Rjmvmi1998
Member
Im running through the systems of a new to me RV10. This plane was completed in 2009 so the avionics and bus structure are a little dated. I have identified what I believe to be a Bridge Rectifier in the Bus structure as seen in the picture link I posted below.
My understanding of a bridge rectifier is to transform AC to DC power. How it’s used in the application is confusing me.
My best guess, and hopefully someone can validate this, is as follows.
The airplane has two batteries, 1 primary, and 1 standby. During normal operation with the Alternator running and voltage above 13V, both batteries are connected to the system for charging. If the voltage drops below 13V, a low voltage warning system automatically sheds the standby battery leaving only the primary battery providing electricity. The inflight procedure at this point, assuming I cannot regain the alternator, is to engage the endurance bus switch and turn off the primary battery. In preparation for landing, I would then turn on the primary and standby battery to land the airplane.
So, back to the rectifier. When I am operating with only the endurance bus energized, is the rectifiers job to choose which battery (primary or standby) to power the endurance bus? It does this by only letting the supply with the highest voltage pass through to the bus? And as that battery’s voltage starts to drop, it would switch to the other battery, back and forth Etc?
I’m obviously not an Electrical Enigener so pardon my description and I’m sure my nomenclature is way off, but hopefully you get the gist of what I am describing.
Thanks
https://share.icloud.com/photos/03cfO-bnJX3r_IC8K6zEccS1g
My understanding of a bridge rectifier is to transform AC to DC power. How it’s used in the application is confusing me.
My best guess, and hopefully someone can validate this, is as follows.
The airplane has two batteries, 1 primary, and 1 standby. During normal operation with the Alternator running and voltage above 13V, both batteries are connected to the system for charging. If the voltage drops below 13V, a low voltage warning system automatically sheds the standby battery leaving only the primary battery providing electricity. The inflight procedure at this point, assuming I cannot regain the alternator, is to engage the endurance bus switch and turn off the primary battery. In preparation for landing, I would then turn on the primary and standby battery to land the airplane.
So, back to the rectifier. When I am operating with only the endurance bus energized, is the rectifiers job to choose which battery (primary or standby) to power the endurance bus? It does this by only letting the supply with the highest voltage pass through to the bus? And as that battery’s voltage starts to drop, it would switch to the other battery, back and forth Etc?
I’m obviously not an Electrical Enigener so pardon my description and I’m sure my nomenclature is way off, but hopefully you get the gist of what I am describing.
Thanks
https://share.icloud.com/photos/03cfO-bnJX3r_IC8K6zEccS1g