Helicopter Phase Control Unit Yaw Rotation Correction
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Remote control helicopters lack self-stability when rotated about the yaw axis, leading to phase deviations in roll and pitch operations, causing deviations from the operator's intended control, especially during pirouette maneuvers.
Innovation Solution
A driving controller with a yaw axis angular velocity detecting unit, main rotor RPM detecting unit, and phase control unit that generates corrected roll and pitch control signals to align with the intended operations by calculating phase deviations based on yaw axis angular velocity and main rotor RPM signals, ensuring accurate roll and pitch control even during yaw axis rotation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the remote control helicopter is rotated about the yaw axis at high speed (pirouette maneuver), then the aerial acrobatics performance is improved, but phase deviations occur in roll and pitch operations causing control inaccuracy
Solution Approach 1:
The system performs preliminary calculation of the phase deviation angle based on yaw angular velocity and main rotor RPM before the actual roll/pitch control action. This pre-calculated phase information is then used to correct the control signals, ensuring accurate control even during high-speed pirouette maneuvers.
Solution Approach 2:
The system continuously monitors yaw angular velocity and main rotor RPM, calculates the resulting phase deviation, and feeds this information back to correct the roll and pitch control signals in real-time, maintaining control precision during dynamic yaw rotations.
2Adaptability or versatility
If the main rotor rotational speed varies, then the helicopter can adapt to different flight conditions, but the phase deviation in roll and pitch control increases
Solution Approach 1:
The system dynamically adjusts the phase correction based on the actual main rotor RPM. Since the phase deviation angle depends on both yaw angular velocity and main rotor speed, the system continuously updates the correction amount as rotor speed changes, maintaining control precision across varying flight conditions.
Solution Approach 2:
The system changes the control parameter (phase correction amount) based on the main rotor RPM parameter. By calculating the phase deviation as a function of both yaw rate and rotor speed, the system adapts the control signals to match the current operational state, preserving accuracy despite speed variations.
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
Enables precise and stable control of remote control helicopters by correcting phase deviations, ensuring roll and pitch operations align with the operator's intentions, even during high-speed yaw axis rotations, thereby maintaining intended flight directions.
Implementation Method 1
since the model helicopter has no self-control stability of a yaw axis, a gyrocompass device is indispensable to stabilization of driving control of the model helicopter
Implementation Method 2
A difference between the pitch angles of the two rotor blades causes a change in a lift force applied to the model helicopter. Such a lift force change is generated when a phase is retarded by 90 degrees due to a Coriolis force produced by the rotation of the main rotors
Data Source
AI summary
A driving controller of remote control equipment includes a yaw axis angular velocity detecting unit for outputting a yaw axis angular velocity as a yaw axis angular velocity signal; a main rotor RPM detecting unit for outputting a main rotor RPM as a main rotor RPM signal; and a phase control unit for detecting a phase deviation in a roll axis and a pitch axis based on the yaw axis angular velocity signal and the main rotor RPM signal, and generating a roll and a pitch control signal by correcting a roll and a pitch operation signal by the phase deviation. The driving controller further includes an actuator control unit for generating a roll and a pitch actuator driving signal respectively based on the roll and the pitch control signal, and outputting the generated roll and pitch actuator driving signals to a roll and a pitch control actuator, respectively.