Single-engine hovercraft control system and method
A control system of a hovercraft that includes one engine and one propulsion fan enclosed in a duct in which swivel side flaps are located is described. The control system includes, downstream of the duct, at least three rudders. Each of the rudders operates in the full range of angular position, regardless of the position of the swivel side flaps. A control method of such a hovercraft is also described.
1 . A control system of a hovercraft including one motor and a propulsion fan enclosed by a duct in which swivel side flaps are located, the control system comprising:
at least three directional rudders located downstream of the duct, wherein each of the at least three directional rudders is operating in a full range of angular positions independently of a position of the swivel side flaps;
a bottom plate in the duct downstream the propulsion fan and parallel to ground, the bottom plate forming a pocket redirecting a part of airflow passing the hovercraft into an apron of an air-cushion; and
a top plate in the duct downstream the propulsion fan and parallel to the ground, wherein the bottom plate and the top plate are mountings for a rotational axis of the at least three directional rudders, the swivel side flaps, and horizontal rudders.
2 . The control system according to claim 1 , wherein the swivel side flaps rotate symmetrically relative to a longitudinal axis of the hovercraft.
3 . A control method of the hovercraft using the control system according to claim 1 , the control method comprising:
controlling a thrust generating progressive movement of the hovercraft by varying an angle of the swivel side flaps; and
independently controlling a direction of flight of the hovercraft by varying respective angles of at least three directional rudders, wherein the at least three directional rudders operate over a full range of angular positions independently of a position of the swivel side flaps.
4 . The control method according to claim 3 , wherein the swivel side flaps rotate symmetrically relative to a longitudinal axis of the hovercraft.
5 . The control method according to claim 4 , wherein the respective angles of the at least three directional rudders are equal.
6 . The control method according to claim 3 , wherein the respective angles of the at least three directional rudders are equal.