Numerical integration orbits and Brouwer and modified Brouwer orbits
Numerical integration orbits and Brouwer and modified Brouwer orbits
Hertz, H. G.↗
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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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Orbital imagery for planetary exploration. Volume 3 - Orbit selection and definition
Orbital imagery for planetary exploration - orbital selections for Mars, Venus, Mercury, and Jupiter
Hopper, M. L.↗
Methods for determining the orbital transfer requirements for near-earth orbits
Methods for determining orbital transfer requirements for near-earth orbits
Griffith, D. J.↗
Orbit and position determination for Mars orbiters and landers
Statistical orbit and position determination for Mars orbiters and landers based on Viking 1973 mission requirements, discussing tracking problems
Anderson, S. G.↗
Orbit and position determination for Mars orbiters and landers
Statistical orbit and position determination for Mars orbiters and landers based on Viking 1973 mission requirements, discussing tracking problems
Anderson, S. G.↗
Studies of orbit lifetimes of Venus and Mars Orbiters
Orbital lifetime calculations for Venus and Mars Orbiter mission plannings
Coady, R. E.↗
Use of orbit-to-orbit shuttles for hyperbolic rendezvous with returning planetary spacecraft
Use of orbit-to-orbit shuttles for hyperbolic rendezvous with returning interplanetary spacecraft
Brooks, D. R.↗
Space shuttle: Investigation of the McDonnell-Douglas orbiter and booster shuttle models in proximity at Mach numbers 2.0 to 6.0. Volume 2: Mach number 5 orbiter proximity data
Space Shuttle abort stage separation wind tunnel tests of orbiter and booster vehicles - orbiter proximity data, Mach number 5
Trimmer, L. L.↗
Space shuttle: Investigation of the McDonnell-Douglas orbiter and booster shuttle models in proximity at Mach numbers 2.0 to 6.0 Volume 4: Mach number 3 orbiter proximity data
Space shuttle abort stage separation wind tunnel tests of orbiter and booster vehicles - orbiter proximity data, Mach number 3
Trimmer, L. L.↗
Space shuttle: Investigation of the McDonnell-Douglas orbiter and booster shuttle models in proximity at Mach numbers 2.0 to 6.0. Volume 6: Mach number 2 orbiter proximity data
Space shuttle abort stage separation wind tunnel tests of orbiter and booster vehicles - orbiter proximity data, Mach number 2
Trimmer, L. L.↗
Earth based orbit determination for a Mars orbiting spacecraft
Earth based orbit determination for Mars orbiting spacecraft, comparing batch and sequential tracking filter data processing methods
Jordan, J. F.↗
Use of orbit-to-orbit shuttles as earth capture systems for round-trip planetary missions
Orbit-to-orbit shuttles as earth capture systems for round trip planetary missions, using hyperbolic rendezvous technique with returning interplanetary spacecraft
Brooks, D. R.↗
Cartography and orbit determination using TV data from a Mars orbiting spacecraft
Mars surface cartography and orbit determination using TV data from Mars orbiting spacecraft
Mohan, S. N.↗
Techniques of orbital decay and long-term ephemeris prediction for satellites in earth orbit
In the special perturbation method, Cowell and variation-of-parameters formulations of the motion equations are implemented and numerically integrated. Variations in the orbital elements due to drag are computed using the 1970 Jacchia atmospheric density model, which includes the effects of semiannual variations, diurnal bulge, solar activity, and geomagnetic activity. In the general perturbation method, two-variable asymptotic series and automated manipulation capabilities are used to obtain analytical solutions to the variation-of-parameters equations. Solutions are obtained considering the effect of oblateness only and the combined effects of oblateness and drag. These solutions are then numerically evaluated by means of a FORTRAN program in which an updating scheme is used to maintain accurate epoch values of the elements. The atmospheric density function is approximated by a Fourier series in true anomaly, and the 1970 Jacchia model is used to periodically update the Fourier coefficients. The accuracy of both methods is demonstrated by comparing computed orbital elements to actual elements over time spans of up to 8 days for the special perturbation method and up to 356 days for the general perturbation method.
Barry, B. F.↗
Equinoctial orbit elements - Application to artificial satellite orbits.
The matrizant of the two-body problem is developed in terms of elements that are free from singularities for zero eccentricities and zero- and ninety-degree inclinations. Retrograde equinoctial elements eliminate the singularity for inclinations near 180 degrees, with only minor changes in the expressions for the matrizant. The 'single-averaged' variation-of-parameters equations for these elements are developed for third-body, oblateness, and drag effects. Higher order terms are included in the expansions for the third-body and oblateness potential. A computer program that uses these equations to predict orbital evolution is described. Numerical results are given for a near-circular orbit.
Cefola, P. J.↗
Results of tests to determine the aerodynamic characteristics of two potential aeromaneuvering orbit-to-orbit shuttle (AMOOS) vehicle configurations in the NASA-Ames 3.5 foot hypersonic wind tunnel
An aerodynamic wind tunnel investigation was conducted in the NASA-Ames Research Center (ARC) 3.5-foot hypersonic facility to provide data for use in obtaining experimental force and static stability characteristics of two potential aeromaneuvering orbit-to-orbit shuttle (AMOOS) vehicle configurations. The experimental data were compared with the aerodynamic characteristics estimated using Newtonian theory, thus establishing the usefulness of these predictions. The candidate AMOOS configurations selected for the wind tunnel tests were the AMOOS 5B and HB configurations. Two flap configurations were tested for each candidate - a forward or compression surface flap and an aft or expansion flap. Photographs and sketches of the two configurations with different control surfaces are shown. It was determined that Newtonian theory generally predicted the aerodynamics of the 5B configuration with acceptable accuracy for all expansion flap deflections and for compression flap deflections less than or equal to 10 degrees. Flow separation upstream of large compression flap deflections was detected from the experimental data.
Ketter, F. C., Jr.↗
Tracking and orbit determination of near earth orbiting satellites using earth synchronous relay satellites
A Tracking Data Relay Satellite System (TDRSS) made up of two earth synchronous data relay satellites is proposed for the late 1970s to aid in the tracking, or take the place of ground tracking, or near-earth orbiters. Theoretical error analysis studies were conducted to evaluate the TDRSS concept of tracking user satellites. All major factors affecting orbit determination accuracy were considered in the analysis, including tracking system and dynamic modeling errors.
Bryant, W. C., Jr.↗
Results of oil flow visualization tests of an 0.010-scale model (52-OT) of the space shuttle orbiter-tank mated and orbiter configurations in the AEDC VKF tunnel B (IA17B)
An 0.010-scale model of the space shuttle (orbiter-tank mated and orbiter configurations) was tested in the AEDC VKF Tunnel B to investigate aerodynamic flow patterns. The tests utilized oil flow techniques to visualize the flow patterns. Tunnel free stream Mach number was 7.95 and nominal unit Reynolds number was 3.7 million per foot. Model angle of attack was varied from -5 deg through 10 deg and angle of sideslip was 0 deg and 2 deg. Photographs of resulting oil flow patterns are presented.
Daileda, J. J.↗