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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 415 records · Page 23
All sourcesNASA NTRSDOE OSTI
NASA NTRS2010

Integration of Ares I-X Ground System Modifications with Space Shuttle Operations

This discussion will focus on the development and implementation cycles and their respective challenges of accommodating and integrating with Space Shuttle Operations. There is a difference during the development and implementation cycles while trying to still operate an ongoing program within the same facilities and infrastructure. Due to this unique environment requirements are generated from outside Ares I-X that have significant impacts on design and implementation of those designs. Impacts are technical, schedule, and cost. So in this unique environment besides dealing with changing test flight vehicle changes the system (hardware and team members) must be flexible enough to accommodate operational and manifest changes while still maintaining delivery and performance requirements. The purpose of this session will be to highlight some of these challenges and identify the lessons learned from this experience.

Stover, Billy R.↗
NASA NTRS2012

A Comparative Study of Interval Management Control Law Capabilities

This paper presents a new tool designed to allow for rapid development and testing of different control algorithms for airborne spacing. This tool, Interval Management Modeling and Spacing Tool (IM MAST), is a fast-time, low-fidelity tool created to model the approach of aircraft to a runway, with a focus on their interactions with each other. Errors can be induced between pairs of aircraft by varying initial positions, winds, speed profiles, and altitude profiles. Results to-date show that only a few of the algorithms tested had poor behavior in the arrival and approach environment. The majority of the algorithms showed only minimal variation in performance under the test conditions. Trajectory-based algorithms showed high susceptibility to wind forecast errors, while performing marginally better than the other algorithms under other conditions. Trajectory-based algorithms have a sizable advantage, however, of being able to perform relative spacing operations between aircraft on different arrival routes and flight profiles without employing ghosting. methods. This comes at the higher cost of substantially increased complexity, however. Additionally, it was shown that earlier initiation of relative spacing operations provided more time for corrections to be made without any significant problems in the spacing operation itself. Initiating spacing farther out, however, would require more of the aircraft to begin spacing before they merge onto a common route.

Barmore, Bryan E.↗
NASA NTRS1974

Space shuttle/payload interface analysis. (Study 2.4) Volume 4: Business Risk and Value of Operations in Space (BRAVO). Part 2: User's manual

The BRAVO User's Manual is presented which describes the BRAVO methodology in terms of step-by-step procedures, so that it may be used as a tool for a team of analysts performing cost effectiveness analyses on potential future space applications. BRAVO requires a relatively general set of input information and a relatively small expenditure of resources. For Vol. 1, see N74-12493; for Vol. 2, see N74-14530.

Source record↗
NASA NTRS2002

Refractive Secondary Solar Concentrator Demonstrated High-Temperature Operation

Space applications that utilize solar thermal energy--such as electric power conversion systems, thermal propulsion systems, and furnaces--require highly efficient solar concentration systems. The NASA Glenn Research Center is developing the refractive secondary concentrator, which uses refraction and total internal reflection to efficiently concentrate and direct solar energy. When used in combination with advanced lightweight primary concentrators, such as inflatable thin films, the refractive secondary concentrator enables very high system concentration ratios and very high temperatures. Last year, Glenn successfully demonstrated a secondary concentrator throughput efficiency of 87 percent, with a projected efficiency of 93 percent using an antireflective coating. Building on this achievement, Glenn recently successfully demonstrated high-temperature operation of the secondary concentrator when it was used to heat a rhenium receiver to 2330 F. The high-temperature demonstration of the concentrator was conducted in Glenn's 68-ft long Tank 6 thermal vacuum facility equipped with a solar simulator. The facility has a rigid panel primary concentrator that was used to concentrate the light from the solar simulator onto the refractive secondary concentrator. NASA Marshall Space Flight Center provided a rhenium cavity, part of a solar thermal propulsion engine, to serve as the high-temperature receiver. The prototype refractive secondary concentrator, measuring 3.5 in. in diameter and 11.2 in. long, is made of single-crystal sapphire. A water-cooled splash shield absorbs spillage light outside of the 3.5-in. concentrator aperture. Multilayer foil insulation composed of tungsten, molybdenum, and niobium is used to minimize heat loss from the hightemperature receiver. A liquid-cooled canister calorimeter is used to measure the heat loss through the multilayer foil insulation.

Wong, Wayne A.↗
NASA NTRS1991

JPL's Space Flight Operations Center: Development project overview

The topics are covered in view graph form and include the following: (1) major elements of deep space flight programs; (2) development schedule; (3) primary design goals; (4) Space Flight Operations Center (SFOC) data systems architecture; (5) technical guidelines; (6) SFOC data system functional architecture; (7) typical SFOC node; (8) SFOC components; (9) SFOC software categories; (10) planned subsystem core diagram for Mars observer; (11) SFOC use of public domain/3rd party software; (12) SFOC hardware; (13) SFOC target six mission configuration; and (14) SFOC development status and plans.

Ebersole, M.↗
NASA NTRS1982

NASA Deep Space Network operations organization

The organization of the NASA Deep Space Network (DSN), a network of tracking station control and data handling facilities, is briefly reviewed. It has been designed, constructed, maintained, and operated by the Jet Propulsion Laboratory at California Institute of Technology in support of NASA lunar and interplanetary flight programs. Some important technological and organizational advances made by DSN since the early development of spacecraft tracking in the 1950s are considered.

Chafin, R. L.↗
NASA NTRS2008

Delay-Tolerant Networking for Space Flight Operations: Design and Development

Large-scale future space exploration will offer complex communication challenges that may be best addressed by establishing a network infrastructure. The Internet protocols are not well suited for operation of a network over interplanetary distances; a Delay-Tolerant Networking (DTN) architecture has been proposed instead. DTN is now a rapidly growing research field, but most implementations are mainly aimed at supporting applications of DTN technology to terrestrial networking problems. Those implementations are not necessarily suitable for deployment in an interplanetary network. Interplanetary Overlay Network (ION) is an implementation of the DTN architecture that is specifically designed for use in resource-constrained embedded systems, such as interplanetary robotic spacecraft.

DTN↗
NASA NTRS2000

Using Cell Phones From Satellites

During the past several years, an interest has grown in using commercial telecommunications techniques to supply Telemetry and Command (T&C) services. Recently, the National Aeronautics and Space Administration (NASA) Space Operations Management Office (SOMO) has outlined plans to utilize satellite-based telecommunications services to support space operations in space missions over the next several decades. NASA currently obtains the bulk of its telecommunications services for earth-orbiting satellites via the existing government-owned and controlled Space Network (SN) system. This system consists of the constellation of Tracking and Data Relay Satellites (TDRS) in Geostationary Earth Orbit (GEO) and the associated ground terminals and communications intrastructure. This system is valuable and effective for scientific satellites costing over one million dollars. However, for smaller satellites, this system becomes problematic due to the cost of transponders and support infrastructure. The nominal transponders for using the TDRS cannot be obtained for a cost in dollars, and size, weight, or power that the 3 Corner Satellite project can afford. For these types of nanosatellite missions, alternatives that fit the mission cost and satellite profiles are needed. In particular, low-cost access using existing commercial infrastructure would be useful to mission planners. In particular, the ability to obtain low data rate T&C services would be especially valuable. The nanosatellites generally have low T&C requirements and therefore would benefit from using commercial services that could operate in the 2400 bps - 9600 bps range, especially if contact times longer than the 5 - 10 minute ground station passes could be found.

Horan, Stephen↗
NASA NTRSDate not supplied

The Requirements and Design of the Space Weather Science Operation Center

The Space Weather Science Operations Center (SWxSOC) is a NASA project to develop an open-source cloud-based multi-mission Science Operations Center for the community targeting space weather missions that require data products be released consistently and automatically. The first customer of this SOC is the Heliophysics Environmental and Radiation Measurement Experiment Suite (HERMES) that will fly on the Lunar Gateway. The HERMES instrumentation includes an ion mass spectrometer, an electron electrostatic analyzer, a proton and electron telescope for energetic particles, and a set of magnetometers. After a one year transit to the Moon, HERMES will begin a science campaign that addresses heliophysics and space-weather objectives. In this presentation, we will discuss the overall architecture and design of the SOC, the requirements it satisfies and the systems engineering approach used. We will also discuss plans for how to increase it’s capabilities to support new and different missions.

Steven Daniel Christe↗
NASA NTRS1992

Engineering, construction, and operations in space - III: Space '92; Proceedings of the 3rd International Conference, Denver, CO, May 31-June 4, 1992. Vols. 1 & 2

The present volume on engineering, construction, and operations in space discusses surface structures on the moon and Mars, surface equipment, construction, and transportation on the moon and Mars, in situ materials use and processing, and space energy. Attention is given to such orbital structures as LEO and the space station, space mining and excavation, space materials, space automation and robotics, and space life support systems. Topics addressed include lunar-based astronomy, space systems integration, terrestrial support for space functions, and space education. Also discussed are space plans, policy, and history, space science and engineering, geoengineering and space exploration, and the construction and development of a human habitat on Mars.

Space life support systems↗
NASA NTRS2008

Operationally Responsive Space Standard Bus Battery Thermal Balance Testing and Heat Dissipation Analysis

The focus of this paper will be on the thermal balance testing for the Operationally Responsive Space Standard Bus Battery. The Standard Bus thermal design required that the battery be isolated from the bus itself. This required the battery to have its own thermal control, including heaters and a radiator surface. Since the battery was not ready for testing during the overall bus thermal balance testing, a separate test was conducted to verify the thermal design for the battery. This paper will discuss in detail, the test set up, test procedure, and results from this test. Additionally this paper will consider the methods taken to determine the heat dissipation of the battery during charge and discharge. It seems that the heat dissipation for Lithium Ion batteries is relatively unknown and hard to quantify. The methods used during test and the post test analysis to estimate the heat dissipation of the battery will be discussed.

Marley, Mike↗
NASA NTRS1972

Space rescue operations in the early 1980's.

Discussion of planning requirements for space rescue missions in connection with an emergency situation involving a manned satellite with a small crew. A space rescue mission may be divided basically into three major operational phases including the response time phase, the phase concerned with the rescue operations, and the final phase which begins with the casting-off operation from the rendezvous position with the distressed vehicle. The types of possible emergency situations are discussed together with the space rescue equipment, a pressurized emergency module, an unpressurized emergency module, a portable airlock, an attachable docking fixture, a fluid jet type detumble system, a stick-on rocket type detumble system, and an antitumbling space vehicle.

Wild, J. W.↗
NASA NTRS1978

Overview of future programs - USA

An overview of U.S. manned space flight is presented and recent advanced studies are considered. In connection with long range mission planning, studies are being conducted of future space systems, space vehicles, and space operations. An early Space Construction Base is being studied for launch in 1985 and associated geosynchronous operations are projected for 1987. The Space Construction Base is envisioned as a facility for erecting large structures in space, for basing Manned Orbital Transfer Vehicles that operate between low earth orbit and geosynchronous orbit; and for the conduct of industrial operations and scientific experiments in space. Ways and means for erecting large structures in space are examined. One particular plan involves the development of the technology to demonstrate the capabilities of a solar power station to translate solar energy to electrical energy for use on commercial power stations on earth. Advanced transportation is also being studied, particularly for needs that complement the Shuttle. The use of the Shuttle System as a Heavy Lift Launch Vehicle to place large diameter payloads up to 200,000 pounds in weight is also being explored.

Freitag, R. F.↗
NASA NTRS1985

The Space Flight Operations Center development project

This paper presents an overview of the Jet Propulsion Laboratory's (JPL) plan for developing a multi-mission facility called the Space Flight Operations Center (SFOC). The SFOC development is a five-year project with the objective of developing and adapting up-to-date computing, networking and data management technology to meet the future data processing and data management requirements for JPL's flight project mission operations. Presented are the project background, basic goals and objectives, design concept and project implementation approach.

Ebersole, M. M.↗
NASA NTRS1975

Mutual assistance in space

Operating principles, system functions, and technological problems associated with developing compatible spacecraft, station approach, and docking facilities between the U.S. and the U.S.S.R. are reported. Two designs, the probe cone and the androgynous docking device are examined.

Bushuev, K.↗