Flight Vehicle Nose Orientation for Wind-Aware Landing Control
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Solution Overview
Problem
Flight vehicles used in industries like home delivery face challenges in improving landing performance due to lift generation during landing operations, which can prolong the time required and hinder operational efficiency.
Innovation Solution
A method where the flight vehicle generates lift in response to wind from the nose direction, with the nose direction controlled based on wind speed and direction data to initiate descent, reducing lift interference and optimizing landing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the flight vehicle is configured to generate lift in response to wind from the nose direction, then flight efficiency is improved, but landing operation time increases and landing performance deteriorates
Solution Approach 1:
The patent applies dynamics by making the rotor blade pitch angle adjustable during different flight phases. The pitch angle is set to a first value during flight to generate lift for improved efficiency, and dynamically changed to a second value during landing to reduce or eliminate lift generation, thereby solving the contradiction between flight efficiency and landing performance.
Solution Approach 2:
The patent changes the parameter of rotor blade pitch angle between two distinct values. During flight, the pitch angle is maintained at a first value that optimizes lift generation for forward motion. During landing, the pitch angle is changed to a second value that reduces or eliminates lift, allowing the vehicle to descend properly without being lifted by wind-induced lift forces.
2Use of energy by moving object
If the flight vehicle is configured to generate lift in response to wind from the nose direction, then flight efficiency is improved, but landing performance deteriorates
Solution Approach 1:
The patent applies dynamics by making the rotor blade pitch angle adjustable during different flight phases. The pitch angle is set to a first value during flight to generate lift for improved efficiency, and dynamically changed to a second value during landing to reduce or eliminate lift, thereby solving the contradiction between flight efficiency and landing performance.
Solution Approach 2:
The patent changes the parameter of rotor blade pitch angle between two distinct values. During flight, the pitch angle is maintained at a first value that optimizes lift generation for forward motion. During landing, the pitch angle is changed to a second value that reduces or eliminates lift, allowing the vehicle to descend properly without being lifted by wind-induced lift forces.
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 method enhances landing performance by minimizing lift-induced delays and improving operational efficiency, allowing for faster and more reliable landings.
Implementation Method 1
the flight vehicle's lift-generating configuration may cause the landing operation to take longer or be more difficult. This is because when the flight vehicle in the hovering posture receives wind from the nose direction during the landing operation, lift is generated and the flight vehicle is lifted up.
Data Source
AI summary
A landing method, etc., for a flight vehicle having directional characteristics, which can improve the landing performance of the flight vehicle having directional characteristics by turning the airframe in a nose direction with a good balance between lift and drag based on wind speed data and wind direction data related to the landing site. In the method for landing a flight vehicle of the present invention, the flight vehicle comprises to generate lift in response to wind from the nose direction of the airframe and based on wind speed data and wind direction data related to the landing site, the nose direction of the airframe is controlled and the descent of the airframe is initiated.