Tuned mass damper for aircraft
Embodiments herein describe mitigating flexible modes in an airframe of an aircraft by operating a battery for the aircraft as a tuned mass damper. One embodiment comprises an Unmanned Aerial Vehicle (UAV). The UAV includes a flexible airframe, a plurality of propulsors coupled to the flexible airframe that generate thrust for the UAV, a battery that provides electrical power for the plurality of propulsors, and a suspension system that suspends the battery from the flexible airframe and operates the mass of the battery as a tuned mass damper to dampen flexible modes generated in the flexible airframe during flight.
1. An Unmanned Aerial Vehicle (UAV), comprising:
an airframe comprising a central body and arms that extend from the central body;
propulsors coupled to the arms to generate thrust for the UAV, wherein at least one of variable thrust and variable torque from the propulsors cause deflection of one or more of the arms to generate vibration modes in the airframe;
a battery configured to provide electrical power to the propulsors; and
a suspension system that suspends the battery from the central body, and comprising a flexure tuned to operate a mass of the battery as a tuned mass damper to dampen the vibration modes generated in the airframe during flight.
2. The UAV of claim 1 , wherein:
the battery is suspended from the airframe proximate to a center of gravity of the UAV.
3. The UAV of claim 1 , wherein:
the flexure is compliant in one or more degrees of freedom to dampen the vibration modes generated in the airframe.
4. The UAV of claim 1 , wherein:
the flexure is compliant in an axis of pitch of the UAV to dampen the vibration modes generated in the airframe.
5. The UAV of claim 1 , wherein:
the suspension system comprises at least one composite structure.
6. The UAV of claim 5 , wherein:
the at least one composite structure comprises one or more composite beams.
7. The UAV of claim 6 , wherein:
the one or more composite beams include a constrained layer damping treatment applied to one or more surfaces.
8. The UAV of claim 1 , wherein each of the propulsors comprises:
an electric motor; and
a rotor mechanically coupled to the electric motor that is configured to generate thrust.
9. The UAV of claim 8 , wherein:
at least one of the vibration modes generated in the airframe is perpendicular to a plane of the rotor.
10. The UAV of claim 8 , wherein:
at least one of the vibration modes generated in the airframe is in a plane of the rotor.
11. An aircraft, comprising:
an airframe comprising a central body and arms that extend from the central body;
propulsors coupled to the arms to generate thrust for the aircraft, wherein at least one of variable thrust and variable torque from the propulsors cause deflection of one or more of the arms to generate vibration modes in the airframe;
a battery configured to provide electrical power to the propulsors; and
a suspension system that suspends the battery from the central body, and comprising a flexure compliant in one or more degrees of freedom and tuned to operate a mass of the battery as a tuned mass damper to dampen the vibration modes generated in the airframe during flight.
12. The aircraft of claim 11 , wherein:
the flexure is compliant in six degrees of freedom to dampen the vibration modes generated in the airframe.
13. The aircraft of claim 11 , wherein:
the flexure is compliant in an axis of pitch of the aircraft to dampen the vibration modes generated in the airframe.
14. The aircraft of claim 11 , wherein:
the suspension system comprises at least one composite structure.
15. The aircraft of claim 14 , wherein:
the at least one composite structure comprises one or more composite beams.
16. The aircraft of claim 15 , wherein:
the one or more composite beams include a constrained layer damping treatment applied to one or more surfaces.
17. The aircraft of claim 11 , wherein:
each of the propulsors comprises:
an electric motor; and
a rotor mechanically coupled to the electric motor that is configured to generate thrust.
18. The aircraft of claim 17 , wherein:
at least one of the flexible modes generated in the airframe is perpendicular to a plane of the rotor.
19. The aircraft of claim 17 , wherein:
at least one of the vibration modes generated in the airframe is in a plane of the rotor.
20. A method of operating an aircraft that includes an airframe comprising a central body and arms that extend from the central body, propulsors coupled to the arms, a battery configured to provide electrical power to the propulsors, and a suspension system that suspends the battery from the central body and comprises a flexure, the method comprising:
tuning the flexure of the suspension system to operate a mass of the battery as a tuned mass damper to dampen vibration modes in the airframe generated during flight operations;
generating, during the flight operations, the vibration modes in the airframe due to at least one of variable thrust and variable torque from the propulsors that cause deflection of one or more of the arms;
and
dampening, by the flexure and the mass of the battery, the vibration modes generated in the airframe during the flight operations.