Use of coherent optics for onboard data processing
Digitized optical detectors for cloud data processing onboard satellite using Fourier analysis
Strong, J. P., III↗
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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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Engine onboard checkout system study
Design and implementation of space shuttle propulsion system onboard checkout and monitoring function
Vandekoppel, R. W.↗
Onboard spacecraft optical data processing
Onboard optical data processing for earth resource spacecraft and planetary spacecraft
Abidi, A. S. H.↗
Midcourse and approach guidance requirements for simplified onboard control of moon to earth trajectories
Development of procedures for midcourse and approach guidance of moon to earth trajectories based on optical angular measurements and onboard calculations
Hamer, H. A.↗
Fixed-angle translunar guidance procedures using onboard optical measurements
Fixed angle translunar guidance procedures using onboard optical measurements
Hamer, H. A.↗
An engineering study of onboard checkout techniques. Task 1: Requirements analysis and concepts
Concepts and requirements analysis for automated onboard checkout of manned space station
Mckinley, A. P.↗
An engineering study of onboard checkout techniques. Task 2: Software
Language and executive software requirements for automated onboard checkout of manned space station
Welsh, D. M.↗
Onboard versus ground checkout of fluid mechanical systems
Tradeoff of autonomous onboard checkout versus ground checkout of space shuttle fluid mechanical systems
Mavros, L. A.↗
Onboard cislunar navigation capability and procedures during Apollo lunar missions
Apollo cislunar navigation capability and procedures, describing onboard data acquisition and digital processing equipment
Swigert, J. L., Jr.↗
Onboard optical guidance instruments for outer planet spacecraft
Outer planets Grand Tour spacecraft onboard optical guidance instruments, discussing vidicon and image dissector systems designs
Stanton, R. H.↗
Simplified interplanetary guidance using onboard optical measurements
Midcourse and planetary approach guidance by onboard optical measurements, noting application to earth-Mars trajectories and Grand Tour missions
Hamer, H. A.↗
A guide to onboard checkout. Volume 7: RF communications
The radio frequency communications subsystem for a space station is considered, with respect to onboard checkout requirements. The subsystem comprises all equipment necessary for transmitting and receiving, tracking and ranging, command, multiple voice and television information, and broadband experiment data. The communications subsystem provides a radio frequency interface between the space station and ground stations, either directly or indirectly, through a data relay satellite system, independent free-flying experiment modules, and logistics vehicles. Reliability, maintenance, and failure analyses are discussed, and computer programming techniques are presented.
Source record↗
A guide to onboard checkout. Volume 5: Data management
The baseline data management subsystem for a space station is discussed. The subsystem consists of equipment necessary to transfer, store, and process data to and from users and subsystems. It acquires and conditions a wide variety of input data from experiments, vehicle subsystems sensors, uplinked ground communications, and astronaut-activated controls. Computer techniques for failure analysis, reliability, and maintenance checkout onboard the space station are considered.
Source record↗
A guide to onboard checkout. Volume 3: Electrical power
The baseline electrical power subsystem for a space station is considered. The subsystem was anlayzed in order to define onboard checkout requirements. Reliability, failure effects, and maintenance are discussed.
Source record↗
A guide to onboard checkout. Volume 4: Propulsion
The propulsion system for a space station is considered with respect to onboard checkout requirements. Failure analysis, reliability, and maintenance features are presented. Computer analysis techniques are also discussed.
Source record↗
Design and fabrication of a prototype for an automatic transport system for transferring human and other wastes to an incinerator unit onboard spacecraft, phase A
Three transport system concepts were experimentally evaluated for transferring human and nonhuman wastes from a collection site to an incineration unit onboard spacecraft. The operating parameters, merits, and shortcomings of a porous-pneumatic, nozzle-pneumatic, and a mechanical screw-feed system were determined. An analysis of the test data was made and a preliminary design of two prototype systems was prepared.
Labak, L. J.↗
Apollo experience report: Onboard navigational and alignment software
The onboard navigational and alignment routines used during the nonthrusting phases of an Apollo mission are discussed as to their limitations, and alternate approaches that have more desirable capabilities are presented. A more efficient procedure for solving Kepler's equation, which is used in the calculation of Kepler's problem and Lambert's problem is included, and a sixth-order predictor scheme with a Runge-Kutta starter is recommended for numerical integration. The extension of the rendezvous navigation state to include angle biases and the use of a fixed coordinate system is also evaluated.
Savely, R. T.↗
Simplified interplanetary guidance procedures using onboard optical measurements
Simplified guidance procedures have been developed which are based on preflight determination of the characteristics of perturbed trajectories. The results are devoted primarily to planetary approach guidance; however, some considerations for midcourse guidance are included. The methods are studied for an Earth-to-Mars trajectory but would be applicable to Grand Tour and other types of missions. Generally requiring only a single onboard optical angular measurement, the approach procedure predicts guidance corrections for the control of periapsis radius as well as orbital plane orientation. An error analysis has shown that the periapsis radius at Mars can be controlled to a 1 sigma accuracy of about 20 km if the guidance is performed 1/2 day before periapsis passage. If the guidance is performed at the Martian sphere of influence (2.2 days before periapsis), the error doubles because of the increased effect of measurement and maneuvering errors.
Hamer, H. A.↗