STOL Aircraft Flight Envelope Control for Short Runway Operation
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Solution Overview
Problem
Current Short Takeoff and Landing (STOL) fixed wing aircraft lack the capability to operate within a safe flight envelope in real-time, necessitating a system that monitors performance and automatically adjusts flight systems to maintain safe operation, especially in scenarios requiring shorter runway distances for emergency or remote area operations.
Innovation Solution
A computerized system integrated into the aircraft, comprising sensors, actuators, and a CPU that monitors altitude, airspeed, and power levels, and adjusts flight attitude and power to maintain the aircraft within a safe flight envelope by utilizing distributed electrically driven propellers and enhanced aileron and flap systems, allowing for controlled takeoff and landing on short distances.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If STOL aircraft use conventional flight control systems, then the aircraft structure remains simple, but the aircraft cannot maintain safe operation within a defined flight envelope in real-time
Solution Approach 1:
The patent implements a computerized system with sensors that continuously monitor flight parameters (altitude, airspeed, power level, attitude) and feed this data back to a CPU. The CPU compares actual parameters against stored flight envelope boundaries and automatically commands actuators to adjust flight control surfaces, ensuring the aircraft remains within safe operational limits through closed-loop feedback control.
Solution Approach 2:
The flight control system operates autonomously without requiring constant pilot intervention. The CPU automatically determines when flight status is outside the safe envelope and independently drives appropriate actuators to manipulate flight control apparatus, enabling the system to self-correct and maintain safe operation.
2Length of stationary object
If STOL aircraft use conventional takeoff and landing systems, then the aircraft design remains simple, but the takeoff and landing distances are too long for remote or emergency operations
Solution Approach 1:
The patent employs dynamically adjustable flight control surfaces including ailerons with integrated propellers, flaps, and rudders. These surfaces can be actively adjusted in real-time during takeoff and landing phases to optimize lift and drag characteristics, enabling the aircraft to achieve safe operation in much shorter distances compared to conventional STOL aircraft.
Solution Approach 2:
The system continuously monitors and adjusts multiple flight parameters including altitude, airspeed, power level, and aircraft attitude. By dynamically changing these parameters and coordinating multiple flight control surfaces, the system optimizes performance during critical takeoff and landing phases to reduce required distances.
Data Source
AI summary
An aircraft has a pilot compartment and a power source, apparatus adapted to control attitude and direction, apparatus adapted to vary power of the power source, sensors sensing at least altitude, airspeed, power level, and aircraft attitude, a CPU coupled to a data repository, to the sensors and to actuators adapted to change the flight attitude and direction and to vary power, and safe flight envelope data and conditions stored in the data repository defining flight conditions at boundaries of safe and unsafe operation. The CPU monitors the sensors while the aircraft is in operation, determines if flight status is outside the safe flight envelope, and if so, drives appropriate actuators to manipulate the apparats adapted to control flight attitude and direction and/or the apparatus adapted to vary power of the power source in a programmed manner until the flight status is within the safe flight envelope.