TY - JOUR
ID - 105009
TI - Coplanar Maneuvers Transfer for Mission Design with Lowest ∆ʋ using Series Solution
JO - Kirkuk Journal of Science
JA - KUJSS
LA - en
SN - 3005-4788
AU - J. Hamwdi, Mayada
AU - A.Zaki, Wafaa
AU - K. Izzet, Ahmed
AD -
Y1 - 2015
PY - 2015
VL - 10
IS - 3
SP - 155
EP - 170
KW - Coplanar Maneuvers
KW - Series Solution
KW - Hohmann Transfer Maneuver
KW - Orbital Maneuver Optimization
DO - 10.32894/kujss.2015.105009
N2 - Orbital maneuver transfer time is traditionally accomplished using direct numerical sampling to find the mission design with the lowest delta-ʋ requirements. The availability of explicit time series solutions to the Lambert orbit determination problem allows for the total delta-ʋ of a series of orbital maneuvers to be expressed as an algebraic function of only the individual transfer times. Series solution was applied for Hohmann transfer and Bi-elliptic transfer and comparing between Hohmann transfer and Bi-elliptic transfer for long distance. It has been concluded that Hohmann transfer is more appropriate when the ratio of radius of final orbit to initial orbit (R) is less than 11.94.
The purpose of this work is to minimize total full requirements, as well known that no refueling station in space, then using the computed ∆ʋ for determining the mass propellant consumed ∆m, at different specific impulse of the propellants, help us to carefully plane a mission to minimize the propellant mass carried on the rocket.
UR - https://kujss.uokirkuk.edu.iq/article_105009.html
L1 - https://kujss.uokirkuk.edu.iq/article_105009_6fa051f4b110c18db7634a8e6fa1cd35.pdf
ER -