Rotorcraft Load-Balancing Control for Stable Takeoff
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Solution Overview
Problem
Conventional rotorcraft attitude control methods using gyroscope sensors result in delayed control command signals and instability during takeoff, increasing the risk of falling.
Innovation Solution
A rotorcraft equipped with load sensors on its landing rods, which detect and balance loads to stabilize the fuselage before takeoff, allowing for automatic control of rotor outputs to maintain balanced loads and stabilize the aircraft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If attitude control is performed by detecting attitude using a gyroscope sensor, then the rotorcraft can maintain flight stability, but control command signals are delayed and takeoff stability deteriorates
Solution Approach 1:
The control device calculates target rotor outputs based on load sensor data before takeoff occurs, establishing preliminary control commands that are executed immediately when takeoff begins, eliminating the delay associated with attitude detection during the critical takeoff phase
2Device complexity
If conventional attitude detection methods are used, then the system structure remains simple, but takeoff stability deteriorates and falling risk increases
Solution Approach 1:
Load sensors are introduced as intermediary devices that measure forces on the landing gear, providing indirect information about rotor output balance and attitude that enables more reliable takeoff control without requiring complex direct attitude measurement systems
Data Source
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AI summary
According to one embodiment, a rotorcraft includes rotors (3), a fuselage (2), at least three rods (4), at least one load sensor (5) and a control device (6). The rotors (3) obtain lift. The fuselage (2) is coupled to the rotors (3). The at least three rods (4) support the fuselage (2). The at least one load sensor (5) detects loads (F1, F2, F3, F4) applied on the at least three rods (4). The control device (6) automatically controls the rotors (3) so that measured values of the loads (F1, F2, F3, F4) detected by the at least one load sensor (5) are brought to targeted values of the loads (F1, F2, F3, F4).