FUEL TANK WITH WATER BLADDER
FIG2 is a schematic illustration of a controller of the aircraft of FIG1
As shown in FIG2, the controller 20 may include a processing unit 201, a memory unit 202, a networking unit 203, an optional sensing element 204 to sense the volume of the fuel in the fuel tank housing 13 at any given time and a servo control element 205. The controller 20 may be provided as a flight computer for the aircraft 10 or as a stand-alone component. The processing unit 201 may be provided as a central processing unit (CPU), which is coupled with the memory unit 202 and is communicative with the sensing element 204 and the servo control element 205 by way of the networking unit 203. The memory unit 202 has the minimal volume of the bladder 14 and the volume of the portion 160 of the coolant flow system 16 that is within the fuel tank housing 13 stored thereon in one or more first storage units and has executable instructions stored thereon in one or more second storage units. When executed, the executable instructions cause the processing unit to operate as described herein.
schematic
171
heat exchanger
201
processing unit
14
bladder
202
memory unit
203
networking unit
11
engine
130
rigid fuel tank housing
204
sensing element
20
controller
10
aircraft
131
inflatable fuel tank housing
15
fuel system
205
servo control element
150
first portion
13
fuel tank housing
['5. The tank assembly according to any preceding claim, further comprising a controller (20) configured to sense the volume of the first fluid and to control the flow system accordingly, wherein the controller is further configured to control the flow system to draw at least a portion of the volume of the second fluid from the bladder and the housing based on an external requirement.', '6. The aircraft according to claim 5, wherein the controller comprises a sensing element (204).']