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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.

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At least 1,063 records · Page 59
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

GPS early-orbit subsystem for earth satellites

The early-orbit capability of the Goddard Trajectory Determination System, which determines starting vectors for earth satellites from angles-only or range-angles observations, is described and documented. Early-orbit results obtained from a variety of satellites, data types and methods of solution are also presented.

Laczo, V. T.↗
NASA NTRS1973

Waste collection subsystem development

Engineering studies, design activity and testing associated with the development of a waste collection system to accommodate both male and female crewmembers in a space environment are reported.

Swider, J. E., Jr.↗
NASA NTRS1973

Analyses of requirements for computer control and data processing experiment subsystems: Image data processing system (IDAPS) software description (7094 version), volume 2

A description of each of the software modules of the Image Data Processing System (IDAPS) is presented. The changes in the software modules are the result of additions to the application software of the system and an upgrade of the IBM 7094 Mod(1) computer to a 1301 disk storage configuration. Necessary information about IDAPS sofware is supplied to the computer programmer who desires to make changes in the software system or who desires to use portions of the software outside of the IDAPS system. Each software module is documented with: module name, purpose, usage, common block(s) description, method (algorithm of subroutine) flow diagram (if needed), subroutines called, and storage requirements.

Source record↗
NASA NTRS1973

Thermal control subsystem design of a Saturn/Uranus atmospheric entry probe for descent missions to 20 bars.

A study of scientific probes to explore the atmospheres of Saturn and Uranus to depths of between 2 and 30 bars is summarized. The study assessed configuration tradeoffs of recommended exploratory payloads, determined the types and quantities of the thermal control devices required, and evaluated thermal structural details and viable mission alternatives. These results indicated that a vented probe design with an environmental pressurization system for the first 2.5 bars of descent would satisfy the requirements for missions to either Saturn or Uranus to depths of approximately 20 bars. Parametric atmospheric descent thermal analyses are discussed and the effect of worst-case atmospheric models and navigational arrival uncertainties on mission performance are presented.

Webb, C. M.↗
NASA NTRS1974

Apollo experience report: Command and service module communications subsystem

The development of spacecraft communications hardware from design to operation is described. Programs, requirements, specifications, and design approaches for a variety of functions (such as voice, telemetry, television, and antennas) are reviewed. Equipment environmental problems such as vibration, extreme temperature variation, and zero gravity are discussed. A review of the development of managerial techniques used in refining the roles of prime and subcontractors is included. The hardware test program is described in detail as it progressed from breadboard design to manned flight system evaluations. Finally, a series of actions is recommended to managers of similar projects to facilitate administration.

Lattier, E. E., Jr.↗
NASA NTRS1974

Plated wire memory subsystem

The design, construction, and test history of a 4096 word by 18 bit random access NDRO Plated Wire Memory for use in conjunction with a spacecraft input/output and central processing unit is reported. A technical and functional description is given along with diagrams illustrating layout and systems operation. Test data is shown on the procedures and results of system level and memory stack testing, and hybrid circuit screening. A comparison of the most significant physical and performance characteristics of the memory unit versus the specified requirements is also included.

Carpenter, K. H.↗
NASA NTRS1973

Design, testing, and delivery of an interactive graphics display subsystem

An interactive graphics display system was designed to be used in locating components on a printed circuit card and outputting data concerning their thermal values. The manner in which this was accomplished in terms of both hardware and software is described. An analysis of the accuracy of this approach is also included.

Holmes, B.↗
NASA NTRS1974

Preliminary flight prototype waste collection subsystem

The zero gravity test program demonstrated the feasibility and practicability of collecting urine from both male and female crew members in a zero gravity environment in an earthlike manner not requiring any manual handling of urine containers. In addition, the testing demonstrated that a seat which is comfortable in both regimes of operation could be designed for use on the ground and in zero-gravity. Further, the tests showed that the vortex liquid/air separator is an effective liquid/air separation method in zero gravity. Visual observations indicate essentially zero liquid carry over. The system also demonstrated its ability to handle post elimination wipes without difficulty. The designs utilized in the WCS were verified as acceptable for usage in the space shuttle or other space vehicles.

Swider, J. E., Jr.↗
NASA NTRS1974

Apollo experience report: Spacecraft structure subsystem

The flightworthiness of the Apollo spacecraft structure was verified primarily through a rigorous, vehicle level, ground test program and flight tests. The failures and anomalies encountered during this testing were the major factors considered in determining necessary modifications to the basic design of the spacecraft structure. In this report, these failures, their causes, and their resolutions are discussed. A description of the spacecraft structure and discussions of the ground and flight test programs are presented.

Smith, P. D.↗
NASA NTRS1974

Development of the Viking Mars lander thermal control subsystem design

Two Viking spacecraft, each consisting of a lander capsule coupled to an orbiter, will be launched toward Mars during the summer of 1975. About a year later, the orbiters will go into orbit around Mars and the landers will descend to the surface for 90-day landed missions. The lander must withstand a wide variety of environmental and operational conditions during all phases of the mission, including prelaunch sterilization. On the surface of Mars, the lander internal temperatures must be controlled under widely varying thermal environments and atmospheric conditions. The lander thermal design is based on the maximum use of passive techniques and is integrated into the overall vehicle design and operation. The solutions to the unusual combinations of design problems and a summary of the results of full scale model testing under simulated mission conditions are presented.

Morey, T. F.↗
NASA NTRS1974

An automated water iodinating subsystem for manned space flight

Controlling microbial growth by injecting iodine (l2) into water supplies is a widely acceptable technique, but requires a specialized injection method for space flight. An electrochemical l2 injection method and l2 level monitor are discussed in this paper, which also describe iodination practices previously used in the manned space program and major l2 biocidal characteristics. The development and design of the injector and monitor are described, and results of subsequent experiments are presented. Also presented are expected vehicle penalties for utilizing the l2 injector in certain space missions, especially the Space Shuttle, and possible injector failure modes and their criticality.

Houck, O. K.↗