Coaxial Counter-Rotating Rotor for Extended Aerial Payload Transport
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Solution Overview
Problem
Existing aerial payload transportation devices face limitations in flight time due to low energy density batteries and lack of hovering capability, and require extensive infrastructure for take-off and landing.
Innovation Solution
A drone apparatus with a coaxial counter-rotating propeller unit, powered by gasoline for higher energy density, and a clutch for safe descent, combined with fixed-pitch propellers for maneuvering and orientation control, allowing vertical take-off and landing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If lithium polymer batteries are used for power, then the apparatus can operate electrically, but the flight time is limited due to small energy density
Solution Approach 1:
The patent changes the energy source from lithium polymer batteries to gasoline-powered internal combustion engine, fundamentally altering the energy density parameter. Gasoline has significantly higher energy density than lithium polymer batteries, enabling extended flight times while maintaining portable operation capability
Solution Approach 2:
The patent replaces the electrical power system (battery-motor) with a mechanical power system (internal combustion engine-propeller). This substitution enables access to higher energy density fuel sources and eliminates the flight time limitations of battery-powered systems
2Device complexity
If the same propellers are used for primary thrust and control in multi rotors, then the device structure is simplified, but the apparatus is unable to hover and has limited maneuverability
Solution Approach 1:
The patent divides the propulsion system into two distinct functional segments: a main propeller for primary thrust generation and multiple smaller control propellers for maneuverability and hovering. This segmentation allows each propeller type to be optimized for its specific function, enabling both simplified structure and superior operational capability
Solution Approach 2:
The patent creates a multi-functional propulsion system where the main propeller provides primary lift and thrust, while the control propellers provide both stabilization and maneuvering functions. This universal design allows the apparatus to perform hovering, precise positioning, and various flight maneuvers simultaneously
3Ease of operation
If cyclic pitch control is implemented on the main rotor, then maneuverability is improved, but the device complexity increases significantly
Solution Approach 1:
The patent extracts the complex cyclic pitch control mechanism from the main rotor system and replaces it with a simpler collective pitch control system. The complexity of differential blade pitch control is removed, while maneuverability is maintained through the control propellers that provide differential thrust for attitude control
4Reliability
If fixed-pitch propellers are used for control, then the system becomes simpler and more reliable, but the range of motion and adaptability is reduced
Solution Approach 1:
The patent uses fixed-pitch control propellers that generate counteracting forces to balance and control the aircraft's attitude. The differential rotation of these fixed-pitch propellers creates controlled unbalanced forces that enable precise maneuvering while maintaining system simplicity and reliability
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 longer flight times, safe transportation of heavier payloads, and reduces infrastructure requirements for take-off and landing.
Implementation Method 1
The propeller unit is used to provide a primary thrust to the apparatus
Implementation Method 2
The clutch disengages in case of failure of the engine to facilitate auto-rotation thereby enabling a safe descent
Implementation Method 3
The plurality of propellers is adapted to help in maneuvering and orientation control
Data Source
AI summary
A vertical take-off and landing aircraft includes a primary rotor unit having a rotor axis, an upper rotor system, and a lower rotor system. The upper rotor system includes an upper swashplate configured to translate along the rotor axis and not configured to tilt relative to the rotor axis and a pair of top blades configured to rotate about the rotor axis. Translation of the upper swashplate causes a pitch of each of the top blades to change equally. The lower rotor system includes a lower swashplate configured to translate along the rotor axis and not configured to tilt relative to the rotor axis and a pair of bottom blades configured to rotate about the rotor axis. Translation of the lower swashplate causes a pitch of each of the bottom blades to change equally. The aircraft further includes a plurality of secondary rotors each having fixed-pitch rotor blades.