TY - JOUR
T1 - Aerodynamic performance of control surfaces on mars airplane balloon experiment two
AU - Kanazaki, Masahiro
AU - Tomisawa, Kai
AU - Fujita, Koji
AU - Oyama, Akira
AU - Nagai, Hiroki
N1 - Funding Information:
Part of this work was conducted under the Collaborative Research Project of the Institute of Fluid Science, Tohoku University.
Publisher Copyright:
© 2019 The Japan Society of Mechanical Engineers.
PY - 2019
Y1 - 2019
N2 - We redesigned the Mars Airplane Balloon Experiment Two (MABE-2) based on MABE-1 to improve the vehicle's stability and controllability. Following the redesign, the MABE-2 vehicle had a larger horizontal tail volume than that of MABE-1 for improved stability performance. In addition, to further improve the stability and control characteristics, a rectangular planform was employed for the horizontal tail wing; in contrast, MABE-1 had a tapered planform. The vertical tail position of MABE-2 was moved to the end of the horizontal tail wing, because the vertical tail of MABE-1, which was positioned at the mid span of the horizontal tail wing, showed aerodynamic interaction with the horizontal tail wing. In this paper, we discussed the aerodynamic performance of a control surface based on computational fluid dynamics with variation in the deflection angle between the control surface and the horizontal tail (elevator), and we examined the effects of this redesign on longitudinal control characteristics. Numerical investigations confirmed the linear variation in the pitching moment and the aerodynamic force with the changing elevator deflection angle in MABE-2. Surface pressure observations indicated that MABE-2 shows a smooth variation in the pressure distribution with changing elevator deflection angle, while MABE-1 does not. These results demonstrate that the aerodynamic control characteristics of MABE-2 were improved in comparison to those of MABE-1.
AB - We redesigned the Mars Airplane Balloon Experiment Two (MABE-2) based on MABE-1 to improve the vehicle's stability and controllability. Following the redesign, the MABE-2 vehicle had a larger horizontal tail volume than that of MABE-1 for improved stability performance. In addition, to further improve the stability and control characteristics, a rectangular planform was employed for the horizontal tail wing; in contrast, MABE-1 had a tapered planform. The vertical tail position of MABE-2 was moved to the end of the horizontal tail wing, because the vertical tail of MABE-1, which was positioned at the mid span of the horizontal tail wing, showed aerodynamic interaction with the horizontal tail wing. In this paper, we discussed the aerodynamic performance of a control surface based on computational fluid dynamics with variation in the deflection angle between the control surface and the horizontal tail (elevator), and we examined the effects of this redesign on longitudinal control characteristics. Numerical investigations confirmed the linear variation in the pitching moment and the aerodynamic force with the changing elevator deflection angle in MABE-2. Surface pressure observations indicated that MABE-2 shows a smooth variation in the pressure distribution with changing elevator deflection angle, while MABE-1 does not. These results demonstrate that the aerodynamic control characteristics of MABE-2 were improved in comparison to those of MABE-1.
KW - Aerodynamic control
KW - Computational fluid dynamics
KW - Horizontal tail wing
KW - Longitudinal motion
KW - Mars airplane balloon experiment
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U2 - 10.1299/jfst.2019jfst0017
DO - 10.1299/jfst.2019jfst0017
M3 - Article
AN - SCOPUS:85078819452
VL - 14
JO - Journal of Fluid Science and Technology
JF - Journal of Fluid Science and Technology
SN - 1880-5558
IS - 3
ER -