A preliminary study of optimizing the skin lamination on the straight section of the fuselage has be done when only the airtight loads is considered. Combined the finite element software NASTRAN solver and the genetic algorithm to achieve the specific process by ISIGHT software,and to make up for deficiencies by ISIGHT C + + programming. Under airtight loading,analysis obtained the best lamination sequence,ply angles and layers of the fuselage skin. Contrast the before and after the optimization of composite fuselage,the equivalent section of the fuselage to reduce the 16. 2% of the body weight of the structure; contrast to the metal air-frame of A320-200,corresponding fuselage sections reduced 26. 5%,improving the structural efficiency.The calculation method can be automated to improve the computational efficiency. This method can achieve the initial read,automated calculations and read the results of the whole process,and reduces the amount of computation time.

The Quiet Spike is a telescoping forward fuselage extension that alters the bow shock of the classic N-wave pressure signature generated by aircraft travelling at supersonic speed.The bow shock is broken up into sequence of weak shocks to reduce sonic boom.Supersonic airliner of the"shuttle"layout is analyzed.Based on CFD(Computerized Fluid Dynamics) and waveform parameter method,different geometrical parameters of multi-segment quiet spikes are studied.The results shows that length of quiet spike can regulate the interference degree of the shock wave,diameter and vertex angle can decide the initial pressure of the quiet spike,the segment makes a significant influence on the rising time.