Systems and methods for esotaira structure applications

Abstract

The present subject matter to novel structural designs for omni-directional aerial vehicles, such as drones or personal aircraft. The structures comprise multiple flanges arranged around a central void space. Flanges may be shaped as polygons or circles. The flanges allow positioning of propellers or rotors in various configurations to enable thrust and movement in any direction. This provides advantages over traditional fixed-wing aircraft or helicopters with limited directional capabilities. The structures may be used individually or bonded together to form larger compounds. Different designs optimize for maneuverability, strength, and internal volume. By enabling omni-directional flight and bonding, these structural designs enhance aerial vehicle capabilities and applications.

Description

SYSTEMS AND METHODS FOR ESOTAIRA STRUCTURE APPLICATIONSCROSS-REFERENCE TO RELATED APPLICATION

[0001] This application claims priority to U.S. Provisional Pat. Appl. No. 63 / 604,678, titled “SYSTEMS AND METHODS FOR OMNI-DIRECTIONAL STRUCTURE APPLICATIONS,” filed Nov. 30, 2023, which is hereby incorporated by reference herein in its entirety.FIELD

[0002] The present invention relates to combinable structures for use in aerial vehicle applications.BACKGROUND

[0003] Unmanned Aerial Vehicles (UAVs) include fully or partially autonomous aircraft that operate without an onboard human pilot. These aerial vehicles may be used for various purposes, including surveillance, reconnaissance, aerial photography, agriculture, delivery services, and other purposes. UAVs may be equipped with various sensors, cameras, navigation systems, and other technical features, which may provide improved navigation abilities or other functionality. UAVs are typically smaller than other aerial vehicles, which may improve their ability to access hard-to-reach or hazardous areas, gather data, and execute missions with little or no human intervention.BRIEF DESCRIPTION OF THE DRAWINGS

[0004] FIG. 1 illustrates a rhombus flanged variation of a rhombus Matthai structure 100, according to an embodiment.

[0005] FIG. 2 illustrates a floret pentagonal flanged variation of a pentagonal Matthai structure 200, according to an embodiment.

[0006] FIG. 3 illustrates a line drawing of a hexagonal flanged variation of a first hexagonal Matthai structure 300, according to an embodiment.

[0007] FIG. 4 illustrates a structural drawing of a hexagonal flanged variation of a second hexagonal Matthai structure 400, according to an embodiment.

[0008] FIG. 5 illustrates a circular flanged variation of the circular Matthai structures 500, according to an embodiment.

[0009] FIG. 6 illustrates tessellated hexagons 600, according to an embodiment.

[0010] FIG. 7 illustrates the formation of an omni-directional hexagonal flanged lattice structure 700, according to an embodiment.

[0011] FIG. 8 illustrates the formation of modularly bonded Matthai structures 800.

[0012] FIG. 9 illustrates modularly bonded Matthai structures 900.

[0013] FIG. 10 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1000, according to an embodiment.

[0014] FIG. 11 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1100, according to an embodiment.

[0015] FIG. 12 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1200, according to an embodiment.

[0016] FIG. 13 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1300, according to an embodiment.

[0017] FIG. 14 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1400, according to an embodiment.

[0018] FIG. 15 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1500, according to an embodiment.

[0019] FIG. 16 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1600, according to an embodiment.

[0020] FIG. 17 illustrates a first hybrid propeller Matthai structure 1700, according to an embodiment.

[0021] FIG. 18 illustrates a second hybrid propeller Matthai structure 1800, according to an embodiment.

[0022] FIG. 19 illustrates a third hybrid propeller Matthai structure 1900, according to an embodiment.

[0023] FIG. 20 illustrates a square flanged alternate variation of the square Hunter structures 2000, according to an embodiment.

[0024] FIG. 21 illustrates a line drawing of an octagonal flanged variation of a first octagonal Hunter structure 2100, according to an embodiment.

[0025] FIG. 22 illustrates a structural drawing of an octagonal flanged variation of a second octagonal Hunter structure 2200, according to an embodiment.

[0026] FIG. 23 illustrates a line drawing of an expanded octagonal flanged variation of a third octagonal Hunter structure 2300, according to an embodiment.

[0027] FIG. 24 illustrates a structural drawing of an expanded octagonal flanged variation of a fourth octagonal Hunter structure 2400, according to an embodiment.

[0028] FIG. 25 illustrates a line drawing of a circular flanged variation of the circular Hunter structures 2500, according to an embodiment.

[0029] FIG. 26 illustrates a line drawing of tessellating octagons 2600, according to an embodiment.

[0030] FIG. 27 illustrates the formation of an octagonal flanged lattice structure components 2700, according to an embodiment.

[0031] FIG. 28 illustrates a line drawing of the formation of a first group of modularly bonded Hunter structures 2800, according to an embodiment.

[0032] FIG. 29 illustrates modularly bonded Hunter structures 2900.

[0033] FIG. 30 illustrates a first circular flanged variation of the Hunter structure 3000, according to an embodiment.

[0034] FIG. 31 illustrates a second circular flanged variation of the Hunter structure 3000, according to an embodiment.

[0035] FIG. 32 illustrates a third circular flanged variation of the Hunter structure 3000, according to an embodiment.

[0036] FIG. 33 illustrates a fourth circular flanged variation of the Hunter structure 3000, according to an embodiment.

[0037] FIG. 34 illustrates a fifth circular flanged variation of the Hunter structure 3000, according to an embodiment.

[0038] FIG. 35 illustrates a sixth circular flanged variation of the Hunter structure 3000, according to an embodiment.

[0039] FIG. 36 illustrates a seventh circular flanged variation of the Hunter structure 3000, according to an embodiment.

[0040] FIG. 37 illustrates an eighth circular flanged variation of the Hunter structure 3000, according to an embodiment.

[0041] FIG. 38 illustrates a ninth circular flanged variation of the Hunter structure 3000, according to an embodiment.

[0042] FIG. 39 illustrates a first hybrid propeller Hunter structure 3900, according to an embodiment.

[0043] FIG. 40 illustrates a second hybrid propeller Hunter structure 4000, according to an embodiment.

[0044] FIG. 41 illustrates a third hybrid propeller Hunter structure 4100, according to an embodiment.

[0045] FIGs. 42A-42B illustrate an angular hybrid propeller Matthai rolling cage 4200, according to an embodiment.

[0046] FIGs. 43 A-43B illustrate a circular hybrid propeller Matthai rolling cage 4300, according to an embodiment.

[0047] FIG. 44 illustrates a first hybrid propeller Matthai variation rolling cage 4400, according to an embodiment.

[0048] FIG. 45 illustrates a second hybrid propeller Matthai variation rolling cage 4500, according to an embodiment.

[0049] FIG. 46 illustrates a third hybrid propeller Matthai variation rolling cage 4600, according to an embodiment.

[0050] FIG. 47 illustrates a fourth hybrid propeller Matthai variation rolling cage 4700, according to an embodiment.

[0051] FIG. 48 is a flowchart depicting a method 4800 of operating an aerial vehicle, according to an embodiment.

[0052] FIG. 49 illustrates a block diagram schematic of various components of a vehicle control system 4900, according to an embodiment.DETAILED DESCRIPTION

[0053] Dynamic Prop Configurations

[0054] Current aviation technology does not provide consumer-friendly multidirectional aircraft that are affordable while offering sufficient lift, power, safety, reliability, and control for consumer use. Traditional vehicles lack the geometric characteristics required for producing versatile aircraft capable of full freedom of motion and maneuverability. This capability enables movement in any direction, rotation about any axis, and stationary positioning in any chosen attitude. Generally, aviation technology does not include a variety of configurable and customizable drones that can bond into functional integrated swarms, working as a coherent unit towards a common goal while maintaining flight. The proposed geometries,including circular, spherical, hyperbolic, parabolic, and ecliptic designs, provide useful measurement tools for advancing STEM and redefining aeronautics. The presented super symmetrical structures particularly address the application of bondable omni-directional structures. Multi-directional movement and bonding are achieved using a variety of symmetrical arrangements that enhance vehicle efficiency, lift, stability, and scalability. Aircraft with thrust vectors oriented according to these geometries exhibit unique maneuvering capabilities not attainable with conventional designs.

[0055] Dynamic Propeller Configurations for Efficient Omni-Directional Flight

[0056] The design of the omni-directional drones employs advanced propeller technology that improves both operational efficiency and maneuverability. Unlike traditional fixed-propeller systems, the propellers in these lattice structures are adjustable, enabling them to tilt and reorient in real-time based on flight requirements. This capability broadens the operational scope of the drones, allowing them to execute a variety of aerial maneuvers with enhanced fluidity.

[0057] While the devices may be described herein with respect to propellers, other forms of propulsion may be used without departing from the scope of this disclosure. Examples of propulsion devices may include jet propulsion systems, such as turbofans or turbojets, which use the expulsion of high-velocity gases to generate thrust. Electromagnetic propulsion systems, such as ion thrusters or Hall-effect thrusters, are suitable for space applications, leveraging electrically charged particles to achieve propulsion. Additionally, biological or biomimetic propulsion systems, such as oscillating fins or undulating bodies, may mimic natural movements to generate propulsion in aquatic or aerial environments. These and other forms of propulsion may be implemented as alternatives to traditional propellers depending on the specific application or operating environment.

[0058] Omni-Directional Flight Mode

[0059] In omni-directional mode, the propellers tilt at angles specifically engineered to support stability and maneuverability across multiple axes. By adjusting the pitch and orientation of each propeller, the drone generates lift and thrust in various directions. This adaptability facilitates transitions between vertical and horizontal flight, allowing navigation through complex environments. The multi-axiscontrol provided by this configuration enables rapid direction changes, hovering, and diagonal movement without the limitations of traditional flight systems.

[0060] The modulation of thrust vectors through propeller tilting is advantageous in scenarios requiring precise positioning, such as search and rescue operations, industrial inspections, and aerial surveys. By optimizing thrust from each propeller, the drone maintains stability and control while executing maneuvers, improving the effectiveness and efficiency of its missions.

[0061] Transitioning to Standard Flight Mode

[0062] When the need for omni-directional flight decreases, the propellers transition to a horizontal plane. This reorientation is designed to optimize thrust output from each motor or energy generator, achieving full thrust capacity. In this configuration, the drones demonstrate increased speed and energy efficiency, making them suitable for longer distances or high-speed operations.

[0063] The ability to switch between omni-directional and horizontal flight modes provides a balance between maneuverability and energy conservation. By minimizing thrust reduction during these transitions, the drones sustain performance while maximizing fuel or battery efficiency. This feature is useful in applications requiring operational endurance, such as long-range deliveries, environmental monitoring, and sustained aerial photography.

[0064] Fuel and Battery Economy

[0065] The innovative design prioritizes aerodynamic performance and integrates advanced energy management systems. By enabling rapid mode transitions, the drones can engage in energy-saving tactics that extend operational time. In horizontal flight mode, the systems can operate efficiently, drawing on the motors’ full thrust capabilities, which results in reduced power consumption. During omni-directional operations, intelligent control systems optimize energy use to maintain flight stability without compromising responsiveness.

[0066] This dual-functionality and efficient energy use offer benefits for both commercial and consumer applications. Delivery services can use the drones’ adaptability to urban environments, optimizing flight paths to avoid obstacles while conserving battery life for return journeys. In industrial contexts, drones can shift between detailed inspections and rapid travel to different work sites, enhancing productivity and minimizing downtime.

[0067] The capacity for propeller tilting within the omni-directional drone lattice structures represents an advancement in drone technology. By enabling dynamic reorientation of thrust vectors, these drones achieve maneuverability, efficiency, and versatility. This approach redefines drone technology applications across various industries and positions these omni-directional drones as a leading force in the future of aerial mobility. The interplay between agility and efficiency facilitates possibilities for exploration, delivery, inspection, and more. These advanced lattice structures may be used to provide improved performance, efficiency, and adaptability across many applications.

[0068] Flange Adjustments

[0069] Alternatively, instead of tilting the propellers, the flanges themselves could shift the thrust vector between horizontal and tilted angles. Flange movement could be achieved using mechanisms similar to helicopter rotor control systems. This method may be less efficient and more mechanically complex compared to tilting the propellers or motors using hinges or other techniques.

[0070] Operation of an Omni-Directional lattice structure

[0071] An omni-directional drone can be operated using a controller in manual and GPS-assisted modes. For straightforward maneuvers, a conventional controller is sufficient, though a copilot may assist in manual operations for complex tasks. The pilot controls vehicle positioning while the copilot manages pitch and roll angles. Alternatively, virtual reality goggles and motion controllers can be used, allowing pilots to direct the vehicle by pointing and moving their heads.

[0072] While manual control is possible, automatic operation enhances maneuverability and capabilities. Autonomous midair docking and task performance rely on Al and machine learning. Distance sensors and docking mechanisms may be integrated into the design, allowing for advanced control strategies and software solutions.

[0073] An interface system where the user points in a given direction and the drone moves to that point in space optimizes the operation of an omni-directional drone. A connected app with a visual screen can give a user the point of view needed to provide directional information for the drone to use as it travels.

[0074] Alternative Structural Design for Omni-Directional Drones

[0075] An omni-directional chassis could be designed with minimal screws or bolts by employing tensegrity principles. This approach relies on tension andcompression to hold the structure together, reducing weight while increasing strength. The design may incorporate extrusion rods (e.g., T-slotted aluminum extrusions), to connect edges and provide a magnetic bonding mechanism for attachments. These rods would replace traditional motor arms and slide into a specially designed central core.

[0076] The propulsion devices would clamp onto these extrusion rods, with tensioner tuning rods connecting the core to 3D-printed connectors. This design could also adjust harmonic resonances during operation to minimize interference with flight control signals. A sturdy cable would be threaded through the extrusion rods and knotted to maintain chassis integrity. Depending on the specific configuration, the chassis may take the form of a platonic solid, Archimedean solid, or Catalan solid, optimizing both structural efficiency and aesthetic design.

[0077] Drone & Aerospace Applications: Personal Flight Vehicles

[0078] Innovation: The lattice structure introduces a new category of personal flight vehicles, allowing for advanced omni-directional flight capabilities that differ from traditional electric vertical take-off and landing (eVTOL) designs.

[0079] Applications: These adaptable structures can be configured in various sizes, accommodating individual passengers and larger setups for transporting goods or other living beings.

[0080] Features: The geometric design supports stability and smooth flight, aiming to provide a user-friendly experience while potentially making personal aviation more accessible and economically feasible.

[0081] Drone & Aerospace Applications: Drone Delivery Systems

[0082] Innovation: Lattice structures provide a solution to current limitations in unmanned aerial vehicle (UAV) delivery systems, particularly in densely populated urban environments.

[0083] Applications: These structures are well-suited for logistics and supply chain operations, enabling companies to deliver products efficiently in crowded spaces.

[0084] Features: The ability to integrate payloads at various points within or around the lattice enhances flexibility and load capacity, allowing for the transport of heavier items and effective navigation through complex urban landscapes.

[0085] Drone & Aerospace Applications: Bondable and Configurable Swarm Drones

[0086] Innovation: The properties of lattice structures facilitate the formation of multiple drones that can connect in midair, allowing for dynamic, super- symmetrical configurations.

[0087] Applications: This capability is particularly advantageous for military and law enforcement, enabling rapid deployment of temporary structures for surveillance, crowd control, or intelligence gathering.

[0088] Features: The ability to dock midair increases operational flexibility, enabling coordinated efforts among drones to create makeshift infrastructure or perform collaborative tasks with improved efficiency.

[0089] Drone & Aerospace Applications: Space Exploration

[0090] Innovation: Lattice structures can be engineered for space applications, particularly for maneuverability in the vacuum of space.

[0091] Applications and Benefits: These structures can withstand the unique conditions of extraterrestrial environments, allowing for effective operation under varying atmospheric pressures, gravitational forces, and the lack of gravitational forces, thus supporting the sustainable use of terrestrial and off-world resources.

[0092] Drone & Aerospace Applications: Oceanic Exploration and Environmental Research

[0093] Innovation: The design of lattice structures enhances capabilities for oceanic exploration and environmental monitoring.

[0094] Applications: These structures can support various marine tasks, including underwater exploration, data collection, and conservation efforts in challenging environments.

[0095] Features: Their versatile configurations adapt to different tasks, such as wildlife observation or search missions, providing support for ecological research and environmental protection initiatives.

[0096] Drone & Aerospace Applications: Film, Television Production, Aerial Photography, AR / VR

[0097] Innovation: Lattice structures can be equipped with advanced imaging technology, making them suitable for capturing high-quality visuals in film and media production.

[0098] Applications: These structures support various payloads for filmmakers, journalists, and AR / VR developers, enhancing creative storytelling through innovative aerial perspectives.

[0099] Features: The design reduces or minimizes obstruction in the camera’s field of view while increasing or maximizing views that traditional drones cannot capture. This allows for superior tracking and imaging capabilities that improve production quality across multiple media formats.

[0100] Drone & Aerospace Applications: Satellite Services

[0101] Innovation: The implementation of lattice structures in unmanned aerial systems addresses the last-mile challenges in satellite communication and 5G infrastructure.

[0102] Applications: These systems can establish a comprehensive mesh network, facilitating efficient data transmission for telecommunication companies and loT applications.

[0103] Features: Their adaptability for satellite functions, including antenna integration, enhances connectivity and service delivery across various industries, supporting the growing demand for reliable wireless communication.

[0104] Drone & Aerospace Applications: Industrial Inspection Services

[0105] Innovation: Lattice structures enhance capabilities for conducting inspections in complex and challenging environments.

[0106] Applications: These structures are useful in industries such as energy, oil, gas, and hazardous waste management. These industries often require access to confined or hazardous spaces.

[0107] Features: Equipped with high-resolution imaging technologies, these structures increase safety and reduce inspection costs. They provide detailed data collection capabilities, changing operational standards in industrial inspections. These drones can access places that other drones cannot reach.

[0108] Drone & Aerospace Applications: Industrial Manufacturing

[0109] Innovation: Lattice structures in additive manufacturing processes enable high-quality, customized 3D lattice composites.

[0110] Applications: These structures improve material efficiency in manufacturing. They enable complex designs and functional features that are traditionally difficult to achieve. Aerospace applications use lattice-based composites in components such as fuel nozzles and airframe substructures. These composites achieve weight reductions while maintaining thermal efficiency. This improves fuel economy and operational performance. The strength-to-weight ratio of lattice structures suits high-performance applications requiring fire resistance and impactabsorption. They integrate into aerospace panels to maintain structural integrity during extreme conditions, including atmospheric re-entry.

[0111] Features: They reduce production costs and time while enhancing material performance. This promotes advancements in manufacturing, leading to more innovative and sustainable practices.

[0112] Drone & Aerospace Applications: Search and Rescue Operations

[0113] Innovation: The lattice structure improves the functionality of unmanned aerial vehicles in search and rescue missions.

[0114] Applications: These drones navigate difficult terrains and collect realtime data for civil and military uses. This enhances situational awareness during operations.

[0115] Features: Their autonomous capabilities and ability to coordinate with other units facilitate information sharing and operational efficiency. This leads to improved outcomes in rescue missions.

[0116] Optical Applications

[0117] Display Systems: Advanced lattice configurations are used in programmable 3D internal structures for LED and liquid crystal displays (LCDs). By optimizing light distribution, these lattices improve color accuracy and energy efficiency. This allows for thinner, lighter display devices with enhanced visual performance.

[0118] Optical Lenses: Lattice structures are incorporated into the design of optical lenses. They control light pathways and focusing capabilities to improve visual clarity and resolution. Their unique geometry enables the creation of lightweight, high-performance lenses suitable for various applications from photography to augmented reality.

[0119] Biomedical Applications

[0120] Medical Implants and Prosthetics: Lattice structures feature customizable and biomimetic designs. These designs reduce implant stiffness to closely match that of human bone. This mitigates stress shielding and promotes natural integration. The porosity and high surface area-to-volume ratio of these lattices enhance fluid flow, which supports tissue integration and regrowth.

[0121] Bioprinting and Regenerative Medicine: In bioprinting applications, lattice structures serve as supportive frameworks. They stabilize biological materialssuch as tissues, bones, and organs during the regeneration process. This capability is useful for developing engineered tissues and organs for transplantation.

[0122] Material Science and Nanotechnology: At molecular and nano scales, lattice configurations inspire novel material structures. These structures offer enhanced strength, flexibility, and adaptability. These frameworks support the design of advanced composite materials with superior mechanical properties for applications ranging from aerospace to biomedical engineering.

[0123] Renewable Energy Systems

[0124] Lattice structures offer potential for improving the design of solar panel arrays, wind turbine blades, and various energy capture systems. By arranging components for optimal spatial orientation, these frameworks can enhance the efficiency of energy collection and reduce the use of structural materials. This approach leads to more sustainable and cost-effective energy solutions.

[0125] Automotive Applications

[0126] Structural Components: In automotive design, lattice structures are used in engine components, chassis reinforcements, and crash-absorption systems. Their omnidirectional strength and resilience make them suitable for bumpers and impact zones. This use enhances vehicle safety by effectively absorbing energy during collisions.

[0127] Heat Management and Efficiency: Lattice configurations improve cooling and heat dissipation in automotive engines. This optimization contributes to overall vehicle performance and prolongs component lifespan. Their lightweight nature leads to better fuel efficiency and lower emissions.

[0128] Construction and Architectural Applications

[0129] Reinforcement Materials: Modular lattice structures enhance composite material performance in construction. They provide resistance to compression, tension, and shear stresses. This results in high strength-to-weight ratios, shock absorption, and increased structural flexibility. These properties are valuable in high-stress environments such as bridges and high-rise buildings.

[0130] Energy Absorption and Collapse Control: Lattice materials offer controlled collapse responses under load. They outperform traditional metallic foams in energy absorption and reliability. This feature ensures the safety and resilience of structures subjected to dynamic loads, such as earthquakes or high winds.

[0131] Architectural Components: Lattice structures can be integrated into various architectural elements, including doors, floors, and furniture. Their lightweight yet durable design enhances thermal management and shock resistance. This contributes to sustainable and efficient building practices. Their structure also makes them suitable for providing improved scaffolding structures.

[0132] Robotics

[0133] The adaptable geometry of lattice structures enhances mobility and flexibility in robotic systems. This is particularly useful for compact and confined operational spaces. By using spatially efficient, multi-directional frameworks, robotics designs can achieve greater agility. This is essential for performing complex maneuvers in constrained environments.

[0134] Enhanced Signal Reception and Transmission

[0135] Lattice geometries enable multi-directional signal acquisition without requiring physical reorientation. This feature benefits satellites and ground-based antennas that maintain communication with various sources or switch between signals quickly. These geometries support compact, spatially efficient structures that maximize surface area and enhance signal capture. Reducing the size and weight of antenna dishes can lower launch and payload costs for satellites.

[0136] The stability of lattice configurations provides resilience against atmospheric drag and impacts from micro-meteorites. This stability helps extend the operational lifespan of satellites and antennas in space. Traditional satellite dishes need actuators or motors to align with target signals. Omnidirectional lattice frameworks minimize the need for such adjustments. This conserves energy resources for prolonged satellite functionality. Ground-based communication arrays can use lattice geometries for consistent signal strength, ensuring network reliability regardless of satellite orientation or movement in orbit.

[0137] Complex Data Representation & Error Detection / Correction Applications

[0138] The spatial relationships inherent in lattice structures facilitate frameworks for visualizing and modeling complex datasets, particularly in genomics, meteorology, and financial modeling. By translating data into multi-dimensional geometries, users can detect patterns and correlations that traditional methods might miss.

[0139] Lattice structures enhance data transmission reliability through geometric redundancy, which serves as a spatial checksum. This allows for error detection based on deviations in angle relationships. Their symmetrical properties facilitate multi-dimensional error correction codes, improving transmission reliability without significant data overhead. This intrinsic fault tolerance identifies and corrects errors in high-noise environments, such as satellite communications. By assigning data to specific geometric positions, lattice configurations reduce errors from multipath interference and phase distortions, enhancing signal integrity. Additionally, their predictable patterns allow for immediate error detection, reducing latency and making them suitable for real-time applications, including quantum error correction, where they can stabilize quantum states for more robust systems.

[0140] FIG. 1 illustrates a rhombus flanged variation of a rhombus Matthai structure 100, according to an embodiment. The rhombus Matthai structure 100 includes twelve individual rhombus structures 110 joined on adjacent sides and at a common vertex.

[0141] The rhombus Matthai structure 100 represents a specific geometric variation within the Matthai structure design. This design facilitates mechanical stability and coupling with other Matthai structures. When used as an aerial vehicle, the structure supports omni-directional movement. FIG. 2 illustrates a floret pentagonal flanged variation of a pentagonal Matthai structure 200, according to an embodiment. The pentagonal Matthai structure 200 includes twelve individual pentagonal structures 210 joined on adjacent sides and at a common vertex.

[0142] The pentagonal configuration provides mechanical stability and the ability to couple with other Matthai structures. When implemented in bonded arrangements, this pentagonal Matthai structure can integrate into spatial crystalline cube lattices. When configured as an aerial vehicle, the pentagonal Matthai structure supports omni-directional movement through appropriate placement of propulsion devices. FIG. 3 illustrates a line drawing of a hexagonal flanged variation of a first hexagonal Matthai structure 300, according to an embodiment. The first hexagonal Matthai structure 300 includes twelve individual hexagonal structures 310 joined on adjacent sides and at a common cubic center structure 320.

[0143] The hexagonal flanged variation shows the Matthai structure's core strength attributes. The hexagonal shape improves mechanical stability and strength under both tension and compression. The hexagonal flanges are flush with adjacenthexagonal flanges. This facilitates manufacturing and bonding with other omnidirectional lattice structures. The design has spacious flanges that promote air circulation. The narrowing effect toward the center structure accelerates laminar airflow.

[0144] When configured as an aerial vehicle, the hexagonal Matthai structure maintains stability against external forces. It enables omni-directional movement through the placement of propulsion devices. The structure can be arranged in various spatial crystalline cube lattices. This makes it useful for constructing stable structures when bonded. In predictable lattice arrangements, the hexagonal Matthai structure bonds with Rhombic Dodecahedral structures. This enhances its versatility for various applications. The geometric properties of this hexagonal flanged variation facilitate space-filling capabilities while maintaining structural integrity during operation.

[0145] FIG. 4 illustrates a structural drawing of a hexagonal flanged variation of a second hexagonal Matthai structure 400, according to an embodiment. The second hexagonal Matthai structure 400 includes twelve individual hexagonal structures 410 joined on adjacent sides and at a common cubic center structure 420.

[0146] This hexagonal flanged variation displays the Matthai structure's core characteristics. The hexagonal layout allows efficient coupling with other Matthai structures while maintaining simple manufacturing due to the flush alignment of adjacent hexagonal flanges. When used as an aerial vehicle, the hexagonal Matthai structure supports omni-directional movement with well-placed propulsion devices.

[0147] FIG. 5 illustrates a circular flanged variation of the circular Matthai structures 500, according to an embodiment. The circular Matthai structure 500 includes twelve circular structures 510 joined on nearby tangent edges.

[0148] The flanges may be separated by 120 degrees, similar to the hexagonal flanged variation. The shape includes twelve circular flanges extending inward and outward due to the shape’s fractional ability. The structure has six planes, similar to the hexagonal flanged variation. One or more flanges may be on each plane.

[0149] Advantages of the circular variation include increased structural support. The chassis design generates balanced airflow. Curved configurations like elliptic, hyperbolic, or parabolic shapes support this effect. Relationships between propellers and angles of incidence create aerodynamic airflow that supports omnidirectional movement.

[0150] Further modifications may improve bonding potential. Changing the flange edge length to include a coupling mechanism can bond or separate multiple omni-directional structures.

[0151] The hexagonal shape may be used to provide improved mechanical stability. The hexagonal shape reduces surface tension and stress. Hexagonal flanges on a Matthai structure facilitate coupling with other structures. Circular or wide angular flanges promote cooling of circulated air. Compared to traditional aircraft, this design remains stable against external forces. Bonded Matthai structures form stable spatial lattices. A resonate material may be implemented into the structural design to may be used during the fabrication process to produce vibration for various applications. The Matthai structure may serve as a UAV or personal flight vehicle.

[0152] FIG. 6 illustrates tessellated hexagons 600, according to an embodiment. The tessellated hexagons 600 are shown as a flattened tessellated hexagon configuration 610, a deflected tessellated hexagon configuration 620, and a connected tessellated hexagon configuration 630.

[0153] The tessellated hexagon configurations demonstrate how hexagonal structures can be arranged and modified to create various geometric patterns and structural arrangements. These tessellated configurations provide a foundation for understanding how the structures can be combined and modified to form larger compound structures while maintaining their geometric properties. The flattened configuration 610 shows the basic tessellation pattern. The deflected configuration 620 demonstrates how the hexagons can be modified to create different spatial arrangements. The connected configuration 630 illustrates how the hexagonal structures can be joined to form integrated assemblies. These tessellated patterns are relevant for applications requiring efficient space-filling capabilities and structural stability. These applications include the construction of modular structures or the development of bondable omni-directional structures. The tessellation patterns enable the creation of stable spatial lattices that can be used for various applications.

[0154] FIG. 7 illustrates formation of an omni-directional hexagonal flanged lattice structure 700, according to an embodiment. The omni-directional hexagonal flanged lattice structure 700 may include a first hexagonal flanged lattice 710, a second hexagonal flanged lattice 720, and a third hexagonal flanged lattice 730. The first hexagonal flanged lattice 710, second hexagonal flanged lattice 720, and the thirdhexagonal flanged lattice 730 may combine to form a hexagonal Matthai structure, such as the first hexagonal Matthai structure 300 shown in FIG. 3.

[0155] The modular formation shows the Matthai structure's ability to be assembled from component lattices while retaining enhanced mechanical stability and strength under tension and compression. The hexagonal flanged configuration allows efficient coupling between the component lattices and maintains manufacturing simplicity through the alignment of adjacent hexagonal flanges. When assembled, the structure includes the benefits of the Matthai design. The structure can be used as an aerial vehicle that supports omni-directional movement with propulsion devices. The structure can be arranged in spatial crystalline cube lattices.

[0156] FIG. 8 illustrates formation of modularly bonded Matthai structures 800. The modularly bonded Matthai structures 800 may include a first hexagonal Matthai structure 810 and a second hexagonal Matthai structure 820. The first hexagonal Matthai structure 810 and the second hexagonal Matthai structure 820 may combine to form a combined modularly bonded Matthai structure, such as shown in FIG. 9.

[0157] The modular bonding capability shows the Matthai structure's ability to create larger compound structures. FIG. 9 illustrates modularly bonded Matthai structures 900. The modularly bonded Matthai structures 900 may include a first hexagonal Matthai structure 910 and a second hexagonal Matthai structure 920. As shown in FIG. 8, the first hexagonal Matthai structure 910 and the second hexagonal Matthai structure 920 may combine to form a combined modularly bonded Matthai structure 900.

[0158] The combined structure demonstrates the Matthai design's capability to create larger compound structures while maintaining enhanced mechanical stability and increased strength under both tension and compression. The combined structure preserves the advantages of the Matthai design. FIG. 10 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1000, according to an embodiment. The hexagonal Matthai structure 1000 includes twelve hexagonal structures 1010 joined to form an inner cube 1020.

[0159] Flanges may be proportionally angled at 120° relative to adjacent flanges, with adjacent flanges sharing connected vertices. The twelve hexagonal flanges may extend inward or outward based on the shape’s fractional capability.

[0160] From a horizontal plane perspective, each propeller shaft is angled at 135°. One or more (e.g., 12) propellers, either with a single curved blade or a plurality of cupped blades, may surround the central hub. A propeller may use as few as one curved blade and optionally a blade counterweight to generate airflow.

[0161] One or more (e.g., 12) independent thrust vectors may attach to the structure. Due to the symmetrical properties of this multi-rotor structure, it can generate thrust in various directions. The propellers can be arranged in either clockwise or counterclockwise orientation. Bidirectional motors and propellers can produce bidirectional thrust, allowing for dedicated control of direction and rotation during flight.

[0162] When propellers are angled at 45° from a horizontal plane perspective, there is a loss of thrust of 50% per motor. Despite fixed positions of propulsion at 45° angles from a horizontal plane, the drone maintains a positive thrust-to-weight ratio and generates adequate lift to enable flight.

[0163] Advantages of any angular variation include the ability of the Matthai structure’s flange edges to vary and potentially include any number of edges or divisions. Hexagonal flanges allow each flange to be flush with another adjacent hexagonal flange, maintaining simplicity in manufacturing. This also provides large external edges for the structure to bond with other omni-directional structures. Considering efficiency with angular design, hexagonal flanges for a Matthai structure may offer improved performance compared to other structural designs, such as the rhombic flanged variation.

[0164] Further modifications of any angular variation may include reducing angular edges around the UAV’s frame to improve maneuverability in flight. This may involve modifying straight lines to reduce sharp vertices that diminish the aerodynamic potential of the vehicle.

[0165] FIG. 11 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1100, according to an embodiment. The hexagonal Matthai structure 1100 includes twelve hexagonal structures 1110. Within each of the twelve hexagonal structures 1110, a ducted propeller 1120 or other propulsion device may be disposed.

[0166] Configured as an aerial vehicle with ducted propellers 1120, the hexagonal Matthai structures propulsion devices can be arranged clockwise or counterclockwise. Bidirectional motors and propellers generate thrust for directionalcontrol and rotation during flight. The structure can form various spatial crystalline cube lattices. It is effective for constructing stable structures in bonded configurations.

[0167] FIG. 12 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1200, according to an embodiment. The hexagonal Matthai structure 1200 includes twelve hexagonal structures 1210 joined to form an inner cube 1220.

[0168] FIG. 13 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1300, according to an embodiment. The hexagonal Matthai structure 1300 includes twelve hexagonal structures 1310. Within each of the twelve hexagonal structures 1310, a ducted propeller 1320 or other propulsion device may be disposed.

[0169] When configured as an aerial vehicle with ducted propellers 1320, the hexagonal Matthai structure supports omni-directional movement. The propulsion devices can be arranged in either clockwise or counterclockwise orientation. FIG. 14 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1400, according to an embodiment. The hexagonal Matthai structure 1400 includes twelve hexagonal structures 1410 joined to form an inner cube 1420.

[0170] FIG. 15 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1500, according to an embodiment. The hexagonal Matthai structure 1500 includes twelve hexagonal structures 1510. Within each of the hexagonal structures 1510, a ducted propeller 1520 or other propulsion device may be disposed.

[0171] When configured as an aerial vehicle with the ducted propellers 1520, the hexagonal Matthai structure supports omni-directional movement. The propulsion devices can be arranged in either clockwise or counterclockwise orientation.Bidirectional motors and propellers generate bidirectional thrust. This allows for dedicated control of direction and rotation during flight. FIG. 16 illustrates a first angular hexagonal flanged variation of the hexagonal Matthai structure 1600, according to an embodiment. The hexagonal Matthai structure 1600 includes twelve hexagonal structures 1610. Within each of the hexagonal structures 1610, a ducted propeller 1620 or other propulsion device may be disposed.

[0172] When configured as an aerial vehicle with the ducted propellers 1620, the hexagonal Matthai structure supports omni-directional movement. The propulsiondevices can be arranged in either clockwise or counterclockwise orientation. FIG. 17 illustrates a first hybrid propeller Matthai structure 1700, according to an embodiment. The omni-directional Matthai structure propeller arrangement 1700 includes twelve hexagonal structures 1710. Within each of the hexagonal structures 1710, a coplanar oriented propeller 1720 (e.g., oriented coplanar relative to the surrounding hexagonal duct) or a vertically oriented propeller 1730 (e.g., oriented vertical relative to gravity) or other propulsion device may be disposed.

[0173] The hexagonal flanged variation illustrates the Matthai structure's attributes of mechanical stability and increased strength under both tension and compression. The hexagonal configuration allows for efficient coupling with other structures while maintaining manufacturing simplicity through the alignment of adjacent hexagonal flanges. The dual propeller orientation options provide flexibility in thrust vector generation. This enables omni-directional movement. The propulsion devices can be arranged in either clockwise or counterclockwise orientation. FIG. 18 illustrates a second hybrid propeller Matthai structure 1800, according to an embodiment. The omni-directional Matthai structure propeller arrangement 1800 includes twelve hexagonal structures 1810. Within each of the hexagonal structures 1810, a horizontally oriented propeller 1820 (e.g., oriented horizontal relative to gravity) or a vertically oriented propeller 1830 (e.g., oriented vertical relative to gravity) or other propulsion device may be disposed.

[0174] The dual flight mode configuration illustrates the Matthai structure's adaptability in propulsion arrangements. The dual propeller orientation options, horizontal and vertical, offer flexibility in thrust vector generation. The system can operate efficiently in both standard and omni-directional flight modes. Horizontal propellers achieve maximum thrust output and energy efficiency. Vertical propellers support omni-directional capabilities, enabling complex maneuvers and precise positioning. Propulsion devices can be arranged in clockwise or counterclockwise orientation. The dual flight mode configuration supports rapid transitions between flight modes. It maintains energy efficiency, making it suitable for applications requiring both long-range travel and precise maneuvering capabilities.

[0175] FIG. 19 illustrates a third hybrid propeller Matthai structure 1900, according to an embodiment. The standard Matthai structure propeller arrangement 1900 includes twelve hexagonal structures 1910. Within each of the hexagonal structures 1910, a first set of horizontally oriented propellers 1920 (e.g., orientedhorizontal relative to gravity) and a second set of horizontally oriented propellers 1930 or other propulsion device may be disposed.

[0176] The dual horizontal propeller configuration optimizes thrust output and energy efficiency during standard flight mode. When operating with horizontal propellers, the system can achieve higher thrust capacity, which is suitable for longer distances or high-speed operations. The propulsion devices can be arranged in either clockwise or counterclockwise orientation. This standard flight mode configuration enables efficient energy use while maintaining performance and is suitable for applications requiring operational endurance, such as long-range deliveries, environmental monitoring, and aerial photography. The geometric properties of this standard configuration support efficient space-filling capabilities and maintain structural integrity during operation.

[0177] FIG. 20 illustrates a square flanged alternate variation of the square Hunter structures 2000, according to an embodiment. The square Hunter structures 2000 includes twelve square structures 2010 joined along adjacent sides that share a common vertex.

[0178] The square flanged variation demonstrates the Hunter structure's fundamental characteristics of enhanced maneuverability and structural stability. The structure's design enables efficient coupling with other Hunter structures while maintaining manufacturing simplicity through the alignment of adjacent flanges. When implemented as an aerial vehicle, this Hunter structure supports omnidirectional movement through the strategic placement of propulsion devices. The structure can be arranged in various spatial configurations, making it particularly effective for applications requiring precise positioning and control. The geometric arrangement allows for efficient space-filling capabilities while maintaining structural integrity during operation. The structure's frame allows for the integration of various components at available vertices, enhancing its utility for aerial tasks. When configured in bonded arrangements, multiple Hunter structures can combine to increase lifting capacity through enhanced thrust generation.

[0179] FIG. 21 illustrates a line drawing of an octagonal flanged variation of a first octagonal Hunter structure 2100, according to an embodiment. The first octagonal Hunter structure 2100 includes twelve octagonal structures 2110 joined along adjacent sides.

[0180] The octagonal flanged variation demonstrates the Hunter structure's characteristics of maneuverability and structural stability. The octagonal configuration allows efficient coupling with other Hunter structures while maintaining manufacturing simplicity through the alignment of adjacent octagonal flanges. When used as an aerial vehicle, this structure supports omni-directional movement through strategic placement of propulsion devices. The frame of the structure allows the integration of various components at available vertices, enhancing its utility for aerial tasks. When configured in bonded arrangements, multiple Hunter structures can combine to increase lifting capacity through enhanced thrust generation. The geometric properties of this octagonal flanged variation facilitate space-filling capabilities while maintaining structural integrity during operation. The structure can be arranged in various spatial configurations, making it effective for applications that require precise positioning and control.

[0181] FIG. 22 illustrates a structural drawing of an octagonal flanged variation of a second octagonal Hunter structure 2200, according to an embodiment. The first octagonal Hunter structure 2200 includes twelve octagonal structures 2210 joined along adjacent sides. When used as an aerial vehicle, this structure supports movement in any direction through the strategic placement of propulsion devices.

[0182] FIG. 23 illustrates a line drawing of an expanded octagonal flanged variation of a third octagonal Hunter structure 2300, according to an embodiment. The third octagonal Hunter structure 2300 includes twelve modified octagonal structures 2310 joined along adjacent sides.

[0183] The expanded octagonal flanged variation exhibits the Hunter structure's characteristics of maneuverability and structural stability. The modified octagonal design allows coupling with other Hunter structures and maintains simplicity in manufacturing through alignment of adjacent octagonal flanges. When used as an aerial vehicle, this structure supports omni-directional movement through strategic placement of propulsion devices.

[0184] FIG. 24 illustrates a structural drawing of an expanded octagonal flanged variation of a fourth octagonal Hunter structure 2400, according to an embodiment. The fourth octagonal Hunter structure 2400 includes twelve modified octagonal structures 2410 joined along adjacent sides.

[0185] FIG. 25 illustrates a line drawing of a circular flanged variation of the circular Hunter structures 2500, according to an embodiment. The circular Hunter structures 2500 includes circular structures 2510 joined along tangential sides.

[0186] The circular flanged variation shows the Hunter structure's fundamental characteristics of enhanced maneuverability and additionally increases structural stability. Fracture and structural damage may be reduced or minimized due to the design of the chassis. Pressure generated from the configurations of curves, such as elliptic, hyperbolic, and parabolic, enhances overall balance and stability. In contrast to planar fixed wing aircraft, the arched structure of the chassis, combined with propellers arranged according to geometric ratios, improves efficiency and airflow. This configuration supports omni-directional movement.

[0187] FIG. 26 illustrates a line drawing of tessellating octagons 2600, according to an embodiment. The tessellating octagons 2600 include a first flattened configuration of octagons 2610. The tessellating octagons 2600 include a second flattened configuration of octagons 2620, where inner octagon perimeters may be combined to form a square inner perimeter.

[0188] The tessellating octagonal configuration demonstrates how the structure can be modified and arranged in different planar configurations while maintaining its central characteristics. The ability to tessellate and reconfigure the octagonal structures enables efficient space-filling capabilities and versatile structural arrangements. When the inner octagon perimeters are combined to form a square inner perimeter in configuration 2620, the structure provides enhanced stability and manufacturing simplicity through the geometric alignment of components. This tessellating capability supports the structure's potential for modular bonding and integration with other components, particularly useful in applications requiring scalable and reconfigurable geometries.

[0189] The flattened configurations illustrate how the octagonal structures can be arranged to optimize spatial efficiency while maintaining the structural integrity needed for various applications. These tessellating arrangements can serve as the foundation for more complex three-dimensional structures when implemented in aerial vehicle applications.

[0190] FIG. 27 illustrates a line drawing of octagonal flanged lattice structure components 2700, according to an embodiment. The octagonal flanged lattice structure components 2700 may include a first set of four octagons 2710 arrangedvertically, a second set of four octagons 2720 arranged horizontally, and a third set of four octagons 2730 arranged vertically. The octagon sets may be combined to form an octagonal flanged lattice structure 2740.

[0191] The octagonal configuration allows for efficient coupling with other structures, maintaining manufacturing simplicity through the alignment of adjacent octagonal flanges. The geometric arrangement demonstrates the structure's ability to be modified and arranged in different spatial configurations while retaining its characteristics of maneuverability and structural stability. When used in an aerial vehicle application, this lattice structure maintains structural integrity during operation and enables omni-directional movement through the placement of propulsion devices.

[0192] The capability to combine multiple octagonal sets into a unified lattice structure 2740 supports the potential for modular bonding and integration. This is useful in applications requiring scalable and reconfigurable geometries. The geometric properties of the lattice configuration facilitate efficient space-filling while providing stability for various applications. The structure's frame allows the integration of various components at available vertices. When arranged in bonded configurations, multiple lattice structures can combine to increase lifting capacity through additional thrust generation. This makes it useful for applications requiring precise positioning and control.

[0193] FIG. 28 illustrates a line drawing of the formation of a first group of modularly bonded Hunter structures 2800, according to an embodiment. The first group of modularly bonded Hunter structures 2800 may include a first octagonal Hunter structure 2810 and a second octagonal Hunter structure 2820. The symmetrical properties of the geometry allow multiple aircraft to be connected at different orientations in flight, enabling midair docking for collaborative tasks. The first octagonal Hunter structure 2810 and the second octagonal Hunter structure 2820 may combine to form a combined modularly bonded Hunter structure, such as shown in FIG. 29.

[0194] FIG. 29 illustrates modularly bonded Hunter structures 2900. The modularly bonded Hunter structures 2900 may include a first octagonal Hunter structure 2910 and a second octagonal Hunter structure 2920. As shown in FIG. 28, the first octagonal Hunter structure 2910 and the second octagonal Hunter structure 2920 may combine to form a combined modularly bonded Hunter structure 2900.

[0195] The modular bonding capability illustrates the Hunter structure's characteristics of improved maneuverability and structural stability when combined with other Hunter structures. The octagonal configuration allows efficient coupling between structures while maintaining manufacturing simplicity through flush alignment of adjacent octagonal flanges. When configured in bonded arrangements, multiple Hunter structures can combine to increase lifting capacity through enhanced thrust generation. The symmetrical properties of the geometry allow multiple aircraft to connect at different orientations during flight, enabling midair docking for collaborative tasks. FIG. 30 illustrates a first circular flanged variation of the Hunter structure 3000, according to an embodiment. The Hunter structure 3000 includes twelve combined modified semicircular structures 3010.

[0196] Angles of flanges are 90° in relation to adjacent propeller flanges that share connected vertices. Flanges have 12 round, circular extensions that either extend inward or outward. Propellers can be attached to the aircraft in various orientations. There are eight planes, with multiple curved propulsion devices stationed on each. Propeller shafts are angled at 109.4712206° in relation to adjacent shafts, substantially equal to 109.5°. From a horizontal plane perspective, each propeller shaft is angled at 55°.

[0197] Propellers have one or more blades that surround the central hub. A counterweight may be used if there is only one blade. The structure struggles to produce lift because the fixed propeller positions at 55° angles result in a loss of thrust beyond 70%. While powerful, the thrust-to-weight ratio is low, preventing sufficient lift. This structure may perform well in space with alternative propulsion methods, despite challenges on Earth.

[0198] Further modifications could improve bonding potential by changing edge lengths to allow coupling mechanisms. The chassis will need redesigning to accommodate these changes. One or more flange areas may include propulsion devices. Propellers have specific spin directions which may be mirrored or reversed.

[0199] The Hunter structure design could become popular in the UAV market due to its symmetrical properties. It might be outfitted with materials to produce vibration for various applications. The structure resembles Calcium Hexaboride, which has thermoelectric and superconductive properties. With proper material design, the UAV may convert atmospheric heat into electrical energy.

[0200] FIG. 31 illustrates a second circular flanged variation of the Hunter structure 3000, according to an embodiment. The Hunter structure 3100 includes twelve combined modified semicircular structures 3110. Propulsion devices placed on or connected to the nodes of this structure support omni-directional thrust.

[0201] FIG. 32 illustrates a third circular flanged variation of the Hunter structure 3000, according to an embodiment. The Hunter structure 3200 includes twelve combined modified semicircular structures 3210. Propulsion devices placed on or connected to the nodes of this structure support omni-directional thrust.

[0202] FIG. 33 illustrates a fourth circular flanged variation of the Hunter structure 3000, according to an embodiment. The Hunter structure 3300 includes twelve combined modified semicircular structures 3310. The symmetrically proportional relationships between propellers and their angles of incidence create aerodynamic airflow.

[0203] In contrast to planar fixed wing aircraft, the arched structure of the chassis combined with propellers arranged according to geometric ratio improves efficiency and airflow that supports omni-directional movement. The structure's versatile frame allows for the integration of various components at available vertices, enhancing its utility for aerial tasks.

[0204] FIG. 34 illustrates a fifth circular flanged variation of the Hunter structure 3000, according to an embodiment. The Hunter structure 3400 includes twelve combined modified semicircular structures 3410.

[0205] FIG. 35 illustrates a sixth circular flanged variation of the Hunter structure 3000, according to an embodiment. The Hunter structure 3500 includes twelve combined modified semicircular structures 3510, eight propulsion mechanisms 3520, and one or more power sources 3530.

[0206] The circular flanged variation displays the Hunter structure's primary features of maneuverability and structural stability. Fragmentation is reduced by the engineered design of the chassis. Configurations that are curvy, elliptic, hyperbolic, and parabolic generate airflow that improves balance and stability. The symmetrical relationships between propellers and their angles of incidence create aerodynamic airflow that support omni-directional movement. The propulsion mechanisms are arranged to optimize thrust generation while maintaining stability. The frame can integrate various components at vertices, enhancing functionality for aerial tasks.When configured in bonded arrangements, multiple Hunter structures can combine to increase lifting capacity through enhanced thrust generation.

[0207] FIG. 36 illustrates a seventh circular flanged variation of the Hunter structure 3000, according to an embodiment. The Hunter structure 3600 includes twelve combined modified semicircular structures 3610, eight propulsion mechanisms 3620, and one or more power sources 3630.

[0208] FIG. 37 illustrates an eighth circular flanged variation of the Hunter structure 3000, according to an embodiment. The Hunter structure 3700 includes twelve combined modified semicircular structures 3710.

[0209] FIG. 38 illustrates a ninth circular flanged variation of the Hunter structure 3000, according to an embodiment. The Hunter structure 3800 includes twelve combined modified semicircular structures 3810, eight propulsion mechanisms 3820, and one or more power sources 3830.

[0210] FIG. 39 illustrates a first hybrid propeller Hunter structure 3900, according to an embodiment. The horizontal propeller Hunter structure 3900 may include twelve modified octagonal structures 3910, eight vertical propellers 3920, and four horizontal propellers 3930. The first hybrid propeller Hunter structure 3900 may provide improved omni-directional flight.

[0211] The first hybrid propeller Hunter structure 3900 flanges may be angled at 90° in relation to adjacent flanges. The structure includes 12 octagonal flanges that extend inward or outward. There are three planes, with one or more flanges stationed on each plane. One or more independent thrust vectors can be attached to the aircraft with various orientations. The symmetrical properties of this multi-rotor structure enable it to produce thrust in any direction. The propellers can be arranged in either clockwise or counterclockwise orientation. Bidirectional motors and propellers generate bidirectional thrust and allow for control of direction and rotation during flight.

[0212] The flanges can have any number of edges and divisions. Octagonal flanges are flush with adjacent octagonal flanges, maintaining simplicity in manufacturing. They provide large external edges for bonding with other omnidirectional structures. Octagonal flanges are considered the optimal choice for efficiency. Multiple flight mode configurations can be used to enhance the structure’s efficiency.

[0213] FIG. 40 illustrates a second hybrid propeller Hunter structure 4000, according to an embodiment. The second hybrid propeller Hunter structure 4000 may include twelve modified octagonal structures 4010, eight horizontal propellers 4020, and four additional horizontal propellers 4030. The second hybrid propeller Hunter structure 4000 may provide improved flight efficiency, such as for hover applications.

[0214] The second hybrid propeller configuration demonstrates the Hunter structure's characteristics of enhanced maneuverability and structural stability. The octagonal configuration allows efficient coupling between structures. It maintains manufacturing simplicity by aligning adjacent octagonal flanges flush. The horizontal propeller arrangement provides improved flight efficiency compared to angled configurations. It is particularly useful for applications requiring sustained hover capabilities.

[0215] FIG. 41 illustrates a third hybrid propeller Hunter structure 4100, according to an embodiment. The third hybrid propeller Hunter structure 4100 may include twelve modified octagonal structures 4110, eight horizontal propellers 4120, and four vertical propellers 4130. The third hybrid propeller Hunter structure 4100 may provide improved flight in both horizontal and hover flight.

[0216] The hybrid propeller configuration demonstrates the Hunter structure's characteristics of improved maneuverability and structural stability. The octagonal configuration allows efficient coupling between structures. It maintains manufacturing simplicity through the alignment of adjacent octagonal flanges. The combination of horizontal and vertical propellers optimizes thrust generation for forward flight and hover capabilities. The dual-mode propeller configuration provides versatility by enabling efficient horizontal flight while maintaining hover performance. When configured in bonded arrangements, multiple Hunter structures can combine. The structure's frame allows for the integration of various components at available vertices, enhancing its utility for aerial transportation and delivery tasks.

[0217] FIGs. 42A-42B illustrate an angular hybrid propeller Matthai rolling cage 4200, according to an embodiment. FIG. 42A shows the angular hybrid propeller Matthai rolling cage 4200 from a perspective viewpoint, and FIG. 42B shows the angular hybrid propeller Matthai rolling cage 4200 from a top-front-right viewpoint. The angular hybrid propeller Matthai rolling cage 4200 may include a rolling cage 4210, which may include a plurality of hexagonal structures 4220. Each of the plurality of hexagonal structures 4220 may include a propulsion device 4230.

[0218] The design allows the angular Matthai structure to roll on both even and uneven surfaces. Circular external rings connect to the edges of the outermost hexagonal flanges. The figure currently shows six external and circular rings attached to the angular Matthai structure. This configuration provides at least three degrees of freedom similar to pitch, yaw, and roll. Additional circles may be added to the external cage to enhance movement freedom, which is not shown in the current figure. In combination with omni-directional propeller arrangements, this circular and spherical cage design illustrates wheels within wheels. A gimbal system may be applied to decouple internal movement from the external cage structure. This design offers protection for the propulsion and electronic systems contained within. The gimbal system may include a multi-axis gimbal (e.g., 3-axis gimbal). Alternatively, one or more concentric rings (e.g., ball bearing rings) may be used to decouple internal and external movements.

[0219] FIGs. 43 A-43B illustrate a circular hybrid propeller Matthai rolling cage 4300, according to an embodiment. FIG. 43A shows the circular hybrid propeller Matthai rolling cage 4300 from a perspective viewpoint, and FIG. 43B shows the circular hybrid propeller Matthai rolling cage 4300 from a top-front-right viewpoint. The circular hybrid propeller Matthai rolling cage 4300 may include a rolling cage 4310, which may include a plurality of circular structures 4320. Each of the plurality of circular structures 4320 may include a propulsion device 4330.

[0220] The circular flanged Matthai structure includes a circular cage design. This structure may be complex to fabricate but will provide increased internal and external strength due to its arched curvature. The outermost portion of the circular flanges has a straight angular strut so that the flanges will not impede movement of the external cage. Similar to the angular Matthai structure with hexagonal flanges, this figure illustrates six external circular rings attached to the structure.

[0221] FIG. 44 illustrates a first hybrid propeller Matthai variation rolling cage 4400, according to an embodiment. The first hybrid propeller Matthai variation rolling cage 4400 includes a rolling cage 4410, which is disposed around a cubic internal structure 4420. The cubic internal structure 4420 includes a plurality of propeller struts 4430, where each propeller strut includes a propeller configured to be substantially colinear with the strut.

[0222] This variation of the Matthai structure has one or more propellers angled at 35 degrees relative to a horizontal plane when in omni-directional flightmode. The propellers attach to armature that point inward towards the center of mass of the structure. It is important that the external circular cage is not directly connected to the propeller arms, allowing the propellers to transition between a coplanar flight mode and an omni-directional flight mode. Each propeller is connected to one end of a propulsion arm, not both ends, permitting unrestricted tilting during flight mode changes. The propellers connect to the inner structure rather than the external cage. This configuration facilitates optimal airflow without air interference from the propellers. The central cubic core of the structure connects to six rectangular spaces along imaginary X, Y, and Z axes. These spaces can serve various purposes, such as structural support, electronic housing, storage, attachment housing, and camera placement. An internal hyperbolic, curved cube can provide additional support to the structure. Curved or straight octahedral struts also support the core of the structure. An alternative design includes propeller arms extending to an outer cube, resembling a geometric tesseract with propulsion affixed to the connecting arms. However, this alternative design would not support the transition between omni-directional and coplanar flight modes, resulting in limited functionality.

[0223] FIG. 45 illustrates a second hybrid propeller Matthai variation rolling cage 4500, according to an embodiment. The second hybrid propeller Matthai variation rolling cage 4500 may include a rolling cage 4510, which may be disposed around a cubic internal structure 4520. The cubic internal structure 4520 may include a plurality of propeller struts 4530, where each propeller strut includes a propeller that may be configured to be substantially horizontal.

[0224] FIG. 46 illustrates a third hybrid propeller Matthai variation rolling cage 4600, according to an embodiment. The third hybrid propeller Matthai variation rolling cage 4600 includes a rolling cage 4610, which is disposed around a curved cubic internal structure 4620. The curved cubic internal structure 4620 includes a plurality of smaller curved rhomboid structures 4625. The curved cubic internal structure 4620 includes a plurality of propeller struts 4630, where each propeller strut includes a propeller that is configured to be substantially colinear with the strut.

[0225] This variation of the Matthai structure features propellers angled at 35 degrees relative to a horizontal plane when in omni-directional flight mode. The propellers are attached to armature that point inward towards the center of mass of the structure. The external circular cage is not directly connected to the propeller arms, allowing the propellers to transition between a coplanar flight mode and an omni-directional flight mode. Each propeller is connected to one end of a propulsion arm, not both ends, permitting unrestricted tilting during flight mode changes.

[0226] FIG. 47 illustrates a fourth hybrid propeller Matthai variation rolling cage 4700, according to an embodiment. The fourth hybrid propeller Matthai variation rolling cage 4700 may include a rolling cage 4710, which may be disposed around a curved cubic internal structure 4720. The curved cubic internal structure 4720 may include a plurality of smaller curved rhomboid structures 4725. The curved cubic internal structure 4720 may include a plurality of propeller struts 4730, where each propeller strut includes a propeller that may be configured to be substantially horizontal.

[0227] Each of the strut-mounted propellers described herein may be mounted on a 3-axis gimbal. The 3-axis gimbal may allow the propeller to rotate freely in three dimensions, to be locked in a particular orientation, or to be actively steered to a predetermined orientation. For example, the plurality of propeller struts 4630 in the third hybrid propeller Matthai variation rolling cage 4600 may be reoriented to the horizontal structure of the plurality of propeller struts 4730 in the third hybrid propeller Matthai variation rolling cage 4600.

[0228] Each of the rolling cage configurations shown and described with respect to FIGs. 42A-47 may include a 3-axis gimbaled inner structure. The 3-axis gimbal may allow the gimbaled inner structure to rotate freely in three dimensions, to be locked in a particular orientation, or to be actively steered to a predetermined orientation. In an example, curved cubic internal structure 4720 and the plurality of propeller struts 4730 may be actively rotated to provide propulsion in a particular direction. In another example, the gimbaled inner structure may be configured to maintain an upright position (e.g., the direction substantially opposite from the gravity force vector), such as to ensure that a GPS antenna maintains an upright view of the sky.

[0229] Each of the rolling cage configurations shown and described with respect to FIGs. 42A-47 may be configured to operate in a rolling mode, operate in a flight mode, and transition smoothly between the rolling mode and the flight mode. In an example, the rolling mode may be used to conserve energy, or when the structure is intended to maintain as low of elevation as possible. In another example, the flight mode may be used to provide direct flight, such as when terrain is difficult to navigate efficiently.

[0230] The structures described herein can be implemented across physical realities, virtual realities, simulated realities, and alternate realities to enable advanced aerial vehicle capabilities. In physical reality applications, the structures support diverse operational configurations. The lattice designs accommodate various passenger and cargo transport requirements. The structures enable industrial inspection tasks in complex environments like energy facilities and hazardous sites. The geometric frameworks facilitate navigation through challenging terrain during search and rescue missions. The structures incorporate distance sensors and docking mechanisms to support autonomous operation.

[0231] For virtual reality implementations, the structures integrate with advanced visualization systems. The designs support augmented reality (AR) and virtual reality (VR) content creation through specialized imaging configurations. The control interfaces use virtual reality displays and motion tracking. Users can direct vehicle movement through intuitive pointing and head movement gestures. The structures enable real-time visual feedback through connected display applications.

[0232] The structures provide frameworks for simulated reality applications, such as for aerodynamic simulations. The geometric relationships support visualization of complex data patterns. The configurations enable testing of autonomous docking procedures through machine learning systems. The designs allow simulation of propulsion arrangements to analyze airflow dynamics. The structures facilitate evaluation of spatial efficiency and structural integrity.

[0233] In alternate reality environments, the structures adapt to different operational conditions. The designs function in space environments with varying gravitational forces and atmospheric pressures. The configurations support underwater exploration and data collection tasks. The structures establish communication networks through geometric arrangements in orbital environments.

[0234] While various interconnected flanges are described herein as hexagonal, octagonal, circular, and rhombic configurations, other polygonal configurations may be used. For example, the inner structures may include triangular, square, pentagonal, or other n-sided polygonal configurations.

[0235] FIG. 48 is a flowchart depicting a method 4800 of operating an aerial vehicle. Method 4800 includes providing 4810 a structural framework having a plurality of interconnected flanges arranged around a central space; generating 4820 thrust via thrust generating devices coupled to the structural framework; andcontrolling 4830 a plurality of thrust-generating devices to enable omni-directional movement of the aerial vehicle.

[0236] Method 4800 may further include transitioning the plurality of thrustgenerating devices between: a horizontal configuration for efficient forward flight; and an angled configuration for omni-directional movement. Transitioning may include adjusting orientation of the plurality of thrust-generating devices relative to a reference plane while maintaining thrust generation.

[0237] Method 4800 may further include connecting the aerial vehicle with one or more additional aerial vehicles during flight to form an integrated swarm.

[0238] Method 4800 may further include: operating in a first mode where the plurality of thrust-generating devices is oriented substantially horizontal to maximize thrust output and energy efficiency; and operating in a second mode where the plurality of thrust-generating devices is oriented at angles to enable complex maneuvers and precise positioning.

[0239] Method 4800 may further include coordinating thrust vectors from the plurality of thrust-generating devices to maintain stability against external forces. Method 4800 may further include enabling movement on surfaces via an external cage structure while maintaining flight capability. Method 4800 may further include operating in an autonomous control mode for midair docking operations.

[0240] Method 4800 may further include adjusting harmonic resonances during operation to minimize interference with flight control signals. Method 4800 may further include optimizing energy use through intelligent control systems to maintain flight stability without compromising responsiveness. Method 4800 may further include operating the plurality of thrust-generating devices in a bidirectional manner to control direction and rotation during flight. Connecting may include aligning coupling interfaces between multiple aerial vehicles; and maintaining operational capability while connected.

[0241] Method 4800 may further include transitioning between flight modes while maintaining positive thrust-to-weight ratio. Method 4800 may further include coordinating thrust generation between vertical and horizontal propellers to achieve desired flight characteristics. Method 4800 may further include operating in GPS- assisted mode for enhanced maneuverability and positioning.

[0242] FIG. 49 illustrates a block diagram schematic of various components of a vehicle control system 4900, such as may be used to implement the vehicles andstructures described herein. In general, system 4900 can include one or more of a memory 4902, a processor 4904, one or more antennas 4906, a communication module 4908, a network interface device 4910, a user interface 4912, and a power source 4914 (e.g., power supply). System 4900 may include a device affixed to a surface (e.g., wall, door), though system 4900 may also be a free-standing device or a portable device (e.g., mobile electronic device).

[0243] Memory 4902 can be used in connection with the execution of application programming or instructions by processor 4904, and for the temporary or long-term storage of executable instructions 4916 (e.g., program instructions, program instruction sets) or navigation data 4918, such as navigation device inputs, context data, or directive inputs. For example, memory 4902 can contain executable instructions 4916 that are used by the processor 4904 to run other components of system 4900 and generate navigation instructions based on navigation data 4918.

[0244] Memory 4902 can comprise a computer readable medium that can be any medium that can contain, store, communicate, or transport data, program code, or instructions for use by or in connection with system 4900. The computer readable medium can be, for example but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device. More specific examples of suitable computer readable medium include but are not limited to, an electrical connection having one or more wires or a tangible storage medium such as a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or EEPROM), Dynamic RAM (DRAM), any solid-state storage device, in general, a compact disc read-only memory (CD-ROM), or other optical or magnetic storage device. Computer readable media includes but is not to be confused with, computer readable storage medium, which is intended to cover all physical, non-transitory, or similar embodiments of computer readable media.

[0245] Processor 4904 can correspond to one or more computer processing devices or resources. For instance, processor 4904 can be provided as silicon, as a Field Programmable Gate Array (FPGA), an Application-Specific Integrated Circuit (ASIC), any other type of Integrated Circuit (IC) chip, a collection of IC chips, or the like. As a more specific example, processor 4904 can be provided as a microprocessor, Central Processing Unit (CPU), or plurality of microprocessors orCPUs that are configured to execute instructions sets stored in an internal memory 4920 or memory 4902.

[0246] Antenna 4906 may include one or more antennas, and may be configured to provide for wireless communications between, for example, system 4900 and one or more navigation input devices, user input devices, or navigation output devices. Antenna 4906 can be arranged to operate using one or more wireless communication protocols and operating frequencies such as the IEEE 802.15.1, Bluetooth, Bluetooth Low Energy (BLE), near field communications (NFC), ZigBee, GSM, CDMA, Wi-Fi, RF, UWB, and the like. By way of example, antenna 4906 may include RF antenna(s), and as such, may transmit or receive RF signals through free space to be received / transferred by another electronic device having an RF transceiver.

[0247] Communication module 4908 may be configured to communicate according to any suitable communications protocol with one or more different systems or devices either remote or local to system 4900, such as a control panel or external control device.

[0248] Network interface device 4910 includes hardware to facilitate communications with other devices, such as a control panel or host server over a communication network, using any one of a number of transfer protocols (e.g., frame relay, internet protocol (IP), transmission control protocol (TCP), user datagram protocol (UDP), hypertext transfer protocol (HTTP), etc.). Example communication networks can include a local area network (LAN), a wide area network (WAN), a packet data network (e.g., the Internet), mobile telephone networks (e.g., cellular networks), Plain Old Telephone (POTS) networks, wireless data networks (e.g., IEEE 802.11 family of standards known as Wi-Fi or IEEE 802.16 family of standards known as WiMax), networks based on the IEEE 802.15.4 family of standards, and peer-to-peer (P2P) networks, among others. In some examples, network interface device 4910 can include an Ethernet port or other physical jack, a Wi-Fi card, a Network Interface Card (NIC), a cellular interface (e.g., antenna, filters, and associated circuitry), or the like. In some examples, network interface device 4910 can include one or more antennas to wirelessly communicate using, for example, at least one of single-input multiple-output (SIMO), multiple-input multiple-output (MIMO), or multiple-input single-output (MISO) techniques.

[0249] User interface 4912 can include one or more input devices or display devices. Examples of suitable user input devices that may be included in user interface 4912 include without limitation, one or more buttons, a keyboard, a mouse, a touch- sensitive surface, a stylus, a camera, a microphone, a PIN pad, touch screen, fingerprint reader, magnetic stripe reader, chip reader, etc. Examples of suitable user output devices that may be included in user interface 4912 include without limitation, one or more LEDs, an LCD panel, a display screen, a touchscreen, one or more lights, a speaker, etc. It should be appreciated that user interface 4912 can also include a combined user input and user output device, such as a touch-sensitive display or the like.

[0250] Power source 4914 may be any suitable internal power source, such as a battery, capacitive power source or similar type of charge- storage device, etc., or can include one or more power conversion circuits suitable to convert external power into suitable power (e.g., conversion of externally supplied AC power into DC power) for components of the system 4900. Power source 4914 can also include some implementation of surge protection circuitry to protect the components of system 4900 from power surges.

[0251] System 4900 can also include one or more busses or interlinks 4922 operable to transmit communications between the various hardware components. A system bus or interlink 4922 may be any of several types of commercially available bus structures or bus architectures. A computing device manager may reconfigure the system 4900 by connecting a device to the system 4900 via bus or interlink 4922, such as by changing device parameters (e.g., configurable interpolling delays), by overwriting a device management policy, by updating software, by reflashing firmware, or other reconfigurations.

[0252] Additional examples of these features include the following:

[0253] Example 1 is an aerial vehicle comprising: a structural framework including a plurality of interconnected flanges arranged around a central space; and a plurality of thrust-generating devices operatively coupled to the structural framework; wherein the structural framework is configured to enable omni-directional movement of the aerial vehicle through operation of the plurality of thrust-generating devices.

[0254] In Example 2, the subject matter of Example 1 includes wherein the plurality of interconnected flanges includes twelve flanges.

[0255] In Example 3, the subject matter of Examples 1-2 includes wherein the plurality of thrust-generating devices include propellers configured to transition between a substantially horizontal orientation and an angled orientation relative to a reference plane.

[0256] In Example 4, the subject matter of Examples 1-3 includes wherein the structural framework includes coupling interfaces adapted for connecting to additional aerial vehicles during flight.

[0257] In Example 5, the subject matter of Examples 1-4 includes wherein the structural framework includes: a central core; and support members extending between the central core and the interconnected flanges.

[0258] In Example 6, the subject matter of Examples 1-5 includes an external cage structure including circular rings connected to outer edges of the interconnected flanges.

[0259] In Example 7, the subject matter of Examples 3-6 includes wherein: the horizontal orientation is configured for efficient hover flight; and the angled orientation is configured for omni-directional movement.

[0260] In Example 8, the subject matter of Examples 1-7 includes wherein the plurality of thrust-generating devices include mounting mechanisms configured to adjust orientation of the plurality of thrust-generating devices relative to the structural framework.

[0261] In Example 9, the subject matter of Examples 1-8 includes wherein the structural framework implements tensegrity principles.

[0262] In Example 10, the subject matter of Examples 1-9 includes wherein each interconnected flange includes a polygonal configuration.

[0263] In Example 11, the subject matter of Example 10 includes wherein the polygonal configuration includes at least one of: a hexagonal configuration; an octagonal configuration; a circular configuration; a rhombic configuration; or a pyramidal configuration.

[0264] In Example 12, the subject matter of Examples 6-11 includes wherein: the plurality of thrust-generating devices is coupled to the structural framework; and the structural framework rotates independent of the external cage structure.

[0265] In Example 13, the subject matter of Examples 1-12 includes compartments disposed along X, Y, and Z axes relative to the central space.

[0266] In Example 14, the subject matter of Examples 1-13 includes wherein adjacent flanges are configured to align flush with each other.

[0267] In Example 15, the subject matter of Examples 1-14 includes wherein the plurality of thrust-generating devices include: a first set configured for vertical thrust; and a second set configured for horizontal thrust.

[0268] In Example 16, the subject matter of Examples 1-15 includes wherein the structural framework includes: a hyperbolic curved internal support structure; and octahedral struts providing additional structural support.

[0269] Example 17 is a method of operating an aerial vehicle, comprising: providing a structural framework having a plurality of interconnected flanges arranged around a central space; generating thrust via thrust generating devices coupled to the structural framework; and controlling a plurality of thrust-generating devices to enable omni-directional movement of the aerial vehicle.

[0270] In Example 18, the subject matter of Example 17 includes transitioning the plurality of thrust-generating devices between: a horizontal configuration for efficient forward flight; and an angled configuration for omni-directional movement.

[0271] In Example 19, the subject matter of Example 18 includes wherein transitioning includes adjusting orientation of the plurality of thrust-generating devices relative to a reference plane while maintaining thrust generation.

[0272] In Example 20, the subject matter of Examples 17-19 includes connecting the aerial vehicle with one or more additional aerial vehicles during flight to form an integrated swarm.

[0273] In Example 21, the subject matter of Examples 17-20 includes operating in a first mode where the plurality of thrust-generating devices are oriented substantially horizontal to maximize thrust output and energy efficiency; and operating in a second mode where the plurality of thrust-generating devices are oriented at angles to enable complex maneuvers and precise positioning.

[0274] In Example 22, the subject matter of Examples 17-21 includes coordinating thrust vectors from the plurality of thrust-generating devices to maintain stability against external forces.

[0275] In Example 23, the subject matter of Examples 17-22 includes enabling movement on surfaces via an external cage structure while maintaining flight capability.

[0276] In Example 24, the subject matter of Examples 17-23 includes operating in an autonomous control mode for midair docking operations.

[0277] In Example 25, the subject matter of Examples 17-24 includes adjusting harmonic resonances during operation to minimize interference with flight control signals.

[0278] In Example 26, the subject matter of Examples 17-25 includes optimizing energy use through intelligent control systems to maintain flight stability without compromising responsiveness.

[0279] In Example 27, the subject matter of Examples 17-26 includes operating the plurality of thrust-generating devices in a bidirectional manner to control direction and rotation during flight.

[0280] In Example 28, the subject matter of Examples 20-27 includes wherein connecting includes: aligning coupling interfaces between multiple aerial vehicles; and maintaining operational capability while connected.

[0281] In Example 29, the subject matter of Examples 17-28 includes transitioning between flight modes while maintaining positive thrust-to-weight ratio.

[0282] In Example 30, the subject matter of Examples 17-29 includes coordinating thrust generation between vertical and horizontal propellers to achieve desired flight characteristics.

[0283] In Example 31, the subject matter of Examples 17-30 includes operating in GPS-assisted mode for enhanced maneuverability and positioning.

[0284] Example 32 is at least one machine-readable medium including instructions that, when executed by processing circuitry, cause the processing circuitry to perform operations to implement of any of Examples 1-31.

[0285] Example 33 is an apparatus comprising means to implement any of Examples 1-31.

[0286] Example 34 is a system to implement any of Examples 1-31.

[0287] Example 35 is a method to implement any of Examples 1-31.

[0288] The above detailed description includes references to the accompanying drawings, which form a part of the detailed description. The drawings show, by way of illustration, specific embodiments that may be practiced. These embodiments may also be referred to herein as “examples.” Such embodiments or examples can include elements in addition to those shown or described. However, the present inventors also contemplate examples in which only those elements shown ordescribed are provided. Moreover, the present inventors also contemplate examples using any combination or permutation of those elements shown or described (or one or more aspects thereof), either with respect to a particular example (or one or more aspects thereof), or with respect to other examples (or one or more aspects thereof) shown or described herein. That is, the above-described embodiments or examples or one or more aspects, features, or elements thereof may be used in combination with each other.

[0289] As will be appreciated by one of skill in the art, the various embodiments of the present disclosure may be embodied as a method (including, for example, a computer-implemented process, a business process, or any other process), apparatus (including, for example, a system, machine, device, computer program product, or the like), or a combination of the foregoing. Accordingly, embodiments of the present disclosure or portions thereof may take the form of an entirely hardware embodiment, an entirely software embodiment (including firmware, middleware, microcode, hardware description languages, etc.), or an embodiment combining software and hardware aspects. Furthermore, embodiments of the present disclosure may take the form of a computer program product on a computer-readable medium or computer-readable storage medium, having computer-executable program code embodied in the medium, that define processes or methods described herein. A processor or processors may perform the necessary tasks defined by the computerexecutable program code. In the context of this disclosure, a computer readable medium may be any medium that can contain, store, communicate, or transport the program for use by or in connection with the systems disclosed herein. As indicated above, the computer readable medium may be, for example but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device. More specific examples of suitable computer readable medium include but are not limited to, an electrical connection having one or more wires or a tangible storage medium such as a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable readonly memory (EPROM or Flash memory), a compact disc read-only memory (CD- ROM), or other optical, magnetic, or solid state storage device. As noted above, computer-readable media includes but is not to be confused with, computer-readable storage medium, which is intended to cover all physical, non-transitory, or similar embodiments of computer-readable media.

[0290] In the foregoing description various embodiments of the present disclosure have been presented for the purpose of illustration and description. They are not intended to be exhaustive or to limit the invention to the precise form disclosed. Obvious modifications or variations are possible considering the above teachings. The various embodiments were chosen and described to provide the best illustration of the principals of the disclosure and their practical application, and to enable one of ordinary skill in the art to use the various embodiments with various modifications as are suited to the particular use contemplated. All such modifications and variations are within the scope of the present disclosure as determined by the appended claims when interpreted in accordance with the breadth they are fairly, legally, and equitably entitled.

Claims

CLAIMSWhat is claimed is:

1. An aerial vehicle comprising: a structural framework including a plurality of interconnected flanges arranged around a central space; and a plurality of thrust-generating devices operatively coupled to the structural framework; wherein the structural framework is configured to enable omni-directional movement of the aerial vehicle through operation of the plurality of thrust-generating devices.

2. The aerial vehicle of claim 1, wherein the plurality of thrust-generating devices include propellers configured to transition between a substantially horizontal orientation and an angled orientation relative to a reference plane.

3. The aerial vehicle of claim 1, wherein the structural framework includes coupling interfaces adapted for connecting to additional aerial vehicles during flight.

4. The aerial vehicle of claim 1, wherein the structural framework includes: a central core; and support members extending between the central core and the interconnected flanges.

5. The aerial vehicle of claim 1, further comprising an external cage structure including circular rings connected to outer edges of the interconnected flanges.

6. The aerial vehicle of claim 2, wherein: the horizontal orientation is configured for efficient hover flight; and the angled orientation is configured for omni-directional movement.

7. The aerial vehicle of claim 1, wherein the plurality of thrust-generating devices include mounting mechanisms configured to adjust orientation of the plurality of thrust-generating devices relative to the structural framework.

8. The aerial vehicle of claim 1, wherein each interconnected flange includes a polygonal configuration.

9. The aerial vehicle of claim 8, wherein the polygonal configuration includes at least one of: a hexagonal configuration; an octagonal configuration; a circular configuration; a rhombic configuration; or a pyramidal configuration.

10. The aerial vehicle of claim 5, wherein: the plurality of thrust-generating devices are coupled to the structural framework; and the structural framework rotates independent of the external cage structure.

11. The aerial vehicle of claim 1, wherein the plurality of thrust-generating devices include: a first set configured for vertical thrust; and a second set configured for horizontal thrust.

12. The aerial vehicle of claim 1, wherein the structural framework includes: a hyperbolic curved internal support structure; and octahedral struts providing additional structural support.

13. A method of operating an aerial vehicle, comprising: providing a structural framework having a plurality of interconnected flanges arranged around a central space; generating thrust via thrust generating devices coupled to the structural framework; and controlling a plurality of thrust-generating devices to enable omni-directional movement of the aerial vehicle.

14. The method of claim 13, further including: transitioning the plurality of thrust-generating devices between: a horizontal configuration for efficient forward flight; and an angled configuration for omni-directional movement.

15. The method of claim 14, wherein transitioning includes adjusting orientation of the plurality of thrust-generating devices relative to a reference plane while maintaining thrust generation.

16. The method of claim 13, further including connecting the aerial vehicle with one or more additional aerial vehicles during flight to form an integrated swarm.

17. The method of claim 13, further including: operating in a first mode where the plurality of thrust-generating devices are oriented substantially horizontal to maximize thrust output and energy efficiency; and operating in a second mode where the plurality of thrust-generating devices are oriented at angles to enable complex maneuvers and precise positioning.

18. The method of claim 13, further including operating in an autonomous control mode for midair docking operations.

19. The method of claim 13, further including operating the plurality of thrustgenerating devices in a bidirectional manner to control direction and rotation during flight.

20. The method of claim 16, wherein connecting includes: aligning coupling interfaces between multiple aerial vehicles; and maintaining operational capability while connected.

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