Aircraft Flight Control Deflector Panels Torque Reduction
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Solution Overview
Problem
Existing anti-torque and yaw control systems in aircraft, such as tail rotors and multi-bladed ducted fans, pose safety risks and are energy-inefficient, while conventional flight control mechanisms for fixed-wing aircraft require substantial engine power.
Innovation Solution
A flight control system utilizing moveable deflector panels on an airfoil that pivot to create asymmetrical profiles, altering airflow to generate lift and counteract torque, with mechanisms for controlled rotation and airflow management to enhance efficiency and safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If tail rotors are used for anti-torque and yaw control, then yaw control is provided, but safety risks increase due to exposed spinning blades
Solution Approach 1:
The patent introduces an intermediary mechanism (duct or shroud) that encloses the spinning blades of the tail rotor, allowing the blades to remain enclosed while still generating the necessary anti-torque effect. This intermediary structure protects ground personnel and prevents contact with stationary objects while maintaining the functional effectiveness of the tail rotor.
Solution Approach 2:
The patent employs a simple, lightweight duct or shroud structure that can be easily manufactured and installed. This protective enclosure is a relatively simple addition that significantly improves safety without adding substantial complexity or cost to the aircraft system.
2Reliability
If multi-bladed ducted fans are used for anti-torque control, then safety is improved by enclosing blades, but device complexity increases
Solution Approach 1:
The patent designs the tail rotor assembly so that the duct or shroud serves multiple functions: it encloses the blades for safety, maintains aerodynamic efficiency, and can be integrated with the existing tail rotor structure. This multi-functional design reduces overall system complexity despite the addition of the protective enclosure.
3Reliability
If multi-bladed variable pitch fans are placed in forward section of tail boom, then safety is improved by inaccessibility, but engine power consumption increases substantially
Solution Approach 1:
The patent utilizes the existing aerodynamic environment around the tail rotor to generate anti-torque control. The system leverages the natural airflow and aerodynamic forces already present in the helicopter's operating environment, rather than requiring additional powered fans that would consume engine power. The tail rotor itself serves the dual purpose of providing anti-torque and can be positioned to utilize beneficial aerodynamic effects.
4Use of energy by moving object
If supplemental strake systems are added to reduce engine power requirements, then energy efficiency is improved, but device complexity increases
Solution Approach 1:
The patent introduces strakes or supplemental aerodynamic surfaces at specific locations on the tail rotor assembly where they can most effectively reduce the power requirements. These localized aerodynamic modifications are placed strategically to optimize their effect on reducing engine power consumption while adding minimal complexity to the overall system.
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
Provides safe, energy-efficient anti-torque and yaw control for rotary-wing aircraft and flight control for fixed-wing aircraft, reducing engine power requirements and minimizing safety hazards.
Implementation Method 1
altering airflow to generate lift
Implementation Method 2
generate lift and counteract torque
Data Source
Figure 1
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AI summary
A system for providing a simple, safe and inexpensive mechanism to provide flight control in an aircraft. In one embodiment, an anti-torque system (20) for a rotary-wing aircraft has an airfoil (22) with a first surface (24) extending from a first trailing edge (28) and a leading edge (30), and a second surface (26) extending from a second trailing edge (32) to join the first surface (24) at the leading edge (30). The airfoil (22) has a first moveable deflector panel (34) pivotally coupled to the first trailing edge (28), and a second moveable deflector panel (36) pivotally coupled to the second trailing edge (32). Means are provided to pivot the deflector panels (34), (36) in unison about their respective pivot axes (35), (37) to alter the direction of travel of the airflow downstream of the pivot axes (35), (37) over the surfaces of the deflector panels (34), (36), thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. In another embodiment, the flight control system (10) is arranged within a fixed-wing aircraft.