RC Airplane Inertial Attitude Control via Sensor Fusion
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Solution Overview
Problem
Existing RC airplane training systems rely on optical/IR sensors and off-axis gyroscopes, which are ineffective in cloudy weather, near reflective surfaces, and indoors, as they lack inertial knowledge to estimate and control the airplane's attitude within a specific flight envelope.
Innovation Solution
The system uses an attitude sensor array comprising accelerometers and gyroscopes to estimate the RC airplane's inertial attitude, allowing for control and stabilization within predefined inertial flight envelopes, independent of weather conditions and reflective surfaces, with modes like 'panic', 'beginner', and 'intermediate' for safety and learning.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If optical/IR sensors are used to monitor airplane attitude, then the system can provide training assistance, but the sensors become ineffective in cloudy weather, near reflective surfaces, and indoors
Solution Approach 1:
The patent replaces optical/IR sensors with an inertial measurement unit (IMU) comprising accelerometers and gyroscopes. This substitution eliminates dependence on visual horizon detection, enabling reliable attitude estimation in all environmental conditions including cloudy weather, reflective surfaces, and indoor facilities.
Solution Approach 2:
The system changes the measurement parameters from optical horizon detection to inertial measurements. By using accelerometers to detect gravity vector and gyroscopes to measure angular velocity, the system achieves environment-independent attitude determination through fundamental physics parameters rather than optical references.
2Measurement precision
If off-axis gyroscopes are used for attitude control, then the system can maintain relative angular position, but the system lacks inertial knowledge to control absolute inertial attitude
Solution Approach 1:
The patent merges accelerometers and gyroscopes into a unified inertial measurement system. The accelerometers provide inertial reference through gravity vector detection, while gyroscopes measure angular velocity. Together they deliver both precise angular position measurement and absolute inertial attitude knowledge, eliminating the information loss of pure gyroscope systems.
Solution Approach 2:
The system implements feedback using inertial attitude estimates from the IMU to command the RC airplane to specific inertial attitudes and to maintain predefined inertial flight envelopes. This closed-loop feedback ensures both measurement precision and inertial knowledge are utilized for active control.
3Ease of operation
If relative angular positioning is used for training, then the system can provide basic guidance, but it cannot enforce inertial flight envelopes or command specific inertial attitudes
Solution Approach 1:
The system uses feedback from inertial attitude estimates to automatically enforce flight envelopes and command specific attitudes. The flight control processor continuously monitors inertial pitch, roll, and yaw against predefined envelope limits and automatically intervenes to maintain compliance, achieving high automation without sacrificing ease of operation.
Solution Approach 2:
The RC airplane system performs self-service by autonomously monitoring its own inertial attitude and automatically correcting deviations from safe flight envelopes. The pilot receives guidance while the system independently manages inertial envelope compliance, combining ease of operation with advanced automation.
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 reliable attitude control and stabilization of RC airplanes in various conditions, reducing the likelihood of crashes by autonomously maintaining the airplane within defined inertial flight envelopes, enhancing pilot safety and training efficiency.
Implementation Method 1
one or more accelerometers to measure inertial acceleration along each of the roll, pitch, and yaw axes of the RC airplane
Implementation Method 2
one or more gyroscopes configured to measure angular velocity about the pitch and roll axes of the RC airplane
Data Source
AI summary
The present disclosure describes flight training systems and methods for radio-controlled (RC) airplanes that rely on inertial attitude estimates. Preferred embodiments include an RC airplane with one or more control processors configured to (i) estimate an inertial attitude of the RC airplane based on one or more measurements from an attitude sensor array and (ii) control the inertial attitude of the RC airplane based the inertial attitude estimate. In operation, controlling the attitude of the RC airplane may include both controlling the RC airplane to a specific inertial attitude and/or keeping the inertial attitude of the RC airplane within a predefined flight envelope.