Hello all!
I am currently conducting my thesis research. My aim is to determine the most efficient way to combine high power density batteries with high energy density batteries in an hybrid system for powering electric aircraft. The idea is by using two different types of batteries which are optimise for takeoff and cruise phase, it is possible to decrease the overall weight of the system by 1025% without affecting power capability. (I have attached the hypothesis for more detail
For proof of concept, I am designing such power management and distribution system for a VTOL drone. The requirements are:
6s (22.2V)
8000mAh
180 A for take off
20 A for cruise
<1.2kg
The Two solutions are:
Choose one or the other
If current required is <20, then use battery A (High energy density)
If current required is >20, then use battery B (high power density)
or Add one to the other
If current required is <20, only use battery A
If current required is >20, use 20A from battery A and the rest from battery B
The problems:
What would be the best solution, considering weight as a crucial limiting factor?
What would be the best way to design such power circuit?
Can it be scaled? The idea is to use this solution on system that operates at 100V + and 1000A+
I am asking the help of the community and posting a new thread since I couldn't find anything to support my problem from previous thread. My problem requires a lot more power than usual, and a close attention to the weight of all components. Any support is greatly appreciated, and any support is a step toward a better greener electric world
Friendly,
Gabriel
I am currently conducting my thesis research. My aim is to determine the most efficient way to combine high power density batteries with high energy density batteries in an hybrid system for powering electric aircraft. The idea is by using two different types of batteries which are optimise for takeoff and cruise phase, it is possible to decrease the overall weight of the system by 1025% without affecting power capability. (I have attached the hypothesis for more detail
For proof of concept, I am designing such power management and distribution system for a VTOL drone. The requirements are:
6s (22.2V)
8000mAh
180 A for take off
20 A for cruise
<1.2kg
The Two solutions are:
Choose one or the other
If current required is <20, then use battery A (High energy density)
If current required is >20, then use battery B (high power density)
or Add one to the other
If current required is <20, only use battery A
If current required is >20, use 20A from battery A and the rest from battery B
The problems:
What would be the best solution, considering weight as a crucial limiting factor?
What would be the best way to design such power circuit?
Can it be scaled? The idea is to use this solution on system that operates at 100V + and 1000A+
I am asking the help of the community and posting a new thread since I couldn't find anything to support my problem from previous thread. My problem requires a lot more power than usual, and a close attention to the weight of all components. Any support is greatly appreciated, and any support is a step toward a better greener electric world
Friendly,
Gabriel
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