Modular UAV Thrust-Vectoring Control for Tight Turns
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Solution Overview
Problem
Conventional small UAVs lack maneuverability and speed range to execute tight-radius turns at high angular rates over a wide range of speeds, necessitating the development of a durable and low-cost aircraft capable of such maneuvers, especially in urban environments.
Innovation Solution
The use of thrust-vectoring modules with articulated electric motors and frangible components to enable tight-radius turns and mitigate impact damage, featuring a modular design with interchangeable airframes and components that can eject during impact to absorb landing energy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional fixed-wing UAVs are used, then the aircraft structure is simple and cost is low, but the aircraft lacks maneuverability and cannot execute tight-radius turns at high angular rates
Solution Approach 1:
The aircraft is divided into modular components including T/V modules, airframe, payload module, and battery module. Each T/V module contains an electric motor, propeller, and positioning device that can independently control thrust vectoring, enabling tight-radius turns and high angular rates while keeping individual components simple to manufacture
Solution Approach 2:
The positioning devices enable dynamic adjustment of the rigid links and electric motors to vary thrust vector direction in real-time. This dynamic control allows the aircraft to execute tight-radius turns at high angular rates over a wide speed range while maintaining a relatively simple overall structure
2Ease of operation
If VTOL aircraft with lateral tilting propellers are used, then low-speed maneuverability is improved, but the device complexity and cost increase
Solution Approach 1:
Instead of a single complex VTOL mechanism, the aircraft uses multiple independent T/V modules with individual positioning devices. Each module handles a specific thrust vectoring function, simplifying the design of individual components while achieving collective VTOL capability and improved low-speed maneuverability
Solution Approach 2:
The T/V modules serve multiple functions: they provide thrust for forward flight, enable VTOL operations, and execute tight-radius turns. The positioning devices control both the orientation of the modules and the direction of thrust vectors, consolidating multiple control functions into a unified system that reduces overall device complexity
3Strength
If durable aircraft components are used, then impact resistance is improved, but the weight and cost of the aircraft increase
Solution Approach 1:
The battery module is designed as a separable component that can be easily removed and replaced. This extraction approach allows the use of lighter materials for the battery housing and mounting structure, reducing overall aircraft weight while maintaining durability through modular replacement rather than permanent reinforcement
Solution Approach 2:
The frangible components are designed to break away or be discarded during impact events to protect critical systems. After impact, these components can be recovered, replaced, or reused, allowing the aircraft to use lighter materials overall while maintaining impact resistance through sacrificial elements rather than permanent strengthening
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
Enables the UAV to perform tight-radius turns at high angular rates over a wide speed range while minimizing damage from impacts through the use of frangible components and modular design, enhancing durability and reducing assembly time.
Implementation Method 1
an electric motor, wherein the electric motor is configured to rotate the propeller
Implementation Method 2
a positioning device coupled with the second end of the rigid link, wherein the positioning device is configured to position the electric motor by rotating the rigid link
Implementation Method 3
aerial vehicle for reducing impact loads comprises an airframe; a payload module coupled to the airframe via one or more passive engagement tabs; and a battery module configured to interface with the airframe and the payload module, wherein the payload module and the battery module are configured to eject from the airframe during impact
Data Source
AI summary
An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.