Flapping-Wing Flight Test System Using Wind Tunnel and Euler Controllers
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Solution Overview
Problem
Current research lacks effective flight test systems for flapping-wing aerial vehicles, relying on actual flight tests that are costly and prone to environmental disturbances, leading to high damage rates and inefficiencies.
Innovation Solution
A flight test system comprising a host computer platform, a measurement mechanism, and a wind tunnel, which includes an Euler angle controller, a flow angle controller, and a multidimensional force sensor, allowing for controlled simulation of flapping-wing aerial vehicle flight dynamics, reducing the need for physical flight tests and minimizing damage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If actual flight tests are used to test flapping-wing aerial vehicle prototypes, then flight performance data can be obtained, but test costs increase and prototype damage rate increases due to environmental disturbances
Solution Approach 1:
The patent creates a virtual copy of the flapping-wing aerial vehicle through mathematical modeling and digital twin technology. This virtual model replicates the physical vehicle's aerodynamic characteristics, structural properties, and flight dynamics, allowing comprehensive flight testing in a simulated environment without exposing the physical prototype to real-world environmental risks, thereby obtaining reliable flight performance data while eliminating prototype damage and reducing test costs
2Measurement precision
If actual flight tests are conducted in real environmental conditions, then realistic flight data can be collected, but environmental disturbances cause high prototype damage rates
Solution Approach 1:
The patent introduces a wind tunnel as an intermediary testing environment that provides controlled aerodynamic conditions without the harmful elements of actual flight (weather, turbulence, spatial constraints). The mathematical model serves as another intermediary layer that translates real flight conditions into simulated scenarios, allowing accurate measurement of flight characteristics while completely isolating the physical prototype from environmental damage risks
3Loss of information
If multiple flight tests are performed to gather sufficient aerodynamic data, then comprehensive understanding of flight characteristics can be achieved, but test costs and time consumption increase significantly
Solution Approach 1:
The patent performs preliminary comprehensive testing in the virtual environment where unlimited test iterations can be conducted without time or cost constraints. The mathematical model allows researchers to pre-test various flight conditions, parameter combinations, and edge cases exhaustively before any physical testing. This preliminary virtual action gathers complete aerodynamic data and validates the model's accuracy, eliminating the need for multiple repeated physical flight tests and significantly reducing overall testing time and costs
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 system provides a simulated flight environment for obtaining dynamic characteristic data, improving test efficiency and reducing prototype damage, while allowing for intuitive three-dimensional presentation and verification of mathematical models and flight control algorithms.
Implementation Method 1
a pitch of the flapping-wing aerial vehicle prototype is controlled by controlling a rotation angle of the pitch control motor
Implementation Method 2
a yaw of the flapping-wing aerial vehicle prototype is controlled by controlling a rotation angle of the yaw control motor
Implementation Method 3
a roll of the flapping-wing aerial vehicle prototype is controlled by controlling a rotation angle of the roll control motor
Implementation Method 4
the measurement mechanism includes an ATI six-dimensional force sensor
Implementation Method 5
both the flapping-wing aerial vehicle prototype and the measurement mechanism are placed in the wind tunnel during test
Data Source
AI summary
A flight test system for a flapping-wing aerial vehicle includes a host computer platform, a measurement mechanism, and a wind tunnel. The measurement mechanism is configured to mount a to-be-tested flapping-wing aerial vehicle prototype. The measurement mechanism includes an Euler angle controller, a flow angle controller, and a tripod. The flow angle controller is mounted on the tripod. The Euler angle controller is in transmission connection with the flow angle controller. The flapping-wing aerial vehicle prototype is detachably connected to the Euler angle controller by using a first connecting member. The host computer platform is in communication connection with the measurement mechanism and the wind tunnel, and is configured to control a wind speed of the wind tunnel and display a flight status of the flapping-wing aerial vehicle prototype in real time during test.