WEIGHT ESTIMATION

 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.

M_draft_formula
M Draft = Estimated term draft/Estimated term reference*M Reference

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

An UHCA was born