Modular UAV Thrust Vectoring for Urban Maneuverability
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Solution Overview
Problem
Conventional small UAVs lack the maneuvering capability and speed range necessary for operating in urban environments due to reliance on airflow over control surfaces, leading to increased system complexity and limited maneuverability.
Innovation Solution
A modular miniature unmanned aircraft equipped with thrust vectoring modules, comprising directly articulated electrical motors, that directly control the thrust vector for lateral and longitudinal control, enabling tight-radius turns at high angular rates over a wide range of speeds, including post-stall conditions, by independently controlling pitch, roll, and yaw.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional fixed wing small UAVs use airflow over control surfaces for maneuvering, then the system structure is relatively simple, but the maneuvering capability and speed range are insufficient for urban operations
Solution Approach 1:
The patent replaces the conventional aerodynamic control surface system with a direct thrust vectoring system using electrically articulated propellers. This substitution eliminates the need for complex control surfaces and airflow-dependent mechanisms, providing direct mechanical control over thrust direction to achieve superior maneuvering capability in urban environments
Solution Approach 2:
The thrust vectoring modules serve multiple functions: they provide forward thrust, enable tight-radius turns, control pitch and roll, and allow operation across a wide speed range including hover capability. This multi-functionality replaces what would traditionally require separate systems for each function
2Adaptability or versatility
If VTOL aircraft use lateral tilting of propellers to generate control forces through gyroscopic and aerodynamic effects, then vertical takeoff and landing capability is achieved, but system complexity increases and maneuverability is limited
Solution Approach 1:
The patent replaces indirect control through gyroscopic and aerodynamic effects with direct mechanical articulation of the propeller thrust vector. Each propeller can be independently articulated to point in different directions, providing direct and immediate control forces without relying on secondary physical effects
Solution Approach 2:
The system uses dynamically adjustable propeller articulation angles to adapt thrust direction in real-time. The electric articulation mechanisms allow continuous variation of thrust vector orientation, enabling the aircraft to execute tight-radius turns at high angular rates and maintain stability across varying flight conditions
3Ease of operation
If control forces are generated through secondary gyroscopic or aerodynamic effects, then the basic flight control is achieved, but system complexity increases and achievable maneuverability is limited
Solution Approach 1:
The patent substitutes indirect control methods based on gyroscopic and aerodynamic secondary effects with direct thrust vector control. The electrically articulated propellers provide immediate and precise control forces by directly changing thrust direction, eliminating the delays and limitations associated with secondary effects
Solution Approach 2:
The system pre-positions the propeller thrust vectors in the desired directions before maneuvers are executed. The articulation mechanisms are positioned in advance to optimize thrust direction for upcoming maneuvers, enabling more effective and responsive control
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 solution allows for reduced system complexity, increased durability, and the ability to execute tight-radius turns at high angular rates over a wide speed range, including hover mode operations, with a low aspect ratio planform and disposable airframe design, enhancing maneuverability and operational flexibility in cluttered environments.
Implementation Method 1
Each of the at least two thrust vectoring modules may comprise a directly articulated electrical motor
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 module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring 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 thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.