Proceedings of a conference held at Goddard Space Flight Center, Greenbelt, Maryland, June 15-16, 1970.

Includes bibliographical references.

Space measurements survey: Instruments and spacecraft, October 1957-March 1965.

Mode of access: Internet.

Preliminary criteria for the fracture control of space shuttle structures.

"Compiling, integrating, and editing of the document were performed by the Design Criteria Program Office of the McDonnell Douglas Astronautics Company under the direction of the Langley Research Center's Structural Systems Office (SSO)."

Pre-development study of a heat flux measurement device suitable for use on flight vehicles,

"Project no. AA-1577-Y. Subcontract no. 112705."

Space vehicle displays design criteria.

"Prepared under the direction of an advisory committee chaired by Dr. Jerome I. Elkind...Preparation of the monograph was directed by Dr. Thomas J. Triggs at Bolt Beranek and Newman, Inc."

Space vehicle gyroscope sensor applications.

Cover title.

Advances in sterilization and decontamination : a survey submitted to National Aeronautics and Space Administration, Langley Research Center, Hampton, Virginia /

On cover: Technology utilization.

11th Space Simulation Conference : proceedings of a symposium held at Lyndon B. Johnson Space Center, Houston, Texas, September 23-25,1980 /

Includes bibliographical references.

Outer-space environment models for use with space vehicle simulators.

"Project no. 6114, task no. 60806. Prepared under Contract no. AF 33(616)-6858 by W. A. Livingston Jr. of the Cornell Aeronautical Laboratory, Inc."

Shieldose : a computer code for space-shielding radiation dose calculations /

Includes bibliographical references (p. 29).

Propulsion systems for space flight.

Includes bibliography.

Modeling, Simulation, and Characterization of Space Debris in low-Earth Orbit

Every space launch increases the overall amount of space debris. Satellites have limited awareness of nearby objects that might pose a collision hazard. Astrometric, radiometric, and thermal models for the study of space debris in low-Earth orbit have been developed. This modeled approach proposes analysis methods that provide increased Local Area Awareness for satellites in low-Earth and geostationary orbit. Local Area Awareness is defined as the ability to detect, characterize, and extract useful information regarding resident space objects as they move through the space environment surrounding a spacecraft. The study of space debris is of critical importance to all space-faring nations. Characterization efforts are proposed using long-wave infrared sensors for space-based observations of debris objects in low-Earth orbit. Long-wave infrared sensors are commercially available and do not require solar illumination to be observed, as their received signal is temperature dependent. The characterization of debris objects through means of passive imaging techniques allows for further studies into the origination, specifications, and future trajectory of debris objects. Conclusions are made regarding the aforementioned thermal analysis as a function of debris orbit, geometry, orientation with respect to time, and material properties. Development of a thermal model permits the characterization of debris objects based upon their received long-wave infrared signals. Information regarding the material type, size, and tumble-rate of the observed debris objects are extracted. This investigation proposes the utilization of long-wave infrared radiometric models of typical debris to develop techniques for the detection and characterization of debris objects via signal analysis of unresolved imagery. Knowledge regarding the orbital type and semi-major axis of the observed debris object are extracted via astrometric analysis. This knowledge may aid in the constraint of the admissible region for the initial orbit determination process. The resultant orbital information is then fused with the radiometric characterization analysis enabling further characterization efforts of the observed debris object. This fused analysis, yielding orbital, material, and thermal properties, significantly increases a satellite’s Local Area Awareness via an intimate understanding of the debris environment surrounding the spacecraft.

Diseño e implementación de un receptor GNSS multifrecuencia y multiconstelación

Este proyecto presenta el diseño, test y validación de una cabecera de recepción multiconstelación y multifrecuencia para Sistemas de Navegación Global por Satélite (GNSS). El receptor presentado ha sido diseñado para adquirir las bandas E5/L5 y E1/L1 de los sistemas Galileo y NAVSTAR-GPS. Para trasladar en frecuencia las dos bandas a la vez, se implementa un receptor con arquitectura superheterodina basado en un mezclador de rechazo a frecuencia imagen (IRM). Medidas de ambos sistemas han sido realizadas validando el correcto funcionamiento del receptor en la banda E1/L1. Para ello no sólo se han adquirido los satélites de la constelación GPS, sino que además se han adquirido con éxito los satélites GIOVE-A/B utilizados en la fase de validación en órbita del sistema europeo Galileo.

Numerical study of low-cost alternative orbits around the Moon

In this paper, we have investigated a region of direct stable orbits around the Moon, whose stability is related to the H2 Family of periodic orbits and to the quasi-periodic orbits that oscillate around them. The stability criteria adopted was that the path did not escape from the Moon during an integration period of 1000 days (remaining with negative two-body Moon-probe orbital energy during this period). Considering the three-dimensional four-body Sun-Earth-Moon-probe problem, we investigated the evolution of the size of the stability region, taking into account the eccentricity of the Earth's orbit, the eccentricity and inclination of the Moon's orbit, and the solar radiation pressure on the probe. We also investigated the evolution of the region's size and its location by varying the inclination of the probe's initial osculating orbit relative to the Moon's orbital plane between 0 degrees and 180 degrees. The size of the stability region diminishes; nevertheless, it remains significant for 0 <= i <= 25 degrees and 35 degrees <= i <= 45 degrees. The orbits of this region could be useful for missions by space vehicles that must remain in orbit around the Moon for periods of up to 1000 days, requiring low maintenance costs. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved.

O estudo da usinagem em torneamento da superliga à base de níquel Pyromet 31v

The search for materials with higher properties and characteristics (wear resistance, oxidation, corrosion, etc.) has driven research of various materials. Among the materials that are being studied with such properties and characteristics are super alloys based on nickel which has an important role in the aeronautical, automotive, marine, production of gas turbines and now in space vehicles, rocket engineering , experimental aircraft, nuclear reactors, steam-powered plants, petrochemical and many other applications because besides having all the characteristics and properties mentioned above also have an excellent performance at high temperatures. The super alloy based on nickel studied in this work is the super alloy Pyromet 31v normally used in the manufacture of exhaust valves in common engines and diesel engines of high power by cater requirements such as mechanical strength and corrosion resistance at temperatures of approximately 815 ° C. The objective of this work is to produce results to demonstrate more specific information about the real influence of coatings on cutting tools and cutting fluids in turning and thus promote the optimization of the machining of these alloys. The super alloy Pyromet 31v was processed through turning, being performed with various machining parameters such as cutting speed, feed rate, depth in conditions of Minimum Amount of Fluid (MAF), abundant fluid, cutting tools with coating and without coating in early in his work life and with wear. After turning were obtained several samples of chips and the part generated during the machining process, was measured roughness of the material, subsequently made macrostructural analysis of the tools used order to detect possible wear and microstructural analysis of samples collected being that the latter was used for Optical Microscopy, Scanning Electron Microscopy (SEM) and ... (Complete abstract click electronic access below)