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Articles by Affiani Machmudah
Total Records ( 2 ) for Affiani Machmudah
  Affiani Machmudah and Setyamartana Parman
  This study addresses a point-to-point of an arm robot motion planning in complex geometrical obstacle considering all kinematics and dynamics constraints. A continuous function of a seventh degree polynomial is utilized as a joint angle path. The path planning optimization objective is to minimize a joint angle traveling distance under avoiding collision constraint. After the best path has been discovered, the trajectories will be optimized with an objective is to minimize the total traveling time and the torque under the maximum velocity, the maximum acceleration, the maximum jerk and the maximum torque constraints. Three Degree of Freedom (3-DOF) planar robot will be utilized to simulate the proposed method. The computational strategy utilizing a Genetic Algorithm (GA) will be presented. There is no information regarding the region of the feasible seventh degree polynomial joint angle path so that the GA should search it first. At the first computation where the population is generated randomly, all individuals commonly collide with obstacles. It needs a requirement to escape from zero fitness. After the feasible individual has been discovered, the GA should evolve this individual to find the best one with the highest fitness value. Results show that the feasible joint angle path which is very smooth in the motion has succeeded to be found. The trajectories are also discovered successfully without exceeding the constraint values.
  Setyamartana Parman , Bambang Ari-Wahjoedi , Edward Halawa and Affiani Machmudah
  Attitude maneuvers of a Communication Technology Satellite (CTS)-like spacecraft using constant-amplitude thrusters is of great importance. The spacecraft consists of a rigid main body and two symmetrical solar panels. When the panels are large, they cannot be treated as rigid bodies anymore. They are supposed to behave structural flexibility. To discrete their motion, the finite element method is followed. Under constant-amplitude thrusts, steady-state attitude angle oscillations may occur in large amplitude after the maneuvers. Since, the spacecraft should point to the earth precisely, these oscillations must be reduced into small permissible values. To reduce residual attitude angle oscillations, Proportional Derivative (PD) based constant-amplitude input shaping logic is proposed to determine time locations of thruster switching. Then, under such inputs, attitude maneuvers of the spacecraft are simulated numerically. Results of simulations show that the precise orientation of the satellite can be achieved.
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