Aircraft CG Management Using Repositionable Payload Rails
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Solution Overview
Problem
Conventional aircraft face challenges in managing their center of gravity (CG) due to varying payloads, which can affect stability and performance, especially in rotary-wing aircraft where small deviations in CG can significantly impact handling characteristics.
Innovation Solution
A weight distribution system with control logic that includes sensors and actuators to detect and correct CG imbalances by relocating payloads or hardware modules across the airframe, using a modular rail system and automated or manual repositioning mechanisms to maintain the CG within a calibrated range.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a payload of distinct shape, size, or weight is attached to an aircraft's airframe, then the aircraft can transport the payload to destinations, but the vehicle's center of gravity shifts and unwanted bending moments are introduced to the aircraft
Solution Approach 1:
The patent implements a dynamic weight distribution system where payloads and hardware modules can be repositioned along the airframe using motorized actuators and rail systems. This dynamic adjustment capability allows the aircraft to adapt its center of gravity position in real-time, resolving the contradiction between payload transport versatility and center of gravity stability by making the weight distribution configuration changeable rather than fixed
Solution Approach 2:
The aircraft system is divided into separable components including payloads, hardware modules, and repositionable subsystems that can be independently positioned along the airframe. This segmentation allows individual components to be moved to different locations to achieve desired center of gravity positions, enabling the aircraft to maintain stability while transporting various payload configurations
2Stability of the object's composition
If the center of gravity is adjusted by manually relocating payloads or hardware modules, then the center of gravity can be maintained within acceptable limits, but the operation becomes time-consuming and labor-intensive
Solution Approach 1:
The system incorporates sensors that automatically detect center of gravity position and control logic that autonomously determines required adjustments. The motorized actuators then self-execute the repositioning operations without human intervention, allowing the aircraft to self-correct its weight distribution and eliminating the time loss associated with manual CG adjustment operations
Solution Approach 2:
The patent implements a closed-loop feedback system where sensors continuously monitor the center of gravity position and provide data to the control logic. Based on this feedback, the system automatically activates actuators to reposition payloads or hardware modules, creating an automated control cycle that maintains center of gravity stability without requiring manual measurement or adjustment time
3Stability of the object's composition
If automated repositioning mechanisms are implemented to maintain center of gravity, then the adjustment process becomes faster and more precise, but the device complexity increases
Solution Approach 1:
The patent employs universal mounting rails and standardized hardware modules that can accommodate different payload types and configurations. The same actuator systems and control architecture serve multiple functions including payload repositioning, hardware module relocation, and center of gravity management, reducing overall system complexity through multi-functionality rather than requiring separate specialized systems for each function
Data Source
AI summary
Presented are weight distribution systems for aircraft center of gravity (CG) management, methods for making/operating such systems, and aircraft equipped with CG management systems. A method is presented for managing the CG of an aircraft. The aircraft includes first and second landing gears and an airframe that removably attaches thereto one or more payloads and/or hardware modules. The method includes supporting the aircraft on a support leg that operatively attaches to the airframe and, while supported on the support leg, determining if the aircraft pivots onto the first or second landing gear. If the aircraft pivots onto either landing gear, the method responsively identifies a new airframe position for the payload/hardware module that will shift the aircraft's CG to within a calibrated “acceptable” CG range; doing so should balance the aircraft on the support leg. The payload/hardware module is then relocated to the new airframe position.