Aircraft Weight Element for Center of Gravity Control
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Solution Overview
Problem
Conventional remote-controlled miniature aircraft with pendulum weight elements are bulky, difficult to transport, prone to damage, and require extensive training due to complex designs, limiting their application as reconnaissance drones.
Innovation Solution
A compact and robust design featuring a closed wing configuration with integrated upper and lower lift surfaces, propeller drives positioned above or below the lift surfaces, and a weight element that can be variably positioned to stabilize and control the aircraft, eliminating the need for a fuselage and tail boom, allowing for vertical take-off and landing capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a pendulum weight element is used to control the center of gravity, then the aircraft can achieve hovering state, but the aircraft becomes bulky and requires extended training period
Solution Approach 1:
The patent extracts the weight element from the traditional pendulum configuration underneath the aircraft and repositions it to the nose of the aircraft. This extraction and relocation eliminates the need for a tail boom and pendulum arrangement, achieving a compact flying wing design while maintaining center of gravity control capability for hovering state
Solution Approach 2:
Instead of placing the weight element at the rear (pendulum configuration), the patent inverts the arrangement by positioning the weight element at the nose of the aircraft. This inversion simplifies the overall structure by eliminating the tail boom while maintaining the ability to control center of gravity for stable flight and hovering
2Ease of operation
If a tail boom and pendulum arrangement are used, then the center of gravity can be controlled, but the aircraft becomes difficult to transport and prone to damage
Solution Approach 1:
The patent merges the functions of the tail boom, control surfaces, and weight element arrangement into a single integrated flying wing structure. The weight element is incorporated into the nose of the wing itself, eliminating separate components and reducing the aircraft to a compact, robust form that is resistant to damage during transport
3Stability of the object's composition
If conventional aircraft design with fuselage and tail unit is used, then stable flight can be achieved, but the aircraft construction becomes complex and larger
Solution Approach 1:
The patent makes the flying wing serve multiple functions simultaneously: it provides lift, houses the weight element, integrates control surfaces, and eliminates the need for separate fuselage and tail units. This multi-functionality achieves stable flight characteristics while minimizing structural complexity and size
Solution Approach 2:
The patent segments the control functions into separate control surfaces (elevons, rudders) that can be independently actuated, allowing stable flight control without requiring a complex fuselage and tail assembly. The weight element is also segmented as a separate adjustable component within the nose
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 results in improved flying characteristics, reduced risk of damage during transport and flight, and accelerated training for operation, enabling stable and efficient vertical take-off and landing with slow take-off speeds, making the aircraft suitable for reconnaissance missions.
Implementation Method 1
the upper lift surface and the lower lift surface are integrated into a single closed wing... the upper lift surface is arranged above a lower lift surface... to generate a lifting force for taking off and/or landing from a standstill
Implementation Method 2
at least one pair of propeller drives... to generate an air flow over the upper lift surface and/or the lower lift surface... vertical take-off and/or landing capabilities
Implementation Method 3
weight element, the position of which can be varied in the longitudinal direction of the aircraft in order to change the center of gravity of the aircraft
Data Source
AI summary
The invention pertains to a remote-controlled miniature aircraft with at least one lift surface (17), with at least one pair of propeller drives (12, 13) and with a weight element (20), the position of which can be varied in the longitudinal direction of the miniature aircraft (10) in order to change the center of gravity of the miniature aircraft (10). In order to realize a more compact construction with improved flying characteristics, the lift surface (17) of the miniature aircraft (10) is arranged above a plane defined by the rotational axes of the propeller drives (12, 13) in order to generate a lifting force for taking off and/or landing from a standstill.