tailieunhanh - Aircraft Design Projects Episode 4

Tham khảo tài liệu 'aircraft design projects episode 4', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Project study scheduled long-range business jet 71 Wing taper ratio Wing av. thickness 15 Wing LE sweep 30 R Mwing Mfuel 8100 32400 kg Hence the wing is calculated at Mwing 11 209 kg This is per cent of MTOM. This is uncharacteristically high for this type of aircraft. The formula is based on old and existing aircraft types. The average value of aspect ratio for the source aircraft is about 6. The much higher aspect ratio of our design 10 seems to have caused a large increase in wing mass. In addition the formula was based on traditional metallic construction whereas our design will incorporate substantial composite structure. For these reasons we will apply a reduction factor of 25 per cent to the estimated mass Mwing 11 209 X 8407 kg MTOM As we have used the wing gross area we will assume that this mass includes the flap weight. Tail structure With little knowledge of the tail design at this time we will assume a representative percentage. We know that the extra control surface canard will add some weight so we will use a slightly higher percentage than normal for this type of aircraft per cent . As we will be constructing these surfaces in composite materials we will apply a technology reduction factor of 25 per cent. Mtail X 81 000 X 1519 kg MTOM Fuselage structure The mass of the body will be estimated using a formula for body1 with the parameter values shown below MTOM 81 000 kg O A length max. diameter VD 255m s Gives Mbody 9232 kg Increasing by 8 per cent for pressurisation 4 per cent for tail engine location and reducing by 10 per cent for modern materials and construction gives Mbody 9306 kg MTOM Nacelle structure Based on an engine thrust of 254 kN Mnacelles 1729 kg MTOM 72 Aircraft Design Projects Landing gear We will assume this to be per cent MTOM Mlanding gear 3604 kg Surface controls Using a typical value of X MTOM Ms controls 911 kg Aircraft structure Summing the above .