National Aeronautics and Space Administration
Small Business Innovation Research 2002 Program Solicitations
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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 Wireless Power Transmission
H3.06 Propellant Depots
H3.07 Space Nuclear Power For Human Missions
H3.08 Vibroacoustic Prediction and Simulation Technologies
H3.09 Spaceport Command, Control, and Monitor Technologies
H3.10 Solar Power Generation and Power Management
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, 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 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, 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.
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:
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.
Advanced technologies are being solicited for cryogenic systems for multiple aerospace applications. New and innovative techniques are desired in spaceport technologies, space environment applications, and extraterrestrial applications (lunar & 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
Innovative technologies are being solicited for storage, handling, distribution and recovery systems for new spaceport cryogenic facilities. Desired features include: improved operational efficiencies, increased safety & reliability, autonomous loading and off-loading operations and recovery of high value waste gases. Extraterrestrial spaceport systems have an added emphasis for lightweight and highly reliable characteristics. Specific areas of interest include the following:
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. Innovations are required in the following areas:
H3.03 Spaceport/Range Instrumentation and Control Technologies
Lead Center: KSC
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 Range 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 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 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.
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 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:
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.
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 electromagnetic 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 2002 solicitation include, but are not limited to, those listed below:
H3.05 Wireless Power Transmission
Lead Center: MSFC
The goal of this activity is to conduct research for Space Solar Power Wireless Power Transmission (WPT) technology development to reduce the cost of electrical power and 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 road-map 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.
Technology Elements
Objectives
Tasks
H3.06 Propellant Depots
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. 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:
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.
H3.07 Space Nuclear Power For Human Missions
Lead Center: GRC
Participating Center(s): JSC, MSFC
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: electric power for in-space propulsion, vehicle housekeeping, and science payloads, and on planetary surfaces; 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 impor-tance. 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 of redesign. Technologies that enable challenging missions such as, electric power production for bimodal nuclear thermal propulsion, nuclear electric propulsion, 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.
H3.08 Vibroacoustic Prediction and Simulation Technologies
Lead Center: KSC
The launch acoustic and vibration environment induced by a rocket engine imposes severe conditions on the launch pad infrastructure. Nearby structures and equipment subjected to these intense environments must be designed to withstand them. The problem is that the environments are non-stationary and random while existing design methods attempt to utilize stationary models of the worst conditions to describe them. An important consideration in the development of all foreseeable future launch vehicles is cost. Yet the inherently conservative design approaches used lead to costly structure and equipment designs. This problem is compounded by a lack of knowledge of the environment induced by a launch vehicle being designed at the same time as the launch facility. This has in many cases lead to overbuilt facilities and poor design due to improper accounting for the launch environment.
Specific interests for the 2002 solicitation include developing tools for analytically simulating the launch acoustic environment and its vibration effect on launch pad structures and equipment. The response of the types of structures normally encountered on launch pads such as open trusses, frames, concrete slabs and beams, and corrugated metal enclosures are of particular interest from the response viewpoint. From the acoustic and potentially overpressure environment determination viewpoint, tools that can be used to analytically predict the environment for any generalized launch pad design are sought. Typical launch pad designs will look at issues like covered versus uncovered exhaust ducts or trenches, active and passive acoustic and overpressure suppression systems, and exhaust plume deflector geometries, so the prediction tools should address one or more of these.
In conjunction with the analytical tool developments described above, it will be necessary to verify tool results. These verifications can take advantage of either full or sub-scale data. Technologies for generating sub-scale test data to verify analytical tools and assess their applicability to full scale problems are also sought.
H3.09 Vibroacoustic Prediction and Simulation Technologies
Lead Center: KSC
The goal of this subtopic is to promote the development of intelligent command, control and monitoring systems, vehicle health monitoring systems and associated sensors required by Spaceports to operate future generations of 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. In order to realize this, it will be necessary to have systems that integrate a suite of ground resources and instrumentation that provide the total Spaceport 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 highly flexible and reliable command and control system architectures, sensors, and instrumentation systems, that are uniquely suited to and used at Earth and planetary spaceports for mission planning, processing, launch, controlling, and landing of space vehicles. The specific focuses are on sensors, transducers, instrumentation and control and monitor systems hardware and software that will be applied to the following areas of command, control, and monitoring:
H3.10 Solar Power Generation and Power Management
Lead Center: GRC
Over the last thirty years NASA has periodically investigated the feasibility of large-scale space solar power systems including possible solar power satellites that could deliver power to space and terrestrial locations by wireless transmission for both government missions and commercial markets. "Large-scale" is defined as providing power to a user in the range from 1 megawatt (MW) to approximately 1 gigawatt (GW) or more. Previous concept definition efforts have determined that Space Solar Power (SSP) system performance goals (for space science and exploration as well as commercial applications) could potentially be accomplished through pursuit of focused strategic technology development efforts. A similar approach is intended with this effort.
Dramatic advances in a wide range of space technologies are needed in order to achieve the necessary breakthrough improvements in diverse space systems needed to make SSP systems feasible. New systems concepts must be created and refined which incorporate existing and new technologies in revolutionary ways. This opportunity has the intent to explore options for, and the viability of, highly innovative new concepts and technologies that might dramatically lower the cost and increase performance of critical SSP technologies/systems in the areas of Solar Power Generation and Power Management and Distribution.
Power Generation
Photovoltaic Cells and Arrays: Proposal efforts could include technology development, studies and demonstrations in the areas of innovative solar cells, solar array blanket technology and array structural and deployment methods. Concepts are sought which, at the multi-kilowatt level and in the near term, could enable total array specific powers to exceed 500W/kg. High voltages are required with sustaining operating voltages up to 1000 volts dc. Array designs should have the potential to achieve total array specific powers of 1000 W/kg or more at the multi-hundred kilowatt to MWe output level. 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 multi-MWe output levels at costs consistent with the economic viability of a large SSP system 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 spectrum splitting concentrator concepts (with up to 100x concentration), multi-quantum well and multi-quantum dot concepts, advanced multi-band gap schemes, and thermophotovoltaics.
High-Voltage Arrays/Arc Mitigation: Lightweight, high power, high efficiency solar arrays are absolutely necessary for SSP; most concepts also require high voltages. However, high power, high voltage arrays in various 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 the following:
Power Management
Power Distribution: NASA is interested in components and systems for distributing megawatt levels of electric power in large satellite systems. Preliminary studies have identified the following key technology studies and demonstrations:
High-Temperature Semiconductors for PMAD Systems: NASA is interested in high-temperature, power semiconductors for use in high-voltage DC-DC converters. To reduce the weight of heat rejection systems our studies have indicated that 300oC chassis temperatures are required. NASA is seeking proposals to demonstrate technology readiness in both silicon carbide and gallium nitride semiconductors. 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 and Health Management: Fault management through autonomous control will be necessary for future SSP 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.
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