Radiant cooler design and emissivity study. Part 1 - Radiant cooler design Final report, 8 Apr. - 31 Oct. 1969
Design and thermal analysis of radiant cooler for operation from side of Nimbus spacecraft
Source record↗
SEARCH · Search NASA
Results for “Designs”
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.
Lunar Orbiter program guidance and control system - Design survey. NASA/ERC design criteria program - Guidance and control
Design and tests of Lunar Orbiter guidance and control systems
Source record↗
Design and construction of heated ion source for organic analysis and design and construction of double focusing mass spectrometer analyzer Final report
Design and modification of pyrolysis, gas chromatograph, double focusing mass spectrometer and addition of heated ion source for Martian life detection
Source record↗
Stability characterization of advanced injectors. Design guide for stable H2/O2 combustors. Volume 1 - Design application
Design guide for stable hydrogen/oxygen combustors - Vol. 1
Source record↗
Designers manual for circuit design by analog/digital techniques Final report
Manual for designing circuits by hybrid computer
Beck, C. H.↗
Designers manual for computer-aided design of control circuits Final technical report
Computer aided design of linear time invariant feedback control circuits
Bedrosian, S. D.↗
A computer aided design system for the design of filters
Filters design by on-line graphic interface computerized synthesis utilizing three screen CRT display
Adkins, A. F.↗
TRIAD - Preliminary design of an operational earth resources survey system. 1969 summer faculty fellowship program in engineering systems design
TRIAD, preliminary design of operational earth resources survey system
Carver, K. R.↗
Reconfigurable G and C computer study for space station use. Volume 7, appendix 5 - D-200 computer family. Appendix 6 - System error analysis. Appendix 7 - Reliability derivation for candidate computers. Appendix 8 - Power converter design data. Appendix 9 - Data transmission medium design Final report, 29 Dec. 1969 - 31 Jan. 1971
D-200 computer family, system error analysis, reliability derivation, and power converter design for reconfigurable guidance and control computer - Vol. 7
Source record↗
Structural design criteria applicable to a space shuttle. NASA space vehicle design criteria
Structural design criteria applicable for earth-to-orbit space shuttles and independent of external vehicle configuration
Source record↗
Design of a simulated cruise scene visual attachment. Volume 1 - Design report
Television-type, out-window visual simulation image generator design and specifications for aircraft or spacecraft manned flight simulation
Kielar, C. W.↗
Thermionic spacecraft design study, 120 kw nuclear electric propulsion system. Volume 2: External fuel reactor spacecraft design
Design and development of electrically propelled spacecraft based on external-fuel reactor concepts for thermionic reactors - Vol. 2
Source record↗
Integrating the relay link design and trajectory design for the Viking '75 mission
Relay data link and trajectory design integration for Viking orbiter 1975 mission
Marquet, D. W.↗
Conceptual design and feasibility evaluation model of a 10 to the 8th power bit oligatomic mass memory. Volume 1: Conceptual design
The oligatomic (mirror) thin film memory technology is a suitable candidate for general purpose spaceborne applications in the post-1975 time frame. Capacities of around 10 to the 8th power bits can be reliably implemented with systems designed around a 335 million bit module. The recommended mode was determined following an investigation of implementation sizes ranging from an 8,000,000 to 100,000,000 bits per module. Cost, power, weight, volume, reliability, maintainability and speed were investigated. The memory includes random access, NDRO, SEC-DED, nonvolatility, and dual interface characteristics. The applications most suitable for the technology are those involving a large capacity with high speed (no latency), nonvolatility, and random accessing.
Recksiedler, A. L.↗
Application of EVA guidelines and design criteria. Volume 1: EVA selection/systems design considerations
Parameters that require consideration by the planners and designers when planning for man to perform functions outside the vehicle are presented in terms of the impact the extravehicular crewmen and major EV equipment items have on the mission, vehicle, and payload. Summary data on man's performance capabilities in the weightless space environment are also provided. The performance data are based on orbital and transearth EVA from previous space flight programs and earthbound simulations, such as water immersion and zero-g aircraft.
Brown, N. E.↗
Design integration and noise studies for jet STOL aircraft. Task 7A: Augmentor wing cruise blowing valveless system. Volume 2: Design exploration
A design integration study program was conducted to determine size and performance parameters of an augmentor wing cruise blowing (valveless) system in a 150-passenger STOL airplane for the purpose of defining size and configuration of static rig, flow duct, and wind tunnel test hardware. The studies encompassed blowing systems powered by low-pressure (single stage) and high-pressure (three and four stage) engine fans. A range of wing aspect ratios, wing thicknesses, and duct flow velocity effects were investigated to establish airplane characteristics which minimize takeoff gross weight while achieving sideline noise requirements for an advanced commercial STOL airplane.
Source record↗
Laser communication experiment. Volume 1: Design study report: Spacecraft transceiver. Part 1: Transceiver design
The ATS-F Laser Communications Experiment (LCE) is the first significant step in the application of laser systems to space communications. The space-qualified laser communications system being developed in this experiment, and the data resulting from its successful deployment in space, will be applicable to the use of laser communications systems in a wide variety of manned as well as unmanned space missions, both near earth and in deep space. Particular future NASA missions which can benefit from this effort are the Tracking and Data Relay Satellite System and the Earth Resources Satellites. The LCE makes use of carbon dioxide lasers to establish simultaneous, two-way communication between the ATS-F synchronous satellite and a ground station. In addition, the LCE is designed to permit communication with a similar spacecraft transceiver proposed to be flown on ATS-G, nominally one year after the launch of ATS-F. This would be the first attempt to employ lasers for satellite-to-satellite communications.
Source record↗
Laser communication experiment. Volume 1: Design study report: Spacecraft transceiver. Part 3: LCE design specifications
The requirements for the design, fabrication, performance, and testing of a 10.6 micron optical heterodyne receiver subsystem for use in a laser communication system are presented. The receiver subsystem, as a part of the laser communication experiment operates in the ATS 6 satellite and in a transportable ground station establishing two-way laser communications between the spacecraft and the transportable ground station. The conditions under which environmental tests are conducted are reported.
Source record↗