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Technical Paper

25-Ah Li Ion Cell for the Mars 2001 Lander

1999-08-02
1999-01-2640
Geometric requirements within the spacecraft also constrain the cell design leading to a cell with an aspect ratio quite different from those 25-Ah Li ion cells previously developed by BATC.
Technical Paper

50 to 100-Ah Lithium Ion Cells for Aircraft and Spacecraft Applications

1997-06-18
971230
As a part of a program jointly supported by the USAF and Canada's Department of National Defense, BlueStar is developing large (50 to 100-Ah)lithium ion cells for aircraft and spacecraft applications. Presently, 20-Ah cells are being developed as the first stage of the scale-up process and the design of these cells involves several tradeoffs related to the specific nature of this application.
Technical Paper

747 Shuttle Carrier Aircraft/Space Shuttle Orbiter Mated Ground Vibration Test: Data via Transient Excitation and Fast Fourier Transform Analysis

1977-02-01
770970
The experimental procedure employed to define the natural modes of vibration of the 747 Shuttle Carrier Aircraft and Space Shuttle Orbiter mated configuration is described. A discussion of test results and comparison to structural analysis results is also included. Random transient signals were used as inputs to electromagnetic shakers to provide excitation to the mated vehicle test configuration. Acceleration signals were processed via the Fast Fourier Transform algorithm. Magnitude and phase transfer functions were formed and processed to produce modal frequencies, damping, and modal displacements.
Technical Paper

90 Ah Dependent Pressure Vessel (DPV) Nickel Hydrogen Battery Qualification Test Results

1999-08-02
1999-01-2590
In 1995, the Naval Research Laboratory (NRL) began a program to investigate whether a 90 Ah dependent pressure vessel (DPV) NiH2 battery pack could be a lower volume replacement for a 90 Ah NiH2 IPV spacecraft battery. Nickel Hydrogen (NiH2) dependent pressure vessel (DPV) battery cells are presumed to offer all the features of the NiH2 IPV battery cell with considerably less volume.
Technical Paper

A -183°C Cryogenic Freezer for the International Space Station

2003-07-07
2003-01-2525
In the course of CRYOSYSTEM phase B (development phase) financed by the European Space Agency, AIR LIQUIDE (France) and Astrium Space Infrastructure (Germany) have developed an optimized design of a −183°C freezer to be used on board the International Space Station for the freezing and storage of biological samples. The CRYOSYSTEM facility consists of the following main elements: - the CRYORACK, an outfitted standard payload rack (ISPR) accommodating up to three identical Vial Freezers - the Vial Freezer, a dewar vessel capable of fast and ultra-rapid freezing, and storing up to approximately 900 vials below −183°C; the dewar is cooled by a Stirling machine producing > 6 W at 90 K. The Vial Freezer is operational while accommodated in the CRYORACK or attached to the Life Science Glovebox (LSG). One CRYORACK will remain permanently on-orbit for several years while four Vial Freezers and two additional CRYORACKs support the cyclic upload/download of samples.
Technical Paper

A -183°C Cryogenic Freezer for the International Space Station

2000-07-10
2000-01-2325
In the frame of the CRYOSYSTEM A-phase study financed by the European Space Agency, AIR LIQUIDE (France) and ORBITAL HYDRAULIC-BREMEN (Germany) have been studying a -183°C freezer to be used on-board the International Space Station for freezing and storing biological samples.
Technical Paper

A 50 Wh Open Core High-Speed Flywheel

1999-08-02
1999-01-2615
In low earth orbit satellite applications, spacecraft power is provided by photovoltaic cells and batteries. Unfortunately, use of batteries present difficulties due to their poor energy density, limited cycle lifetimes, reliability problems, and the difficulty in measuring the state of charge.
Technical Paper

A Baseline Design for the Space Station Habitat

1988-07-01
881119
A baseline design has been selected for the Space Station Habitat (HAB) element. The HAB provides the primary living space to support man's permanent presence in space. The HAB element is designed to provide an environment that maximizes safety and human productivity. This paper outlines some of the current design features including the common core elements and the man-systems hardware. The HAB is arranged in three areas based on crew activity and acoustical considerations. The first area is the quiet zone, which contains the crew quarters. The second area is a buffer zone for noise suppression, where the stowage, medical facilities, and personal hygiene facilities are located. The third area is the active zone which contains the galley/wardroom, laundry and exercise facilities. Each of these three areas will be discussed together with the applicable requirements, the common utility elements, and the man-systems hardware furnishings.
Technical Paper

A British Reusable Booster Concept

1967-02-01
670389
Even lower costs can be shown for a modular concept (MUSTARD) in which basically identical lifting bodies units are utilised as both boosters and spacecraft. The concept is shown to be feasible, and progress on some aspects of the associated structural analysis is described.
Technical Paper

A CFD-Based, Application-Oriented, Integrated Simulation Environment for Rapid Prediction of Aerodynamic Sensitivities of 3-D Configurations

1997-10-01
975606
Primarily tailored to fit conceptual design applications, the functionalities of the mesh generation module has been expanded to allow analysis engineers with limited specific expertise to use advanced CFD simulation tools for complex aircraft and spacecraft configurations starting from no more input that a three-side layout blueprint.
Technical Paper

A Catalytic Combustion System Coupled with Adsorbents for Air Clean Up in Sealed Spacecraft Environment

2003-07-07
2003-01-2624
Catalytic combustion coupled with activated carbon and molecular sieve adsorbents is applicable to all areas of air and gas clean up ranging from high to low levels of pollutants and trace contaminants control in a spacecraft environment is of no exception. In this study we propose a combined activated charcoal and catalytic combustion system based on a 70 watt power input achieving 350°C, operating on a 6 hour per 24 hour day catalytic cycle with an actual flow of 10.6 l min-1 in a residual free volume of 60 m3.
Journal Article

A Comparison between One- and Two-Loop ATCS Architectures Proposed for CEV

2009-07-12
2009-01-2458
In an effort to help future crewed spacecraft thermal control analysts understand the characteristics of one-and two-loop Active Thermal Control Systems (ATCS), a comparison was made between the one- and two-loop ATCS architectures officially proposed for the Crew Exploration Vehicle (CEV) in Design Analysis Cycle 1 (DAC1) and DAC2, respectively.
Technical Paper

A Comparison of INTELSAT VIII Spacecraft Thermal Vacuum Test Techniques

1997-07-01
972525
The INTELSAT VIII / VIIIA program consists of six communication satellites (of two different designs) being produced by Lockheed Martin Astro Space for the International Telecommunications Satellite Organization (INTELSAT). Two spacecraft level thermal vacuum test facilities were required to test the first four spacecraft due to schedule constraints. ...Cal rods were used to independently control the thermal environments of the six spacecraft faces for this facility. A typical cal rod test approach measures cal rod fluxes via calorimeters at discrete locations and controls the applied fluxes based on a correction from the calorimeter to Optical Solar Reflector (OSR) or blanket thermo-optical properties. ...Three thermal balance cases, simulating equinox beginning of life, winter solstice end of life, and inverted spacecraft winter solstice end of life were common to the 801 and 802 test profiles. A comparison of these three balance cases confirms that the developed cal rod equivalent sink test technique is a good substitute for the hot wall test approach when chamber multiple zone temperature control is unavailable.
Technical Paper

A Comparison of Russian and American Oxygen Generation Hardware

1994-06-01
941250
Cooperation between Russia and the United States on manned spaceflight has led to unprecedented openness, resulting in the ability to now compare the characteristics of environmental control/life support hardware selected to generate oxygen (O2) by water electrolysis for space station applications. This comparison in this paper focuses on the characteristics that have the greatest effect on the cost of assembling and maintaining the hardware in space: launch weight, volume, power consumption, resupply requirements and maintenance labor.
Technical Paper

A Comparison of Satellite Flight Temperatures with Thermal Balance Test Data

2003-07-07
2003-01-2460
Flight temperatures were compared to thermal balance test correlation data for two spacecraft. Results show that locations that were correlated with ground test data did not necessarily have similar correlation with flight data. ...Furthermore, flight correlation data verified the importance of the continued use of an ±11°C thermal uncertainty margin in spacecraft thermal design.
Journal Article

A Comparison of the Apollo and Early Orion Environmental Control, Life Support and Active Thermal Control System's Driving Requirements and System Mass

2008-06-29
2008-01-2081
The Orion Crew and Service Modules are often compared to the Apollo Command and Service Modules due to their similarity in basic mission objective: both were dedicated to getting a crew to lunar orbit and safely returning them to Earth. Both spacecraft rely on the environmental control, life support and active thermal control systems (ECLS/ATCS) for the basic functions of providing and maintaining a breathable atmosphere, supplying adequate amount of potable water and maintaining the crew and avionics equipment within certified thermal limits.
Technical Paper

A Complex Simulation Model of Human Organism as a Link of the Space Vehicle Ecological and Technical System

1995-07-01
951531
Among the fundamental problems of the ETS development requiring the HOCSM adaptation are: (a) forming the mass and energetic loads of spacecraft crew for the simulation of the ETS functions; (b) the investigation of environment effects on a human organism and its responses; (c) the analysis of interactions between the crew and the individual life support system or its functional blocks; (d) the decisions of design problems for development of the anti exposure and space suits.
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