초록 ▼

The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant

The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

대표청구항 ▼

1. An aircraft comprising: a fuselage;a trimmable horizontal stabilizer in a rear zone of the fuselage, the trimmable horizontal stabilizer is actuated by a trimming actuator;the trimmable horizontal stabilizer comprising a load-bearing structure extending in a span direction;the load-bearing struct

1. An aircraft comprising: a fuselage;a trimmable horizontal stabilizer in a rear zone of the fuselage, the trimmable horizontal stabilizer is actuated by a trimming actuator;the trimmable horizontal stabilizer comprising a load-bearing structure extending in a span direction;the load-bearing structure having a portion disposed inside the rear zone of the fuselage that includes at least one pivot element coupled to a pivoting device configured to rotate about a lateral axis and a connection fitting connected to the trimming actuator;wherein:the rear zone of the fuselage comprises at least a first section, and a second section, aft of the first section, wherein the first section of the rear fuselage comprises a bulkhead having the pivoting device coupled to the at least one pivot element of the trimmable horizontal stabilizer;said portion of the load-bearing structure and said trimming actuator are disposed inside the second section of the rear zone of the fuselage;the at least one pivot element is mounted on a forward side of said portion of the load-bearing structure and coupled to the pivoting device on the bulkhead of the first section of the rear zone of the fuselage;the connection fitting is mounted on a rearward side of said portion of the load-bearing structure and is connected to the trimming actuator which is disposed to exert a force in a Z-axis direction of the aircraft via the connection fitting during a trimming operation; anda supporting structure for the trimming actuator is in the second section of the rear zone of the fuselage and is arranged to transmit trimming actuator loads from the trimming actuator to the first section,wherein the supporting structure of the trimming actuator comprises upper and lower longitudinal beams joined to the bulkhead of the fuselage and extending to a position aft of the connection fitting, and a vertical beam joined to rear ends of the upper and lower longitudinal beams. 2. The aircraft according to claim 1, wherein: the load-bearing structure is a torsion box comprising forward and rear spars and upper and lower skins;the at least one pivot element is mounted on the forward spar and the connection fitting for the trimming actuator is mounted on the rear spar. 3. The aircraft according to claim 1, wherein the trimming actuator comprises a rotor actuator positioned close to the bulkhead and an arrangement of rods or cables to exert a force in the direction of the Z-axis of the aircraft over the connection fitting. 4. The aircraft according to claim 1, wherein the horizontal stabilizer is a forward swept horizontal stabilizer. 5. An aircraft comprising: a fuselage;a trimmable horizontal stabilizer including a load bearing structure extending through a rear zone of the fuselage,a trimming actuator mounted within the rear zone and coupled to a connection fitting attached to an aft region of the load bearing structure;a pivot element coupled a front region of the load bearing structure and pivotably attached to a bulkhead of the fuselage at a pivot point, wherein the pivot element is configured to pivot at least a portion the trimmable horizontal stabilizer about the pivot point;the connection fitting is connected to a rear region of the load-bearing structure and connected to the trimming actuator, wherein the trimming actuator moves the connection fitting which pivots the at least a portion of the trimmable horizontal stabilizer about the pivot point; anda supporting structure including upper and lower longitudinal beams joined to the bulkhead and extending aft in the fuselage beyond the connection fitting, and a connecting beam bridging rear ends of the upper and lower longitudinal beams, wherein the supporting structure supports the trimming actuator. 6. The aircraft of claim 5 wherein the load bearing structure is a torsion box and the front region is a front spar of the torsion box and the rear region is a rear spar of the torsion box. 7. The aircraft of claim 5 wherein the trimmable horizontal stabilizer includes a forward swept stabilizer. 8. The aircraft of claim 5 wherein the pivot element includes a first pivot element and a second pivot element each pivotably attached to the bulkhead and separated in a lateral direction within the fuselage. 9. The aircraft of claim 5 wherein the trimming actuator is proximate the connecting beam.