Deployable Wing Structure for Descent Control in Flying Objects
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Solution Overview
Problem
There is a demand for a flying object that can fly suitably, particularly in controlling its descent speed and stabilizing its attitude during vertical and horizontal flight modes.
Innovation Solution
A flying object design featuring a fuselage with laterally extending wings, including a fixed wing portion and a deployable wing portion that can be deployed forward, increasing the wing's planform area in the deployed state to enhance air resistance and stabilize the object's attitude.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the wing area is increased to control descent speed, then the descending speed can be suppressed, but the energy consumption during horizontal flight increases
Solution Approach 1:
The wing configuration is made dynamic through the deployable wing portion that can be extended or retracted. During descent, the deployable wing portion is extended to increase the planform area and air resistance, suppressing descending speed. During horizontal flight, the deployable wing portion is retracted to minimize wing area and reduce energy consumption, thereby resolving the contradiction between descent control and energy efficiency.
Solution Approach 2:
The wing is divided into a fixed wing portion and a deployable wing portion. The deployable wing portion can be independently controlled to extend forward or retract, allowing the wing area to be adjusted according to flight conditions. This segmentation enables optimal performance in different flight phases without compromising the other.
2Stability of the object's composition
If the wing area is increased to stabilize attitude during vertical descent, then the attitude can be stabilized, but the device complexity increases
Solution Approach 1:
The deployable wing portion provides dynamic adjustability of wing area to stabilize attitude during vertical descent when needed, while maintaining a compact configuration during horizontal flight to minimize complexity. The ability to change wing area on demand allows attitude stabilization without permanently increasing structural complexity.
Solution Approach 2:
The deployable wing portion serves multiple functions: it increases wing area for attitude stabilization during vertical descent, and can be retracted to reduce drag during horizontal flight. This multi-functionality allows a single structural element to address both stability requirements and complexity concerns across different flight phases.
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 design allows for controlled descent speed and stabilized flight by increasing air resistance during vertical descent and reducing energy consumption during horizontal flight, enhancing the flying object's overall performance.
Implementation Method 1
a wing (14) extending laterally from the fuselage (12) and configured to generate lift during cruising
Implementation Method 2
an area of a planform of the wing in a deployed state in which the deployable wing portion is deployed forward in the front-rear direction is larger than an area of the planform of the wing in a superposed state, allowing for controlled descent speed by increasing air resistance
Data Source
AI summary
A flying object includes: a fuselage; a wing that extends laterally from the fuselage and can generate lift during cruising; and a thrust generation unit that can generate thrust. The wing includes a fixed wing portion fixed to the fuselage, and a deployable wing portion deployable forward in a front-rear direction from the fixed wing portion, and a plane area of the wing in a deployed state in which the deployable wing portion is deployed forward in the front-rear direction is larger than a plane area of the wing in a superposed state in which the deployable wing portion is superposed on the fixed wing portion.