National Aeronautics and Space Administration
Small Business Innovation Research & Technology Transfer 2003 Program Solicitations

TOPIC F3 Space Utilities and Power

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F3.01 Thermal Control Systems for Human Space Missions
F3.02 Spaceport Cryogenic Fluids Handling and Storage Technologies
F3.03 Spaceport/Range Instrumentation and Control Technologies
F3.04 Electromagnetic Physics Measurements, Control, and Simulation Technologies
F3.05 Wireless Power Transmission
F3.06 Propellant Depots and In-Space Cryogenic Fluids, Handling and Storage
F3.07 Spaceport Command, Control and Monitor Technologies
F3.08 Solar Power Generation and Power Management
F3.09 Power Technologies for Human Missions


A key goal of the 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, surface and transportation systems for human exploration and the commercial development of space. In additional another key objective is to drive down the cost of human/robotic exploration missions and campaigns. Some selective specific objectives include 1) development and validation of technology for a range of power levels and/or requirements, such as - Large space platforms - Space transportation systems for human exploration and space development - Mobile, piloted or human-supporting lunar or planetary surface systems, and - Various other 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, and 3) establishing a foundation for profitable commercial development of space applications of these technologies in the mid- to far-term. Some of the 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 - Energy Storage Systems

F3.01 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:


Offerors 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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F3.02 Spaceport Cryogenic Fluids Handling and Storage Technologies
Lead Center: KSC
Participating Center(s): GRC, JSC, MSFC

Cryogenic systems are essential for a variety of aerospace applications, including Earth based spaceports (EBS) and extraterrestrial bases(ETB). Each application has unique performance requirements that need to be met. Sizes of these systems range from the small (100 l for Mars consumables) to very large (>3400 m3 for Earth based launch systems). Advanced cryogenic technologies are being solicited for all these applications. Proposed technologies should offer enhanced safety, reliability, or economic efficiency over current state of the art, or should feature enabling technologies to allow NASA to meet the goals of the Space Flight Enterprise. Earth based systems should focus on enhancing technologies to minimize recurring costs. Extraterrestrial systems should focus on enabling technologies that maximize efficiency and minimize system mass and power. Technology focus areas are divided as follows; passive systems, storage and distribution components, refrigeration systems, advanced instrumentation, and advanced operational concepts. Intended applications are listed following each focus area solicitation.

Passive Systems
Passive systems are required to minimize heat leak into cryogenic storage and distribution systems for the purpose of extending propellant storage life and decreasing transfer line losses. Proposed systems can include insulation as well as advanced materials and mechanical supports. Space applications should feature extremely low levels of heat leak to allow for long term storage of cryogens and minimization of refrigeration power. Earth based systems should focus more on a balance between simplicity and robustness vs efficiency to achieve a minimum operational cost.


Storage and Distribution Components
Innovative designs for systems components such as shut-off and flow control valves, pumps, compressors, relief devices, couplings, etc.. that minimize thermal and fluid loss and maximize operational effectiveness. Earth based systems are generally larger and should be optimized for robust operations with many cycles. Extraterrestrial systems should be optimized for low mass, high efficiency, and long life with less cycles and minimum/no maintenance.


Refrigeration Systems
Active thermal control systems to cool gasses and liquids for the purpose of liquefaction, zero boil-off, and densification of cryogens. Space systems should enable the development of small scale flight quality cryocooolers optimized for long life, low mass and high efficiency. Earth based systems should focus on integrating active thermal control systems with storage and distribution systems for increased reliability and operability while maximizing economic efficiency.


Advanced Instrumentation
Instrumentation designed to provide pressure, temperature flow rate, composition, and liquid level data as well as to monitor the health of system components.


Advanced Operational Concepts
Advanced cryogenic systems concepts, including all phases of cryogenic use from production, liquefaction, delivery, storage, control and transfer.


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F3.03 Spaceport/Range Instrumentation and Control Technologies
Lead Center: KSC
Participating Center(s): GSFC, JSC

The goal of this subtopic is to develop instrumentation, systems and associated sensors required by Spaceports/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 communications technologies that are uniquely suited to Earth and planetary spaceports for the 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
Development of technologies for instrumentation systems that perform, or support the following functions on satellite platforms or launch vehicles: metric tracking, area surveillance, navigation aids, communications 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, low power, spectrum efficient transceivers high gain antennas. These technologies will provide directors, controllers and vehicles vital real-time data that is necessary to safely interface with the National Airspace System for all phases of ascent and decent.

Search and Rescue (SAR) Technologies
As a participating agency of the National Search and Rescue Plan and a member of the National Search and Rescue Committee (NSARC), NASA supports SAR technologies and application of aerospace technology for the search, rescue, survival, and recovery of victims of distress as a result of land, sea and air incidents. These incidents are predominantly accidental in nature. However, with the occurrence of 9/11, it is recognized that NASA may be called upon to provide technology for SAR in response to Homeland Defense.

Distress Alerting: SAR communications, distress alerting will soon undergo a major improvement with the addition of the Distress Alerting Satellite System (DASS). The DASS system leverages on the use of the GPS satellite constellation by utilizing the system's slightly modified on-board repeaters. A Proof-of-Concept system is currently being developed for DASS. Once proven, DASS will evolve to greatly compliment the existing Cospas-Sarsat satellite system and will be compatible with existing 406 MHz beacons. Areas in which innovative research is particularly sought in communications for SAR distress alerting are:


Low cost enhancement of 406 MHz distress beacons: It is desired to improve basic 406 MHz beacon protocols while remaining compatible with the existing Cospas-Sarsat satellite system and utilizing the DASS under development. Proposals should include but not be limited to:


Remote Sensing for SAR: Where beacons have either failed in the incident or were not properly utilized, innovative research in portable low cost remote sensing instruments are sought. These must be capable of locating downed aircraft, vessels in distress or incapacitated individuals based on the spectral, spatial or polarization characteristics presented by the target to be discriminated from its surroundings. Current remote sensing systems under study include active sensors, Synthetic Aperture Radar for Search and Rescue (SAR2) and Laser-Search and Rescue (L-SAR).

Techniques capable of supporting interactive analysis and target recognition in airborne polarimetric SAR at foliage penetrating wavelengths: Polarimetric SAR employs simultaneous horizontal and vertical polarization transmit and receive modes. This provides four independent channels that provide significantly more information than a traditional detected (amplitude) SAR image. SAR operation at P-Band or UHF frequencies provides significant foliage penetration and the ability to detect plane parts otherwise obscured by foliage. One significant problem in crash site detection is that traditional automatic target recognition approaches using modeling and templates may not work since the crash geometry is unknown. It is thus necessary to fully exploit the polarimetric information and to additionally infer from the structure and/or neighboring returns whether it is a candidate crash site. Proposals should develop the needed methodologies and plans for a prototype inferential system capable of exploiting polarimetric, foliage penetrating SAR data for crash site detection, along with a Concept of Operations for its employment.

Techniques to support interactive analysis of spectral/polarization signatures of targets using Hyperspectral instruments: As a member of NSARC, the Civil Air Patrol has expressed a need to apply Hyperspectral imaging for Search and Rescue. Proposals should describe innovative methods to address the following Hyperspectral instrument requirements for Search and Rescue:


Automated Multiple Object Optical Tracking and Recognition System
Develop an automated optical multiple-object tracking and object recognition system to be used during the early stages (first 2 minutes) of a vehicle's ascent. Applying image processing techniques to a wide area view should reduce operational costs compared with radar-based tracking systems and provide more information during a catastrophic event. This system would provide critical position data in near real-time for recovery and analysis of objects of interest. Solutions provided from this capability would be utilized for analysis of nominal or catastrophic events that may occur during a launch operation.


Decision Support Instrumentation and Models
New and innovative methods are needed 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 software 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.

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.

Measurement of Chemical Species in Hypergolic Propellant Systems
Propulsion systems for manned spacecraft use highly reactive propellants in space whose performance can be significantly effected by the presence of impurities, often at the part-per-million level. These result from the reactivity of the propellant with materials of construction of the propellant manufacturing facility, the spacecraft propellant supply system, the ground storage system, and exposure to air or other accidentally introduced impurities. Examples of problems from impurities include the flow decay of nitrogen tetroxide caused by iron nitrate adduct formed from attack on stainless steel by nitrogen tetroxide and the degradation of silver solder on the Shuttle tank screens caused by contamination of the monomethylhydrazine ground supply system.

To detect these contaminants or impurities, sensors are sought that can survive the highly reactive environment of the propellant hydrazines and/or nitrogen tetroxide while providing accurate, real-time information on the presence and concentration of specific contaminants. These sensors could be employed on ground-based propellant storage facilities, in the spacecraft propellant supply systems, or in propulsion test systems to monitor the changes in the propellants when subjected to known sources of contamination.

Specific contaminates of interest include, but are not limited to, those listed below:


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F3.04 Electromagnetic Physics Measurements, Control, and Simulation Technologies
Lead Center: KSC
Participating Center(s): JSC

Spacecraft launch operations involving toxic and explosive vapors, liquid and solid propellants, as well as the operation of electronic components on the ground, in space, and in extra-terrestrial environments have created special concerns for understanding the dynamics of surfaces in contact with each other as well as the production and dissipation of electrostatic charge due to this interaction. These concerns are of crucial importance to NASA in the fabrication, processing, launch, and safe operation of unique and expensive spacecraft launching from Earth as well as from other planetary surfaces.

Specific interests for the 2003 solicitation include, but are not limited to, those listed below:


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F3.05 Wireless Power Transmission
Lead Center: MSFC

This activity has two related goals. The first goal of this activity is to conduct research for Space Solar Power (SSP) Wireless Power Transmission (WPT) technology development to reduce the cost of electrical power and to provide a stepping stone to NASA for delivery of power between objects in space, between space and surface sites, between ground and space and between ground and air platform vehicles. WPT can involve lasers or microwave along with the associated power interfaces. Microwave and laser transmission techniques have been studied with several promising approaches to safe and efficient WPT identified. These investigations have included microwave phased array transmitters, as well as visible light laser transmission and associated optics. Within the roadmap of SSP WPT there is a need to produce "proof-of-concept" validation of critical WPT technologies for both the near-term as well as far-term applications. These investments will be harvested in near-term beam safe demonstrations of commercial WPT applications. Proposals are sought that include such activities as the technology elements, architecture, and demonstration program for wireless transmission of power. Receiving sites (users) include ground-based stations for terrestrial electrical power, orbital sites to provide power for satellites and other platforms; and space-based sites for spacecraft and space vehicle propulsion.

The second goal of this activity is conduct research on any and/or all aspects of using lasers to remove orbital debris in the 1-10 cm size regime to reduce associated costs while increasing capability. Traveling at hypervelocity’s, there exist approximately 150,000 objects this size distributed nonuniformly over a range of altitudes from 400 km to 1500 km. These objects represent a significant environmental hazard for spaceflight. A laser pulse of sufficient intensity striking an object ablates a thin layer of material from its surface resulting in a small, but finite orbit change. Many pulses per second for several minutes at the appropriate point in the object’s orbit lowers perigee sufficiently for atmospheric capture and object termination. The key technologies for this approach are the laser beam director and associated technologies; the sensors subsystem and associated technologies for detecting and tracking the object while on orbit; and the system integration process employed. The laser and/or sensors may be located either on the ground or in space. The Project Orion study and other related literature references have found that there are a number of feasible laser and associated sensor, technical and cost options for completely removing 1-10 cm debris up to 1500 km. Crucial to success is a robust systems integration process for synergistically using diverse technologies. Emerging new technologies both in lasers and associated sensors are expected to enhance these initial findings. Research proposals are sought across the board in this area and may take any combination of the following approaches: theoretical analysis, simulation, experimentation, systems and subsystem’s design, and/or demonstrations.

Technology Elements

Objectives

Tasks

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F3.06 Propellant Depots and In-Space Cryogenic Fluids, Handling and Storage
Lead Center: MSFC
Participating Center(s): GRC, JSC

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. In-Space cryogenic or gel propellant storage depot technology is quite unique, in that it has been studied in detail but little research has been accomplished in space, where the effects of low gravity come into play. The in-space propellant depot will provide affordable propellants and similar consumables as needed in the development of space. An in-space propellant depot not only requires technology development in key areas such as cryogenic or gel storage and 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. Also, these technologies 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. 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. Specific areas of interest include:


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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F3.07 Spaceport Command, Control and Monitor Technologies
Lead Center: KSC
Participating Center(s): MSFC

Spaceport Command, Control and Monitor Systems need to be able to support both the evolving role of spaceports and ranges, as well as the eventual requirements of next generation spacecraft. Some of the technology areas are required to support the concept that spaceport processing systems may not be located on the surface of the Earth, but may reside on an orbiting space station or on the surface of the Moon or Mars. To that end, traditional Command and Control Systems that are developed for a specific vehicle will have to evolve into systems that are adaptable and can communicate with multiple potential vehicles and at multiple spaceports. The following topics require work:

Sensors / Connection / Data Acquisition / Communication
Computing Hardware / Architecture
Advanced Software / Interfaces
End Item Control / Health Monitoring / State Determination / Simulation

Sensor / Connection / Data Acquisition / Communication
Traditionally, sensor systems have been less reliable than the systems that they monitor. In addition, intrusive sensing adds additional failure modes. NASA is seeking improvements in sensor technology, specifically aimed at non-intrusive sensing techniques. In addition, new technology that replaces mechanical sensors is desired. Technology that supports smart sensors, including sensors that perform qualification, integrity checking, self identification and may know their history such that they know when they are operating in a degraded mode, is needed to support health management.

Wiring and interconnects continue to be a maintenance problem as spacecraft and spaceports age. In addition, wiring weight, and cost continue to be a hindrance to Integrated Health Management. Development on Wireless, or self-healing wired technology that supports health monitoring is desired.

Another area of interest is in Automated inspection. Technology areas from new or multiple sensing capabilities to the automated and autonomous control system that would allow non-intrusive inspections are of interest.

Computing Hardware / Architecture
In the spaceport operational concept, integrated spacecraft checkout would occur both at a ground-based spaceport as well as a space-based or other non-terrestrial spaceport. To achieve desired efficiencies, the same software should be used at any spaceport. This leads to the need to evaluate concepts and architectures for software that may be mobile between the spacecraft and the spaceport and operate at an appropriate level of abstraction that the differences between terrestrial and non-terrestrial spaceports can be hidden.

Explore the architecture for mobile software that would support service discovery and remote execution in support of future spacecraft / spaceport interaction.

Explore the best network technology for spaceport / spacecraft communications that meets all the criteria for active operations during all mission phases. This network connection must support umbilical separation and re-mating, in addition to existing lightning and space radiation effects.

Advanced Software / Interfaces
In the spaceport concept of mobile software between spacecraft and spaceport, software concepts and techniques must be developed and refined to support mobile heterogeneous systems in a critical role.

Evaluate the use of Java or other languages that support mobile software between heterogeneous systems that could be used for both a terrestrial and space based spaceport processing system. On a real-time spaceport processing system, consider that the system must be stable, responsive and support remote operation.

Development of a set of standards that allow mobile software in a heterogeneous system to execute on a platform independent basis, move between systems and query the host system or set of systems for the services and capabilities available is desired to support future spaceport processing systems.

Investigate Loss-Less Telemetry compression and improved security algorithms for spacecraft to spaceport communication that maximizes measurement throughput over existing bandwidth capabilities.

End Item Control / Health Monitoring / State Determination
End Item Control has always been by its nature specific to each system. The types of process control that is performed to service a spacecraft at a spaceport can be reduced in scope and made generic such that one set of End Item Control software could be developed for any number of spacecraft and spaceports.

Evaluate the best abstraction technique to develop a common set of software to support spaceport and spacecraft servicing operations.

Evaluate a structured software specification language that provides a readable reference by non-computer software professionals and adequately describes programming constructs such that process control (both procedural and reactive) can be automatically generated.

Evaluate techniques for automated software test and validation of the automatically generated software, including test coverage of logic paths. Tests that can be developed from the same specification that generated the software is desired.

Advanced simulation techniques that could be utilized to support development testing of spaceports and spaceport processing systems is needed. The capability should be evolvable to be utilized in real-time to support decision analysis and improved situational awareness.

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F3.08 Solar Power Generation and Power Management
Lead Center: GRC

NASA is interested in the development of highly advanced solar power generation and power management systems, sub-systems and components for use in spacecraft of power levels ranging from 10kW -1MW. This opportunity has the intent to explore options for, and the viability of, highly innovative new concepts and technologies that might dramatically increase performance, improve environmental robustness and lower the cost of critical technologies/systems. Proposals should focus on incorporation of modular and scalable techniques which allow the use of technologies across a wide range of power levels.

Solar Power Generation
Proposal efforts for photovoltaic cells and arrays could include technology development, validation, studies and demonstrations in the areas of innovative solar cells, solar array blanket technology and associated array structure and deployment methods.

Cell and blanket technology shall have the potential for significant cost reduction compared to state-of-the-art space qualified arrays at these sizes. Technology advances needed to achieve MWe output levels at costs consistent with the economic viability of large space power systems should be identified. For example, innovative processes for thin film solar array manufacture. Other areas of interest include demonstration of high efficiency, lightweight concentrator cell and array designs, multi-bandgap cells, advanced concentrator concepts (with up to 100x concentration), multi-quantum well and multi-quantum dot concepts and advanced multi-band gap schemes.

Concepts are sought at the 10 - 100kW levels which, within 10 years, could enable total array specific power to exceed 300W/kg for the missions of LEO, GEO and beyond. Array designs at the multi-hundred kilowatt to MWe output level should have the potential to achieve total array specific powers of 500 W/kg or more.

Lightweight, high power, high efficiency solar arrays are absolutely necessary for large space platforms. Most concepts also require high voltages however; high power, high voltage arrays in specific Earth orbits are subject to continuous arcing, which can destroy lightweight substrates. Therefore, enabling research and technology development and/or demonstrations are needed that leads to operational array voltage level of 1000 v which are resistant to radiation damage and arcing voltages up to 10 kV. Proposals should have provisions for verification in ground-based plasma chambers and/or space flight experiments

Power Management
NASA is interested in scalable, modular components and systems for distributing up to megawatt levels of electric power in satellite systems. Preliminary studies have identified the following key technology areas for studies and demonstrations:

NASA is interested in high-voltage DC-to-DC converters, initially investigating designs for accommodating at least 1000 volt distribution with a clear evolution path for growing to 10k-volt systems. Proposed designs should consider a modular switch and transformer combination that allows for multiple increments of input voltage and current as well as multiple increments of output voltage and current.

To reduce the weight of heat rejection systems, studies have indicated that 300°C converter chassis temperatures are required. NASA is seeking proposals in high-temperature, power semiconductors for use in high-voltage DC-DC converters. Proposal topics include, but are not limited to defect-free epitaxy, dynamic characterization, space radiation hardness, device packaging to sustain simultaneous high voltages and temperatures, life prediction and thermal management.

Intelligent power controls, fault and health management through autonomous control will be necessary for future large space power systems. Concepts and demonstrations of such components and systems are requested to enable development of intelligent controls which will sense/detect faults, shut down affected regions and re-route power to maintain operations. Self-healing concepts are sought which allow the system and components to maintain high reliability. Detection and reporting of failures due to the environment (micrometeoroids) or component breakdown will have to be a part of the system. Materials that can recognize failures and initiate self-correction are of interest.

Concepts for cabling, switches, distribution units and current-limiting switches housed in distribution units with the capability of handling systems of up to 100k volts are required for achieving efficient power management in large spacecraft. Proposals should focus on development of revolutionary approaches to reduce overall system mass by incorporating scalable and modular techniques.

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F3.09 Power Technologies for Human Missions
Lead Center: GRC
Participating Center(s): JSC, MSFC

Advanced concepts are required for current and future NASA missions that improve the performance of the power system and/or reduce the overall costs while improving the high degree of reliability and safety required for human-rated vehicles. NASA needs innovative developments in power technologies in the areas of static and dynamic power conversion from either reactor, isotopic or solar heat sources, photovoltaics and other direct conversion devices, energy storage, and power management and distribution and diagnostics and autonomous control systems which are capable of meeting the safety and reliability requirements of missions of human space flight.

NASA is interested in the development of highly advanced systems, subsystems and components for use with nuclear reactors, radioisotopes and solar power generation for future precursor and human missions. Principally these systems of interest are non-nuclear, however they may operate in close proximity to radiation sources. Anticipated power levels range from 100's of watts to multi-megawatts. Applications include: electric power for in-space propulsion, vehicle housekeeping, and science payloads, surface and atmospheric mobility, science stations, resource production, robotic outposts and human bases.

Major technologies being pursued are:

Supporting technology includes:

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 easily bridge the gap of robotic to human missions with a minimum of redesign.

Technologies that enable challenging missions such as, electric power production for bimodal nuclear thermal propulsion, high-power nuclear electric propulsion, crew vehicle power and planetary surface power are of particular interest. Technologies that easily and efficiently scale in power output and can be used in a host of applications (high commonality) are desired.

Another focus for human space flight is supplying power for vehicle crew life support and for suits and tools. Most likely future missions will employ separate crewed vehicles will be used to descend and ascend from planet surfaces to the space transfer vehicle in orbit. For example, a Mars lander may need to be self-sufficient (survive on stored energy) for some extended period of time before the prime source of surface power is supplied. Smaller systems will be required for suit life support power and hand tools where energy storage systems are the most practical solution. Such solutions are also of interest for nearer-term human missions on the ISS, Shuttle, or Orbital Space Plane.

Innovative concepts are solicited to advance the technology of fuel cell power plants and associated planetary in situ reactant production plant subsystems, such as high temperature electrolyzers.

Technologies of interest include proton exchange membrane fuel cells, solid oxide fuel cells, integrated or separate reformers, and other advanced concepts that can provide notable improvements in conversion efficiency, operational life, reliability, load following performance, and mass/volume power density (W/kg and W/l). Oxidant streams of interest are focused on near-pure oxygen, but fuel streams of interest include near-pure hydrogen and reformate from near-pure hydrocarbons such as methane, ethanol, and methanol. Applications of interest for these systems encompass a range, from small power plants (~10 W) for in-cabin crew equipment, through mid-range ~10 kW for vehicle avionics, to high power (~70 kW, 270 V) systems applicable to electromechanical actuation for vehicle flight control.

In addition, concepts are solicited to advance the technology of primary and secondary (rechargeable) batteries. Of special interest are new technologies, which could exploit the advantages in cost, energy density (W-hr/kg and W-hr/l), and reliability that may be possible with larger batteries built up from many small cells in series and parallel. Technologies of interest include lithium ion, lithium polymer, and other advanced concepts that can provide dramatic increases in energy density and rate capability while maintaining safety and reliability levels appropriate to in-cabin and exterior applications on crewed vehicles.

The applications of interest range from in-cabin crew equipment like cameras, tools and computers to large vehicle support systems, from low (<1C) to high (20C) discharge rates, and from low (100 W-hr) to high (100 kW-hr) capacities.


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