Distributed Electric Propulsion Aircraft Yaw Moment Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current fixed-wing aircraft, particularly in General Aviation, face safety concerns due to the higher risk of accidents in single-engine configurations and the higher operational costs and complexity of multi-engine configurations, which require specific training for emergency situations.
Innovation Solution
A distributed electric propulsion fixed-wing aircraft with symmetrically arranged electric propulsive units and a control unit that simulates single-engine or multi-engine configurations, providing a yawing moment to manage sideslip angles and power distribution, allowing for safe operation and training in both single-engine and multi-engine modes while maintaining low operational costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a multi-engine configuration is used, then flight safety is improved, but operational cost and device complexity increase
Solution Approach 1:
The distributed electric propulsion system with multiple propulsive units is designed to perform multiple functions: it can operate in multi-engine mode for normal flight with enhanced safety, and simulate single-engine conditions for training purposes. The control unit enables the same hardware configuration to serve different operational requirements, making the system universal and multi-functional.
Solution Approach 2:
The system uses software control to create a virtual copy of single-engine thrust characteristics within the multi-engine aircraft. By controlling the power distribution among multiple propulsive units, the system replicates the asymmetrical thrust conditions of a single-engine aircraft, allowing pilots to train for single-engine scenarios without actually flying a single-engine plane.
2Device complexity
If a single-engine configuration is used, then operational cost is reduced, but flight safety deteriorates
Solution Approach 1:
The system creates a virtual single-engine experience by controlling the power output of multiple propulsive units to replicate single-engine thrust characteristics. This allows pilots to train in realistic single-engine failure scenarios while operating from a safer multi-engine platform, combining the cost benefits of single-engine operations with the safety of multi-engine configuration.
Solution Approach 2:
The control unit dynamically adjusts the power distribution among propulsive units in real-time. During normal operation, all units can operate symmetrically for efficient multi-engine performance. During training scenarios, the control system dynamically creates asymmetrical thrust conditions to simulate single-engine or engine-failure situations, providing adaptive training without requiring actual single-engine aircraft.
3Adaptability or versatility
If multi-engine training is provided, then pilot qualification is improved, but training complexity and time increase
Solution Approach 1:
The same aircraft platform and training program can cover both single-engine and multi-engine qualifications. The control unit allows instructors to switch between different training modes (single-engine simulation, multi-engine normal operation, multi-engine failure scenarios) without changing aircraft or curriculum, making the training system universal and reducing total training time.
Solution Approach 2:
The training program merges single-engine and multi-engine qualification into a single integrated course. By using the distributed propulsion system to simulate various engine configurations and failure scenarios, the program combines what would traditionally require separate training courses into one unified program, reducing overall training time while maintaining comprehensive pilot qualification.
Data Source
Figure 1
Figure 2
Figure 3
AI summary
It is disclosed a distributed electric propulsion fixed-wing aircraft comprising a plurality of propulsive units, wherein propulsive units are arranged symmetrically with respect to the longitudinal plane, wherein of propulsive units comprises first propulsive units at a first side of the longitudinal plane and second propulsive units at a second side of the longitudinal plane, wherein the distributed propulsion aircraft further comprises a control unit configured to provide a yawing moment so that a sideslip angle is generated, so that the distributed electric propulsion aircraft flies as a fixed-wing aircraft equipped with a single propeller.