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Author: Prasun N. Desai Publisher: ISBN: Category : Astrodynamics Languages : en Pages : 36
Book Description
In this investigation, which considers precession effects, minimum initial LEO masses were obtained for parking orbits characterized by having near-equatorial inclinations, high eccentricities, and three-dimensional departure burns. Shows that there are a set of orbits characterized by low to moderate essentricities (e = 0.2 to 0.5) and nonequatorial inclinations (i = 70° to 140°) that reduce the initial LEO mass penalty. Therefore, careful selection of a parking orbit at Mars can enhance the potential for satisfying science requirements with minimal mass penalties.
Author: Prasun N. Desai Publisher: ISBN: Category : Astrodynamics Languages : en Pages : 36
Book Description
In this investigation, which considers precession effects, minimum initial LEO masses were obtained for parking orbits characterized by having near-equatorial inclinations, high eccentricities, and three-dimensional departure burns. Shows that there are a set of orbits characterized by low to moderate essentricities (e = 0.2 to 0.5) and nonequatorial inclinations (i = 70° to 140°) that reduce the initial LEO mass penalty. Therefore, careful selection of a parking orbit at Mars can enhance the potential for satisfying science requirements with minimal mass penalties.
Author: National Aeronautics and Space Adm Nasa Publisher: ISBN: 9781729111871 Category : Languages : en Pages : 36
Book Description
For any round-trip Mars mission, the selection of a parking orbit at Mars must consider the precession caused by the oblateness of the planet. This precession will affect the departure condition for Earth return and, therefore, the initial mass required in low Earth orbit (LEO). In this investigation, which considers precession effects, minimum initial LEO masses were obtained for parking orbits characterized by having near-equatorial inclinations, high eccentricities, and three-dimensional departure burns (i.e., a burn with an in-plane and an out-of-plane velocity increment component). However, because near-equatorial inclination orbits have poor planetary coverage characteristics, they are not desirable from a science viewpoint. To enhance the potential for satisfying science requirements along with landing site accessibility, a penalty in the initial LEO mass is required. This study shows that there are a set of orbits characterized by low to moderate essentricities (e = 0.2 to 0.5) and nonequatorial inclinations (i = 70 to 140 deg) that reduce this initial LEO mass penalty. Therefore, careful selection of a parking orbit at Mars can enhance the potential for satisfying science requirements with minimal mass penalties. Desai, Prasun N. and Braun, Robert D. and Powell, Richard W. Langley Research Center RTOP 506-49-11-01...
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781720574255 Category : Languages : en Pages : 50
Book Description
The determination of orbital window characteristics is of major importance in the analysis of human interplanetary missions and systems. The orbital launch window characteristics are directly involved in the selection of mission trajectories, the development of orbit operational concepts, and the design of orbital launch systems. The orbital launch window problem arises because of the dynamic nature of the relative geometry between outgoing (departure) asymptote of the hyperbolic escape trajectory and the earth parking orbit. The orientation of the escape hyperbola asymptotic relative to earth is a function of time. The required hyperbola energy level also varies with time. In addition, the inertial orientation of the parking orbit is a function of time because of the perturbations caused by the Earth's oblateness. Thus, a coplanar injection onto the escape hyperbola can be made only at a point in time when the outgoing escape asymptote is contained by the plane of parking orbit. Even though this condition may be planned as a nominal situation, it will not generally represent the more probable injection geometry. The general case of an escape injection maneuver performed at a time other than the coplanar time will involve both a path angle and plane change and, therefore, a DELTA V penalty. Usually, because of the DELTA V penalty the actual departure injection window is smaller in duration than that determined by energy requirement alone. This report contains the formulation, characteristics, and test cases for five different launch window modes for Earth orbit. These modes are: (1) One impulsive maneuver from a Highly Elliptical Orbit (HEO) (2) Two impulsive maneuvers from a Highly Elliptical Orbit (HEO) (3) One impulsive maneuver from a Low Earth Orbit (LEO) (4) Two impulsive maneuvers from LEO (5) Three impulsive maneuvers from LEO.Young, ArchieMarshall Space Flight CenterLAUNCH WINDOWS; LOW EARTH ORBITS; MARS MISSIONS; ELLIPTICAL ORBITS; SPACECRAFT LAUNCHING; HY
Author: James E. Oberg Publisher: Stackpole Books ISBN: 0811766624 Category : Science Languages : en Pages : 222
Book Description
How feasible is a manned Mars flight? How soon will it be possible? How long will it take? What kind of spacecraft will make the journey? What kind of data will be collected? What are the advantages of a manned flight over an unmanned? Mission to Mars discusses these questions and more in this serious, documented treatment of the not-too-distant manned expedition to Mars. The shuttle has proved successful and an enthusiastic boost to American interest in space. But while many laypeople wonder “what’s next,” scientists are planning what they feel is the next logical step. Drawing on the vast amount of data sent back by Viking orbiters and probes, and existing developments in propulsion and space technology, space experts all over have been speculating, analyzing, and exchanging ideas relative to the long-awaited mission to Mars. Other factors, critical to an intelligent discussion of such an undertaking are included here: spaceship design and assembly, propulsion systems, navigation principles, life support systems, selecting a landing site, scientific activities on Mars, cost factors, political and social issues.
Author: Prasun N. Desai
Author: Prasun N. Desai
Author: National Aeronautics and Space Adm Nasa
Author: Prasun N. Desai
Author: National Aeronautics and Space Administration (NASA)
Author: James E. Oberg
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Author: James Evans Lyne
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