| 摘要 |
<p>The invention relates to wing-in-ground-effect vehicles with air lift. The technical result is an increase in the pitch angle and altitude range within which the necessary static stability is achieved, and also an increase in manoeuvrability in the floating and gliding modes. The wing-in-ground-effect vehicle comprises a fuselage (1), a composite wing with a centre section (2) and panels (3), a horizontal stabilizer (4) mounted on a single or on twin vertical stabilizers (5), floats (13), an airscrew (14) located in front of the centre section and kinematically connected to an engine (11) that is located in the centre section (2), and an engine (39) having a raisable water screw (38) and a water rudder (46). The centre section (2) has a forward swept trailing edge, is anhedral and is provided with leading and/or trailing edge flaps. The span of the horizontal stabilizer (4) is at least 1.2 times greater than the span of the centre section (2), the static moment of the horizontal stabilizer and the panels being ? ?? +? ? =0.25...0.45, including ? ?? =0.19...0.34.</p> |
