Abstract
Flight tests were carried out to identify the system parameters for Variable Stability and Response Airplane(VSRA) equipped with a Direct Lift Control(DLC) flap system by a forced vibration method. Sinusoidal input with various freququency was applied to the DLC flap around the trim of the horizontal steady flight, and the stability and control derivatives of the VSRA system were identified from the data of response frequency characteristics of the airframe. Then, response from a linear system model consisting of the identified stability and control derivatives was compared with other flight test response by general input in order to verify the accuracy of the identification. Moreover, lift, drag, and pitching moment of the DLC flap were estimated from the identified control derivatives and compared with the wind tunnel test results. The lift control capability of the DLC flap at flying speed of 53.6m/s was {plus_minus}0.2026g of vertical acceleration factor for the maximum steady input of {plus_minus}25{degree}. Although it decreased at the frequency of 1 Hz, the objective band width could be obtained. 9 refs., 14 figs., 1 tab.
Citation Formats
Tsukano, Y, Ono, T, and Ishikawa, K.
Identification of the stability and control derivatives of a DLC-flap system for VSRA; VSRA/DLC flap kei no antei{center_dot}soju bikeisu no dotei.
Japan: N. p.,
1991.
Web.
Tsukano, Y, Ono, T, & Ishikawa, K.
Identification of the stability and control derivatives of a DLC-flap system for VSRA; VSRA/DLC flap kei no antei{center_dot}soju bikeisu no dotei.
Japan.
Tsukano, Y, Ono, T, and Ishikawa, K.
1991.
"Identification of the stability and control derivatives of a DLC-flap system for VSRA; VSRA/DLC flap kei no antei{center_dot}soju bikeisu no dotei."
Japan.
@misc{etde_10150424,
title = {Identification of the stability and control derivatives of a DLC-flap system for VSRA; VSRA/DLC flap kei no antei{center_dot}soju bikeisu no dotei}
author = {Tsukano, Y, Ono, T, and Ishikawa, K}
abstractNote = {Flight tests were carried out to identify the system parameters for Variable Stability and Response Airplane(VSRA) equipped with a Direct Lift Control(DLC) flap system by a forced vibration method. Sinusoidal input with various freququency was applied to the DLC flap around the trim of the horizontal steady flight, and the stability and control derivatives of the VSRA system were identified from the data of response frequency characteristics of the airframe. Then, response from a linear system model consisting of the identified stability and control derivatives was compared with other flight test response by general input in order to verify the accuracy of the identification. Moreover, lift, drag, and pitching moment of the DLC flap were estimated from the identified control derivatives and compared with the wind tunnel test results. The lift control capability of the DLC flap at flying speed of 53.6m/s was {plus_minus}0.2026g of vertical acceleration factor for the maximum steady input of {plus_minus}25{degree}. Although it decreased at the frequency of 1 Hz, the objective band width could be obtained. 9 refs., 14 figs., 1 tab.}
place = {Japan}
year = {1991}
month = {Jul}
}
title = {Identification of the stability and control derivatives of a DLC-flap system for VSRA; VSRA/DLC flap kei no antei{center_dot}soju bikeisu no dotei}
author = {Tsukano, Y, Ono, T, and Ishikawa, K}
abstractNote = {Flight tests were carried out to identify the system parameters for Variable Stability and Response Airplane(VSRA) equipped with a Direct Lift Control(DLC) flap system by a forced vibration method. Sinusoidal input with various freququency was applied to the DLC flap around the trim of the horizontal steady flight, and the stability and control derivatives of the VSRA system were identified from the data of response frequency characteristics of the airframe. Then, response from a linear system model consisting of the identified stability and control derivatives was compared with other flight test response by general input in order to verify the accuracy of the identification. Moreover, lift, drag, and pitching moment of the DLC flap were estimated from the identified control derivatives and compared with the wind tunnel test results. The lift control capability of the DLC flap at flying speed of 53.6m/s was {plus_minus}0.2026g of vertical acceleration factor for the maximum steady input of {plus_minus}25{degree}. Although it decreased at the frequency of 1 Hz, the objective band width could be obtained. 9 refs., 14 figs., 1 tab.}
place = {Japan}
year = {1991}
month = {Jul}
}