massBreakdown Element

Mass breakdown

Namespace: Empty

Schema: Empty

All All
      Element designMasses

Design masses

      Element fuel

Fuel mass

      Element mOEM

Operating empty mass

      Element payload

Payload mass

Attribute externalDataDirectorySimple Type string
Attribute externalDataNodePathSimple Type string
Attribute externalFileNameSimple Type string

1. General

The massBreakeDown is subdivided in designMasses , fuel , payload and mOME (operating empty mass).


The design masses contain the overall values for mTOM and so forth. These should be listed as specified by the TLAR or found from initial sizing.

fuel and payload

The fuel and payload nodes should contain maximum values, i.e. full fuel tanks, all passengers on board and full cargo holding. These values may exceed the maximum allowable take-off mass as the actual loading of the aircraft should be specified in the weight and balance section of the aircraft.


The operation empty mass structure is based on the Airbus Mass Standard brake down [AIRBUS MASS STANDARD 2008]. The operator’s mass empty (OME) is defined by the sum of the following component masses:

  • operator’s items
  • manufacturer’s mass empty (MME)

2. massDescription

Each sub component has the following massDescription which include a:

  • Name
  • Description
  • parentUID
  • Mass value
  • Mass location
  • Mass orientation
  • Mass Inertia.

The massdescription can be found at the designMasses direct under each item. At the fuel , payload and mOME under massDescription in each item and sub item.

Concerning symmetry please note that any item referenced by its UID, e.g. wingUID, accounts for the complete component, e.g. right and left side. Hence for these items their complete mass needs to be specified. If the mass of geometricallly symmetrical components is different, please use the symmetry modifyers for UIDs: _symm and _mirror. See also the overall CPACS definition section on symmetry

See Also