The objective of the proposal is to set up a three-level-parameter cost estimation method that allows the determination of the final cost for the fuselage design under analysis.
The tree-structure of the procedure allows a quick, easy and friendly-user inclusion of the main parameters determining the final cost of a fuselage both at the raw material level and at the component level and at the fuselage level.
Level 0 contains information concerning the raw materials (rivet, fastener, composite raw material, honeycomb, gasket, sealant, paint), level 1 collects information regarding the components (stringer, skin, frame, doublers, floor-beam, pressure bulkhea) and level 2 deals with the fuselage as entire object.
The upper levels are connected to the lower levels by manufacturing routes that are expressed in terms of hours and hour cost (that is man-hours and machine-hours), and in terms of manufacturing technology.
Each of the three levels collects information and details to estimate the cost. Some of these parameters can be set as cost drivers in order to carry out both the analogous method and the parameter method.
Levels 0 and 1 can collect historical data that will be used by the analogous method.
The entire fuselage is thus defined by filling the three levels and the estimated cost can be computed by one of the methods (Analogous, Parametric or BottomUp).
At level 1 the software will allow the maintenance and repair parameters to be interfaced to the Structural Health Monitoring (SHM) system in order to estimate the SHM technology cost and its cost benefit on manufacturing, maintenance and repair. A Bayesian based Dynamic Data Driven Application System (BDDDSA), developed by the Topic Manager, will be also integrated to the software.
The cost estimation module will be endowed with GUI interface. It will be linked to CAD model to obtain geometrical parameters at each level. The module will also be interfaced to a multidisciplinary optimization tool.