| 摘要 |
<p>An improved aerobatic aircraft design having a first engine (18) located in the nose portion (14) of the fuselage (12) and a second engine (22) located in the tail portion (16) of the fuselage (12). The thrust components of both the first (18) and second (22) engines are coaxial along the long axis (70) of the fuselage (12). Both engines can individually provide sufficient power for the aircraft to takeoff, maintain altitude, and/or land.</p> |
