Non-harmonic deployment of active devices for rotor performance enhancement

Research output: Contribution to journalConference article

7 Citations (Scopus)

Abstract

A computational method is introduced which generates a non-harmonic deployment schedule for an active device that is optimized to reduce the total power required of a rotor over a designated flight envelope. A trailing edge flap is added to the UH-60A's rotor and the flap's span, deflection magnitudes, and deployment azimuth positions are all optimized to minimize the total power of the rotor over a flight envelop of μ=0.05 to μ=0.37. The formal optimization effort is carried out through the coupling of a comprehensive analysis code, RCAS, and an evolutionary algorithm based optimizer CMA-ES. A peak power savings of 15.23%, at μ=.30, is found from a twist optimization study which provides an achievable power savings limit for the active device study. With a trailing edge flap, an optimized deployment schedule is found at each advance ratio over an entire flight envelope which minimizes total power of the rotor, including a peak power savings of 9.51% at μ=.30. The resulting effects of the non-harmonic trailing edge deployments on the rotors hub vibratory and pitch-link loads are also analyzed.

Original languageEnglish (US)
Pages (from-to)2215-2227
Number of pages13
JournalAnnual Forum Proceedings - AHS International
Volume3
StatePublished - Sep 9 2013
Event69th American Helicopter Society International Annual Forum 2013 -
Duration: May 21 2013May 23 2013

Fingerprint

Rotors
Flight envelopes
Flaps
Computational methods
Evolutionary algorithms

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

@article{2b5ad843aff146d5aba5a45fbd6fd8d5,
title = "Non-harmonic deployment of active devices for rotor performance enhancement",
abstract = "A computational method is introduced which generates a non-harmonic deployment schedule for an active device that is optimized to reduce the total power required of a rotor over a designated flight envelope. A trailing edge flap is added to the UH-60A's rotor and the flap's span, deflection magnitudes, and deployment azimuth positions are all optimized to minimize the total power of the rotor over a flight envelop of μ=0.05 to μ=0.37. The formal optimization effort is carried out through the coupling of a comprehensive analysis code, RCAS, and an evolutionary algorithm based optimizer CMA-ES. A peak power savings of 15.23{\%}, at μ=.30, is found from a twist optimization study which provides an achievable power savings limit for the active device study. With a trailing edge flap, an optimized deployment schedule is found at each advance ratio over an entire flight envelope which minimizes total power of the rotor, including a peak power savings of 9.51{\%} at μ=.30. The resulting effects of the non-harmonic trailing edge deployments on the rotors hub vibratory and pitch-link loads are also analyzed.",
author = "Frank Kody and Maughmer, {Mark David} and Sven Schmitz",
year = "2013",
month = "9",
day = "9",
language = "English (US)",
volume = "3",
pages = "2215--2227",
journal = "Annual Forum Proceedings - AHS International",
issn = "1552-2938",
publisher = "American Helicopter Society",

}

Non-harmonic deployment of active devices for rotor performance enhancement. / Kody, Frank; Maughmer, Mark David; Schmitz, Sven.

In: Annual Forum Proceedings - AHS International, Vol. 3, 09.09.2013, p. 2215-2227.

Research output: Contribution to journalConference article

TY - JOUR

T1 - Non-harmonic deployment of active devices for rotor performance enhancement

AU - Kody, Frank

AU - Maughmer, Mark David

AU - Schmitz, Sven

PY - 2013/9/9

Y1 - 2013/9/9

N2 - A computational method is introduced which generates a non-harmonic deployment schedule for an active device that is optimized to reduce the total power required of a rotor over a designated flight envelope. A trailing edge flap is added to the UH-60A's rotor and the flap's span, deflection magnitudes, and deployment azimuth positions are all optimized to minimize the total power of the rotor over a flight envelop of μ=0.05 to μ=0.37. The formal optimization effort is carried out through the coupling of a comprehensive analysis code, RCAS, and an evolutionary algorithm based optimizer CMA-ES. A peak power savings of 15.23%, at μ=.30, is found from a twist optimization study which provides an achievable power savings limit for the active device study. With a trailing edge flap, an optimized deployment schedule is found at each advance ratio over an entire flight envelope which minimizes total power of the rotor, including a peak power savings of 9.51% at μ=.30. The resulting effects of the non-harmonic trailing edge deployments on the rotors hub vibratory and pitch-link loads are also analyzed.

AB - A computational method is introduced which generates a non-harmonic deployment schedule for an active device that is optimized to reduce the total power required of a rotor over a designated flight envelope. A trailing edge flap is added to the UH-60A's rotor and the flap's span, deflection magnitudes, and deployment azimuth positions are all optimized to minimize the total power of the rotor over a flight envelop of μ=0.05 to μ=0.37. The formal optimization effort is carried out through the coupling of a comprehensive analysis code, RCAS, and an evolutionary algorithm based optimizer CMA-ES. A peak power savings of 15.23%, at μ=.30, is found from a twist optimization study which provides an achievable power savings limit for the active device study. With a trailing edge flap, an optimized deployment schedule is found at each advance ratio over an entire flight envelope which minimizes total power of the rotor, including a peak power savings of 9.51% at μ=.30. The resulting effects of the non-harmonic trailing edge deployments on the rotors hub vibratory and pitch-link loads are also analyzed.

UR - http://www.scopus.com/inward/record.url?scp=84883374316&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84883374316&partnerID=8YFLogxK

M3 - Conference article

AN - SCOPUS:84883374316

VL - 3

SP - 2215

EP - 2227

JO - Annual Forum Proceedings - AHS International

JF - Annual Forum Proceedings - AHS International

SN - 1552-2938

ER -