3.4 WEIGHT ESTIMATION
The evaluation of the mass is only a rough approximation, because there were only some geometrical values to start with. Influence of the huge dimensions, which offers new and excludes present construction methods could not be taken into account. Here the single masses of the A340-300 were extrapolated.
If there were several equations for one part, an average value of the different results was taken to find a factor to extrapolate the A340 mass.
At the end, the MTOW is estimated by addition of the single masses (see appendix III.4) .
Table 3.4: Mass split
| Type | A340 300 | B747 200 | C601 | |||
| Unit | [Kg] | [%] | [Kg] | [%3 | [Kg] |
[%] |
| Wing |
36800 |
14.5 |
43200 |
11.9 |
87600 |
16.5 |
| Fuselage |
25000 |
9.9 |
33800 |
9.3 |
47500 |
9.3 |
| H. stabl. |
2100 |
0.8 |
3700 |
1.0 |
5500 |
1.0 |
| V. stabl. |
1000 |
0.4 |
1900 |
0.5 |
2790 |
0.5 |
| Gear |
9150 |
3.6 |
14900 |
4.1 |
20300 |
3.8 |
| Pylon |
3070 |
1.2 |
2300 |
0.7 |
7600 |
1.4 |
| Structure |
77200 |
30.5 |
99800 |
27.5 |
171290 |
32.4 |
| Engine |
16900 |
6.7 |
23600 |
6.5 |
35900 |
6.8 |
| System |
10300 |
4.1 |
11200 |
3.1 |
17800 |
3.4 |
| Equipment |
9500 |
3.7 |
11100 |
3.0 |
16610 |
3.1 |
| MWE |
114000 |
45.0 |
146000 |
40.2 |
241590 |
45.5 |
| Op . Equip . |
10100 |
3.9 |
16800 |
4.7 |
29110 |
5.5 |
| OEW |
124000 |
48.9 |
163000 |
44.9 |
270700 |
51.1 |
| Pay load |
28100 |
11.1 |
38400 |
10.6 |
56960 |
10.7 |
| Fuel |
101400 |
40 |
161500 |
44.5 |
203300 |
38 |
| MTOW |
253500 |
100 |
362900 |
100 |
531000 |
100 |