Abstract
This study investigates control allocation for a compound rotorcraft to optimize performance in acceleration, pull-up, and turning maneuvers. Simulations of a hypothetical compound rotorcraft based on a UH-60A airframe and main rotor with a wing and pusher propeller are used. The study presents general background on the simulated compound rotorcraft's performance in trim and the trim methodology employed. In addition to the four traditional controls, this study explores two additional control effectors: propeller pitch and symmetric wing flap deflection, which can be optimized for performance in trim or maneuvering flight. Trim analysis of quasi-steady maneuvers is used to gain an understanding of the control allocation that minimizes power required. The results of the optimization are incorporated into a g-command model inversion controller to regulate longitudinal and vertical load factor. A combined longitudinal and vertical load factor command controller is used to ensure optimal control allocation with regards to the propulsive force distribution between the main rotor and propeller, and the lift force distribution between the main rotor and wing.
| Original language | English (US) |
|---|---|
| Title of host publication | American Helicopter Society International - 5th Decennial AHS Aeromechanics Specialists' Conference 2014 |
| Subtitle of host publication | Current Challenges and Future Directions in Rotorcraft Aeromechanics |
| Publisher | American Helicopter Society International |
| Pages | 434-449 |
| Number of pages | 16 |
| ISBN (Electronic) | 9781634391788 |
| State | Published - Jan 1 2014 |
| Event | 5th Decennial AHS Aeromechanics Specialists' Conference 2014: Current Challenges and Future Directions in Rotorcraft Aeromechanics - San Francisco, United States Duration: Jan 22 2014 → Jan 24 2014 |
Publication series
| Name | American Helicopter Society International - 5th Decennial AHS Aeromechanics Specialists' Conference 2014: Current Challenges and Future Directions in Rotorcraft Aeromechanics |
|---|
Other
| Other | 5th Decennial AHS Aeromechanics Specialists' Conference 2014: Current Challenges and Future Directions in Rotorcraft Aeromechanics |
|---|---|
| Country | United States |
| City | San Francisco |
| Period | 1/22/14 → 1/24/14 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
Cite this
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Optimizing control of a compound rotorcraft in quasi-steady maneuvers. / Thorsen, Adam T.; Horn, Joseph Francis; Ozdemir, Gurbuz T.
American Helicopter Society International - 5th Decennial AHS Aeromechanics Specialists' Conference 2014: Current Challenges and Future Directions in Rotorcraft Aeromechanics. American Helicopter Society International, 2014. p. 434-449 (American Helicopter Society International - 5th Decennial AHS Aeromechanics Specialists' Conference 2014: Current Challenges and Future Directions in Rotorcraft Aeromechanics).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
TY - GEN
T1 - Optimizing control of a compound rotorcraft in quasi-steady maneuvers
AU - Thorsen, Adam T.
AU - Horn, Joseph Francis
AU - Ozdemir, Gurbuz T.
PY - 2014/1/1
Y1 - 2014/1/1
N2 - This study investigates control allocation for a compound rotorcraft to optimize performance in acceleration, pull-up, and turning maneuvers. Simulations of a hypothetical compound rotorcraft based on a UH-60A airframe and main rotor with a wing and pusher propeller are used. The study presents general background on the simulated compound rotorcraft's performance in trim and the trim methodology employed. In addition to the four traditional controls, this study explores two additional control effectors: propeller pitch and symmetric wing flap deflection, which can be optimized for performance in trim or maneuvering flight. Trim analysis of quasi-steady maneuvers is used to gain an understanding of the control allocation that minimizes power required. The results of the optimization are incorporated into a g-command model inversion controller to regulate longitudinal and vertical load factor. A combined longitudinal and vertical load factor command controller is used to ensure optimal control allocation with regards to the propulsive force distribution between the main rotor and propeller, and the lift force distribution between the main rotor and wing.
AB - This study investigates control allocation for a compound rotorcraft to optimize performance in acceleration, pull-up, and turning maneuvers. Simulations of a hypothetical compound rotorcraft based on a UH-60A airframe and main rotor with a wing and pusher propeller are used. The study presents general background on the simulated compound rotorcraft's performance in trim and the trim methodology employed. In addition to the four traditional controls, this study explores two additional control effectors: propeller pitch and symmetric wing flap deflection, which can be optimized for performance in trim or maneuvering flight. Trim analysis of quasi-steady maneuvers is used to gain an understanding of the control allocation that minimizes power required. The results of the optimization are incorporated into a g-command model inversion controller to regulate longitudinal and vertical load factor. A combined longitudinal and vertical load factor command controller is used to ensure optimal control allocation with regards to the propulsive force distribution between the main rotor and propeller, and the lift force distribution between the main rotor and wing.
UR - http://www.scopus.com/inward/record.url?scp=84911367865&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84911367865&partnerID=8YFLogxK
M3 - Conference contribution
T3 - American Helicopter Society International - 5th Decennial AHS Aeromechanics Specialists' Conference 2014: Current Challenges and Future Directions in Rotorcraft Aeromechanics
SP - 434
EP - 449
BT - American Helicopter Society International - 5th Decennial AHS Aeromechanics Specialists' Conference 2014
PB - American Helicopter Society International
ER -