Rocket-Driven Emergency Power Unit for Electric Aircraft Landing
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Solution Overview
Problem
Electric vertical take-off and landing (eVOTL) aircraft face challenges in ensuring safe and controlled landing in case of a battery pack malfunction, as existing systems lack reliable emergency power solutions to maintain aircraft operation during such failures.
Innovation Solution
The integration of an emergency power unit (EPU) that includes a rocket engine and turbine to generate electric power, allowing the aircraft to continue operating and land safely in the event of a battery pack malfunction, by activating the rocket engine to produce a stream of exhaust fluid and driving a turbine to generate electric power for the aircraft's motor.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a battery pack is used to power the electric motor, then the aircraft can operate efficiently during normal conditions, but the system lacks reliability in case of battery malfunction
Solution Approach 1:
The emergency power unit is pre-configured with rocket propellant and turbine components before any malfunction occurs. Upon detection of battery failure, the system immediately activates the rocket engine and directs exhaust to the turbine, which is already positioned to drive the generator. This preliminary arrangement of components and pre-positioning of the turbine in the exhaust path enables instantaneous response without requiring complex real-time reconfiguration, thus improving reliability while limiting complexity growth.
Solution Approach 2:
The turbine acts as an intermediary device that couples the rocket engine's exhaust energy to the electrical generator. Rather than directly converting rocket exhaust to electricity, the turbine extracts mechanical energy from the exhaust flow and transmits it to rotate the generator shaft. This intermediary mechanism provides a reliable energy transfer path that is independent of the failed battery system, enhancing overall system reliability without requiring direct coupling that would increase complexity.
2Reliability
If an emergency power unit with rocket engine and turbine is added, then reliability during battery malfunction is improved, but device complexity increases
Solution Approach 1:
The turbine serves multiple functions: it extracts energy from the rocket exhaust to drive the generator, and simultaneously its rotation directly drives the propeller through a direct-drive connection. This multi-functionality means that a single component (the turbine) performs both power generation and propulsion functions, eliminating the need for separate generators, gearboxes, or additional transmission systems that would otherwise be required. Consequently, while the EPU adds components, the overall complexity increase is mitigated by this universal component that performs multiple critical functions.
Solution Approach 2:
The emergency power system merges the rocket engine, turbine, generator, and propeller drive into an integrated power plant architecture. The rocket engine and turbine are combined in a turbojet-style arrangement where exhaust flow directly drives the turbine. The turbine shaft is merged to simultaneously drive both the electrical generator and the propeller. This merging of functions and components creates a compact emergency power system that achieves high reliability without proportionally increasing complexity, as shared components serve multiple purposes within the integrated assembly.
3Use of energy by moving object
If the turbine is directed into the exhaust stream, then energy extraction efficiency is improved, but the structural integrity may be compromised by high temperatures and pressures
Solution Approach 1:
The turbine is designed to operate with specific parameters optimized for rocket exhaust conditions. The blade geometry, pitch angles, and rotational speed are selected to match the high-temperature, high-pressure exhaust flow characteristics. By changing the operational parameters (temperature tolerance, pressure rating, rotational velocity) to suit the extreme exhaust environment, the turbine achieves efficient energy extraction while maintaining structural integrity through parameter optimization rather than requiring excessive material strength that would increase weight and complexity.
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
Enables the aircraft to perform emergency maneuvers and achieve a safe and controlled landing even in the event of a battery pack malfunction, by providing temporary backup power through the EPU, ensuring passenger safety and operational reliability.
Implementation Method 1
a rocket engine for generating a stream of exhaust fluid using a rocket propellant
Implementation Method 2
a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine
Implementation Method 3
an electric generator operatively connected to be driven by the turbine and to supply electric power to the electric motor
Data Source
AI summary
Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.