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Silicone rubber adhesives and potting compounds - polymeric materials for spacecraft
Outgassing characteristics of nine epoxide adhesives, and thermal vacuum performance for adhesives tested
Outgassing characteristics of liquid and paste silicones and effects of postcuring procedures
An important consideration in the design of spacecraft for interplanetary missions is the compatibility of storage materials with the propellants. Serious problems can arise because many propellants are either extremely reactive or subject to catalytic decomposition, making the selection of proper materials of construction for propellant containment and control a critical requirement for the long-life applications. To aid in selecting materials and designing and evaluating various propulsion subsystems, available information on the compatibility of spacecraft materials with propellants of interest was compiled from literature searches and personal contacts. The compatibility of both metals and nonmetals with hydrazine, monomethyl hydrazine, nitrated hydrazine, and diborance fuels and nitrogen tetroxide, fluorine, oxygen difluoride, and Flox oxidizers was surveyed. These fuels and oxidizers encompass the wide variety of problems encountered in propellant storage. As such, they present worst case situations of the propellant affecting the material and the material affecting the propellant. This includes material attack, propellant decomposition, and the formation of clogging materials.
Information is given in simple terms of the Apollo 15 lunar exploration and scientific equipment, to be used in conjunction with other material shown over commercial TV. The EVAs of the astronauts on the surface are divided into experiments and traverses. The landing site and experimental equipment are described, and life sketches are given of the crew.
A description of the history and development of the Skylab program is presented. Mission objectives, launch preparations, and crew activities and training program are outlined. Skylab design and operation are presented, and research programs on Skylab are described along with ground-based supporting projects.
The role of volcanism in the geology of Hawaii is discussed in terms of origin, structure, and morphology.
The Apollo 17 mission is discussed and illustrated. Lunar surface and orbital experiments are briefly described, and results are outlined.
The Planetary Geology Field Conference on the central Snake River Plain was conceived and developed to accomplish several objectives. Primarily, field conferences are sponsored by the National Aeronautics and Space Administration to draw attention to aspects of terrestrial geology that appear to be important in interpreting the origin and evolution of extraterrestrial planetary surfaces. Another aspect is to present results of recent research in a region. A final objective of this conference is to bring together investigators of diverse backgrounds who share a common interest in the Snake River Plain. The Snake River Plain appears to be similar in surface morphology to many volcanic regions on the Moon, Mars, and possibly Mercury. Therefore, the Snake River Plain, in combination with the relatively good state of preservation, the lack of forests or other heavy vegetation, and the good network of jeep trails, is an area nearly ideal for analog studies.
In an effort to establish baseline information whereby specific projects can be evaluated, a current set of parameters which are typical of coal gasification applications was developed. Using these parameters a computer model allows researchers to interrelate cost components in a sensitivity analysis. The results make possible an approximate estimation of hydrogen energy economics from coal, under a variety of circumstances.
The field trip was prepared to provide an opportunity to see first hand some the environmental hazards associated with clays in the Houston, Texas area. Because of the very high clay content in area soils and underlying Beaumont Formation clay, Houston is a fitting location to host the Clay Mineral Society. Examinations were made of (1) expansive soils, (2) subsidence and surface faulting, and (3) a landfill located southeast of Houston at the Gulf Coast Waste Disposal Authority where clay is part of the liner material.
This volume presents technical issues involved in applying mathematical techniques known as Formal Methods to specify and analytically verify aerospace and avionics software systems.
In January 2006, the Stardust spacecraft returned the first in situ collection of samples from a comet, and the first samples of contemporary interstellar dust. Stardust is the first US sample return mission from a planetary body since Apollo, and the first ever from beyond the moon. This handbook is a basic reference source for allocation procedures and policies for Stardust samples. These samples consist of particles and particle residues in aerogel collectors, in aluminum foil, and in spacecraft components. Contamination control samples and unflown collection media are also available for allocation.
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This document provides guidance for assessing similarity relative to nondestructive evaluation (NDE) detectability based on Probability of Detection demonstrations when comparing different NDE inspection situations. Differences in inspection situations addressed by the similarity assessment methodology herein can include differences in the component being inspected, and differences in the conditions for the inspection. Additional differences in the inspection situation relative to differences in the method or procedure are not addressed in this document but can be assessed using NDE calibration or instrument standardization specimens.
Purpose: This document provides guidance on the design and analysis of a NASA Standard nondestructive evaluation (NDE) probability of detection (POD) study. A Standard NDE flaw size is considered to be conservative such that most inspectors, trained and certified in the specific NDE method, are expected to provide at least 90/95 POD for that flaw size to inspect fracture-critical hardware. Scope: This document is specifically applicable to NASA Technical Standards that establish the NDE requirements for any NASA system or component, flight or ground, where fracture control and a quantitative demonstration of POD is a requirement, including NASA-STD-5009B, Nondestructive Evaluation Requirements for Fracture-Critical Metallic Components, and NASA-STD-5019A,Fracture Control Requirements for Spaceflight Hardware.