Stealth Double Wings for Tailless Aircraft Stability
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Solution Overview
Problem
Stealth military aircraft without vertical tails face challenges in achieving stable and rapid attitude flight control, especially in adverse weather conditions, leading to restricted movement and poor agility, which compromises flight safety and mission effectiveness.
Innovation Solution
The aircraft incorporates stealth double wings with a main wing and two rotating shafts, link rods, and wings that can be adjusted to function as vertical tails, allowing for enhanced controllability and stability by controlling the position of the wings via a system, maintaining the surface integrity of the main wing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If vertical tails are removed to achieve radar-stealth effect, then radar cross section is reduced, but attitude flight control stability deteriorates
Solution Approach 1:
The patent applies the dynamics principle by making the wing surfaces movable rather than fixed. The first and second wings can rotate relative to the main body through rotating shafts, allowing the aircraft to dynamically adjust its configuration. When vertical tails are needed for stability, the wings rotate to vertical positions; when stealth is prioritized, they return to horizontal positions. This dynamic reconfiguration resolves the contradiction between fixed stealth geometry and variable stability requirements.
Solution Approach 2:
The patent implements multi-functionality by designing the wings to serve multiple purposes: they function as both horizontal wings for lift generation and as vertical tails for stability control. The same wing structures that provide aerodynamic lift can be rotated to vertical positions to provide directional stability, eliminating the need for separate vertical tail surfaces that would compromise stealth characteristics.
2Object-affected harmful factors
If vertical tails are removed to achieve radar-stealth effect, then radar cross section is reduced, but rapid and smooth change of attitude flight control becomes difficult
Solution Approach 1:
The dynamic reconfiguration of wings to vertical positions provides the necessary surfaces for rapid attitude changes. The rotating shaft mechanisms enable quick transition between configurations, allowing the aircraft to achieve rapid pitch and yaw control when needed while maintaining stealth posture during cruise phases.
Solution Approach 2:
The aircraft control system is segmented into independent controllable units - the first and second wings can be adjusted independently through their respective rotating shafts. This segmentation allows for fine-grained control of attitude changes, enabling smooth and rapid transitions by coordinating the movement of individual wing segments rather than relying on fixed surfaces.
3Ease of operation
If spoilers are used for flight direction adjustment without vertical tails, then flight control is achieved, but flexibility and agility are reduced
Solution Approach 1:
The patent replaces fixed spoiler-based control with dynamic wing reconfiguration. Instead of relying solely on spoilers for flight direction adjustment, the aircraft can actively change its geometry by rotating wings to vertical positions, providing much greater flexibility and agility. This dynamic morphing capability allows for rapid and extensive attitude changes that spoilers alone cannot achieve.
4Object-affected harmful factors
If flying-wing and tailless designs are used, then radar-stealth effect is improved, but flight safety under adverse weather conditions deteriorates
Solution Approach 1:
The dynamic wing reconfiguration system provides adaptability for adverse weather conditions. When encountering turbulence or severe weather, the wings can be rotated to vertical positions to provide tail-like stability, enhancing flight safety without compromising the inherent stealth design. This on-demand stability provision resolves the contradiction between fixed stealth geometry and variable weather-resistant requirements.
Data Source
AI summary
An aircraft with stealth double wings comprises a main body and stealth double wings. The main body has two main wings respectively having a surface into which a space is formed. The stealth double wings respectively are located in the spaces and include a first and a second rotating shaft, a link rod, a first and a second wing. The link rod has two ends respectively connected with the two rotating shafts. The two rotating shafts respectively have another end connected with the first and second wings. Thereby, when the first wing is moved to cover and enclose the space's opening, the second wing is driven to be located within the space, and when the first wing is moved upwardly away from the space, the second wing is driven to cover and enclose the space's opening, so as to keep the surface intact.