Item Details
Estimates of Minimum Energy Requirements for RangeControlled Return of a Nonlifting Satellite From a Circular Orbit
by Charlie M. Jackson, Jr.
 Format
 Book; Government Document; Online; EBook
 Published
 Washington, [D.C.] : National Aeronautics and Space Administration, 1961.
 Language
 English
 Series
 NASA Technical Note
 Summary
 Existing expressions are used to obtain the minimum propellant fraction required for return from a circular orbit as a function of vacuum trajectory range. The solutions for the parameters of the vacuum trajectory are matched to those of the atmospheric trajectory to obtain a complete return from orbit to earth. The results are restricted by the assumptions of (1) impulsive velocity change, (2) nearly circular transfer trajectory, (3) spherical earth, atmosphere, and gravitational field, (4) exponential atmospheric density variation with attitude and (5) a nonrotating atmosphere. Calculations are made to determine the effects of longitudinal and lateral range on required propellant fraction and reentry loading for a nonrotating earth and for several orbital altitudes. The single and twoimpulse method of return is made and the results indicate a "trade off" between propellant fraction required and landingposition accuracy. An example of a return mission from a polar orbit is discussed where the initial deorbit point is the intersection of the North Pole horizon with the satellite orbit. Some effects of a rotating earth are also considered. It is found that, for each targetorbitalplane longitudinal difference, there exists a target latitude for which the required propellant fraction is a minimum.
 Description
 33 p. : ill. ; 26 cm.
 Mode of access: Internet.
 Notes
 Document ID: 20040006328.
 "NASA TN D980."
 "Langley Research Center, Langley Air Force Base, Va."
 "November 1961."
 Cover title.
 Includes bibliographical references (p. 15).
 Series Statement
 NASA technical note ; D980
 Copyright & PermissionsRights statements and licenses provide information about copyright and reuse associated with individual items in the collection.
 No Copyright  United States
 Technical Details

 Staff View
LEADER 03067nam a2200481Ia 4500001 011448732003 MiAaHDL005 20141009010000.0006 m d007 cr bn auaua008 070716s1961 dcua bt f000 0 eng da 20040006328a sdruiuc6395688a (OCoLC)155852909a FER c FERa UIUUa L1629a Jackson, Charles M.a Estimates of minimum energy requirements for rangecontrolled return of a nonlifting satellite from a circular orbit / c by Charlie M. Jackson, Jr.a Washington, [D.C.] : b National Aeronautics and Space Administration, c 1961.a 33 p. : b ill. ; c 26 cm.a NASA technical note ; v D980a Document ID: 20040006328.a "NASA TN D980."a "Langley Research Center, Langley Air Force Base, Va."a "November 1961."a Cover title.a Includes bibliographical references (p. 15).a Existing expressions are used to obtain the minimum propellant fraction required for return from a circular orbit as a function of vacuum trajectory range. The solutions for the parameters of the vacuum trajectory are matched to those of the atmospheric trajectory to obtain a complete return from orbit to earth. The results are restricted by the assumptions of (1) impulsive velocity change, (2) nearly circular transfer trajectory, (3) spherical earth, atmosphere, and gravitational field, (4) exponential atmospheric density variation with attitude and (5) a nonrotating atmosphere. Calculations are made to determine the effects of longitudinal and lateral range on required propellant fraction and reentry loading for a nonrotating earth and for several orbital altitudes. The single and twoimpulse method of return is made and the results indicate a "trade off" between propellant fraction required and landingposition accuracy. An example of a return mission from a polar orbit is discussed where the initial deorbit point is the intersection of the North Pole horizon with the satellite orbit. Some effects of a rotating earth are also considered. It is found that, for each targetorbitalplane longitudinal difference, there exists a target latitude for which the required propellant fraction is a minimum.a Mode of access: Internet.a Trajectories (Mechanics)a Artificial satellites x Orbits.a Artificial satellites x Propulsion systems.a United States. b National Aeronautics and Space Administration.a Langley Research Center.b UIU c UIUC d 20141113 s google u uiug.30112106915025 y 1961 r pd q bib
 Staff View