Aircraft Empennage Horizontal Stabilizer Vertical Tail Root Interface
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Solution Overview
Problem
Existing aircraft empennage configurations, such as Conventional, T-Tail, and Cross-Tail, face challenges in optimizing the horizontal tail plane (HTP) placement, leading to increased weight, cost, and complexity due to structural reinforcements and aerodynamic inefficiencies, which affect the vertical tail plane (VTP) and rear fuselage.
Innovation Solution
The empennage configuration positions the horizontal tail plane at the vertical tail plane root area, using a framework with two lateral torsion boxes and a parallelogram framework connected to the rear fuselage section, allowing the HTP to be entirely outside the rear fuselage and minimizing structural reinforcements, thus reducing weight and cost.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the horizontal tail plane is attached to the middle section of the rear fuselage using conventional configuration, then the horizontal tail plane can be positioned for aerodynamic control, but significant structural reinforcements and cut-outs are required which increase weight and cost
Solution Approach 1:
The horizontal tail plane is extracted from the conventional rear fuselage attachment location and repositioned to interface at the vertical stabilizer root. This removes the need for cut-outs and extensive reinforcements in the rear fuselage, as the attachment point is relocated to a structurally efficient location where the vertical stabilizer already provides support.
Solution Approach 2:
The attachment location is moved from the horizontal dimension (rear fuselage cross-section) to a vertical dimension arrangement where the horizontal tail plane interfaces at the base of the vertical stabilizer. This dimensional repositioning allows the horizontal tail plane to be supported by the vertical stabilizer structure rather than requiring separate fuselage reinforcements.
2Ease of manufacture
If the horizontal tail plane is positioned inside the rear fuselage, then attachment is simplified, but a significant portion of the horizontal tail plane is hidden and not useful for aircraft control, requiring increased total size
Solution Approach 1:
The horizontal tail plane is extracted from the interior fuselage space and repositioned to interface externally at the vertical stabilizer root. This ensures the entire horizontal tail plane surface is exposed and effective for aerodynamic control, eliminating the hidden portion problem while maintaining simple attachment through the vertical stabilizer structure.
3Strength
If structural reinforcements are added to the rear fuselage to support the horizontal tail plane, then load distribution is improved, but manufacturing complexity and cost increase due to double curvature areas and fairings
Solution Approach 1:
The attachment function is extracted from the complex rear fuselage area and relocated to the vertical stabilizer root interface. This eliminates the need for double curvature areas, fairings, and complex reinforcements in the rear fuselage, as the load path is redirected through the vertical stabilizer structure which has a simpler geometry.
4Weight of stationary object
If the horizontal tail plane interface is located at the vertical tail plane root, then structural efficiency is enhanced and weight is reduced, but the vertical tail plane must bear additional loads
Solution Approach 1:
The attachment function is merged with the vertical stabilizer root structure. The horizontal tail plane interfaces at the vertical stabilizer root, combining the support functions of both vertical and horizontal stabilizers at a common structural node. This utilizes the existing load-bearing capacity of the vertical stabilizer root without requiring separate reinforcement structures.
Data Source
AI summary
An aircraft empennage includes a vertical tail plane, a rear fuselage section attached to the vertical tail plane and including a skin and internal reinforcing members, a horizontal tail plane comprising two lateral torsion boxes and a framework located between the two lateral torsion boxes comprising a front spar, a rear spar and two ribs extending between the front and the rear spar and each adjacent to a lateral torsion box. The framework encloses a portion of the vertical tail plane along its spanwise direction. The aircraft empennage includes an attachment assembly attaching the framework to the rear fuselage section, the attachment assembly crossing the skin and extends between the internal reinforcing members of the rear fuselage section and the framework.