Gimballed Thrust Unit Layout for Orientation-Independent Flight
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Solution Overview
Problem
Multirotor drones are limited in maneuverability and stability due to their orientation dependency, which restricts their size and performance in various applications.
Innovation Solution
An aerial vehicle with three or more gimballed thrust units capable of two degrees of rotational freedom, allowing independent orientation and thrust control, enabled by a control unit that computes and issues commands based on sensor data to achieve hover and flight in any orientation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If multirotor drones use fixed orientation relative to heading, then the structure is simple and easy to control, but maneuverability and stability are limited
Solution Approach 1:
The propulsion system is segmented into multiple independent gimballed thrust units, each capable of independent orientation control. This segmentation allows the vehicle to decouple heading from orientation, enabling each thrust unit to contribute to both propulsion and moment generation independently, thereby resolving the contradiction between control simplicity and maneuverability.
Solution Approach 2:
The thrust units are made dynamically adjustable through gimbal mechanisms that allow real-time reorientation of each thrust vector. This dynamic capability enables the system to adapt thrust direction and magnitude independently for each unit, providing enhanced maneuverability while maintaining controllable complexity through centralized control algorithms.
2Stability of the object's composition
If multirotor drones increase size for greater stability, then stability improves, but orientation dependency limits further size increase
Solution Approach 1:
By segmenting the propulsion into multiple independently controllable gimballed thrust units, the system can generate stabilizing moments without requiring a larger physical structure. Each unit can be independently oriented to counteract disturbances, providing active stability control that is independent of vehicle size.
Solution Approach 2:
The system changes the control parameters by independently varying the orientation and thrust magnitude of each gimballed unit. This allows the vehicle to maintain stability through active control of thrust vector parameters rather than relying on passive structural stability, enabling orientation independence regardless of size.
3Adaptability or versatility
If gimballed thrust units are added for independent orientation control, then maneuverability and precision improve, but device complexity increases
Solution Approach 1:
Each gimballed thrust unit is designed as a universal module that performs multiple functions: propulsion, orientation control, and moment generation. This multi-functionality reduces the need for separate systems for each function, thereby managing complexity while achieving enhanced maneuverability and precision.
Solution Approach 2:
The system manages complexity by changing control parameters (thrust magnitude and orientation angles) of existing gimballed units rather than adding more physical components. The control algorithm dynamically adjusts these parameters to achieve desired maneuvers, providing precision control without proportionally increasing hardware complexity.
4Ease of manufacture
If standard multirotor design is used, then manufacturing is simple and cost-effective, but performance and precision are limited
Solution Approach 1:
The propulsion system is segmented into standardized gimballed thrust unit modules that can be manufactured using conventional processes. Each module is a self-contained unit with standardized interfaces, allowing for simplified manufacturing and assembly while enabling precise control through the gimbal mechanisms and independent actuation of each module.
Data Source
AI summary
An aerial vehicle includes a hull containing the main processor, energy storage, support components such as sensors, wireless communication, and landing gear. Attached to the hull are at least three thrust or propulsion units each with two degrees of freedom from the hull allowing them to orient independently in any direction and apply thrust independently from the hull or any other thrust or propulsion unit. In some embodiments, a mount for auxiliary attachments is included or the auxiliary system is built into the hull. Components like the energy storage, auxiliary attachments, and/or propulsion units may also be replaceable as required.