Contrarotating Propellers for Paramotor Weight and Torque
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Solution Overview
Problem
Current paramotor systems are excessively heavy and inefficient, making them unwieldy for military missions that require long-range, silent, and reliable flight, especially when compared to electric systems which have limited duration and high weight batteries.
Innovation Solution
A series hybrid electric propulsion system with contrarotating propellers is proposed, utilizing a downsized engine, generator, and electric motors to optimize weight and efficiency, along with advanced monocoque carbon fiber designs and modular systems for improved reliability and safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If traditional paramotor systems are used to meet military mission requirements, then the system can achieve required range and altitude, but the weight becomes excessively high making launch and landing extremely difficult and dangerous
Solution Approach 1:
The propulsion system is divided into two independent engines, each with its own propeller and fuel tank. This segmentation allows the weight to be distributed across multiple components rather than concentrated in one heavy engine, making the overall system more manageable for launch and landing while maintaining the required flight duration through redundant power sources
Solution Approach 2:
One propeller is positioned inside the hub of the other propeller, creating a nested configuration where the inner propeller rotates within the outer propeller's hub structure. This nesting arrangement reduces the overall spatial footprint and allows for more compact fuel tank placement, thereby reducing total system weight while maintaining dual-engine redundancy for extended flight duration
2Duration of action of moving object
If heavier equipment is added to increase fuel capacity for longer flight duration, then the range is extended, but the launch weight increases making the mission impractical
Solution Approach 1:
Fuel capacity is segmented into multiple smaller tanks distributed across the wing structure rather than one large heavy tank. This allows adequate fuel volume for extended flight duration while distributing weight to maintain manageable launch characteristics
Solution Approach 2:
Fuel tanks are positioned within the wing structure and nested around the propeller assembly, utilizing available space efficiently. This nesting of fuel storage within the existing structural envelope avoids adding external weight while maintaining sufficient fuel capacity for the required flight duration
3Power
If a single heavy engine is used to provide sufficient thrust, then the power requirement is met, but the system becomes unwieldy and unsafe for military operations
Solution Approach 1:
The propulsion power is segmented into two independent engine-propeller systems instead of one heavy engine. Each engine provides sufficient thrust individually, and the distributed configuration improves reliability by eliminating single-point failure, making the system safer for military operations while maintaining required power output
Solution Approach 2:
The dual-engine configuration is nested within a single wing structure with both engines mounted on the same wing. This nested arrangement maintains compact overall dimensions while providing redundant power sources, improving reliability without compromising the power requirement for military mission operations
4Ease of operation
If contrarotating propellers are implemented to cancel torque effects, then flight control is improved, but the device complexity increases
Solution Approach 1:
The propeller system is segmented into two separate counter-rotating propellers instead of one complex single propeller. Each propeller is a standard off-the-shelf component, and their counter-rotation cancels torque effects to improve flight control. The segmentation into two simple rotating components is less complex than designing and manufacturing one large complex propeller with integrated torque cancellation features
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 system achieves significant weight reduction and improved fuel efficiency, enabling longer flight durations and reduced noise, while maintaining reliability and safety through redundant propulsion and advanced navigation and autopilot capabilities.
Implementation Method 1
multiple propellers capable of rotating in opposite direction and providing thrust
Implementation Method 2
multiple propellers capable of rotating in opposite direction and providing thrust
Implementation Method 3
a flexible wing (paraglider or parachute) for providing lift
Data Source
AI summary
Current foot-launched 2-stroke commercial PPG offerings can meet the specified threshold (and in some cases, objective) requirements for flight ceiling, payload capacity and range with little to no modification. We will discuss those in the next section. The APES system enhances the effectiveness and lethality of the PPG-equipped unit by reducing weight of the PPG, increasing reliability and redundancy, reducing pilot workload, and seamlessly integrating with UAV's and UGV's. System improvements in the following areas is assessed: Series hybrid-electric powertrain, Coaxial propellers. Localization, autopilot, and formations, Auto landing and other advanced features, Integration with unmanned systems, and Launch Considerations.