Rotorcraft empennage mounting system
An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearwardly from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof.
1. An aircraft comprising:
an airframe defining a cockpit and having a bulkhead positioned rearwardly from the cockpit and oriented perpendicular to a roll axis of the airframe, the bulkhead having upper and lower edges;
a rotor mast secured to the airframe by mounting to the bulkhead;
a tail boom secured to the airframe by mounting to the bulkhead;
an empennage mounted to the tail boom;
an engine secured to the airframe by mounting to the bulkhead, being secured thereto between a point of attachment of the tail boom to the bulkhead and the lower edge; and
a propeller secured to the engine; and
the empennage, further comprising
two first vertical stabilizers each including a first rudder, the first and second vertical stabilizers being separated by a distance greater than a diameter of the propeller, and
a second vertical stabilizer positioned between the first and second vertical stabilizers and including a second rudder and positioned within a stream tube of the propeller, the first vertical stabilizers being positioned outside the stream tube of the propeller.
2. The aircraft of claim 1 , wherein the bulkhead comprises a monolithic structural member.
3. The aircraft of claim 1 , wherein the bulkhead is a monolithic sheet of structural material.
4. The aircraft of claim 1 , further comprising landing gear mounted to the bulkhead, the engine being positioned between a point of attachment of the landing gear and the point of attachment of the tail boom.
5. The aircraft of claim 1 , wherein:
the cockpit includes a cockpit shell; and
the bulkhead is mounted to a rearward surface of the cockpit shell.
6. The aircraft of claim 1 , wherein:
the cockpit includes a cockpit shell; and
the bulkhead comprises a rearward wall of the cockpit shell.
7. The aircraft of claim 1 , further comprising an engine frame mounted to the bulkhead, the engine being secured to the bulkhead by mounting the engine to the engine frame.
8. The aircraft of claim 1 , wherein the bulkhead comprises a firewall operable to isolate the cockpit from the engine.
9. The aircraft of claim 1 , further comprising a rotor mounted to the mast and selectively coupled to the engine.
10. The aircraft of claim 9 , wherein the rotor operates in autorotation.
11. The aircraft of claim 1 , wherein:
the airframe includes a pylon projecting upwardly from a remaining portion of the airframe, the rotor mast projecting out from the pylon; and
the tail boom mounts to the airframe only at the pylon.
12. An aircraft comprising:
an airframe defining a cockpit and having a bulkhead positioned rearward from the cockpit and substantially orthogonoal to the roll axis of the airframe, the bulkhead defining upper and lower edges;
a rotor mast secured to the airframe by mounting to the bulkhead;
a tail boom secured to the airframe by mounting to the bulkhead;
an empennage mounted to the tail boom;
landing gear secured to the airframe by mounting to the bulkhead;
an engine secured to the airframe by mounting to the bulkhead and secured to the bulkhead between an attachment of the tail boom to the bulkhead and an attachment of the landing gear to the bulkhead;
a propeller coupled to the engine and defining an axis of rotation, the air frame and propeller defining a stream tube; and
the empennage, further comprising
a first horizontal stabilizer positioned above but not in the stream tube,
a second horizontal stabilizer positioned below but not in the stream tube,
first vertical stabilizers each including a first rudder extending between the first and second horizontal stabilizers, the stream tube being positioned laterally between the first vertical stabilizers, and
a second vertical stabilizer positioned laterally between the first vertical stablizers and extending from the first horizontal stabilizer to the second horizontal stabilizer.
13. The aircraft of claim 12 , wherein the bulkhead comprises a monolithic structural member.
14. The aircraft of claim 12 , wherein the bulkhead is a monolithic sheet of material.
15. The aircraft of claim 12 , wherein:
the cockpit further includes a cockpit shell; and
the bulkhead is mounted abutting a rearward surface of the cockpit shell.
16. The aircraft of claim 12 , wherein:
the cockpit includes a cockpit shell; and
the bulkhead comprises a rear wall of the cockpit shell.
17. The aircraft of claim 12 , further comprising a rotor mounted to the mast and selectively coupled to the engine, the rotor operating in autorotation.
18. The aircraft of claim 12 , wherein the stream tube is defined as the stream tube at 40 knots.
19. The aircraft of claim 12 , wherein the first and second horizontal stabilizers are laterally separated by a distance less than a diameter of the propeller.