초록 ▼

Embodiments are directed to obtaining data from a plurality of sensors located on a rotorcraft, wherein a first plurality of the sensors is associated with a hub of the rotorcraft and a second plurality of the sensors is associated with blades of the rotorcraft, processing the data to isolate blade

Embodiments are directed to obtaining data from a plurality of sensors located on a rotorcraft, wherein a first plurality of the sensors is associated with a hub of the rotorcraft and a second plurality of the sensors is associated with blades of the rotorcraft, processing the data to isolate blade dynamics using the data from the sensors associated with the blade from rotorcraft maneuvering dynamics using the data from the sensors associated with the hub, obtaining at least one parameter associated with the blade dynamics based on the processing, and analyzing the at least one parameter to control at least one of the rotorcraft and the blades.

대표청구항 ▼

1. A method applied to a rotorcraft comprising a rotor including blades, the method comprising: obtaining data from a first plurality of hub sensors disposed on a hub of the rotorcraft;obtaining data from a second plurality of blade sensors disposed on each of the blades;processing the data to isola

1. A method applied to a rotorcraft comprising a rotor including blades, the method comprising: obtaining data from a first plurality of hub sensors disposed on a hub of the rotorcraft;obtaining data from a second plurality of blade sensors disposed on each of the blades;processing the data to isolate blade dynamics from rotorcraft maneuvering dynamics using relative blade-hub acceleration based on the data obtained from the hub and blade sensors;obtaining at least one parameter associated with the blade dynamics based on the processing; andanalyzing the at least one parameter to control at least one of the rotorcraft and the blades. 2. The method of claim 1, wherein the hub and blade sensors comprise accelerometers. 3. The method of claim 1, further comprising: measuring acceleration from the blade sensors at a root of each of the blades to minimize high order effects. 4. The method of claim 1, further comprising: filtering the processed data prior to obtaining the at least one parameter. 5. The method of claim 1, further comprising: controlling, in accordance with the at least one parameter, at least one of: a swashplate, an actuator, an individual blade, or combinations thereof. 6. The method of claim 1, wherein the processing of the data comprises transforming the data from a rotating frame to a fixed frame. 7. The method of claim 1, further comprising: scheduling a maintenance activity when at least one of the data and the at least one parameter indicate that operation of at least one of the blades is within a threshold of a mechanical stop or a limit. 8. An apparatus for use in a rotorcraft having at least one rotor with blades, the apparatus comprising: at least one processor; andmemory having instructions stored thereon that, when executed by the at least one processor, cause the apparatus to:obtain data from a first plurality of hub sensors disposed on a hub of the rotorcraft;obtain data from a second plurality of blade sensors disposed on each of the blades;process the data to isolate blade dynamics from rotorcraft maneuvering dynamics using relative blade-hub acceleration based on the data obtained from the hub and blade sensors;obtain at least one parameter associated with the blade dynamics based on the processing; andanalyze the at least one parameter to control at least one of the rotorcraft and the blades. 9. The apparatus of claim 8, wherein the hub and blade sensors comprise gravimetric accelerometers. 10. The apparatus of claim 8, wherein the instructions, when executed by the at least one processor, cause the apparatus to: measure acceleration at a root of the blades to minimize high order effects. 11. The apparatus of claim 8, wherein the instructions, when executed by the at least one processor, cause the apparatus to: filter the processed data prior to obtaining the at least one parameter. 12. The apparatus of claim 8, wherein the at least one parameter is analyzed to control at least one of: a swashplate, an actuator, and an individual blade. 13. The apparatus of claim 8, wherein the instructions, when executed by the at least one processor, cause the apparatus to: transform the data from a rotating frame to a fixed frame. 14. The apparatus of claim 13, wherein the instructions, when executed by the at least one processor, cause the apparatus to: obtaining a coning angle, a longitudinal tilt of a tip path plane (TPP), and a latitudinal tilt of the TPP based on the transformation of the data. 15. The apparatus of claim 8, wherein the instructions, when executed by the at least one processor, cause the apparatus to: schedule a maintenance activity when at least one of the data and the at least one parameter indicate that operation of at least one of the blades is within a threshold of a mechanical stop or a theoretical limit. 16. An aircraft comprising: an airframe;a hub extending from the airframe and including hub arms, the hub being rotatable about an axis;blades respectively extending from each of the hub arms, the blade being configured to generate lift according to the rotation of the hub;hub arm sensors respectively disposed at each of the hub arms to measure motion associated with the hub;blade sensors respectively disposed as multiple blade sensors at roots of each of the blades to measure motion associated with each of the blades; anda control computer configured to:obtain data from the hub sensors and the blade sensors;process the data to isolate blade dynamics from aircraft maneuvering dynamics using relative blade-hub acceleration based on the data obtained from the hub arm sensors and the multiple blade sensors for each of the blades;obtain at least one parameter associated with the blade dynamics for each of the blades based on the processing; andcontrol each of the blades using the obtained one parameter. 17. The aircraft of claim 16, wherein the control computer utilizes control laws to provide at least one requirement selected from: minimizing hub moments, maximizing aircraft maneuverability, maximizing gust rejection, and maintaining or maximizing stability margins, and wherein the blades are controlled in accordance with the control laws and the obtained one parameter. 18. The aircraft of claim 16, wherein the at least one parameter pertains to at least one of angles, velocities, accelerations, and positions associated with the blades.