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At least 145 records · Page 8
All sourcesNASA NTRSDOE OSTI
NASA NTRS1991

Cosmoids - Solution to the Pioneer 10 and 11 meteoroid measurement enigma

Experimental results from the three dust experiments on the Pioneer 11 and 12 spacecraft are used here to define the distribution and structural characteristics of what is believed to be the dominant population of meteoroids in the inner solar system. No two experiments agreed on the dust distribution and only the Imaging Photopolarimeter experiment could be fitted to the prevailing model of dust spiraling inward from the asteroid belt. Meteoroid Detection Experiment data showed a nearly constant flux from 1 to 18 AU. Reexamination of Asteoroid/Meteoroid Experiment or 'Sisyphus' data shows that the instrument measured a population of long-period meteoroids called cosmoids, composed mainly of water which dominates the dust distribution. Once the prevailing short period dust model is discounted, the results from the three instruments are shown to agree.

Dubin, Maurice↗
NASA NTRS1992

Spacecraft survivability in the meteoroid and debris environment

A number of methods for providing adequate protection from meteoroid and orbital debris impact are available to space vehicle designers. Several techniques to reduce the risks from meteoroid and debris (M&D) impact are presented and assessed in the context of Space Station Freedom (SSF) applications. Evaluations of these options were made using BUMPER, a computer program to perform M&D analyses. M&D survivability can be improved by conducting an in-depth analysis of spacecraft penetration risks to reveal weak areas of the design and to determine optimal distribution of shielding and/or protection capability around the space vehicle. This paper compares enhanced hypervelocity impact shielding techniques that are more weight efficient than conventional shielding approaches. Other design and operational strategies to reduce meteoroid and debris risks are also discussed.

Christiansen, Eric L.↗
NASA NTRS1992

Phobos and Deimos are sources of meteoroids

Data of Pioneer 10 meteoroid penetration detectors were revised taking into account the orientation of detectors and the spacecraft velocity relative to the sporadic meteor flux. The meteor flux density increases as an exponent to the orbit of Mars for two times for the particles with masses greater than 10(exp -6) g and six times for the particles with masses greater than 10(exp -12) - 10(exp -9) g then decreases after the orbit. Ejections of secondary meteoroid particles from surfaces of Phobos and Deimos are a possible explanation for the increase in meteoroid flux.

Andreev, V. V.↗
NASA NTRS1993

Report of the Meteoroid and Debris Special Investigation Group

The LDEF Meteoroid and Debris Special Investigation Group (hereafter M&D SIG) was formed to maximize the data harvest from LDEF by permitting the characterization of the meteoroid and space debris impact record of the entire satellite. Thus, our work is complementary to that of the various M&D PI's, all of whom are members of the SIG. This presentation will summarize recent results and discussions concerning five critical SIG goals: (1) classification of impactors based upon composition of residues, (2) small impact (microimpact) features, (3) impact cratering and penetration data to derive projectile sizes and masses, (4) particulate flux estimates in low-Earth orbit, and (5) the LDEF Meteoroid and Debris database.

Zolensky, Michael E.↗
NASA NTRS1993

New meteoroid model predictions for directional impacts on LDEF

An extensive body of data, from meteors, zodiacal light, spacecraft-borne impact detectors (Helios, Pioneer, Galileo, Ulysses), and other sources, forms the basis of a new numerical model for the distributions of interplanetary meteoroids. For each of the five populations in this model it is possible to evaluate meteoroid concentration and flux for oriented surfaces or detectors having arbitrary position and velocity in interplanetary space. For a spacecraft in geocentric orbit the effects of gravitational focussing and shielding by the Earth have been newly derived with full attention to the directionality of the particles, both on approach (i.e., relative to a massless Earth) and at the target. This modeling approach was exercised to provide an estimate of meteoroid fluence for each of several oriented surfaces on LDEF.

Divine, Neil↗
NASA NTRS1992

Meteoroid ablation in Neptune's atmosphere

Meteoroid ablation in the Neptune atmosphere can influence the chemistry of the upper atmosphere through the supply of oxygen, in the case of water-ice meteoroid ablation, which will eventually be converted to CO in the upper atmosphere, and through the ablation and recondensation of relatively refractory meteoroid material, which leads to the production of dust particles that can act as sites for lower-atmosphere condensation of hydrocarbons. An analysis is presently made of ablation rate calculation uncertainties. The ablation equations presented are applicable to other planets.

Moses, Julianne I.↗
NASA NTRS1997

The Space Shuttle Program Pre-Flight Meteoroid and Orbital Debris Risk/Damage Predictions and Post-Flight Damage Assessments

The pre-flight predictions and postflight assessments carried out in relation to a series of Space Shuttle missions are reviewed, and data are presented for the meteoroid and orbital debris damage observed on the Hubble Space Telescope during the 1994 Hubble repair mission. Pre-flight collision risk analyses are carried out prior to each mission, and in the case of an unacceptable risk, the mission profile is altered until the risk is considered to be acceptable. The NASA's BUMPER code is used to compute the probability of damage from debris and meteoroid particle impacts based on the Poisson statistical model for random events. The penetration probability calculation requires information concerning the geometry of the critical systems, the penetration resistance and mission profile parameters. Following each flight, the orbiter is inspected for meteoroid and space debris damage. The emphasis is on areas such as the radiator panels, the windows and the reinforced carbon-carbon structures on the leading wing edges and on the nose cap. The contents of damage craters are analyzed using a scanning electron microscope to determine the nature and origin of the impactor. Hypervelocity impact tests are often performed to simulate the observed damage and to estimate the nature of the damaging particles. The number and type of damage observed provides information concerning the orbital debris environment.

Levin, George M.↗
NASA NTRS2003

Simulation of Prebiotic Processing by Comet and Meteoroid Impact: Implications for Life on Early Earth and Other Planets

We develop a reacting flow model to simulate the shock induced chemistry of comets and meteoroids entering planetary atmospheres. Various atmospheric compositions comprising of simpler molecules (i.e., CH4, CO2, H2O, etc.) are investigated to determine the production efficiency of more complex prebiotic molecules as a function of composition, pressure, and entry velocity. The possible role of comets and meteoroids in creating the inventory of prebiotic material necessary for life on Early Earth is considered. Comets and meteoroids can also introduce new materials from the Interstellar Medium (ISM) to planetary atmospheres. The ablation of water from comets, introducing the element oxygen into Titan's atmosphere will also be considered and its implications for the formation of organic and prebiotic material.

Dateo, Christopher E.↗
NASA NTRS1992

Interim Report of the Meteoroid and Debris Special Investigation Group

The LDEF Meteoroid and Debris Special Investigation Group (hereafter M&D SIG) was formed to maximize the data harvest from LDEF by permitting the characterization of the meteoroid and space debris impact record of the entire satellite. Thus, our work is complementary to that of the various M&D PIs, all of whom are members of the SIG. This presentation will summarize recent results and discussions concerning five critical SIG goals: (1) Classification of impactors based upon composition of residues; (2) Small impact (microimpact) features; (3) Impact cratering and penetration data to derive projectile sizes and masses; (4) Particulate flux estimates in low-Earth orbit; (5) The LDEF Meteoroid and Debris database.

Zolensky, Michael E.↗
NASA NTRS2004

MEM: A physical-based directional meteoroid model

Three years of research conducted by the University of Western Ontario into the nature and distribution of the sporadic sources have been incorporated into a Meteoroid Engineering Model (MEM) by members of the Meteoroid Environments Office at NASA's Marshall Space Flight Center. This paper gives a broad overview of this model, new features of which include: a) identification of the sporadic radiants with real sources of meteoroids, such as comets, b) a physics-based approach which yields accurate fluxes and directionality for interplanetary spacecraft anywhere from 0.2 AU to 2 AU. and c) velocity distributions obtained from theory and validated against observation. Its use and application is also described, along with existing limitations and plans for future improvements.

McNamara, H.↗
NASA NTRS2004

NASA's Meteoroid Environment Office

The Meteoroid Environment Office (MEO) has recently been formed within the Engineering Directorate at NASA's Marshall Space Flight Center. With agency-wide responsibility for defining the meteoroid environments for spacecraft engineering operations purposes, the MEO will distribute a state-of-the-art sporadic meteoroid model as well as meteor shower forecasts for spacecraft operators. To improve these models and forecasts, the MEO will manage an observation and research program. Office responsibilities, products, and plans will be discussed in this paper. The MEO is sponsored by the Office of Safety and Mission Assurance at NASA Headquarters.

Suggs, Robert M.↗
NASA NTRS2005

Foam core shield (FCS) systems : a new dual - purpose technology for shielding against meteoroid strike damage and for thermal control of spacecrafts/satellite components

A new technology is being developed that can protect spacecraft and satellite components against damage from meteoroid strikes and control the thermal environment of the protected components. This technology, called Foam Core Shield (FCS) systems, has the potential to replace the multi-layer insulation blankets (MLI) that have been used on spacecraft for decades. In order to be an attractive candidate for replacing MLI, FCS systems should not only provide superior protection against meteoroid strikes but also provide an equal or superior ability to control the temperature of the protected component. Properly designed FCS systems can provide these principal functions, meteoroid strike protection and thermal control, with lower system mass and a smaller system envelope than ML.

thermal environment↗
NASA NTRS2006

Improving The Near-Earth Meteoroid And Orbital Debris Environment Definition With LAD-C

To improve the near-Earth meteoroid and orbital debris environment definition, a large area particle sensor/collector is being developed to be placed on the International Space Station (ISS). This instrument, the Large Area Debris Collector (LAD-C), will attempt to record meteoroid and orbital debris impact flux, and capture the same particles with aerogel. After at least one year of deployment, the whole system will be brought back for additional laboratory analysis of the captured meteoroids and orbital debris. This project is led by the U.S. Naval Research Laboratory (NRL) while the U.S. Department of Defense (DoD) Space Test Program (STP) is responsible for the integration, deployment, and retrieval of the system. Additional contributing team members of the consortium include the NASA Orbital Debris Program Office, JAXA Institute of Space and Astronautical Science (ISAS), Chiba University (Japan), ESA Space Debris Office, University of Kent (UK), and University of California at Berkeley. The deployment of LAD-C on the ISS is planned for 2008, with the system retrieval in late 2009.

Liou, J.-C.↗
NASA NTRS2008

Flux of Kilogram-Sized Meteoroids from Lunar Impact Monitoring

Routine lunar impact monitoring has harvested over 110 impacts in 2 years of observations using 0.25, 0.36 and 0.5 m telescopes and low-light-level video cameras. The night side of the lunar surface provides a large collecting area for detecting these impacts and allows estimation of the flux of meteoroids down to a limiting luminous energy. In order to determine the limiting mass for these observations, models of the sporadic meteoroid environment were used to determine the velocity distribution and new measurements of luminous efficiency were made at the Ames Vertical Gun Range. The flux of meteoroids in this size range has implications for Near Earth Object populations as well as for estimating impact ejecta risk for future lunar missions.

Suggs, Robert↗
NASA NTRS2013

The Meteoroid Environment and Spacecraft

Difference between a meteoroid and asteroid? center dot It's all a matter of size, but there is no formal limit on the size of the biggest meteoroid or smallest asteroid. center dot Generally anything bigger than 10 meters in diameter is considered an asteroid. center dot However, the currently accepted process is that if it is detected in space and given a designation by the Minor Planet Center, it is an asteroid, no matter how big - example: 2008 TC3 is listed as an asteroid, despite being only 2 meters in diameter. Dynamical studies (e.g. Wiegert & Vaubaillon, 2008) indicate that - Helion sources originate mainly from Jupiter family comets (JFCs) - Apex sources from retrograde Halley family comets (HFCs) and long period comets. - Toroidal sources from prograde HFCs? center dot >90% of meteoroids in inner Solar System come from comets. Three main sources - Photographic (Super‐Schmidt) - Specular Radar center dot (Harvard Radio Meteor Project (HRMP) center dot CMOR center dot AMOR - HPLA center dot ALTAIR center dot Jicamarca center dot Arecibo center dot Photographic have lower number statistics and unique biases - Nighttime only - approx. V3.5 dependence on light production - Detection sensitivity is function of angular velocity center dot Radar has different biases - Ionization production also steep function of velocity (V3.5‐4) - Initial trail radius, finite velocity and diffusion attenuation center dot HPLA biases - Still controversy over how much and what sort of biases may or may not be present.

Cooke, William J.↗
NASA NTRS2019

Meteoroid Impact Detection for Exploration of Asteroids (MIDEA)

Asteroids contain a wealth of resources including water and precious metals that can be extracted. These resources could be applied to in-space manufacture of products that depend less on material launched from Earth's surface. The Meteoroid Impact Detection for Exploration of Asteroids (MIDEA) concept addresses the challenge of characterizing an asteroid surface using a small satellite with a constellation of free-flying plasma sensors to assess the asteroid’s viability for in situ resource utilization (ISRU). The plasma sensors detect ions ejected from the surface of an asteroid by meteoroid impacts, enabling the surface composition to be inferred. The objective of this NIAC Phase I study was to demonstrate feasibility of the MIDEA architecture in the context of proximity operations around an asteroid target and to develop the design of an orbital geometry and attitude control strategy for the ultralight plasma sensors. This was undertaken through a simulation framework to identify and characterize a favorable orbit for the MIDEA sensor constellation, and developing a sensor geometry that is consistent with maintaining the pointing requirements necessary to operate with sufficient power generation. Our study showed that a polar orbit aligned along the asteroid terminator provided sufficient stability for the sensors in the low gravitational environment under the influence of substantial solar radiation pressure. Reflector vanes using controlled reflectivity devices implemented with liquid crystal technology are capable of maintaining the sensor attitude so that it consistently points its solar panels in the sun direction and the sensor electrode at the asteroid surface. Finally, the reduction in meteoroid impact detection due to visibility constraints from the proposed orbit does not substantially extend the expected mission duration. These results indicate that the MIDEA concept can be achievable using a 10–20 kg spacecraft, which would be able to characterize the surface composition of an asteroid within 30–50 days of proximity operations. This architecture, implemented in parallel to multiple asteroid targets, would enable widespread exploration of near-Earth asteroids at low cost.

Asteroids↗
NASA NTRSDate not supplied

Realistic gravitational focusing of meteoroid streams

A meteor shower can be modeled, to first order, as a parallel stream of particles encountering the Earth. Gravity bends the trajectories of these particles inward, producing an increase in flux both near the planet and along the anti-radiant line. This effect is known as gravitational focusing, and the interception of a portion of meteoroid trajectories by the Earth or another massive body is known as planetary shielding. For a perfectly parallel meteoroid stream, gravitational focusing produces a flux singularity along the anti-radiant line, near which intense enhancements in flux occur. In reality, meteoroids will exhibit some dispersion in their motion that removes this singularity. We present a modified analytic treatment of gravitational focusing and planetary shielding that takes this dispersion into account and discuss its ramifications for several problems in meteor astronomy.

Althea Valkyrie Moorhead↗
NASA NTRSDate not supplied

Handling Singularities in Meteoroid Environment Modeling

A meteoroid environment model must describe, at a bare minimum, the local density or flux of meteoroids. To accomplish this, many models make use of analytic equations to convert orbital distributions to number density, or to compute the effects of a planet's gravity on flux and speed. However, these equations often contain singularities that are unrealistic. For instance, the orbit-to-density conversion used by Jones (2006) is unbound at peri- and aphelion, and the gravitational focusing algorithms presented by Staubach et al. (1997) are unbound along the anti-radiant line. We present methods for removing these singularities that result in more realistic descriptions of the meteoroid environment.

Althea Valkyrie Moorhead↗