VSTOL Aircraft Pivotable Propulsion and Detachable Cabin
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Solution Overview
Problem
Conventional tilt rotor VSTOL aircraft face issues with pitch attitude misalignment during vertical takeoff and landing due to thrust vector misalignment, leading to discomfort and exceeding tilt range capabilities, and current airport operations hinder air transport efficiency by requiring lengthy access and check-in procedures.
Innovation Solution
The design incorporates pivotable propulsion units and airfoil assemblies that allow thrust lines to orient parallel or perpendicular to the fuselage axis, with intermediate airfoils providing lift and stability, and a detachable cabin that converts into a roadable vehicle for improved ground transportation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional tilt rotor VSTOL aircraft are used without cyclic control for rotor alignment, then the aircraft can achieve vertical takeoff and landing capability, but the thrust vector misalignment causes drastic pitch attitude that exceeds rotor tilt range and creates occupant discomfort
Solution Approach 1:
The patent implements cyclic control mechanisms that dynamically adjust rotor tilt angles in real-time during flight operations. The cyclic control system allows continuous variation of rotor pitch and roll attitudes, enabling precise thrust vector alignment with the center of gravity throughout the flight envelope, from vertical hover to horizontal flight transitions.
Solution Approach 2:
The patent incorporates feedback control systems that continuously monitor aircraft attitude, thrust vector orientation, and center of gravity position. This feedback enables automatic adjustment of rotor cyclic control inputs to maintain optimal thrust alignment, preventing excessive pitch attitudes and ensuring smooth transitions between flight modes while maintaining occupant comfort.
2Reliability
If large scale airport operations with traditional check-in procedures are used, then passengers can be processed through established protocols, but the access time and block time to final destination are significantly increased
Solution Approach 1:
The patent segments the traditional airport operation into multiple independent phases: vertical takeoff from remote locations, direct point-to-point flight, and vertical landing. This eliminates the need for lengthy ground access to large airports and traditional check-in procedures, reducing total travel time while maintaining reliable passenger processing at simplified locations.
Solution Approach 2:
The VSTOL aircraft serves as an intermediary between origin and destination points, enabling direct transportation without requiring passengers to access traditional airport infrastructure. The aircraft can operate from remote locations near cities, acting as a mediator that bridges the gap between point-to-point flight efficiency and reliable passenger processing capabilities.
3Use of energy by moving object
If the aircraft is designed with fixed wing configuration for efficient cruise, then fuel efficiency is improved, but the aircraft cannot achieve vertical takeoff and landing without compromising pitch control and stability
Solution Approach 1:
The patent employs dynamic wing configurations that can adjust their geometry and orientation during flight. The wings can be tilted, folded, or repositioned to optimize aerodynamic efficiency during horizontal cruise while enabling vertical thrust generation during takeoff and landing phases. This dynamic adaptability allows the aircraft to achieve both fuel-efficient cruise and VSTOL capability.
Solution Approach 2:
The aircraft design integrates multiple flight modes into a single platform, making the wings and propulsion system multi-functional. The same wing structure serves both as a lift-generating surface for efficient cruise flight and as a mounting platform for rotors that provide vertical thrust. The propulsion system similarly provides both forward thrust for cruise and vertical lift for takeoff and landing.
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 configuration enhances stability during flight transitions and reduces passenger access time to airports by enabling efficient VSTOL operations and converting the aircraft cabin into a roadable vehicle for ground transport, thus improving overall travel efficiency.
Implementation Method 1
propellers operably driven by a respective engine of a propulsion unit... provide thrust to the aircraft along a thrust line
Implementation Method 2
The engine and propellers are mounted for pivotal movement within the defined space between the primary airfoil and the secondary empennage airfoils so as to achieve a first operational position wherein the thrust line of the propellers is orientated substantially parallel to the longitudinal axis of the fuselage and a second operational position wherein the thrust line of the propellers is oriented substantially perpendicular to the longitudinal axis of the aircraft
Data Source
AI summary
Vertical short takeoff and landing (VSTOL) aircraft include primary airfoils extending outwardly from a forward region of the aircraft fuselage, and secondary empennage airfoils extending outwardly from an aft region of the aircraft fuselage so as to be separated from the forward primary airfoils and thereby define a space therebetween which accommodates non-cyclic controllable propellers operably driven by a respective engine of a propulsion unit. The propulsion units are mounted for pivotal movement within the defined space between the primary airfoil and the secondary empennage airfoils so as to achieve a first operational position wherein the thrust line of the propellers is orientated substantially parallel to the longitudinal axis of the fuselage and a second operational position wherein the thrust line of the propellers is oriented substantially perpendicular to the longitudinal axis of the aircraft. The propulsion units may be mounted aft of the aircraft center of gravity (CG).