water evaporator heat rejection devices for use in vacuum environments.
• Microgravity compatible refrigerator/freezer technologies and/or system designs for food or scientific samples storage. Also, refrigerator/freezer technologies and/or system designs for long-duration planetary (partial gravity) usage.
• Low vibration or vibration isolating fluid components including fans, pumps, compressors, coolers, tubing, fittings, heat exchangers, and valves for use in microgravity processing applications.
• Highly accurate, remotely monitored, in situ, non-intrusive thermal instrumentation for meeting in-space science, manufacturing and safety needs.
• Materials and concepts for thermally efficient containment and processing of hazardous materials and samples in space.
• Advanced analytical tools for thermal design and analyses, which are amenable to concurrent engineering processes.
• Fluid quick disconnects that allow activation without exact alignment of the halves that have low activation force (approx. 10 lbf) with internal pressures of 500 psi, that are not sensitive to level 200 contamination, that leak less than 1x10^-6 sccs He at 500 psia over a temperature range of -100° F to +100° F and that can be used with ammonia, water or R-134a.

Proposers should indicate explicitly how their research is expected to improve the mass, power, volume, safety, reliability, and/or design and analyses techniques for future thermal control systems for human space missions as compared to state-of-the-art technologies.

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H3.02 Spaceport and In-Space Cryogenic Fluids, Handling, and Storage Technologies
Lead Center: KSC
Participating Center(s): GRC, JSC, MSFC

Advanced technologies are being solicited for cryogenic technologies for multiple aerospace applications. New and innovative techniques are desired in spaceport technologies, space environment applications, and extraterrestrial applications (lunar and Mars environments). These focus areas include technologies that will increase the performance, operational efficiencies, safety, and reliability of cryogenic systems and provide for autonomous cryogenic operations in Earth, space and extraterrestrial environments.

Planetary Spaceport Cryogenic Fluids, Handling and Storage Technologies
Advanced technologies are being solicited for spaceport cryogenic systems for conditioning, storage, densification (sub-cooling) of cryogenic propellants and transfer and control to improve operational efficiencies, safety and reliability, and enable autonomous loading and off-loading operations. Planetary spaceports include Earth, Moon and Mars applications. Extraterrestrial spaceport systems have an added emphasis for lightweight and highly reliable characteristics. Specific areas of interest include the following:

• Cryogenic pumping systems that minimize thermal losses and can be utilized in liquid oxygen and/or liquid hydrogen and other cryogenic systems. These systems should possess high reliability and demonstrate ease of maintenance.
• New technology valves for cryogenic applications, including LOX, LH₂, and LCH₄ that minimize thermal losses and pressure drops across the component. Components should be adaptable to electromechanical activation and in a size range from 1/2 to 5 inches.
• Leak-proof compliant cryogenic quick disconnects that can be reliably mated, de-mated, and re-mated under misalignment (15 degrees for connectors 1-inch and larger) and dusty/windy conditions. Smaller connectors (1/4-inch to 1-inch) that require a low connecting force (for Mars applications) are critical. Reconnect issues that must be resolved include thermal (potential icing), sealing (surface damage due to environmental contamination), and cleanliness (potentially imposed by wind, etc.).
• Leak-proof, easy to use cryogenic couplings utilizing robust sealing technology that are compatible with cryogenic temperatures and liquid oxygen.
• New and innovative technologies to provide for propellant densification (sub-cooled LH₂ and LOX). These technologies should provide for increased efficiencies and reduced costs associated in producing densified propellants.
• Recovery and storage system for gaseous hydrogen as vented from propellant storage (1000 gal/day) and/or during vehicle loading and drain-back operations (100,000 gal/day). Gaseous helium recovery (from hydrogen stream) is also desired.
• Propellant servicing mechanisms including umbilical alignment, latching, and release mechanisms which provide reliable and verifiable single and multiple connector mating, and enable autonomous loading operations. Integrated alignment and connection methods are desirable. Innovative latching technologies such as shape memory alloy applications and technologies that allow for maximum preload with minimal application loading are also desirable.
• A modular, reliable and cost effective oxygen and hydrogen production and liquefaction architecture are needed to enable production at an Earth based launch site. A modular system is desired to add/subtract capacity as needs fluctuate. Natural gas or coal as feedstock with a production ratio of 1 ton LH₂ to 10 ton LOX is desired. The system may also produce electricity and LN2 (poly-generation plant). Modules that can be idle for extended periods and then brought on line quickly (48 hours or less) are also desired.
• Flowmeters and densitometers for measurement of densified, multi-phase cryogen at flowrates from 1.4 to 5.6 liter per second.
• Energy efficient, cost effective distribution systems for transfer of cryogens over long distances (up to several miles in distance).
• Low heat leak, lightweight, electromechanical shut-off valves for LO2 and LCH4 applications in size ranges from 1 to 1.5 inches.
• Cryocooler systems with cooling capacity greater than 10 watts operating in the 20-40 K range.
• Efficient LH₂ storage systems for transporting LH₂ to Mars and storage on the Martian surface.

In-Space Environment Cryogenic Fluids, Handling and Storage Technologies
Components or concept proposals are being solicited to improve the performance, operating efficiency, safety and reliability of cryogenic fluid storage and handling in a low gravity (10^-6 g to 10^-2 g) environment. Tanks of high energy propellant fluids, stored in their most efficient state (as low pressure sub-critical cryogenic fluids), are required for spacecraft and orbit transfer vehicle propulsion and power systems and space station life support. Generally, applications of this technology require long term storage (> 30 days), on-orbit fluid transfer and supply and unique instrumentation. Technology innovations are required in the following areas:

• Lightweight, low thermal conductivity cryogenic tanks strut and support concepts
• Low thermal conductivity cryogenic tank penetrations, i.e., instrumentation feed-throughs, feedlines, vent lines
• Lightweight, insulating, thermal protection schemes
• Robust insulation concepts for multiple launch/landing and ambient/vacuum pressure cycles
• Devices for vapor-free acquisition of cryogenic liquids
• Small, low power, lightweight (2 liter/minute) liquid oxygen transfer pumps
• Tank pressure control (e.g., thermodynamic vent) and/or integrated tank boil-off control and product liquefaction technologies
• Lightweight mechanical fittings and flex hoses with low heat leak
• Autonomous cryogenic disconnects and couplings
• Instrumentation for monitoring cryogens in low gravity including mass quantity gauging, liquid-vapor sensing and free surface imaging

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H3.03 Spaceport/Range Instrumentation and Control Technologies
Lead Center: KSC
Participating Center(s): None

The goal of this subtopic is to develop instrumentation, systems and associated sensors required by Space-ports/Ranges to operate future generation space vehicles safely and efficiently. Technologies developed under this subtopic shall support the reduction of vehicle and payload cost per pound to orbit while increasing the safety of ground and flight operations by orders of magnitude.

The vision of the future is that multiple vehicles will be operating simultaneously in various phases of processing, launch, and landing from multiple terrestrial and planetary Spaceports/Ranges. In order to realize this, it will be necessary to have systems that integrate a suite of ground and space based sensors and instrumentation that provide the total Spaceports/Ranges solution. These systems need to be distributed and capable of supporting multiple sites and operational phases without reconfiguration. This will require autonomous knowledge based expert systems that can be implemented at multiple sites and require minimal infrastructure and personnel to operate.

This subtopic focuses on the development of sensors, instrumentation systems, meteorological and range technologies that uniquely suited to and used at Earth and planetary spaceports for processing, launch, tracking, controlling, and landing of space vehicles. The specific focuses are on sensors, transducers, instrumentation and systems that will be applied to the following areas:

Space Based Range
This focus area includes the development of technologies for satellite platforms or vehicles that provide remote sensing and instrumentation systems that perform or support the following functions: metric tracking, area surveillance, navigation aids, and atmospheric sensing. Each of these functions will require development of one or more of the following technologies; Integrated multi-, hyper-, and ultra-spectral instrumentation and sensors; Multi-channel transceivers. These will provide directors/controllers and vehicles vital real-time data that is necessary to interface with the National Airspace System for all phases of ascent and decent.

Decision Models and Simulation
New and innovative methods to ensure safe and cost effective real-time decision models that safely reduce conservatism and provide the necessary fidelity. Improvements in real-time computational capability and code development can significantly improve assessments. Specific technologies needed.

Range Dispersion Monitoring Instrumentation
Develop ground-based and airborne time-resolved real-time instruments to measure atmospheric chemical species associated with spaceport propellants and combustion products. Deployable instruments, both physical sampling and remote sensing, shall be capable of being networked to provide real-time data to a central processor for formatting and ingestion into a spaceport decision model. Sensors will be capable of identifying specific chemical species including hydrogen chloride, nitrogen dioxide, hydrazine (anhydrous, monomethyl, and unsymmetrical dimethyl), hydrocarbons, sulfur hexafluoride, and particulate matter.

Conflagration Decision Model: Heat and mass emission factors from solid propellant burning under water needs to be assessed and modeled. In addition to heat quenching, the chemical interaction of burning solid propellant and associated combustion products needs to be known as a function of water depth and salinity. The model output should yield mass and heat content of gaseous products including hydrogen chloride, solid products including particulate aluminum oxide and ammonium perchlorate, and liquid products including hydrochloric acid for unit mass of solid propellant involved, Unburnt propellant mass should also be assessed. Assessments are to be based on empirical studies using Space Shuttle-like solid propellants.

Decision Model On-Screen Editor
Develop methodology to enable on-screen editing of graphical outputs, such as meteorological parameters utilized in spaceport decision models. Shapes, slopes, and uncertainty bandwidths of curves should be automatically digitized based on operator on-screen inputs. This editing capability must allow the user to make changes to the forecasted toxic corridor in near real time. Methodology must execute with sufficient speed to accommodate user inputs, decision model reevaluations, and input refinements to assess decisions, consequences, and uncertainties. Source code and executable code must be provided for inclusion in various spaceport decision models.

Knowledge-based Database
Develop and document a knowledge-based database with the capability to automatically maintain itself. This will include self-editing, error correction, and automatic formatting and filing of ingested data. The database will automatically poll the remote sensors on a given time schedule, evaluate the data and flag those sensors not responding with the correct data. Any data outside the preset parameters will be adjusted to a best fit, flagged and filed automatically.

Command, Control and Monitoring
New and Innovative technologies that include real-time advisory systems for the operator's and the user's; data reduction, analysis, and archiving; configuration validation and management; and low cost high fidelity training capabilities that minimize impact to operational systems. There is additional focus on sensors, transducers and instrumentation systems uniquely suited for instrumentation test beds to be characterized as payloads on Space Shuttle or other future space vehicle flights or Ground Support Equipment.

Miniature Mass Spectrometers for Hazardous Gas Detection
Development is needed for small, lightweight, rugged, inexpensive, mass spectrometers or other technology capable of measuring one part per million to 100 percent of hydrogen, helium, nitrogen, oxygen, and argon in a high-vibration environment. These instruments will be used on and around space launch vehicles for leak detection during ground processing, test firings, pre-launch propellant loading, launch, ascent, and descent (post reentry). The primary improvements in technology and performance over current instruments are size and weight reduction, cost reduction, and operation in a high vibration environment. Current instruments typically fill one or more equipment racks, weigh several hundred kilograms, and must be operated in an air conditioned, vibration free environment, typically several hundred feet from the potential leak locations. Their cost, size, and complexity mandate that each instrument must sample multiple leak locations on a time-shared basis. The target cost of an operational version of the desired instrument is $5,000-$20,000 each. The needed instrument accuracy is plus or minus ten parts per million or 5 percent of reading, whichever error is greater. The instrument should possess mass resolution capable of meeting the desired accuracy goals for hydrogen in the presence of 100 percent helium and for oxygen in the presence of 100 percent nitrogen. The instrument should be less than 3500 cubic centimeters total volume and have mass less than ten kilograms, including high-vacuum pump. The instrument should be able to withstand an 18 G vibration over a range of 5-2500 Hz. for 15 minutes on each axis without damage. The instrument should be capable of meeting the specified accuracy requirements for twelve hours without calibration. It should be capable of analyzing all five specified gases and providing the concentration of each within one second. While advances are primarily sought in development of complete instruments, advances in key enabling technology such as vacuum pumps, ionizers, and detectors are also sought.

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H3.04 Electromagnetic Physics Measurements, Control, and Simulation Technologies
Lead Center: KSC
Participating Center(s): None

Spacecraft launch operations involving toxic and explosive vapors and solid propellants as well as the operation of electronic components in space and in extraterrestrial environments have created special concerns for understanding the electromagnetic dynamics of surfaces in contact with each other and the production of electrostatic charge due to this interaction. Specific interests for the 2001 solicitation include but are not limited to those listed below:

• Development of instrumentation to study the electromagnetic dynamics of surfaces in sliding contact with each other and its effects on the generation of electrostatic charge under a wide range of atmospheric conditions. Frictional contact between surfaces generates energetic electrons, ions, and photons. NASA is interested in instrumentation to measure the number and the type of the particles transferred as well the amount of mass transferred between surfaces after breaking contact. These instruments should be compact and light-weight and work under ultrahigh vacuum conditions (10^-12 Torr).
• Development of dust generators that would deliver 1 to 40 mm uncharged particles at speeds ranging from 10 to 30 m/s at atmospheric pressures ranging from 100 mTorr to 760 Torr and at temperatures ranging from -100° C to 20° C.
• Develop techniques for measuring the charge-to-mass ratio and the speed of dry particles (1 to 100 mm) under high vacuum conditions (10-12 torr) over a broad range of temperatures. These techniques must be capable of supporting the future development of the electromagnetic characterization of materials during exposure to dust impingement in a vacuum, atmospheric, and non-terrestrial atmospheric environments.
• Develop improved triboelectric charge measurement and decay test devices that will become part of new testing standards for protective clothing and other materials to be used in space, extraterrestrial and hazardous environments. Performance of the devices should be compared to similar data already collected by the Kennedy Space Center using existing technology. Proposals should focus on electric field detection equipment, digital scope electronics, air/gas ionization and motorized devices. Instruments and devices proposed for demonstration should be light weight, small in size, and suitable for operation in a vacuum with temperature ranges from -160° C (- 250° F) to 200° C (400° F), in various gaseous environments with pressures from 100 millitorr to 5000 torr and temperatures from -160° C (- 250° F) to 200° C (400° F) as well as terrestrial environments with temperatures from - 75° C (-100° F) to 65° C (150° F) and humidity from 10 percent to 100 percent. New concepts should give consideration to computer hardware and software to maximize capabilities to induce, detect, acquire, and record electric fields on material samples while plotting wave-forms in volts versus time.
• Development of miniature sensors for detecting and measuring the electric potential and charge distribution generated on spacecraft and landers. Developing software for modeling spacecraft and landers electric potentials based on previous flight experiment data and models.
• Develop cost-effective methods for ground based simulation of the environments of low Earth orbit space, deep space and planetary surfaces.

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H3.05 Space Solar Power For Human Missions
Lead Center: MSFC
Participating Center(s): None

The goal of this activity is to conduct preliminary strategic technology research and development to enable large, multi-megawatt Space Solar Power (SSP) systems and wireless power transmission (WPT) for government missions and commercial markets (in-space and terrestrial). Dramatic advances in solar power generation (SPG) are needed for in space and surface use including systems for 50-100 kWe, 100-1000 kWe, and 1-10 MWe. These systems are required for large-scale space utilities and many transportation options. Solar power generation research and development required for collection of solar energy and conversion to electrical energy are critical to meet the low cost/specific mass goals for HEDS missions. Systems approaches for the utilization of SSP concepts and technologies, ranging from the near-term to the far-term, including systems concepts, architectures, technology, infrastructure (e.g., transportation), and economics have been modeled and refined under NASA's Space SSP Exploratory Research and Technology Program. Also, under the program technology research, development and demonstration activities to produce proof-of-concept validation of critical SSP elements for both nearer and farther-term applications have been conducted. Existing investments will be harvested for near-term demos, while multiple research and technology paths for large SSP systems will be pursued.

Goal
New technologies for enabling megawatt-class, low-mass, extremely high voltage solar arrays for large space solar power applications, including transportation vehicles, orbital facilities, and surface infrastructures.

Technology Elements

• Solar power generation
• Wireless power transmission
• Power management and distribution (PMAD)
• Energy storage
• Structures, materials and controls
• Thermal management and materials
• Robotic assembly, maintenance and operations

Objectives

• Develop advanced SSP concepts that incorporate the above listed technology elements
• Develop various SPG concepts including photovoltaic concentrator systems, solar thermal dynamic concentrator systems and thin film systems
• Integrate information on scores of technology options across several different systems concepts
• Perform tightly focused research and technology activities targeting all poles and promising system concepts
• Develop initial small-scale demonstrations of key SSP concepts and components using nearer-term technologies

Tasks

• Develop advanced SSP system technologies
• Undertake required/beneficial technology demonstrations (e.g., solar electric transportation applications, SPG, WPT, etc.)
• Conduct technology development work in the areas of SPG; WPT; PMAD; energy storage; structures, materials and controls; thermal management and materials; and robotic assembly, maintenance and operations
  

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H3.06 Propellant Depots
Lead Center: MSFC
Participating Center(s): None

The focus of this subtopic is to develop and advance enabling technologies required to build and operate a propellant depot near Earth or in deep space. Cryogenic propellant storage depot technology is a unique area in that it has been studied in detail but little research has been accomplished in space, where the unique effects of low gravity come into play. The propellant depot will provide affordable propellants and similar consumables as needed in the development of space. A propellant depot not only requires technology development in key areas such as cryogenic storage or fluid transfer but in other areas such as lightweight structures, highly reliable connectors and autonomous operations. These technologies can be applicable to a broad range of propellant depot concepts or specific to a certain design. Specific areas of interest include:

• Electrolysis system that manufactures cryogenic propellants from water or ice in a low gravity environment. This system should incorporate innovative techniques and components to provide an automated, safe and highly reliable process.
• Water storage and transfer interface such as a bladder positive-expulsion system or other innovative techniques.
• Reliable and safe cryogenic storage for extended periods of time. This includes zero boil-off systems, advanced insulations and thermal control techniques such as vapor cooled shielding, systems utilizing the boil-off for drag make-up and innovative tank designs.
• Automated assembly, operations and maintenance. This includes cryogenic connects, disconnects and couplings; robotic assembly and repair; docking of large components; health monitoring and smart systems.
• Lightweight structures including inflatables, deployables and advanced composites.
• Micrometeoroid and space debris protection schemes and associated technologies including advanced lightweight materials, self-healing, integration with other structures and tankage and possible avoidance techniques.
• Associated propellant tank-set technologies including fluid slosh and orientation in low gravity environments, tank support structure dynamic interaction in orbit, support struts thermal performance, integrated insulation, instrumentation and plumbing penetrations and coating degradation.
• Schemes for warm tank chill down including spray nozzle configurations, liquid flow rate and duration, number of gas venting steps and performance in a low gravity environment.
• Stratification / hot spot management including mixing needs, mixing strategies and performance determination in low gravity environments.
• Low gravity performance and operating life determination of key components such as the liquid pumps, condensers, pressurization, liquid acquisition device, refrigerator and mass gauging instrumentation.
• Low heat leak valves and lines that are highly reliable with long life.
• Connects/disconnects with small or no fluid and heat leakage. The connects/disconnects should also have small pressure drops, small force and alignment requirements and long life with high reliability.
• Procedure for the capability for a no-vent fill with consideration given to micro-g condensation and fluid mixing.

Several options are available to test the technology needed for propellant depots. Technologies can be tested in the laboratory, on Expendable Launch Vehicles, the Space Shuttle, the ISS, a Small Scale Depot, or a Full Scale Depot. Laboratory testing can use sub- or full-scale tank sets for tests carried out on components, subsystems, and integrated systems on the ground. Identified improvements can be incorporated into subsequent tank sets, which may be used on the ground or in orbital tests. In some cases, a "proto-flight" approach may be used, where the original ground-test tank set can potentially be modified for subsequent testing on-orbit. For example, test requirements may be addressed by building a subscale experiment, which simulates the hydrogen fluid systems of the storage facility, evaluating their performance in a vacuum chamber, and then demonstrating micro-g fluid transfer by performing an orbital experiment.

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H3.07 Space Nuclear Power For Human Missions
Lead Center: GRC
Participating Center(s): MSFC

Space Nuclear Power
NASA is interested in the development of highly advanced systems, subsystems and components for use with both nuclear reactors and radioisotopes for future robotic and manned missions. Principally, these systems of interest are non-nuclear; however, they may operate in close proximity to nuclear sources. Anticipated power levels range from 100's of watts to multi-megawatts. Applications include: in-space primary propulsion, vehicle housekeeping, and science payloads, and on planetary surfaces; surface and atmospheric mobility, science stations, resource production, outposts and bases. Major technologies being pursued are:

• High efficiency power conversion > 20 percent, 2 kWe to MWe
• Low mass thermal management (radiators) < 6 kg/m²
• Electrical power management, control and distribution. > 1000 V, kWe to MWe

Supporting technology includes:

• High temperature materials/coatings > 1300 K
• Deployment systems Large radiators, surface mobility,
• Systems to mitigate planetary surface environments. (Dust, wind, planetary atmospheres, CO₂, etc.)

In addition to overall system mass, volume and cost reductions, safety and reliability are of extreme importance. It is envisioned that these technologies will be used on robotic and eventually human missions, and it is to the Agency's advantage to develop those technologies that transcend the robotic and human mission set with a minimum or redesign. Technologies that enable challenging missions such as bimodal nuclear thermal propulsion, high power nuclear electric propulsion and high power surface power are of particular interest. Technologies that are easily and efficiently scaled in power output and can be used in a host of applications (high commonality) are desired.

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