Journal of Institute of Control, Robotics and Systems (제어로봇시스템학회논문지)

Institute of Control, Robotics and Systems (제어로봇시스템학회)
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3-Dimensional Trajectory Optimization and Explicit Guidance for a Satellite Launch Vehicle with Yaw Maneuver

횡방향 기동을 하는 위성발사체의 3차원 궤적최적화와 직접식 유도기법

  • No, Ung-Rae (Korea Aerospace Research Institute) ;
  • Kim, Yu-Dan (Dept.of Aerospace Engineering, Seoul National University) ;
  • Park, Jeong-Ju (Korea Aerospace Research Institute) ;
  • Tak, Min-Je (Dept. of Aerospace Engineering, Korea Advanced Institute of Science and Technology)
  • Published : 2002.07.01
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Abstract

Ascent trajectory optimization and explicit guidance problems for a satellite launch vehicle with yaw maneuver in a 3-dimension are considered. The trajectory optimization problem with boundary conditions is formulated as a nonlinear programming problem by parameterizing the inertial pitch and yaw attitude control variables, and is solved by using the SQP algorithm. The flight constraints such as gravity-turn and range safety conditions are imposed. An explicit inertial guidance algorithm in the exoatmospheric phase is also presented. The guidance algorithm provides steering command and time-to-go value directly using the current states of the vehicle and the desired orbit insertion conditions. The liquid propelled Delta 2910 launch vehicle is used as a numerical model.

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References

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