Variable Geometry Aircraft Wing Pivot Mechanism
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional swing-wing aircraft face challenges in achieving both energy-efficient cruising and maneuverable flight behaviors due to the conflict between slender wings for efficient cruising and the need for pivoting kinematics, which increases weight and radar detectability, while also requiring a pivoting drive.
Innovation Solution
The aircraft features a pivot axis oriented at a maximum deviation of 40° from the longitudinal direction, allowing for the same aircraft to switch between energy-efficient and maneuverable configurations using aerodynamic forces for pivoting, eliminating the need for a dedicated pivoting drive and reducing radar signature.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a dedicated pivoting drive system is installed to enable wing sweep variation, then the aircraft can switch between energy-efficient and maneuverable configurations, but the weight increases and radar signature becomes more detectable
Solution Approach 1:
The patent applies the self-service principle by enabling the outer wing sections to pivot automatically using aerodynamic forces generated during flight. The control system activates control surfaces on the inner wing sections to create differential lift, which naturally pivots the outer wing sections to the desired sweep angle without requiring a dedicated mechanical drive system, thereby reducing weight while maintaining configuration adaptability
Solution Approach 2:
The patent replaces the traditional mechanical pivoting drive system with an aerodynamic-based system. Instead of using motors, gears, and linkages to physically rotate the wings, the invention uses aerodynamic forces generated by control surface deflections to achieve the same pivoting effect, substituting a mechanical system with a fluid dynamics-based system that reduces weight and complexity
2Adaptability or versatility
If a dedicated pivoting drive system is installed to enable wing sweep variation, then the aircraft can switch between energy-efficient and maneuverable configurations, but the radar detectability increases
Solution Approach 1:
The patent applies the self-service principle by enabling the outer wing sections to pivot automatically using aerodynamic forces generated during flight. The control system activates control surfaces on the inner wing sections to create differential lift, which naturally pivots the outer wing sections to the desired sweep angle without requiring a dedicated mechanical drive system, thereby reducing weight while maintaining configuration adaptability
Solution Approach 2:
The patent replaces the traditional mechanical pivoting drive system with an aerodynamic-based system. Instead of using motors, gears, and linkages to physically rotate the wings, the invention uses aerodynamic forces generated by control surface deflections to achieve the same pivoting effect, substituting a mechanical system with a fluid dynamics-based system that reduces weight and complexity
3Use of energy by moving object
If slender wings are used for energy-efficient cruising, then fuel efficiency improves, but maneuverability and roll control capability deteriorate
Solution Approach 1:
The patent applies the dynamics principle by making the wing configuration variable rather than fixed. The aircraft can dynamically adjust the sweep angle of the outer wing sections during flight, transitioning from a slender, high-aspect-ratio configuration for efficient cruising to a shorter, more maneuverable configuration when agility is required. This dynamic adaptability allows the aircraft to optimize performance for different flight phases without being constrained by a fixed wing design
4Adaptability or versatility
If the pivot axis is oriented in the vertical direction (conventional swing-wing), then wing sweep variation is achieved, but a complex tilting mechanism and dedicated drive system are required
Solution Approach 1:
The patent replaces the traditional mechanical pivoting drive system with an aerodynamic-based system. Instead of using motors, gears, and linkages to physically rotate the wings, the invention uses aerodynamic forces generated by control surface deflections to achieve the same pivoting effect, substituting a mechanical system with a fluid dynamics-based system that reduces weight and complexity
Solution Approach 2:
The patent applies the self-service principle by enabling the outer wing sections to pivot automatically using aerodynamic forces generated during flight. The control system activates control surfaces on the inner wing sections to create differential lift, which naturally pivots the outer wing sections to the desired sweep angle without requiring a dedicated mechanical drive system, thereby reducing weight while maintaining configuration adaptability
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
This configuration enables the aircraft to perform multiple flight missions with reduced weight and radar detectability, achieving efficient cruising and agile flight behaviors without the need for a complex pivoting mechanism, while maintaining low radar signature.
Implementation Method 1
utilizing aerodynamic forces acting on the outer wing sections
Data Source
Figure 1~2
Figure 3~4
Figure 5
AI summary
The aircraft (10) has a body (12) with a pair of airfoils (14-1, 14-2) distant from each other in a transverse direction (y), where each airfoil includes inner airfoil sections (16-1, 16-2) and outer airfoil sections (20-1, 20-2). The inner sections are fixedly arranged with respect to the body. The outer sections are pivotable around pivot axes (18-1, 18-2) and connected to the inner sections. The pivot axes are oriented in a direction deviated from a longitudinal direction (x) of the aircraft around 20 degrees. A control device (24) controls automatic pivoting of the outer sections. An independent claim is also included for a method for changing geometry of an aircraft.