Analysis of a wheel-damped reaction boom control system
Hybrid satellite attitude control system deformation model, utilizing pivoted flexible boom with tip mass as actuator and inertia wheels to dampen gravity induced librations
Buckingham, A. 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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Thermal and tidal effect on the rotation of Mercury
Thermal tidal friction and gravitation effects on Mercury libration after solidification, noting equilibrium with orbital and rotational periods locked in 3/2 resonant state
Liu, H.-S.↗
On determining the moon's density function
Relation between moon density function, figure, external gravitational potential, and physical libration constants
Levie, S. L., Jr.↗
Laser ranging retroreflector
Laser ranging retroreflector deployed on lunar surface to study lunar librations for defining precisely lunar orbits and studying earth planetary structure - Apollo 14 flight
Alley, C. O.↗
Orbital science photography. Part H - Astronomical photography
Astronomical photography of zodiacal light and lunar libration clouds
Dunkelman, L.↗
Time-optimal control of gravity-gradient satellites with disturbances
Satellite time optimal attitude control, using gravity gradient technique with active libration damping
Zach, F. C.↗
Lunar far-side communication
Lunar far side communication, discussing libration point and lunar orbit relay system for high bit rate telemetry, TV and astronaut backpack communication
Coffman, J. W.↗
A semi-analytic theory for the motion of a lunar satellite
Lunar satellite motion semianalytic solution, considering perturbative effects due to gravitational fields, solar radiation pressure and libration
Felsentreger, T. L.↗
Lunar gravity analysis from long-term effects
Global lunar gravity field from weighted least squares analysis of Lunar Orbiters elements, deriving zonal and sectorial harmonics from libration data
Laing, P. A.↗
Preliminary study of the application of the Timation 3 satellite to earth physics
The Timation 3 is a timing and navigation satellite originally planned for launch in December 1972 into a circular orbit at 98 deg inclination 14,000 km altitude with gravity gradient stabilization. An error analysis indicates a satellite position uncertainty of about one meter, 80 percent of which is attributable to the assumed gravity model errors. The remaining uncertainties have a period equal to that of the satellites and can be filtered out yielding an effective uncertainty of about 10 cm in the study of phenomena having different periodicities. The accomplishment of these results depends on a careful consideration of solar radiation pressure taking account of the spacecraft reflecting properties and variations in the presentation area. Consideration is also given to the displacement of the laser reflectors from the center of mass of the spacecraft and to the dynamic coupling of any libration in attitude with the orbital motion. The results indicate that a good set of well distribution laser observations of Timation 3 could yield determinations of polar motion, sea floor spreading, solid earth tides, and earth rotation at the 10 cm level.
Carpenter, L.↗
Moments of inertia of the lunar globe, and their bearing on chemical differentiation of its outer layers.
It is pointed out that the observed moments of inertia of the moon, disclosed by its librations, are influenced mainly by the distribution of mass in the outer zone in which the lithostatic pressure is less than 10 kb (i.e., in the outer shell not more than 200 km deep); a conspicuous departure of such moments from those expected in hydrostatic equilibrium disclosed that these layers could never have been fluid. In the same way, the actual shape of the lunar surface cannot represent a solidified surface of a fluid, petrified at any distance from the earth. The shape of the moon and differences of its moments of inertia must reflect the way in which the initial process of cold accretion fell short of producing a globe with strictly spherically-symmetrical stratification of material. Such melting or lava flows as may have occurred at the moon's surface from time to time must have remained localized, and without much effect on the dynamical properties of the moon.
Kopal, Z.↗
Lunar orbital photography of astronomical phenomena.
This paper reports further progress on photography of faint astronomical and geophysical phenomena accomplished during the recent Apollo missions. Command module pilots have been able to photograph such astronomical objects as the solar corona, zodiacal light-corona transition region, lunar libration region, and portions of the Milky Way. The methods utilized for calibration of the film by adaptation of the High Altitude Observatory sensitometer are discussed. Kodak 2485 high-speed recording film was used in both 35-mm and 70-mm formats. The cameras used were Nikon f/1.2 55-mm focal length and Hasselblad f/2.8 80-mm focal length. Preflight and postflight calibration exposures were included on both the flight and control films, corresponding to luminances extending from the inner solar corona to as faint as 1/10 of the luminance of the light of the night sky. The photographs obtained from unique vantage points available during lunar orbit are discussed.
Mercer, R. D.↗
Gegenschein-Moulton region photography from lunar orbit
Apollo 16 photography during lunar orbit of the Gegenschein-Moulton region was used to determine the libration points of the Sun-Earth system. Triangulation for the system is discussed, along with background experimental information.
Dunkelman, L.↗
Minimum impulse three-body trajectories.
A rapid and accurate method of calculating optimal impulsive transfers in the restricted problem of three bodies has been developed. The technique combines a multi-conic method of trajectory integration with primer vector theory and an accelerated gradient method of trajectory optimization. A unique feature is that the state transition matrix and the primer vector are found analytical without additional integrations or differentiations. The method has been applied to the determination of optimal two and three impulse transfers between the L2 libration point and circular orbits about both the earth and the moon.
D'Amario, L.↗
The particle resonance in spiral galaxies - Nonlinear effects.
A theory is developed to account for the nonlinear effects, near the particle resonance, found by numerical integration. There are four equilibrium points in the rotating frame of reference: two of them unstable, at the minima of potential (L1, L2), and two stable, at the maxima of potential (L4, L5). Many particles are trapped in librating orbits around L4, L5. Using the lowest-order terms of a 'third integral' of motion near L4, L5, the behavior of the trapped orbits is determined, and the approximate theoretical results are compared with the orbits found numerically by computer. An estimate of the trapped mass is given. It amounts to about 30% of the total mass between 9 and 11 kpc when the particle resonance is at r sub s = 10 kpc and the maximum force due to the spiral is 4% of the axisymmetric force. Some effects due to these mass concentrations are found numerically and theoretically.
Contopoulos, G.↗
Asteroidal source of meteorites.
An effective mechanism for the placement of asteroidal fragments into earth-crossing orbits is discussed. It is pointed out that an asteroid in an orbit with a semimajor axis of about 3.27 AU, corresponding to the most apparent Kirkwood Gap, has a period almost exactly half that of Jupiter and will experience strong resonant perturbations by Jupiter. In the proposed mechanism, fragments 10 to 500 m in diameter resulting from collisions between asteroids located just outside the region in which libration due to the perturbations takes place are injected into the Kirkwood Gap.
Zimmerman, P. D.↗
Space Trajectory Error Analysis Program (STEAP) for halo orbit missions. Volume 1: Analytic and user's manual
Development, test, conversion, and documentation of computer software for the mission analysis of missions to halo orbits about libration points in the earth-sun system is reported. The software consisting of two programs called NOMNAL and ERRAN is part of the Space Trajectories Error Analysis Programs (STEAP). The program NOMNAL targets a transfer trajectory from Earth on a given launch date to a specified halo orbit on a required arrival date. Either impulsive or finite thrust insertion maneuvers into halo orbit are permitted by the program. The transfer trajectory is consistent with a realistic launch profile input by the user. The second program ERRAN conducts error analyses of the targeted transfer trajectory. Measurements including range, doppler, star-planet angles, and apparent planet diameter are processed in a Kalman-Schmidt filter to determine the trajectory knowledge uncertainty. Execution errors at injection, midcourse correction and orbit insertion maneuvers are analyzed along with the navigation uncertainty to determine trajectory control uncertainties and fuel-sizing requirements. The program is also capable of generalized covariance analyses.
Byrnes, D. V.↗
Space Trajectory Error Analysis Program (STEAP) for halo orbit missions. Volume 2: Programmer's manual
The six month effort was responsible for the development, test, conversion, and documentation of computer software for the mission analysis of missions to halo orbits about libration points in the earth-sun system. The software consisting of two programs called NOMNAL and ERRAN is part of the Space Trajectories Error Analysis Programs. The program NOMNAL targets a transfer trajectory from earth on a given launch date to a specified halo orbit on a required arrival date. Either impulsive or finite thrust insertion maneuvers into halo orbit are permitted by the program. The transfer trajectory is consistent with a realistic launch profile input by the user. The second program ERRAN conducts error analyses of the targeted transfer trajectory. Measurements including range, doppler, star-planet angles, and apparent planet diameter are processed in a Kalman-Schmidt filter to determine the trajectory knowledge uncertainty.
Byrnes, D. V.↗