Analysis of Mariner VII preencounter anomaly
Mariner 7 preencounter anomaly in radio tracking data and trajectory investigated by computerized simulation
Gordon, H. J.↗
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Performance verification trajectories for the McDonnell-Douglas high cross-range shuttle configuration
Space shuttle trajectory performance data for east and west test range launch simulations
Etheridge, O. E.↗
Magnetic field of Mercury confirmed
Observations made by Mariner 10 during its third encounter with Mercury (Mercury III) are presented which confirm the tentative conclusion drawn from the first encounter (Mercury I) that Mercury has a modest intrinsic magnetic field. Some comparison between Mercury I and III data and trajectories is attempted, and the superior affirmative nature of Mercury III is pointed out. Definitive bow shock and magnetopause detections of solar wind deflection were made during both passes.
Ness, N. F.↗
Preentry communications study. Outer planets atmospheric entry probe
A pre-entry communications study is presented for a relay link between a Jupiter entry probe and a spacecraft in hyperbolic orbit. Two generic communications links of interest are described: a pre-entry link to a spun spacecraft antenna, and a pre-entry link to a despun spacecraft antenna. The propagation environment of Jupiter is defined. Although this is one of the least well known features of Jupiter, enough information exists to reasonably establish bounds on the performance of a communications link. Within these bounds, optimal carrier frequencies are defined. The next step is to identify optimal relative geometries between the probe and the spacecraft. Optimal trajectories are established for both spun and despun spacecraft antennas. Given the optimal carrier frequencies, and the optimal trajectories, the data carrying capacities of the pre-entry links are defined. The impact of incorporating pre-entry communications into a basic post entry probe is then assessed. This assessment covers the disciplines of thermal control, power source, mass properties and design layout. A conceptual design is developed of an electronically despun antenna for use on a Pioneer class of spacecraft.
Hinrichs, C. A.↗
Variational Algorithms for Nonlinear Smoothing Applications
A variational approach is presented for solving a nonlinear, fixed-interval smoothing problem with application to offline processing of noisy data for trajectory reconstruction and parameter estimation. The nonlinear problem is solved as a sequence of linear two-point boundary value problems. Second-order convergence properties are demonstrated. Algorithms for both continuous and discrete versions of the problem are given, and example solutions are provided.
Bach, Ralph E. Jr.↗
Foil bearings for axial and radial support of high speed rotors: Design, development, and determination of operating characteristics
Flexible surface thrust and journal foil bearings were fabricated, and their performance was demonstrated, both individually and jointly as a unified rotor support system. Experimental results are documented with graphs and oscilloscopic data of trajectories, waveforms, and scans of amplitude response. At speeds of 40,000 to 45,000 rpm and a mean clearance of the order of 15 to 20 micrometers (600 to 800 micrometers, the resilient, air lubricated, spiral groove thrust bearings support a load of 127 N (29 lb; 13 kgf), equivalent to 3.0 N/sq cm (4.5 lb/sq in 0.31 kgf sq cm). Journal bearings with polygonal sections provided stable and highly damped supports at speeds up to 50,000 rpm.
Licht, L.↗
RF coverage analysis and performance for Shuttle communication links
This paper describes the current work at NASA/Johnson Space Center in the area of RF coverage analysis and performance-assessment for the Space Shuttle Program communication and tracking radio links. Trajectories, antenna data, ground station and Shuttle hardware performance characteristics and RF link math models were assimilated to generate RF link performance predictions for the three basic mission phases - ascent, on-orbit, and descent. Results identify some earlier deficiencies that required re-configuration of the ground station. Overall performance is currently satisfactory.
Loh, Y.-C.↗
Encounter with Venus - An update
This report deals with early results from the Pioneer Venus Orbiter and multiprobe missions, which encountered Venus on December 4 and December 9, 1978, respectively. Initial results for the multiprobe mission and for the first 30 days of the Orbiter mission have already been reported. Additional mission features and updated mission parameters based on refined tracking data and trajectory computations are presented here. Scientific results for both missions are discussed which cover the first 130 days (or orbits) of the nominal 243-day Orbiter mission.
Colin, L.↗
Numerical simulation of airfoil ice accretion
A mathematical model of glaze and rime ice accretion on a two-dimensional airfoil is presented. The model employs standard methods for calculating the flow field and cloud droplet trajectories. This data is used as input to a thermodynamic analysis of the ice accretion process which includes liquid runback. The structure of the model allows for dynamic updating of the droplet collection efficiency and heat and mass transfer processes as the accreted ice shape changes. This results in the improved shape prediction over previously described methods. Simulations made with the model are compared to experimental results obtained for a NACA 0012 airfoil in the NASA/Lewis Icing Research Tunnel. The agreement with experiment is found to be generally satisfactory for some cases, but a need for improvements is indicated by others. Suggestions for improvements are made.
Macarthur, C. D.↗
The magnetic field of Mars: Implications from gasdynamics modeling
On January 21, 1972 the Mars-3 spacecraft observed a variation in the magnetic field during its periapsis passage over the dayside of Mars that was suggestive of entry into a Martian magnetosphere. The original data and trajectory have been obtained to simulate the observed variation of the magnetic field using gasdynamics. In the gasdynamic model, a flow field is first generated and then this flowfield is used to carry the interplanetary magnetic field through the Martian magnetosheath. The independence of the flow field and magnetic field calculation allows rapid convergence on an IMF orientation which would result in a magnetic variation similar to that observed by Mar-3. There appears to be no need to invoke an entry into a Martian magnetosphere to explain these observations.
Russell, C. T.↗
The magnetic field of Mars - Implications from gas dynamic modeling
On January 21, 1972, the Mars 3 spacecraft observed a variation in the magnetic field during its periapsis passage over the dayside of Mars that was suggestive of entry into a Martian magnetosphere. Original data and trajectory of the spacecraft have been obtained (Dolginov, 1983) and an attempt is made to simulate the observed variation of the magnetic field by using a gas dynamic simulation. In the gas dynamic model a flow field is generated and this flow field is used to carry the interplanetary magnetic field through the Martian magnetosheath. The independence of the flow field and magnetic field calculation makes it possible to converge rapidly on an IMF orientation that would result in a magnetic variation similar to that observed by Mars 3. There appears to be no need to invoke an entry into a Martian magnetosphere to explain these observations.
Russell, C. T.↗
TOMS and the NOAA/FAA volcano support plan
A plan to detect volcanic ash clouds that are aircraft hazards is discussed. The plan utilizes NOAA satellite data and trajectory analysis. Because current operational satellite sensors cannot unambiguously distinguish volcanic eruptions from meteorological clouds, the plan is designed to react to known eruptions rather than detect eruptions. However, the Total Ozone Mapping Spectrometer (TOMS) instrument has been used to detect sulfur dioxide clouds from volcanic eruptions regardless of cloudiness. If TOMS was flown on an operational NOAA satellite, NOAA would have an automated volcanic eruption detection system which could more effectively support the Federal Aviation Administration.
Matson, Michael↗
Three component laser Doppler measurements in an axisymmetric jet
A three-component laser Doppler anemometer (LDA) was used to acquire a detailed set of three-dimensional mean and fluctuating velocity measurements in a low-speed air jet entering a stagnant ambient, over the first 20 jet exit diameters along the jet trajectory. These data are physically consistent with previous measurements in axisymmetric jets. The relative difficulty of obtaining three-dimensional and two-dimensional LDA data is briefly discussed.
Kuhlmann, John M.↗
Three component velocity measurements in an axisymmetric jet using LDA
A commercial three-component laser Doppler anemometer (LDA) has been used to acquire a detailed set of three-dimensional mean and fluctuating velocity measurements in a low-speed air jet entering a stagnant ambient, over the first 15 jet exit diameters along the jet trajectory. These data are consistent with previous measurements in axisymmetric, turbulent jets. Mean velocity and Reynolds stress data approach a self-preserving behavior by x/D equal to about 15. However, the RMS turbulence fluctuations were not self-preserving at this axial location, as expected based upon previous experimental studies. These data confirm the ability to obtain reliable three-dimensional velocity data using the present three-dimensional LDA system.
Kuhlman, John M.↗
Three-component velocity measurements in an axisymmetric jet using LDV
A three-component laser Doppler velocimeter (LDV) has been used to acquire three-dimensional mean and fluctuating velocity measurements in a low-speed air jet entering a stagnant ambient, over the first 16 jet exit diameters along the jet centerline trajectory. These data are consistent with previous measurements in axisymmetric, turbulent jets. A comparison between radial traverses through the jet centerline in two orthogonal directions is also self-consistent. Mean velocity and Reynolds stress data approach a self-preserving behavior by x/D = 16. However, the RMS turbulence fluctuations were not yet self-preserving at this axial location, as expected based upon previous experimental studies. These data confirm the ability to obtain reliable three-dimensional velocity data using the present three-dimensional LDV system.
Kuhlman, John M.↗
A Trajectory Algorithm to Support En Route and Terminal Area Self-Spacing Concepts
This document describes an algorithm for the generation of a four dimensional aircraft trajectory. Input data for this algorithm are similar to an augmented Standard Terminal Arrival Route (STAR) with the augmentation in the form of altitude or speed crossing restrictions at waypoints on the route. Wind data at each waypoint are also inputs into this algorithm. The algorithm calculates the altitude, speed, along path distance, and along path time for each waypoint.
Aircraft operations↗
A Revised Trajectory Algorithm to Support En Route and Terminal Area Self-Spacing Concepts
This document describes an algorithm for the generation of a four dimensional trajectory. Input data for this algorithm are similar to an augmented Standard Terminal Arrival (STAR) with the augmentation in the form of altitude or speed crossing restrictions at waypoints on the route. This version of the algorithm accommodates descent Mach values that are different from the cruise Mach values. Wind data at each waypoint are also inputs into this algorithm. The algorithm calculates the altitude, speed, along path distance, and along path time for each waypoint.
Aircraft operations↗
The NASA Fireball Network Database
The NASA Meteoroid Environment Office (MEO) has been operating an automated video fireball network since late-2008. Since that time, over 1,700 multi-station fireballs have been observed. A database containing orbital data and trajectory information on all these events has recently been compiled and is currently being mined for information. Preliminary results are presented here.
Moser, Danielle E.↗