Pivoting Load Pole With Retractable Cable for Tailsitter Stability
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Solution Overview
Problem
Existing external load management systems for tailsitter aircraft do not effectively harmonize the cargo's center of gravity with the aircraft's center of gravity during transitions between hover and flight modes, leading to instability and safety risks.
Innovation Solution
A load management system featuring a retractable cable and pole configuration that adjusts the attachment point of external loads relative to the aircraft's center of gravity, deploying during transitions to maintain stability in both hover and flight modes, controlled by a processing circuitry-based controller.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a fixed external load carrying system is used for tailsitter aircraft, then the system is simple in structure, but the aircraft becomes unstable during transitions between hover and flight modes due to improper center of gravity alignment
Solution Approach 1:
The patent applies the dynamics principle by implementing a retractable cable that can change its length dynamically during flight mode transitions. The cable transitions from a retracted state during hover to an extended state during forward flight, allowing the external load's center of gravity to be repositioned relative to the aircraft's center of gravity. This dynamic adjustment resolves the stability issue during mode transitions while maintaining a relatively simple overall system structure.
2Reliability
If the retractable cable is deployed during hover mode, then the cargo's center of gravity can be adjusted, but the aircraft experiences unnecessary drag and increased energy consumption
Solution Approach 1:
The system dynamically adjusts the cable length based on flight mode. During hover, the cable remains retracted to minimize drag and energy consumption. During forward flight transition, the cable deploys to achieve proper center of gravity alignment. This dynamic behavior ensures optimal energy efficiency in each flight phase while maintaining the necessary center of gravity control capability.
Solution Approach 2:
The patent changes the physical parameter of cable length based on operational requirements. By transitioning the cable from a retracted configuration during hover to an extended configuration during forward flight, the system optimizes both energy efficiency and center of gravity alignment for each specific flight phase.
3Reliability
If the cable is deployed during transition to forward flight, then the load's center of gravity harmonizes with the aircraft's center of gravity, but the system requires additional control mechanisms
Solution Approach 1:
The patent incorporates feedback control mechanisms that monitor the aircraft's flight mode and automatically trigger cable deployment or retraction. The controller receives input about the current flight phase (hover, transition, or forward flight) and autonomously adjusts the cable length accordingly, harmonizing the load's center of gravity with the aircraft's center of gravity without requiring complex manual control systems.
Data Source
AI summary
Load management system and methods are described for aircraft, including tailsitters. A load management system can comprise a pole coupled the fuselage and free to rotate and swing. The pole can comprise a cargo hook and a distal end that can be releasably coupled to a cargo cable or cargo. The pole can be coupled near its distal end to a retractable cable that is deployed from a position aft of the pole. During landing, takeoff, and when otherwise in hover mode, the retractable cable can be retracted—holding the pole along or near the fuselage. During transition to, or during, flight mode, the retractable cable can be deployed which can harmonize the cargo's center of gravity with the needs of the tailsitter aircraft.