Convertible Biplane Cargo Aircraft for VTOL-to-Forward Flight Transition
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current aircraft designs, such as fixed-wing, helicopters, tiltrotor, and tiltwing, face limitations in versatility and efficiency, particularly in transitioning between vertical takeoff and landing (VTOL) and wing-borne lift orientations, which affects their ability for autonomous cargo delivery and high-speed, long-range flight.
Innovation Solution
An aircraft with a fuselage and distributed thrust array featuring first and second wings, propulsion assemblies, and a flight control system that allows transition between thrust-borne lift in VTOL orientation and wing-borne lift in biplane orientation, enabling efficient forward flight and autonomous cargo delivery.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If fixed-wing aircraft use wings to generate lift, then forward airspeed and range are improved, but runway length requirement increases
Solution Approach 1:
The aircraft employs dynamically adjustable wings that can change their orientation from a horizontal configuration during forward flight to a vertical configuration during takeoff and landing. This dynamic transformation allows the same wing structure to serve both functions, eliminating the need for long runways while maintaining high forward airspeed capability.
Solution Approach 2:
The wings are designed to perform multiple functions: generating lift during forward flight, providing thrust during vertical takeoff and landing, and enabling transition between different flight modes. This multi-functionality resolves the contradiction by allowing the aircraft to achieve both high speed and short runway requirement through the same structural element.
2Length of moving object
If VTOL aircraft use rotors for vertical lift, then runway requirement is reduced, but forward airspeed decreases
Solution Approach 1:
The aircraft uses dynamically reconfigurable wings that transition from a vertical orientation during VTOL operations to a horizontal orientation during forward flight. This dynamic reconfiguration allows the same structure to provide vertical lift when needed and generate aerodynamic lift for high-speed forward flight, resolving the speed limitation of conventional VTOL aircraft.
Solution Approach 2:
The invention replaces the traditional rotor-based VTOL mechanism with a wing-based system that uses aerodynamic forces. During vertical takeoff, the wings are positioned vertically and generate thrust similar to rotors, but during forward flight, they transition to horizontal position to generate lift, substituting the rotor mechanical system with an aerodynamic wing system that enables high forward airspeed.
3Adaptability or versatility
If tiltrotor aircraft use proprotors for VTOL and forward flight, then versatility is improved, but downwash inefficiency increases
Solution Approach 1:
The aircraft employs dynamically adjustable wings that can change their pitch angle and orientation continuously during transition between VTOL and forward flight modes. This dynamic adjustment optimizes the wing position at each stage of flight, reducing downwash interference and improving propeller efficiency compared to the fixed-geometry tiltrotor approach.
Solution Approach 2:
The invention changes the geometric parameters of the wing structure during flight transitions, adjusting pitch angle, roll angle, and orientation to optimize performance at each flight phase. This parameter optimization reduces energy loss from downwash inefficiency while maintaining versatility across different flight modes.
4Power
If tiltwing aircraft rotate wing to vertical orientation for VTOL, then vertical thrust efficiency is improved, but hover control difficulty increases
Solution Approach 1:
The aircraft divides the control function across multiple independently controllable propulsion assemblies distributed along the wings. Each assembly can be controlled independently, providing multiple degrees of freedom for hover control. This segmentation of the propulsion system simplifies hover control by distributing control authority across multiple actuators rather than requiring complex control of a single large propeller.
Solution Approach 2:
The invention employs a flight control system that uses feedback from sensors to continuously adjust the pitch and roll angles of the wings and the thrust output of individual propulsion assemblies. This feedback control maintains dynamic stability during hover and transition phases, compensating for the complexity of controlling a vertically-oriented wing configuration.
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 aircraft achieves high-speed, high-endurance forward flight and efficient cargo delivery by independently controlling propulsion assemblies and aerodynamic surfaces, enhancing dynamic stability and control during hover and forward flight.
Implementation Method 1
A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing
Implementation Method 2
wing-borne lift in a biplane orientation
Data Source
AI summary
An autonomous cargo delivery aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes a fuselage having an aerodynamic shape with a leading edge, a trailing edge and first and second sides. First and second wings are coupled to the fuselage proximate the first and second sides, respectively. A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing. A flight control system is operably associated with the distributed thrust array and configured to independently control each of the propulsion assemblies. The first side of the fuselage includes a door configured to provide access to a cargo bay disposed within the fuselage from an exterior of the aircraft with a predetermined clearance relative to the first pair of propulsion assemblies.