The Mariner 6 and 7 flight paths and their determination from tracking data
Determination of orbit estimates for Mariner 6 and 7 space probe flights
SEARCH · Search NASA
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.
Determination of orbit estimates for Mariner 6 and 7 space probe flights
Solder coating process for printed copper circuit protection
Open circuit and bias degradation tests in copper and cadmium sulfide thin film solar cells
High efficiency transformerless amplitude modulator coupled to RF power amplifier
Development of method and apparatus for spinning satellite about selected axis after reaching predetermined orientation
Analysis of typical Jupiter-Saturn-Pluto trajectory to determine characteristics of outer planet space missions and planetary quarantine constraints
Planetary quarantine constraint on 1977 Jupiter- Saturn-Pluto mission, determining fuel loading penalties, optimum biasing strategies and outer planet navigational characteristics
SDS-930 computer determines impact cost-decision value at any chronological point in definition phase of multiprogram project. Options, option combinations, and different displays are listed. Graphical procedure was chosen as best method for project.
Results of a study in which the amplitude of the E-W component E sub w of the convection electric field in the nightside magnetosphere has been inferred from the observed cross-L motions of whistler ducts within the plasmasphere, and several ducts distributed over 1 to 2 earth radii in L space and over plus or minus deg 15 around the longitude of the Eights, Antarctica, whistler station have been tracked simultaneously. The method appears capable of resolving fluctuations in E sub w with period T equal to approximately 15 min and rms amplitude as low as 0.05 mV/m. For variations with T greater than 1 hour the method has a sensitivity of the order of 0.01 mV/m. Three case studies are presented, two of which illustrate convection activity associated with relatively isolated substorms. In these two cases E sub w reversed from westward to eastward for a period following the decay of substorm bay activity. In the third case the substorm bay activity was prolonged, and E sub w remained westward and at enhanced levels until local dawn. Evidence was found that, at least in a limited longitudinal sector, perturbing substorm E sub w fields can penetrate deep within the plasmasphere. In two of the case studies comparisons of E sub w and the interplanetary magnetic-field theta component show evidence of a possible relation based on brief (less than or equal to 1 hour) southward excursions but not on long preceding southward events.
Results of an experiment to measure the scintillation at a satellite from a ground-based laser transmitter. The GEOS-II satellite in a nearly circular orbit of 1250 km was illuminated by a ground-based laser tracking station using a 4880-A CW argon laser. A detector aboard the satellite measured the incident light and telemetered the data to recording equipment on the ground. Log-amplitude variance, probability distributions, and scintillation frequency distributions are derived from the data. The probability distribution is shown to be log-normal. Log-amplitude variance and normalized power spectral density are shown to be within the limits measured for stellar scintillation.-
A philosophical view of the development of the universe and mans' place in developing his cultural conditions are presented. The effects of population growth on the ecology are analyzed. Propositions for improving the conditions of mankind are presented. The influence of cybernation and automation on the development of space exploration are described.
A flight control system concept is defined for approach flightpath control of an augmentor wing (or similar) powered-lift STOL configuration. The proposed STOL control concept produces aircraft transient and steady-state control responses that are familiar to pilots of conventional jet transports, and has potential for good handling qualities ratings in all approach and landing phases. The effects of trailing-edge rate limits, real-engine dynamics, and atmospheric turbulence are considered in the study. A general discussion of STOL handling qualities problems and piloting techniques is included.
Explore the source record for details and available documents.
Explore the source record for details and available documents.
A total of 48 operational flight instrumentation measurements were identified for use in performance monitoring and fault detection. The Operational Flight Instrumentation List contains all measurements identified for fault detection and annunciation. Some 16 controller data words were identified for use in fault detection and annunciation.
The operational flight instrumentation required for performance monitoring and fault detection are presented. Measurements by the burn through monitors are presented along with manifold and helium source pressures.
Stratospheric and mesospheric water vapor measurements were taken using the microwave lines at 22 GHz (22.235 GHz) and 183 GHz (183.31 GHz). The resonant cross sections for both the 22 GHz and the 183 GHz lines were used to model the optical depth of atmospheric water vapor. The range of optical depths seen by a microwave radiometer through the earth's limb was determined from radiative transfer theory. Radiometer sensitivity, derived from signal theory, was compared with calculated optical depths to determine the maximum height to which water vapor can be measured using the following methods: passive emission, passive absorption, and active absorption. It was concluded that measurements using the 22 GHz line are limited to about 50 km whereas the 183 GHz line enables measurements up to and above 100 km for water vapor mixing ratios as low as 0.1 ppm under optimum conditions.
The optimization of landing trajectories of the Boeing 737 is presented. The primary factor considered was the noise delivered to the population residing near an air terminal but passenger comfort, fuel consumption and time elapsed during the maneuver were also considered. A digital simulation of the aircraft, a noise model and a passenger comfort model, was completed. The digital simulation was made more efficient time-wise. A population model for an urban area was developed and the noise model was integrated into the population model. A steepest descent optimization algorithm was programmed. Some constant glide slope trajectories into an urban Airport were simulated and evaluated with respect to the performance index, and their ground track plotted.