Convertible aircraft system

A convertible aircraft system comprises:

• a fuselage;
• a proximal flight assembly;
• a distal flight assembly;
• a support spar;
• a tail assembly;
• the fuselage comprises a nose and a stern;
• the proximal flight assembly and the distal flight assembly each comprise a hinged blade, at least one lockable rotation mechanism, a hinge mechanism, and at least one thruster;
• the hinged blade comprises a first elongated portion and a second elongated portion;
• the tail assembly being mounted onto the stern;
• the support spar being mounted onto the nose;
• the support spar being oriented orthogonal to a roll axis of the fuselage and a pitch axis of the fuselage;
• the hinged blade being operatively coupled to the support spar by the lockable rotation mechanism, wherein the lockable rotation mechanism is used to allow and prevent rotation of the hinged blade about the support spar;
• the first elongated portion being operatively coupled to the second elongated portion by the hinge mechanism, wherein the hinge mechanism is used to bistably move the second elongated portion;
• the at least one thruster being laterally mounted to the first elongated portion;
• a propulsion axis of the at least one thruster being oriented orthogonal to the first elongated portion and the support spar;
• and
• the proximal flight assembly and the distal flight assembly being positioned offset from each other along the support spar.