Dual-Section Control Yoke for Aircraft Parachute and Chassis Coordination
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Solution Overview
Problem
Conventional control systems for paramotors and three-axis controlled aircraft require pilots to manage both the parachute and chassis during take-off and landing, creating a challenge in coordinating simultaneous control of the parachute and chassis, especially with the need to steer the front wheels and control lines.
Innovation Solution
A control device with two separately movable and rotatable control horn sections that can be used to control aircraft surfaces and wheels, allowing pilots to control the parachute and chassis independently through translational and rotational movements, replacing the need for foot pedals and conventional control lines.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If conventional control systems with separate control lines and steering wheel are used, then the parachute and chassis can be controlled, but the pilot cannot simultaneously and independently control both the parachute and chassis during take-off and landing
Solution Approach 1:
The control yoke is divided into two independently movable control yoke sections, each capable of translational and rotational movement. This segmentation allows the pilot to control different functions (parachute and chassis) with separate control inputs, resolving the contradiction between ease of operation and device complexity by providing independent control channels within a unified structure.
Solution Approach 2:
Each control yoke section is designed to perform multiple control functions through different movement types (translational movement for one function, rotational movement for another function). This multi-functionality allows a single control device to manage both parachute and chassis control, improving operational ease while maintaining manageable system complexity.
2Ease of operation
If conventional control lines are used for parachute control, then the parachute can be controlled, but the pilot must also steer the front wheels with a separate steering wheel, creating coordination difficulty
Solution Approach 1:
The control system merges the functions of separate control lines and steering wheel into a unified control yoke structure with two control sections. Both control functions (parachute and chassis) are integrated into one device, reducing the number of separate control devices while enabling simultaneous control operation.
Solution Approach 2:
The control yoke sections are designed with dynamic movement capabilities, allowing translational and rotational movements to be detected and converted into corresponding control surface and wheel movements. This dynamic design enables flexible control of multiple functions from a single control device.
3Ease of operation
If traditional foot pedals are used for rudder control, then the rudder can be controlled, but pilots with limited mobility experience difficulty
Solution Approach 1:
The control system replaces the mechanical foot pedal system with a control yoke section that can be operated by hand movements. This substitution allows pilots with limited leg or foot mobility to control the rudder and other aircraft functions through hand-based translational and rotational movements of the control yoke sections.
Data Source
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AI summary
The invention describes a device for controlling an aircraft with a control yoke (1) comprising a first (1A) and a second (1B) control yoke section. The two control yoke sections are each connected to a control device (2) for controlling the aircraft, wherein the first and second control yoke sections are translationally movable separately and rotationally movable in the same direction and are provided for controlling the aircraft.