Abstract
An advanced control system capable of providing consistent handling qualities throughout the operational flight envelope is a desirable feature for future rotorcraft. Performance and agility requirements and ADS-33 handling quality requirements for military rotorcraft have driven the need for high bandwidth control systems. The present work evaluates an adaptive model inversion based controller to achieve these requirements. The controller was tested using a non-linear simulation model of the UH-60A helicopter. An Attitude Command Attitude Hold response type is used for roll and pitch axes and Rate Command Attitude Hold response type is used for yaw axis. A linear model at a single design point is used for the model inversion controller. An adaptive neural network (ANN) is used in the pitch and roll channels to compensate for errors when operating at off-design points. The ANN improves the tracking ability of the controller for all speeds. High bandwidth control can also lead to higher structural loads on rotorcraft. Therefore, a modification to the controller has been developed in order to avoid exceeding prescribed limits on longitudinal and lateral hub moment. The load limiting function is achieved by limiting internal variable within the pitch and roll axis command filter. Results show that the longitudinal hub moment response stays within the prescribed limits during aggressive maneuvers for a range of operating conditions. The lateral hub moment limiting system was not effective due to a second transient peak in the opposite direction of the pilot command.
| Original language | English (US) |
|---|---|
| Title of host publication | Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference |
| Pages | 34-48 |
| Number of pages | 15 |
| State | Published - Dec 1 2004 |
| Event | Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference - Providence, RI, United States Duration: Aug 16 2004 → Aug 19 2004 |
Publication series
| Name | Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference |
|---|---|
| Volume | 1 |
Other
| Other | Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference |
|---|---|
| Country | United States |
| City | Providence, RI |
| Period | 8/16/04 → 8/19/04 |
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All Science Journal Classification (ASJC) codes
- Engineering(all)
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Adaptive model inversion control of a helicopter with structural load limiting. / Sahani, Nilesh A.; Horn, Joseph F.
Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference. 2004. p. 34-48 AIAA 2004-4753 (Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference; Vol. 1).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
TY - GEN
T1 - Adaptive model inversion control of a helicopter with structural load limiting
AU - Sahani, Nilesh A.
AU - Horn, Joseph F.
PY - 2004/12/1
Y1 - 2004/12/1
N2 - An advanced control system capable of providing consistent handling qualities throughout the operational flight envelope is a desirable feature for future rotorcraft. Performance and agility requirements and ADS-33 handling quality requirements for military rotorcraft have driven the need for high bandwidth control systems. The present work evaluates an adaptive model inversion based controller to achieve these requirements. The controller was tested using a non-linear simulation model of the UH-60A helicopter. An Attitude Command Attitude Hold response type is used for roll and pitch axes and Rate Command Attitude Hold response type is used for yaw axis. A linear model at a single design point is used for the model inversion controller. An adaptive neural network (ANN) is used in the pitch and roll channels to compensate for errors when operating at off-design points. The ANN improves the tracking ability of the controller for all speeds. High bandwidth control can also lead to higher structural loads on rotorcraft. Therefore, a modification to the controller has been developed in order to avoid exceeding prescribed limits on longitudinal and lateral hub moment. The load limiting function is achieved by limiting internal variable within the pitch and roll axis command filter. Results show that the longitudinal hub moment response stays within the prescribed limits during aggressive maneuvers for a range of operating conditions. The lateral hub moment limiting system was not effective due to a second transient peak in the opposite direction of the pilot command.
AB - An advanced control system capable of providing consistent handling qualities throughout the operational flight envelope is a desirable feature for future rotorcraft. Performance and agility requirements and ADS-33 handling quality requirements for military rotorcraft have driven the need for high bandwidth control systems. The present work evaluates an adaptive model inversion based controller to achieve these requirements. The controller was tested using a non-linear simulation model of the UH-60A helicopter. An Attitude Command Attitude Hold response type is used for roll and pitch axes and Rate Command Attitude Hold response type is used for yaw axis. A linear model at a single design point is used for the model inversion controller. An adaptive neural network (ANN) is used in the pitch and roll channels to compensate for errors when operating at off-design points. The ANN improves the tracking ability of the controller for all speeds. High bandwidth control can also lead to higher structural loads on rotorcraft. Therefore, a modification to the controller has been developed in order to avoid exceeding prescribed limits on longitudinal and lateral hub moment. The load limiting function is achieved by limiting internal variable within the pitch and roll axis command filter. Results show that the longitudinal hub moment response stays within the prescribed limits during aggressive maneuvers for a range of operating conditions. The lateral hub moment limiting system was not effective due to a second transient peak in the opposite direction of the pilot command.
UR - http://www.scopus.com/inward/record.url?scp=19644398759&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=19644398759&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:19644398759
SN - 1563476703
SN - 9781563476709
T3 - Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference
SP - 34
EP - 48
BT - Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference
ER -