Articulatable Tail Section for Aircraft Flight Mode Transition
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Solution Overview
Problem
Current aircraft designs face limitations in efficiently transitioning between rotor-borne and wing-borne flight modes, requiring separate control systems and flight surfaces, which complicates construction and control.
Innovation Solution
An aircraft with an articulatable tail section that includes a propulsion system and stabilizers, capable of rotating about two perpendicular axes, allowing for simultaneous pitch and yaw control in both flight modes using a single actuation system, thereby simplifying design and operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate control systems and flight surfaces are used for rotor-borne and wing-borne flight modes, then each flight mode can be optimized independently, but the overall device complexity increases
Solution Approach 1:
The patent implements a universal control system where the stabilizer serves dual functions: controlling pitch during rotor-borne flight and providing aerodynamic stability during wing-borne flight. The actuation system articulates the stabilizer about two perpendicular rotational axes, enabling it to perform multiple control functions across different flight modes without requiring separate control systems, thus reducing overall device complexity while maintaining flight mode optimization
Solution Approach 2:
The patent merges the control functions for rotor-borne and wing-borne flight modes into a single integrated control system. The actuation system combines multiple articulation axes and control surfaces (including the stabilizer and its components) into one coordinated mechanism that manages both flight modes, eliminating the need for separate control systems and reducing overall complexity
2Reliability
If multiple separate control systems are implemented for different flight modes, then each system can be specialized, but the ease of operation deteriorates due to increased control complexity
Solution Approach 1:
The actuation system is designed as a universal control mechanism that handles both rotor-borne and wing-borne flight modes through a single coordinated interface. The system articulates the stabilizer about two perpendicular rotational axes, allowing one control system to perform multiple specialized functions without requiring the operator to manage separate control systems, thereby improving ease of operation while maintaining control precision
Solution Approach 2:
The control system dynamically adapts its behavior based on the flight mode. The actuation system can articulate the stabilizer about different rotational axes depending on whether the aircraft is in rotor-borne or wing-borne mode, providing mode-appropriate control characteristics through a single dynamic system rather than requiring static separate control systems
Data Source
AI summary
An aircraft may include a body structure and a propulsion system coupled to the body structure and including a mounting shaft and a rotor. The rotor may include a rotor hub and a set of rotor blades, wherein the rotor is configured to orient the set of rotor blades at a first collective blade angle during a first flight mode and orient the set of rotor blades at a second collective blade angle during a second flight mode. The propulsion system may further include a motor coupled to the rotor and configured to rotate the rotor in a first rotational direction in the first flight mode to produce thrust in a first thrust direction and rotate the rotor in a second rotational direction opposite the first rotational direction in the second flight mode to produce thrust in a second thrust direction opposite the first thrust direction.