VTOL Aircraft Propulsion Layout for Drag Reduction
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
State-of-the-art VTOL aircraft face challenges in achieving an optimal trade-off between energy efficiency, aerodynamic stability, manoeuvrability, and safety due to the complexity and inefficiency of thrust element placement, which increases mass, drag, and parasite drag, affecting performance and endurance.
Innovation Solution
The aircraft design features a fuselage-mounted rear set of fixed propulsion units and configurable units at the wings and tail, allowing for efficient thrust generation and control, minimizing drag, and enabling three-point and four-point attitude control, eliminating the need for ailerons, elevators, and rudders, with ducted fans providing high thrust-to-space ratio and reduced noise.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple thrust elements are arranged along main components for optimal vertical flight performance, then vertical flight capability is improved, but parasite drag increases and horizontal flight performance deteriorates
Solution Approach 1:
The propulsion system is segmented into multiple independent thrust elements distributed along the fuselage and wings. Each thrust element can be independently controlled to generate vertical or horizontal thrust, allowing the aircraft to optimize its configuration for different flight phases and reduce parasite drag during horizontal flight by retracting or deactivating unnecessary vertical thrust elements.
Solution Approach 2:
The thrust elements are designed to be dynamically adjustable between vertical and horizontal orientations. This dynamic reconfiguration allows the aircraft to adapt its thrust vectoring capabilities for optimal vertical flight performance while minimizing parasite drag during horizontal cruise by aligning thrust elements with the airflow direction.
2Adaptability or versatility
If additional propulsion units are introduced for vertical thrust generation, then vertical flight capability is improved, but aircraft mass increases and energy consumption increases
Solution Approach 1:
The propulsion units are designed with multi-functionality, serving dual purposes as vertical thrust generators during takeoff and landing, and as horizontal thrust generators during cruise flight. This universal design eliminates the need for separate dedicated vertical and horizontal propulsion systems, reducing overall aircraft mass while maintaining full vertical flight capability.
3Ease of operation
If configurable propulsion units are mounted on pivotable supports for thrust direction control, then manoeuvrability is improved, but device complexity increases and reliability decreases
Solution Approach 1:
The patent replaces complex mechanical pivotable support systems with a more reliable thrust vectoring mechanism. Instead of physically pivoting entire propulsion units on complex supports, the invention uses adjustable thrust vectoring nozzles or deflectors that can change thrust direction with simpler mechanical components, reducing device complexity while maintaining manoeuvrability.
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 design results in a highly efficient, controllable, and safe VTOL aircraft with improved speed, endurance, and reduced energy consumption, achieving an optimized trade-off between vertical and horizontal flight characteristics.
Implementation Method 1
a first group of propulsion units mounted fixedly on the aircraft in a vertical thrust generating configuration, and a second group of propulsion units each of which is mounted on the aircraft configurable between a vertical thrust generating configuration and a horizontal thrust generating configuration
Data Source
Figure 1
Figure 2
Figure 3
AI summary
The invention relates to a vertical take-off and landing (VTOL), aircraft (1) comprising a fuselage (2) supporting two main wings (6), a first group of propulsion units (11) mounted fixedly on the aircraft (1) in a vertical thrust generating configuration, and a second group of propulsion units (12) each of which is mounted on the aircraft (1) configurable between a vertical thrust generating configuration and a horizontal thrust generating configuration, wherein the first group is subdivided into two front sets (13) and a rear set (14), wherein the two front sets (13) are mounted at opposite sides of the fuselage (2) ahead of the main wings (6) and the rear set (14) is mounted in the fuselage (2), passing therethrough, and wherein the second group is subdivided into a wing set (15) and a tail set (16), wherein the propulsion units (12) of the wing set (15) are mounted at opposite tips (27) of the main wings (6) and the propulsion units (12) of the tail set (16) are mounted at opposite sides of the fuselage (2).