Systems and methods for maintaining attitude control under degraded energy source conditions using multiple propulsors

1. A system for maintaining attitude control under degraded or depleted energy source conditions using multiple electric propulsors, the system comprising:

a plurality of propulsors;

at least an energy source providing electric power to the plurality of propulsors; and

a vehicle controller communicatively coupled to each propulsor of the plurality of propulsors, the vehicle controller designed and configured to:

calculate initial power levels for the plurality of propulsors, the initial power levels including an initial power level for each propulsor of the plurality of propulsors;

detect a present power output capability of the at least an energy source;

calculate at least a power demand of the plurality of propulsors as a function of the initial power levels;

determine that the present power output capability is insufficient to match the at least a power demand; and

for each initial power level of the plurality of initial power levels:

generate a reduced power level, the reduced power level less than the initial power level, wherein generating the reduced power level includes:

calculating a proportional reduction factor; wherein calculating the proportional reduction factor further comprises: identifying a propulsor, of the plurality of propulsors, requiring a maximal power consumption; and calculating the proportional reduction factor as a function of the maximal power consumption; and

multiplying the initial power level by the reduction factor; and

direct a corresponding propulsor of the plurality of propulsors to consume electrical power at the reduced power level.

2. The system of claim 1 , wherein calculation of initial power levels further comprises calculation of initial power levels based on an attitude control goal.

3. The system of claim 1 , wherein detecting the present power output capability of the at least an energy source further comprises detecting, by the vehicle controller, an electric potential of the least an energy source under load.

4. The system of claim 1 , wherein identifying the propulsor further comprises: determining back electromotive force for each propulsor of the plurality of propulsors; and identifying the maximal back electromotive force.

5. The system of claim 4 , wherein determining back electromotive force further comprises estimating back electromotive force as a function of the initial power level.

6. The system of claim 4 , wherein determining back electromotive force further comprises estimating back electromotive force as a function of a computer model of the propulsor.

7. The system of claim 1 , wherein calculating the proportional reduction factor further comprises calculating the proportional reduction factor as a function of the energy source potential under load.

8. The system of claim 1 , wherein calculating the proportional reduction factor further comprises calculating the proportional reduction factor as a function of the at least a power demand.

9. A method of maintaining attitude control of an electronic multi-propulsion system under degraded energy source conditions, the method comprising:

calculating, by a vehicle controller communicatively connected to a plurality of propulsors powered by at least an energy source, initial power levels for the plurality of propulsors, the initial power levels including an initial power level for each propulsor of the plurality of propulsors;

detecting, by the vehicle controller, a present power output capability of the at least an energy source;

calculating, by the vehicle controller, at least a power demand of the plurality of propulsors as a function of the initial power levels;

determining, by the vehicle controller, that the present power output capability is insufficient to match the aggregate demand; and

for each initial power level of the plurality of initial power levels:

generating, by the vehicle controller, a reduced power level, the reduced power level less than the initial power level, wherein generating the reduced power level includes:

calculating a proportional reduction factor; wherein calculating the proportional reduction factor further comprises: identifying a propulsor, of the plurality of propulsors, requiring a maximal power consumption; and calculating the proportional reduction factor as a function of the maximal power consumption; and

multiplying the initial power level by the reduction factor; and

directing, by the vehicle controller, a corresponding propulsor of the plurality of propulsors to consume electrical power at the reduced power level.

10. The method of claim 9 , wherein calculation of initial power levels further comprises calculation of initial power levels based on an attitude control goal.

11. The method of claim 9 , wherein determining the present power output capability of the at least an energy source further comprises determining, by the vehicle controller, an electric potential of the least an energy source under load.

12. The method of claim 9 , wherein identifying the propulsor further comprises:

determining back electromotive force for each propulsor of the plurality of propulsors; and

identifying the maximal back electromotive force.

13. The method of claim 12 , wherein determining back electromotive force further comprises estimating back electromotive force as a function of the initial power level.

14. The method of claim 12 , wherein determining back electromotive force further comprises estimating back electromotive force as a function of a computer model of the propulsor.

15. The method of claim 9 , wherein calculating the proportional reduction factor further comprises calculating the proportional reduction factor as a function of the energy source potential under load.

16. The method of claim 9 , wherein calculating the proportional reduction factor further comprises calculating the proportional reduction factor as a function of the aggregate demand.