Adjustable Load Element for VTOL Aircraft Center of Gravity
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Fixed-wing aircraft with vertical take-off capability face complexity in transitioning between vertical take-off/landing and horizontal flight due to challenges in managing the center of gravity, which limits their flexibility and suitability for various flight situations.
Innovation Solution
A vertical take-off fixed-wing aircraft design that includes a load element coupled to the fuselage, an actuator device to vary the load element's position, and a control device to adjust the load element's position from a first position on the tail during vertical operations to a second position during horizontal flight, facilitating smooth transitions and adapting to different flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the aircraft uses a fixed center of gravity position, then the structure is simple, but the transition between vertical take-off and horizontal flight becomes complex and difficult to control
Solution Approach 1:
The patent applies the dynamics principle by making the center of gravity position adjustable rather than fixed. The load element can be moved along the fuselage to different positions (first position for vertical take-off, second position for horizontal flight) to dynamically adapt the aircraft's weight distribution to the current flight phase, thereby simplifying transition control while managing system complexity through a controlled adjustment mechanism.
2Stability of the object's composition
If the load element is positioned for vertical take-off, then vertical operation stability is improved, but horizontal flight performance deteriorates
Solution Approach 1:
The patent implements dynamics by enabling the load element to change position between vertical take-off and horizontal flight modes. During vertical take-off, the load element is positioned at the first position to optimize stability; during horizontal flight, it moves to the second position to optimize flight performance and speed, thus resolving the contradiction between vertical stability and horizontal performance.
3Speed
If the load element is positioned for horizontal flight, then horizontal flight performance is improved, but vertical take-off stability deteriorates
Solution Approach 1:
The patent applies the dynamics principle by making the center of gravity adjustable. For horizontal flight, the load element is positioned at the second position to maximize speed and performance; for vertical landing, it moves to the first position to ensure stability. This dynamic repositioning resolves the contradiction between horizontal speed and vertical landing stability.
4Ease of manufacture
If the aircraft structure is simplified without center of gravity adjustment, then manufacturing is easier, but adaptability to different flight situations deteriorates
Solution Approach 1:
The patent implements dynamics by introducing an adjustable load element that can be repositioned along the fuselage. This allows a relatively simple base structure to gain adaptability for different flight modes (vertical take-off, horizontal flight, vertical landing) through controlled movement of the load element, thus improving flight mode adaptability while maintaining ease of manufacture.
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 design enhances flight stability and flexibility by optimizing the center of gravity positioning, allowing the aircraft to operate effectively in various flight modes and selecting suitable take-off and landing sites, thereby improving overall flight characteristics.
Implementation Method 1
an actuator device, by means of which a position of the load element can be varied in relation to a fuselage of the fixed-wing aircraft... to displace a centre of gravity of the fixed-wing aircraft by means of the load element
Data Source
Figure 1
Figure 2~3
Figure 4a~4g
AI summary
A fixed-wing aircraft (110) comprises a load element (112), which is coupled to a fuselage (111) of the fixed-wing aircraft (110); and an actuator device (120), by means of which a position (71, 72) of the load element (112) can be varied in relation to the fuselage (111) during a flight of the fixed-wing aircraft (110) in order to displace a centre of gravity of the fixed-wing aircraft (110) by means of the load element (112).