Adjustable Fuselage Control Surface for Emergency Aircraft Stability
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Solution Overview
Problem
Commercial subsonic planes become uncontrollable in case of drop-out or damage to propulsion elements, ailerons, elevator, rudder, and communication channels, especially during extreme weather or stall conditions, leading to potential catastrophic failures.
Innovation Solution
Incorporating adjustable fuselage control surfaces that can extend from the fuselage to influence air currents, providing an additional control mechanism to maintain plane stability and controllability even in emergency situations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the plane uses conventional control surfaces (ailerons, elevator, rudder), then the plane is controllable under normal flying conditions, but it becomes uncontrollable in case of drop-out or damage to these control surfaces
Solution Approach 1:
The fuselage control surface can change its configuration parameter (extended vs. retracted) to adapt to different operational conditions. In normal conditions, it remains retracted to avoid interference. In emergency conditions, it extends to provide alternative control authority, thus resolving the contradiction between reliability and versatility.
Solution Approach 2:
The control surface is designed to be dynamically deployable rather than fixed. It can transition between retracted and extended states based on operational needs, allowing the system to adapt its control characteristics dynamically to maintain reliability across different failure scenarios.
2Reliability
If the fuselage control surface is extended to provide control authority, then the plane becomes controllable in emergency situations, but the fuselage control surface may interfere with normal control surfaces when in extended position
Solution Approach 1:
The fuselage control surface is designed as a dynamic component that can be extended or retracted based on operational requirements. During normal flight, it remains retracted to avoid interfering with conventional control surfaces. In emergency situations, it extends to provide necessary control authority, thus resolving the contradiction between emergency controllability and ease of operation.
3Reliability
If the fuselage control surface is made adjustable between retracted and extended positions, then the plane gains enhanced control capability in emergencies, but the device complexity increases
Solution Approach 1:
The control system is segmented into independent components: the conventional control surfaces and the fuselage control surface. This segmentation allows the fuselage control surface to be operated independently when needed, providing control redundancy without requiring complex integration with the existing control system, thus managing device complexity while enhancing reliability.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The adjustable fuselage control surfaces enable the plane to remain controllable during propulsion or control surface failures, and can recover from stall conditions, enhancing safety by preventing deep stall and reducing the need for uncommon pilot skills.
Implementation Method 1
the fuselage control surface can influence the air currents outside the plane and the plane is controllable
Data Source
Figure 1
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Figure 2b
AI summary
The invention relates to a subsonic plane (1) or flight simulator, actually or simulatedly comprising an elongate fuselage (2) with a cockpit (3) placed near a first, front end of the fuselage, two wings (5) disposed on opposite sides of the fuselage, provided with ailerons (4), and a tail (6) located near a second, rear end of the fuselage, which is provided with an elevator (7) and a rudder (8). The fuselage is furthermore provided with at least one adjustable fuselage control surface (9) for controlling the plane. The fuselage control surface is adjustable between a neutral rest position and at least one working position in which the fuselage control surface extends away from the fuselage.