Tilt-Rotor Drone Steering Without Cyclic-Pitch Control
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Solution Overview
Problem
Current drones with adaptable wing structures face limitations in maneuverability during rotary-wing flight configurations, requiring complex cyclic-pitch control mechanisms for horizontal steering.
Innovation Solution
The drone features a rotor with an axis of rotation that can be oriented relative to the front section, utilizing actuators and a stator connected to the front section to steer without complex cyclic-pitch control, along with a propeller-driven drivetrain and epicyclic gearbox for efficient power transmission, allowing for both fixed-wing and rotary-wing configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If complex cyclic-pitch control is used at the connection between wings and rotor, then horizontal steering in rotary-wing configuration is achieved, but device complexity increases
Solution Approach 1:
Instead of controlling wing pitch to achieve horizontal steering (conventional approach), the patent inverts the approach by orienting the rotor axis itself to control horizontal movement. The rotor axis can be tilted relative to the fuselage, and this tilt direction controls the horizontal steering in rotary-wing configuration, eliminating the need for complex cyclic-pitch control mechanisms.
Solution Approach 2:
The patent introduces a dynamic orientation mechanism for the rotor axis that can tilt and rotate relative to the fuselage. This dynamic adjustment of the rotor axis orientation enables horizontal steering capability without requiring complex pitch control systems, as the steering is achieved through the movement of the rotor axis itself rather than through cyclic pitch variations.
2Volume of moving object
If folding wings are used for compact storage in launcher, then ease of storage is improved, but structural complexity increases
Solution Approach 1:
The patent divides the wing structure into multiple segments that can fold relative to each other and to the fuselage. Each wing is divided into sections connected by folding joints, allowing the wings to be collapsed into a compact configuration for storage in the launcher while maintaining the ability to deploy to full span for flight operations.
Solution Approach 2:
The wing structure incorporates dynamic folding mechanisms that allow the wings to transition between extended and folded configurations. These mechanisms include articulated joints and locking systems that enable the wings to be folded against the fuselage for compact storage while maintaining structural integrity during both storage and flight phases.
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 horizontal steering in rotary-wing configuration without complex cyclic-pitch control, improving maneuverability and efficiency by using actuators to orient the rotor and adjust wing incidence, while maintaining aerodynamic performance and stability across flight modes.
Implementation Method 1
the stator may be connected by at least one actuator to the front section, the actuator being designed to modify the orientation of the stator relative to the front section when actuated
Implementation Method 2
a drivetrain connecting the motor to the propeller, this drivetrain comprising a universal joint allowing drive to be transmitted from the motor to the propeller despite the changes in orientation of the axis of rotation of the rotor relative to the front section
Implementation Method 3
The rotor may be driven via an epicyclic reduction gearbox
Implementation Method 4
A deflector advantageously covers this joint, so as to maintain continuity of the fuselage at the transition between the front section and the stator, in spite of the changes in orientation of the latter
Data Source
AI summary
A drone including a front section, a wing structure supported by a rotor located behind the front section, and a propeller at the rear. The wing structure including two wings rotating the rotor, the wing structure being able to move between a flight configuration, in which the rotor is immobile relative to the front section and the propulsion provided by the propeller, and a flight configuration with the wing structure rotating, in which the rotor is rotated relative to the front section, the rotor being connected to the front section with a possibility of orienting its axis of rotation relative thereto in order able to direct the drone in the rotary wing structure configuration by acting on said orientation.