Abstract: An automatic pilot system for a model airplane comprising one or more flexible control elements. When installed on a vertical stabilizer of the airplane, a flexible control element acts as an automatic rudder which provides directional control for the airplane so that it takes off in a straight line at high speed and glides in a circular path of a predetermined radius at low speed. When installed on a horizontal stabilizer of the airplane, a flexible control element acts as an automatic elevator which provides a reduced angle of attack during take-off to minimize the aerodynamic drag, an increased angle of attack during gliding flight to make the flight slower and longer-lasting, and an even greater angle of attack during landing to make the landing even slower for safety. When installed on a wing of the airplane, a flexible control element acts as an automatic dihedral wing tip which provides increased lateral stability for the airplane.

Abstract: An impact absorbing wing connection system for model airplanes and other flying toys of the type having a fuselage (10) and separate wings (14) that are to be inserted into wing slots (12) in the fuselage for flight. The friction between the touching surfaces of the wings and the wing slots is reduced by a low friction coating (18) over the wing roots (16) or by other friction reducing means so that a tight fit is preserved. The wings are oriented into their proper flying positions by their exact fit with the fuselage, and they are kept in these positions during normal flight by a set of non-elastic break-away links (26) which are attached to the wings and to the fuselage through a corresponding set of wing connecting members (20) and fuselage connecting members (24), respectively. In case of a crash, the inertia forces of the wings are conveyed to the break-away links by the connecting members.

Abstract: An automatic tow release system for model aircraft launched with the help of a tow line (12) which has novel means for continuously and automatically adjusting the climb angle of the fuselage and automatically releasing the tow line (12) when the aircraft reaches a predetermined climbing position. The tow release system comprises a primary (16) and a secondary (18) control string, a connecting body (20), a primary (42) and a secondary (44) connecting means between the connecting body (20) and the aircraft, and a release promoting means. The release promoting means is a feature of the particular design of the tow release system. The control strings (16, 18) are attached to the tow line (12) at one end and to the connecting body (20) at the other end. The connecting body (20) is demountably connected to the aircraft during the tow through the primary (42) and secondary (44) connecting means, respectively.