Compound Aircraft Trim Prediction for Pitch and Thrust Control
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Solution Overview
Problem
Conventional rotorcraft and high-speed Vertical Take-Off and Landing (VTOL) aircraft require significant pilot skill and workload due to complex control inputs, leading to increased training demands and potential pilot errors.
Innovation Solution
The implementation of pitch attitude trim prediction and propulsor trim prediction circuitry, which generates predicted trim values based on aircraft velocity and pitch attitude, allowing for automatic adjustments of flight control effectors to reduce pilot input and optimize flight operations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If conventional control systems are used with multiple control inputs, then the aircraft can achieve precise control of flight states, but the pilot workload and training requirements increase significantly
Solution Approach 1:
The control system automatically determines trim solutions and adjusts control effectors without requiring continuous pilot input. The system monitors flight parameters and self-adjusts to maintain optimal trim conditions, reducing pilot workload while preserving control precision through automated trim management.
Solution Approach 2:
The system continuously monitors flight parameters including airspeed, vertical speed, and control effector positions. Based on this feedback, the control system dynamically selects appropriate trim solutions and adjusts control surfaces to maintain precise flight state control while minimizing required pilot intervention.
2Adaptability or versatility
If multiple trim solutions are provided for specific states, then the aircraft can optimize for different mission requirements (fuel burn, noise, agility), but the control system complexity increases
Solution Approach 1:
The control system dynamically selects among multiple trim solutions based on current flight conditions and mission requirements. Rather than providing fixed trim settings, the system adapts its trim strategy in real-time, switching between different control effector combinations to optimize for fuel efficiency, noise reduction, or agility as needed.
Solution Approach 2:
The system pre-calculates multiple trim solutions for various flight states and mission requirements. By having these solutions prepared in advance, the system can quickly switch between optimization goals without requiring complex real-time calculations, thereby managing system complexity while maintaining versatility.
3Ease of operation
If automatic trim control is implemented, then pilot workload is reduced, but the extent of automation increases system complexity
Solution Approach 1:
The automatic trim control system is segmented into distinct functional modules: a trim solution determination module that selects appropriate trim strategies, a control effector adjustment module that implements the trim changes, and a monitoring module that verifies flight state maintenance. This segmentation manages automation complexity by creating discrete, manageable components rather than a monolithic system.
Data Source
Figure 1
Figure 2A~2D
Figure 3A~3D
AI summary
A control circuitry (130) includes a propulsor trim prediction circuitry (404) configured to generate a predicted propulsor collective blade pitch trim value (444, 562) for a target state of an aircraft (100) based on an aircraft velocity (422) and a pitch attitude deviation from a reference (550, 622). The control circuitry (130) further includes an output circuitry (516, 518) configured to output a propulsor collective blade pitch angle command (452, 564) based on the predicted propulsor collective blade pitch trim value (444, 562). The propulsor collective blade pitch angle command (452, 564) is configured to cause an adjustment in a blade pitch angle of a propulsor (112, 114) of the aircraft (100). Additionally or alternatively, the control circuitry (130) includes a pitch attitude trim prediction circuitry (402) configured to generate a predicted pitch attitude trim value (442). The output circuitry (516, 518) is configured to output an aircraft pitch attitude trim command (550), configured to cause an adjustment in a pitch angle of the aircraft (100), based on the predicted pitch attitude trim value (442).