Satellite orbits derived from a gravitational model of the earth

1961 ◽  
Vol 7 ◽  
pp. 154-163
Author(s):  
Paul H. Savet
2019 ◽  
Vol 28 (1) ◽  
pp. 180-190
Author(s):  
Ireneusz Wlodarczyk

AbstractWe computed the impact solutions of the potentially dangerous Near Earth Asteroid (NEA) 2001 BB16 based on 47 optical observations from January 20.08316 UTC, 2001, through February 09.15740 UTC, 2016, and one radar observation from January 19.90347 UTC, 2016. We used two methods to sample the starting Line of Variation (LOV). First method, called thereafter LOV1, with the uniform sampling of the LOV parameter, out to LOV = 5 computing 3000 virtual asteroids (VAs) on both sides of the LOV, which gives 6001 VAs and propagated their orbits to JD2525000.5 TDT=February 12, 2201. We computed the non-gravitational parameterA2=(34.55±7.38)·10–14 au/d2 for nominal orbit of 2001 BB16 and possible impacts with the Earth until 2201. For potential impact in 2195 we find A2=20.0·10−14 au/d2. With a positive value of A2, 2001 BB16 can be prograde rotator. Moreover, we computed Lyapunov Time (LT) for 2001 BB16, which for all VAs, has a mean value of about 25 y. We showed that impact solutions, including the calculated probability of a possible collision of a 2001 BB16 asteroid with the Earth depends on how to calculate and take into account the appropriate gravitational model, including the number of perturbing massive asteroids. In some complicated cases, it may depend also on the number of clones calculated for a given sigma LOV1. The second method of computing the impact solutions, called thereafter LOV2, is based on a non-uniformly sampling of the LOV. We showed that different methods of sampling the LOV can give different impact solutions, but all computed dates of possible impacts of the asteroid 2001 BB16 with the Earth occur in accordance at the end of the 22nd century.


2018 ◽  
Vol 7 (1) ◽  
pp. 94
Author(s):  
Anatole Eugene Djieto Lordon ◽  
Mbohlieu YOSSA ◽  
Christopher M Agyingi ◽  
Yves Shandini ◽  
Thierry Stephane Kuisseu

Gravimetric studies using the ETOPO1-corrected high resolution satellite-based EGM2008 gravity data was used to define the surface extent, depth to basement and shape of the Mamfe basin. The Bouguer anomaly map was produced in Surfer 11.0. The Fast Fourier Transformed data was analyzed by spectral analysis to remove the effect of the regional bodies in the study area. The residual anomaly map obtained was compared with the known geology of the study area, and this showed that the gravity highs correspond to the metamorphic and igneous rocks while the gravity lows match with Cretaceous sediments. Three profiles were drawn on the residual anomaly map along which 2D models of the Mamfe basin were drawn. The modeling was completed in Grav2dc v2.06 software which uses the Talwini’s algorithm and the resulting models gave the depth to basement and the shape of the basement along the profiles. After processing and interpretation, it was deduced that the Mamfe basin has an average length and width of 77.6 km and 29.2 km respectively, an average depth to basement of 5 km and an overall U-shape basement. These dimensions (especially the depth) theoretically create the depth and temperature conditions for petroleum generation. 


2021 ◽  
Author(s):  
Kiyoshi Kuramoto ◽  

<p>MMX (Martian Moons eXploration) is the 3rd sample return mission of JAXA/ISAS following Hayabusa and Hayabusa2. The MMX spacecraft will be launched in 2024 by an H-III rocket and make a round trip to the Martian system ~5 years. In the proximity of the Martian moons for 3 years, MMX will observe them along with the Martian atmosphere and surrounding space and conduct multiple landings on Phobos to collect Phoboss-indigenous materials. Owing to the lack of definitive evidence, the origin of Phobos and Deimos is under debate between the two leading hypotheses: the capture of volatile-rich primordial asteroid(s) and the in-situ formation from a debris disk that generated by a giant impact onto early Mars. Whichever theory is correct, the Martian moons likely preserve key records on the evolution of the early solar system and the formation of Mars. Through close-up observations of both moons and sample return from Phobos, MMX will settle the controversy of their origin, reveal their evolution, and elucidate the early solar system evolution around the region near the snow line. Global circulation and escape of the Martian atmosphere will also be monitored to reveal basic processes that have shaped and altered the Martian surface environment. The MMX spacecraft consists of three modules with chemical propulsion systems. By releasing used modules at appropriate timings, the spacecraft mass is reduced to allow orbital tuning to quasi-satellite orbits around Phobos, landings on Phobos surface, and the escape from the Martian gravity to return to the Earth. MMX will arrive at the Martian system in 2025 and start close-up observations of Phobos from quasi-satellite orbits. Among the total of 7 mounted instruments for scientific observations, TENGOO (telescope camera) and LIDAR will conduct high-resolution topography mapping and OROCHI (multi-band visible camera), MIRS (infra-red spectrometer provided by CNES), MEGANE (gamma-ray and neutron spectrometer provided by NASA), and MSA (ion mass spectrum analyzer) will survey surface composition and its heterogeneity. Hydrous minerals and interior ice are important observational targets because they, if identified, strongly support the capture hypothesis. Data taken by these instruments will be also useful for the landing site selection and characterization. Before the first landing, a rover (provided by CNES/DLR) will be released near the sampling site to collect data on surface regolith properties to be referred for the mothership landing operation. The rover will carry cameras, miniRAD (thermal mapper), and RAX (laser Raman spectrometer) to collect data on the physical and mineralogical characteristics of the Phobos surface around the sampling site. In early 2027, Mars will come to its closest approach to the Earth which minimizes the communication delay between the spacecraft and the Earth station. Together with the timing relatively far from Sun-Mars conjunctions and the Martian equinoxes, this period is the most favorable for landing operations that need real-time communication with the ground station and solar illumination undisturbed by eclipses. MMX will use two sampling systems, the C-sampler using a coring mechanism equipped on the tip of a manipulator and the P-sampler (provided by NASA) using a pneumatic mechanism equipped on a landing leg. After the stay near Phobos, the MMX spacecraft will be transferred to Deimos-flyby orbits to conduct Deimos observations, and then the return module will depart the Martian system in 2028. During the stay in the Martian system, MMX will also conduct wide-area observations of the Martian atmosphere using imagers (OROCHI, MIRS, and TENGOO) to study the atmospheric dynamics and the water vapor and dust transport. Simultanenousely, MSA will survey ions not only released and sputtered from Phobos's surface but also escaped from the Martian upper atmosphere. CMDM (dust monitor) will continuously survey the dust flux around the moons to assess the processes of space weathering by micrometeoroid bombardments and the possible formation of dust rings along the moons’ orbits. The sample capsule will come back to the Earth in 2029. Complimentarily with remote sensing studies, returned samples will provide us strong cosmo-chemical constraints for the origin of Phobos as well as those for early solar system processes.   </p>


2017 ◽  
Vol 7 (1) ◽  
Author(s):  
L.E. Sjöberg ◽  
E.W. Grafarend ◽  
M.S.S. Joud

AbstractA geosynchronous satellite orbits the Earth along a constant longitude. A special case is the geostationary satellite that is located at a constant position above the equator. The ideal position of a geostationary satellite is at the level of zero gravity, i.e. at the geocentric radius where the gravitational force of the Earth equals the centrifugal force. These forces must be compensated for several perturbing forces, in particular for the lunisolar tides. Considering that the gravity field of the Earth varies not only radially but also laterally, this study focuses on the variations of zero gravity not only on the equator (for geostationary satellites) but also for various latitudes. It is found that the radius of a geostationary satellite deviates from its mean value of 42164.2 km only within ±2 m, mainly due to the spherical harmonic coefficient J


Author(s):  
Sung Wook Paek 1 ◽  
Sangtae Kim 2

The development of oceanography and meteorology has greatly benefited from remotely sensed satellite data of the atmosphere and ocean. For oceanographers, meteorologists, hydrologists and climatologists to obtain high-quality satellite data, orbits along which the satellites move must be designed carefully. For this reason, Sun-synchronous, repeat ground track orbits have traditionally been used for visible-wavelength and infrared Earth observations. As the needs for varied datasets are growing, however, new classes of Earth-observing missions are emerging such as interferometry and radiometry to name a few. On the other side, satellite platforms and onboard sensors are getting more compact and less expensive, allowing developing nations to launch their own satellites and under-researched parts of the Earth be studied. In light of these changes, this paper introduces new types of satellite orbits from celestial mechanics perspectives, whose applications will be detailed further in the follow-up work.


This paper is devoted to developing the necessary orbital theory for predicting the lifetimes of satellites moving in an oblate atmosphere and subjected to the perturbations due to odd zonal harmonics in the geopotential. The effects of odd zonal harmonics and atmospheric oblateness are expressed as multiplying factors, F (oz) and F (ao), to be applied to the lifetime predictions calculated in the absence of the perturbations. The results are valid for the great majority of orbits about the Earth, and in particular for all orbital eccentricities between 0 and 1; but the limits set for the controlling parameters exclude ( a ) near-polar orbits with perigee heights lower than about 180 km, and ( b ) orbits having inclinations within a narrow band centred on 63.4°. The results show that, when the controlling parameters are at their upper limits, either F (oz) or F (ao) can change the lifetime by up to about 35%, and taken together they can produce changes of up to 60%, if the initial and final positions of perigee are at specified points on the orbit and the eccentricity exceeds 0.2. Such combinations of values rarely arise, however, and the effects are more often of order 10-20%. Even at these moderate levels, the effects need to be taken into account in order to make realistic estimates of the decay dates of satellites in the last few months of their lives.


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