Parasitic probe antenna Patent
Low loss parasitic probe antenna for prelaunch tests of spacecraft antennas
Cribb, H. E.↗
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Electronic checkout system for space vehicles Patent
Digital computer system for automatic prelaunch checkout of spacecraft
Johnson, H. G.↗
Device for separating occupant from an ejection seat Patent
Ejector for separating astronaut from ejection seat during prelaunch or initial launch phase of flight
Mussett, E. W.↗
Natural environment criteria for the NASA High Energy Astronomy Observatory /HEAO/
Prelaunch, launch, and inflight earth orbital environment data for HEAO spacecraft
Weidner, D. K.↗
Sounding rocket instrumentation data Aerobee 350, Flight 17.05GT-CG
Aerobee 350 flight and instrument data including prelaunch tests, instrument installation and orientation, and postflight analysis information
Pincus, B. R.↗
Automatic theodolite for pre-launch azimuth alignment of the Saturn space vehicles
Prelaunch automatic azimuth alignment theodolites for Saturn 1B and Saturn 5 space vehicles inertial guidance system, discussing return images separation and error signal generation
Kokot, W.↗
The role of space simulation testing in the development of Mariner spacecraft
Thermal/vacuum space simulation assembly level testing for prelaunch confidence of Mariner spacecraft
Devries, T. R.↗
Program to determine space vehicle response to wind turbulence
Computer program was developed as prelaunch wind monitoring tool for Saturn 5 vehicle. Program accounts for characteristic wind changes including turbulence power spectral density, wind shear, peak wind velocity, altitude, and wind direction using stored variational statistics.
Wilkening, H. D.↗
Spacecraft orbit/earth scan derivations, associated APL program, and application to IMP-6
The derivation of a time shared, remote site, demand processed computer program is discussed. The computer program analyzes the effects of selected orbit, attitude, and spacecraft parameters on earth sensor detections of earth. For prelaunch analysis, the program may be used to simulate effects in nominal parameters which are used in preparing attitude data processing programs. After launch, comparison of results from a simulation and from satellite data will produce deviations helpful in isolating problems.
Smith, G. A.↗
Crew/cargo and logistics module definition
The logistics requirements for the space station cargo, the initial buildup, and the 90 day resupply are presented, along with the conceptual selection for the orbiter crew accommodations and the GSS logistics system. Various module configurations are outlined; structural/mechanical, environmental, temperature, voice communication, and data bus subsystems are also reviewed. Ground operations and module prelaunch and launch operations are discussed, as well as logistics system interfaces for space shuttles and stations.
Source record↗
IMP series report/bibliography
The main characteristics of the IMP spacecraft and experiments are considered and the scientific knowledge gained is presented in the form of abstracts of scientific papers using IMP data. Spacecraft characteristics, including temporal and spatial coverages, are presented followed by an annotated bibliography. Experiments conducted on all IMP's (including prelaunch IMP's H and J) are described. Figures are presented showing the time histories, through the end of 1970, of magnetic field, plasma, and energetic particle experiments.
King, J. H.↗
Apollo/Saturn 5 consolidated instrumentation plan for AS-511 (Apollo 16)
The consolidated instrumentation plan, for employing optical and electronic data acquisition systems to monitor the performance and trajectory of Apollo Saturn 5 vehicle 511 during the launch phase of the mission (prelaunch, liftoff to insertion), is presented. Telemetry, optical, and electronic tracking equipment on board the vehicle and data acquisition systems monitoring the flight are discussed. Flight safety instrumentation, vehicle data transmission systems, and geophysical instrumentation are also described.
Clark, D. E.↗
Computer simulation of Saturn 5 response to pre-launch wind loads
A digital computer program is described which was developed to estimate Saturn 5 response to prelaunch wind conditions at Cape Kennedy. The program computes displacement and bending moment statistics as a function of parameters defining the atmospheric environment. A sample problem is provided to illustrate utilization of the program.
Coffin, T.↗
Space shuttle guidance, navigation and control design equations. Volume 4: Deorbit and atmospheric operations
A baseline set of equations which fulfill the computation requirements for guidance, navigation, and control of the space shuttle orbiter vehicle is presented. All shuttle mission phases are covered from prelaunch through landing/rollout. The spacecraft flight mode and the aircraft flight mode are addressed. The baseline equations may be implemented in a single guidance, navigation, and control computer or may be distributed among several subsystem computers.
Cox, K. J.↗
Cold-welding test environment
A flight test was conducted and compared with ground test data. Sixteen typical spacecraft material couples were mounted on an experimental research satellite in which a motor intermittently drove the spherical moving specimens across the faces of the fixed flat specimens in an oscillating motion. Friction coefficients were measured over a period of 14-month orbital time. Surface-to-surface sliding was found to be the controlling factor of generating friction in a vacuum environment. Friction appears to be independent of passive vacuum exposure time. Prelaunch and postlaunch tests identical to the flight test were performed in an oil-diffusion-pumped ultrahigh vacuum chamber. Only 50% of the resultant data agreed with the flight data owing to pump oil contamination. Identical ground tests were run in an ultrahigh vacuum facility and a ion-pumped vacuum chamber. The agreement (90%) between data from these tests and flight data established the adequacy of these test environments and facilities.
Wang, J. T.↗
Television Data Display System (TDDS)
A television data display system at KSC is described which displays computer processed data derived from space vehicle launch and prelaunch tests. The general system capabilities and technical features are discussed in separate sections under the headings of: (1) operational use, (2) system description, (3) computer programs, (4) computer hardware, and (5) adaptability.
Sendler, K.↗
Use of the space shuttle to avoid spacecraft anomalies
An existing data base covering 304 spacecraft of the U.S. space program was analyzed to determine the effect on individual spacecraft failures and other anomalies that the space shuttle might have had if it had been operational throughout the period covered by the data. By combining the results of this analysis, information on the prelaunch activities of selected spacecraft programs, and shuttle capabilities data, the potential impact of the space shuttle on future space programs was derived. The shuttle was found to be highly effective in the prevention or correction of spacecraft anomalies, with 887 of 1,230 anomalies analyzed being favorably impacted by full utilization of shuttle capabilities. The shuttle was also determined to have a far-reaching and favorable influence on the design, development, and test phases of future space programs. This is documented in 37 individual statements of impact.
Source record↗
Computer simulation for attitude disturbance torques for the Tiros-series.
Description of the Tiros-M Magnetic Attitude Prediction Program (TMMGAP), a simulation program designed to assist in the rotational motion control of the Tiros-series spacecraft. The subsystems of the program include input, attitude simulation, executive, attitude control and output components, simulating solar radiation pressure torque, gravity gradient torque, residual magnetic moment torque, and magnetic attitude control torques. The program provides data for prelaunch studies for launch window selection and mission planning, facilitates spacecraft spin axis reorientation after launch, provides spin axis control recommendations to meet mission constraints, and assists in the interpretation of cloud cover data. The program is characterized as effective in controlling spin axis and in processing picture data.
Sugai, I.↗