Tiltable Duct Aircraft Control for Stable Transition Flight
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Solution Overview
Problem
Flying objects with tiltable ducts face instability and reduced lift force during forward flight due to pitch moment and momentum drag, limiting their speed and maneuverability, especially when transitioning between rotary-wing and fixed-wing modes.
Innovation Solution
A flying object design incorporating a main body, a main wing, a first propulsion portion (tiltable duct) at the front, a second propulsion portion (propeller) at the rear, and a horizontal tail wing, controlled by a system that adjusts the tilt angle, pitch angle, and power of the second propulsion portion to maintain stability and generate sufficient lift force across flight modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If the duct length is reduced to decrease crosswind effect during vertical takeoff and landing, then the crosswind resistance is improved, but the lift force during forward flight decreases
Solution Approach 1:
The duct is made tiltable to dynamically adjust its orientation based on flight mode. During vertical takeoff and landing, the duct is positioned vertically to reduce crosswind effect. During forward flight, the duct is tilted to generate sufficient lift force, thus resolving the contradiction between crosswind resistance and lift generation
2Speed
If the flying object posture is tilted for high-speed forward flight, then the speed is improved, but the posture stability deteriorates due to pitch moment and momentum drag
Solution Approach 1:
A second propulsion portion is added at the rear of the main body to act as a counterweight. When the first propulsion portion is tilted for forward flight, the second propulsion portion generates opposing thrust to balance the pitch moment and momentum drag, maintaining posture stability while enabling high-speed flight
3Speed
If a tiltable duct is provided for high-speed flight capability, then the speed range is improved, but the device complexity increases
Solution Approach 1:
The tiltable duct and the second propulsion portion are integrated into a coordinated control system. The controller synchronizes the tilt angle of the first propulsion portion with the thrust of the second propulsion portion, allowing the system to achieve high-speed flight capability while managing structural complexity through unified control
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
The system effectively offsets moments generated during tilting of the first propulsion portion, enabling stable posture control and sufficient lift force generation without air disturbance, allowing for efficient transition between rotary-wing and fixed-wing flight modes.
Implementation Method 1
By applying a duct to a propeller of a flying object capable of vertically taking off and landing, a thrust force may increase by an effect of the duct
Implementation Method 2
when a sufficient force is not generated to overcome a pitch moment and a momentum drag that are generated by the shape of the duct
Implementation Method 3
when a sufficient force is not generated to overcome a pitch moment and a momentum drag that are generated by the shape of the duct
Implementation Method 4
In the case of a flying object with a tiltable duct, a lift force generated in the duct during a forward flight may decrease
Data Source
AI summary
The flying object according to one embodiment comprises: a main body; a main wing formed on a side surface of the main body; a duct-shaped first propulsion part which is provided outside the main wing and can be tilted; a second propulsion part arranged behind the main body; horizontal tail wings formed on both side surfaces of the second propulsion part; and a control part for controlling the movement of the first propulsion part, second propulsion part, and horizontal tail wings, wherein the control part controls the second propulsion part and the horizontal tail wings according to the tilt angle of the first propulsion part.