WO2024110859A1

WO2024110859A1 - A controlled aerial vehicle

Info

Publication number: WO2024110859A1
Application number: PCT/IB2023/061726
Authority: WO
Inventors: Sandeep REDDY ENTI; Rangoju Vidyasagar; Bayela Sairaj
Original assignee: Cbai Technologies Private Limited
Priority date: 2022-11-21
Filing date: 2023-11-21
Publication date: 2024-05-30

Abstract

The present disclosure relates to a controlled aerial vehicle (100). The controlled aerial vehicle (100) includes a frame (102) defining housing. The frame (102) is configured to house a control module of the controlled aerial vehicle (100). Further, the controlled aerial vehicle (100) includes a plurality of elongated arms (104a, 104b, 104c, 104d) extending outwardly from the frame (102). Further, the vehicle (100) is provided with one or more landing structures (110a, 110b) coupled to the bottom surface (102b) of the frame (102) for providing support for the aerial vehicle during landing and take-off. Furthermore, a mounting means (114) is releasably connectable to the frame configured to receive and support a payload or imaging module (112). The present disclosure provides a controlled aerial vehicle configuration with the payload or imaging module (112) having more clearance to protect the payload during the event of a crash.

Description

“A CONTROLLED AERIAL VEHICLE”

FIELD OF THE DISCLOSURE

[001] The present disclosure in general relates to aircrafts. Particularly, but not exclusively, the present disclosure relates to a controlled aerial vehicle. Further, embodiments of the present disclosure relate to a mounting means of controlled aerial vehicle.

BACKGROUND OF THE DISCLOSURE

[002] The information in this section merely provides background information related to the present disclosure and may not constitute prior art(s) for the present disclosure.

[003] Controlled aerial vehicles are becoming increasingly accepted as a normal part of everyday life. Nowadays, controlled aerial vehicles are not only considered for military or law enforcement purposes, instead, controlled aerial vehicles are being used in farming, ranching, package delivery, and other common applications. The different types of controlled aerial vehicles can be differentiated in terms of the type (fixed-wing, multirotor, etc.), the degree of autonomy, the size and weight, and the power source. These specifications are important, for example for the controlled aerial vehicles’ cruising range, the maximum flight duration, and the loading capacity.

[004] Controlled aerial vehicles are comprised of any size modular airframe to which any number of rotors (electric engines) are attached. A singular rotor drives a singular propeller and when this assembly is used in multiples, such as tri -rotor, quad-rotor, hexa-rotor, or any multiple, these rotor/propellers combine as the mechanism for lifting the modular airframe into flight. Controlled aerial vehicles have a variety of electronic systems for GPS, navigation, or wireless communications. Controlled aerial vehicles are energized by any number of modalities including but not limited to batteries, a combustion engine, jet propulsion, or any other means. Controlled aerial vehicles can include the capability to carry a payload (including but not limited to a camera, packages for delivery, and armaments for example) and are used as a platform for attaching any number of other sensors to capture and record the environment such as infra-red, ultrasonic and many others. The controlled aerial vehicle typically has a landing structure system either retractable or stationary.

[005] Landing structure plays a major role during controlled aerial vehicle crashes on the ground due to some technical error. Upon impact or crash, the landing structure starts flexing. This flexing acts like a cushioning effect and absorbs the impact load. Once the impact load exceeds the elastic limit of the landing structure, it leads to failure or permanent deformation of the landing structure. In that scenario controlled aerial vehicle components like battery, payload, and the controlled aerial vehicle structure absorbs the impact. During that event, the impact loads are transferred directly to the camera/payload which would lead to its damage. In a multirotor-controlled aerial vehicle, a belly-mounted payload/camera does not provide enough clearance to protect the payload/camera from impact loads during a crash, particularly during a crash where the landing structure impacts the ground first.

[006] The present disclosure is directed to overcome one or more limitations stated above or any other limitations associated with the prior art.

SUMMARY OF THE DISCLOSURE

[007] One or more shortcomings of the prior art are overcome by the system/assembly as claimed, and additional advantages are provided through the provision of the system/assembly as claimed in the present disclosure. Additional features and advantages are realized through the techniques of the present disclosure. Other embodiments and aspects of the disclosure are described in detail herein and are considered a part of the claimed disclosure. [008] In one non-limiting embodiment of the present disclosure, a controlled aerial vehicle is disclosed. The controlled aerial vehicle comprises a frame having a top surface, a bottom surface, and a sidewall structure. The controlled aerial vehicle further comprises a plurality of elongated arms extending outwardly from the frame, one or more landing structures connected to the frame, and a mounting means removably mounted onto the top surface of the frame. The mounting means is configured to receive and support a payload module. The mounting means is oriented in a width-wise direction of the frame and configured to provide clearance to protect the pay load module from impact loads during a crash.

[009] In an embodiment of the present disclosure, the mounting means defines a plurality of apertures configured to receive and support the payload module.

[010] In an embodiment of the present disclosure, the mounting means is positioned external to the frame and is connected to the top surface using fastening members.

[Oil] In an embodiment of the present disclosure, the top surface of the frame is defined as a flat surface to mount the mounting means.

[012] In an embodiment of the present disclosure, the mounting means comprises a connector plate to enhance the stability of the connection between the mounting means and the payload module.

[013] In an embodiment of the present disclosure, the mounting means is adapted to be removably mounted onto the top surface of the frame to accommodate different payload module configurations.

[014] In an embodiment of the present disclosure, the plurality of elongated arms are connected to the frame by at least one binding screw mechanism or a lock pin mechanism, enabling the elongated arms to displace between an extended position and a collapsed position.

[015] In an embodiment of the present disclosure, the controller aerial vehicle comprises a battery module connected to the frame. The battery module is mounted to the bottom surface of the frame and is adapted to power a control module and the rotor assembly of the controlled aerial vehicle.

[016] In an embodiment of the present disclosure, the one or more landing structures are made of composite materials and are adapted to absorb impact load by elastic deformation.

[017] In an embodiment of the present disclosure, the controller aerial vehicle comprises a plurality of safety pillars configured to prevent damage to the battery module during vertical drop conditions.

[018] The foregoing summary is illustrative only and is not intended to be in any way limiting. In addition to the illustrative aspects, embodiments, and features described above, further aspects, embodiments, and features will become apparent by reference to the drawings and the following description.

BRIEF DESCRIPTION OF FIGURES

[019] The novel features and characteristics of the disclosure are set forth in the description. The disclosure itself, however, as well as a mode of use, further objectives, and advantages thereof, will best be understood by reference to the following detailed description of an embodiment when read in conjunction with the accompanying drawings. One or more embodiments are now described, by way of example only, with reference to the accompanying drawings wherein like reference numerals represent like elements and in which: [020] Figure 1 illustrates an exemplary schematic view of a controlled aerial vehicle, in accordance with an embodiment of the present disclosure.

[021] Figure 2 illustrates a zoomed perspective view of a mounting means securable to a top surface of the controlled aerial vehicle, in accordance with an embodiment of the present disclosure.

[022] Figure 3 illustrates a schematic view of the mounting means, in accordance with an embodiment of the present disclosure.

[023] Figure 4 illustrates two cases for comparison of mounting a payload or imaging module with or without the mounting means, in accordance with an embodiment of the present disclosure.

[024] Figure 5 illustrates a safe landing condition of the payload or imaging module i.e. when there is no deformation in one or more landing structures, in accordance with an embodiment of the present disclosure.

[025] Figure 6 illustrates a condition in which one or more landing structures fail and the controlled aerial vehicle lands on the safety pillars, in accordance with an embodiment of the present disclosure.

[026] Figure 7 illustrates a condition when the controlled aerial vehicle falls at an angular tilt, in accordance with an embodiment of the present disclosure.

[027] Skilled artisans will appreciate that elements in the drawings are illustrated for simplicity and have not necessarily been drawn to scale. For example, the dimensions of some of the elements in the drawings may be exaggerated relative to other elements to help to improve understanding of embodiments of the present invention.

DETAILED DESCRIPTION [028] While the embodiments in the disclosure are subject to various modifications and alternative forms, specific embodiment thereof has been shown by way of example in the figures and will be described below. It should be understood, however, that it is not intended to limit the disclosure to the particular forms disclosed, but on the contrary, the present disclosure is to cover all modifications, equivalents, and alternatives falling within the scope of the disclosure.

[029] It is to be noted that a person skilled in the art would be motivated by the present disclosure and modify various features of the system or method, without departing from the scope of the disclosure. Therefore, such modifications are considered to be part of the disclosure.

[030] Accordingly, the drawings show only those specific details that are pertinent to understanding the embodiments of the present disclosure, so as not to obscure the disclosure with details that will be readily apparent to those of ordinary skilled in the art having the benefit of the description herein.

[031] The terms “comprises”, “comprising”, or any other variations thereof used in the disclosure, are intended to cover a non-exclusive inclusion, such that a system and method that comprises a list of components does not include only those components but may include other components not expressly listed or inherent to such system, method, or assembly, or device. In other words, one or more elements in a system or device proceeded by “comprises... a” does not, without more constraints, preclude the existence of other elements or additional elements in the system or device.

[032] In the following description of the embodiments of the disclosure, reference is made to the accompanying figure that forms a part hereof, and which is shown by way of illustration of specific embodiments in which the disclosure may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the disclosure, and it is to be understood that other embodiments may be utilized and that changes may be made without departing from the scope of the present disclosure. The following description is, therefore, not to be taken in a limiting sense.

[033] The following paragraphs describe the present disclosure with reference to Figures. 1 to 7. With general reference to the drawing, a controlled aerial vehicle is illustrated and generally identified with reference numeral 100. The controlled aerial vehicle (100) of the present disclosure may be a quad-rotor aerial vehicle (e.g., an aerial vehicle having four rotor assemblyies). It will be appreciated that the aerial vehicle may be a multi-rotor aerial vehicle having six rotor assemblies, eight rotor assemblies, and the like. The controlled aerial vehicle (100) of the present disclosure may include a controlled aerial vehicle structure referred to as a frame. In the corresponding figures, the frame is denoted by referral numeral 102. In an embodiment, the frame (102) may be made of metal such as aluminium, or suitable plastic or polymer, or any other suitable material or combination of materials. In another embodiment, the frame (102) may be made of composite materials but is not limited to the same. For instance, the frame (102) may be made of carbon fiber, fiberglass, and other suitable materials. The frame (102) may be a truss structure, a monocoque, or a semi-monocoque structure.

[034] The frame (102) may define a housing configured to receive and support electronic components hereinafter referred to as a control module (not shown). The control module may include a main computer board, onboard electronics, GPS module, air telemetry, and radio receiver each of them connected to the main computer board. In another embodiment, the control module may include a power distribution board. The frame (102) may include a top surface (102a), a bottom surface (102b), and a sidewall structure (102c) a portion of which extends from the top surface (102a) and the remaining portion of which extends from the bottom surface (102b). The top surface (102a) and the bottom surface (102b) may be snapped to the bottom surface (102b) to form the housing defining a space therebetween to accommodate the control module. In another embodiment, the top surface (102a) and the bottom surface (102b) may be connected by other means including but not limited to screw connections. The frame (102) may have various shapes according to different configurations on the appearance of the controlled aerial vehicle (100). For instance, the frame (102) may be squareshaped, a polygonal shape, an aerodynamic shape, a streamlined shape, or any regular or irregular shape.

[035] Further, the controlled aerial vehicle (100) comprises a plurality of elongated arms (104a, 104b, 104c, and 104d) extending outwardly from the frame (102). In an embodiment, the frame (102) may be defined with one or more connecting ports (not shown). One or more connecting ports may be defined at a predefined location on the frame (102). For instance, one or more connecting ports may be defined at the outermost corners of the frame (102). In an embodiment, the first end of each of the elongated arms (104a, 104b, 104c, and 104d) may be receivable by corresponding connecting ports of the one or more connecting ports defined on the frame (102).

[036] In an embodiment, each of the plurality of elongated arms (104a, 104b, 104c, 104d) may be either fixedly connected or may be movably connected to the frame (102). In an embodiment, the first end of the elongated arms (104a, 104b, 104c, 104d) may be connected to the frame (102) by at least one binding screw mechanism or a lock pin mechanism which enables the elongated arms (104a, 104b, 104c, 104d) to displace between an extended position and collapsed position.

[037] In an embodiment, the extended position is defined as a position in which the elongated arms (104a, 104b, 104c, 104d) are fully stretched or deployed outwardly from the frame (102). The extended position provides stability and balance to the aerial vehicle by spreading the elongated arms (104a, 104b, 104c, 104d) outward, supporting its structure and ensuring effective control during flight. In an embodiment, the collapsed position is defined as a position in which the elongated arms (104a, 104b, 104c, 104d) are brought closer to the frame (102) or folded inwards. This configuration is useful during non-operational phases, such as storage, transportation, or when the controlled aerial vehicle (100) is not in use. Collapsing the elongated arms (104a, 104b, 104c, 104d) makes the controlled aerial vehicle (100) more compact, reducing its overall size and facilitating easier handling, storage, or transport.

[038] It should be noted that the number of elongated arms depends on the type of the controlled aerial vehicle (100) i.e., whether the controlled aerial vehicle (100) is a quadrotor, hexa-rotor, octa-rotor, or a multi-rotor controlled aerial vehicle. Although the controlled aerial vehicle (100) depicted in the figures is a quad-rotor-controlled aerial vehicle, the same should not be construed as a limitation of the present disclosure.

[039] In an embodiment, the plurality of elongated arms (104a, 104b, 104c, 104d) may be symmetrical with respect to the substantial center of the frame (102). The second end of each of the plurality of elongated arms (104a, 104b, 104c, and 104d) [refer to FIG.2] opposite to the first end may be defined with a receiving portion. The receiving portion defined in each of the plurality of elongated arms (104a, 104b, 104c, and 104d) may be configured to receive and support motors. The motors are also referred to as rotor assembly and are denoted by referral numerals 106a, 106b, 106c, and 106d as apparent from FIG.l. The rotor assembly (106a, 106b, 106c, 106d) includes a motor and a propeller connected to the motor. The motor is configured to drive the propeller to rotate and hence provide propulsion to the controlled aerial vehicle (100). The motor of the rotor assembly (106a, 106b, 106c, 106d) may be powered by a battery module (108) connected to the frame (102). In an embodiment, the battery module (108) may be releasably connected to the frame (102). In another embodiment, the battery module (108) may be mounted to the bottom surface (102b) of the frame (102). The battery module (108) may be adapted to power the control module and the rotor assembly (106a, 106b, 106c, and 106d) of the controlled aerial vehicle (100). In an embodiment, the battery module (108) may include a series of batteries or maybe an individual battery of the necessary capacity.

[040] The frame (102) may further include one or more landing structures (110a, 110b). One or more landing structures (110a, 110b) may be connected to the frame (102). In some embodiments, one or more landing structures (110a, 110b) may be fixedly secured to the frame (102). In another embodiment, the one or more landing structures (110a, 110b) may be rotatably connected to the frame (102), and the one or more landing structures (110a, 110b) may be lowered or raised based on the condition of the controlled aerial vehicle (100). For instance, one or more landing structures (110a, 110b) are raised when the controlled aerial vehicle (100) takes off and are lowered when the controlled aerial vehicle is about to land. One or more landing structures (110a, 110b) may be made of composite materials. The said landing structures (110a, 110b) may be adapted to absorb impact load by elastic deformation. One or more landing structures (110a, 110b) provide support for the controlled aerial vehicle (100) during landing and take-off.

[041] In a preferred embodiment, the frame (102) further comprises a plurality of safety pillars (118) located at four corners of the battery module (108). During vertical drop conditions, the controlled aerial vehicle (100) lands on its landing structures (110a, 110b). The landing structures (110a, 110b) absorb impact load by undergoing elastic deformation. However, when the impact load exceeds the elastic limit of landing structures (110a, 110b), the landing structures (110a, 110b) undergo plastic deformation or break. In those scenarios, the plurality of safety pillars (118) is configured for preventing damage to the battery module (108). In an embodiment, the controlled aerial vehicle (100) is capable of remote -piloted or pre-programmed flight. In some embodiments, the controlled aerial vehicle (100) receives control signals from the control module (not shown). In other embodiments, the controlled aerial vehicle (100) stores flight information and executes the stored flight information. In some embodiments, the controlled aerial vehicle (100) operates on a combination of real-time and stored commands.

[042] In an embodiment, the frame (102) also includes a connection point (not shown). In some embodiments, the connection point facilitates the connection of a power or data source to the frame (102). For example, a cord to supply power to the battery module (108) of the frame (102) may be connected at the connection point. In another example, a data connection may be established via the connection point to provide data to the rotor assembly (106a, 106b, 106c, and 106d) of the frame (102). Data may include commands to move the rotor assembly (106a, 106b, 106c, and 106d) based on a movement schedule or programming. Data may also include positional calibration for movement of the elongated arms (104a, 104b, 104c, 104d). Other data may also be used, accessed, and/or communicated via the connection point. In an embodiment, movement of the one or more components of the rotor assembly (106a, 106b, 106c, and 106d) is monitored by a sensor. For example, the movement of one or more components of the controlled aerial vehicle (100) may be measured by a position sensor or a camera. Other manners of monitoring the movement of the remote-controlled aerial vehicle arm are contemplated.

[043] In an embodiment, the frame (102) further includes a pay load or imaging module (112). The payload or imaging module comprises a casing that houses at least one piece of optical equipment and an electronic control and processing system. Optionally, the pay load or imaging module (112) may also comprise one or more pieces of secondary optical equipment. In a preferred embodiment, the optical equipment may, for example, and without limitation, comprise a camera that may be suitable for capturing images in the visible or infrared range, or for example may be a laser pointer.

[044] The frame (102) further includes a mounting means (114) in accordance with an embodiment of the present disclosure. The mounting means (114) may be configured to receive and support the payload or imaging module (112). The pay load or imaging module (112) may be connected to the frame (102) by the mounting means (114). In an embodiment, most of the components of the pay load or imaging module (112) are mounted on the mounting means (114). Notably, a significant aspect of this embodiment involves mounting most components of the payload or imaging module (112) directly onto the mounting means (114), contributing to a consolidated and efficient configuration.

[045] In an embodiment, the mounting means (112) may include a connector plate (120) to enhance the stability of the connection. The top surface (102a) may be defined as a substantially flat surface, providing a standardized and reliable foundation for the mounting means (114). To ensure a robust attachment, the mounting means (114) is positioned external to the frame (102) and secured to the top surface (102a) using fastening members such as fasteners. This external mounting not only simplifies the assembly process but also allows for greater adaptability in accommodating diverse payload or imaging module configurations.

Moreover, the orientation of the mounting means (114) is a key consideration. According to the present disclosure, the mounting means (114) is specifically oriented in the width- wise direction of the frame (102), aligning with the structural requirements of the aerial vehicle. The mounting means (114) is configured to provide clearance to protect the pay load module (112) from impact loads during a crash. This strategic orientation enhances the overall stability and balance of the system during operation.

[046] To accommodate different payload or imaging module types, a plurality of apertures (116) is defined in the mounting means (114). These apertures are customizable in terms of shape and dimensions based on the specific requirements of the payload or imaging module (112). This customization ensures a precise fit and secure support for diverse components, contributing to the versatility of the aerial vehicle system.

[047] Crucially, the removability feature of the mounting means (114) adds another layer of flexibility to this embodiment. By being removably mounted onto the top surface (102a) of the frame (102), the mounting means (114) facilitates easy assembly and disassembly processes. This feature is particularly advantageous for maintenance, upgrades, and adjustments to accommodate evolving operational needs.

[048] In an embodiment illustrated in Fig. 4, a comparative analysis is presented to highlight the advantages of incorporating the mounting means (114) in the controlled aerial vehicle configuration, as proposed in the present disclosure. Two distinct cases are depicted for comparison, emphasizing the impact on the clearance of the payload or imaging module (112) under different mounting conditions.

[049] Case 1 represents the controlled aerial vehicle configuration with the inclusion of the mounting means (114) in accordance with the present disclosure. In this scenario, the payload or imaging module (112) is strategically positioned, ensuring it is not in close proximity to the ground. The mounting means (114) plays a pivotal role in maintaining a favorable clearance for the payload or imaging module (112). This embodiment is configured to prioritize the protection of the payload or imaging module (112) from potential damage during various operational scenarios.

[050] Conversely, Case 2 illustrates the conventional controlled aerial vehicle configuration without the additional mounting means (114). In this case, the pay load or imaging module (112) is directly mounted to the frame (102), without the specialized support provided by the mounting means. As Fig. 4 clearly demonstrates, Case 2 exhibits less clearance compared to Case 1, making the payload or imaging module (112) more vulnerable to potential damage. [051] The visual representation in Fig. 4 underscores the significance of the mounting means (114) in enhancing the overall safety and protection of the payload or imaging module (112). The comparison vividly showcases that the configuration with the mounting means (114) (Case 1) provides a more substantial clearance, mitigating the risk of damage to the payload or imaging module (112) during the aerial vehicle's operation. This embodiment, as depicted in Fig. 4, substantiates the practical benefits of incorporating the mounting means (114) in the design, emphasizing its role in optimizing the clearance and safeguarding critical components of the controlled aerial vehicle.

[052] Figs. 5 to 7 illustrate the clearance from the ground to the payload or imaging module (112) under different landing conditions. Fig. 5 illustrates a safe landing condition i.e. when there is no deformation in one or more landing structures (110a, 110b). In this condition both the landing structures (110a, 110b) are parallel and in contact with the ground. In an embodiment, a distance of 156 mm is observed between the ground and the payload or imaging module (112) in the controlled aerial vehicle configuration as proposed in the present disclosure.

[053] Fig. 6 illustrates a condition in which one or more landing structures (110a, 110b) fail and the controlled aerial vehicle (100) lands on the safety pillars (118). In an embodiment, a distance of 50 mm is observed between the safety pillars (118) and the pay load or imaging module (112) in the controlled aerial vehicle configuration as proposed in the present disclosure in order to protect the payload or imaging module (112) from damage. Another condition of landing is when the safety pillars (118) also break and the controlled aerial vehicle (100) lands on a lower surface of the battery module (108). In an embodiment, Fig. 6 illustrates a clearance of 30 mm from the lower surface of the battery module (108) and the payload or imaging module (112) to protect the pay load or imaging module (112) from damage. Fig. 7 illustrates a condition when the controlled aerial vehicle (100) falls at an angular tilt. In such a scenario, when the controlled aerial vehicle (100) tilts during its fall thereby allowing the elongated arms (104a, 104b, 104c, and 104d) to touch the ground and act as a support structure. In an embodiment, it can be observed that a clearance of 70 mm from the ground to the payload or imaging module (112) is provided in such a scenario. Therefore, the mounting means (114) of the present disclosure provides enough clearance and eliminates the chances of damage to the pay load or imaging module (112) during an event of a crash. Further, the mounting means (114) may be easy to assemble and disassemble.

[054] The incorporation of the mounting means (114) in the frame (102) as described in the present disclosure offers several notable advantages. One key benefit is the enhanced protection of the payload or imaging module (112). The mounting means (114) is specifically configured to receive and support the payload or imaging module (112), providing a secure connection that minimizes the risk of damage during controlled aerial vehicle operations. This is particularly evident in the comparison between Case 1, where the mounting means is employed, and Case 2, which represents a conventional configuration without the additional mounting means. Fig. 4 illustrates that Case 1 , with the mounting means, offers significantly more clearance to safeguard the pay load or imaging module (112) from potential damage, highlighting the protective advantage of the mounting means.

[055] Furthermore, the configuration of the mounting means (114) includes a plurality of apertures (116) with variable shapes and dimensions, tailored to the specific type of payload or imaging module (112). This adaptability ensures a secure and customized fit, addressing the diverse requirements of different components. Additionally, the mounting means (114) is removably attached to the top surface (102a) of the frame (102), allowing for easy assembly and disassembly. This feature not only facilitates efficient maintenance and upgrades but also contributes to the versatility of the overall system.

[056] The advantages extend to various landing conditions, as depicted in Figs. 5 to 7. The controlled aerial vehicle configuration proposed in the present disclosure, with the mounting means (114), demonstrates superior protection during safe landings, failures of landing structures, and even angular tilts. The clearance provided by the mounting means (114) in these scenarios ensures that the payload or imaging module (112) remains safeguarded from potential damage. Importantly, the mounting means (114) proves to be a crucial element in preventing harm during events like crashes, where the configured clearances effectively eliminate the chances of damage to the payload or imaging module (112). Overall, the mounting means (114) not only enhances the safety and protection of the payload but also offers ease of assembly and adaptability to diverse operational requirements.

[057] The various embodiments of the present disclosure have been described above with reference to the accompanying drawings. The present disclosure is not limited to the illustrated embodiments; rather, these embodiments are intended to fully and completely disclose the subject matter of the disclosure to those skilled in this art. In the drawings, like numbers refer to like elements throughout. Thicknesses and dimensions of some components may be exaggerated for clarity.

[058] Herein, the terms “attached”, “connected”, “interconnected”, “contacting”, “mounted”, “coupled” and the like can mean either direct or indirect attachment or contact between elements, unless stated otherwise.

[059] Well-known functions or constructions may not be described in detail for brevity and/or clarity. As used herein the expression “and/or” includes any and all combinations of one or more of the associated listed items. [060] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises”, “comprising”, “includes” and/or “including” when used in this specification, specify the presence of stated features, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, operations, elements, components, and/or groups thereof.

[061] While considerable emphasis has been placed herein on the particular features of this disclosure, it will be appreciated that various modifications can be made, and that many changes can be made in the preferred embodiments without departing from the principles of the disclosure. These and other modifications in the nature of the disclosure or the preferred embodiments will be apparent to those skilled in the art from the disclosure herein, whereby it is to be distinctly understood that the foregoing descriptive matter is to be interpreted merely as illustrative of the disclosure and not as a limitation.

[062] EQUIVALENTS:

[063] The embodiments herein and the various features and advantageous details thereof are explained with reference to the non-limiting embodiments in the description. Descriptions of well-known components and processing techniques are omitted so as to not unnecessarily obscure the embodiments herein. The examples used herein are intended merely to facilitate an understanding of ways in which the embodiments herein may be practiced and to further enable those of skill in the art to practice the embodiments herein. Accordingly, the examples should not be construed as limiting the scope of the embodiments herein.

[064] The foregoing description of the specific embodiments will so fully reveal the general nature of the embodiments herein that others can, by applying current knowledge, readily modify and/or adapt for various applications such specific embodiments without departing from the generic concept, and, therefore, such adaptations and modifications should and are intended to be comprehended within the meaning and range of equivalents of the disclosed embodiments. It is to be understood that the phraseology or terminology employed herein is for the purpose of description and not of limitation. Therefore, while the embodiments herein have been described in terms of preferred embodiments, those skilled in the art will recognize that the embodiments herein can be practiced with modification within the spirit and scope of the embodiments as described herein.

[065] Any discussion of documents, acts, materials, devices, articles and the like that has been included in this specification is solely for the purpose of providing a context for the disclosure. It is not to be taken as an admission that any or all of these matters form a part of the prior art base or were common general knowledge in the field relevant to the disclosure as it existed anywhere before the priority date of this application.

[066] The numerical values mentioned for the various physical parameters, dimensions or quantities are only approximations and it is envisaged that the values higher/lower than the numerical values assigned to the parameters, dimensions or quantities fall within the scope of the disclosure, unless there is a statement in the specification specific to the contrary.

[067] List of reference numerals: -

Claims

We Claim:

1. A controlled aerial vehicle (100) comprising: a frame (102) having a top surface (102a), a bottom surface (102b), and a side wall structure (102c); a plurality of elongated arms (104a, 104b, 104c, 104d) extending outwardly from the frame (102); one or more landing structures (110a, 110b) connected to the frame (102); and a mounting means (114) removably mounted onto the top surface (102a) of the frame (102), the mounting means (114) configured to receive and support a payload module (112), wherein the mounting means (114) is oriented in a width -wise direction of the frame (102) and configured to provide clearance to protect the payload module (112) from impact loads during a crash.

2. The controlled aerial vehicle (100) as claimed in claim 1, wherein the mounting means (114) defines a plurality of apertures (116) configured to receive and support the payload module (112).

3. The controlled aerial vehicle (100) as claimed in claim 1, wherein the mounting means (114) is positioned external to the frame (102) and is connected to the top surface (102a) using fastening members.

4. The controlled aerial vehicle (100) as claimed in claim 1, wherein the top surface (102a) of the frame (102) is defined as a flat surface to mount the mounting means (114).

5. The controlled aerial vehicle (100) as claimed in claim 1, wherein the mounting means (114) comprises a connector plate (120) to enhance the stability of the connection between the mounting means (114) and the payload module (112).

6. The controlled aerial vehicle (100) as claimed in claim 1, wherein the mounting means (114) is adapted to be removably mounted onto the top surface (102a) of the frame (102) to accommodate different payload module (112) configurations.

7. The controlled aerial vehicle (100) as claimed in claim 1, wherein the plurality of elongated arms (104a, 104b, 104c, 104d) are connected to the frame (102) by at least one binding screw mechanism or a lock pin mechanism, enabling the elongated arms (104a, 104b, 104c, 104d) to displace between an extended position and a collapsed position.

8. The controlled aerial vehicle (100) as claimed in claim 1, comprises a battery module (108) connected to the frame (102), wherein the battery module (108) is mounted to the bottom surface (102b) of the frame (102) and is adapted to power a control module and the rotor assembly (106a, 106b, 106c, and 106d) of the controlled aerial vehicle (100).

9. The controlled aerial vehicle (100) as claimed in claim 1, wherein the one or more landing structures (110a, 110b) are made of composite materials and are adapted to absorb impact load by elastic deformation.

10. The controlled aerial vehicle (100) as claimed in claim 1, comprises a plurality of safety pillars (118) configured to prevent damage to the battery module (108) during vertical drop conditions.