Fluid tank for integration into a structure of an unmanned aircraft

A fluid tank for integration into a structure of an unmanned aircraft, comprising:

• a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior,
• at least one receiving chamber in the enclosed interior for storing fluid,
• a collection chamber arranged on the lower side and fluidically connected to the at least one receiving chamber;
• and
• at least one baffle running transversely to an axial direction of the fluid tank, wherein the at least one baffle comprises at least one upper inflow opening,
• wherein the collection chamber has a bottom surface, through which there extends a drain,
• wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber,
• wherein the collection chamber is arranged centrally in a longitudinally axial direction between the first axial wall and the second axial wall,
• wherein the at least one receiving chamber comprises a first receiving chamber adjoining the first axial wall axially, and a second receiving chamber adjoining the second axial wall axially.