Fuselage structure for accommodating tails and canards of different sizes and shapes

An aircraft comprising:

• a fuselage comprising an aft portion,
• the aft portion including at least one front horizontal structural interface and at least one rear horizontal structural interface,
• the at least one front horizontal structural interface connected to a front spar of a first horizontal tail or to a front spar of a second horizontal tail,
• the at least one rear horizontal structural interface connected to a rear spar of the first horizontal tail or to a rear spar of the second horizontal tail,
• wherein the first and second horizontal tails are of different sizes.

An aircraft comprising:

• a fuselage comprising a forward portion that includes at least one front canard structural interface and at least one rear canard structural interface,
• the at least one front canard structural interface connected to a front spar of a first canard or to a front spar of a second canard,
• the at least one rear canard structural interface connected to a rear spar of the first canard or to a rear spar of the second canard,
• wherein the first and second canards are of different sizes.

A method of enhancing an aircraft having a fuselage with an aft portion and a forward portion, the aircraft including one or more of a vertical tail, a horizontal tail and a canard, the method comprising:

• wherein if the aircraft has a vertical tail, providing the aft portion of the fuselage with at least one front vertical structural interface and at least one rear vertical structural interface,
• wherein if the aircraft has a horizontal tail, providing the aft portion of the fuselage with at least one front horizontal structural interface and at least one rear horizontal structural interface,
• wherein if the aircraft has a canard, providing the forward portion of the fuselage with at least one front canard structural interface and at least one rear canard structural interface,
• the method further comprising making at least one enhancement to the aircraft selected from the group consisting of:
• allowing the at least one front vertical structural interface to connect to a front spar of a first vertical tail and allowing the at least one rear vertical structural interface to connect to a rear spar of the first vertical tail or, in the alternative, allowing the at least one front vertical structural interface to connect to a front spar of a second vertical tail and allowing the at least one rear vertical structural interface to connect a rear spar of the second vertical tail, wherein the first and second vertical tails are of different sizes;
• allowing the at least one front horizontal structural interface to connect to a front spar of a first horizontal tail and allowing the at least one rear horizontal structural interface to connect to a rear spar of the first horizontal tail or, in the alternative, allowing the at least one front horizontal structural interface to connect to a front spar of a second horizontal tail and allowing the at least one rear horizontal structural interface to connect to a rear spar of the second horizontal tail, wherein the first and second horizontal tails are of different sizes;
• and
• allowing the at least one front canard structural interface to connect to a front spar of a first canard and allowing the at least one rear canard structural interface to connect to a rear spar of the first canard or, in the alternative, allowing the at least one front canard structural interface to connect to a front spar of a second canard and allowing the at least one rear canard structural interface to connect to a rear spar of the second canard, wherein the first and second canards are of different sizes.