Blown Lift Flight Path Control With Unified Thrust Settings
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Solution Overview
Problem
Controlling the flight path of a blown lift aircraft with multiple electric propulsion units is complex and counterintuitive for pilots, requiring individual adjustments of power levers and pitch controls, which can lead to increased cockpit complexity and safety risks due to non-intuitive power settings.
Innovation Solution
A control operator system with at least two selectable settings, coupled to a computing device, controls the thrust-producing devices on a blown lift aircraft using algorithms, lookup tables, and machine learned models to maintain a desired flight path angle based on sensor inputs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional individual power lever control is used for each engine, then the pilot can control thrust independently, but the cockpit complexity and pilot workload increase significantly
Solution Approach 1:
The patent combines multiple individual power lever controls into a single collective control system. The system integrates control of multiple thrust-producing devices through one control interface, merging the functions of multiple levers into a unified control mechanism that reduces cockpit complexity while maintaining independent thrust control capability.
Solution Approach 2:
The single control system performs multiple functions by controlling different thrust-producing devices based on detected aircraft operating conditions. The control system automatically adjusts power distribution across multiple engines/propellers according to flight phase, configuration, and environmental factors, making one control device universal for all propulsion units.
2Reliability
If power controls are used to maintain flight path in blown lift aircraft, then lift is increased, but the control becomes counterintuitive compared to conventional aircraft
Solution Approach 1:
The control system automatically detects aircraft operating conditions and independently determines the appropriate power settings for thrust-producing devices. The system self-adjusts power controls based on detected parameters such as flight phase, configuration, and environmental conditions, eliminating the need for pilot interpretation of counterintuitive control responses.
Solution Approach 2:
The system continuously monitors aircraft operating conditions and uses this feedback to automatically adjust power settings. Sensors detect parameters like airspeed, configuration state, and environmental conditions, and the control system processes this information to make real-time power adjustments, creating a closed-loop control system that adapts to changing conditions without pilot intervention.
3Measurement precision
If multiple individual controls are used for power, pitch, and trim adjustments, then precise flight path control is achieved, but the number of controls and cockpit space requirements increase
Solution Approach 1:
The patent merges multiple control functions (power control, pitch control, and trim adjustments) into a single integrated control system. Instead of separate controls for each parameter, the system combines these functions and automatically coordinates them based on detected operating conditions, reducing the number of physical controls while maintaining precise flight path control capability.
Solution Approach 2:
The control system performs preliminary adjustments by pre-calculating and automatically applying the necessary power, pitch, and trim settings based on detected flight conditions. The system anticipates required control changes and makes them proactively, eliminating the need for sequential manual adjustments by the pilot.
Data Source
AI summary
In accordance with some embodiments, a system for controlling an aircraft is provided. The system can include a computing device, wherein the computing device includes at least one processor configured to control a flight path angle of the aircraft, and wherein the aircraft is a blown lift aircraft. The system can also include a control operator communicatively coupled to the computing device, wherein the control operator is configured to have at least two selectable settings. The system can also include at least two thrust-producing devices operatively coupled to a pair of wings on the aircraft and communicatively coupled to the computing device. The computing device may control the flight path angle of the aircraft by selectively operating the at least two thrust-producing devices based on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected setting of the control operator.