Aircraft Wing Fuel Storage Using Modified Flared Spars
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Solution Overview
Problem
Traditional aircraft wing structures with multi spar and rib construction limit fuel storage capacity and increase complexity due to numerous internal spaces, especially in smaller wings which require wet wing construction, leading to leakage issues and reduced crashworthiness.
Innovation Solution
The elimination of traditional spars and ribs, replaced by modified flared spars with angled hat sections, allowing for a contiguous fuel bladder that conforms to the wing's internal space, enhancing fuel storage capacity and crashworthiness while reducing leakage risks.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional multi spar and rib construction is used, then structural stiffness is improved, but fuel storage capacity deteriorates due to numerous internal spaces
Solution Approach 1:
The patent removes traditional spars and ribs from the wing structure, extracting the internal framework that creates separated spaces. This allows the fuel bladder to occupy the entire internal volume of the wing without being partitioned by structural elements, thereby maximizing fuel storage capacity while maintaining structural integrity through alternative design approaches.
Solution Approach 2:
The patent merges the structural support function and fuel storage function into a unified design. The fuel bladder itself becomes the primary internal component, eliminating the need for separate spars and ribs. The bladder is designed to work with the wing's outer skin to provide both structural support and fuel containment, consolidating multiple functions into a single integrated system.
2Quantity of substance
If fuel bladder is inserted between spars and ribs, then fuel storage is enabled, but device complexity deteriorates due to complicated interconnect plumbing
Solution Approach 1:
The patent removes the traditional spar and rib framework that creates complex internal compartments. By eliminating these structural elements, the fuel bladder can be installed as a single contiguous unit without requiring complex interconnect plumbing to bridge multiple separated spaces, thereby reducing system complexity.
Solution Approach 2:
The patent employs a flexible fuel bladder that can conform to the wing's internal geometry. This flexible membrane design allows the bladder to be installed as a single piece that can be inflated or filled in situ, eliminating the need for rigid plumbing connections between multiple fuel cells or compartments.
3Volume of stationary object
If wet wing construction is used in smaller wings, then fuel storage is achieved, but reliability deteriorates due to numerous leakage points
Solution Approach 1:
The patent uses a flexible fuel bladder as a self-contained fuel containment system. This sealed membrane structure eliminates the need for multiple rigid joints, fasteners, and seals that characterize wet wing construction. The bladder's continuous flexible structure provides fewer potential leakage points and inherent self-sealing capabilities.
Solution Approach 2:
The patent designs the fuel bladder with built-in safety features including self-sealing capabilities and crash-resistant construction. The bladder is pre-engineered to withstand impact forces and automatically seal any potential rupture points, providing beforehand protection against leakage scenarios.
4Volume of stationary object
If traditional spars and ribs are eliminated, then fuel storage capacity is improved, but structural strength deteriorates
Solution Approach 1:
The patent makes the fuel bladder serve multiple functions: it contains fuel, provides structural support to the wing, and acts as a crash-resistant protective element. By designing the bladder with integrated structural ribs or reinforcement elements, it simultaneously performs fuel containment and structural support functions that traditionally required separate spars and ribs.
Solution Approach 2:
The patent employs composite materials in the construction of the fuel bladder to achieve high strength-to-weight ratio. The bladder incorporates reinforced materials such as Kevlar, carbon fiber, or other high-strength composites that provide both fuel containment and structural support capabilities, replacing the need for traditional metal spars and ribs.
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 increases fuel storage volume, simplifies bladder installation and removal, minimizes leakage, and enhances the aircraft's crashworthiness by eliminating the need for complex plumbing and reducing the number of fittings.
Implementation Method 1
the polyurethane dispersion layer may comprise an elastomeric material dispersed or dissolved in a liquid medium
Implementation Method 2
self-sealing volume formed by a membrane defining an internal cavity
Data Source
AI summary
A system and method for improving fuel storage within the wing of an aircraft. In one exemplary embodiment, the system and method eliminate the traditional spars and ribs, and any spanwise and cordwise connecting vertical webs, within a wing. Instead, the system comprises a plurality of modified flared spars, each having a length defined by an angled hat section, to form a wing structure. The modified flared spars may also comprise one or more lengths defined by a specialized section configured to accommodate a portion of a box section, or any other internal component of the wing. The system and method may also involve a contiguous fuel bladder of any size/type. The fuel bladder for the wing may comprise a fabric coated or impregnated with an elastomeric material that may include a polyurethane dispersion layer combined with a sealant.