Vibratory loads reduction testing of the NASA/Army/MIT active twist rotor
Vibratory loads reduction testing of the NASA/Army/MIT active twist rotor
- Neue Suche nach: Wilbur, M.L.
- Neue Suche nach: Mirick, P.H.
- Neue Suche nach: Yaeger, W.T. jun.
- Neue Suche nach: Langston, C.W.
- Neue Suche nach: Cesnik, C.E.S.
- Neue Suche nach: Shin, S.
- Neue Suche nach: Wilbur, M.L.
- Neue Suche nach: Mirick, P.H.
- Neue Suche nach: Yaeger, W.T. jun.
- Neue Suche nach: Langston, C.W.
- Neue Suche nach: Cesnik, C.E.S.
- Neue Suche nach: Shin, S.
Recent studies have indicated that controlled strain-induced blade twisting can be attained using piezoelectric Active Fiber Composite technology, and that such advancement may provide a mechanism for reduced rotorcraft vibrations and increased rotor performance. Top validate these findings experimentally, a cooperative effort between the NASA Langley Research Center, the Army Research Laboratory, and the MIT Active Materials and Structures Laboratory has been developed. As a result of this collaboration a four-bladed, aeroelastically scaled, active-twist model rotor has been designed and fabricated for testing in the heavy gas test medium of the NASA Langley Transonic Dynamics Tunnel. Initial wind tunnel testing has been conducted to assess the impact of active blade twist on both fixed- and rotating-system vibratory loads in forward flight. The active twist control was found to have a pronounced effect on all system loads and was shown to offer generally reductions in fixed-system loads of 60% to 95%, depending upon flight condition, with 1.1 deg to 1.4 deg of dynamic blade twist observed. A summary of the systems developed and the vibratory loads reduction results obtained are presented in this paper.
Dokumentinformationen
Vibratory loads reduction testing of the NASA/Army/MIT active twist rotor
Experimentelle Erprobung der Reduzierung der Schwingbeanspruchung von Rotorblättern durch Regelung des Verdrehwinkels über piezoelektrische Verstärkungsfasern
Journal of the American Helicopter Society ; 47 , 2 ; 123-133
2002
11 Seiten, 13 Bilder, 3 Tabellen, 22 Quellen
Aufsatz (Zeitschrift)
Englisch
Biegebeanspruchung , Drehmomentmessung , Entlastung , Faser , Faserverbundwerkstoff , Flügelblatt , Modellversuch , Piezoelektrikum , piezoelektrischer Aktor , Rotor (Drehflügel) , Schwingbeanspruchung , Schwingungsbegrenzung , Torsionsbeanspruchung , Transschallwindkanal , Verdrehwinkel , Winkelregelung
Ähnliche Titel
Vibratory Loads Reduction Testing of te NASA-Army-MIT Active Twist Rotor
| Online Contents | 2002