Steep Aircraft Approach with Low Idle and Ice Protection Air Priority
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Solution Overview
Problem
Aircraft operating during steep approach phases face challenges in managing engine idle speed and ice protection systems to achieve steeper approach angles while ensuring adequate acceleration for go-around procedures, particularly at airports with noise or obstacle constraints.
Innovation Solution
The method involves operating engines at a lower idle speed and utilizing pressurized air from the engines to power the ice protection system, while reducing air supply to other pneumatic loads like the environmental control system, fuel tank inerting system, or cargo heating system, and ensuring dual-engine support for ice protection during steep approaches.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the aircraft operates at a higher idle speed to ensure adequate acceleration for go-around procedures, then the acceleration capability is improved, but the approach angle becomes shallower than required for steep approaches
Solution Approach 1:
The patent extracts the pneumatic load requirements from the engine during steep approach, selectively removing non-essential pneumatic loads (environmental control system, fuel tank inerting system, cargo heating system) to reduce engine burden. This allows the engine to operate at lower idle speed while still providing sufficient acceleration capability for go-around procedures, thereby enabling steeper approach angles without compromising safety.
Solution Approach 2:
The patent applies preliminary action by pre-configuring the engine and pneumatic system before the steep approach phase. The system pre-identifies and removes non-essential pneumatic loads before they are needed, and pre-configures the ice protection system to receive prioritized pneumatic supply. This preparation enables the aircraft to execute steep approaches with optimized engine performance from the outset.
2Reliability
If pressurized air is supplied to the ice protection system during steep approach, then ice protection capability is improved, but the available pressurized air for other systems is reduced
Solution Approach 1:
The patent applies local quality by providing differentiated pneumatic supply priorities to different systems during steep approach. The ice protection system receives guaranteed pressurized air supply with high priority, while other pneumatic loads are reduced or eliminated. This localized optimization ensures critical ice protection functionality without compromising overall pressurized air availability for essential systems.
3Object-affected harmful factors
If the aircraft executes a steep approach angle of 4.5 degrees or more, then noise reduction and obstacle clearance are improved, but the engine must operate at lower idle speed which reduces acceleration capability
Solution Approach 1:
The patent applies parameter changes by modifying the engine operating parameters during steep approach. The engine idle speed is reduced to enable steeper approach angles, while the pneumatic system parameters are reconfigured to prioritize ice protection and eliminate non-essential loads. These parameter changes allow the aircraft to achieve noise reduction and obstacle clearance benefits of steep approaches while maintaining adequate acceleration capability through optimized resource allocation.
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
This approach enables aircraft to execute steep approach angles of 4.5 degrees or more while maintaining the ability for rapid engine acceleration during go-around procedures, balancing descent rate and operational efficiency.
Implementation Method 1
supplying pressurized air extracted from the engine to the ice protection system of the aircraft during the steep approach phase of flight of the aircraft
Data Source
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AI summary
Systems and methods to facilitate a steep final approach phase of flight of an aircraft are disclosed. In one embodiment, a method for operating an aircraft during a steep approach phase of flight of the aircraft comprises operating an engine of the aircraft at an idle speed associated with the steep approach type that is lower than an idle speed associated with a non-steep approach type capable of being executed by the aircraft. The method also comprises operating an ice protection system of the aircraft during the steep approach phase of flight of the aircraft.