Control system for UAVs

Abstract

A stabilization system and method for an unmanned aerial vehicle (UAV) (fig 1, 100) carrying a payload 2414. A housing body houses control circuitry of the UAV. One or more rotors 2402, 2404, 2406, 2408 are arranged around the housing body 2410 to power flight of the UAV. One or more sliding guides are provided at the housing body. A movable attachment point (fig 29, 2908) is slidably connected to the sliding guide(s) (fig 29, 2805) of the housing body. One or more sensors are capable of sensing displacement of the movable attachment point and generating a signal relating to the displacement and to transmit it to the control circuitry. The control circuitry is arranged, in response to receiving the signal relating 0 to the displacement, to analyse the signal and to output a control signal for adjusting rotor speeds 1 of one or more of the rotors so as to stabilize a payload carried by the UAV. The housing body may include two sliding guides crossing one another and that intersect at a central region of the housing body. The sliding guides may be perpendicular to one another. A corresponding method is also disclosed.

Description

Unmanned aerial vehicles (UAVs), also known as drones, have applications in numerous fields, including surveillance, package delivery, agriculture, and humanitarian efforts. The capabilities of UAVs have grown significantly over time. UAVs or drones can be operated remotely or function autonomously without a human pilot on board. UAVs include components such as control systems, sensors, navigation systems, and communication systems, which enable them to navigate during flight and execute designated tasks. UAVs have grown in popularity in recent years due to their potential in a wide array of applications and industries which has in turn attracted innovation. Modular drones are the outcome of the significant advancements in the field of UAV or drone technology. Modular drones offer architecture with flexibility in design, customization, and adaptability in the shape and components of the UAV. Modular drones provide the ability to swap or upgrade drone components without requiring technical knowledge of the propulsion systems, payload attachments, communication systems, sensors, batteries, and frame structure. By using standardized connectors and interfaces, users can effortlessly replace or upgrade these components. Modular drones generally consist of a main control unit that serves as the brain of the drone, and interchangeable payloads or modules that can be attached or detached as required by a user. Along with modular drone technology, integrating a swarm of drones is a further innovation in the field of drone technology. The swarm concept is inspired by insects and their colonies where individual insects work in collaboration to complete a task. In swarm or integrated formations, the drones’ autonomous operations are carried out with the help of wireless communication between individual drones in real-time. This integration of drones offers several advantages over traditional individual drone operations since the swarm capability offers greater speed and efficiency. By working together, the workload is also distributed. In the context of swarm drone technology, effective communication between individual drones and their central control system plays an important role in the swarm capability and integration of drones. In recent years, the utilization of UAVs has skyrocketed across various sectors, from aerial photography and package delivery to critical search and rescue operations. However, a persistent challenge has plagued these flying marvels: the instability of their payloads. As UAVs navigate through unpredictable air currents or execute complex maneuvers, their attached payloads often suffer from undesirable oscillations and movements, compromising the safety of transported goods, or the precision of deployed equipment. Known methods and devices have their limitations and drawbacks. For instance, balancing the payload only in near-flight testing does not ensure its stability during the entire flight, especially for payloads containing movable elements such as liquids. Known systems may also not adequately address complex, multi-directional disturbances. Collapsible arm systems and specialized attachment apparatuses focus on specific applications rather than providing comprehensive stabilization solutions. Platform stabilization systems for vertical take-off and landing (VTOL) aircraft may not be directly applicable to the diverse payload types and sizes carried by modern UAVs. The limitations of existing payload stabilization methods have created a pressing need for a more sophisticated, adaptable, and efficient solution. As UAVs continue to evolve and take on increasingly complex roles in our society, the demand for a stabilization system that can maintain payload equilibrium across diverse operational scenarios has never been more critical. The preceding discussion of the background is intended only to facilitate an understanding of the present disclosure. It should be appreciated that the discussion is not an acknowledgment or admission that any of the material referred to was part of the common general knowledge in the art as at the priority date of the application. SUMMARY In accordance with an aspect of the present disclosure there is provided a stabilization system for an unmanned aerial vehicle (UAV) carrying a payload, the system comprising: a housing body that houses control circuitry of the UAV; one or more rotors arranged around the housing body, the rotors configured to power flight of the UAV; one or more sliding guides provided at the housing body; a movable attachment point that is slidably connected to the sliding guide(s) of the housing body, the moveable attachment point being arranged for attachment to a payload; and one or more sensors that are capable of sensing displacement of the movable attachment point and generating a signal relating to the displacement and to transmit it to the control circuitry, wherein the control circuitry is arranged, in response to receiving the signal relating to the displacement, to analyze the signal and to output a control signal for adjusting rotor speeds of one or more of the rotors so as to stabilize a payload carried by the UAV. The system may include a memory for storing computer-readable program code and a processor for executing the computer-readable program code. The housing body may include two sliding guides crossing one another. The sliding guides may also be termed sliding paths. The sliding guides may intersect at a central region of the housing body. The sliding guides may be perpendicular to one another. The moveable attachment point may be located at a central region of the housing body in a resting position of the attachment point. One or more biasing device(s) may be provided in the one or more sliding guide(s). The biasing device(s) may be arranged to dampen lateral movement of the attachment point. The biasing device(s) may be one or more springs, or other biasing means or damping means or shock absorbing means (e.g. hydraulic shock absorbers or electromagnetic shock absorbers). The one or more sensors may include a fixed capacitor plate at a terminal end of one or more of the sliding guide(s). The one or more sensors may further include a movable capacitor plate traversable along the sliding guide(s). Generating a signal relating to the displacement may include sensing a change in capacitance of the fixed and moveable capacitor plates. The one or more sensors may include one or more piezoelectric sensors integrated into the sliding path(s). The piezoelectric sensor(s) may be arranged to generate the signal relating to the displacement of the movable attachment point. The system may include a vertical shaft extending from the housing body for connecting a payload thereto. The one or more sliding guide(s) may be in the form of a V-shaped guide structure with inclined surfaces. The movable attachment point may be capable of traversing the inclined surfaces. A tether may connect the attachment point to a payload. The V-shaped guide structure may include a series of discrete steps on the inclined surfaces. The system may include a control signal generator component for generating rotor speed adjustment signal(s) based on output from the control circuitry. The system may further include a rotor speed controller for implementing rotor speed adjustment based on the rotor speed adjustment signal(s). The system may include an adaptive positioning module for adjusting positions of UAV rotors in response to payload displacement. In accordance with another exemplary aspect of the present disclosure there is provided an unmanned aerial vehicle (UAV) comprising a stabilization system as defined herein, and a payload attached to the attachment point of the stabilization system. In accordance with another aspect of the present disclosure there is provided a method for stabilizing a payload carried by an unmanned aerial vehicle (UAV), the method comprising: detecting displacement of a movable attachment point along one or more sliding guides at a housing body of the UAV; receiving and processing data relating to the displacement using control circuitry onboard the UAV, and in response thereto, generating one or more control signals; and adjusting speeds of one or more rotors of the UAV based on the generated control signal(s) so as to counteract the displacement of the moveable attachment point and thereby stabilizing the payload carried by the UAV. The step of detecting may include measuring changes in capacitance between fixed and movable capacitor plates provided along the sliding guides. The step of detecting may include measuring electrical signals generated by piezoelectric sensors in response to pressure from movement of the attachment point. In accordance with a further aspect of the disclosure there is provided a computer program product for a stabilization system for an unmanned aerial vehicle (UAV) carrying a payload, the computer program product comprising a computer-readable medium having stored computer-readable program code for performing the steps of the method(s) of the present disclosure. In accordance with another aspect of the present disclosure there is provided a control system for an integrated assembly of unmanned aerial vehicles (UAVs), comprising a control unit housing capable of initiating integration of the UAVs using a control-unit-to-control-unit configuration, brick-to-brick configuration, or a propeller-to-propeller unit configuration. Further features provide for the computer-readable medium to be a non-transitory computer-readable medium and for the computer-readable program code to be executable by a processing circuit. The control unit housing may house modules including a battery, power distribution board, sensing unit, global positioning system (GPS) unit, digital signal processing (DSP) module or control circuitry, and a radio control receiver. The control unit housing may allow for various configurations of a UAV. Each configuration may comprise either a centralized, or decentralized communication respectively. Each side of the control unit housing may include a locking mechanism. The locking mechanism may be configured to attach to a control unit housing of another UAV or a propeller unit. The locking mechanism of the individual modular UAV unit may allow an angle of the propeller unit to change its orientation if a balancing issue arises or initiate an integration process. The UAV or done may be modular. The control system may include a connecting mechanism, the connecting mechanism may connect the control unit housing and the propeller unit. The control unit housing may be connected to another control unit housing. In some embodiments, the control system may include a payload inversion mechanism configured to overcome a balancing issue, a gravity shifting mechanism configured to overcome a problem relating to propeller failure, and a detailed decision-making mechanism configured to overcome battery-related or miscellaneous issues. In accordance with a further aspect of the present disclosure there is provided a control system for modular UAVs or drones and an integration process. The control system and integration process may include a detailed assembly and an alignment mechanism. The detailed assembly may comprise a central control unit, a propeller unit, and a motor to actuate the propeller. The central control unit may comprise relevant modules to fulfill an intended task. The relevant modules may be a battery, power distribution board, sensing unit, GPS unit, DSP module or control circuitry, or a radio control receiver. The propeller unit may include a connection with the central control unit. The connection may be a fixed support and a movable lock. The connection between the central control unit and the propeller unit may be a flexible lock and support. The support may allow the propeller unit to adjust its angle based on configuration and integration requirements. The support may allow the arms of the UAVs or drones to alter their orientation in scenarios like initiation of an integration process to fit in other control units or for balancing the thrust of a UAV or drone during flight. The modular UAVs or drones may include a railing mechanism to hold a payload during flight and an inversion mechanism to allow carrying of the payload on top of the drone to counteract the effects of unwanted friction forces acting on the payload. The modular UAVs or drones may be integrated via control-unit-to-control-unit or brick-to-brick configuration and propeller-to-propeller integration which may be achieved through centralized or de-centralized communication respectively. For propeller-to-propeller integration, the propeller guard of the propeller unit may include locking points to lock the propeller unit of a UAV or drone with the propeller unit of one or more other modular UAVs or drones. The propeller-to-propeller integration may happen between solo UAV units, or central unit-to-central-unit integrated UAVs based on the configuration and integration requirements. The UAV may undergo inversion to lift the payload on top of the drone. The UAV may include a gravity shifting mechanism. The gravity shifting mechanism may be tilting of the UAV or changing the orientation of the arms of the UAV. In accordance with a further aspect of the present disclosure there is provided an integration process for integrating modular UAVs or drones, the process comprising: communication between the control unit of the drone to be integrated and the base station; acquiring the data from the base station regarding the available options for integration; decision-making as to an integration configuration to be followed; and locking of the UAV units in an integrated configuration. The integrated configuration may be via a control-unit-to-control-unit configuration or brick-to-brick configuration and / or a propeller-to-propeller integration. The locking may be achieved either through master-slave configuration for the control-unit-to-control-unit or wireless communication for the propeller-to-propeller configuration. The masterslave configuration setting may be accomplished by setting one control unit as master and a consecutive unit as a slave and exchanging addresses between both control units. The masterslave configuration may comprise the first slave becoming the master of the second slave and so on. The integration process may include running of checks on each control unit for failure assessment where an error exists during communication for data acquisition. The running of checks may include taking of necessary steps to overcome a fault. Taking the necessary steps to overcome the fault may include a response to a fault. A response to each fault may include communication with the base station, changing the Revolutions Per Minute (RPM) of the motor actuating the propeller to balance thrust, or shifting the master-slave controls. The response to a fault may include landing the UAV to integrate at a later stage or integration. Embodiments of the technology will now be described, by way of example only, with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS In the drawings: Figure 1 is a three-dimensional view of an example embodiment of a modular UAV; Figure 2 is a three-dimensional view of an example embodiment of the control unit housing; Figure 3 is a cross-sectional view of the example embodiment of the control unit housing; Figure 4 is a three-dimensional bottom view of the example embodiment of the control unit housing; Figure 5 is an exploded assembly view of an example embodiment of a propeller unit and control unit housing; Figure 6 is a three-dimensional view of a second example embodiment of a UAV; Figure 7 is an exploded assembly view of an example embodiment of two modular UAVs interfacing with each other for integration; Figure 8 is a three-dimensional view of a third example embodiment of three modular UAVs in a brick-to-brick integration; Figure 9 is a three-dimensional view of the example embodiment of Figure 8 carrying a payload; Figure 10 is a top view of an example embodiment of a propeller unit including five distinct attachable points; Figure 11 is a three-dimensional view of an example embodiment of modular UAVs in a propeller-to-propeller integrated assembly; Figure 12 is a diagrammatic representation of a payload inversion mechanism; Figure 13 is a diagrammatic representation of a gravity shifting mechanism; Figure 14 is a flow diagram illustrating an integration process of modular UAVs; Figure 15 is a flow diagram illustrating an example scenario of heavy payload; Figure 16 is a flow diagram illustrating an example scenario of rough environmental conditions; Figure 17 is a flow diagram illustrating an example scenario of internal failure; Figure 18 is a flow diagram illustrating an example scenario of an internal failure because of an error in sensors; Figure 19 is a flow diagram illustrating an example scenario of an internal failure because of issue in a propeller unit; Figure 20 is a flow diagram illustrating an example scenario of an internal failure because of battery loss; Figure 21 is a flow diagram illustrating an integration process based on UAVs in communication with a base station; Figure 22 is a flow diagram illustrating a further example of an integration process; Figure 23 is a flow diagram illustrating an example of a post-integration mechanism of labelling control units according to a master-slave configuration; Figure 24 is a conceptual diagram showing another example of an Unmanned Aerial Vehicle (UAV) carrying a payload in accordance with aspects of the present disclosure; Figure 25 is an exemplary simplified representation illustrating potential pendulum motion of an exemplary payload attached to a UAV; Figure 26 is an exemplary conceptual diagram depicting a mechanism for stabilizing a payload attached to a UAV; Figure 27 is a diagram showing a central housing body of an exemplary UAVs payload stabilization system with perpendicular sliding paths; Figure 28 is an illustration of another exemplary version of the central housing body incorporating springs into sliding paths; Figure 29 is an illustration of another example of a central housing body with integrated capacitors in sliding paths; Figure 30 is an exemplary flow diagram illustrating a process of a payload stabilization mechanism according to aspects of the present disclosure; Figure 31 is an illustration of yet another example of a central housing body incorporating piezoelectric sensors; Figure 32 is an exemplary flow diagram illustrating a payload stabilization mechanism using piezoelectric sensors according to aspects of the present disclosure; Figure 33 is an exemplary illustration of a dynamic stabilization mechanism focusing on adaptive positioning of an attachment point and rotor to achieve load equilibrium; Figure 34 is an exemplary diagram showing a configuration of a dynamic stabilization mechanism demonstrating multi-directional stabilization capabilities; Figure 35 is an illustration of an exemplary passive stabilization mechanism utilizing a V-shaped guide structure; Figure 36 is an exemplary diagram showing a modification to an upper assembly of a payload stabilization system, introducing a stepped V-structure design; and Figure 37 is a high-level flow diagram of a method in accordance with exemplary aspects of the present disclosure. DETAILED DESCRIPTION WITH REFERENCE TO THE DRAWINGS The present disclosure relates to the field of unmanned aerial vehicles (UAVs) or drones. More particularly, systems and methods are disclosed for stabilizing payloads carried by UAVs or drones. The present disclosure extends to exemplary dynamic and passive mechanisms for mitigating unwanted oscillations and maintaining payload equilibrium during UAV flight operations across various operational scenarios. Methods for stabilizing payloads on Unmanned Aerial Vehicles (UAVs) are disclosed. These methods may include the use of a dynamic stabilization mechanism to mitigate unwanted oscillations and to maintain payload stability during flight operations of UAVs. The method may involve implementing a sophisticated system within a central body of a UAV. In exemplary aspects, a stabilization mechanism of a UAV may incorporate a central housing body featuring sliding paths or sliding guides. These paths can, e.g., accommodate the movement of a central attachment point in response to external forces acting on a payload of the UAV. It will be appreciated that two intersecting sliding paths may be used, however, embodiments may be possible that implement a single sliding path. A system of the present disclosure may be implemented using various sensing and damping technologies, including spring-based damping, capacitive sensing, or piezoelectric sensing. The direction and magnitude of payload displacement may be detected and processed by a Digital Signal Processing (DSP) block or control circuitry, which may generate appropriate control signals to adjust rotor speeds (e.g., rotor speeds of propeller(s) of the UAV), thereby achieving dynamic stabilization. Exemplary methods may also involve adaptive positioning of the attachment point and rotor adjustments to achieve load equilibrium. This may be accomplished by allowing the attachment point to move from its initial position to a stabilized position while simultaneously adjusting rotor positions to induce compensatory forces. The system may respond to multi-directional disturbances by dynamically adjusting the attachment point and modulating the thrust of multiple rotors, e.g., so as to provide comprehensive stabilization capabilities. Further exemplary embodiments of the present disclosure may include a passive stabilization system utilizing a V-shaped guide structure that may achieve automatic load centering through geometric properties and gravitational forces, without requiring active rotor adjustments. Further exemplary features may include introducing a stepped V-structure design in the assembly, providing discrete increments for an attachment point movement and allowing more precise control over the stabilization process. Exemplary methods may be implemented to effectively stabilize payloads on UAVs during complex maneuvers or in turbulent conditions, enhancing the vehicle's operational capabilities and expanding its potential applications in fields such as package delivery (e.g., with a package held at the attachment point). A control system in an integrated system of drones, or swarm of drones, may be utilized for coordinated and synchronized movements as it may enable the drones to function as a unified entity, capable of completing complex tasks collectively. Centralized and decentralized control systems are widely used in communication between the integrated or swarm drones. In a centralized control system, a central control unit communicates with and sends instructions to all the drones or drone units, whereas in a decentralized control system there is reliance on local communication and decision-making among the drone units themselves. The disclosure provides a control system for an integrated assembly of unmanned aerial vehicles (UAVs) that may include a control unit housing capable of initiating integration of the UAVs using a control-unit-to-control-unit configuration, brick-to-brick configuration, or a propeller-to-propeller unit configuration. The control unit housing may house modules such as a battery, power distribution board, sensing unit, GPS unit, Digital Signal Processing (DSP) module or control circuitry, and a radio control receiver. The control unit housing allows for various configurations of a UAV. Each configuration may include either a centralized, or decentralized communication system respectively. Centralized communication may be through a master-slave algorithm using a physical connection of control units, whereas decentralized communication may be wireless communication. The integrated system may enable a drone to not only overcome problems faced during flight on its own but also through the integrated control systems complete an intended task without sabotaging flight time to achieve completion of said task. An integrated assembly may also be referred to as a swarm assembly, swarm, integrated unit, modular drone swarm, and the like, throughout the present disclosure. The terms “problems”, “errors”, “issues” and “failures” may be used interchangeably. Throughout this disclosure, the terms “unmanned aerial vehicle”, “UAV”, “drone”, “modular drone” and “modular UAV” are used interchangeably and should be broadly construed to include any aircraft without any human pilot, crew, or passengers on board and may include any remote-controlled pilotless aircraft or small flying device. Reference to a UAV or drone includes but is not limited to reference to a modular UAV or modular drone. Examples of UAVs include a bicopter UAV, tricopter UAV, a quadcopter UAV, a hextacopter UAV, an octocopter UAV, or any other combination of modular UAVs. The control unit housing may be similar to the central control unit and control unit. In exemplary embodiments, each side of the control unit housing includes a locking mechanism and / or a connecting mechanism. The connecting mechanism may be configured to attach to a control unit housing of another UAV or a propeller unit. Either of the connecting mechanism or the locking mechanism of the individual modular UAV unit may allow an angle of the propeller unit to change its orientation if a balancing issue arises or initiate an integration process to resolve an error. The connecting mechanism may include a projected structure and its complementary aperture on the central control unit and the fixed support or vice versa. The locking mechanism may include circular fittings or nodes projecting from the projected structure into complementary receiving formations in the complementary aperture. Alternatively, the nodes may be in the complementary aperture and the complementary receiving formations on the projected structure. The control unit housing may include a holding mechanism, which may be a railing system or track to facilitate securing or carrying of a payload. The holding mechanism may include a further securing device such as a magnet to allow greater security when transporting a payload. The magnet may be an electron magnet, or any other suitable magnet. The holding mechanism may also include a stopper to restrain or retain the securing device from exiting the holding mechanism of a UAV control unit or entering the holding mechanism of another UAV control unit. The propeller unit may include connection points for connection of a propeller unit of a UAV to another propeller unit of an adjacent UAV. The connection points are similar to locking points situated on the propeller guard of a propeller unit. The control system may include an alignment mechanism, a failure assessment mechanism, or a mechanism for overcoming the issues or errors of a UAV through integration and detailed decision-making. The integration and detailed decision making may be associated with or based on Al algorithms and a trained control system. In some embodiments, the control system may include a payload inversion mechanism configured to overcome a balancing issue, a gravity shifting mechanism configured to overcome a problem relating to propeller failure, and a detailed decision-making mechanism configured to overcome battery-related or miscellaneous issues. The payload inversion mechanism may be similar to inverted payload lift and gravity shifting. The disclosed systems, methods, mechanisms and control systems may be arranged to stabilize a load of a UAV or drone during flight, even if the drone or UAV encounters disturbances (e.g., due to turbulence, weather conditions, wind, etc). This may include active control of one or more propulsion systems of the drone based on data sensed by one or more sensors, due to the pitch, roll, or yaw of the drone, as the case may be, as well as momentum or other force(s) of the load / payload which may be carried by the drone or UAV. The present disclosure extends to a payload stabilization system for Unmanned Aerial Vehicles (UAVs). The system(s) may be designed to mitigate unwanted oscillations and maintain payload stability during flight operations. The system(s) may include a central housing body with sliding path(s), accommodating a movable attachment point for payload connection. Multiple embodiments are presented, including spring-based damping, capacitive sensing, and piezoelectric sensing mechanisms, each capable of detecting and responding to payload displacements. A Digital Signal Processing (DSP) block or control circuitry may analyse sensor data and it may generate control signals to adjust rotor speeds, thereby achieving dynamic stabilization. The system(s) disclosed may feature adaptive positioning of the attachment point and rotor adjustments to maintain load equilibrium, capable of responding to multi-directional disturbances. Alternative embodiments include a passive V-shaped guide structure for automatic load centering and a stepped V-structure design for precise movement control. This may significantly enhance UAV payload stability across various operational conditions, expanding potential applications in package delivery. The system's adaptability to different payload weights and sizes, coupled with its lightweight and compact design, may make it suitable for integration into diverse UAV platforms without compromising aerodynamics or performance of the UAV or drone(s). The present disclosure addresses the challenges mentioned in the background, introducing UAV payload stabilization. By combining mechanical design with advanced sensing and control technologies, the present systems and methods may usher in a new era of stable, precise, and versatile UAV operations. In the accompanying drawings, exemplary embodiments of the technology are shown. However, it will be appreciated that the present disclosure may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided by way of example only, so as to facilitate an understanding of the present disclosure to those skilled in the art. In the drawings, like numbers may refer to like features or elements throughout. Figure 1 is three-dimensional view of an example embodiment of a modular drone (100) having an assembly of a tricopter type UAV drone. The tricopter UAV may include a central control unit (102), three propeller units (104) with propellers (106), and motors, preferably brushless DC motors (108), to actuate the propellers. Each propeller unit (104) of the UAV may be connected with the central control unit (102) via a support (110) and a moveable lock (112) that helps the propeller unit (104) to adjust its angle based on configuration and integration requirements. Figure 2 is a three-dimensional view of an example embodiment (200) of a central control unit (102) including a locking mechanism for each arm or propeller unit. The example embodiment (200) includes the connecting mechanism between the control unit (102) and the fixed support (110) joining the propeller unit (104) with the central control unit (102). The locking mechanism may include a projected structure (202) and a complementary aperture (204) on both the central control unit (102) and the fixed support (110) respectively, the projected structure (202) of either the locking mechanism of the central control unit or the fixed support of the propeller unit and the complementary aperture (204) of either the central control system or fixed support of the propeller unit are configured to complementarily fit into each other. The locking mechanism may include an assembly of circular fittings on both the projected structure (202) and opposite or complementary locking structure (204). The circular fittings are located on the boundaries or surfaces of the locking mechanism of the central control unit (102) and fixed support (110). Figure 3 is a cross-sectional view of the example embodiment (200) of the central control unit (102) or a housing or enclosure thereof. The control unit (102) may include one or more modules based on the application or function of the of UAV. The control unit (102) may include a locking mechanism (202) on each side of the control unit’s housing, which may, e.g., be one number greater than the number of arms, whereas in the case of a tricopter UAV the number of locks on the sides of the control unit (102) may be four. The presence of an extra lock may be necessary for central-unit-to-central-unit integration of the drone. Apart from the locking mechanism (202), the control unit may further include modules such as a battery, power distribution board, sensing unit, GPS unit, DSP module or control circuitry (205), and a radio control receiver. Further modules may be provided depending on the application or function of the UAV. These modules are represented by the boxes indicated in Figure 3 on the control unit (102) of the exemplary embodiment (200). Various components may be provided for implementing the methods and systems described in the present disclosure. The control circuitry (205) may include various components for carrying out the methods disclosed, and its components may form part of the system of the present disclosure. As described above, the exemplary block diagram of Figure 3 illustrates exemplary components which may be provided by a stabilization system for an unmanned aerial vehicle (UAV). The control circuitry (205) may e.g., be provided onboard the UAV or drone. The control circuitry (205) may include a processor for executing the functions of components / systems / methods described herein, which may be provided by hardware or by software units executing on / by the control circuitry. The software units may be stored in a memory component and instructions may be provided to the processor to carry out the functionality of the described components of the present disclosure. In some cases, for example in a cloud computing implementation, software units arranged to manage and / or process data on behalf of the control circuitry (205) may be provided remotely. Some or all of the components may be provided by a software application downloadable onto and executable on the control circuitry (205). It will be appreciated that one or more of the components of the control circuitry (205) of Figure 3 may be used in conjunction with any one or more of the other embodiments of the present disclosure, and vice versa. Figure 4 is a bottom view of an example embodiment (300) of a central control unit (302) including a railing system (308) to carry a payload, the railing system may be a track. The railing system (308) may for example include a magnet (305) to attract or magnetically hold a payload. The magnet may be an electromagnet. The end of the railing system on the control unit (302) is depicted at (304) to include a stopper (306) which may be arranged to restrain the magnet (305) from either moving out of the track (308) or entering the railing system (308) of another control unit of an integrated drone. The stopper (306) may create a junction between the two or more integrated control units thereby restraining the movement of the magnet in each control unit. In a scenario of heavy payload lifting, the drone carrying the payload may be arranged to invert itself and the payload or load may be shifted to an operatively top side of the control unit of the drone as depicted in the embodiment (300). It will be appreciated that the magnet may be replaced by another fastener, a quick release mechanism, one or more solenoid actuated fasteners or a clip or any other fastener that can releasably attach the payload to the drone / UAV. e.g., under control of its control system. Figure 5 is an exploded view of an example embodiment (400) of one arm between a central control unit (102) and propeller unit (104) of a tricopter UAV. Figure 5 illustrates the components and locking mechanism between independent parts. The central control unit (102) is connected to the support (110) via a locking mechanism (202) on each part (i.e., cooperating locking devices may be provided on the control unit (102) as well as on the support (110)). The support (110) and moveable lock (112) are joined via the fixtures (402, 404) that may be configured to allow the moveable lock (112) to move / pivot about when a change in angle of one of the propeller units (104) is required in a scenario of component failure or integration of different units. Figure 6 is an example embodiment (500) illustrating an assembly of a quadcopter UAV drone. The quadcopter UAV may include a central control unit (102) and four propeller units (104). Each propeller unit (104) of the UAV is connected with the central control unit (102) via a fixed support (110) and moveable lock (112) that helps the propeller unit (104) to adjust its angle based on the configuration and integration requirements. Figure 7 is an example embodiment (600) of an interface of two tricopter UAVs integrated with each other via control-unit-to-control-unit integration to form a hexcopter drone. Control-unit-to- control-unit integration may include a control unit of a UAV connecting to a control unit of another UAV via a locking mechanism. Each control unit of a UAV may include a spare / extra lock (202) for integration with another control unit in a control-unit-to-control-unit integration. Both units of the tricopter UAV may be arranged to change angles of arms carrying their propeller units other than a standard orientation, so as to be capable of integration with other units. In other words, the propeller carrying arms may be arranged to swivel or pivot, so as to accommodate multiple drones or UAVs to be connected or integrated into a UAV assembly or larger drone. Figure 8 is an example embodiment (700) of a brick-to-brick integration of three control units to form an octocopter UAV. The integrated octocopter of the example embodiment (700) may be formed from the integration of two tricopter and one bicopter drone units respectively. Brick-to-brick integration may include having a control unit of a first UAV connected to one or more other control unit(s) of related UAVs. In other words, a plurality of UAV control units may be assembled to one another, e.g., in series, so as to form a larger UAV. Figure 9 illustrates the example embodiment (800) of the integrated octocopter of Figure 8 carrying a shared payload (701) according to exemplary aspects of the present disclosure. Figure 10 is a top view of an example embodiment (900) of a propeller unit including five possible locking points (902) on a propeller guard (903) of the propeller unit for propeller-to-propeller integration of drones. Presently, five locking points (902) are provided, but any number of locking points may be implemented. It will be understood that the locking points may be connecting points, linking points, propeller locking mechanisms, propeller-to-propeller connecting points, and the like. The locking points allow connection between a propeller guard of a first propeller unit and a propeller guard of a second propeller unit. Figure 11 illustrates an example embodiment (1000) of propeller-to-propeller integration of four brick-to-brick integrated octocopter drones. The propeller-to-propeller integration may include a propeller unit of a UAV connecting to a propeller unit of another UAV via locking points on the propeller guard of the propeller units. Referring to Figure 12, an example embodiment (1100) of payload inversion is illustrated. In an example scenario of heavy payload lifting, a tricopter UAV (1102) carrying the payload inverts itself (1104) to shift the payload lift to a top side (1106). In other words, an underside of the UAV may be flipped to be a top side thereof, with the payload on the top side of the UAV. Inverting the payload may be advantageous in certain scenarios, and it may e.g., help overcome the effect of additional frictional forces acting on the heavy payload that may make the flight of the drone problematic. Figure 13 is an example embodiment (1200) of gravity shifting according to exemplary aspects of the present disclosure. Under a scenario of component failure in the propeller unit or arm of the drone, the quadcopter UAV carrying a payload may tilt itself (1204) from an original orientation (1202) so as to balance the thrust of the drone. The tilt of the UAV to facilitate gravity shifting may also be understood as the UAV changing orientation, banking, adjusting the drone angle, and the like. Figure 14 is an example embodiment (1300) showing a high-level flow diagram of integration between multiple units of UAVs. The process of integration between UAVs may be initiated by the selection of master-slave configuration (1302) between the control units. Out of all the integrated control units, one of the control units may be configured as the master control unit, and one or more of the rest of the control units, may be configured as slave control units. Each slave control unit may become the master control unit for the next slave control unit and so on. A key factor for the unified working of the integrated system may be the communication (1304) between the drones. Communication between the drones may be wireless communication or physical communication. The drones integrated via control-unit-to-control-unit may communicate through centralized communication and the integrated system formed through propeller-to-propeller integration may communicate via decentralized communication. The data for the integrated system may be acquired from both types of communication (1306). The acquired data may then be processed through Al algorithms (1308) for effective decision-making. In case of an error in the integrated system during the process of communication, it may indicate an error (1310) in one or more of the individual integrated units of the system. The error in the integrated system may be solved by individual checks placed on each integrated unit of the system, which may be distributed into multiple types. If the system faces balancing issues (1312) it may be the result of various issues such as, for example, one of the units may have the problem of either heavy payload lifting (1314), the system is facing rough environmental conditions (1316), or any unit may have faced internal failure (1318). These issues may result in problems pertaining to the overall balancing of the system which may be resolved either by tweaking or adjusting the thrust of the propeller (1320) or resolving the individual problems (1314, 1316, 1318), that is, resolving the heavy payload issue, environmental issue and / or the issue of internal failure. Figure 15 is an example flow diagram depicting a scenario (1400) of resolving an issue of heavy payload (1314) faced by an integrated system or individual drones which may hamper task fulfillment. Heavy payload may be similar to heavy payload lifting. If the integrated system or the individual unit is unable to carry the payload, it may result in balancing issue(s). To resolve the balancing issue(s), the control system may cause inversion of the drone (1402) carrying the payload to adjust its thrust. The inversion of the drone may result in the mitigation of the effect of additional frictional forces (or aerodynamic forces) acting on the payload when carried in a hanging position. The additional frictional forces (or aerodynamic forces) may affect the flight and balancing of the UAV or integrated system. After inversion of the drone carrying the payload, the payload may be carried on top of the UAV. If an individual UAV is able to continue flight in the inverted condition (1404), it may complete the task individually. Alternatively, the heavy payload issue may be resolved by undergoing the integration process (1406), that is, integrating the drones via control-unit-to-control-unit integration or propeller-to-propeller integration according to aspects of the present disclosure. Figure 16 is an example flow diagram depicting a scenario (1500) of resolving an issue of rough environmental conditions (1316) faced by an integrated system or individual drones that may prevent task fulfillment by the system. In such an example scenario, the control system may check whether a payload is connected with the UAV or not (1502). If no payload is attached, then the possibility of thrust and balancing issues related to the payload lift may be ruled out and the drone may communicate with a base station to change the master-slave configuration of the integrated system according to the conditions (1506). If the payload is attached, inverting the drone (1504), e.g., by the system implementing / actuating the necessary thrust adjustments, may resolve the issue. If neither solution will sufficiently resolve the issue, the drone may go into the integration process (1406) to complete the intended task, that is, integrating the drones via control-unit-to-control-unit integration or propeller-to-propeller integration. Figure 17 is an example flow diagram depicting a scenario (1600) of resolving an issue of internal failure (1318) in an exemplary system. Internal failure, prior to the integration process, may be the result of various types of errors faced by the system such as, for example, an error in sensors (1602), propeller issue(s) (1604), or battery lossZissue(s) (1606) of a drone. These errors resulting in internal failure may be resolved separately. If the system faces another issue or error, apart from an issue with the sensor, propeller, or battery then the system may be directed to undergo the integration process (1406) to complete the intended task. Figures 18 to 20 are further flow diagrams illustrating example scenarios for resolving internal failures or errors faced by the control system such as, for example, an error in sensors (1602), propeller issue(s) (1604), or battery lossZissue(s) (1606) of a drone. Figure 18 is an example flow diagram depicting a scenario for resolving an error with sensors (1602) of the control unit in an individual UAV or in an integrated system. To overcome an error with the sensors problem (1602), the system may check whether there is only one control unit or more than one control unit (1702). If there is only one control unit then the system may undergo the integration process (1406). If there is more than one control unit, then the control unit exhibiting the fault, for example the control unit having an error with the sensor, may transmit a signal to its immediate slave (1704) and if the slave sensors are functioning properly (1706), the faulty control unit may shift its control (1708) to the immediate slave. If the slave sensors are not functioning properly, then the drone or integrated UAV system may undergo the integration process (1406) to complete the intended task. Figure 19 is an example flow diagram depicting a scenario (1800) of an error with a propeller unit or propellers (1604) of an UAV unit or integrated system. To overcome this issue (1604), Al data received by the control system or base station may be processed to find a new center of gravity (1802) either by tilting the drone or changing the angle of the propeller arms, that is, e.g., employing gravity shifting. Propeller arms may be similar to propeller units. The process of gravity shifting may also be acquired by adjusting the thrust (1804) of the propeller which may be effected / implemented, e.g., by changing the RPM of the motor actuating the propellers. The continuous monitoring of the drone flight after gravity shifting may be done by evaluating the feedback values provided to a microcontroller (1806). If the problem (1604), that is, the error in a propeller unit, is not solved by gravity shifting, the drone may use a computer vision algorithm for a safe landing (1808) to enable the drone to initiate the integration process (1406) to complete the intended task. Otherwise, the drone or UAV may continue the flight and complete the intended task on its own without integration with other units. Figure 20 is a flow diagram illustrating an example scenario (1900) for resolving a battery issue (1606). To overcome the issue of battery health, the control system or base station may continuously monitor data from a battery monitoring system (1902), thereafter the data may be processed (1904) to allow for decision-making. If the drone is too far from the base station (1906), the control system may initiate the integration process (1406). Otherwise, the control system may utilize a computer vision algorithm to cause safe landing (1908) and at a later stage initiate the integration process (1406) to complete the intended task. Figure 21 is a flow diagram illustrating an example embodiment (2000) of the integration process (1406). To initiate the integration process (1406), a drone may notify and request a base station (2002) for instruction to configure drone integration. Once the request for integration is received at the base station (2004), the UAV may send configuration data to the base station (2006) to consider possible integration options in the surrounding airspace, that is, scan for units or UAVs to be integrated in the surrounding airspace. The data acquired at the base station may be processed using machine learning algorithm(s) (2008) from a trained dataset of drone configuration and orientations (2010) relevant to integration. Once the data is processed at the base station, it may be transmitted back to the drone or master drone of the integrated system that requested (2012) initiation of the integration process. The data when received by the drone (2014) is then analyzed to initiate the integration process (2016). Figure 22 is a flow diagram illustrating an example scenario (2100) of an initializing action (2016) of the integration process. The process may start with waiting for a drone to reach an integration site (2102). Once the drone reaches the integration site (2102), data may be processed (2104) to evaluate the existing options, including whether control-unit-to-control unit (2106) or propeller-to-propeller (2108) configuration-based integration will be best suited. A decision may be made as to the appropriate option for integration configuration. After decision-making, locking may be initiated (2110) and communication may be effected / implemented. The communication may be centralized (2112) for a brick-to-brick (2106) configuration and decentralized (2114) for a propeller-to-propeller configuration (2108). The mode of communication for centralized communication may be through a master-slave algorithm (1302) using a physical connection of control units, whereas for decentralized communication, the mode of communication may be wireless communication (2116). Figure 23 is a flow diagram illustrating an example embodiment (2200) of a process of masterslave configuration (1302). The process may be initiated by inspection of the number of control units integrated (2202). Among the control units, one unit may be declared a master unit (2204) which may be permanently set as such for integration later on. After one of the units is declared a master, it may then scan other control units integrated with it (2206). If there are control units (2208) integrated with the master unit, then the address of the master unit may be transmitted to the consecutive control units which may then be declared as slave units and labeled as (i = 1) (2210), where i is the order of the slave unit present next to a master unit. Once the master address is transmitted and the first slave is declared, the slave address may also be read by the master unit (2212). The slave may then scan for any other control units connected to it except for the master unit (2214). If there are other control units (2216) apart from the master unit, the slave unit may become a master unit for a next slave, and its data may be transmitted to the next slave unit which may be declared a slave unit and labeled (i + 1) (2218). The slave (i + 1) then repeats the same cycle to declare the next slave (2220) and so on. If there are not any control units present (2216) next to the first slave unit, then the first slave unit information is transmitted to the first master unit (2222) and the intended task of the integrated system may be continued or completed. Embodiments of a control system for an integrated assembly of UAVs are disclosed. The control system may include a control unit housing. Each side of the control unit housing may have a locking mechanism. The control unit housing may house modules such as a battery, power distribution board, sensing unit, GPS unit, DSP module or control circuitry, and a radio control receiver. The control unit housing may allow for various configurations of a UAV. For example, a connecting mechanism can be connected between the control unit housing and a propeller unit. For example, one control unit can be connected to another control unit. Figure 24 is an exemplary illustration of an Unmanned Aerial Vehicle (UAV) (2416) carrying a payload (2414). In the exemplary embodiment, the UAV (2416) is depicted as a quadcopter configuration, featuring four rotors or propeller units (2402, 2404, 2406, 2408). In the present embodiment, the rotors or propeller units (2402, 2404, 2406, 2408) may be symmetrically arranged around a central body (2410) which may, e.g., have a central control unit thereat according to aspects of the present disclosure (e.g., as described with reference to Figures 1-23 above). The central body (2410) may serve as a primary structural component, housing the UAV's payload stabilization mechanism(s) or system components. Beneath the central body, a vertical shaft (2412) may connect to the payload (2414). The payload (2414) may include various types of cargo, sensing equipment, or specialized tools, depending on the UAV's mission profile. Figure 25 is an exemplary illustration of a simplified representation (2500) of the potential pendulum motion that a payload attached to a UAV might experience. The diagram depicts a planar model of a pendulum system, with a pivot point (2502) representing an attachment point (of the payload) on the UAV. The pendulum arm is represented by a straight line of length L (2504), which may correspond to a distance between the UAV’s attachment point (2502) and a center of mass of the payload (2414, see e.g., Fig. 24). Angular displacement of the pendulum from its equilibrium position is denoted by the reference sign 0 (2506). This angle is, e.g., formed between a vertical axis (2508), which may represent the gravitational direction, and the pendulum arm (2504). A horizontal distance between the equilibrium position and the displaced position of the payload is depicted by reference sign (2510). The exemplary model (2500) of Figure 25 may provide a basis for understanding oscillatory behavior of the payload (e.g., 2414) under the influence of gravity and inertial forces during UAV maneuvers. The pendulum motion illustrated here forms the foundation for more complex stabilization mechanisms that may be employed in the UAV's payload management system to counteract unwanted movements and maintain payload stability. The model (2500) may be utilized by one or more control systems to control flight parameters (propeller(s) speed / power, flight control systems etc.) according to exemplary aspects of the present disclosure. For example, one or more sensor(s) may be arranged to detect the angle 0 (2506) between shaft (2412) and the drone body (2410), and the system may output corrective data to stabilize the drone and its payload. This control may be implemented in near real-time. Figure 26 depicts a conceptual diagram of mechanism / system for stabilizing a payload attached to an Unmanned Aerial Vehicle (UAV). The mechanism may be relatively sophisticated. A dynamic stabilization mechanism / system (2600) may be designed to mitigate pendulum-like oscillations that can occur when a UAV carries a heavy payload (e.g., 2414). The stabilization mechanism may include a horizontal support structure (2601), serving as a reference frame for a payload suspension system. The horizontal support structure (2601) may, e.g., be attached to the drone and / or to the housing or control unit (e.g., to 2410 in Figure 24). Three exemplary distinct attachment points (2604, 2606, 2608) are shown on the support structure (2601), each corresponding to a different stage of a stabilization process. A payload (2414) may be connected to the support structure via a flexible tether or cable (2610), the configuration of which changes in response to external forces acting on the system. The tether or cable (2610) may, e.g., be provided as an alternative to the shaft (2412), but it is envisaged that a shaft (e.g., a relatively rigid shaft, or a flexible shaft) can also be used in some applications. Figure 26 demonstrates three exemplary sequential states of the system, each characterized by a unique angle 0 (theta) formed between an imaginary vertical axis and the tether: an initial state (0i) where the payload is suspended from attachment point (2602) at a first location (2604), forming first angle 0i with the vertical axis; an intermediate state (02) where the suspension point (2602) shifts to a second, transverse, location (2606), resulting in second angle 02 with vertical; and a third state (03) where the suspension point (2602) moves further to a third, transverse position (2608), creating a third angle 03 with the vertical axis. The relationship between these angles is 0i >02 >03, indicating a progressive reduction in the deflection angle as the attachment point (2602) moves in concert with the payload's (2414) motion. This progressive reduction in angle corresponds to a damping of the pendulum-like motion of the payload. Figure 27 shows another example embodiment of a central control unit (2700) having a housing body (2702) for the UAV's payload stabilization system (similar to that of Figure 4). The housing body (2702) has two preferably perpendicular sliding paths (2704, 2706) intersecting at its centre. These sliding paths (2704, 2706) may be arranged to accommodate movement of an attachment point (2708). This attachment point (2708) may correspond to the attachment points (2602, 2502) of the payload stabilization mechanism / system diagrams depicted e.g., in Figures 25-26, and the control system may utilize data relating to these diagrams to generate control parameters for stabilization of the drone or UAV during flight. It will be appreciated that embodiments may be possible that implement a single sliding path (e.g., including the first sliding path 2704, but omitting the second sliding path 2706). The attachment point (2708) may be designed to slide or move within these sliding paths (2704, 2706) in response to external forces acting on the payload (2414). The attachment point may e.g., be a button or pin that is slidably held by sliding paths or sliding guides, and the payload may be attachable to the attachment point by an appropriate fastener. The sliding paths may also be termed slots or guide rails (e.g., forming part of a rail / railing system). When the UAV experiences sudden acceleration or deceleration, resulting in a jerk motion, the inertia of the payload (2414) causes it to move relative to the UAV's body. The sliding mechanism / system (2704, 2706, 2708) may include the attachment point (2708) moving along the paths (2704, 2706), and this may allow for relative motion (of the payload attached to the attachment point in relation to the body (2702)) while maintaining a controlled connection between the payload (2414) and the UAV. It will be appreciated that Figure 27 may depict an underside of the UAV’s control unit (2700), but it may also be an upper side of the UAV’s control unit, e.g., when the UAV or drone is inverted according to aspects of the present disclosure. This sliding mechanism / system (e.g., with the sliding tracks or paths (2704, 2706)) may provide a means to absorb and / or dampen sudden movements, e.g., of the load / payload and / or sudden movements of the drone or UAV. By enabling controlled motion of the attachment point (2708) in two preferably perpendicular directions, the system can compensate for complex, multidimensional forces acting on the payload (2414). Figure 28 illustrates another exemplary embodiment of a central control unit (2800) having a housing body (2802) for the UAV's payload stabilization system. In this embodiment, springs (2805) or biasing means / devices have been incorporated into the preferably perpendicular sliding paths (2804, 2806). These springs are positioned along the length of each sliding path (2804, 2806). The attachment point (2808) remains at the intersection of the two paths in a resting position, now supported by the spring mechanisms in both transverse directions. In other words, the biasing / springs may urge the attachment point (and the payload) to a resting position. The addition of springs (2805) introduces a damping and restoring force to the payload stabilization system, which may alleviate / dampen sudden movements of the payload, and of the attachment point. When the payload (2114) experiences sudden movements due to UAV maneuvers or external disturbances, the springs compress or extend, absorbing the kinetic energy of the motion and subsequently exerting a force to return the payload to its neutral / resting position. This springmass system may be arranged to create a dynamic equilibrium, allowing for controlled oscillations that significantly reduce the transmission of abrupt forces. It will be appreciated that in the various embodiments of the present disclosure, the sliding paths need not be perpendicular, and they may simply extend transversely, across one another at any appropriate angle. Figure 29 illustrates a further exemplary embodiment of the central control unit and its housing body (2902) which may enclose the UAV's payload stabilization system. In this iteration, capacitors have been integrated into the sliding paths (2909, 2911), replacing the springs from the embodiment of Figure 28. Each capacitor may have two plates: e.g., one fixed plate (2909) anchored at the terminus of each sliding path, and one movable plate (2911) that can traverse along the path on either side of the attachment point (2908). The attachment point (2908) may be urged to remain in a resting position at the intersection of the two paths during normal operation. In a similar way to the embodiment of Figure 28, with the embodiment of Figure 29, when the payload (2414) experiences a sudden jerk or displacement due to LIAV maneuvers or external disturbances, the attachment point (2908) may slide along the relevant path (2904, 2906). This may, in turn, push the movable capacitor plate (2911) towards its fixed counterpart / cooperating capacitor plate (2909). This movement may alter the distance between the capacitor plates, thereby changing the capacitance of the affected capacitor. The variation in capacitance may serve as a precise measure of the displacement magnitude and direction. This capacitance change can then be utilized by the UAV's DSP block or control circuitry to adjust rotor speeds or positions, accordingly, generating a counteracting force that guides the attachment point (2908) back to its neutral / resting / equilibrium position. This electromechanical feedback loop may enable rapid and accurate stabilization of the payload, significantly enhancing the UAV's ability to maintain payload equilibrium during complex flight maneuvers or in turbulent conditions. It will also be appreciated that the embodiments of Figures 28-29 may be used in conjunction with one another, e.g., using both capacitors and springs or biasing devices. It will also be appreciated that any one or more of the embodiments of the present disclosure may be used in conjunction with any one or more features of the other embodiments. Figure 30 is an exemplary operational flow diagram of a payload stabilization mechanism / system that may be implemented, e.g., utilizing features of the system shown in Figure 29. The process may begin with the "Displacement of hinge" (3002), which represents an initial movement of the attachment point (2908) along the sliding paths (2904, 2906) in response to external forces acting on the payload (2414). This displacement may directly lead to a "Change in capacitance △C" (3004), as the movable capacitor plate (2911) shifts relative to the fixed plate (2909), altering the capacitance of the system. Data relating to this capacitance change may be received and processed by a "DSP block" (3006) or control circuitry, i.e., a digital signal processing unit, or the like. The DSP block (3006) analyses the capacitance variations, interpreting them as indicators of the magnitude and direction of payload displacement. Based on this analysis, the DSP block may generate and output appropriate control signals for use by the system according to aspects of the present disclosure. These control signals may subsequently trigger or actuate a "Change of propeller rotor speed" (3008). The UAV's propulsion system may respond by adjusting the rotational velocities of its rotors / propellers (e.g., 2402, 2404, 2406, 2408, see Figure 24), creating compensatory forces to counteract the initial displacement of the payload in relation to the housing (e.g., 2410, 2902). The outcome of this process may be "Payload stability" (3010) and / or active payload stabilization. By rapidly detecting displacements, processing the information, and implementing corrective propulsion adjustments, the system may be arranged to achieve dynamic stabilization of the payload (2414). This mechanism / system may ensure continuous monitoring and correction, maintaining the payload in a stable position relative to the UAV body (e.g., 2410, 2902, 2802, 2702) despite external perturbations or flight maneuvers. Figure 31 is yet a further exemplary embodiment of a central control unit (3100) having a housing body (3102) for the UAV's payload stabilization system. In the present embodiment, one or more piezoelectric sensor(s) (3133) (presently four of them) have been integrated into the perpendicular sliding paths (3104, 3106), replacing the previously described capacitive system (or implemented in addition thereto). The sensor(s) (3133) may, e.g., be implemented at terminal ends of each of the paths (3104, 3106). The attachment point (3108), located at the intersection of the two paths (3104, 3106) (at equilibrium / resting position), may be arranged to interact directly with these piezoelectric sensor(s) (3133). When the payload (2414) experiences a sudden displacement due to UAV maneuvers or external forces, the attachment point (3108) may move along the relevant path (3104 or 3106, as the case may be), applying pressure to a layer (3135) of the piezoelectric sensor (3133) facing the direction of motion. This applied pressure may induce a deformation in the piezoelectric material, which, due to its unique properties, can generate an electrical signal. The magnitude characteristics of this electrical signal are directly proportional to the force and speed of the displacement, providing precise information about the payload's motion. Data relating to this electrical signal may be received / processed by a processing unit of the control system of the UAV, and this data may be used for flight control according to aspects of the present disclosure. Figure 32 is an exemplary operational flow diagram of a payload stabilization mechanism / system that may be implemented, e.g., utilizing features of the system shown in Figure 31 (or features from one or more of the other embodiments disclosed). The process may initiate with the "Displacement of hinge" (3202), representing the movement of the attachment point (e.g., 3108) along the sliding paths (3104, 3106) in response to external forces acting on the payload (2414). This displacement may directly lead to the "Compression of piezoelectric material" (3204), as the attachment point applies pressure to the piezoelectric sensor (3133) in the direction of motion. The compression of the piezoelectric material may result in the generation of an "Electrical signal" (3206). The electrical signal (3206) may then be received and processed by the "DSP block" (3208) or control circuitry. The DSP block (3208) or control circuitry may subsequently trigger / actuate a "Change of propeller rotor speed" (3210) or transmit a signal / instruction to this effect. The UAV's propulsion system may then respond by adjusting the rotational velocities of its rotors / propellers (e.g., 2402, 2404,2406, 2408), creating compensatory forces to counteract the initial displacement of the payload. The outcome of this process (3200) may be termed "Payload stability" (3212). In other words, payload stabilization may be implemented by aspects of the present disclosure. By rapidly detecting displacements, converting them to electrical signals, processing the information, and implementing corrective propulsion adjustments, the system may be arranged to achieve dynamic stabilization of the payload (2414). Figure 33 is an exemplary diagram illustrating a dynamic stabilization mechanism / system (3300) for a UAV payload system, focusing on the adaptive positioning of the attachment point (e.g., 2502, 2602, 2708, 2808, 2908, 3108) and rotor to achieve load equilibrium. In Figure 33, The initial attachment point position is denoted as P1 (3302), while Pn (3304) represents the stabilized position of the upper attachment point after load displacement. The distance between these points is marked as x (3306), quantifying the displacement of the attachment point (e.g., 2708, 2808, 2908, 3108). The weight force W = mg (3308) acts vertically downward on the payload, where m is the mass and g is the gravitational acceleration. The UAV rotor initial position R1 (3310) and its adjusted position R1' (3312) (and / or data relating to these, or sensed data relating to these positions) may be implemented as elements in the stabilization process. The mechanism / system may operate by allowing the upper attachment point (e.g., 2502, 2602, 2708, 2808, 2908, 3108) to move from P1 (3302) to Pn (3304), effectively reducing the angle between the tether or cable (e.g., 2610 in Fig. 26, or 2412 in Fig. 24) and the load attached (2414), damping the payload's motion. Subsequently, the rotor position shifts from R1 (3310) to R1' (3312), creating angle 6 (3314) and inducing a force that guides the payload (2414) back towards its original position P1 (3302). This dynamic adjustment of the attachment point (e.g., 2502, 2602, 2708, 2808, 2908, 3108) through rotor position may demonstrate a sophisticated approach to payload stabilization, utilizing principles of force balancing and geometric reconfiguration to minimize undesired oscillations. Figure 34 is an exemplary diagram illustrating an advanced configuration of the dynamic stabilization mechanism / system (3400) for UAV payload systems, expanding upon the concepts introduced in Figure 33 described above. Figure 34 depicts an exemplary arrangement of rotors and an attachment point (e.g., 2502, 2602, 2708, 2808, 2908, 3108), demonstrating the system's capability to respond to multi-directional disturbances. In this configuration, R1 (3410) and R2 (3412) represent the initial positions of two rotors. Point P1 (3402) denotes the initial upper attachment point (e.g., 2502, 2602, 2708, 2808, 2908, 3108) for the payload suspension system, situated between R1 (3410) and R2 (3412). As the system responds to external forces, the attachment point (e.g., 2502, 2602, 2708, 2808, 2908, 3108) may shift to either point Pn (3404) or Pn' (3405), depending on the direction of the disturbance (e.g. during flight). Distance x (3407) quantifies the displacement of the attachment point from its initial position P1 (3402). Angles 01 (3406) and 02 (3408) are formed between the horizontal axis and the lines connecting P1 (3402) to Pn (3404) and Pn' (3405) respectively. The system can dynamically adjust the attachment point to either Pn (3404) or Pn' (3405) by modulating the thrust vectors of rotors R1 (3410) and R2 (3412) to create a balanced force distribution that guides the payload back towards its equilibrium position at P1 (3402). Figure 35 is an exemplary diagram illustrating an advanced passive stabilization mechanism / system (3500) for a UAV payload system, utilizing a V-shaped guide structure to achieve automatic load centering without rotor position adjustment. The conceptual diagram of Figure 35 depicts a symmetrical V-shaped surface (3502) with angles 01 (3504) formed between each side of the V and the horizontal axis. The payload's initial / resting position is (3506) when connected to the vertex of the V shaped structure through a tether or cable (3510) representing the system's equilibrium state. When the payload experiences a sudden jerk or external force, the upper attachment point (e.g., 2502, 2602, 2708, 2808, 2908, 3108) may displace to position Pn (3519) on one side of the V-shaped structure (3502). The weight force, in conjunction with the inclined surface 3502 of the structure, may generate a component force parallel to the V-shaped guide, inducing a restoring motion. In other words, the guide structure or guide rails may be sloped along a V-shaped structure, so that the payload would tend to hang from a central region of the V-shaped structure of the guide rail(s) or guide paths, according to aspects of the present disclosure. The structure (3502) may be symmetrical, and the system's (3500) symmetry may be evidenced by a mirrored configuration on an opposite side of the V-shaped structure. Unlike the previous embodiment of Figure 34, the present embodiment’s (3500) geometry may eliminate the need for active rotor adjustment to achieve payload stabilization. Instead, the geometric properties of the V-shaped guide, coupled with gravitational forces, may be arranged to create a self-centering effect. As the attachment point (e.g.. 2502, 2602, 2708, 2808, 2908, 3108) slides along the inclined surface of the guide, potential energy is converted to kinetic energy, driving the system back towards an equilibrium position at P1 (3501). Figure 36 illustrates an exemplary modification to an upper assembly of a payload stabilization system according to aspects of the present disclosure. In the present embodiment, a stepped V-structure (3615) is implemented. The stepped V structure may be arranged to enhance control over the attachment point's lateral movement. Figure 36 depicts a conceptual diagram of the upper assembly, where the previously smooth V-shaped structure has been replaced with a series of discrete steps (3602). This stepped configuration may be symmetrically arranged on both sides of a central point, which represents an initial equilibrium position P1 (3604) for the payload attachment. The payload (2414) may be suspended from P1 (3604). The stepped design / system (3600) may serve a function in the stabilization mechanism by introducing controlled resistance to the movement of the attachment point (e.g., 2502,2602,2708, 2808, 2908, 3108). In the event of a sudden jerk or external force, the attachment point's movement is constrained to discrete increments corresponding to each step, rather than allowing continuous sliding along a smooth surface. This discretization of movement limits the maximum displacement of the attachment point (for a given angle of inclination of the drone / UAV) and it may allow for more precise control of the stabilization process. In other words, the guide or path or rail system may be arranged to follow a stepped profile as is diagrammatically depicted in Figure 36, to create stepped positions for the attachment point during various angles of pitch or roll of the drone / UAV. As external forces act on the system, the attachment point (e.g., 2502, 2602, 2708, 2808, 2908, 3108) may move through the discrete steps (3602), but the stepped design may prevent it from traveling too far from the center, thereby maintaining a closer approximation to the desired equilibrium state. As before it will be appreciated that any one or more features of any one or more of the embodiments may be implemented in conjunction with any one or more features of the other embodiments of the present disclosure. The technology of the present disclosure further extends to a stabilization system for an unmanned aerial vehicle (UAV) carrying a payload. The system may include a housing body that houses control circuitry of the UAV. One or more rotors may be arranged around the housing body, the rotors configured to power flight of the UAV. One or more sliding guides may be provided at the housing body. A movable attachment point may be provided, and it may be slidably connected to the sliding guide(s) of the housing body. The moveable attachment point may be arranged for attachment to a payload. One or more sensors may be provided and capable of sensing displacement of the movable attachment point and generating a signal relating to the displacement and to transmit it to the control circuitry. The control circuitry may be arranged, in response to receiving the signal relating to the displacement, to analyze the signal and to output a control signal for adjusting rotor speeds of one or more of the rotors so as to stabilize a payload carried by the UAV. The housing body may include two sliding guides crossing one another. The sliding guides may also be termed sliding paths. The sliding guides may intersect at a central region of the housing body. The sliding guides may be perpendicular to one another. The moveable attachment point may be located at a central region of the housing body in a resting position of the attachment point. One or more biasing device(s) may be provided in the one or more sliding guide(s). The biasing device(s) may be arranged to dampen lateral movement of the attachment point. The biasing device(s) may be one or more springs, or other biasing means or damping means or shock absorbing means (e.g. hydraulic shock absorbers or electromagnetic shock absorbers). The one or more sensors may include a fixed capacitor plate at a terminal end of one of the sliding guide(s). The one or more sensors may further include a movable capacitor plate traversable along the sliding guide(s). Generating a signal relating to the displacement may include sensing a change in capacitance of the fixed and moveable capacitor plates. The one or more sensors may include one or more piezoelectric sensors integrated into the sliding path(s). The piezoelectric sensor(s) may be arranged to generate the signal relating to the displacement of the movable attachment point. The system may include a vertical shaft extending from the housing body for connecting a payload thereto. The one or more sliding guide(s) may be in the form of a V-shaped guide structure with inclined surfaces. The movable attachment point may be capable of traversing the inclined surfaces. A tether may connect the attachment point to a payload. The V-shaped guide structure may include a series of discrete steps on the inclined surfaces. The system may include a control signal generator component (e.g., forming part of the control circuitry housed by the UAV’s housing body) for generating rotor speed adjustment signal(s) based on output from the control circuitry. The system may further include a rotor speed controller for implementing rotor speed adjustment based on the rotor speed adjustment signal(s). The system may include an adaptive positioning module for adjusting positions of UAV rotors in response to payload displacement. In accordance with another exemplary aspect of the present disclosure there is provided an unmanned aerial vehicle (UAV) comprising a stabilization system as defined herein, and a payload attached to the attachment point of the stabilization system. In accordance with another aspect of the present disclosure there is provided a method (3700) for stabilizing a payload carried by an unmanned aerial vehicle (UAV). An exemplary method (3700) is shown in the high-level block diagram of Figure 37. The method may include detecting (3702) displacement of a movable attachment point along one or more sliding guides at a housing body of the UAV. The method may include receiving and processing (3704) data relating to the displacement using control circuitry onboard the UAV, and in response thereto, generating one or more control signals. The method may further include adjusting (3706) speeds of one or more rotors of the UAV based on the generated control signal(s) so as to counteract the displacement of the moveable attachment point and thereby stabilizing the payload carried by the UAV. The step of detecting (3702) may include measuring changes in capacitance between fixed and movable capacitor plates provided along the sliding guides. The step of detecting (3702) may alternatively, or in addition, include measuring electrical signals generated by piezoelectric sensors in response to pressure from movement of the attachment point. The technology of the present disclosure further extends to a payload stabilization system for an unmanned aerial vehicle (UAV). The system may include any one or more of: a) a central housing body; b) a plurality of rotors arranged (e.g., symmetrically) around said central housing body; c) two perpendicular sliding paths intersecting at a center of said central housing body; d) a movable attachment point situated at the intersection of said sliding paths; e) a sensing mechanism for detecting displacement of said movable attachment point; f) a digital signal processing (DSP) block (or control circuitry) for analyzing data from said sensing mechanism; and g) a control system for adjusting rotor speeds based on signals from said DSP block or control circuitry. Said sensing mechanism may include springs incorporated into said sliding paths. Said sensing mechanism may include any one of: a) fixed capacitor plates anchored at termini of said sliding paths; and b) movable capacitor plates traversable along said sliding paths. Said sensing mechanism may include piezoelectric sensors integrated into said sliding paths. The system may further comprise a vertical shaft extending from said central housing body for connecting a payload. The present disclosure extends to a method for stabilizing a payload on an unmanned aerial vehicle (UAV). The method may include any one or more of: a) detecting displacement of a movable attachment point along sliding paths in a central housing body of said UAV; b) processing data related to said displacement using a digital signal processor (DSP) (or control circuitry); c) generating control signals based on said processed data; and d) adjusting speeds of rotors on said UAV based on said control signals to counteract said displacement. Said step a) of detecting in the method may include measuring changes in capacitance between fixed and movable capacitor plates along said sliding paths. Said detecting may alternatively, or in addition, include measuring electrical signals generated by piezoelectric sensors in response to pressure from movement of said attachment point. The present disclosure extends to a passive stabilization system for an unmanned aerial vehicle (UAV) payload. The system may include any one or more of: a) a V-shaped guide structure with (e.g., symmetrical) inclined surfaces; b) a movable attachment point capable of traversing said inclined surfaces; and c) a tether connecting said attachment point to a payload. Said V-shaped guide structure may include a series of discrete steps on said inclined surfaces. The present disclosure extends to a method for passively stabilizing a payload on an unmanned aerial vehicle (UAV). The method may include any one or more of: a) allowing a movable attachment point to traverse inclined surfaces of a V-shaped guide structure in response to external forces on said payload; and b) utilizing gravitational forces and geometry of said V-shaped guide structure to induce a restoring motion of said attachment point towards an equilibrium position. The method may further include constraining movement of said attachment point to discrete increments corresponding to steps on said inclined surfaces. The present disclosure further extends to an unmanned aerial vehicle (UAV) which includes one or more of: a) a central body; b) a plurality of rotors arranged around said central body; c) a payload stabilization system according to any of the aspects of the present disclosure; and d) a payload attached to said payload stabilization system. The present disclosure yet further extends to a control system for an unmanned aerial vehicle (UAV) with a payload stabilization system. The system may include any one or more of: a) a sensing mechanism or sensors for detecting displacement of a payload attachment point; b) a digital signal processing (DSP) block (or control circuitry) for analyzing data from said sensing mechanism; c) a control signal generator for producing rotor speed adjustment signals based on output from said DSP block or control circuitry; and d) a rotor speed controller for implementing said rotor speed adjustment signals. The control system may further include an adaptive positioning module for adjusting positions of UAV rotors in response to payload displacement. The foregoing description has been presented for the purpose of illustration; it is not intended to be exhaustive or to limit the technology to the precise forms disclosed. Persons skilled in the relevant art can appreciate that many modifications and variations are possible in light of the above disclosure. Any of the steps, operations, components or processes described herein may be performed or implemented with one or more hardware or software units, alone or in combination with other devices. Components or devices configured or arranged to perform described functions or operations may be so arranged or configured through computer-implemented instructions which implement or carry out the described functions, algorithms, or methods. The computer-implemented instructions may be provided by hardware or software units. In one embodiment, a software unit is implemented with a computer program product comprising a non-transient or non- transitory computer-readable medium containing computer program code, which can be executed by a processor for performing any or all of the steps, operations, or processes described. Software units or functions described in this application may be implemented as computer program code using any suitable computer language such as, for example, Java™, C++, or Perl™ using, for example, conventional or object-oriented techniques. The computer program code may be stored as a series of instructions, or commands on a non-transitory computer-readable medium, such as a random access memory (RAM), a read-only memory (ROM), a magnetic medium such as a hard-drive, or an optical medium such as a CD-ROM. Any such computer-readable medium may also reside on or within a single computational apparatus, and may be present on or within different computational apparatuses within a system or network. Flowchart illustrations and block diagrams of methods, systems, and computer program products according to embodiments are used herein. Each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, may provide functions which may be implemented by computer readable program instructions. In some alternative implementations, the functions identified by the blocks may take place in a different order to that shown in the flowchart illustrations. Some portions of this description describe the examples in terms of algorithms and symbolic representations of operations on information. These algorithmic descriptions and representations, such as accompanying flow diagrams, are commonly used by those skilled in the data processing arts to convey the substance of their work effectively to others skilled in the art. These operations, while described functionally, computationally, or logically, are understood to be implemented by computer programs or equivalent electrical circuits, microcode, or the like. The described operations may be embodied in software, firmware, hardware, or any combinations thereof. The language used in the specification has been principally selected for readability and instructional purposes, and it may not have been selected to delineate or circumscribe the inventive subject matter. It is therefore intended that the scope of the present disclosure be limited not by this detailed description, but rather by any claims that issue on an application based hereon. Accordingly, the present disclosure is intended to be illustrative, but not limiting, of the scope of any accompanying claims. Finally, throughout the specification and any accompanying claims, unless the context requires otherwise, the word ‘comprise’ or variations such as ‘comprises’ or ‘comprising’ will be understood to imply the inclusion of a stated integer or group of integers but not the exclusion of any other integer or group of integers.

Claims

1. A stabilization system for an unmanned aerial vehicle (UAV) carrying a payload, the system comprising:a housing body that houses control circuitry of the UAV;one or more rotors arranged around the housing body, the rotors configured to power flight of the UAV;one or more sliding guides provided at the housing body;a movable attachment point that is slidably connected to the sliding guide(s) of the housing body, the moveable attachment point being arranged for attachment to a payload; andone or more sensors that are capable of sensing displacement of the movable attachment point and generating a signal relating to the displacement and to transmit it to the control circuitry,wherein the control circuitry is arranged, in response to receiving the signal relating to the displacement, to analyze the signal and to output a control signal for adjusting rotor speeds of one or more of the rotors so as to stabilize a payload carried by the UAV.

2. The system as claimed in claim 1, wherein the housing body includes two sliding guides crossing one another and that intersect at a central region of the housing body.

3. The system as claimed in claim 2, wherein the sliding guides are perpendicular to one another.

4. The system as claimed in any one of the preceding claims, wherein the moveable attachment point is located at a central region of the housing body in a resting position of the attachment point.

5. The system as claimed in any one of the preceding claims, wherein one or more biasing device(s) are provided in the one or more sliding guide(s), the biasing device(s) arranged to dampen lateral movement of the attachment point.

6. The system as claimed in claim 1, wherein the one or more sensors include a fixed capacitor plate at a terminal end of one of the sliding guide(s), and a movable capacitor plate traversable along the sliding guide(s); and wherein generating a signal relating to the displacement includes sensing a change in capacitance of the fixed and moveable capacitor plates.

7. The system as claimed in claim 1, wherein the one or more sensors includes one or more piezoelectric sensors integrated into the sliding path(s), wherein the piezoelectric sensor(s) are arranged to generate the signal relating to the displacement of the movable attachment point.

8. The system as claimed in claim 1, wherein the system includes a vertical shaft extending from the housing body for connecting a payload thereto.

9. The system as claimed in claim 1, wherein the one or more sliding guide(s) is / are in the form of a V-shaped guide structure with inclined surfaces, wherein the movable attachment point is capable of traversing the inclined surfaces; and wherein a tether connects the attachment point to a payload.

10. The system as claimed in claim 9, wherein the V-shaped guide structure comprises a series of discrete steps on the inclined surfaces.

11. The system as claimed in claim 1, wherein the system includes a control signal generator component for generating rotor speed adjustment signal(s) based on output from the control circuitry; and a rotor speed controller for implementing rotor speed adjustment based on the rotor speed adjustment signal(s).

12. The system as claimed in claim 11, wherein the system includes an adaptive positioning module for adjusting positions of UAV rotors in response to payload displacement.

13. An unmanned aerial vehicle (UAV) comprising a stabilization system as claimed in any one of claims 1 to 12, and a payload attached to the attachment point of the stabilization system.

14. A method for stabilizing a payload carried by an unmanned aerial vehicle (UAV), the method comprising:detecting displacement of a movable attachment point along one or more sliding guides at a housing body of the UAV;receiving and processing data relating to the displacement using control circuitry onboard the UAV, and in response thereto, generating one or more control signals; andadjusting speeds of one or more rotors of the UAV based on the generated control signal(s) so as to counteract the displacement of the moveable attachment point and thereby stabilizing the payload carried by the UAV.

15. The method as claimed in claim 14, wherein the step of detecting includes measuring changes in capacitance between fixed and movable capacitor plates provided along the sliding guides.5 16. The method as claimed in claim 14, wherein the step of detecting includes measuringelectrical signals generated by piezoelectric sensors in response to pressure from movement of the attachment point.37

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