Rotorcraft Load-Sensor Attitude Control for Stable Takeoff
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Solution Overview
Problem
Conventional rotorcraft attitude control methods using gyroscope sensors result in delayed control responses and instability during takeoff, increasing the risk of falling.
Innovation Solution
A rotorcraft system equipped with at least three rods and load sensors that automatically control rotor outputs to balance loads detected by sensors, stabilizing the fuselage before takeoff by adjusting rotor pitch angles and rotation numbers.
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 the control response is delayed causing attitude instability during takeoff
Solution Approach 1:
The patent replaces the gyroscope sensor-based attitude detection system with a load sensor-based detection system. Instead of using mechanical gyroscopic sensors to detect attitude changes, the invention uses load sensors to detect load changes on rods, which directly indicate attitude changes. This substitution eliminates the delayed response characteristic of gyroscope-based systems and provides immediate detection of attitude changes, thereby resolving the technical contradiction between flight stability and control response time.
Solution Approach 2:
The patent introduces load sensors as an intermediary element between the rotorcraft's attitude state and the control system. The load sensors detect load changes on the rods, which serve as intermediate indicators of attitude changes. This intermediary detection method allows the control system to respond immediately to attitude changes without the delays inherent in gyroscope-based direct attitude measurement, thus improving control response time while maintaining flight stability.
2Device complexity
If conventional attitude control methods are used, then the system structure remains simple, but the rotorcraft experiences attitude instability and increased falling risk during takeoff
Solution Approach 1:
The patent replaces the conventional gyroscope sensor system with a load sensor system, maintaining relatively simple device structure while dramatically improving takeoff safety. The load sensors detect load changes on the rods that directly correlate with attitude changes, providing immediate and reliable detection without the complexity of gyroscope-based attitude measurement systems. This substitution achieves both simplicity and reliability, resolving the contradiction between device complexity and takeoff safety.
3Stability of the object's composition
If load sensors are used to detect load changes on rods, then takeoff stability is improved, but the device complexity increases due to additional sensors and control mechanisms
Solution Approach 1:
The patent implements a control system where the load sensors serve multiple functions: they detect load changes on the rods, provide immediate attitude change information, and enable automatic rotor output adjustment. The control device integrates these functions, using the same system for both detection and control purposes. This multi-functionality approach improves takeoff stability while minimizing the increase in device complexity by making the load sensor system perform multiple critical functions rather than requiring separate dedicated systems for each function.
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 approach enhances stability and safety during takeoff by ensuring balanced loads on the rotorcraft's rods, reducing the risk of instability and falling.
Implementation Method 1
The at least one load sensor detects loads applied on the at least three rods
Implementation Method 2
The rotors obtain lift
Data Source
AI summary
According to one implementation, a rotorcraft includes rotors, a fuselage, at least three rods, at least one load sensor and a control device. The rotors obtain lift. The fuselage is coupled to the rotors. The at least three rods support the fuselage. The at least one load sensor detects loads applied on the at least three rods. The control device automatically controls the rotors so that measured values of the loads detected by the at least one load sensor are brought to targeted values of the loads.