SEARCH · Engineering Papers
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.
Periodic and almost periodic trajectories in cislunar space - techniques for determining behavior of dynamical systems of known periodic solutions, and space flight safety concept
Meteoroid flux and puncture models for cislunar space
Radar measurement of differential group delay to moon, showing large differences in total cislunar electron content above 1000 km in solar and antisolar directions
NASA has been investigating potential translunar excursion concepts to take place in the 2020s that would be used to test and demonstrate long duration life support and other systems needed for eventual Mars missions in the 2030s. These potential trajectory concepts could be conducted in the proving ground, a region of cislunar and near-Earth interplanetary space where international space agencies could cooperate to develop the technologies needed for interplanetary spaceflight. Enabled by high power Solar Electric Propulsion (SEP) technologies, the excursion trajectory concepts studied are grouped into three classes of increasing distance from the Earth and increasing technical difficulty: the first class of excursion trajectory concepts would represent a 90-120 day round trip trajectory with abort to Earth options throughout the entire length, the second class would be a 180-210 day round trip trajectory with periods in which aborts would not be available, and the third would be a 300-400 day round trip trajectory without aborts for most of the length of the trip. This paper provides a top-level summary of the trajectory and mission design of representative example missions of these three classes of excursion trajectory concepts.
The dataset contains one million integrated cislunar orbit trajectories, for a time span of up to six years. The data was generated on LLNL HPC systems and is saved in the form of both HDF5 and CSVs.
We experimentally and computationally investigate a proposed frequency-domain method for detecting and tracking cislunar spacecraft and near-earth asteroids using heliostat fields at night. Unlike imaging, which detects spacecraft and asteroids by their streak in sidereally-fixed long-exposure photographs, our proposed detection method oscillates the orientation of heliostats concentrating light from the stellar field and measures the light’s photocurrent power spectrum at sub-milliHertz resolution. If heliostat oscillation traces out an ellipse fixed in the galactic coordinate system, spacecraft or asteroids produce a peak in photocurrent power spectrum at a frequency slightly shifted from the starlight peak. The frequency shift is on the scale of milliHertz and proportional to apparent angular rate relative to sidereal. Relative phase corresponds to relative angular position, enabling tracking. A potential advantage of this frequency-domain method over imaging is that detectivity improves with apparent angular rate and number of heliostats. Since heliostats are inexpensive compared to an astronomical observatory and otherwise unused at night, the proposed method may cost-effectively augment observatory systems such as NASA’s Asteroid Terrestrial-impact Last Alert System (ATLAS).
Reduced three-body and four-body problems in connection with cislunar trajectories
Optical devices for cislunar space experiments, reflecting telescopes for space astronomy, and pulsed laser tracking of passive satellites
Cislunar or earth swingby for interplanetary missions
Secular change examination in cislunar geomagnetic tail field gradient during summers of 1966 and 1967, using Explorer 33 and 35 results
Cumulative flux of interplanetary and cislunar space dust particles by Mariner 4 and OGO 3 spacecraft, noting particle impact rate
Cislunar space data for use as spacecraft development program design criteria guidelines
Space navigator operations, procedures and computer interface and manually aided onboard Apollo cislunar navigation system possible improvement
Picogram dust particle flux measurements in selenocentric cislunar and interplanetary space by Mariner 4, OGO 3 and Explorer 35
Apollo cislunar navigation capability and procedures, describing onboard data acquisition and digital processing equipment
Dust particle measurements in selenocentric and cislunar space /1967-1969/ by Lunar Explorer 35 and OGO 3
Since July 1967, knowledge concerning the distributions of picogram size particulate matter in selenocentric space has been obtained from the Lunar Explorer 35 dust particle experiment. For almost 40% of the time, the mean sporadic cumulative flux is quite similar to the flux in interplanetary space. However, there are fluctuations of an order of magnitude during major meteor showers. The coincident increase of the flux in selenocentric space during the shower periods has been observed for the fourth year. The 100-picogram sensor does not show an increase during shower times, indicating a mass threshold of less than 100 picograms for particles with velocities equal to or greater than lunar escape velocity. The flux values from Lunar Explorer 35 are compared to other long-lifetime measurements in selenocentric, cislunar and interplanetary space with excellent agreement for masses less than one nanogram.
CISLUNAR is a stand-alone computer program designed to generate the trajectory of a low-thrust spacecraft travelling in Earth-Moon space. The program allows the creation of functional trajectories dependent on the supplied spacecraft characteristics. The trajectory generation is a user interactive process. The original intent was for the program user to modify the necessary control values until a staisfactory trajectory has been created.