SEARCH · Engineering Papers
Results for “SPACECRAFT CONSTRUCTION MATERIAL”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Characterization of Oribtal Debris via Hyper-Velocity Ground-Based Tests
Existing DoD and NASA satellite breakup models are based on a key laboratory-based test, Satellite Orbital debris Characterization Impact Test (SOCIT), which has supported many applications and matched on-orbit events involving older satellite designs reasonably well over the years. In order to update and improve the break-up models and the NASA Size Estimation Model (SEM) for events involving more modern satellite designs, the NASA Orbital Debris Program Office has worked in collaboration with the University of Florida to replicate a hypervelocity impact using a satellite built with modern-day spacecraft materials and construction techniques. The spacecraft, called DebriSat, was intended to be a representative of modern LEO satellites and all major designs decisions were reviewed and approved by subject matter experts at Aerospace Corporation. DebriSat is composed of 7 major subsystems including attitude determination and control system (ADCS), command and data handling (C&DH), electrical power system (EPS), payload, propulsion, telemetry tracking and command (TT&C), and thermal management. To reduce cost, most components are emulated based on existing design of flight hardware and fabricated with the same materials. All fragments down to 2 mm is size will be characterized via material, size, shape, bulk density, and the associated data will be stored in a database for multiple users to access. Laboratory radar and optical measurements will be performed on a subset of fragments to provide a better understanding of the data products from orbital debris acquired from ground-based radars and telescopes. The resulting data analysis from DebriSat will be used to update break-up models and develop the first optical SEM in conjunction with updates into the current NASA SEM. The characterization of the fragmentation will be discussed in the subsequent presentation.
Simulated space environmental effects on a polyetherimide and its carbon fiber-reinforced composites
The selection of materials for spacecraft construction requires identification of candidate materials which can perform reliably in the space environment. Understanding the effects of the space environment on the materials is an important step in the selection of candidate materials. This work examines the effects of energetic electrons, thermal cycling, electron radiation in conjunction with thermal cycling, and atomic oxygen on a thermoplastic polyetherimide and its carbon-fiber-reinforced composites. Composite materials made with non-sized fibers as well as materials made with fibers sized with an epoxy were evaluated. The mechanical and thermomechanical properties of the materials were studied and spectroscopic techniques were used to investigate the mechanisms for the observed effects. Considerations for future material development are suggested.
Performance evaluation of ''Thermo-lag'' material for entry heat protection of advanced manned spacecraft Material development report, 1 Oct. 1962 - 1 Apr. 1963
Performance evaluation of Thermo-lag material for advanced manned spacecraft reentry heat protection
Wanted- new materials.
Material research and development requirements for space vehicles, covering thermal control, cryogenic uses and material systems
SPACECRAFT APPLICATIONS OF POLYMERIC MATERIALS
Brief description of an engineering test program to determine the effects of the space environment on polymeric materials
Nonmetallic-material selection criteria, test requirements, test techniques and data, and configuration control as applied to manned spacecraft
Manned spacecraft nonmetallic construction materials selection criteria, testing and configuration control, considering flammability hazard
SELF-SEALING SPACECRAFT STRUCTURE IN THE METEOROID ENVIRONMENT
Elastomeric self-sealing structural materials for spacecraft operating in ameteoroid environment
Measured effects of the various combinations of nuclear radiation, vacuum, and cryotemperatures on engineering materials Final biennial report, 1 May 1964 - 1 May 1966
Effects of radiation, vacuum, and cryotemperatures on nonmetallic engineering materials for spacecraft containing nuclear reactors
STRUCTURES AND MATERIALS IMPASSE
Discussion of the problems associated with materials and different structural design approaches to launch vehicles
Structures, materials, reentry.
Materials, space vehicle structures and reentry research and development
Composites at low temperatures.
Composite material with titanium strength-weight ratio and aluminum safety for aerospace vehicle construction
Thermal control of spacecraft.
Thermal design and materials for temperature control of space vehicles
Polymers for spacecraft hardware materials specifications and engineering information Monthly technical progress report no. 21, Feb. 10 - Mar. 9, 1966
Chemical test methods for potting compound base materials and additional polymeric materials for spacecraft hardware fabrication
Methods for experimental determination of the extra-terrestrial solar absorptance of spacecraft materials
Spectral diffuse reflectance and simulated solar absorptance measurements for determination of solar absorptance of spacecraft materials
Metal-metal composites - A new structural material.
Spacecraft metal-metal composites consisting of continuous filaments in metal matrix
EVAPORATION EFFECTS ON MATERIALS IN SPACE
Vacuum environmental effects on the evaporation, sublimation and decomposition rates of materials for space application
Materials problems in satellites.
Satellite material problems in corrosion, fatigue failure, vacuum degradation, etc