DESC:FIELD OF DISCLOSURE
The present disclosure is generally related to a system and a method for landing drones, and more particularly to a system and a method for landing drones on inclined surfaces.
BACKGROUND
Drones, also known as unmanned aerial vehicles (UAVs), are commonly used in various industries such as photography, agriculture, delivery services, and surveillance. These devices are typically designed to take off and land on flat surfaces. However, in real-world scenarios, drones often need to land on uneven or inclined surfaces, which can pose a challenge.
One of the major issues with current drone technology is the difficulty in landing these devices on inclined or uneven surfaces. One of the reasons for this is that drones are designed with landing gears that are rigid and do not adjust to the topography of the landing area. As a result, when a drone attempts to land on an inclined surface, it can easily lose balance and tip over, potentially causing damage to the drone and its cargo. Furthermore, the inability to land on inclined surfaces limits the locations where drones can safely land, which in turn restricts their utility in various applications.
There have been several attempts to address this problem. Some solutions involve the use of complex mechanical systems or additional equipment to alter the landing surface, such as levelling devices or platforms. However, these solutions can be cumbersome, expensive, and impractical, especially in remote or hard-to-access locations. Other solutions propose the use of advanced control algorithms to adjust the drone's flight path and landing approach based on the detected inclination of the landing surface. However, these solutions require sophisticated sensors and high computational power, and they may not always be reliable in different weather conditions or with varying payloads.
Other methods involve adjusting the structure of the drone itself to accommodate uneven landing surfaces. For instance, some drones are designed with flexible landing gears that can bend or flex to match the contour of the landing surface. However, these designs can compromise the structural integrity of the drone and may not provide sufficient stability during landing, especially for larger drones carrying heavy payloads. Moreover, the flexibility of the landing gears may not be adjustable, limiting their effectiveness on surfaces with varying degrees of inclination.
Therefore, there is a need to overcome the problems discussed above. A system and method that allow drones to land safely and securely on inclined surfaces, without the need for additional equipment or complex control algorithms, would be a significant advancement in the field. Such a system should ideally be simple, cost-effective, and adaptable to different types of drones and payloads. Furthermore, the system should provide reliable performance under various environmental conditions and across a wide range of surface inclinations.
SUMMARY
A system for landing drones on inclined surfaces in accordance with the present disclosure comprises a frame, one or more attachment means, two or more servo systems, a controller, and a luggage carrier. The frame of the drone comprises a top surface coupled to a first end of the two or more landing gears. The one or more attachment means comprise a cavity at a first portion of the one or more attachment means for coupling a second end of the two or more landing gears. The two or more servo systems configured to be coupled within a loop at a second portion of the one or more attachment means. Further, the controller is configured to be coupled to the frame of the drone. The luggage carrier is configured to be coupled to the one or more attachment means and the two or more servo systems via one or more upper holes and one or more lower holes respectively. The luggage carrier comprises one or more image capturing units and the one or more sensor units coupled to an outer surface of the luggage carrier. Also, the controller is configured to be communicatively coupled via a communication network to the one or more image capturing units, the one or more sensor units, and the two or more servo systems.
A method for landing drones on inclined surfaces, the method is being performed by a system in accordance with the present disclosure. The system comprises a frame of the drone comprising a top surface and two or more landing gears, one or more attachment means, two or more servo systems, a controller, a luggage carrier, one or more image capturing units, and one or more sensor units. The controller is communicatively coupled to the one or more image capturing units, the one or more sensor units, and the two or more servo systems via a communication network. The method comprises monitoring by the one or more image capturing units and the one or more sensor units a landing area for the landing of the drone. The method further includes transmitting by the one or more image capturing units and the one or more sensor units, signals corresponding to the monitoring of the landing area to the controller. The method involves adjusting by the controller the drone to a center of the landing area corresponding to the received signals. Further, the method comprises calculating by the controller, an inclination angle of the landing area corresponding to the received signals. The method also involves determining by the controller, control signals for adjusting an angle of the luggage carrier corresponding to the inclination angle of the landing area. The method comprises transmitting by the controller the determined control signals to the two or more servo systems. Moreover, the method includes adjusting by the two or more servo systems the luggage carrier based on the determined control signals over the landing area.
In an embodiment of the present disclosure, the controller is configured to receive signals corresponding to monitoring of the landing area via the one or more image capturing units and the one or more sensor units. Further, the controller calculates an inclination angle of the landing area based on the received signals. The controller further generates a control signal corresponding to the calculated inclination angle of the landing area. The generated control signal is transmitted to each of the two or more servo systems by the controller.
In an embodiment of the present disclosure, the two or more servo systems are configured to adjust an angle of the luggage carrier with respect to the inclination angle of the landing area based on the received control signal from the controller.
In an embodiment of the present disclosure, the luggage carrier of the drone is configured to couple to the one or more attachment means and the two or more servo systems via one or more upper holes and one or more lower holes respectively.
In an embodiment of the present disclosure, the one or more upper holes comprise c-shaped holes and the one or more lower holes comprise a series of holes.
In an embodiment, the one or more attachment means comprise one or more protrusions that are configured to couple to the one or more upper holes of the luggage carrier. The one or more protrusions are L-shaped.
BRIEF DESCRIPTION OF FIGURES
The foregoing and other features of this disclosure will become more fully apparent from the following description and appended claims, taken in conjunction with the accompanying drawings. Understanding that these drawings depict only several embodiments in accordance with the disclosure and are, therefore, not to be considered limiting of its scope, the disclosure will be described with additional specificity and detail through use of the accompanying drawings, in which:
Fig. 1 illustrates an exemplary representation of a system 100 for landing drones on inclined surfaces in accordance with the present disclosure;
Fig. 2a illustrates an exemplary representation of a side-view of a luggage carrier 201 in accordance with the present disclosure;
Fig. 2b illustrates an exemplary representation of a bottom-view of the luggage carriage 201 in accordance with the present disclosure;
Fig. 3a illustrates an exemplary representation of a back-view of one or more attachment means 300 in accordance with the present disclosure;
Fig. 3b illustrates an exemplary representation of a front-view of the one or more attachment means 300 in accordance with the present disclosure;
Fig. 4 illustrates an exemplary block diagram 400 of the system 100 for landing drones on the inclined surfaces in accordance with the present disclosure;
Fig. 5 illustrates an exemplary flow chart of a method 500 for landing drones on the inclined surfaces in accordance with the present disclosure.
LIST OF REFERENCE NUMERALS
100 – System
101 – two or more landing gears
102, 201 – luggage carrier
103, 300 – one or more attachment means
104, 404 – two or more servo systems
202 – one or more upper holes
203 – one or more lower holes
301 – cavity
302 – one or more protrusions
303 – loop
304 – hooks
401 – one or more image capturing units
402 – one or more sensor units
403 – controller
DETAILED DESCRIPTION
Embodiments of the present invention are best understood by reference to the figures and description set forth herein. All the aspects of the embodiments described herein will be better appreciated and understood when considered in conjunction with the following description and the accompanying drawings. It should be understood, however, that the following descriptions, while indicating preferred embodiments and numerous specific details thereof, are given by way of illustration and not of limitation. Many changes and modifications may be made within the scope of the embodiments herein without departing from the spirit and scope thereof, and the embodiments herein include all such modifications.
As used herein, the term ‘exemplary’ or ‘illustrative’ means ‘serving as an example, instance, or illustration.’ Any implementation described herein as exemplary or illustrative is not necessarily to be construed as advantageous and/or preferred over other embodiments. Unless the context requires otherwise, throughout the description and the claims, the word ‘comprise’ and variations thereof, such as ‘comprises’ and ‘comprising’ are to be construed in an open, inclusive sense, i.e., as ‘including, but not limited to.’
This disclosure is generally drawn, inter alia, to methods, apparatuses, systems, devices implemented as automated tools for landing of drones on inclined surfaces.
Fig. 1 illustrates an exemplary representation of a system 100 for landing drones on inclined surfaces in accordance with the present disclosure. The system 100 comprises a frame of the drone. The frame comprising a top surface and two or more landing gears 101. The two or more landing gears 101 comprise a first end and a second end. The first end of each of the two or more landing gears 101 is coupled to the top surface of the frame. The second end of each of the two or more landing gears 101 is coupled to the one or more attachment means 103. In an embodiment of the present disclosure, the two or more landing gears 101 of the drone may be either of retractable landing gears or fixed landing gears. The one or more attachment means 103 comprises a cavity 301, a loop 303, and one or more protrusions 302. The cavity 301 of the one or more attachment means 103 is configured to couple the second end of each of the two or more landing gears 101. Further, two or more servo systems 104 are coupled within the loop 303 of the one or more attachment means 103. Also, the one or more protrusions 302 of the one or more attachment means 103 are coupled to a luggage carrier 102 of the drone. Furthermore, the luggage carrier 102 is coupled to the one or more attachment means 103 and the two or more servo systems 104. Moreover, an outer surface of the luggage carrier 102 is coupled to one or more image capturing units 401 and one or more sensor units 402. A controller 403 is also coupled to the frame of the drone and is configured to operate the drone. The controller (not shown) is configured to be communicatively coupled to the two or more servo systems 104, the one or more image capturing units (not shown) and the one or more sensor units (not shown) via a communication network. In an embodiment of the present disclosure, the controller is communicatively coupled to a remote controller for controlling the operation of the drone via receiving corresponding signals from the remote controller, for e.g., flight of the drone as well as landing of the drone.
Fig. 2a illustrates an exemplary representation of a side-view of the luggage carrier 201 in accordance with the present disclosure. The luggage carrier 201 is configured to carry useful items as a payload with the drone during flight. The luggage carrier 201 may be either an enclosed case or an open case. In an embodiment, the luggage carrier 201 is made of lightweight materials such as carbon fiber, or plastic, to minimize weight on the drone. Also, the capability of the luggage carrier 201 for carrying payload is made appropriate for range of purposes, for e.g., delivery services, search and rescue missions, or the like. Further, the luggage carrier 201 comprises the one or more upper holes 202 and the one or more lower holes 203. The one or more upper holes 202 of the luggage carrier 201 are configured to couple to the one or more protrusions 302 of the one or more attachment means 103. The one or more upper holes 202 are configured to restrict the movement of the luggage carrier 201 with respect to the one or more attachment means 103. In an embodiment of the present disclosure, the one or more upper holes 202 are c-shaped hole. In another embodiment of the present disclosure, the one or more upper holes 202 are round holes. In an embodiment, the one or more upper holes 202 are single holes on opposite sides of the luggage carrier 201. Furthermore, the one or more lower holes 203 of the luggage carrier 201 are configured to couple the two or more servo systems 104 with the luggage carrier 201. In an embodiment of the present disclosure, the one or more lower holes 203 comprise a series of holes. In an embodiment, the one or more lower holes 203 are below the one or more upper holes 202 over the luggage carrier 201. In an embodiment, the one or more lower holes 203 are also on a same side of the luggage carrier 201 as the one or more upper holes 202.
Fig. 2b illustrates an exemplary representation of a bottom-view of the luggage carriage 201 in accordance with the present disclosure. The bottom of the luggage carrier 201 is a flat surface of the case of the luggage carrier 201. In an embodiment, the bottom of the case of the luggage carrier 201 is coupled to the one or more image capturing units and the one or more sensor units. In another embodiment, the sides of the case of the luggage carrier 201 are coupled to the one or more image capturing units and the one or more sensor units. In an embodiment, the one or more image capturing units comprise a camera. In an embodiment, the one or more sensor units are ultrasonic sensors, LiDAR, Time-of-flight (ToF) sensors, and the like.
Fig. 3a and 3b illustrate exemplary representations of a back-view and a front-view of the one or more attachment means 103 in accordance with the present disclosure. The one or more attachment means 103 comprises a first portion and a second portion. The first portion of the one or more attachment means 103 are coupled to the second portion. The first portion comprises the cavity 301, one or more protrusions 302 and hooks 304. The first portion is made up of two symmetrical halves. The two symmetrical halves of the first portion are coupled to each other via the hooks 304 at both sides of the first portion. The hooks 304 are configured to couple the two symmetrical halves of the first portion via some nut and screw kind of arrangement. In an embodiment, the two symmetrical halves of the first portion are coupled to each other via some other arrangement. The one or more protrusions 302 are coupled at an upper end of either one of the two symmetrical halves of the first portion of the one or more attachment means 300. The one or more protrusions 302 are configured to couple with the one or more upper holes 202 of the luggage carrier 102, 201. In an embodiment of the present disclosure, the one or more protrusions 302 is a single protrusion. In another embodiment of the present disclosure, the one or more protrusions 302 are multiple protrusions. In an embodiment of the present disclosure, the one or more protrusions 302 comprises an L-shaped protrusion. The second portion of the one or more attachment means 300 comprise the loop 303 for coupling the two or more servo systems 104 therewithin. The loop 303 comprises holes at an upper end and a lower end for coupling some portion of the two or more servo systems 104 with the loop 303 via some kind of nut and screw kind of arrangement. In an embodiment, the loop 303 may also comprise other means for coupling the two or more servo systems 104 to the one or more attachment means 300.
Fig. 4 illustrates an exemplary block diagram of the system 100 for landing drones on the inclined surfaces in accordance with the present disclosure. The system 100 comprises the one or more image capturing units 401, the one or more sensor units 402, the controller 403 and the two or more servo systems 404. The one or more image capturing units 401 and the one or more sensor units 402 are coupled to the controller 403 via wired or wireless connections. Further, the controller 403 is also coupled to the two or more servo systems 404 via wired or wireless connections. The one or more image capturing units 401 and the one or more sensor units 402 are configured to monitor the landing area and generate signals corresponding to the monitoring of the landing area for landing of the drone. The one or more image capturing units 401 are configured to capture image of the target area for the landing of the drone. The captured image by the one or more image capturing units 401 are transmitted to the controller 403 for further processing. The one or more sensor units 402 are configured to measure one or more parameters corresponding to the monitoring of the landing area. The measured one or more parameters by the one or more sensor units 402 are further transmitted to the controller 403. The one or more parameters may comprise an inclination angle of the landing area, total landing area, a position of the landing area, nearby surroundings of the landing area, vicinity of any bird or other creatures near landing area, and a combination thereof. The controller 403 is configured to receive signals corresponding to the monitoring of the landing area by the one or more image capturing units 401 and the one or more sensor units 402. Further, the controller 403 is configured to calculate an inclination angle of the landing area based on the received signals from the one or more image capturing units 401 and the one or more sensor units 402. Also, the controller 403 is configured to generate control signals to be transmitted to the two or more servo systems 404 for adjusting an angle of the luggage carrier 102, 201 with respect to the inclination angle of the surface of the landing area. The control signals are generated by the controller 403 based on the calculated inclination angle of the landing area. Each of the two or more servo systems 404 are configured to adjust the angle of the luggage carrier 102, 201 with respect to the inclination angle of the surface of the landing area based on the received control signals from the controller 403. The servo system 404 is an electromagnetic device for converting electricity into precise controlled motion using a feedback mechanism. Further, the servo system 404 can be used to generate linear or circular motion. The two or more servo systems 404 comprise a feedback device, a motor, and a control unit. The control unit of the servo systems 404 is used to compare a desired angular adjustment of the luggage carriage 102, 201 with an actual angular adjustment to calculate an error signal. The control unit transmits the calculated error signal to the feedback device for controlling the motor. The servo systems 404 provide high accuracy speed, precision, that makes them ideal for applications requiring precise control and positioning.
In an embodiment of the present disclosure, the controller 403 may include a hardware processor (e.g., a central processing unit (CPU), a graphics processing unit (GPU), a hardware processor core, or any combination thereof), a main memory and a static memory, some or all of which may communicate with each other via an interlink (e.g., bus). The controller 403 may additionally include a storage device (e.g., drive unit), a network interface device. The controller 403 may include an inbuilt Analog-to-Digital Convertor (ADC) and an output controller 403, such as a serial (e.g., universal serial bus (USB), parallel, or other wired or wireless (e.g., infrared (IR), near field communication (NFC), Bluetooth, Wi-Fi or like) connection. The storage device may include a machine-readable medium that is non-transitory on which is stored one or more sets of data structures or instructions (e.g., software) embodying or utilized by any one or more of the techniques or functions described herein. The instructions may also reside, completely or at least partially, within the main memory, within static memory, or within the hardware processor during execution thereof by the controller 403. The machine-readable medium may include any medium that is capable of storing, encoding, or carrying instructions for execution by the controller 403 and that cause the controller 403 to perform any one or more of the tasks of the present disclosure, for example, calculation of the inclination angle of the landing area, based on the signals from the one or more image capturing units 401 and/or one or more sensor units 402. For example, the machine-readable medium comprises Machine-Learning (ML) algorithms and Artificial Intelligence (AI) algorithms that can be used to perform the tasks, for example, centering the drone in the landing area, calculation of the inclination angle of the landing area, based on the signals from the one or more image capturing units 401 and/or the one or more sensor units 402. Non-limiting machine-readable medium examples may include solid-state memories, and optical and magnetic media. Specific examples of machine-readable medium may include: non-volatile memory, such as semiconductor memory devices (e.g., Electrically Programmable Read-Only Memory (EPROM), Electrically Erasable Programmable Read-Only Memory (EEPROM)) and flash memory devices, magnetic disks, such as internal hard disks and removable disks; magneto-optical disks; and CD-ROM and DVD-ROM disks.
In an embodiment of the present disclosure, a degree of change in the angle of the luggage carrier 102, 201 depends on specific attributes of the control signal generated by the controller 403. In an embodiment, the specific attributes of the control signal are an amplitude, a frequency, a duty cycle and the like. The two or more servo systems 404 adjusts the angle of the luggage carrier 102, 201 based on the specific attributes of the control signal for producing different degrees of adjustment to the angle of the luggage carrier 102, 201. In an embodiment, the angle of the luggage carrier 102, 201 is measured as an angle between the bottom surface of the luggage carrier 102, 201 facing the landing area and ground.
Fig. 5 illustrates an exemplary flow chart of a method 500 for landing drones on the inclined surfaces of the landing area in accordance with the present disclosure. The method 500 is being performed by the system 100 comprising the frame of the drone comprising the top surface and the two or more landing gears 101, the one or more attachment means 103, 300, the two or more servo systems 104, 404, the controller 403, the luggage carrier 102, 201, the one or more image capturing units 401 and the one or more sensor units 402. The controller 403 is communicatively coupled to the one or more image capturing units 401, the one or more sensor units 402 and the two or more servo systems 104, 404 via the communication network.
In step 502, the method 500 comprises monitoring by the one or more image capturing units 401 and the one or more sensor units 402, the landing area for the landing of the drone. The one or more image capturing units 401 are configured to capture the images of the landing area for monitoring the landing area for the drone’s landing. Further, the one or more sensor units 402 are configured to measure the one or more parameters of the landing area. The one or more parameters may comprise an inclination angle of the landing area, total landing area, a position of the landing area, nearby surroundings of the landing area, vicinity of any bird or other creatures near landing area, and a combination thereof.
In step 504, the method 500 involves transmitting signals corresponding to the monitoring of the landing area by the one or more image capturing units 401 and the one or more sensor units 402 to the controller 403. The one or more image capturing units 401 and the one or more sensor units 402 transmit signals corresponding to the captured image and the measured one or more parameters respectively corresponding to the landing area of the drone to the controller 403.
In an embodiment of the present disclosure, the signals corresponding to the monitoring of the landing area comprise the position of the landing area and the inclination of the landing area.
In step 506, the method 500 comprises adjusting by the controller 403, the drone to a center of the landing area based on the received signals of the monitoring of the landing area. The controller 403 adjusts the position of the drone corresponding to the landing area for proper landing of the drone over the landing area.
In step 508, the method 500 further comprises calculating by the controller 403, the inclination angle of the landing area based on the received signals from the one or more image capturing units 401 and the one or more sensor units 402. The inclination of the landing area is calculated for proper placement of the drone over the landing area without any slipping. The slipping of the drone from the landing area may further cause damage to the drone or may be disastrous to the surroundings as well.
In an embodiment, the surface of the landing area may have variable degrees of inclination with respect to the ground. In an embodiment, the surface of the landing area is having a single degree of inclination with respect to the ground. In another embodiment, the surface of the landing area may be parallel with respect to the ground.
In step 510, the method 500 includes determining by the controller 403, the control signals for adjusting the angle of the luggage carrier 102, 201 corresponding to the inclination angle of the landing area. Based on the inclination of the landing area, the controller 403 determines control signals for adjusting the angle of the luggage carrier 102, 201 that may further allow for proper landing of the drone over the landing area.
In step 512, the method 500 comprises transmitting by the controller 403, the determined control signals to the two or more servo systems 104, 404. Each of the two or more servo systems 104, 404 are configured to receive the control signals from the controller 403 corresponding to the inclination of the luggage carrier 102, 201 based on the inclination of the landing area.
In step 514, the method 500 involves adjusting by the two or more servo systems 104, 404, the luggage carrier 102, 201 based on the determined control signals over the landing area. Further, the two or more servo systems 104, 404 are configured to adjust the angle of the luggage carrier 102, 201 to be suitable for landing over the surface of the landing area. The angle of the luggage carrier 102, 201 is adjusted by each of the two or more servo systems 104, 404 based on the received control signals. After landing of the drone over the drone area, propellors motors of the drone are turned off. Furthermore, a gripping of the drone over the inclined surfaces are provided by anti-vibration rubber pads, in addition to a gripping force provided by the two or more servo systems 104, 404. In an embodiment, the anti-vibration rubber pads are coupled at the bottom of the luggage carrier 102, 201.
In an embodiment of the present disclosure, an application of the system 100 is to provide water-less cleaning of solar panels. The system 100 is configured to use brushes or other means for cleaning of the solar panels after landing over the solar panels.
Accordingly, the present invention is advantageous over the prior existing technologies for landing of the drone over the inclined surfaces in terms of proper landing of the drone over the landing area without slipping. One of the applications of the present invention is to provide proper cleaning of solar panels without using water by providing landing of the drone over the surface of the panels. Conventional systems are unable to provide landing of the drones over inclined surfaces. Therefore, the prior existing technologies were using drones that sprinkles water to the solar panels from a distance for cleaning of the solar panels. The drawbacks associated with such cleanings is excess use of water during cleaning. Also, the existing systems use sprinkling water from distance as the only way to clean the panels that results in less efficient cleaning as well as wastage of water. Also, the drones have to be on flight mode throughout the cleaning process for sprinkling water over the panels. The present invention is more efficient than the prior existing technologies in terms of cleaning of solar panels via providing landing over the inclined panels. In fact, the present invention provides water-less cleaning via the use of brushes or other means to clean the surface of the solar panels. Hence, the present invention provides an efficient, less complex, and water-less cleaning of the solar panels via providing landing of the drone over inclined surfaces. Moreover, the system 100 of the present invention is also advantageous for all the related tasks that includes landing of the drones over inclined surfaces.
Although the present invention has been described in terms of certain preferred embodiments, various features of separate embodiments can be combined to form additional embodiments not expressly described. Moreover, other embodiments apparent to those of ordinary skill in the art after reading this disclosure are also within the scope of this invention. Furthermore, not all the features, aspects and advantages are necessarily required to practice the present invention. Thus, while the above detailed description has shown, described, and pointed out novel features of the invention as applied to various embodiments, it will be understood that various omissions, substitutions, and changes in the form and details of the apparatus or process illustrated may be made by those of ordinary skill in the technology without departing from the spirit of the invention. The inventions may be embodied in other specific forms not explicitly described herein. The embodiments described above are to be considered in all respects as illustrative only and not restrictive in any manner.
,CLAIMS:1. A system (100) for landing drones on inclined surfaces, the system (100) comprises:
a frame of the drone, the frame comprising a top surface coupled to a first end of the two or more landing gears (101);
one or more attachment means (103, 300) comprise a cavity (301) at a first portion of the one or more attachment means (103, 300), the cavity (301) is configured to couple a second end of the two or more landing gears (101);
two or more servo systems (104, 404) configured to be coupled within a loop (303) at a second portion of the one or more attachment means (103, 300);
a controller (403) configured to be coupled to the frame of the drone; and
a luggage carrier (102, 201) configured to be coupled to the one or more attachment means (103, 300) and the two or more servo systems (104, 404) via one or more upper holes (202) and one or more lower holes (203) respectively, the luggage carrier (102, 201) comprises one or more image capturing units (401) and the one or more sensor units (402) coupled to an outer surface of the luggage carrier (102, 201), wherein the controller (403) is configured to be communicatively coupled via a communication network to the one or more image capturing units (401), the one or more sensor units (402) and the two or more servo systems (104, 404).
2. The system (100) as claimed in claim 1, wherein the controller (403) is configured to:
receive signals corresponding to monitoring of the landing area via the one or more image capturing units (401) and the one or more sensor units (402);
calculate an inclination angle of the landing area based on the received signals;
generate a control signal corresponding to the calculated inclination angle of the landing area; and
transmit the generated control signal to each of the two or more servo systems (104, 404).
3. The system (100) as claimed in claim 2, wherein the two or more servo systems (104, 404) are configured to adjust an angle of the luggage carrier (102, 201) with respect to the inclination angle of the landing area based on the received control signal from the controller (403).
4. The system (100) as claimed in claim 1, wherein the one or more attachment means (103, 300) comprise one or more protrusions (302) at an upper end of the first portion for coupling with the one or more upper holes (202) of the luggage carrier (102, 201), the one or more protrusions (302) are L-shaped.
5. The system (100) as claimed in claim 1, wherein the luggage carrier (102, 201) is either an enclosed case or an open case.
6. The system (100) as claimed in claim 1, wherein the two or more servo systems (104, 404) comprise a control unit, a feedback device, and a motor.
7. The system (100) as claimed in claim 1, wherein the one or more upper holes (202) comprise c-shaped holes and the one or more lower holes (203) comprise a series of holes.
8. A method (500) for landing drones on inclined surfaces, the method (500) is configured to be performed on a system (100) comprising a frame of the drone comprising a top surface and two or more landing gears (101), one or more attachment means (103, 300), two or more servo systems (104, 404), a controller (403), a luggage carrier (102, 201), one or more image capturing units (401) and one or more sensor units (402), wherein the controller (403) is communicatively coupled to the one or more image capturing units (401), the one or more sensor units (402), and the two or more servo systems (104, 404) via a communication network, the method (500) comprises:
monitoring, by the one or more image capturing units (401) and the one or more sensor units (402) a landing area for the landing of the drone;
transmitting, by the one or more image capturing units (401) and the one or more sensor units (402), signals corresponding to the monitoring of the landing area to the controller (403);
adjusting, by the controller (403), the drone to a centre of the landing area corresponding to the received signals;
calculating, by the controller (403), an inclination angle of the landing area corresponding to the received signals;
determining, by the controller (403), control signals for adjusting an angle of the luggage carrier (102, 201) corresponding to the inclination angle of the landing area;
transmitting, by the controller (403), the determined control signals to the two or more servo systems (104, 404); and
adjusting, by the two or more servo systems, the luggage carrier (102, 201) based on the determined control signals over the landing area.
9. The method (500) as claimed in claim 8, wherein the one or more attachment means (103, 300) comprise one or more protrusions (302), a cavity (301), and a loop (303) for coupling the luggage carrier (102, 201), a second end of the two or more landing gears (101), and the two or more servo systems (104, 404) respectively.
10. The method (500) as claimed in claim 9, wherein the one or more protrusions (302) at an upper end of a first portion of the one or more attachment means (103, 300) are configured to couple to one or more upper holes (202) of the luggage carrier (102, 201), the one or more protrusions (302) are L-shaped.
11. The method (500) as claimed in claim 9, wherein the one or more attachment means (103, 300) comprise a first portion and a second portion, wherein the first portion comprises the cavity (301) and the one or more protrusions (302), and the second portion comprises the loop (303).
12. The method (500) as claimed in claim 8, wherein the luggage carrier (102, 201) is configured to couple to the one or more attachment means (103, 300) and the two or more servo systems (104, 404) via one or more upper holes (202) and one or more lower holes (203) respectively.
13. The method (500) as claimed in claim 12, wherein the one or more upper holes (202) comprise c-shaped holes and the one or more lower holes (203) comprise a series of holes.
14. The method (500) as claimed in claim 8, wherein the two or more servo systems (104, 404) comprise a control unit, a feedback device, and a motor.