Aircraft Landing Gear Energy Dissipation via Fluid Heating
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Solution Overview
Problem
Existing aircraft landing gear systems face challenges in efficiently dissipating electrical energy generated during braking, particularly requiring large resistors, batteries, or superconductors, which are heavy and inefficient, especially during low-speed braking where carbon brakes experience significant wear due to surface plucking.
Innovation Solution
The system incorporates a gearing mechanism connected to a generator that converts kinetic energy into electrical energy, which is then dissipated as heat using an electrical heating element and fluid receptacle, allowing for efficient heat transfer and dissipation, and optionally includes a cavitation braking device to generate heat through liquid cavitation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a large resistor is used to dissipate electrical energy from the generator, then the electrical energy can be converted into heat energy and dissipated, but the system becomes heavy and inefficient
Solution Approach 1:
The patent replaces the traditional mechanical/electrical resistor-based dissipation system with a thermal fluid-based system. The electrical heating element converts electrical energy to heat, which is then transferred to a fluid in a receptacle, eliminating the need for heavy resistors while maintaining energy dissipation functionality.
Solution Approach 2:
The patent uses a fluid (liquid or gas) in a receptacle to absorb and carry away heat energy. The fluid acts as a heat transfer medium, allowing efficient thermal energy dissipation without requiring heavy solid dissipators. The fluid can be circulated or allowed to evaporate, providing effective cooling.
2Ease of operation
If carbon brakes are used for low-speed braking, then braking function is provided, but significant wear occurs due to surface plucking
Solution Approach 1:
The patent replaces the mechanical friction-based carbon brake system with an electro-mechanical braking system. The motor/generator acts as a regenerative brake during deceleration, converting kinetic energy to electrical energy, which is then dissipated as heat through the heating element and fluid system, eliminating direct contact wear.
Solution Approach 2:
The system uses the motor/generator to serve dual purposes: propulsion during acceleration and braking during deceleration. By functioning as a generator during braking, it automatically captures and dissipates kinetic energy without requiring separate brake components, reducing wear and improving efficiency.
3Loss of energy
If large batteries or superconductors are used to store electrical energy from the generator, then energy can be retained, but the system becomes heavy and complex
Solution Approach 1:
The patent extracts the energy storage function entirely from the system by directly dissipating electrical energy as heat through the heating element and fluid receptacle. This eliminates the need for batteries or superconductors, simplifying the system while managing energy through immediate thermal conversion rather than storage.
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 solution effectively slows aircraft movement by quickly dissipating heat energy, reducing wear on carbon brakes and eliminating the need for heavy dissipators, while providing a lightweight and efficient braking mechanism.
Implementation Method 1
the second gearing element is connected to a generator, such that rotation of the second gearing element causes the generator to generate electrical energy
Implementation Method 2
the heat dissipation device comprises an electrical heating element connectable to the generator to receive generated electrical energy and convert it to heat energy
Implementation Method 3
a fluid receptacle adjacent the heating element, such that fluid in the receptacle can be heated by the heating element
Implementation Method 4
The fluid is preferably a liquid and may turn into a gas upon heating. That gas may then leave the fluid receptacle.
Implementation Method 5
optionally includes a cavitation braking device to generate heat through liquid cavitation
Data Source
AI summary
An aircraft landing gear comprising a wheel rotatably mounted on an axle, a first gearing element that rotates with the wheel, a second gearing element configured to mesh with the first gearing element such that rotation of the first gearing element causes rotation of the second gearing element, wherein the second gearing element is connected to a generator, such that rotation of the second gearing element causes the generator to generate electrical energy, further comprising a heat dissipation device connected to the generator wherein the heat dissipation device comprises an electrical heating element connectable to the generator to receive generated electrical energy and convert it to heat energy, and a fluid receptacle adjacent the heating element, such that fluid in the receptacle can be heated. An aircraft landing gear further comprising a cavitation braking device, an aircraft and a method of braking.