On non-coplanar Hohmann transfer using angles as parameters

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• 作者：ángel Rincón ; Patricio Rojo ; Elvis Lacruz…
• 关键词：Hohmann transfer ; Non ; coplanar orbit transfer ; Two ; impulse ; Optimization ; Plane change
• 刊名：Astrophysics and Space Science
• 出版年：2015
• 出版时间：September 2015
• 年：2015
• 卷：359
• 期：1
• 全文大小：842 KB
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• 作者单位：ángel Rincón (1) (2)
  Patricio Rojo (2)
  Elvis Lacruz (3)
  Gabriel Abellán (4)
  Sttiwuer Díaz (5)
  
  1. Departamento de Física, P. Universidad Católica de Chile, Casilla, 306, Santiago, Chile
  2. Departamento de Astronomía, Universidad de Chile, Casilla, 36-D, Santiago, Chile
  3. Centro de Investigaciones de Astronomía, A.P. 264, 5101, Mérida, Venezuela
  4. Departamento de Física, Universidad Central de Venezuela, AP 47270, Caracas, 1041-A, Venezuela
  5. Grupo de Información y Comunicación Cuántica, Departamento de Física, Universidad Simón Bolivar, Sartenejas, Edo. Miranda, 89000, Venezuela
  
• 刊物类别：Physics and Astronomy
• 刊物主题：Physics
  Astronomy
  
• 出版者：Springer Netherlands
• ISSN：1572-946X

文摘

We study a more complex case of Hohmann orbital transfer of a satellite by considering non-coplanar and elliptical orbits, instead of planar and circular orbits. We use as parameter the angle between the initial and transference planes that minimizes the energy, and therefore the fuel of a satellite, through the application of two non-tangential impulses for all possible cases. We found an analytical expression that minimizes the energy for each configuration. Some reasonable physical constraints are used: we apply impulses at perigee or apogee of the orbit, we consider the duration of the impulse to be short compared to the duration of the trip, we take the nodal line of three orbits to be coincident and the three semimajor axes to lie in the same plane. We study the only four possible cases but assuming non-coplanar elliptic orbits. In addition, we validate our method through a numerical solution obtained by using some of the actual orbital elements of Sputnik I and Vanguard I satellites. For these orbits, we found that the most fuel-efficient transfer is obtained by applying the initial impulse at apocenter and keeping the transfer orbit aligned with the initial orbit.