This paper describes a shape optimization study to maximize the range of a guided missile. To design a guided missile having maximum range, a shape optimization system is incorporated with a trajectory analysis program and an optimization technique. In particular, trajectory-dependent aerodynamic coefficients are fully considered. In the trajectory analysis step, a component buildup method is directly connected to the equation of motion to calculate aerodynamic coefficients at every time step. In the optimization step, a real-coded adaptive range genetic algorithm is adopted to determine the optimal shape of the global maximum range. The shape optimization system of a guided missile can maximize the range of the missile and yield the optimal shapes of canards and tailfins. Finally, the effects of trajectory-dependent aerodynamic coefficients, guidance, and control on the range of a missile are illustrated.= Mach number = angle of attack, rad c = canards deflection angle, rad

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This study investigated the effects of dietary supplementation with the effective microorganism (EM) on the growth performance, blood parameter, small intestinal microflora, and noxious gas emission of broilers. A total 720 1-d old ROSS 308 was randomly assigned to 6 dietary treatment groups: control, virginiamycin (6 mg/kg), 0.1% PB 0.1% EM, 0.5% EM, and 1.0% EM. Each treatment was fed to 4 replicates of 30 birds per diet for d 35. Two-phase feeding program with a starter diet from 0 to 3 wk, and a finisher diet from 4 to 5 wk was used in the experiment. Within each phase, a diet was formulated to meet or exceed NRC requirements of broilers for macro-and micronutrients. The diet and water were available ad libitum. Result indicated that during overall periods of the experiment, final weight, body weight gain, and feed intake were not different among dietary treatments. Feed conversion ratio was less (P<0.05) for EM treatments than control, antibiotics, and PB. Total cholesterol (TC), triglyceride (TRG), glucose (GLU), total protein (TP), calcium (CA), aspartate aminotransferase (AST) and alanine aminotransferase (ALT) were not different among dietary treatments. White blood cell (WBC), hemoglobin (Hb), heterophils (HE), lymphocyte (LY), monocytes (MO), and eosinophils (EO) were not different among dietary treatments. HE:LY was less (P<0.05) for EM0.5 treatments than control, antibiotics, and PB. Lactobacillus was greater (P<0.05) for EM treatments than control and antibiotics. E. coli and Salmonella were not different among dietary treatments. NH 3 and CO 2 wereless (P<0.05) for EM treatments than control. These results indicated that EM treatments were effective feed conversion ratio, noxious gas emission and micro flora population on the cecum in broilers.

This paper describes a research result of a external shape optimization study to maximize the range of the guided missile with canards and tailfins in atmospheric flight. For this purpose, the external shape optimization program which can enhance the range of a missile was developed, incorporated with the trajectory analysis and the optimization technique. In the trajectory analysis part, Missile DATCOM which utilizes the semi-empirical method was directly connected to the trajectory code to supply the aerodynamic coefficients efficiently at every time step. In the gliding flight trajectory after apogee, a maximum CL/CD trim condition calculation module was attached under the assumption of the missile continuously flying at maximum CL/CD condition. In the optimization part, a Response Surface Method(RSM) was adopted to reduce the computing time.

This paper investigated the roll lock-in phenomena of a canard-controlled missile with freely spinning tailfins by applying Falanga's roll-rate equation. To confirm and validate the accuracy of the results of the roll-rate and roll lock-in prediction for freely spinning tailfins, the results were compared with Blair's wind tunnel test data. For calculation of the roll-rate of freely spinning tailfins, rolling moment coefficients of the tailfins were obtained from the wind tunnel test data and roll-damping coefficients were calculated by missile DATCOM. The roll-rate and roll lock-in of the freely spinning tailfins were calculated by applying these values to the roll-rate equation for freely spinning tailfins. The calculation results showed good agreement with the wind tunnel test data, and the roll lock-in could be anticipated as well.