Showing papers on "Wing root published in 1991"
TL;DR: In this article, a wind-tunnel model of the cantilevered elastic wing is designed to simulate an energy efficient transport and the experiments include a gust load alleviation (GLA) and two active flutter suppression (AFS) tests.
Abstract: This paper summarizes the wind-tunnel experiments on the active control technology that have been conducted in the large low-speed wind tunnel of the National Aerospace Laboratory. The experiments include a gust load alleviation (GLA) and two active flutter suppression (AFS) tests. A wind-tunnel model of the cantilevered elastic wing is designed to simulate an energy efficient transport
8 citations
Patent•
10 Apr 1991
TL;DR: In this article, an imitation of bird fly folding wing aerocraft which adopts power drive is presented, which has the advantages of simple structure, convenient and practical, low cost and flight fee, no strict limitation of condition of the sky, and can do flights of advance and retreat lifting, vertical lifting, etc.
Abstract: The utility model relates to an imitation of bird fly folding wing aerocraft which adopts power drive. The utility model is composed of an engine (17) which provides power, an air compressor (16), an impact engine which pushes and pulls the fluttering of wings, a wing axle (6) which is used for supporting the wings, and a wing root is hinged on the wing axle, a wings (7) and (8) which can flutter around the wing axle from top to bottom, a guide wing plate (10), an operating swivel plate (1), operating rods (2) and (3), walking wheels (15), etc. The utility model which has the advantages of simple structure, convenient and practical, low cost and flight fee, no strict limitation of condition of the sky, and can do flights of advance and retreat lifting, vertical lifting, etc., in the air is suitable for walking-substitution, or recreation, and the low altitude flight of civil citizen and military affairs.
5 citations
01 Dec 1991
TL;DR: In this paper, a water tunnel flow visualization investigation was performed to study the vortex development and bursting phenomena on a 2.3% scale model of a X-31A-like fighter aircraft.
Abstract: : A water tunnel flow visualization investigation was performed to study the vortex development and bursting phenomena on a 2.3% scale model of a X-31A-Like fighter aircraft. The main focus of this study was two-fold: First, to study the effects of angle of attack and static sideslip on the model vortical flow field. Secondly, to study the effects of dynamic sideslip motion at two reduced yaw rates. Results indicate that the wing root vortex bursting locations move upstream as the AOA increases; and at constant angle of attack (AOA 30 degrees). The dynamic lag effects, which cause the leeward side vortex to burst earlier than in the static case during the positive sideslipping motion and later than in the static case during the negative sideslipping motion, increase with the magnitude of the sideslipping motion.
2 citations
16 Sep 1991
TL;DR: In this paper, the response of an aircraft to two-dimensional vertical atmospheric turbulence has been derived, both for an aircraft regarded as a continuous system and for aircraft split up into a number of panels.
Abstract: Equations for the response of an aircraft to two-dimensional vertical atmospheric turbulence have been derived, both for an aircraft regarded as a continuous system and for an aircraft split up into a number of panels. These equations have been applied to an aircraft model with two degrees of freedom of the size of the Fokker 100, respectively. Two-dimensional turbulence gives a reduction of the loads with respect to one-dimensional turbulence. The reduction of the acceleration in the centre of gravity and the reduction of the wing root bending moment, for the second aircraft model, is 3 percent and 6-8 percent, respectively.
2 citations