A method of using a wing-in-ground-effect craft (WIG craft) to allow integrated increase in aerodynamic and cargo-carrying characteristics, said method comprising the steps of:
- a) generating required lift force (LF) using a high air pressure region between a load-carrying low-aspect-ratio wing (LAW) and a supporting surface, and by way of blowing off flow from an upper surface of said LAW;
- b) creating progressive motion using thrust propulsion units, pitch, roll and yaw controls, wherein that a natural character of dependence of a magnitude of said lift force and locations of focuses of said low-aspect-ratio wing on angle of attack and height of flight is changed via creation, in longitudinal direction, of at least one a forward region of lift force generation and at least one rear region of lift force generation;
- c) projections of focuses onto a longitudinal axis ahead of and behind a center of gravity (CG), through the use of at least one forward LAW, at least one rear LAW and at least two aerodynamic plate-floats (APFs), said at least one forward LAW having a leading edge flap, a semiannular section of an upper surface and flaperons, said at least one rear LAW having with at least one shrouded-screw propulsor (SSP), at least one engine and flaperons, said at least two APFs being joined wing-to end surfaces of said at least one forward LAW and said at least one rear LAW;
- d) creating different conditions of flow of air streams around said at least one forward LAW and said at least one rear LAW;
- e) forming a static air cushion (SAC), a dynamic air cushion (DAC) and a static-and-dynamic air cushion (SDAC) under said at least one forward LAW and said at least one rear LAW;
- f) creating a low air pressure region with reduced irregularity in a longitudinal direction above said WIG craft, with mutual compensation of moments of lift forces of said forward and read regions of generation of said lift forces, relative to the center of gravity, and positions of the focus in terms of height ahead of the center of gravity, and of the focus in terms of angle of attack behind the center of gravity, which is positioned between the focus in terms of height and a point of midway between the focuses;
- g) allowing for interaction of undisturbed free approach air with a lower surface and partially with an upper surface of said at least one forward LAW;
- h) reducing the interaction of the undisturbed free approach air with said upper surface of said at least one forward LAW through suction of air layer over an entire span of said upper surface with said at least one SSP, and interaction thereof with lower and upper surfaces of said at least one rear LAW is prevented by blowing off said lower and upper surfaces of said at least one rear LAW over an entire span with said at least one SSP;
- i) controlling magnitudes of said forward and rear lift forces through variations of at least one of deflection angles of said flaperons of said at least one forward LAW and said at least one rear LAW, and power setting of said at least one SSP;
- j) (1) stabilizing the flight and dampening pitch fluctuations through automatic variation of forward lift force magnitude as a function of pitch angle as strong reversed feedback, the variations being effected by way of dynamic control of positions of said at least one forward LAW flaperon to actuating devices of which control inputs from an angle of attack sensor (AAS) are transmitted;
- j) (2) stabilizing the flight and dampening pitch fluctuations through automatic variation of rear lift force magnitude as a function of pitch angle as strong positive feedback, the variations being effected by way of dynamic control of positions of said rear LAW flaperon to actuating devices of which control inputs from an angle of attack sensor (AAS) are transmitted;
- k) using said at least one SSP to create progressive motion, blow off and suck flow from upper surfaces of load-carrying planes;
- l) removing weight load from said WIG craft with use of excess pressure in said static and dynamic air cushions and additionally remove weight load through use of vertical component of thrust force;
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- m) securing additional controllability and additional thrust force due to a “Bartini effect” and multiplication of velocity of flow passing through said at least one SSP.