Distributed eVTOL Power and Recovery Layout for Ultralight Safety
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Solution Overview
Problem
Ultralight aircrafts face challenges in ensuring adequate safety features while meeting weight requirements, particularly in maintaining stability and safety during flight and emergency landings.
Innovation Solution
The electric aircraft incorporates a distributed lifting system with multiple rotors and batteries, a ballistic recovery system, triple redundant sensors, and an on-board electronic flight control system with autonomous and manual flight controllers, along with a quick-swap battery mechanism and amphibious undercarriage for enhanced safety and weight efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If safety features such as ballistic parachute systems and redundant sensors are added to ultralight aircraft, then reliability and safety are improved, but weight increases and may exceed ultralight classification limits
Solution Approach 1:
The patent divides the aircraft into modular components with distributed battery packs and motors throughout the structure. This segmentation allows safety systems to be integrated into existing modules rather than adding separate heavy systems, maintaining weight efficiency while improving reliability through distributed architecture.
Solution Approach 2:
The structural frame serves multiple functions: it provides structural support, houses battery packs, mounts safety systems, and acts as part of the lifting structure. This multi-functionality eliminates the need for separate dedicated safety system structures, preventing weight increase while improving reliability.
2Stability of the object's composition
If multiple distributed lifting devices with individual battery packs are used, then stability and safety are improved through redundancy, but device complexity increases
Solution Approach 1:
The aircraft uses multiple independent rotor-lifting devices distributed throughout the structure, each with its own battery pack. This segmentation provides stability through redundancy while managing complexity by making each module independent and interchangeable, allowing failed components to be replaced without affecting the entire system.
Solution Approach 2:
The control system dynamically adjusts operational parameters such as rotor speed and power distribution among the distributed lifting devices based on flight conditions and system status. This parameter optimization maintains stability while simplifying control by using standardized adjustment protocols across all modules.
3Reliability
If a ballistic recovery system with parachute deployment mechanism is added, then safety during emergency landings is improved, but weight and device complexity increase
Solution Approach 1:
The ballistic recovery system is merged with the existing structural frame and canopy, using the same structural elements for both normal flight operations and emergency deployment. This integration avoids adding separate heavy support structures, improving emergency landing safety while minimizing weight increase.
Solution Approach 2:
The parachute and deployment mechanism are extracted as a separate, compact module that can be stowed in a dedicated compartment and deployed only when needed. This extraction allows the safety system to be minimized to essential components only, reducing weight while maintaining emergency landing capability.
4Ease of operation
If quick-swap battery mechanisms are implemented, then ease of operation and maintenance are improved, but device complexity increases
Solution Approach 1:
The battery packs are designed with dynamic quick-swap mechanisms that allow rapid replacement without tools or complex procedures. The mechanical interfaces include alignment features and latching systems that guide proper insertion and secure connection automatically, improving ease of operation while keeping the complexity contained in standardized interface components.
Solution Approach 2:
The quick-swap mechanism incorporates self-aligning and self-securing features that guide the operator through the replacement process without requiring technical expertise. The system performs its own alignment and locking functions, reducing the need for complex manual procedures or specialized tools.
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
The solution provides improved stability, safety, and weight efficiency by distributing power and thrust, enabling safe emergency landings and autonomous control while minimizing weight and reducing the risk of system failures.
Implementation Method 1
Each of the plurality of distributed lifting devices includes a rotor to provide lift to the electric aircraft
Implementation Method 2
a motor to drive rotation of the rotor
Implementation Method 3
a battery pack to supply power to the motor
Implementation Method 4
The undercarriage comprises a plurality of floats enabling floatation of the electric aircraft
Data Source
AI summary
An electric aircraft comprises a single passenger seat, vertical takeoff and landing capable rotorcraft with an amphibious undercarriage for ground or water landing and takeoff. An electrical power system includes an independent battery for each motor with quick-swap mechanism to enable drained batteries to be easily removed for external charging and swapped for a charged replacement battery. A ballistic recovery system may be deployed to safely land the aircraft in the event of an emergency and may be manually deployed in response to the passenger activating a deployment mechanism integrated into handles within the cockpit. An on-board flight control system includes an automated flight controller that places constraints on flight maneuvers, and a manual flight controller provides a passenger with a limited level of control over the flight.