Dual-Engine Rotorcraft Layout for Controlled Flight After Failure
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Solution Overview
Problem
Gyrocopters face challenges in easy and safe control during all flight conditions, especially in engine assembly failure, and do not meet safety standards for flying in populated or water areas due to lack of redundancy.
Innovation Solution
A rotorcraft design with independent piston engines for the main rotor and propeller, allowing separate control and adjustment of power delivery, and a freewheel mechanism for autorotation, ensuring continued flight and landing safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the rotor is not motorized and relies on aerodynamic flow for rotation, then the structure is simplified and cost is reduced, but the gyrocopter cannot be controlled safely in all flight conditions especially during engine failure
Solution Approach 1:
The invention divides the engine assembly into two independent parts: a first engine for the propeller and a second engine for the rotor. This segmentation allows independent operation of each engine, so that if one fails, the other can still maintain critical functions (propulsion or lift), thereby resolving the contradiction between simplified structure and control safety during engine failure.
Solution Approach 2:
The invention changes the operational parameter of the rotor from purely passive aerodynamic rotation to actively controllable rotation through a dedicated second engine. This allows the rotor to maintain optimal rotation speed under various flight conditions, including engine failure scenarios, thus improving control safety without significantly increasing overall system complexity.
2Device complexity
If a single engine assembly drives both the rotor and propeller, then the device complexity is reduced, but the redundancy system is insufficient for meeting safety standards in populated or water areas
Solution Approach 1:
The single engine assembly is segmented into two independent engines: the first engine drives the propeller for propulsion, while the second engine drives the rotor for lift generation. This segmentation creates functional redundancy, as each engine can independently maintain its critical function if the other fails, thereby meeting safety standards for operation in populated or water areas without excessive complexity.
Solution Approach 2:
The invention implements beforehand cushioning by providing a second dedicated engine for the rotor that can take over lift generation if the first engine fails. This preparatory redundancy ensures that the gyrocopter can maintain controlled flight and landing capability in critical situations, satisfying safety requirements for operation in sensitive areas.
3Productivity
If the engine assembly is disconnected from the rotor during flight, then the propeller can maintain propulsion, but the rotor is no longer affected by air flow for rotation and the gyrocopter may lose altitude or fly in random trajectories
Solution Approach 1:
The invention segments the power transmission system so that the first engine is mechanically connected only to the propeller, while the second engine is mechanically connected only to the rotor. This allows the first engine to maintain optimal propulsion efficiency while the second engine independently maintains rotor rotation and flight stability, eliminating the contradiction between propulsion efficiency and flight stability.
Solution Approach 2:
The second engine is designed to automatically maintain rotor rotation independently of the first engine's operation. This self-service capability ensures that the rotor continues to receive the necessary rotational energy to maintain lift and stability, even when the first engine is operating at full throttle for maximum propulsion efficiency.
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 safe and controlled flight in all conditions, including engine failures, and meets safety standards for various flying areas by providing redundancy and independent power management.
Implementation Method 1
at least one piston engine for setting in rotation a crankshaft with which the engine assembly is provided, the propeller being associated with the crankshaft
Implementation Method 2
at least one main rotor associated with the basic chassis and movable in rotation around a main axis to generate at least one in-flight maintaining force of the rotorcraft
Implementation Method 3
at least one propeller associated with the basic chassis and movable in rotation around a secondary axis transverse to the main axis to generate at least one propulsion force to move the rotorcraft when it is maintained in flight
Data Source
Figure 1
Figure 2
Figure 3
AI summary
The rotorcraft (1) comprises: - one basic chassis (2); - one main rotor (5) associated with the basic chassis (2) and movable in rotation around a main axis (A) to generate at least one in-flight maintaining force of said rotorcraft (1); - one propeller (6) associated with the basic chassis (2) and movable in rotation around a secondary axis (B) transverse to the main axis (A) to generate at least one propulsion force to move the rotorcraft (1) when it is maintained in flight; - at least one engine assembly (20) associated with the basic chassis (2) and adapted to move the main rotor (5) and the propeller (6) in rotation.