| Popis: |
Compared with the conventional ground rocket launching, air-launching has many advantages. However, comprehensive and integrated system design approach is required because the physical geometry of air launch vehicle is limited by the mother plane. Given mission objective is to launch 7.5kg nano-satellite to the target orbit of 700km x 700km using the mother plane, F-4E Phantom as the first stage. The launching altitude and velocity are 12km, Mach number 1.5, respectively. The total mass, length and diameter constraints of the rocket are imposed by the mother plane. The system design of the air-launching rocket is performed using the MDF(Multidisciplinary Feasible) optimization approach. Sequentially using the gradient based SQP(Sequential Quadratic Programming) algorithm. Analysis modules include mission analysis, staging, propulsion analysis, configuration analysis, weight analysis, aerodynamics analysis, and trajectory analysis. As a result of system optimization, a supersonic air launching rocket with total mass of 1244.91kg, total length of 6.36m, outer diameter of 0.60m, and the payload mass of 7.5kg is successfully designed. |
