WIG Vehicle Excluding Horizontal Stabilizer

Abstract

A body having a fuselage, a wing unit including a main wing, and a propulsion unit including an engine. The wing unit includes a main wing protruding out from the lateral center of the WIG vehicle fuselage, a downward wing which is vertically and downwardly installed on the outer tip of the main wing, and a canard which protrudes out horizontally from the front end of the fuselage, which is in the moving direction of the WIG vehicle from the main wing. The canard includes a horizontal stabilization plate which has a stationary horizontal panel structure, and a variable flap which is installed to face the rear surface of the horizontal stabilization plate. In the lateral cross section shape, the front surface portion including the leading edge is round at a proper thickness to prevent clearance generated by turning of the canard, the trailing edge is sharp and straight, and the thickness of a portion between the thickest portion and rear portion narrows. The lateral cross section of the entire horizontal stabilizer is airfoil-shaped. Accordingly, the invention is able to resolve the design problem of the horizontal stabilizer caused by a ground effect because the WIG vehicle comprises a canard for stabilizing vertical disturbance instead of a horizontal stabilizer.

1 . A wing-in-ground effect vehicle, comprising a body including a fuselage, a wing structure including a main wing, and a propulsion unit including an engine, wherein the wing structure comprises:
 a main wing protruding outward from a central portion of the fuselage of the wing-in-ground effect vehicle;   a downward wing bent vertically downward from a distal end of the main wing; and   a canard protruding horizontally outward from a front part of the fuselage, the canard disposed ahead of the main wing with respect to the direction of travel,   wherein the downward wing includes a downward panel bent downward from and integrally fixed to the distal end of the main wing, and a variable rudder part opposing a rear surface of the downward panel, wherein the downward wing including the rudder part has a vertical cross-section that is configured such that a front portion of the downward wing including a leading edge is rounded at a suitable thickness so that flow separation does not occur, and a rear portion of the downward wing has a thickness converging from a portion having a maximum thickness, with a trailing edge of the downward wing sharply converging in a linear shape, and wherein the entire downward wing has a vertical cross-sectional shape formed as an airfoil, whereby a horizontal stabilizer is excluded.   
     
     
         2 . The wing-in-ground effect vehicle according to  claim 1 , wherein the canard includes a horizontal stabilizing plate having a fixed horizontal panel structure and an elevator part provided to oppose the horizontal stabilizing plate, wherein the elevator part has a side cross-sectional shape such that a front portion of the elevator part including a leading edge is rounded with a suitable thickness so that flow separation does not occur, the thickness converging from a portion that has a peak thickness, and a trailing edge of the elevator part is configured such that it converges in a straight shape, wherein the canard has an airfoil-like overall side cross-section. 
     
     
         3 . The wing-in-ground effect vehicle according to  claim 1 , wherein a lower portion of the downward wing is shaped as an arc or a streamlined “V” in order to decrease friction with sea water or air adjacent to sea surface. 
     
     
         4 . The wing-in-ground effect vehicle according to  claim 3 , wherein the downward wing is made of carbon fiber aluminum. 
     
     
         5 . The wing-in-ground effect vehicle according to  claim 1 , wherein a plurality of ribs and a plurality of spars are provided inside the main wing, wherein the ribs connect the leading edge to the trailing edge of the main wing, and are shaped as an airfoil, and the spars extend across the ribs.