Aircraft Spoiler Control for Aerodynamic Optimization
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Solution Overview
Problem
Aircraft aerodynamic configurations are not optimally managed across different flight phases, requiring separate parameter optimizations for takeoff, approach, and stalled conditions, which can lead to suboptimal performance and increased noise.
Innovation Solution
An automatic process and device that monitor the flight phase and incidence to adjust spoiler deflection angles for optimizing aerodynamic parameters such as fineness, lift, and noise, ensuring optimal configuration in each phase without increasing pilot workload.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a fixed aerodynamic configuration is selected for takeoff optimization, then fineness is improved, but airlift performance deteriorates in approach phase
Solution Approach 1:
The patent applies dynamics by making the aerodynamic configuration adjustable during flight. The system automatically modifies the position of aerodynamic surfaces (flaps, spoilers, ailerons) based on the current flight phase detected by sensors, allowing the aircraft to transition from a takeoff-optimized configuration to an approach-optimized configuration, thereby resolving the contradiction between fineness and airlift performance across different flight conditions
Solution Approach 2:
The system changes aerodynamic parameters dynamically by adjusting the deflection angles of flaps, spoilers, and ailerons according to the flight phase. During takeoff, the configuration is set for maximum fineness, while during approach, the parameters are automatically modified to maximize airlift, thus resolving the contradiction through parameter adaptation
2Force
If spoiler deflection is increased to maximize airlift in near-stalled conditions, then airlift is improved, but noise increases in rated operation
Solution Approach 1:
The patent applies local quality by differentiating the optimization goal for spoilers based on the flight condition. In near-stalled conditions (high incidence), the system prioritizes airlift optimization by increasing spoiler deflection. In rated operation conditions, it prioritizes noise reduction by reducing spoiler deflection. This localized optimization approach resolves the contradiction between airlift and noise
Solution Approach 2:
The system dynamically changes the spoiler deflection parameter based on the detected flight phase and incidence angle. By automatically adjusting this parameter between different operational regimes, the system achieves maximum airlift when needed while minimizing noise during normal operation, thus resolving the contradiction
3Productivity
If separate parameter optimizations are performed for different flight phases, then each phase can be optimized, but device complexity increases
Solution Approach 1:
The patent applies universality by creating a single automated control system that handles multiple flight phases and optimizes multiple aerodynamic parameters simultaneously. The system uses a unified approach to detect flight phase, determine optimal configuration, and actuate multiple surfaces (flaps, spoilers, ailerons) based on pre-stored optimization data, thereby achieving comprehensive aerodynamic optimization without proportionally increasing system complexity
Solution Approach 2:
The system applies preliminary action by pre-storing optimal aerodynamic configurations for various flight phases and conditions. When a flight phase is detected, the system simply retrieves and implements the pre-calculated optimal configuration, avoiding the need for complex real-time calculations and reducing the operational complexity of the control system while maintaining high aerodynamic performance
Data Source
AI summary
A process and device for the automatic flight optimization of the aerodynamic configuration of an aircraft.The device (1) includes means (7, 8, 10) for determining and applying to the spoilers (6) of the aircraft commands for providing the aircraft with an optimum aerodynamic configuration.