A harmonic L4 orbit for the very restricted four-body problem
Harmonic L-4 orbit for very restricted four-body problem determined by method of general perturbations using Chebyshev series
EARTH-MOON SYSTEM↗
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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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Physical constants as determined from radio tracking of the Ranger lunar probes
Radio-tracking data from Ranger lunar missions for estimated physical constants of earth and moon
PHYSICAL PROPERTY↗
Astrodynamics research at MSFC
Earth, moon, and interplanetary trajectories in astrodynamics research project
EARTH-MOON TRAJECTORY↗
The scientific value of manned lunar exploration.
Scientific value of manned lunar exploration
EARTH-MOON SYSTEM↗
Station-keeping in the vicinity of collinear libration points with an application to a lunar communications problem.
Feedback control system to position satellite in vicinity of unstable collinear libration point with application to lunar communication problem
SATELLITE CONTROL↗
The origin and dynamical evolution of the moon.
Tidal friction theory of lunar origin and dynamic evolution
EARTH-MOON SYSTEM↗
Periodic motion around the triangular libration point in the restricted problem of four bodies.
Periodic motion around triangular libration point in restricted four-body problem of earth-moon-sun system
EARTH-MOON SYSTEM↗
Station-keeping in the vicinity of collinear libration points with an application to a lunar communications problem.
Feedback control system to position satellite in vicinity of unstable collinear libration point applied to lunar communication problem
LUNAR COMMUNICATION↗
Development of the iterative guidance mode with its application to various vehicles and missions.
Iterative guidance mode with application to three- dimensional upper stage vacuum flight
INERTIAL GUIDANCE↗
Photography of the Earth's Cloud Satellites from an Aircraft
Photography from aircraft of cloud-like objects in vicinity of libration points L4 and L5 of earth- moon system
AERIAL PHOTOGRAPHY↗
Lunar transportation - Far-term options.
Reuseable shuttle transportation system for lunar base logistics, estimating cost and performance
SPACE FLIGHT↗
Lunar rotational dissipation in solid body and molten core
Analyses of Lunar Laser ranges Shaw a displacement in direction of the Moon's pole of rotation which indicates that strong dissipation is acting on the rotation.
Thermal history earth-moon systems evolutions tide↗
Getting to the Lunar Libration Points
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Astronomical Gravity-Wave Interferometer: Testing ↗
A Survey of Ballistic Transfers to Low Lunar Orbit
A simple strategy is identified to generate ballistic transfers between the Earth and Moon, i.e., transfers that perform two maneuvers: a trans-lunar injection maneuver to depart the Earth and a Lunar Orbit Insertion maneuver to insert into orbit at the Moon. This strategy is used to survey the performance of numerous transfers between varying Earth parking orbits and varying low lunar target orbits. The transfers surveyed include short 3-6 day direct transfers, longer 3-4 month low energy transfers, and variants that include Earth phasing orbits and/or lunar flybys.
Transfers↗
A Survey of Ballistic Transfers to the Lunar Surface
In this study techniques are developed which allow an analysis of a range of different types of transfer trajectories from the Earth to the lunar surface. Trajectories ranging from those obtained using the invariant manifolds of unstable orbits to those derived from collision orbits are analyzed. These techniques allow the computation of trajectories encompassing low-energy trajectories as well as more direct transfers. The range of possible trajectory options is summarized, and a broad range of trajectories that exist as a result of the Sun's influence are computed and analyzed. The results are then classified by type, and trades between different measures of cost are discussed.
Earth-Moon trajectories↗
Targeting Low-Energy Transfers to Low Lunar Orbit
A targeting scheme is presented to build trajectories from a specified Earth parking orbit to a specified low lunar orbit via a low-energy transfer and up to two maneuvers. The total transfer delta V (velocity) is characterized as a function of the Earth parking orbit inclination and the departure date for transfers to each given low lunar orbit. The transfer delta V (velocity) cost is characterized for transfers constructed to low lunar polar orbits with any longitude of ascending node and for transfers that arrive at the Moon at any given time during a month.
mission designs↗
Monthly Variations of Low-Energy Ballistic Transfers to Lunar Halo Orbits
The characteristics of low-energy transfers between the Earth and Moon vary from one month to the next largely due to the Earth's and Moon's non-circular, non-coplanar orbits in the solar system. This paper characterizes those monthly variations as it explores the trade space of low-energy lunar transfers across many months. Mission designers may use knowledge of these variations to swiftly design desirable low-energy lunar transfers in any given month.
Mission Design↗