Tilt-Frame UAV Thrust Governing for VTOL Air Sampling Range
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Solution Overview
Problem
Existing UAV designs, both multirotor and fixed-wing, are inadequate for agricultural VOC sampling due to limited range, endurance, and the complexity of tiltrotor systems, which are heavy and have poor aerodynamic performance.
Innovation Solution
A tilt-frame UAV with a Propeller-Thrust-Governing System (PTGS) that enables vertical takeoff and landing, high-speed cruising, and efficient VOC sampling using a probe-deployment mechanism with adjustable butterfly flaps to control thrust and rotations, allowing for precise VOC collection over larger fields.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a tiltrotor design is used to achieve VTOL capability and long range, then the UAV can land vertically in fields and cruise at high speed, but the system becomes complex and heavy with poor aerodynamic performance
Solution Approach 1:
The propulsion system is divided into separate functional components: fixed-wing lift generation, pusher propeller thrust, and independent control surfaces (elevator, ailerons, rudder). This segmentation allows each component to be optimized for its specific function rather than requiring a complex integrated tiltrotor mechanism, thereby reducing overall system complexity while maintaining VTOL capability.
Solution Approach 2:
The fixed-wing aircraft design incorporates multiple functions into a single platform: vertical takeoff and landing, high-speed cruising, and precise positioning. The pusher propeller and control surfaces serve multiple purposes including thrust generation, pitch control, roll control, and yaw control, eliminating the need for separate tiltrotor mechanisms and reducing system complexity.
2Ease of operation
If a multirotor UAV is used for VOC sampling, then the UAV can hover and land vertically, but the range and endurance are limited requiring frequent battery changes
Solution Approach 1:
The aircraft transitions between different flight parameters and modes: vertical flight mode for takeoff and landing, high-speed cruise mode for long-distance travel, and hover mode for sampling operations. This parameter changing allows the aircraft to optimize performance for each specific task, achieving both long endurance through efficient cruising and precise hovering when needed, without the range limitations of multirotor UAVs.
3Duration of action of moving object
If a fixed-wing UAV is used for long range flight, then the range and endurance are improved, but the UAV cannot land vertically within crops for sampling
Solution Approach 1:
The aircraft employs dynamic control surfaces (elevator, ailerons, rudder) that can be adjusted in real-time to transition between flight modes. The pusher propeller's thrust can be modulated to enable vertical descent and landing, allowing the fixed-wing platform to adapt its behavior from high-speed cruise to vertical landing as mission requirements change, thereby gaining versatility without sacrificing range.
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 UAV effectively samples VOCs over larger fields with improved range and endurance, reducing the need for frequent battery changes and enhancing sampling accuracy by utilizing a lightweight, efficient design that balances thrust and lift generation.
Implementation Method 1
a right motor and associated right propeller are coupled to a right side of the main wing, and a left motor and associated left propeller are coupled to a left side of the main wing. The right and left propellers are angled with respect to the fuselage to provide thrust-generation lines
Implementation Method 2
which can also achieve high-speed cruising flight on fixed wings
Implementation Method 3
a pitch motor and associated pitch propeller located at the rear end of the fuselage, wherein the pitch propeller is angled to provide substantially vertical thrust to control a pitch of the fuselage
Data Source
AI summary
We describe an aircraft design, which is capable of vertical takeoff and landing and also high-speed cruise on a fixed wing. The aircraft comprises a fuselage with a probe-deployment mechanism, which deploys a sample-gathering probe, located at a front end of the fuselage. A main wing is coupled to a middle section of the fuselage, wherein a right motor and right propeller are coupled to a right side of the main wing, and a left motor and left propeller are coupled to a left side of the main wing. The right and left propellers are angled with respect to the fuselage enabling the aircraft to pitch up to a vertical-takeoff mode and pitch down a horizontal-cruising mode. A pitch motor and pitch propeller are located at the rear end of the fuselage, wherein the pitch propeller is angled to provide substantially vertical thrust to control a pitch of the fuselage.