# US 12,006,022 B2 · Aircraft empennage

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- Number: US 12,006,022 B2
- Document ID: US12006022B2
- Status: Granted
- Kind: B2
- Application number: 17/526,386
- Filed: 2021-11-15
- Published: 2022-09-29
- Granted: 2024-06-11
- Earliest claimed: 2021-03-26
- Assignees: Airbus Operations S.L.U.
- Applicants: Airbus Operations S.L.U.
- Inventors: Mario Linares Villegas; Silvia Garcia Toran
- Web page: https://patentgrep.com/patent/US12006022B2

## CPC

- B64C 1/0685: {Tail cones}
- B64C 5/02: Tailplanes
- B64C 1/26: Attaching the wing or tail units or stabilising surfaces
- B64C 5/16: about spanwise axes
- B64C 9/02: Mounting or supporting thereof
- B64C: AEROPLANES; HELICOPTERS

## Abstract

An aircraft empennage, comprising a rear fuselage section, a trimmable horizontal tail plane comprising a first and a second lateral torsion box), each comprising a front spar and a rear spar, a front fitting and a rear fitting, an actuator acting on the front fitting for a rotation of the trimmable horizontal tail plane around a hinge axis passing through the rear fitting, the front fitting comprising a first and a second front fitting units being joined to the front spars of the lateral torsion boxes, and the actuator comprising first and a second actuator units, each acting on the first front fitting unit and the second front fitting unit respectively.

## Claims

### Claim 1

An aircraft empennage, comprising:
a rear fuselage section comprising a skin and a frame,
a trimmable horizontal tail plane comprising a first and a second lateral torsion box, the first and the second lateral torsion box comprising a front spar and a rear spar,
a front fitting and a rear fitting connected to the trimmable horizontal tail plane and to the fuselage section,
an actuator configured to act on the front fitting for a rotation of the trimmable horizontal tail plane around a hinge axis passing through the rear fitting and orthogonal to a vertical longitudinal plane of symmetry of the fuselage section,
wherein the front fitting comprises a first and a second front fitting units, the first front fitting unit being joined to the front spar of the first lateral torsion box and the second front fitting unit being joined to the front spar of the second lateral torsion box, and
wherein the actuator comprises a first and a second actuator units, the first actuator unit being configured to act on the first front fitting unit and the second actuator unit being configured to act on the second front fitting unit,
wherein the first and the second actuator units are located in front of the front spar and rearward of a most forward point of the trimmable horizontal tail plane on a longitudinal axis of the rear fuselage section,
wherein the first front fitting unit and the second front fitting unit each comprise an elongated support bar located in a plane perpendicular to the front spar, the elongated support bars pointing towards lateral sides of the rear fuselage section.

### Claim 2 (depends on 1)

The aircraft empennage, according to claim 1, wherein the horizontal tail plane comprises a swept backward angle.

### Claim 3 (depends on 1)

The aircraft empennage, according to claim 1, wherein the fuselage section comprises a first access door to the first front fitting unit and a second access door to the second front fitting unit, said access doors being located on opposite lateral sides of the rear fuselage section.

### Claim 4 (depends on 1)

The aircraft empennage, according to claim 1, wherein the first and the second actuator units are located adjacent to the skin of the rear fuselage section.

### Claim 5 (depends on 1)

The aircraft empennage, according to claim 1, wherein the first and the second actuator units are located in the same longitudinal section of the fuselage section on an axis parallel to a pitch axis of the fuselage section.

### Claim 6 (depends on 1)

The aircraft empennage, according to claim 1, wherein each of the first and the second actuator units is located under or above each of the front fitting units with respect to a Z-axis of the aircraft empennage.

### Claim 7 (depends on 1)

The aircraft empennage, according to claim 1, wherein the first and the second actuator units are joined to a lower part or to an upper part of a frame.