Rotary Wing Control Flap Algorithm for Weight Reduction
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Solution Overview
Problem
Existing rotary wing aircraft control methods require separate mechanisms for primary and secondary control, leading to weight inefficiencies and limited maneuverability, with no method for solely using control flaps for overall control and periodic rotor blade integrity checking.
Innovation Solution
Implementing an algorithm that computes a resulting flap angle by superimposing flap control and correction angles to manage both primary and secondary control requirements through control flaps, with periodic torsional excitation for rotor blade integrity checks and secondary regulators to mitigate blade flutter and dynamic loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If separate mechanisms are used for primary and secondary control, then control functionality is achieved, but weight increases and maneuverability is limited
Solution Approach 1:
The patent merges primary and secondary control functions into a single control flap system. The control flap integrates both pilot primary control inputs and secondary control requirements, eliminating the need for separate control mechanisms. This integration reduces weight while maintaining full control functionality and improving maneuverability through unified control architecture.
Solution Approach 2:
The control flap is designed to perform multiple functions simultaneously - it handles both primary control (pilot inputs for ascending/descending flight and horizontal maneuvering) and secondary control (flight-physical behavior optimization). This multi-functionality allows a single component to replace what would traditionally require separate mechanisms, reducing overall system weight.
2Weight of moving object
If control flaps are used for both primary and secondary control, then weight is reduced and efficiency is improved, but control complexity increases
Solution Approach 1:
The patent replaces complex mechanical superposition systems with an algorithmic approach. Instead of relying on mechanical torsional stiffness to superimpose blade pitch angles, the system uses computational algorithms to calculate and execute the appropriate control inputs. This substitution reduces mechanical complexity while maintaining precise control over the control flap's deflection angles.
Solution Approach 2:
The system dynamically adjusts control parameters (flap deflection angles) based on real-time flight conditions and control requirements. By continuously optimizing the flap control angle and flap correction angle parameters, the system achieves efficient control with reduced weight, managing complexity through adaptive parameter adjustment rather than fixed mechanical configurations.
3Reliability
If rotor blade integrity checking is implemented, then safety is improved, but system complexity increases
Solution Approach 1:
The patent employs torsional excitation of the rotor blade to assess its integrity. By applying controlled vibrational loads and analyzing the blade's response characteristics, the system can detect changes in structural properties without requiring complex inspection equipment. This vibration-based approach provides reliable integrity checking while keeping the system relatively simple.
Solution Approach 2:
The system incorporates feedback mechanisms to monitor rotor blade integrity over time. By continuously measuring blade response to torsional excitation and comparing it against baseline characteristics, the system can detect degradation or damage. This feedback approach enables proactive safety monitoring with minimal added complexity, as it utilizes existing control systems and sensors.
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
This approach significantly reduces weight, enhances efficiency and maneuverability, allows for periodic rotor blade integrity checks, and improves flight-physical properties by using control flaps for both primary and secondary control, while also reducing fuel consumption and blade flutter.
Implementation Method 1
By deflecting the control flap in combination with the rotor blade that is supported in a partially torsionally soft or pivotable manner, the blade pitch angle can be adjusted
Implementation Method 2
The control flap sits on the rear edge of the rotor blade. By deflecting the control flap in combination with the rotor blade, the blade pitch angle can be adjusted
Implementation Method 3
The rotor blades are connected to the rotor head such that each rotor blade is supported to be able to pivot or twist along the lengthwise axis of its blade on the rotor head
Data Source
AI summary
The invention relates to a method for controlling a rotary wing aircraft with at least one main rotor, comprising a rotor head and rotor blades (12), arranged such that each rotor blade (12) is supported to be able to pivot or twist around the lengthwise axis of its blade on the rotor head and has at least one control flap (14) that can be deflected. According to the invention, the rotary wing aircraft is controlled solely by changing the respective blade pitch angle (X) by means of changing the flap control angle (Y) of the assigned control flaps (14) by the resulting blade pitch angle (X3) being set by applying the resulting flap angle (Y4) to the control flap (14), and the flap angle (Y4) being computed using an algorithm, the input quantities comprising the flap control angle (Y1) depending on the pilot primary control and the flap correction angle (Y2) depending on the secondary control.