Aircraft Edge Device Deflection for Emergency Descent
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Solution Overview
Problem
Conventional aircraft control systems are inadequate for achieving the required descent rate during emergency situations, such as rapid cabin decompression, as they often necessitate increased spoiler surface area or deflection, leading to sub-optimal wing configuration and potential aerodynamic/structural buffet.
Innovation Solution
An emergency descent system incorporating a flight control computer, edge control system, and speedbrake control device that automatically adjusts leading and trailing edge devices to maximize drag, allowing for increased descent rates without excessive weight or structural stress, by computing and implementing specific deflection angles for these devices in response to cabin pressure loss indications.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If spoiler surface area or deflection is increased to achieve required descent rate, then descent rate is improved, but wing configuration becomes sub-optimal and aerodynamic/structural buffet occurs
Solution Approach 1:
The patent implements dynamic adjustment of leading edge and trailing edge device deflection angles based on real-time aircraft state (altitude, speed, angle of attack). The flight control computer continuously computes optimal deflection angles that maximize drag while maintaining stable wing configuration, replacing the static spoiler-only approach with a dynamic, multi-device control system that adapts to changing flight conditions.
Solution Approach 2:
The system changes the deflection angle parameters of leading edge and trailing edge devices according to computed optimal values. By adjusting these angular parameters dynamically rather than using fixed spoiler deflections, the system achieves maximum drag for emergency descent while maintaining aerodynamic stability and avoiding buffet conditions.
2Speed
If conventional control systems are used during emergency descent, then system complexity is minimized, but descent rate requirement cannot be met
Solution Approach 1:
The patent makes existing leading edge and trailing edge devices serve a dual function: their primary function for normal flight control and their secondary function for emergency descent by computing and implementing specific deflection angles that maximize drag. This multi-functionality allows the system to meet descent rate requirements without adding dedicated emergency descent hardware, thus limiting complexity increase.
Solution Approach 2:
The flight control computer automatically computes optimal deflection angles and commands the edge control system to adjust leading edge and trailing edge devices during emergency descent. This automated self-service control eliminates the need for manual pilot intervention and complex mechanical linkages, achieving high descent rates through intelligent software control of existing actuators.
3Speed
If leading edge and trailing edge devices are automatically adjusted to maximize drag, then descent rate is improved, but control system complexity increases
Solution Approach 1:
The flight control computer receives real-time feedback on aircraft state (altitude, speed, angle of attack) and continuously computes optimal deflection angles for leading edge and trailing edge devices. This closed-loop feedback control ensures the devices are positioned to maximize drag at each moment during emergency descent, achieving high descent rates through intelligent, adaptive control rather than simple mechanical systems.
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
The system effectively increases the aircraft's descent rate during emergency situations while maintaining optimal wing configuration, reducing the risk of buffet and improving safety by minimizing lift-to-drag ratio, thus meeting regulatory requirements.
Implementation Method 1
The flight control computer may be configured to compute a first setting for a leading edge device and/or a trailing edge device of an aircraft wing... automatically command the leading edge device, the trailing edge device, or both, to a deflection angle corresponding to the first setting... to maximize drag
Data Source
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AI summary
A system (300) for increasing the descent rate of an aircraft may include a flight control computer(450), an edge control system (460), and a speedbrake control device (532). The flight control computer may be configured to compute a first setting for a leading edge device (150) and/or a trailing edge device (240) of an aircraft wing. The edge control system may be communicatively coupled to the flight control computer and may include an edge control device (453) having a plurality of control device positions (458) including a cruise position (462). The speedbrake control device may include a plurality of speedbrake detents (536) including a flight detent (542). The edge control system (460) may be configured to automatically command the leading edge device (150), the trailing edge device (240), or both, to a deflection angle corresponding to the first setting if the edge control device is in the cruise position and the speedbrake control device is in the flight detent.