Fixed-Wing Control Mechanism With Adjustable Wing Incidence
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Solution Overview
Problem
The inability to change the incidence angle of wings in air vehicles after conceptual design limits aircraft approach and takeoff speeds, necessitating high speeds for runway operations.
Innovation Solution
A fixed-wing control mechanism that allows adjustable incidence angles through actuators, carrier elements, and beams to modify lift and drag forces, utilizing sensors and actuators to adjust wing angles as needed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If the incidence angle of wings is fixed at the conceptual design stage, then the structural simplicity and manufacturing ease are improved, but the approach speed and takeoff speed become high
Solution Approach 1:
The patent applies the dynamics principle by transforming the fixed incidence angle design into a variable one. Actuators are integrated into the wing structure to enable real-time adjustment of the incidence angle during flight operations. This allows the aircraft to optimize its performance characteristics for different operational phases (takeoff, landing, cruise) without compromising structural integrity or manufacturing feasibility.
2Device complexity
If the incidence angle of wings is fixed at the conceptual design stage, then the device complexity is reduced, but the energy required for takeoff and landing increases
Solution Approach 1:
The patent implements parameter changes by enabling dynamic modification of the wing incidence angle parameter during flight. Actuators adjust the angle of attack to optimize lift and drag characteristics during takeoff and landing phases, thereby reducing the energy required for these operations. The system changes operational parameters adaptively rather than relying on fixed design parameters.
3Speed
If the incidence angle of wings is adjustable, then the approach speed and takeoff speed are reduced, but the device complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the wing structure into modular components that can be independently adjusted. The wing is segmented into sections with integrated actuators that can modify the incidence angle locally. This modular approach enables speed optimization while managing device complexity through standardized, reusable components.
4Use of energy by moving object
If the incidence angle of wings is adjustable, then the energy required for takeoff and landing is reduced, but the structural rigidity may be compromised
Solution Approach 1:
The patent implements the nested doll principle by integrating actuators within the existing wing structure. The adjustment mechanisms are nested inside the wing framework, allowing incidence angle modification without adding external structural elements that would compromise rigidity. The actuators are positioned within the structural contours, maintaining overall structural integrity while enabling functional adjustability.
Data Source
AI summary
The present invention relates to at least one fuselage located in an air and/or space vehicle, at least one structural part in the fuselage that supports an inner surface of the fuselage in terms of strength, a plurality of wings extending outward from the fuselage and providing the required lift force to the fuselag, a plurality of beams located in the wings to provide rigidity to wings, a plurality of openings located on the fuselage facing each other which allow the beams to extend into the fuselage and at least one actuator located in the fuselage allowing the beams to be actuated.