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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 289 records · Page 16
All sourcesNASA NTRSDOE OSTI
NASA NTRS1994

International Neutral Buoyancy Simulation of Space Station Hardware

The International Standard Payload Rack (ISPR) Neutral Buoyancy Simulation was conducted at the Marshall Space Flight Center (MSFC) Neutral Buoyancy Simulator facility during April and May 1992. The purpose of this simulation was to evaluate hardware design and operations for the ISPR and U.S. Lab system racks under simulated conditions of microgravity. The ISPR NBS was conducted by an international simulation team including representatives from Boeing, NASA, NASDA, and ESA. Hardware for the ISPR NBS was provided by Boeing, Alenia, ESA, and MSFC. NASDA and its contractors MEH and IHI provided experienced in-tank participants and technical observers who were present for the duration of the simulation. The ISPR NBS was the first Space Station simulation involving NASA, NASDA and ESA. In addition to bringing together technical representatives from around the world, the ISPR NBS included test subjects who are some of the most experienced U.S. and European astronauts. Eight general areas of investigation were addressed during the ISPR NBS, including: utility panel interfaces, rack tilt down, standoff access, wall access behind the rack, rack removal and installation, rack translation, multiple rack operations, and restraints and mobility aids. This paper focuses on aspects of simulation planning, conduct, and reporting that pertain to specifically to the international involvement of the activity.

Lisa C King↗
NASA NTRS2014

Amine Swingbed Payload Testing on ISS

One of NASA Johnson Space Center's test articles of the amine-based carbon dioxide (CO2) and water vapor sorbent system known as the CO2 And Moisture Removal Amine Swing-bed, or CAMRAS, was incorporated into a payload on the International Space Station (ISS). The intent of the payload is to demonstrate the spacecraft-environment viability of the core atmosphere revitalization technology baselined for the new Orion vehicle. In addition to the air blower, vacuum connection, and controls needed to run the CAMRAS, the payload incorporates a suite of sensors for scientific data gathering, a water save function, and an air save function. The water save function minimizes the atmospheric water vapor reaching the CAMRAS unit, thereby reducing ISS water losses that are otherwise acceptable, and even desirable, in the Orion environment. The air save function captures about half of the ullage air that would normally be vented overboard every time the cabin air-adsorbing and space vacuum-desorbing CAMRAS beds swap functions. The JSC team conducted 1000 hours of on-orbit Amine Swingbed Payload testing in 2013 and early 2014. This paper presents the basics of the payload's design and history, as well as a summary of the test results, including comparisons with prelaunch testing.

Button, Amy B.↗
NASA NTRS2014

Amine Swingbed Payload Testing on ISS

One of NASA/Johnson Space Center's test articles of the amine-based carbon dioxide (CO2) and water vapor sorbent system known as the CO2 And Moisture Removal Amine Swing-bed, or CAMRAS, was incorporated into a payload on the International Space Station (ISS). The intent of the payload is to demonstrate the spacecraft-environment viability of the core atmosphere revitalization technology baselined for the new Orion vehicle. In addition to the air blower, vacuum connection, and controls needed to run the CAMRAS itself, the payload incorporates a suite of sensors for scientific data gathering, a water save function, and an air save function. The water save function minimizes the atmospheric water vapor reaching the CAMRAS unit, thereby reducing ISS water losses that are otherwise acceptable, and even desirable, in the Orion environment. The air save function captures about half of the ullage air that would normally be vented overboard every time the cabin air-adsorbing and space vacuum-desorbing CAMRAS beds swap functions. The JSC team conducted 1000 hours of on-orbit Amine Swingbed Payload testing in 2013. This paper presents the basics of the payload's design and history, as well as a summary of the test results, including comparisons with prelaunch testing.

Button, Amy↗
NASA NTRS2003

Reusable Rack Interface Controller Common Software for Various Science Research Racks on the International Space Station

The purpose of the EXPRESS (Expedite the PRocessing of Experiments to Space Station) rack project is to provide a set of predefined interfaces for scientific payloads which allow rapid integration into a payload rack on International Space Station (ISS). VxWorks' was selected as the operating system for the rack and payload resource controller, primarily based on the proliferation of VME (Versa Module Eurocard) products. These products provide needed flexibility for future hardware upgrades to meet everchanging science research rack configuration requirements. On the International Space Station, there are multiple science research rack configurations, including: 1) Human Research Facility (HRF); 2) EXPRESS ARIS (Active Rack Isolation System); 3) WORF (Window Observational Research Facility); and 4) HHR (Habitat Holding Rack). The RIC (Rack Interface Controller) connects payloads to the ISS bus architecture for data transfer between the payload and ground control. The RIC is a general purpose embedded computer which supports multiple communication protocols, including fiber optic communication buses, Ethernet buses, EIA-422, Mil-Std-1553 buses, SMPTE (Society Motion Picture Television Engineers)-170M video, and audio interfaces to payloads and the ISS. As a cost saving and software reliability strategy, the Boeing Payload Software Organization developed reusable common software where appropriate. These reusable modules included a set of low-level driver software interfaces to 1553B. RS232, RS422, Ethernet buses, HRDL (High Rate Data Link), video switch functionality, telemetry processing, and executive software hosted on the FUC computer. These drivers formed the basis for software development of the HRF, EXPRESS, EXPRESS ARIS, WORF, and HHR RIC executable modules. The reusable RIC common software has provided extensive benefits, including: 1) Significant reduction in development flow time; 2) Minimal rework and maintenance; 3) Improved reliability; and 4) Overall reduction in software life cycle cost. Due to the limited number of crew hours available on ISS for science research, operational efficiency is a critical customer concern. The current method of upgrading RIC software is a time consuming process; thus, an improved methodology for uploading RIC software is currently under evaluation.

Lu, George C.↗
NASA NTRS2003

Umbilical Stiffness Matrix Characterization and Testing for Microgravity Science Payloads

This paper describes efforts of testing and analysis of various candidate cables and umbilicals for International Space Station microgravity science payloads. The effects of looping, large vs. small displacements, and umbilical mounting configurations were assessed. A 3-DOF stepper motor driven fixture was used to excite the umbilicals. Forces and moments were directly measured in all three axes with a 6-DOF load cell in order to derive suitable stiffness matrices for design and analysis of vibration isolation controllers. Data obtained from these tests were used to help determine the optimum type and configuration of umbilical cables for the International Space Station microgravity science glovebox (MSG) vibration isolation platform. The data and procedures can also be implemented into control algorithm simulations to assist in validation of actively controlled vibration isolation systems. The experimental results of this work are specific in support of the Glovebox Integrated Microgravity Isolation Technology (g-LIMIT) isolation platform, to be located in the microgravity science glovebox aboard the U.S. Destiny Laboratory Module.

Engberg, Robert C.↗
NASA NTRS1992

The Ultra High Resolution XUV Spectroheliograph. III - A modified configuration for a free flying platform

The Ultra-High Resolution XUV Spectroheliograph (UHRXS) is a comprehensive solar observatory capable of studying solar phenomena at soft X-ray, XUV, EUV, and VUV wavelengths with normal incidence imaging multilayer telescopes capable of very high angular resolution (about 0.1 arcsec), and spectrographs able to achieve high spectral resolution. This instrument has been selected by NASA for flight as an attached payload on the Space Station Freedom. Recent developments have made it clear that accommodations for attached payloads on Freedom will not become available during the initial operations of Freedom and may never be available. We have studied the changes that must be made to place the UHRXS instrument on a Free Flying Plafform such as the Delta Launched Explorer Bus. We report on the configuration, performance, and accommodation on a free flying platform of the revised UHRXS concept.

Walker, Arthur B. C., Jr.↗
NASA NTRS2010

Kennedy Space Center Launch and Landing Support

The presentations describes Kennedy Space Center (KSC) payload processing, facilities and capabilities, and research development and life science experience. Topics include launch site processing, payload processing, key launch site processing roles, leveraging KSC experience, Space Station Processing Facility and capabilities, Baseline Data Collection Facility, Space Life Sciences Laboratory and capabilities, research payload development, International Space Station research flight hardware, KSC flight payload history, and KSC life science expertise.

Wahlberg, Jennifer↗
NASA NTRS1992

Integrated launch and emergency vehicle system

A heavy launch vehicle is discussed. The launch vehicle is comprised of an expendable, multi-container, propellant tank that has a plurality of winged booster propulsion modules at one end and a payload supported by adapter structure at the other end. The preferred payload is an entry module that can be adapted for docking to the space station and used as a return vehicle for the space station crew. Additionally, the payload may include communication satellites, supplies, equipment, and/or structural elements for the space station. The winged propulsion modules are released from the expendable propellant tank, in pairs, and they return to Earth in a controlled glide. After a safe landing, at or near the launch site, the modules are prepared for reuse. The rocket engines for each propulsion module are dual-fuel, dual-mode engines and use methane-oxygen and hydrogen-oxygen from the multi-containers of the propellant tank. When the propulsion modules are released from the expendable propellant tank, the rocket engines are moved into the module cargo bay for the return glide flight.

Martin, James A.↗
NASA NTRS2003

Commercial Research Results from the International Space Station

As part of NASA's mission of enabling commercial opportunities in space, the Space Product Development Office has sponsored the flight of twelve commercial payloads to the International Space Station (ISS) during calendar year 2002. These twelve follow seven commercial payloads flown to the ISS during 2001. Many of these payloads, which were among the first users of this new laboratory, built upon successful commercial investigations that previously were restricted to the limited flight duration of the Space Shuttle. While the majority of early commercial use of the ISS is in the area of biotechnology, there is a significant shift towards commercial materials research over the next two years. New commercial payloads such as Space-DRUMS and Vulcan will advance commercial materials research on the ISS. Commercial flight hardware is available to the broader NASA community in order to provide benefit to the entire NASA microgravity program, and the scientific community on a space available basis and at very low cost. The first commercial operations on the ISS provides not only a needed capability to the commercial development of space program, it will also augment the science program as well.

Nall, Mark↗
NASA NTRS1987

Structural/control interaction (payload pointing and micro-g)

A 203rd order simulation model was developed to evaluate the space station customer accommodation payload pointing and micro-g requirements. The simulation shows the pointing errors on the telescope are significantly smaller than at the base of the telescope. The pointing results could change when the parametric studies are performed. The results show the micro-g requirement is met with an active isolation system.

Larson, C. R.↗
NASA NTRS1983

Space station needs, attributes, and architectural options: Brief analysis

A baseline set of model missions is thoroughly characterized in terms of support requirements, demands on the Space Station, operating regimes, payload properties, and statements of the mission goals and objectives. This baseline is a representative set of mission requirements covering the most likely extent of space station support requirements from which architectural options can be constructed and exercised. The baseline set of 90 missions are assessed collectively and individually in terms of the economic, performance, and social benefits.

Shepphird, F. H.↗
NASA NTRS1989

The Space Station active thermal control technical challenge

The overall conceptual design premise of the two major subsystems that make up the Space Station active thermal control system is discussed. Specifically, the thermal loop required to gather and collect the waste heat from the various systems, modules, and payloads of the Space Station and the large radiators necessary to dissipate the waste heat to space are described. The basic design concepts to be incorporated in the Space Station are described, and the ground and flight tests conducted to date to prove the feasibility of the design approaches are summarized. Future Space Shuttle flight tests planned to further verify the designs are outlined.

Ellis, W. E.↗
NASA NTRS1992

Lessons learned from evaluating launch-site processing problems of Space Shuttle payloads

The authors discuss a trend analysis program that is being conducted on the problem reports written during the processing of Space Shuttle payloads at Kennedy Space Center. The program is aimed at developing lessons learned that can both improve the effectiveness of the current payload processing cycles as well as help to guide the processing strategies for Space Station Freedom. The payload processing reports from STS 26R and STS 41 are used. A two-tier evaluation activity is described, and some typical results from the tier one analyses are presented.

Flores, Carlos A.↗
NASA NTRS2018

The Evolution of Payload Data Capabilities on the Commercial Visiting Vehicles that Service the International Space Station

The visiting vehicles designed by U.S.-based commercial companies to deliver cargo and crew to the International Space Station (ISS) can transfer science payloads to the ISS in an active, powered state. To provide payload developers with situational awareness during transit, NASA is working with current and future visiting vehicles to offer a variety of payload monitoring and control capabilities. This presentation will offer discussion of the following topics: How NASA requirements for the data services available to ISS payloads on the visiting vehicles have expanded over time; The challenges that have been faced in establishing these services.

Wiggins, Lindsay↗
NASA NTRSDate not supplied

The HERMES Payload for Gateway: Heliophysics Enabled by Lunar Exploration

At launch, the first two modules of the Gateway space station will carry external payloads from NASA and ESA designed to observe the space environment. The NASA payload is the Heliophysics Environmental and Radiation Measurement Experiment Suite (HERMES). 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 an approximately one year transit to the Moon, HERMES will begin a science campaign that addresses heliophysics and space-weather objectives. Analyses of the in-situ measurements from HERMES will leverage observations from other Heliophysics spacecraft missions to enable multipoint studies of structure in the solar wind and in the magnetotail. Gateway’s polar lunar orbit is advantageous for this purpose. HERMES also is a pathfinder for future payloads on human-exploration vessels, for which there will be pragmatic interest in the variable radiation environment. Thus, with observations enabled by the ARTEMIS Program, HERMES is expected to be enabling of future exploration missions. Additionally, although HERMES objectives have a space-weather focus, the measurements also can be useful for studies of the Moon. Data, algorithms, calibrations, and related software produced by the project will be fully open and accessible through a Science Operations Center. In this presentation we provide an overview of science plans, including expectations for collaboration with other HSO missions and with international partners. Plain-Language Summary: The HERMES scientific payload will be attached to the HALO module of the Artemis Program's Gateway lunar outpost. HERMES will observe space weather conditions from lunar orbit. The data will be freely available for studies of the Moon and its space environment.

William R Paterson↗