Methods and systems for an interchangeable fan stage system

Abstract

An interchangeable fan stage system enabling hot swapping during operation is provided. This mechanism, integrated with the core nacelle platform, allows for rapid parts replacement without system shutdown. Additionally, the onboard servo control system and periphery driven electric motor system control motor speed and direction, enhancing operational efficiency and reliability.

Description

METHODS AND SYSTEMS FOR AN INTERCHANGEABLE FAN STAGE SYSTEMCROSS-REFERENCE

[0001] This application claims the benefit of U.S. Provisional Application No. US 63 / 671,453, filed July 15, 2024, which is incorporated herein by reference in its entirety.BACKGROUND

[0002] In aviation, aircraft engine efficiency and operational continuity are key for safety and cost-effectiveness. For example, turbines are costly and may be research and development intensive for a singular engineered configuration point. It is desirable to provide a platform or solution allowing for convenient exchange and integration of turbines based on different air mobility applications.SUMMARY

[0003] The present disclosure addresses the above needs by providing a platform that may be implemented in a wide range of air mobility applications (e.g., remote control airplanes, flying cars, vehicles utilizing a propulsion system, etc.) or any other industrial applications where a turbine or fan stage is involved (e.g., power plant energy generation).

[0004] In an aspect, the present disclosure provides methods and systems for an apparatus. The apparatus comprises an interchangeable fan stage system, a core nacelle platform and a mechanism for hot swapping the interchangeable fan stage system.

[0005] In some embodiments, the interchangeable fan stage system is configured to be integrated into the core nacelle platform. In some embodiments, the interchangeable fan stage system and the core nacelle platform are configured for hot swapping during operation of the system. In some embodiments, the interchangeable fan stage system includes a plurality of replaceable fans. In some embodiments, the interchangeable fan stage system is integrated with at least one periphery driven electric motor system. In some embodiments, the apparatus further comprises an onboard servo control system for the periphery driven electric motor system. In some embodiments, the onboard servo control system is configured to control at least one speed or direction of the electric motor from a plurality of defined speeds and directions. In some embodiments, the interchangeable fan stage system and the periphery driven electric motor system are connected by a plurality of structural and electrical connections. In some embodiments, the apparatus further comprises a wiring attachment system for wire hookup into the core nacelle platform, wherein the wiring attachment system is incorporated into the core nacelle platform. In some embodiments, the periphery driven electric motor system comprises at least one rotor and at least one stator. In some embodiments, a central shaft connected to the corenacelle platform holds the periphery driven electric motor system in place. In some embodiments, the interchangeable fan system is integrated into the rotor of the periphery driven electric motor system. In some embodiments, the interchangeable fan system further comprises a plurality of blades attached to a central hub and an outer ring wherein the outer ring is attached to the rotor. In some embodiments, the rotor or the stator of the periphery driven electric motor system are configured for hot swapping between periphery driven electric motor system to another periphery driven electric motor system.

[0006] In some embodiments, the mechanism for hot swapping the interchangeable fan stage system components comprises a trap door mechanism for latching and unlatching the interchangeable fan stage system from the core nacelle platform. In some embodiments, the trap door mechanism is configured to secure the fan stage system during operations and allow for quick release during the hot swapping process. In some embodiments, the mechanism for hot swapping the interchangeable fan stage system further comprises a latching mechanism that locks and unlocks the fan stage system from operational states to a swap state. In some embodiments, the latching mechanism is configured to securely hold the fan stage system in place during operations, and allow for easy removal during the hot swapping process. In some embodiments, the mechanism for hot swapping the interchangeable fan stage system further comprises a spring system that enables an operator or pilot to visually determine which fan stage is being changed out or swapped. In some embodiments, the apparatus further comprises a custom software system that controls and manages the hot swapping mechanism, wherein the custom software system provides real-time status updates, control features, and diagnostics related to the operation and hot swapping of the interchangeable fan stage system.

[0007] In some embodiments, the apparatus further comprises at least one QR label attached to the core nacelle platform, wherein the QR label encodes a variety of information for characterizing the apparatus. In some embodiments, the interchangeable fan stage system further comprises a plurality of integrated sensors configured to collect at least one set of operational or environmental data relevant to the functioning of the apparatus. In some embodiments, the collected operational or environmental data is used to monitor the health and performance of the interchangeable fan stage system and to determine a necessity of a hot swap. In some embodiments, the apparatus further comprises a communication module embedded within the interchangeable fan stage system that connects with an external computing system for data processing and interaction. In some embodiments, the communication module comprises components for wired or remote communications. In some embodiments, the interchangeable fan stage system comprises an improved nacelle core integrated with wiring, programming, orsoftware components. In some embodiments, the wiring, programming, or software components are configured for hot swapping of the interchangeable fan stage system.

[0008] In some embodiments, the improved nacelle core is configured to allow the fan stage system and stator / rotor to be hot swapped during an operation of an engine. In some embodiments, the core nacelle platform is configured to support various operational conditions for the interchangeable fan stage system. In some embodiments, the apparatus further comprises a user interface configured for monitoring the status of the interchangeable fan stage system during operation. In some embodiments, the mechanism for hot swapping comprises safety features configured to prevent accidental activation during engine operation. In some embodiments, the safety features are configured to ensure that the engine operates within predefined parameters during the hot swapping process. In some embodiments, the programming and software components are configured to provide real-time diagnostics related to the interchangeable fan stage system. In some embodiments, the apparatus further comprises a communication module configured to connect the interchangeable fan stage system with an external computing system for data processing and interaction. In some embodiments, the interchangeable fan stage system is part of a motor or engine that is configured for hot swapping during operation of the motor or engine.

[0009] In some embodiments, the fan stage system may be interchangeably integrated with the core nacelle platform. In some embodiments, the motor or engine is an aircraft engine provided with the interchangeable fan stage system. In some embodiments, the core nacelle platform comprises a modular nacelle platform, wherein the modular nacelle platform is configured to allow for a modular stator and a modular fan / turbine stage to be interchangeably integrated as part of an engine. In some embodiments, the modular nacelle platform comprises structures and features configured for an exchange of fan stages, modular stators, and rotors of the engine. In some embodiments, the modular nacelle platform comprises a hot swapping mechanism. In some embodiments, the hot swapping mechanism comprises a latching mechanism that includes mechanical components configured for temporarily joining moving parts relative to each other. In some embodiments, the latching mechanism is actuated to lock or unlock the coupling between the modular stator and the modular fan / turbine stage. In some embodiments, the latching mechanism is actuated to release the coupling and allow the joining of the two parts to separate.

[0010] In some embodiments, the modular nacelle platform includes a latching mechanism. In some embodiments, the modular nacelle platform comprises a rear nacelle core, a front nacelle core, a permanent nacelle cover, a nacelle cover latch, or a combination thereof. In some embodiments, the permanent nacelle cover connects the rear nacelle core and the front nacellecore. In some embodiments, the nacelle cover latch is actuated to be released from the permanent nacelle cover such that a modular fan stage and / or stator is slid into a slot. In some embodiments, the slot has a width to fit one or more fan stages and stators. In some embodiments, the modular nacelle platform comprises a plurality of slots, each corresponding to a location in the nacelle platform. In some embodiments, one slot fits a single fan stage. In some embodiments, a slot is selected from the plurality of slots to receive a modular stator or turbine stage. In some embodiments, the modular nacelle platform accommodates a plurality of fan stages. In some embodiments, the nacelle cover latch joins with the permanent nacelle cover, thereby forming a hatch cover or shell for the internal fan stage, rotor, stator, and other components of the engine. In some embodiments, the modular nacelle platform comprises a supporting structure. In some embodiments, the supporting structure provides additional structural rigidity to the nacelle platform.

[0011] In some embodiments, the supporting structure is configured to mount one or more turbine stages and one or more stators. In some embodiments, the supporting structure helps to lock the modular stator and fan stage in place once they are integrated and mounted to the supporting structure. In some embodiments, the modular fan stage and stator are prevented from moving once they are mounted and secured to the supporting structure. In some embodiments, a wiring attachment system is incorporated into the core nacelle platform. In some embodiments, the nacelle platform comprises built-in wiring and circuitry such that upon mounting the modular stator to the supporting structure, the wiring between the modular stator and the nacelle core is automatically connected. In some embodiments, the wiring connection is located within the permanent nacelle cover such that the fan stage and / or stator may be swapped in and out in a plug and play fashion. In some embodiments, the circuitry of the nacelle platform is configured to automatically detect the opening of the nacelle cover latch and, upon detection, automatically disconnect the wiring. In some embodiments, the connection and disconnection of an electronic communication between the stator and the nacelle is remotely controlled. In some embodiments, the fan stage system and the periphery driven electric motor system are connected through structural and electrical connections.

[0012] In some embodiments, the connections between the fan stage system and the electric motor system ensure an exchange of power and data. In some embodiments, the hot swapping mechanism further comprises a trap door mechanism that controls the latching and unlatching of the hatch cover via the core nacelle platform software. In some embodiments, a user may activate the latching or unlatching of the hatch cover through a button within the user interface of the nacelle platform software. In some embodiments, the latch / unlatch action is actuated by an electronic signal received by the circuitry of the nacelle platform. In some embodiments, manualactivation of the latching and unlatching of the hatch cover is provided in addition to the user interface. In some embodiments, the user interface provides the status of the hatch cover and displays information about the current installed fan stage and stator / rotor. In some embodiments, the modular nacelle platform is configured to lock or unlock the fan stages to switch the fan stages between operational states and a swap state.

[0013] In some embodiments, the latching mechanism locks and unlocks the fan stage system from operational states to a swap state, securing the fan system during operation of the apparatus. In some embodiments, the latching mechanism provides a secure method to fasten and release the components during the hot swapping process. In some embodiments, the latching mechanism ensures that the fan stage system is securely held in place during regular operation.

[0014] In some embodiments, the latch is unlocked during maintenance or hot swapping to allow for easy removal and replacement of components. In some embodiments, the lock or unlock status or a fan stage status is displayed within a graphical user interface (GUI). In some embodiments, the feature to lock or unlock the fan stage is remotely activated via the GUI. In some embodiments, the hot swapping mechanism comprises a spring system. In some embodiments, the spring system is configured to spring out a fan stage from the slot, allowing an operator or pilot to visually determine which fan stage is being changed out or swapped. In some embodiments, the nacelle platform allows for hot swapping a fan stage, a stator, and / or rotor of an engine. In some embodiments, the hot swappable fan stage is coupled to a periphery driven electric motor system such that a modular stator and turbine / fan stage may be conveniently swapped in and out without disassembling parts of the existing system. In some embodiments, the modular stator and turbine stage is a modular package that may slide into the slot in a plug and play fashion. In some embodiments, the modular stator is interchangeable based on different flight conditions or mission criteria. In some embodiments, the mission criteria include thrust / power efficiency requirement, energy efficiency requirement, fuel / distance requirement, or a combination thereof.

[0015] In some embodiments, the stator comprises structures or mechanical features that allow it to be locked to the nacelle platform and interlocked with other stators when multiple stators or fan stages are preferred. In some embodiments, the modular stator comprises interlocking structures to releasably couple the stator to other modular stators. In some embodiments, the fan stage system comprises features integrated with the rotor of the motor system to enhance the efficiency of airflow within the system. In some embodiments, a central shaft connects to the core nacelle platform and holds the periphery driven electric motor system securely in place. In some embodiments, the central shaft ensures optimal alignment and stability of the motor system, allowing for smooth and efficient engine operation. In some embodiments, the fan stagesystem is selected based on blade architecture, blade profile, blade twist, blade sweep, blade angle, pitch of propeller, variable pitch, location of the fan stage in the nacelle, or any combination thereof. In some embodiments, one or more fan stages work in unison to drive an aircraft engine's operation. In some embodiments, the fan stage system is selected by software of the platform and provided to a user via the graphical user interface (GUI).

[0016] In some embodiments, the software determines locations of the one or more fan stages in the nacelle based on pressure, velocity of air through the interchangeable fan stages, volume of airflow, motor efficiency, or any combination thereof. In some embodiments, the software aids the operator or pilot in selecting a fan blade for a flight plan. In some embodiments, the flight plan is inputted by the operator or pilot via the GUI. In some embodiments, the software automatically calculates decisions to decrease battery usage over time to maximize miles per charge of the motor based on an initial flight plan to determine optimal blade selections. In some embodiments, the fan stage system and the core nacelle platform are configured for hot swapping during system operation. In some embodiments, the hot swapping feature allows for the replacement of the fan stage system components without interrupting the engine's operation. In some embodiments, the electric motor system is configured with an onboard servo control system and / or wiring attachment systems for connection with the nacelle core. In some embodiments, the wiring is built into the nacelle system, allowing for wiring hookup between the nacelle core and the stator or fan stage system. In some embodiments, the fan stage, rotor, and / or stator of the system are hot swappable. In some embodiments, the fan stage system is configured into a rotor of an electric motor, allowing both the stator and rotor of the electric motor to be hot swapped.

[0017] Additional cases and advantages of the present disclosure will become readily apparent to those skilled in this art from the following detailed description, wherein only illustrative embodiments of the present disclosure are shown and described. As will be realized, the present disclosure is capable of other and different embodiments, and its several details are capable of modifications in various obvious respects, all without departing from the disclosure. Accordingly, the drawings and description are to be regarded as illustrative in nature, and not as restrictive.INCORPORATION BY REFERENCE

[0018] All publications, patents, and patent applications mentioned in this specification are herein incorporated by reference to the same extent as if each individual publication, patent, or patent application was specifically and individually indicated to be incorporated by reference. To the extent publications and patents and patent applications incorporated by reference contradictthe disclosure contained in the specification, the specification is intended to supersede and / or take precedence over any such contradictory material.BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The novel features of the inventive concepts are set forth with particularity in the appended claims. A better understanding of the features and advantages of the present inventive concepts will be obtained by reference to the following detailed description that sets forth illustrative embodiments, in which the principles of the inventive concepts are utilized, and the accompanying drawings (also “Figure” and “FIG.” herein), of which:

[0020] FIGs. 1-2 show an example of a modular nacelle platform that allows for a modular stator and a modular fan / turbine stage to be interchangeably integrated to the modular nacelle platform.

[0021] FIGs. 3-5 show an example of a modular stator and turbine stage.

[0022] FIGs. 6-9 show an example of a modular nacelle platform with a latching mechanism.

[0023] FIG. 10 illustrates an example of a hot swapping process.

[0024] FIG. 11 illustrates an example of a process for installation of a fan stage system, and / or the installation of a stator and rotor into the core nacelle platform.

[0025] FIG. 12 illustrates various air mobility applications where a propulsion system is involved.

[0026] FIG. 13 shows a non-limiting example of a computing device; in this case, a device with one or more processors, memory, storage, and a network interface, in accordance with some embodiments.

[0027] FIG. 14 shows a non-limiting example of a web / mobile application provision system.

[0028] FIG. 15 shows a non-limiting example of a cloud-based web / mobile application provision system.DETAILED DESCRIPTION

[0029] While various embodiments of the invention have been shown and described herein, it will be obvious to those skilled in the art that such embodiments are provided by way of example only. Numerous variations, changes, and substitutions may occur to those skilled in the art without departing from the invention. It should be understood that various alternatives to the embodiments of the invention described herein may be employed in practicing the invention.

[0030] The term “fluid,” as used herein, refers to a gas or liquid. In some embodiments, a fluid is a gas or liquid having low or substantially low viscosity. A fluid may include, for example, air, oxygen, hydrogen, water vapor, an inorganic liquid, or an organic liquid, such as liquidwater, an alcohol, an aldehyde, or a ketone. A fluid has various fluid properties, such as heat capacity, viscosity, temperature, pressure and flow rate.

[0031] The term “blade,” as used herein, refers to an object that is configured to generate lift upon the flow of a fluid over surfaces of the blade. A blade may have a pressure side, suction side, leading edge and trailing edge. The pressure side and suction side are for generating lift with the flow of fluid (e.g., air) over the blade. In some instances, a blade is used to provide mechanical motion to a turbine generator. In such context, the blade may be referred to as a “turbine blade”.

[0032] The term "fan," as used herein, refers to an assembly composed of a plurality of blades distributed over various stages. Each blade in a fan is configured to generate lift upon the flow of fluid, such as air, over its surfaces. This fluid movement is converted into mechanical energy, effectively pushing air through and out of the system, thereby providing thrust. In the context of aircraft engines, a fan is integral to the engine's performance and efficiency, assisting in creating the required thrust for flight.

[0033] The term "stage," in relation to a fan or turbine, refers to a distinct level or phase in the engine where a set of actions or operations occur. In a multi-stage fan system, a stage comprises a set of blades that work together to compress the airflow progressively as it passes through consecutive stages. The number of stages in a fan stage system may vary based on the specific configuration and requirements of the engine, with each stage contributing to the overall functioning and output of the system.

[0034] The term “drag,” as used herein, refers to the component of aerodynamic or hydrodynamic force parallel to the direction of motion of the airfoil or blade section.

[0035] The term “turbine,” as used herein, refers to a machine, device or system that generates power when a wheel or rotor hub (also “hub” herein) fitted with vanes or blades is made to revolve within the flow of a fluid. A turbine configured to generate power from wind is referred to as a “wind turbine” herein. In some cases, a turbine includes a power generator, such as an induction generator, for converting mechanical energy to electricity (or power).

[0036] Hot Swappable Fan Stage and Nacelle Platform

[0037] Systems and methods herein may provide an interchangeable fan stage system. The interchangeable fan stage system may comprise an improved nacelle core integrated with wiring, programming, and software components thereby allowing for hot swapping the fan stage system. The nacelle core may allow the fan stage system and stator / rotor to be hot swapped during an operation of an engine.

[0038] In some embodiments, the present disclosure relates to an apparatus for enhancing aerodynamic efficiency in various applications. The systems and methods herein may beapplicable in fields such as aerospace engineering, automotive configuration, or renewable energy systems. In some embodiments, the apparatus comprises an interchangeable fan stage system, a core nacelle platform, and a mechanism for hot swapping the interchangeable fan stage system. The systems and methods herein may enable efficient modification of operational parameters without the need for extensive disassembly or reconfiguration. In some embodiments, the interchangeable fan stage system may comprise various configurations tailored to specific operational requirements. In some embodiments, the fan stage system may include a single or multiple fan blades, each configured for varying thrust or efficiency. In some embodiments, the fan blades may be constructed from materials such as composite materials, aluminum, or titanium, or any combination thereof.

[0039] In some embodiments, the core nacelle platform may serve as the structural framework for the apparatus. The nacelle platform may be configured to support various components, including the interchangeable fan stage system. In some embodiments, the core nacelle platform may be constructed from materials such as carbon fiber, steel, or plastic, or any combination thereof. In some embodiments, the mechanism for hot swapping the interchangeable fan stage system may allow for the rapid exchange of fan stages during operation. In some embodiments, the mechanism may utilize a series of latches, clips, or quick-release fasteners to facilitate this process. In some embodiments, alternative mechanisms may include hydraulic systems, pneumatic actuators, or any combination thereof. In some embodiments, the apparatus may incorporate sensors that monitor the performance of the interchangeable fan stage system. In some embodiments, these sensors may track parameters such as temperature, pressure, or rotational speed. In some embodiments, the data collected may be utilized to optimize the performance of the fan stage system in real-time. In some embodiments, the apparatus may be configured for use in a variety of environments, including but not limited to commercial aviation, military applications, or industrial processes. In some embodiments, the configuration may consider factors such as weight, aerodynamics, or noise reduction to enhance overall efficiency. In some embodiments, the interchangeable fan stage system may be part of a motor / engine and may allow for hot swapping during operation of the motor / engine. For example, the fan stage system may be interchangeably integrated with a core nacelle platform. In some embodiments, an aircraft engine is provided with an interchangeable fan stage system.

[0040] In some embodiments, the apparatus may comprise the interchangeable fan stage system configured to be integrated into the core nacelle platform. In some embodiments, this integration may facilitate structural stability and operational efficiency. In some embodiments, the interchangeable fan stage system and the core nacelle platform may be configured for hot swapping during operation of the system. This configuration may allow for seamless transitionsbetween different fan stage configurations without interrupting system performance. In some embodiments, the interchangeable fan stage system may include a plurality of replaceable fans. In some embodiments, each fan may be configured to optimize specific operational parameters such as thrust, efficiency, or noise levels. In some embodiments, the interchangeable fan stage system may integrate with at least one periphery driven electric motor system. In some embodiments, this integration may enhance the overall power efficiency and responsiveness of the apparatus during operation.

[0041] In some embodiments, the apparatus may further comprise an onboard servo control system for the periphery driven electric motor system. In some embodiments, this onboard servo control system may facilitate precise adjustments to the motor’s operation. In some embodiments, the onboard servo control system may be configured to control at least one speed or direction of the electric motor from a plurality of defined speeds and directions. This configuration may enhance the adaptability and performance of the motor during operation. In some embodiments, the interchangeable fan stage system and the periphery driven electric motor system may be connected by a plurality of structural and electrical connections. In some embodiments, these connections may ensure reliable communication and support between the components. In some embodiments, the apparatus may further comprise a wiring attachment system for wire hookup into the core nacelle platform. In some embodiments, the wiring attachment system may be incorporated into the core nacelle platform to facilitate ease of connection and maintenance. In some embodiments, the periphery driven electric motor system may comprise at least one rotor and at least one stator. In some embodiments, this configuration may contribute to the overall efficiency and effectiveness of the motor system within the apparatus.

[0042] In some embodiments, a central shaft connected to the core nacelle platform may hold the periphery driven electric motor system in place. This configuration may enhance the stability and alignment of the motor system within the apparatus. In some embodiments, the interchangeable fan system may be integrated into the rotor of the periphery driven electric motor system. This integration may optimize the overall efficiency of the fan operation in conjunction with the motor system. In some embodiments, the interchangeable fan system may further comprise a plurality of blades attached to a central hub and an outer ring, wherein the outer ring is attached to the rotor. This configuration may improve aerodynamic performance and facilitate effective thrust generation. In some embodiments, the rotor or the stator of the periphery driven electric motor system may be configured for hot swapping between one periphery driven electric motor system and another periphery driven electric motor system. This configuration may allow for rapid changes in motor systems with little downtime or withoutdowntime. In some embodiments, the mechanism for hot swapping the interchangeable fan stage system components may comprise a trap door mechanism for latching and unlatching the interchangeable fan stage system from the core nacelle platform. This mechanism may facilitate ease of access and operation during component swaps. In some embodiments, the trap door mechanism may be configured to secure the fan stage system during operations and allow for quick release during the hot swapping process. This configuration may ensure safety and efficiency during operational transitions. In some embodiments, the mechanism for hot swapping the interchangeable fan stage system may further comprise a latching mechanism that locks and unlocks the fan stage system from operational states to a swap state. This mechanism may enhance the reliability and functionality of the hot swapping process.

[0043] In some embodiments, the latching mechanism may be configured to securely hold the fan stage system in place during operations and allow for easy removal during the hot swapping process. This configuration may enhance the overall safety and efficiency of the apparatus. In some embodiments, the mechanism for hot swapping the interchangeable fan stage system may further comprise a spring system that enables an operator or pilot to visually determine which fan stage is being changed out or swapped. This feature may improve operational clarity and facilitate easier management of fan stage transitions. In some embodiments, the apparatus may further comprise a custom software system that controls and manages the hot swapping mechanism. This custom software system may provide real-time status updates, control features, and diagnostics related to the operation and hot swapping of the interchangeable fan stage system. In some embodiments, the apparatus may further comprise at least one QR label attached to the core nacelle platform. The QR label may encode a variety of information for characterizing the apparatus, enhancing user accessibility to pertinent data. In some embodiments, the interchangeable fan stage system may further comprise a plurality of integrated sensors configured to collect at least one set of operational or environmental data relevant to the functioning of the apparatus. This data collection may enhance operational oversight and system management. In some embodiments, the collected operational or environmental data may be used to monitor the health and performance of the interchangeable fan stage system and to determine the necessity of a hot swap. This monitoring may contribute to proactive maintenance and operational efficiency. In some embodiments, the apparatus may further comprise a communication module embedded within the interchangeable fan stage system that connects with an external computing system for data processing and interaction. This communication capability may enhance the integration of the apparatus within larger system architectures. In some embodiments, the communication module may comprise components forwired or remote communications. This flexibility may facilitate diverse operational environments and enhance data exchange capabilities.

[0044] In some embodiments, the interchangeable fan stage system may comprise an improved nacelle core integrated with wiring, programming, or software components. This integration may enhance the overall functionality and reliability of the system. In some embodiments, the wiring, programming, or software components may be configured for hot swapping of the interchangeable fan stage system. This configuration may facilitate seamless transitions between fan stages without requiring extensive downtime. In some embodiments, the improved nacelle core may be configured to allow the fan stage system and stator / rotor to be hot swapped during the operation of an engine. This capability may enhance operational flexibility and efficiency. In some embodiments, the core nacelle platform may be configured to support various operational conditions for the interchangeable fan stage system. This configuration may ensure optimal performance across diverse environments and applications. In some embodiments, the apparatus may further comprise a user interface configured for monitoring the status of the interchangeable fan stage system during operation. This user interface may provide real-time insights and enhance user interaction with the system.

[0045] In some embodiments, the mechanism for hot swapping may comprise safety features configured to prevent accidental activation during engine operation. These safety features may enhance the reliability and safety of the system during critical operational phases. In some embodiments, the safety features may be configured to ensure that the engine operates within predefined parameters during the hot swapping process. This configuration may mitigate risks associated with engine performance fluctuations during component transitions. In some embodiments, the programming and software components may be configured to provide realtime diagnostics related to the interchangeable fan stage system. This capability may enable proactive maintenance and performance monitoring. In some embodiments, the apparatus may further comprise a communication module configured to connect the interchangeable fan stage system with an external computing system for data processing and interaction. This communication module may facilitate enhanced integration and operational oversight. In some embodiments, the interchangeable fan stage system may be part of a motor or engine that is configured for hot swapping during operation of the motor or engine. This integration may allow for rapid adjustments to performance characteristics with little downtime or without downtime. In some embodiments, the fan stage system may be interchangeably integrated with the core nacelle platform. This integration may enhance the overall efficiency and adaptability of the apparatus during operation. In some embodiments, the motor or engine may be an aircraft engine provided with the interchangeable fan stage system. This application may optimize performanceand operational flexibility in aviation contexts. In some embodiments, the core nacelle platform may comprise a modular nacelle platform, wherein the modular nacelle platform is configured to allow for a modular stator and a modular fan / turbine stage to be interchangeably integrated as part of an engine. This configuration may enhance the versatility and customization options for various operational requirements.

[0046] In some embodiments, the modular nacelle platform may comprise structures and features configured for the exchange of fan stages, modular stators, and rotors of the engine. This configuration may enhance the versatility and adaptability of the apparatus. In some embodiments, the modular nacelle platform may comprise a hot swapping mechanism. This mechanism may facilitate the rapid exchange of components with little downtime or without downtime. In some embodiments, the hot swapping mechanism may comprise a latching mechanism that includes mechanical components configured for temporarily joining moving parts relative to each other. This configuration may ensure secure connections during operation. In some embodiments, the latching mechanism may be actuated to lock or unlock the coupling between the modular stator and the modular fan / turbine stage. This capability may enhance the control over component integration and removal. In some embodiments, the latching mechanism may be actuated to release the coupling and allow the joining of the two parts to separate. This function may facilitate the efficient swapping of components. In some embodiments, the modular nacelle platform may include a latching mechanism. This mechanism may provide additional security and stability for the components housed within the nacelle platform. In some embodiments, the modular nacelle platform may comprise a rear nacelle core, a front nacelle core, a permanent nacelle cover, a nacelle cover latch, or a combination thereof. This configuration may enhance the structural integrity of the apparatus. In some embodiments, the permanent nacelle cover may connect the rear nacelle core and the front nacelle core. This connection may provide a unified structural framework for the apparatus. In some embodiments, the nacelle cover latch may be actuated to be released from the permanent nacelle cover such that a modular fan stage and / or stator is slid into a slot. This mechanism may facilitate straightforward component access. In some embodiments, the slot may have a width to fit one or more fan stages and stators. This configuration may accommodate various configurations and enhance operational flexibility. In some embodiments, the modular nacelle platform may comprise a plurality of slots, each corresponding to a location in the nacelle platform. This configuration may allow for organized storage and integration of components. In some embodiments, one slot may fit a single fan stage. This configuration may ensure precise alignment and effective operation of the fan stage within the nacelle platform.

[0047] In some embodiments, a slot may be selected from the plurality of slots to receive a modular stator or turbine stage. This selection process may facilitate the efficient integration of components within the nacelle platform. In some embodiments, the modular nacelle platform may accommodate a plurality of fan stages. This capability may enhance operational versatility and allow for configuration adjustments based on performance needs. In some embodiments, the nacelle cover latch may join with the permanent nacelle cover, thereby forming a hatch cover or shell for the internal fan stage, rotor, stator, and other components of the engine. This configuration may provide protection and structural integrity for the internal components. In some embodiments, the modular nacelle platform may comprise a supporting structure. This supporting structure may enhance the overall stability and durability of the nacelle platform. In some embodiments, the supporting structure may provide additional structural rigidity to the nacelle platform. This rigidity may contribute to the apparatus's ability to withstand operational stresses. In some embodiments, the supporting structure may be configured to mount one or more turbine stages and one or more stators. This configuration may allow for a modular approach to system integration. In some embodiments, the supporting structure may help to lock the modular stator and fan stage in place once they are integrated and mounted to the supporting structure. This locking mechanism may enhance the reliability of the system during operation. In some embodiments, the modular fan stage and stator may be prevented from moving once they are mounted and secured to the supporting structure. This prevention of movement may enhance operational stability and performance. In some embodiments, a wiring attachment system may be incorporated into the core nacelle platform. This system may facilitate the efficient connection of electrical components. In some embodiments, the nacelle platform may comprise built-in wiring and circuitry such that upon mounting the modular stator to the supporting structure, the wiring between the modular stator and the nacelle core is automatically connected. This automatic connection may streamline the integration process and reduce installation time.

[0048] In some embodiments, the wiring connection may be located within the permanent nacelle cover such that the fan stage and / or stator are swapped in and out in a plug and play fashion. This configuration may streamline the process of component exchange. In some embodiments, the circuitry of the nacelle platform may be configured to automatically detect the opening of the nacelle cover latch. Upon detection, the circuitry may automatically disconnect the wiring. This feature may enhance safety and prevent accidental connections during swaps. In some embodiments, the connection and disconnection of an electronic communication between the stator and the nacelle may be remotely controlled. This capability may provide flexibility in managing component interactions. In some embodiments, the fan stage system and the periphery driven electric motor system may be connected through structural and electrical connections.This connection may facilitate effective integration of the systems. In some embodiments, the connections between the fan stage system and the electric motor system may ensure an exchange of power and data. This exchange may be critical for optimal performance and functionality.

[0049] In some embodiments, the hot swapping mechanism may further comprise a trap door mechanism that controls the latching and unlatching of the hatch cover via the core nacelle platform software. This mechanism may improve the efficiency of component swaps. In some embodiments, a user may activate the latching or unlatching of the hatch cover through a button within the user interface of the nacelle platform software. This interface may enhance user control and convenience. In some embodiments, the latch / unlatch action may be actuated by an electronic signal received by the circuitry of the nacelle platform. This electronic control may ensure precise operation of the latching mechanism. In some embodiments, manual activation of the latching and unlatching of the hatch cover may be provided in addition to the user interface. This manual option may serve as a backup for user operation. In some embodiments, the user interface may provide the status of the hatch cover and display information about the current installed fan stage and stator / rotor. This information may enhance user awareness and facilitate informed decisions during operation.

[0050] FIGs. 1-2 show an example of a modular nacelle platform 100 that allows for a modular stator 110 and a modular fan / turbine stage 120 to be interchangeably integrated to the modular nacelle platform as part of an engine. The modular nacelle platform 100 may comprise structures and features allowing for convenient exchange of different fan stages, modular stator and rotors of an engine. The modular nacelle platform 100 may comprise a hot swapping mechanism. In some embodiments, the hot swapping mechanism may comprise a latching mechanism that includes mechanical components allowing a temporary joining of moving parts relative to each other, may be actuated to lock / unlock the coupling and actuated to release the coupling and allow the joining two parts to separate.

[0051] FIGs. 6-9 show an example of a modular nacelle platform 100 with a latching mechanism. The modular nacelle platform 100 may comprise a rear nacelle core 102, a front nacelle core 104, a permanent nacelle cover 107 and a nacelle cover latch 108. The permanent nacelle cover 107 may connect the rear nacelle core 102 and front nacelle core 104. As shown in FIG. 1, the nacelle cover latch 108 may be actuated to be released from the permanent nacelle cover such that a modular fan stage and / or stator may be slide into a slot 106. In some cases, the slot 106 may have a width to fit one or more fan stages and stators. In alternative cases, the nacelle platform may comprise a plurality of slots each corresponds to a location in the nacelle platform. In such cases, one slot may fit a single fan stage. A slot may be selected from the plurality of slots to receive a modular stator / turbine stage. Although only one modular fan stageand stator is illustrated in FIG. 1, the nacelle platform 100 may accommodate a plurality of fan stages (i.e., multi-stage fan engine) such as at least one, two, three, four, five, six, seven, eight, nine or more fan stages.

[0052] The nacelle cover latch 108 may join with the permanent nacelle cover 107 thereby forming a hatch cover or shell for the internal fan stage, rotor, stator and other components of the engine.

[0053] In some embodiments, the modular nacelle platform 100 may further comprise a supporting structure 109. The supporting structure 109 may provide additional structural rigidity of the nacelle platform 100. The support structure 109 may also be configured to mount one or more turbine stages and one or more stators. The supporting structure 109 may help to lock the modular stator and fan stage in place once they are integrated and mounted to the supporting structure. The modular fan stage and stator may be prevented from moving once they are mounted and secured to the supporting structure 109.

[0054] In some embodiments, a wiring attachment system is incorporated directly into the core nacelle platform. This integrated setup simplifies the electrical layout, beneficially enhancing the stability and durability of the electrical connections. In some embodiments, the shell or the nacelle platform may comprise built-in wiring and circuitry such that upon mounting the modular stator to the supporting structure in place, the wiring between the modular stator and the nacelle core is automatically connected. In some cases, the wiring connection may be located within the permanent nacelle cover 107 such that the fan stage and / or stator may be swapped in / out in a plug and play fashion. In some cases, the circuitry of the nacelle platform may be able to automatically detect an open of the nacelle cover latch and upon the detection, automatically disconnect the wiring. In some cases, the connection and disconnection of the electronic communication between the stator and the nacelle may be remotely controlled.

[0055] In some embodiments, as illustrated in FIG. 1, the fan stage system and the electric motor system are connected through structural and electrical connections. The connections between these two systems may facilitate an efficient exchange of power and data, ensuring the units work in harmony and contributing to the overall operational efficiency of the apparatus.

[0056] In some embodiments, the hot swapping mechanism may further comprise a trap door mechanism that allows for controlling the “latching” and “unlatching” of hatch cover via the core nacelle platform software (e.g., user interface). For example, a user may click on a button within a user interface of the nacelle platform software to latch or unlatch the hatch cover. The latch / unlatch may be actuated / activated by an electronic signal received by a circuitry of the nacelle platform. In some cases, in addition to the software user interface, manual activation of the latching / unlatching of the hatch cover may be provided. The user interface may providestatus of the hatch cover (e.g., latch / unlatch) and may also display information about the current installed fan stage and stator / rotor.

[0057] In some cases, once the fan stage and stator are integrated to the nacelle platform, features may be provided to further lock / unlock the fan stages to switch the fan stages between operational states to a swap state thereby securing the fan system during the operation of the apparatus, contributing to the overall stability and effective performance. This latching mechanism may lock and unlock the fan stage system from operational states to a swap state, providing a secure and effective method to fasten and release the components during the hot swapping process. During regular operation, the latching mechanism may ensure the fan stage system is securely held in place, contributing to the stability of the overall system. During maintenance or hot swapping, the latch may be unlocked to allow for easy removal and replacement of components, further enhancing the apparatus's serviceability and operational efficiency. In some cases, the lock / unlock status or a fan stage status (e.g., swap state, operation state) may be displayed within a graphical user interface (GUI). In some cases, the feature to lock / unlock the fan stage may be remotely activated via the GUI.

[0058] In some embodiments, the hot swapping mechanism may comprise a spring system. The spring system may be configured to spring out a fan stage from the slot allowing an operator or pilot to visually determine which fan stage is being changed out or swapped. By providing a clear visual indication, the spring system may enhance the user interface of the hot swapping mechanism, making it more intuitive and user-friendly. The system may also improve operational transparency, making it easier for operator to track and monitor the progress of hot swapping procedures, ensuring proper execution and successful completion of the process.

[0059] In some embodiments, the fan stage system may be conveniently integrated or coupled to a periphery driven electric motor system to provide a motor for ease of use for various applications (e.g., remote control airplanes, flying cars, vehicles utilizing a propulsion system, etc.) or any other industrial applications where a turbine or fan stage is involved (e.g., power plant energy generation). The periphery driven electronic motor beneficially allows the modular fan stage and stator to slide into a slot 106 and hot swapping during operation of the engine.

[0060] In some embodiments, the nacelle platform herein may allow for hot swapping a fan stage, a stator and / or rotor of an engine to meet various flight conditions or configuration requirements. In some embodiments, the hot swappable fan stage may be coupled to a periphery driven electric motor system such that a modular stator and turbine / fan stage may be conveniently swapped in / out without disassembling parts in the existing system. For example, the modular stator and turbine stage may be a modular package that may slide into the slot 106 in a plug and play fashion. FIGs. 3-5 show an example of a modular stator 308 and turbine stage306. The modular stator 308 may be interchangeable. For example, based on different flight conditions, mission criteria (e.g., thrust / power efficiency requirement, energy efficiency requirement, fuel / distance requirement, etc.), different modular stators may be selected and may be interchangeable. In some cases, the stator 308 may comprise structures / mechanical features allowing it to be locked to the nacelle platform and interlocked with other stators when multiple stators / fan stages are preferred. For example, the modular stator 308 may comprise interlocking structures 1410, 312 to releasably couple the stator 308 to other modular stators.

[0061] In some embodiments, the fan system may comprise features to be integrated with the rotor of the motor system. By aligning the motion of the rotor with the fan system, this configuration may enhance the efficiency of airflow within the system, contributing to the propulsion and overall performance of the aircraft. In some embodiments, the fan stage or turbine stage may comprise a plurality of blades 306 coupled to a central hub 316 and an outer ring 304 forming a bladed disk or blisk. The outer ring 304 may be attached to a rotor 314 of the engine to drive the motion of the blades. In some embodiments, the periphery driven electric motor system may comprise a rotor 314 and a stator 308. The electric motor may convert electrical energy into mechanical energy, thereby driving the operation of the fan stage system.

[0062] Functioning of the aircraft engine may be conveniently modified by selecting different rotor / stator and / or the fan stage system. In some embodiments, the rotor or the stator of the periphery driven electric motor system may be hot-swapped between different electric motor systems. This unique feature provides additional modularity of the apparatus, allowing for customized rotor or the stator, to be replaced or exchanged without stopping the operation of the entire motor system. The hot swappable rotor / stator allows for customizable engine while minimizing disruption to the overall system operation. With this feature, the system may provide flexibility of modifying the engine for various different flight conditions during time-sensitive operations or in situations demanding high system availability. In some embodiments, the stator 308 and the fan stage may form a modular component that may be hot swapped. In some cases, the stator and / or the fan stage may also be interchangeable to further customize the modular component.

[0063] In some embodiments, a central shaft 316 connects to the core nacelle platform and holds the periphery driven electric motor system securely in place. This central shaft ensures optimal alignment and stability of the motor system, allowing for smooth and efficient engine operation.

[0064] In some embodiments, the fan stage system may comprise features to integrate with a periphery driven electric motor system. This integration ensures that the mechanical operations of the fan stage system and the electric motor system are synchronized, leading to smoother andmore efficient operation of the overall apparatus. The integrated configuration may also contribute to maintaining mechanical balance during operation, which is crucial for the stability and performance of the aircraft engine. This integration may allow for effective conversion of electrical energy into mechanical energy, thereby driving the fan stage system.

[0065] The fan stage or turbine stage may be interchangeable. In particular, the capability of hot swapping a fan stage or turbine stage conveniently provides a specific motor / engine for specific flight conditions during operation of the motor system. In some cases, hot swapping a turbine stage, stator and / or rotor of the electric motor system beneficially allows for replacing parts of the assembled motor system without system shutdown.

[0066] The modular nacelle platform may allow one or more fan stages to be swapped or replaced without the need to shut down the entire engine, offering enhanced flexibility and adaptability to various operational needs. In some embodiments, the fan stage system may accommodate one or more hot swappable fan stages. A specific fan stage of the fan stage system may be selected (e.g., blade architecture, blade profile, blade twist, blade sweep, blade angle, pitch of propeller, variable pitch, location of fan stage in nacelle, etc.) for specific performance characteristics and the one or more fan stages may work in unison to drive the aircraft engine's operation. In some cases, a specific fan stage may be selected by the software of the platform and provided to a user via the GUI. For instance, the system herein may select one or more fan stages with respective blade architectures and / or determine locations of the one or more fan stages in nacelle based on pressure, velocity of air through the interchangeable fan stages, volume of airflow as a metric, and / or motor efficiency or other engine performance parameters on the flight path (e.g., drag parameter, etc.). As described later herein, the software system may aid the operator or pilot to select a fan blade for a flight plan. These blades, each specifically configured and arranged, may manipulate the airflow efficiently to generate the lift and thrust necessary for the aircraft's propulsion and flight. The flight plan may be inputted by the operator or pilot via the GUI. As an example, the software may automatically calculate decisions to decrease battery usage overtime to maximize miles per charge of the motor based on an initial flight plan to determine the optimal blade selections.

[0067] If a fan needs to be swapped with a different fan, taken out or added, the modular configuration and hot swapping mechanism allow for individual fan replacement or modularity at the fan stage, stator / rotor level. For instance, different modular stator and turbine stages as illustrated in FIG. 3 may have substantially the same outer dimension such as the thickness, diameter of the shell housing the stator, outer ring, and the like while the blade architecture (e.g., number of blades, shape, etc.) may be different. The consistent outer dimension of the modular fan stage beneficially allows for easy swapping out a modular component, changing locations ofthe fan stage in the nacelle, changing order of multiple interconnected fan stages and the like. This feature reduces engine downtime, as the entire fan stage system does not need to be dismantled for servicing a single fan. The assembled engine may maintain a consistent performance level even when individual fan components require replacement or servicing.

[0068] In some embodiments, the fan stage system is intricately configured to integrate with the core nacelle platform. This integration forms a cohesive and efficient unit, ensuring optimal functionality and performance of the overall apparatus. The configuration further enhances the system's ability to adapt and respond to changing operational demands. As described elsewhere herein, the fan stage system and the core nacelle platform are configured for hot swapping during system operation. This feature allows for the replacement of the fan stage system components without interrupting the engine's operation. As such, the fan stage system may be updated or serviced without downtime, increasing the operational availability of the aircraft. This advanced integration and hot swapping capability bring a new level of flexibility and efficiency to aircraft engine customization and management.

[0069] As described above, the core nacelle platform which houses the engine's vital parts, and may seamlessly integrate with the fan stage system, provides increased efficiency and performance. This unique combination of an interchangeable fan stage system, core nacelle platform, and hot swapping mechanism improves over the traditional engine configuration, offering increased resilience, flexibility, and operational efficiency.

[0070] In some embodiments, the electric motor system may be integrated with an onboard servo control system and wiring attachment systems for connection with the nacelle core herein allowing for quick replacement of components and control of motor speed and direction. The wiring may be entirely built into the nacelle system as described above allowing for easy wiring hookup between the nacelle core and the stator / fan stage system. In some embodiment, the fan stage, rotor and / or stator of the system may be hot swappable. In some cases, the fan stage system may be releasably integrated into a rotor of an electric motor, and both the stator and rotor of the electric motor may be hot swapped as an operator switches between one motor to another motor for different requirement of mission characteristics and specifications. Systems and methods of the present disclosure may enhance aircraft engine configuration, improving operational efficiency, maintenance convenience, and reliability.

[0071] In some embodiments, an onboard servo control system may be integrated into the apparatus. The servo control system may be used to manage the speed or direction of the electric motor from a selection from a set of pre-defined options. The onboard servo control system provides the ability to adapt the motor's operation as required in a wide range of operational conditions. The servo control system may be commanded to make precise adjustments to themotor’s speed and direction, enabling the apparatus to respond effectively to changes in operational demands or conditions.

[0072] In some embodiments, an onboard servo control system may be configured to control the speed or direction of the electric motor from a range of pre-defined speeds and directions. This capability may optimize the adaptability of the apparatus, as it allows the system to quickly adjust to changing operational conditions. Furthermore, by allowing precise control over the motor's speed and direction, the servo control system may also potentially enhance the performance of the apparatus.

[0073] Platform, Software and Systems for Fan selection and Hot Swapping

[0074] In an aspect, the present disclosure provides methods and a platform aiding the operator or pilot to select a fan blade for a flight plan and managing the hot swapping procedure. As described above, a fan stage may have a specific blades architecture, each blade specifically configured and arranged, may manipulate the airflow efficiently to generate the lift and thrust necessary for the aircraft's propulsion and flight. In some embodiments, the platform may comprise library of a plurality of fan stages each is associated with data related to fan construction. In some cases, the data associated with each fan stage / blade may be obtained from testing. For example, data relate to fan construction for contra-rotating fan stages may be collected using a custom-built wind tunnel system. The wind tunnel testing system may comprise a data acquisition system that collects data for replacement fan parts (e.g., blade profiles, blade twists, blade sweeps, and blade angle). In some cases, the platform may be in communication with the data acquisition system that continuously collect data and update the library of fan stage products. As an example, the data associated each blade or fan stage may be related to pressure, velocity of air through the fan stage, volume of airflow as a metric, and / or motor efficiency when the fan stage is integrated with a selected rotor / stator.

[0075] In some embodiments, the platform may comprise an algorithm for selecting one or more fan stages, and / or stator / rotor parts based at least in part on information about a flight plan. For instance, a flight plan may comprise various flight conditions. The flight conditions may indicate expected fuel bum for the aircraft they are flying (e.g., turbine configuration), the expected power and thrust calculations for pressure altitude (altimeter) and temperature and various other conditions (e.g., distance, payload, etc.). The algorithm may then calculate the necessary engine performance required for the flight plan such as thrust ranges and power consumption, and select one or more fan stages, the rotor / stator of an electric motor from the library based on the data stored in association with each fan stage.

[0076] In some cases, the platform may provide a GUI for a user to input a flight plan. An operator or pilot may be guided to input information about a flight plan. For example, a user mayselect a flight path where upon the selection, details about the flight path (e.g., altitude, distance, fuel bum, temperature, etc.) may be automatically populated by the system. For instance, a user may input a destination and a timing of the flight then the system may automatically generate the flight plan (e.g., expected motor efficiency, thrust efficiency, power efficiency, energy efficiency, etc.). As an example, a short distance flight plan may require high vertical thrust with low energy efficiency and a long-distance flight plan may require low power efficiency with high energy efficiency. Based on the user input information, the software may automatically calculate decisions to decrease battery usage overtime to maximize miles per charge of the motor based on an initial flight plan to determine the optimal blade selections.

[0077] In some cases, the fan stage or motor selection process may be a combination of user input via the GUI and algorithm automation. In some cases, an operator or pilot may have the ultimate authority when making the decision. For example, the system may receive a selection of fan stage via the GUI then make the calculations based on the fan stage selected by the pilot. The GUI may display the feedback or calculation for the pilot to confirm or change the selection. The GUI may aid the pilot in the decision-making process to ensure that they understand the performance factors based on the fan blades selection. In some cases, the feedback displayed on the GUI may help the pilot to understand what the required burn should be to get to the required altitude (e.g., destination of a grocery store vs going across the nation to see family), and what the altitude is actually at during flight operations. In some cases, the algorithm may utilize previously gathered operational data and generate recommendations to the pilot about performance modifications for their fan blade selection to ensure a smoother flight given the information given in the flight plan.

[0078] In some embodiments, the software of the platform may be provided to facilitate control and management of the hot swapping mechanism. For example, the lock / unlock status or a fan stage status (e.g., swap state, operation state) may be displayed within a graphical user interface (GUI). In some cases, the feature to lock / unlock the fan stage may be remotely activated via the GUI. The platform may provide real-time status updates, control features, and diagnostics, forming an interactive interface for the operator. This may enable efficient monitoring and control of the hot swapping process, streamlining the replacement or maintenance operations. The software system may also improve fault detection and diagnosis, helping prevent malfunctions and improving system reliability.

[0079] In some embodiments, at least one QR label may be attached to the core nacelle platform. An operator may scan the QR code on the core nacelle platform to read motor performance characteristics and the operator may continue to modify the onboard engine parameters to verify needed metrics from the fan stages. The QR label may encode a variety ofinformation that characterizes the apparatus, such as component specifications, manufacturing details, maintenance history, and other relevant data. The encoded information may be easily accessed by scanning the QR code using a user device, offering a convenient and efficient way to retrieve detailed information about the apparatus. In some cases, upon scanning the QR code using a user device, the user may be directed to an application to access the real-time data collected by the nacelle platform (e.g., fan stage selection, location of fan stage, engine parameters, etc.), the user may choose to swap out one or more fan stages or modify the engine and the data about the modification may be updated in real-time so the user may visualize the parameters of the modification.

[0080] In some embodiments, the fan stage system or nacelle platform may incorporate a variety of integrated sensors. These sensors may collect a wide range of operational or environmental data. The collected data may provide valuable insights into the system's health and performance, potentially identifying operational issues or predicting possible component failures. The data may also be used to determine when hot swapping is necessary, the real-time fan stage parameters or engine parameters.

[0081] In some embodiments, the fan stage system may comprise a communication module. This module may connect with an external computing system for data processing and interaction. The communication module may support both wired and remote communications, ensuring robust and versatile connectivity. By linking with an external computing system, the communication module may enable advanced data analysis, remote monitoring, and control capabilities, enhancing the overall management and performance of the apparatus.

[0082] FIG. 10 illustrates an example of a hot swapping process. In the example, the hot swapping process may involve dismounting the motor system from the fan stage system, followed by scanning a QR label attached to the core nacelle platform. As described above, the QR label may allow the onsite user to access real-time engine parameters or parts installed in the nacelle platform, aiding in the hot swapping process. The central shaft, which holds the motor system in place, may then be unlocked, and the hot swapping mechanism may be activated. This mechanism enables the efficient replacement of components, potentially reducing system downtime and improving operational efficiency.

[0083] In some cases, the hot swapping mechanism may be controlled by a custom software system, as displayed on a user interface. The operator or user may interact with this system, transmitting commands to unlatch the fan stage system and transition it to a hot swapping mode. The changes and progress of the hot swapping operation may be displayed on a screen in realtime. This interactive interface provides the operator with increased control and monitoring capabilities, enabling an efficient and effective hot swapping process.

[0084] In some embodiments, the process of replacing components involves activating the hot swapping mechanism, which may lead to automatic disconnection of the wiring attachment system and the mechanical latch system of the motor. The automatic disconnection of the wiring attachment system may simplify the process of replacing the fan stage system by eliminating the need for manual disconnection of wiring. Similarly, the automatic disconnection of the mechanical latch system may facilitate easy removal of the fan stage system from the core nacelle platform, thus improving the efficiency and speed of the replacement process.

[0085] FIG. 11 illustrates an example of a process for installation of a fan stage system, and / or the installation of a stator and rotor into the core nacelle platform. The installation may be followed by engaging a latch system to secure the newly installed components. The software system may be utilized to read the position or direction of the installed fan stage system and to ensure the proper setup and alignment of the components. This step-by-step installation process may ensure that the components are securely and correctly installed, helping to ensure the proper function and operational readiness of the fan stage system.

[0086] It should be noted that the systems and methods herein may be implemented in a wide range of air mobility applications (e.g., remote control airplanes, flying cars, vehicles utilizing a propulsion system, etc.) or any other industrial applications where a turbine or fan stage is involved (e.g., power plant energy generation). FIG. 12 illustrates various air mobility applications where a propulsion system is involved.Example

[0087] A small airplane is scheduled to fly route A from Washington DC to Charlotte, NC, and then continue on a longer route B from Charlotte, NC to Houston, TX. Prior to departure, the onboard software system and integrated sensors in the fan stage system detect that the fans currently installed are optimized for shorter flights, like route A. After landing in Charlotte, in preparation for the longer route B, the onboard software system activates the hot swapping mechanism to switch the short-haul fans to a new set of fans optimized for longer flights. The advanced fans are engineered to reduce fuel consumption and increase the efficiency of the motor over longer distances. The hot swapping process is initiated by dismounting the periphery driven electric motor system from the fan stage system, effectively severing both structural and electrical connections. The short-haul fans are then removed and placed on a stand for maintenance and the new long-haul fans are prepared for installation. Once the central shaft that holds the periphery driven electric motor system in place is unlocked, the new fans, already integrated into the rotor of the electric motor system, are secured in place by a uniquely configured latching mechanism. Throughout the process, the custom software system providesreal-time updates and diagnostics related to the operation and the hot swapping of the fan stage system, ensuring seamless integration of the new fans.

[0088] Computing system

[0089] The software, platform, systems and methods as described above may be implemented by a computing system. Referring to FIG. 13, a block diagram is shown depicting an exemplary machine that includes a computer system 1300 (e.g., a processing or computing system) within which a set of instructions may cause a device to perform or execute any one or more of the aspects of the algorithm, platform or software of the present disclosure. The components in FIG. 13 are examples only and do not limit the scope of use or functionality of any hardware, software, embedded logic component, or a combination of two or more such components implementing particular embodiments.

[0090] Computer system 1300 may include one or more processors 1301, a memory 1303, and a storage 1308 that communicate with each other, and with other components, via a bus 240. The bus 240 may also link a display 1332, one or more input devices 1333 (which may, for example, include a keypad, a keyboard, a mouse, a stylus, etc.), one or more output devices 1334, one or more storage devices 1335, and various tangible storage media 1336. All of these elements may interface directly or via one or more interfaces or adaptors to the bus 240. For instance, the various tangible storage media 1336 may interface with the bus 240 via storage medium interface 1326. Computer system 1300 may have any suitable physical form, including but not limited to one or more integrated circuits (ICs), printed circuit boards (PCBs), mobile handheld devices (such as mobile telephones or PDAs), laptop or notebook computers, distributed computer systems, computing grids, or servers.

[0091] Computer system 1300 includes one or more processor(s) 1301 (e.g., central processing units (CPUs) or general-purpose graphics processing units (GPGPUs)) that carry out functions. Processor(s) 1301 optionally contains a cache memory unit 1302 for temporary local storage of instructions, data, or computer addresses. Processor(s) 1301 are configured to assist in execution of computer readable instructions. Computer system 1300 may provide functionality for the components depicted in FIG. 2 as a result of the processor(s) 1301 executing non-transitory, processor-executable instructions embodied in one or more tangible computer-readable storage media, such as memory 1303, storage 1308, storage devices 1335, and / or storage medium 1336. The computer-readable media may store software that implements particular embodiments, and processor(s) 1301 may execute the software. Memory 1303 may read the software from one or more other computer-readable media (such as mass storage device(s) 1335, 1336) or from one or more other sources through a suitable interface, such as network interface 1320. The software may cause processor(s) 1301 to carry out one or more processes or one or more steps of one ormore processes described or illustrated herein. Carrying out such processes or steps may include defining data structures stored in memory 1303 and modifying the data structures as directed by the software.

[0092] The memory 1303 may include various components (e.g., machine readable media) including, but not limited to, a random-access memory component (e.g., RAM 1304) (e.g., static RAM (SRAM), dynamic RAM (DRAM), ferroelectric random-access memory (FRAM), phasechange random access memory (PRAM), etc.), a read-only memory component (e.g., ROM 1305), and any combinations thereof. ROM 1305 may act to communicate data and instructions unidirectionally to processor(s) 1301, and RAM 1304 may act to communicate data and instructions bidirectionally with processor(s) 1301. ROM 1305 and RAM 1304 may include any suitable tangible computer-readable media described below. In one example, a basic input / output system 1306 (BIOS), including basic routines that help to transfer information between elements within computer system 1300, such as during start-up, may be stored in the memory 1303.

[0093] Fixed storage 1308 is connected bidirectionally to processor(s) 1301, optionally through storage control unit 1307. Fixed storage 1308 provides additional data storage capacity and may also include any suitable tangible computer-readable media described herein. Storage 1308 may be used to store operating system 1309, executable(s) 1310, data 1311, applications 1312 (application programs), and the like. Storage 1308 may also include an optical disk drive, a solid-state memory device (e.g., flash-based systems), or a combination of any of the above. Information in storage 1308 may, in appropriate cases, be incorporated as virtual memory in memory 1303.

[0094] In one example, storage device(s) 1335 may be removably interfaced with computer system 1300 (e.g., via an external port connector (not shown)) via a storage device interface 1325. Particularly, storage device(s) 1335 and an associated machine-readable medium may provide non-volatile and / or volatile storage of machine-readable instructions, data structures, program modules, and / or other data for the computer system 1300. In one example, software may reside, completely or partially, within a machine-readable medium on storage device(s) 1335. In another example, software may reside, completely or partially, within processor(s) 1301

[0095] Bus 1340 connects a wide variety of subsystems. Herein, reference to a bus may encompass one or more digital signal lines serving a common function, where appropriate. Bus 1340 may be any of several types of bus structures including, but not limited to, a memory bus, a memory controller, a peripheral bus, a local bus, and any combinations thereof, using any of a variety of bus architectures. As an example and not by way of limitation, such architectures include an Industry Standard Architecture (ISA) bus, an Enhanced ISA (EISA) bus, a MicroChannel Architecture (MCA) bus, a Video Electronics Standards Association local bus (VLB), a Peripheral Component Interconnect (PCI) bus, a PCI-Express (PCI-X) bus, an Accelerated Graphics Port (AGP) bus, HyperTransport (HTX) bus, serial advanced technology attachment (SATA) bus, and any combinations thereof.

[0096] Computer system 1300 may also include an input device 1333. In one example, a user of computer system 1300 may enter commands and / or other information into computer system 1300 via 2input device(s) 1333. Examples of an input device(s) 1333 include, but are not limited to, an alpha-numeric input device (e.g., a keyboard), a pointing device (e.g., a mouse or touchpad), a touchpad, a touch screen, a multi-touch screen, a joystick, a stylus, a gamepad, an audio input device (e.g., a microphone, a voice response system, etc.), an optical scanner, a video or still image capture device (e.g., a camera), and any combinations thereof. In some embodiments, the input device is a Kinect, Leap Motion, or the like. Input device(s) 1333 may be interfaced to bus 1340 via any of a variety of input interfaces 1323 (e.g., input interface 1323) including, but not limited to, serial, parallel, game port, USB, FIREWIRE, THUNDERBOLT, or any combination of the above.

[0097] In particular embodiments, when computer system 1300 is connected to network 1330, computer system 1300 may communicate with other devices, specifically mobile devices and enterprise systems, distributed computing systems, cloud storage systems, cloud computing systems, and the like, connected to network 1330. Communications to and from computer system 1300 may be sent through network interface 1320. For example, network interface 1320 may receive incoming communications (such as requests or responses from other devices) in the form of one or more packets (such as Internet Protocol (IP) packets) from network 1330, and computer system 1300 may store the incoming communications in memory 1303 for processing. Computer system 1300 may similarly store outgoing communications (such as requests or responses to other devices) in the form of one or more packets in memory 1303 and communicated to network 1330 from network interface 1320. Processor(s) 1301 may access these communication packets stored in memory 1303 for processing.

[0098] Examples of the network interface 1320 include, but are not limited to, a network interface card, a modem, and any combination thereof. Examples of a network 1330 or network segment 1330 include, but are not limited to, a distributed computing system, a cloud computing system, a wide area network (WAN) (e.g., the Internet, an enterprise network), a local area network (LAN) (e.g., a network associated with an office, a building, a campus or other relatively small geographic space), a telephone network, a direct connection between two computing devices, a peer-to-peer network, and any combinations thereof. A network, such asnetwork 1330, may employ a wired and / or a wireless mode of communication. In general, any network topology may be used.

[0099] Information and data may be displayed through a display 1332. Examples of a display 1332 include, but are not limited to, a cathode ray tube (CRT), a liquid crystal display (LCD), a thin film transistor liquid crystal display (TFT-LCD), an organic liquid crystal display (OLED) such as a passive-matrix OLED (PMOLED) or active-matrix OLED (AMOLED) display, a plasma display, and any combinations thereof. The display 1332 may interface to the processor(s) 1301, memory 1303, and fixed storage 1308, as well as other devices, such as input device(s) 1333, via the bus 1340. The display 1332 is linked to the bus 1340 via a video interface 1322, and transport of data between the display 1332 and the bus 1340 may be controlled via the graphics control 1321. In some embodiments, the display is a video projector. In some embodiments, the display is a head-mounted display (HMD) such as a VR headset. In further embodiments, suitable VR headsets include, by way of non-limiting examples, HTC Vive, Oculus Rift, Samsung Gear VR, Microsoft HoloLens, Razer OSVR, FOVE VR, Zeiss VR One, Avegant Glyph, Freefly VR headset, and the like. In still further embodiments, the display is a combination of devices such as those disclosed herein.

[0100] In addition to a display 1332, computer system 1300 may include one or more other peripheral output devices 1334 including, but not limited to, an audio speaker, a printer, a storage device, and any combinations thereof. Such peripheral output devices may be connected to the bus 1340 via an output interface 1324. Examples of an output interface 1324 include, but are not limited to, a serial port, a parallel connection, a USB port, a FIREWIRE port, a THUNDERBOLT port, and any combinations thereof.

[0101] In addition or as an alternative, computer system 1300 may provide functionality as a result of logic hardwired or otherwise embodied in a circuit, which may operate in place of or together with software to execute one or more processes or one or more steps of one or more processes described or illustrated herein. Reference to software in this disclosure may encompass logic, and reference to logic may encompass software. Moreover, reference to a computer-readable medium may encompass a circuit (such as an IC) storing software for execution, a circuit embodying logic for execution, or both, where appropriate. The present disclosure encompasses any suitable combination of hardware, software, or both.

[0102] Those of skill in the art will appreciate that the various illustrative logical blocks, modules, circuits, and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or combinations of both. To clearly illustrate this interchangeability of hardware and software, various illustrativecomponents, blocks, modules, circuits, and steps have been described above generally in terms of their functionality.

[0103] The various illustrative functional features, logical blocks, modules, and circuits described in connection with the embodiments disclosed herein may be implemented or performed with a general-purpose processor, a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof configured to perform the functions described herein. A general- purpose processor may be a microprocessor, but in the alternative, the processor may be any conventional processor, controller, microcontroller, or state machine. A processor may also be implemented as a combination of computing devices, e.g., a combination of a DSP and a microprocessor, a plurality of microprocessors, one or more microprocessors in conjunction with a DSP core, or any other such configuration.

[0104] The steps of a method or algorithm described in connection with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by one or more processor(s), or in a combination of the two. A software module may reside in RAM memory, flash memory, ROM memory, EPROM memory, EEPROM memory, registers, hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to the processor such the processor may read information from, and write information to, the storage medium. In the alternative, the storage medium may be integral to the processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In the alternative, the processor and the storage medium may reside as discrete components in a user terminal.

[0105] In accordance with the description herein, suitable computing devices include, by way of non-limiting examples, server computers, desktop computers, laptop computers, notebook computers, sub-notebook computers, netbook computers, netpad computers, set-top computers, media streaming devices, handheld computers, Internet appliances, mobile smartphones, tablet computers, personal digital assistants, video game consoles, and vehicles. Those of skill in the art will also recognize that select televisions, video players, and digital music players with optional computer network connectivity are suitable for use in the system described herein. Suitable tablet computers, in various embodiments, include those with booklet, slate, and convertible configurations, known to those of skill in the art.

[0106] In some embodiments, the computing device includes an operating system configured to perform executable instructions. The operating system is, for example, software, including programs and data, which manages the device’s hardware and provides services for execution ofapplications. Those of skill in the art will recognize that suitable server operating systems include, by way of non-limiting examples, FreeBSD, OpenBSD, NetBSD®, Linux, Apple® Mac OS X Server®, Oracle® Solaris®, Windows Server®, and Novell® NetWare®. Those of skill in the art will recognize that suitable personal computer operating systems include, by way of nonlimiting examples, Microsoft® Windows®, Apple® Mac OS X®, UNIX®, and UNIX-like operating systems such as GNU / Linux®. In some embodiments, the operating system is provided by cloud computing. Those of skill in the art will also recognize that suitable mobile smartphone operating systems include, by way of non-limiting examples, Nokia® Symbian® OS, Apple® iOS®, Research In Motion® BlackBerry OS®, Google® Android®, Microsoft® Windows Phone® OS, Microsoft® Windows Mobile® OS, Linux®, and Palm® WebOS®. Those of skill in the art will also recognize that suitable media streaming device operating systems include, by way of non-limiting examples, Apple TV®, Roku®, Boxee®, Google TV®, Google Chromecast®, Amazon Fire®, and Samsung® HomeSync®. Those of skill in the art will also recognize that suitable video game console operating systems include, by way of nonlimiting examples, Sony® PS3®, Sony® PS4®, Microsoft® Xbox 360®, Microsoft Xbox One, Nintendo® Wii®, Nintendo® Wii U®, and Ouya®.

[0107] Non-transitory computer readable storage medium

[0108] In some embodiments, the platforms, systems, media, and methods disclosed herein include one or more non-transitory computer readable storage media encoded with a program including instructions executable by the operating system of an optionally networked computing device. In further embodiments, a computer readable storage medium is a tangible component of a computing device. In still further embodiments, a computer readable storage medium is optionally removable from a computing device. In some embodiments, a computer readable storage medium includes, by way of non-limiting examples, CD-ROMs, DVDs, flash memory devices, solid state memory, magnetic disk drives, magnetic tape drives, optical disk drives, distributed computing systems including cloud computing systems and services, and the like. In some cases, the program and instructions are permanently, substantially permanently, semipermanently, or non-transitorily encoded on the media.

[0109] Computer program

[0110] In some embodiments, the platforms, systems, media, and methods disclosed herein include at least one computer program, or use of the same. A computer program includes a sequence of instructions, executable by one or more processor(s) of the computing device’s CPU, written to perform a specified task. Computer readable instructions may be implemented as program modules, such as functions, objects, Application Programming Interfaces (APIs), computing data structures, and the like, which perform particular tasks or implement particularabstract data types. In light of the disclosure provided herein, those of skill in the art will recognize that a computer program may be written in various versions of various languages. [OHl] The functionality of the computer readable instructions may be combined or distributed as desired in various environments. In some embodiments, a computer program comprises one sequence of instructions. In some embodiments, a computer program comprises a plurality of sequences of instructions. In some embodiments, a computer program is provided from one location. In other embodiments, a computer program is provided from a plurality of locations. In various embodiments, a computer program includes one or more software modules. In various embodiments, a computer program includes, in part or in whole, one or more web applications, one or more mobile applications, one or more standalone applications, one or more web browser plug-ins, extensions, add-ins, or add-ons, or combinations thereof.

[0112] Web application

[0113] In some embodiments, a computer program includes a web application. In light of the disclosure provided herein, those of skill in the art will recognize that a web application, in various embodiments, utilizes one or more software frameworks and one or more database systems. In some embodiments, a web application is created upon a software framework such as Microsoft® .NET or Ruby on Rails (RoR). In some embodiments, a web application utilizes one or more database systems including, by way of non-limiting examples, relational, non-relational, object-oriented, associative, and XML database systems. In further embodiments, suitable relational database systems include, by way of non-limiting examples, Microsoft® SQL Server, mySQL™, and Oracle®. Those of skill in the art will also recognize that a web application, in various embodiments, is written in one or more versions of one or more languages. A web application may be written in one or more markup languages, presentation definition languages, client-side scripting languages, server-side coding languages, database query languages, or combinations thereof. In some embodiments, a web application is written to some extent in a markup language such as Hypertext Markup Language (HTML), Extensible Hypertext Markup Language (XHTML), or extensible Markup Language (XML). In some embodiments, a web application is written to some extent in a presentation definition language such as Cascading Style Sheets (CSS). In some embodiments, a web application is written to some extent in a client-side scripting language such as Asynchronous Javascript and XML (AJAX), Flash® Actionscript, Javascript, or Silverlight®. In some embodiments, a web application is written to some extent in a server-side coding language such as Active Server Pages (ASP), ColdFusion®, Perl, Java™, JavaServer Pages (JSP), Hypertext Preprocessor (PHP), Python™, Ruby, Tel, Smalltalk, WebDNA®, or Groovy. In some embodiments, a web application is written to some extent in a database query language such as Structured Query Language (SQL). In someembodiments, a web application integrates enterprise server products such as IBM® Lotus Domino®. In some embodiments, a web application includes a media player element. In various further embodiments, a media player element utilizes one or more of many suitable multimedia technologies including, by way of non-limiting examples, Adobe® Flash®, HTML 5, Apple® QuickTime®, Microsoft® Silverlight®, Java™, and Unity®.

[0114] Referring to FIG. 14, in a particular embodiment, an application provision system comprises one or more databases 1400 accessed by a relational database management system (RDBMS) 1410. The database may store the fan stages library and other data (e.g., engine parameters) of the present disclosure. Suitable RDBMSs include Firebird, MySQL, PostgreSQL, SQLite, Oracle Database, Microsoft SQL Server, IBM DB2, IBM Informix, SAP Sybase, SAP Sybase, Teradata, and the like. In this embodiment, the application provision system further comprises one or more application severs 1420 (such as Java servers, .NET servers, PHP servers, and the like) and one or more web servers 1430 (such as Apache, IIS, GWS and the like). The web server(s) optionally expose one or more web services via app application programming interfaces (APIs) 1440. Via a network, such as the Internet, the system provides browser-based and / or mobile native user interfaces.

[0115] Referring to FIG. 15, in a particular embodiment, an application provision system alternatively has a distributed, cloud-based architecture 1500 and comprises elastically load balanced, auto-scaling web server resources 1510 and application server resources 1520 as well synchronously replicated databases 1530.

[0116] Mobile Application

[0117] In some embodiments, a computer program includes a mobile application provided to a mobile computing device. In some embodiments, the mobile application is provided to a mobile computing device at the time it is manufactured. In other embodiments, the mobile application is provided to a mobile computing device via the computer network described herein. One or more features of the software such as scanning the QR code to access real-time nacelle platform data or engine parameters may be provided for mobile applications.

[0118] In view of the disclosure provided herein, a mobile application is created by techniques known to those of skill in the art using hardware, languages, and development environments known to the art. Those of skill in the art will recognize that mobile applications are written in several languages. Suitable programming languages include, by way of non-limiting examples, C, C++, C#, Objective-C, Java™, Javascript, Pascal, Object Pascal, Python™, Ruby, VB.NET, WML, and XHTML / HTML with or without CSS, or combinations thereof.

[0119] Suitable mobile application development environments are available from several sources. Commercially available development environments include, by way of non-limitingexamples, AirplaySDK, alcheMo, Appcelerator®, Celsius, Bedrock, Flash Lite, .NET Compact Framework, Rhomobile, and WorkLight Mobile Platform. Other development environments are available without cost including, by way of non-limiting examples, Lazarus, MobiFlex, MoSync, and Phonegap. Also, mobile device manufacturers distribute software developer kits including, by way of non-limiting examples, iPhone and iPad (iOS) SDK, Android™ SDK, BlackBerry® SDK, BREW SDK, Palm® OS SDK, Symbian SDK, webOS SDK, and Windows® Mobile SDK.

[0120] Those of skill in the art will recognize that several commercial forums are available for distribution of mobile applications including, by way of non-limiting examples, Apple® App Store, Google® Play, Chrome WebStore, BlackBerry® App World, App Store for Palm devices, App Catalog for webOS, Windows® Marketplace for Mobile, Ovi Store for Nokia® devices, Samsung® Apps, and Nintendo® DSi Shop.

[0121] Standalone Application

[0122] In some embodiments, a computer program includes a standalone application, which is a program that is run as an independent computer process, not an add-on to an existing process, e.g., not a plug-in. Those of skill in the art will recognize that standalone applications are often compiled. A compiler is a computer program(s) that transforms source code written in a programming language into binary object code such as assembly language or machine code. Suitable compiled programming languages include, by way of non-limiting examples, C, C++, Objective-C, COBOL, Delphi, Eiffel, Java™, Lisp, Python™, Visual Basic, and VB .NET, or combinations thereof. Compilation is often performed, at least in part, to create an executable program. In some embodiments, a computer program includes one or more executable complied applications.

[0123] Web Browser Plug-in

[0124] In some embodiments, the computer program includes a web browser plug-in (e.g., extension, etc.). In computing, a plug-in is one or more software components that add specific functionality to a larger software application. Makers of software applications support plug-ins to enable third-party developers to create abilities which extend an application, to support easily adding new features, and to reduce the size of an application. When supported, plug-ins enable customizing the functionality of a software application. For example, plug-ins are commonly used in web browsers to play video, generate interactivity, scan for viruses, and display particular file types. Those of skill in the art will be familiar with several web browser plug-ins including, Adobe® Flash® Player, Microsoft® Silverlight®, and Apple® QuickTime®. In some embodiments, the toolbar comprises one or more web browser extensions, add-ins, or add-ons.In some embodiments, the toolbar comprises one or more explorer bars, tool bands, or desk bands.

[0125] In view of the disclosure provided herein, those of skill in the art will recognize that several plug-in frameworks are available that enable development of plug-ins in various programming languages, including, by way of non-limiting examples, C++, Delphi, Java™, PHP, Python™, and VB .NET, or combinations thereof.

[0126] Web browsers (also called Internet browsers) are software applications, configured for use with network-connected computing devices, for retrieving, presenting, and traversing information resources on the World Wide Web. Suitable web browsers include, by way of nonlimiting examples, Microsoft® Internet Explorer®, Mozilla® Firefox®, Google® Chrome, Apple® Safari®, Opera Software® Opera®, and KDE Konqueror. In some embodiments, the web browser is a mobile web browser. Mobile web browsers (also called microbrowsers, mini-browsers, and wireless browsers) are configured for use on mobile computing devices including, by way of non-limiting examples, handheld computers, tablet computers, netbook computers, subnotebook computers, smartphones, music players, personal digital assistants (PDAs), and handheld video game systems. Suitable mobile web browsers include, by way of non-limiting examples, Google® Android® browser, RIM BlackBerry® Browser, Apple® Safari®, Palm® Blazer, Palm® WebOS® Browser, Mozilla® Firefox® for mobile, Microsoft® Internet Explorer® Mobile, Amazon® Kindle® Basic Web, Nokia® Browser, Opera Software® Opera® Mobile, and Sony® PSP™ browser.

[0127] Software Modules

[0128] In some embodiments, the platforms, systems, media, and methods disclosed herein include software, server, and / or database modules, or use of the same. In view of the disclosure provided herein, software modules are created by techniques known to those of skill in the art using machines, software, and languages known to the art. The software modules disclosed herein are implemented in a multitude of ways. In various embodiments, a software module comprises a file, a section of code, a programming object, a programming structure, or combinations thereof. In further various embodiments, a software module comprises a plurality of files, a plurality of sections of code, a plurality of programming objects, a plurality of programming structures, or combinations thereof. In various embodiments, the one or more software modules comprise, by way of non-limiting examples, a web application, a mobile application, and a standalone application. In some embodiments, software modules are in one computer program or application. In other embodiments, software modules are in more than one computer program or application. In some embodiments, software modules are hosted on one machine. In other embodiments, software modules are hosted on more than one machine. Infurther embodiments, software modules are hosted on a distributed computing platform such as a cloud computing platform. In some embodiments, software modules are hosted on one or more machines in one location. In other embodiments, software modules are hosted on one or more machines in more than one location.

[0129] Databases

[0130] In some embodiments, the platforms, systems, media, and methods disclosed herein include one or more databases, or use of the same. In view of the disclosure provided herein, those of skill in the art will recognize that many databases are suitable for storage and retrieval of medical imaging information. In various embodiments, suitable databases include, by way of non-limiting examples, relational databases, non-relational databases, object-oriented databases, object databases, entity-relationship model databases, associative databases, and XML databases. Further non-limiting examples include SQL, PostgreSQL, MySQL, Oracle, DB2, and Sybase. In some embodiments, a database is internet-based. In further embodiments, a database is web-based. In still further embodiments, a database is cloud computing based. In a particular embodiment, a database is a distributed database. In other embodiments, a database is based on one or more local computer storage devices. In some embodiments, the platforms, systems, media, and methods disclosed herein include one or more databases, or use of the same. In view of the disclosure provided herein, those of skill in the art will recognize that many databases are suitable for storage and retrieval of medical imaging information. In various embodiments, suitable databases include, by way of non-limiting examples, relational databases, non-relational databases, object-oriented databases, object databases, entity -relationship model databases, associative databases, and XML databases. Further non-limiting examples include SQL, PostgreSQL, MySQL, Oracle, DB2, and Sybase. In some embodiments, a database is internetbased. In further embodiments, a database is web-based. In still further embodiments, a database is cloud computing based. In a particular embodiment, a database is a distributed database. In other embodiments, a database is based on one or more local computer storage devices

[0131] While preferred embodiments of the present invention have been shown and described herein, it will be obvious to those skilled in the art that such embodiments are provided by way of example only. It is not intended that the invention be limited by the specific examples provided within the specification. While the invention has been described with reference to the aforementioned specification, the descriptions and illustrations of the embodiments herein are not meant to be construed in a limiting sense. Numerous variations, changes, and substitutions will now occur to those skilled in the art without departing from the invention. Furthermore, it shall be understood that all aspects of the invention are not limited to the specific depictions, configurations or relative proportions set forth herein which depend upon a variety of conditionsand variables. It should be understood that various alternatives to the embodiments of the invention described herein may be employed in practicing the invention. It is therefore contemplated that the invention shall also cover any such alternatives, modifications, variations or equivalents. It is intended that the following claims define the scope of the invention and that methods and structures within the scope of these claims and their equivalents be covered thereby

Claims

CLAIMSWHAT IS CLAIMED IS:

1. An apparatus comprising: an interchangeable fan stage system; a core nacelle platform; and a mechanism for hot swapping the interchangeable fan stage system.

2. The apparatus of claim 1, wherein the interchangeable fan stage system is configured to be integrated into the core nacelle platform.

3. The apparatus of claim 2, wherein the interchangeable fan stage system and the core nacelle platform are configured for hot swapping during operation of the system.

4. The apparatus of claim 1, wherein the interchangeable fan stage system comprises a plurality of replaceable fans.

5. The apparatus of claim 1, wherein the interchangeable fan stage system is integrated with at least one periphery driven electric motor system.

6. The apparatus of claim 5, further comprising an onboard servo control system for the periphery driven electric motor system.

7. The apparatus of claim 6, wherein the onboard servo control system is configured to control at least a speed or a direction of the electric motor from a plurality of defined speeds and directions.

8. The apparatus of claim 1, wherein the interchangeable fan stage system and the periphery driven electric motor system are connected by a plurality of structural and electrical connections.

9. The apparatus of claim 1, further comprising a wiring attachment system for wire hookup into the core nacelle platform, and wherein the wiring attachment system is incorporated into the core nacelle platform.

10. The apparatus of claim 1, wherein the periphery driven electric motor system comprises at least one rotor and at least one stator.

11. The apparatus of claim 1, wherein a central shaft connected to the core nacelle platform holds the periphery driven electric motor system in place.

12. The apparatus of claim 1, wherein the interchangeable fan system is integrated into the rotor of the periphery driven electric motor system.

13. The apparatus of claim 1, wherein the interchangeable fan system further comprises a plurality of blades attached to a central hub and an outer ring and wherein the outer ring is attached to the rotor.

14. The apparatus of claim 13, wherein the rotor or the stator of the periphery driven electric motor system are configured for hot swapping between the periphery driven electric motor system and another periphery driven electric motor system.

15. The apparatus of claim 1, wherein the mechanism for hot swapping the interchangeable fan stage system comprises a trap door mechanism for latching and unlatching the interchangeable fan stage system from the core nacelle platform.

16. The apparatus of claim 15, wherein the trap door mechanism is configured to secure the fan stage system during operations and allow for quick release during the hot swapping.

17. The apparatus of claim 1, wherein the mechanism for hot swapping the interchangeable fan stage system further comprises a latching mechanism that locks and unlocks the fan stage system from operational states to a swap state.

18. The apparatus of claim 17, wherein the latching mechanism is configured to securely hold the fan stage system in place during operations, and allow for easy removal during the hot swapping process.

19. The apparatus of claim 1, wherein the mechanism for hot swapping the interchangeable fan stage system comprises a spring system that enables an operator or pilot to visually determine which fan stage is being changed out or swapped.

20. The apparatus of claim 1, further comprising a custom software system configured to control and manage the hot swapping mechanism, wherein the custom software system provides real-time status updates, control features, and diagnostics related to operations for hot swapping of the interchangeable fan stage system.

21. The apparatus of claim 1, further comprising at least one QR label attached to the core nacelle platform, wherein the QR label encodes a variety of information for characterizing the apparatus.

22. The apparatus of claim 1, wherein the interchangeable fan stage system further comprises a plurality of integrated sensors configured to collect at least one set of operational or environmental data relevant to a functioning of the apparatus.

23. The apparatus of claim 22, wherein the collected operational or environmental data is used to monitor a health and a performance of the interchangeable fan stage system and to determine a necessity of a hot swap.

24. The apparatus of claim 1, further comprising a communication module embedded within the interchangeable fan stage system that connects with an external computing system for data processing and interaction.

25. The apparatus of claim 24, wherein the communication module comprises components for wired or remote communications.

26. The apparatus of claim 1, wherein the interchangeable fan stage system comprises an improved nacelle core integrated with wiring, programming, or software components.

27. The apparatus of claim 26, wherein the wiring, programming, or software components are configured for hot swapping of the interchangeable fan stage system.

28. The apparatus of claim 26, wherein the improved nacelle core is configured to allow the fan stage system and stator / rotor to be hot swapped during an operation of an engine.

29. The apparatus of claim 1, wherein the core nacelle platform is configured to support various operational conditions for the interchangeable fan stage system.

30. The apparatus of claim 1, further comprising a user interface configured for monitoring the status of the interchangeable fan stage system during operation.

31. The apparatus of claim 1, wherein the mechanism for hot swapping comprises safety features configured to prevent accidental activation during engine operation.

32. The apparatus of claim 31, wherein the safety features are configured to ensure that the engine operates within predefined parameters during the hot swapping process.

33. The apparatus of claim 27, wherein the programming and software components are configured to provide real-time diagnostics related to the interchangeable fan stage system.

34. The apparatus of claim 1, further comprising a communication module configured to connect the interchangeable fan stage system with an external computing system for data processing and interaction.

35. The apparatus of claim 1, wherein the interchangeable fan stage system is part of a motor or engine that is configured for hot swapping during operation of the motor or engine.

36. The apparatus of claim 35, wherein the fan stage system is interchangeably integrated with the core nacelle platform.

37. The apparatus of claim 35, wherein the motor or engine is an aircraft engine provided with the interchangeable fan stage system.

38. The apparatus of claim 1, wherein the core nacelle platform comprises a modular nacelle platform, wherein the modular nacelle platform is configured to allow for a modular stator and a modular fan / turbine stage to be interchangeably integrated as part of an engine.

39. The apparatus of claim 38, wherein the modular nacelle platform comprises structures and features configured for an exchange of fan stages, modular stators, and rotors of the engine.

40. The apparatus of claim 38, wherein the modular nacelle platform comprises a hot swapping mechanism.

41. The apparatus of claim 40, wherein the hot swapping mechanism comprises a latching mechanism that includes mechanical components configured for temporarily joining moving parts relative to each other.

42. The apparatus of claim 41, wherein the latching mechanism is actuated to lock or unlock the coupling between the modular stator and the modular fan / turbine stage.

43. The apparatus of claim 41, wherein the latching mechanism is actuated to release the coupling and allow the joining of the two parts to separate.

44. The apparatus of claim 38, wherein the modular nacelle platform includes a latching mechanism.

45. The apparatus of claim 44, wherein the modular nacelle platform comprises a rear nacelle core, a front nacelle core, a permanent nacelle cover, a nacelle cover latch, or a combination thereof.

46. The apparatus of claim 45, wherein the permanent nacelle cover connects the rear nacelle core and the front nacelle core.

47. The apparatus of claim 45, wherein the nacelle cover latch is actuated to be released from the permanent nacelle cover such that a modular fan stage and / or stator is slid into a slot.

48. The apparatus of claim 47, wherein the slot has a width to fit one or more fan stages and stators.

49. The apparatus of claim 38, wherein the modular nacelle platform comprises a plurality of slots, each corresponding to a location in the nacelle platform.

50. The apparatus of claim 49, wherein one slot fits a single fan stage.

51. The apparatus of claim 49, wherein a slot is selected from the plurality of slots to receive a modular stator or turbine stage.

52. The apparatus of claim 38, wherein the modular nacelle platform accommodates a plurality of fan stages.

53. The apparatus of claim 45, wherein the nacelle cover latch joins with the permanent nacelle cover, thereby forming a hatch cover or shell for the internal fan stage, rotor, stator, and other components of the engine.

54. The apparatus of claim 38, wherein the modular nacelle platform comprises a supporting structure.

55. The apparatus of claim 54, wherein the supporting structure provides additional structural rigidity to the nacelle platform.

56. The apparatus of claim 54, wherein the supporting structure is configured to mount one or more turbine stages and one or more stators.

57. The apparatus of claim 54, wherein the supporting structure helps to lock the modular stator and fan stage in place once they are integrated and mounted to the supporting structure.

58. The apparatus of claim 57, wherein the modular fan stage and stator are prevented from moving once they are mounted and secured to the supporting structure.

59. The apparatus of claim 1, wherein a wiring attachment system is incorporated into the core nacelle platform.

60. The apparatus of claim 59, wherein the nacelle platform comprises built-in wiring and circuitry such that upon mounting the modular stator to the supporting structure, the wiring between the modular stator and the nacelle core is automatically connected.

61. The apparatus of claim 60, wherein the wiring connection is located within the permanent nacelle cover such that the fan stage and / or stator are swapped in and out in a plug and play fashion.

62. The apparatus of claim 60, wherein the circuitry of the nacelle platform is configured to automatically detect the opening of the nacelle cover latch and, upon detection, automatically disconnect the wiring.

63. The apparatus of claim 63, wherein the connection and disconnection of an electronic communication between the stator and the nacelle is remotely controlled.

64. The apparatus of claim 5, wherein the fan stage system and the periphery driven electric motor system are connected through structural and electrical connections.

65. The apparatus of claim 64, wherein the connections between the fan stage system and the electric motor system ensure an exchange of power and data.

66. The apparatus of claim 40, wherein the hot swapping mechanism further comprises a trap door mechanism that controls the latching and unlatching of the hatch cover via the core nacelle platform software.

67. The apparatus of claim 66, wherein a user activates the latching or unlatching of the hatch cover through a button within the user interface of the nacelle platform software.

68. The apparatus of claim 67, wherein the latch / unlatch action is actuated by an electronic signal received by the circuitry of the nacelle platform.

69. The apparatus of claim 66, wherein manual activation of the latching and unlatching of the hatch cover is provided in addition to the user interface.

70. The apparatus of claim 69, wherein the user interface provides the status of the hatch cover and displays information about the current installed fan stage and stator / rotor.

71. The apparatus of claim 39, wherein the modular nacelle platform is configured to lock or unlock the fan stages to switch the fan stages between operational states and a swap state.

72. The apparatus of claim 71, wherein the latching mechanism locks and unlocks the fan stage system from operational states to a swap state, securing the fan system during operation of the apparatus.

73. The apparatus of claim 72, wherein the latching mechanism provides a secure method to fasten and release the components during the hot swapping process.

74. The apparatus of claim 73, wherein the latching mechanism ensures that the fan stage system is securely held in place during regular operation.

75. The apparatus of claim 74, wherein the latch is unlocked during maintenance or hot swapping to allow for easy removal and replacement of components.

76. The apparatus of claim 71, wherein the lock / unlock status or a fan stage status is displayed within a graphical user interface (GUI).

77. The apparatus of claim 76, wherein the feature to lock or unlock the fan stage is remotely activated via the GUI.

78. The apparatus of claim 40, wherein the hot swapping mechanism comprises a spring system.

79. The apparatus of claim 78, wherein the spring system is configured to spring out a fan stage from the slot, allowing an operator or pilot to visually determine which fan stage is being changed out or swapped.

80. The apparatus of claim 1, wherein the nacelle platform allows for hot swapping a fan stage, a stator, and / or rotor of an engine.

81. The apparatus of claim 80, wherein the hot swappable fan stage is coupled to a periphery driven electric motor system such that a modular stator and turbine / fan stage are swapped in and out without disassembling parts of the existing system.

82. The apparatus of claim 81, wherein the modular stator and turbine stage is a modular package that slides into the slot in a plug and play fashion.

83. The apparatus of claim 81, wherein the modular stator is interchangeable based on different flight conditions or mission criteria.

84. The apparatus of claim 83, wherein the mission criteria include thrust / power efficiency requirement, energy efficiency requirement, fuel / distance requirement, or a combination thereof.

85. The apparatus of claim 83, wherein the stator comprises structures or mechanical features that allow it to be locked to the nacelle platform and interlocked with other stators when multiple stators or fan stages are preferred.

86. The apparatus of claim 85, wherein the modular stator comprises interlocking structures to releasably couple the stator to other modular stators.

87. The apparatus of claim 1, wherein the fan stage system comprises features integrated with the rotor of the motor system to enhance the efficiency of airflow within the system.

88. The apparatus of claim 1, wherein a central shaft connects to the core nacelle platform and holds the periphery driven electric motor system securely in place.

89. The apparatus of claim 88, wherein the central shaft ensures optimal alignment and stability of the motor system, allowing for smooth and efficient engine operation.

90. The apparatus of claim 1, wherein the fan stage system is selected based on blade architecture, blade profile, blade twist, blade sweep, blade angle, pitch of propeller, variable pitch, location of the fan stage in the nacelle, or any combination thereof.

91. The apparatus of claim 90, wherein one or more fan stages work in unison to drive an aircraft engine's operation.

92. The apparatus of claim 88, wherein the fan stage system is selected by software of the platform and provided to a user via the graphical user interface (GUI).

93. The apparatus of claim 92, wherein the software determines locations of the one or more fan stages in the nacelle based on pressure, velocity of air through the interchangeable fan stages, volume of airflow, motor efficiency, or any combination thereof.

94. The apparatus of claim 92, wherein the software aids the operator or pilot in selecting a fan blade for a flight plan.

95. The apparatus of claim 94, wherein the flight plan is inputted by the operator or pilot via the GUI.

96. The apparatus of claim 94, wherein the software automatically calculates decisions to decrease battery usage over time to maximize miles per charge of the motor based on an initial flight plan to determine optimal blade selections.

97. The apparatus of claim 1, wherein the fan stage system and the core nacelle platform are configured for hot swapping during system operation.

98. The apparatus of claim 97, wherein the hot swapping feature allows for the replacement of the fan stage system components without interrupting the engine's operation.

99. The apparatus of claim 5, wherein the electric motor system is configured with an onboard servo control system and / or wiring attachment systems for connection with the nacelle core.

100. The apparatus of claim 99, wherein the wiring is built into the nacelle system, allowing for wiring hookup between the nacelle core and the stator or fan stage system.

101. The apparatus of claim 10, wherein the fan stage, rotor, and / or stator of the system are hot swappable.

102. The apparatus of claim 100, wherein the fan stage system is configured into a rotor of an electric motor, allowing both the stator and rotor of the electric motor to be hot swapped.

103. A method for replacing the interchangeable fan stage system, comprising the steps of:(a) dismounting the periphery driven electric motor system from the interchangeable fan stage system, including severing both structural and electrical connections;(b) placing the dismounted periphery driven electric motor system onto a stand for customization, wherein a power cable is attached to the periphery driven electric motor system to maintain an onboard circuitry during customization;(c) scanning the QR label located on the core nacelle platform to transmit the data about the apparatus to the external computing system;(d) unlocking the central shaft that holds the periphery driven electric motor system in place; and(e) Activating the mechanism for hot swapping the interchangeable fan stage system.

104. The method of claim 103, wherein the mechanism for hot swapping the interchangeable fan stage system is controlled by the custom software system.

105. The method of claim 104, wherein the operator interacts with the custom software system for transmitting at least a set of commands for unlatching and transitioning the interchangeable fan stage system to a hot swapping mode.

106. The method of claim 105, wherein the custom software system displays a change of the interchangeable fan stage system on a screen.

107. The method of claim 105, further comprising the steps of:(a) activating the hot swapping of the interchangeable fan stage system;(b) automatically disconnecting the wiring attachment system between the stator of the periphery driven electric motor system and core nacelle platform; and(c) automatically disconnecting a mechanical latch system of the periphery driven electric motor system.

108. A method for installing the interchangeable fan stage system, comprising the steps of:(a) installing a stator and rotor in the interchangeable fan stage system;(b) engaging the mechanical latch system to secure the interchangeable fan stage system, where the interchangeable fan stage system is integrated with the mechanical latching system and the central shaft for structural stability; and(c) utilizing the custom software system to read the position or direction of the interchangeable fan stage system.

109. The method of claim 103, wherein the interchangeable fan stage system is configured to be integrated into the core nacelle platform.

110. The method of claim 109, wherein the interchangeable fan stage system and the core nacelle platform are configured for hot swapping during operation of the system.

111. The method of claim 103, wherein the interchangeable fan stage system includes a plurality of replaceable fans.

112. The method of claim 103, wherein the interchangeable fan stage system is integrated with at least one periphery driven electric motor system.

113. The method of claim 112, further comprising an onboard servo control system for the periphery driven electric motor system.

114. The method of claim 113, wherein the onboard servo control system is configured to control at least one speed or direction of the electric motor from a plurality of defined speeds and directions.

115. The method of claim 103, wherein the interchangeable fan stage system and the periphery driven electric motor system are connected by a plurality of structural and electrical connections.

116. The method of claim 103, further comprising a wiring attachment system for wire hookup into the core nacelle platform, wherein the wiring attachment system is incorporated into the core nacelle platform.

117. The method of claim 103, wherein the periphery driven electric motor system comprises at least one rotor and at least one stator.

118. The method of claim 103, wherein a central shaft connected to the core nacelle platform holds the periphery driven electric motor system in place.

119. The method of claim 103, wherein the interchangeable fan system is integrated into the rotor of the periphery driven electric motor system.

120. The method of claim 103, wherein the interchangeable fan system further comprises a plurality of blades attached to a central hub and an outer ring wherein the outer ring is attached to the rotor.

121. The method of claim 103, wherein the rotor or the stator of the periphery driven electric motor system are configured for hot swapping between periphery driven electric motor system to another periphery driven electric motor system.

122. The method of claim 103, wherein the mechanism for hot swapping the interchangeable fan stage system components comprises a trap door mechanism for latching and unlatching the interchangeable fan stage system from the core nacelle platform.

123. The method of claim 122, wherein the trap door mechanism is configured to secure the fan stage system during operations and allow for quick release during the hot swapping process.

124. The method of claim 103, wherein the mechanism for hot swapping the interchangeable fan stage system further comprises a latching mechanism that locks and unlocks the fan stage system from operational states to a swap state.

125. The method of claim 124, wherein the latching mechanism is configured to securely hold the fan stage system in place during operations, and allow for easy removal during the hot swapping process.

126. The method of claim 103, wherein the mechanism for hot swapping the interchangeable fan stage system further comprises a spring system that enables an operator or pilot to visually determine which fan stage is being changed out or swapped.

127. The method of claim 103, further comprising a custom software system that controls and manages the hot swapping mechanism, wherein the custom software system provides real-time status updates, control features, and diagnostics related to the operation and hot swapping of the interchangeable fan stage system.

128. The method of claim 103, further comprising at least one QR label attached to the core nacelle platform, wherein the QR label encodes a variety of information for characterizing the apparatus.

129. The method of claim 103, wherein the interchangeable fan stage system further comprises a plurality of integrated sensors configured to collect at least one set of operational or environmental data relevant to the functioning of the apparatus.

130. The method of claim 129, wherein the collected operational or environmental data is used to monitor the health and performance of the interchangeable fan stage system and to determine a necessity of a hot swap.

131. The method of claim 103, further comprising a communication module embedded within the interchangeable fan stage system that connects with an external computing system for data processing and interaction.

132. The method of claim 131, wherein the communication module comprises components for wired or remote communications.

133. The method of claim 103, wherein the interchangeable fan stage system comprises an improved nacelle core integrated with wiring, programming, or software components.

134. The method of claim 133, wherein the wiring, programming, or software components are configured for hot swapping of the interchangeable fan stage system.

135. The method of claim 133, wherein the improved nacelle core is configured to allow the fan stage system and stator / rotor to be hot swapped during an operation of an engine.

136. The method of claim 103, wherein the core nacelle platform is configured to support various operational conditions for the interchangeable fan stage system.

137. The method of claim 103, further comprising a user interface configured for monitoring the status of the interchangeable fan stage system during operation.

138. The method of claim 103, wherein the mechanism for hot swapping comprises safety features configured to prevent accidental activation during engine operation.

139. The method of claim 138, wherein the safety features are configured to ensure that the engine operates within predefined parameters during the hot swapping process.

140. The method of claim 134, wherein the programming and software components are configured to provide real-time diagnostics related to the interchangeable fan stage system.

141. The method of claim 103, further comprising a communication module configured to connect the interchangeable fan stage system with an external computing system for data processing and interaction.

142. The method of claim 103, wherein the interchangeable fan stage system is part of a motor or engine that is configured for hot swapping during operation of the motor or engine.

143. The method of claim 142, wherein the fan stage system is interchangeably integrated with the core nacelle platform.

144. The method of claim 143, wherein the motor or engine is an aircraft engine provided with the interchangeable fan stage system.

145. The method of claim 103, wherein the core nacelle platform comprises a modular nacelle platform, wherein the modular nacelle platform is configured to allow for a modular stator and a modular fan / turbine stage to be interchangeably integrated as part of an engine.

146. The method of claim 145, wherein the modular nacelle platform comprises structures and features configured for an exchange of fan stages, modular stators, and rotors of the engine.

147. The method of claim 146, wherein the modular nacelle platform comprises a hot swapping mechanism.

148. The method of claim 147, wherein the hot swapping mechanism comprises a latching mechanism that includes mechanical components configured for temporarily joining moving parts relative to each other.

149. The method of claim 148, wherein the latching mechanism is actuated to lock or unlock the coupling between the modular stator and the modular fan / turbine stage.

150. The method of claim 148, wherein the latching mechanism is actuated to release the coupling and allow the joining of the two parts to separate.

151. The method of claim 146, wherein the modular nacelle platform includes a latching mechanism.

152. The method of claim 151, wherein the modular nacelle platform comprises a rear nacelle core, a front nacelle core, a permanent nacelle cover, a nacelle cover latch, or a combination thereof.

153. The method of claim 152, wherein the permanent nacelle cover connects the rear nacelle core and the front nacelle core.

154. The method of claim 153, wherein the nacelle cover latch is actuated to be released from the permanent nacelle cover such that a modular fan stage and / or stator is slid into a slot.-SO-155. The method of claim 154, wherein the slot has a width to fit one or more fan stages and stators.

156. The method of claim 146, wherein the modular nacelle platform comprises a plurality of slots, each corresponding to a location in the nacelle platform.

157. The method of claim 156, wherein one slot fits a single fan stage.

158. The method of claim 156, wherein a slot is selected from the plurality of slots to receive a modular stator or turbine stage.

159. The method of claim 146, wherein the modular nacelle platform accommodates a plurality of fan stages.

160. The method of claim 159, wherein the nacelle cover latch joins with the permanent nacelle cover, thereby forming a hatch cover or shell for the internal fan stage, rotor, stator, and other components of the engine.

161. The method of claim 146, wherein the modular nacelle platform comprises a supporting structure.

162. The method of claim 161, wherein the supporting structure provides additional structural rigidity to the nacelle platform.

163. The method of claim 161, wherein the supporting structure is configured to mount one or more turbine stages and one or more stators.

164. The method of claim 161, wherein the supporting structure helps to lock the modular stator and fan stage in place once they are integrated and mounted to the supporting structure.

165. The method of claim 154, wherein the modular fan stage and stator are prevented from moving once they are mounted and secured to the supporting structure.

166. The method of claim 103, wherein a wiring attachment system is incorporated into the core nacelle platform.

167. The method of claim 166, wherein the nacelle platform comprises built-in wiring and circuitry such that upon mounting the modular stator to the supporting structure, the wiring between the modular stator and the nacelle core is automatically connected.

168. The method of claim 167, wherein the wiring connection is located within the permanent nacelle cover such that the fan stage and / or stator are swapped in and out in a plug and play fashion.

169. The method of claim 167, wherein the circuitry of the nacelle platform is configured to automatically detect the opening of the nacelle cover latch and, upon detection, automatically disconnect the wiring.

170. The method of claim 168, wherein the connection and disconnection of an electronic communication between the stator and the nacelle is remotely controlled.

171. The method of claim 143, wherein the fan stage system and the periphery driven electric motor system are connected through structural and electrical connections.

172. The method of claim 171, wherein the connections between the fan stage system and the electric motor system ensure an exchange of power and data.

173. The method of claim 147, wherein the hot swapping mechanism further comprises a trap door mechanism that controls the latching and unlatching of the hatch cover via the core nacelle platform software.

174. The method of claim 173, wherein a user activates the latching or unlatching of the hatch cover through a button within the user interface of the nacelle platform software.

175. The method of claim 174, wherein the latch / unlatch action is actuated by an electronic signal received by the circuitry of the nacelle platform.

176. The method of claim 175, wherein manual activation of the latching and unlatching of the hatch cover is provided in addition to the user interface.

177. The method of claim 176, wherein the user interface provides the status of the hatch cover and displays information about the current installed fan stage and stator / rotor.

178. The method of claim 161, wherein the modular nacelle platform is configured to lock or unlock the fan stages to switch the fan stages between operational states and a swap state.

179. The method of claim 151, wherein the latching mechanism locks and unlocks the fan stage system from operational states to a swap state, securing the fan system during operation of the apparatus.

180. The method of claim 179, wherein the latching mechanism provides a secure method to fasten and release the components during the hot swapping process.

181. The method of claim 180, wherein the latching mechanism ensures that the fan stage system is securely held in place during regular operation.

182. The method of claim 175, wherein the latch is unlocked during maintenance or hot swapping to allow for easy removal and replacement of components.

183. The method of claim 178, wherein the lock or unlock status or a fan stage status is displayed within a graphical user interface (GUI).

184. The method of claim 183, wherein a feature to lock or unlock the fan stage is remotely activated via the GUI.

185. The method of claim 173, wherein the hot swapping mechanism comprises a spring system.

186. The method of claim 185, wherein the spring system is configured to spring out a fan stage from the slot, allowing an operator or pilot to visually determine which fan stage is being changed out or swapped.

187. The method of claim 145, wherein the modular nacelle platform allows for hot swapping a fan stage, a stator, and / or rotor of an engine.

188. The method of claim 187, wherein the hot swappable fan stage is coupled to a periphery driven electric motor system such that a modular stator and turbine / fan stage are swapped in and out without disassembling parts of the existing system.

189. The method of claim 188, wherein the modular stator and turbine stage is a modular package that slides into the slot in a plug and play fashion.

190. The method of claim 189, wherein the modular stator is interchangeable based on different flight conditions or mission criteria.

191. The method of claim 190, wherein the mission criteria include thrust / power efficiency requirement, energy efficiency requirement, fuel / distance requirement, or a combination thereof.

192. The method of claim 190, wherein the modular stator comprises structures or mechanical features that allow it to be locked to the nacelle platform and interlocked with other stators when multiple stators or fan stages are preferred.

193. The method of claim 190, wherein the modular stator comprises interlocking structures to releasably couple the stator to other modular stators.

194. The method of claim 181, wherein the fan stage system comprises features integrated with the rotor of the motor system to enhance the efficiency of airflow within the system.

195. The method of claim 166, wherein a central shaft connects to the core nacelle platform and holds the periphery driven electric motor system securely in place.

196. The method of claim 195, wherein the central shaft ensures optimal alignment and stability of the motor system, allowing for smooth and efficient engine operation.

197. The method of claim 194, wherein the fan stage system is selected based on blade architecture, blade profile, blade twist, blade sweep, blade angle, pitch of propeller, variable pitch, location of the fan stage in the nacelle, or any combination thereof.

198. The method of claim 197, wherein one or more fan stages work in unison to drive an aircraft engine's operation.

199. The method of claim 197, wherein the fan stage system is selected by software of the platform and provided to a user via the graphical user interface (GUI).

200. The method of claim 199, wherein the software determines locations of the one or more fan stages in the nacelle based on pressure, velocity of air through the interchangeable fan stages, volume of airflow, motor efficiency, or any combination thereof.

201. The method of claim 199, wherein the software aids the operator or pilot in selecting a fan blade for a flight plan.

202. The method of claim 201, wherein the flight plan is inputted by the operator or pilot via the GUI.

203. The method of claim 199, wherein the software automatically calculates decisions to decrease battery usage over time to maximize miles per charge of the motor based on an initial flight plan to determine optimal blade selections.

204. The method of claim 199, wherein the fan stage system and the core nacelle platform are configured for hot swapping during system operation.

205. The method of claim 204, wherein the hot swapping feature allows for the replacement of the fan stage system components without interrupting the engine's operation.

206. The method of claim 195, wherein the electric motor system is configured with an onboard servo control system and / or wiring attachment systems for connection with the nacelle core.

207. The method of claim 196, wherein the wiring is built into the nacelle system, allowing for wiring hookup between the nacelle core and the stator or fan stage system.

208. The method of claim 207, wherein the fan stage, rotor, and / or stator of the system are hot swappable.

209. The method of claim 208, wherein the fan stage system is configured into a rotor of an electric motor, allowing both the stator and rotor of the electric motor to be hot swapped.

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