Free Propeller Assembly With Electronic Blade Angle Control
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Solution Overview
Problem
Conventional helicopter propeller assemblies have restricted rotor blade movement, limiting flight agility, load capacity, and flexibility, making them unsuitable for high-speed flight, efficient cargo transport, and emergency operations, particularly in challenging environments like high altitudes and rugged terrains.
Innovation Solution
A free propeller assembly structure featuring a circular shaft, main rotor, signal transmitting device, and rotor blade assembly with unrestricted rotation, allowing precise control of rotor blade angles and enabling greater wind pressure generation and efficient energy use.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional mechanical propeller assembly with link rods and hinges is used, then structural stability is maintained, but rotor blade rotation freedom is restricted
Solution Approach 1:
The patent removes the complex mechanical linkage system (link rods, hinges, universal joints) from the propeller assembly, extracting only the essential function of blade rotation control. The rotor blades are directly mounted on the rotating ring without mechanical transmission components, achieving full rotation freedom while simplifying the structure.
Solution Approach 2:
The patent replaces the mechanical control system with an electronic control system. Electronic sensors detect blade position and control signals are transmitted to actuators that adjust blade angles, substituting the mechanical link rod and hinge system with an electronic feedback control mechanism.
2Productivity
If conventional propeller assembly with restricted blade rotation is used, then manufacturing simplicity is maintained, but flight performance and load capacity are limited
Solution Approach 1:
The patent implements dynamic blade angle adjustment capability where rotor blade angles can be changed during flight operations. The blade mounting structures include actuators that allow real-time modification of blade pitch angles, enabling the system to adapt to varying flight conditions and maximize performance.
Solution Approach 2:
The rotating ring structure serves multiple functions: it supports rotor blade rotation, provides mounting positions for multiple blades, incorporates electronic sensors for position detection, and includes actuators for blade angle control. This multi-functional design achieves high flight performance without proportionally increasing manufacturing complexity.
3Ease of repair
If conventional mechanical propeller structure is used, then structural reliability is maintained, but maintenance complexity increases
Solution Approach 1:
The patent removes the mechanical transmission components (link rods, hinges, universal joints) that are prone to wear and require frequent maintenance. By eliminating these parts, the system achieves higher reliability with fewer moving parts while reducing maintenance complexity to only the essential motor and sensor components.
Solution Approach 2:
The electronic control system incorporates sensors that continuously monitor blade position and system status, automatically detecting potential issues before they become failures. The system can self-diagnose and alert operators to maintenance needs, reducing the complexity of routine inspections and repairs.
4Force
If conventional propeller assembly with mechanical linkages is used, then structural stability is maintained, but wind pressure generation capability is limited
Solution Approach 1:
The patent implements dynamic blade angle adjustment capability where rotor blade angles can be changed during flight operations. The blade mounting structures include actuators that allow real-time modification of blade pitch angles, enabling the system to adapt to varying flight conditions and maximize performance.
Solution Approach 2:
The patent changes the operational parameters of the rotor blades by enabling continuous adjustment of blade pitch angles and rotation speeds. The electronic control system can optimize blade angle parameters in real-time based on flight conditions, maximizing wind pressure generation capability without mechanical complexity.
Data Source
AI summary
The present invention relates to a free propeller assembly structure and an aircraft structure has the free propeller assembly. The free propeller assembly structure has at least one free propeller assembly. Each of the at least one free propeller assembly has a circular shaft, a main rotor, a signal transmitting device, and a rotor blade assembly. The main rotor has a shaft hole and multiple blade mounting structures radially disposed. Each blade mounting structure is provided with a positioning recess for mounting a driving motor in each positioning recess. The signal transmitting device includes multiple signal transmitters that are able to transmit interpretable electronic signals or photonic signals. The rotor blade assembly includes at least two rotor blades. One end of each rotor blade is connected with an open end of the positioning recesses of a corresponding one of the blade mounting structures.