UNMANNED AERIAL VEHICLE AND METHOD FOR PROTECTING PAYLOAD

Abstract

Disclosed is an an unmanned aerial vehicle. The unmanned aerial vehicle includes a payload arranged in a container, said container being equipped with a parachute; means for attaching the payload to the unmanned aerial vehicle and means for ejecting the payload from the unmanned aerial vehicle. The means for ejecting the payload from the unmanned aerial vehicle is communicatively coupled with the payload and configured to be actioned upon an emergency situation.

Description

This application claims priority to and the benefit of prior filed provisional patent application No. US 61/972,519, the disclosure of which is incorporated herein by reference in its entirety.

TECHNICAL FIELD

The present disclosure relates generally to an unmanned aerial vehicle; and more specifically, to a method for protecting a payload carried on an unmanned aerial vehicle.

BACKGROUND

An unmanned flying device or vehicle is an aircraft without an on-board human pilot. Unmanned flying devices are known and identified by different names or titles including Unmanned Aerial Vehicles (hereinafter UAVs), Remotely Piloted Aircraft Systems (RPAS), drones, Remotely Piloted Vehicles (RPVs) and the like. These UAVs may be classified and categorized in terms of range or altitude, shapes, sizes, roles and the like. There are multiple civilian purposes and roles for UAVs such as survey, inspection, search and rescue, security, and surveillance. Moreover, the UAV has various components to perform the above mentioned goals.

Typically, the UAV has components which include an airframe, a propulsion system, a flight control system, a navigation system, a sensor system, a communication system, a power source and the like. The sensor system among such components provides different types of payloads carried on the UAV, for example, the payloads can include electro-optical sensing systems/scanners, infra-red systems, radars, LiDAR (light detection and ranging) unit(s), environmental sensors and similar components. Additionally, such payload may be associated with other components, such as a processor for recording and analyzing measured data, means for a wireless communication, a separate power source and the like. Therefore, the payload of the UAV constitutes the most important (i.e. structurally, functionally and monetary) part of the UAV. For example, the payload can provide various types of data to the UAV to decide the operation of the UAV. Further, the components (such as the electro-optical sensing systems/scanners, infra-red systems, radars, LiDAR unit, environmental sensors) of the payload are very expensive. Moreover, a weight associated with such payload can range in tens, hundreds or thousands of kilograms, which is an important structural aspect of the UAV.

In operation, the UAVs can be either remotely operated from a base station or can have autonomous control to control operation (such as flight) thereof. The UAVs are generally subjected to various situations and are required to operate depending upon such situations. For example, the UAVs may operate in a normal flying mode, a safe landing mode, an emergency landing mode and the like. The normal flying mode and the safe landing mode are normal and convenient; however, the problem lies in the emergency landing mode. The emergency landing mode corresponds to landing in error situations when one or more functionalities of the UAV partially or completely break down or interrupt. In such situations, landing becomes difficult and risky. For example, the UAV may crash on the ground, hit an object in the air or land on some undesired location.

Therefore, in such emergency situations, protecting the payload of the UAV becomes a matter of highest priority due to the structural, functional and monetary aspects associated with the payload. For example, the damage caused by uncontrolled landing of the UAV can be extreme due to the considerable weight of the payload, which can be tens, hundreds or thousands of kilograms. Further, the arbitrary location of the emergency landing may lead to a loss of payload and/or loss of important data. Moreover, the uncontrolled landing can either partially or completely damage the payload and may lead to heavy financial loss.

Therefore, in light of the foregoing discussion, there exists a need to overcome the aforementioned drawbacks of protecting a payload carried on an unmanned aerial vehicle.

SUMMARY

The present disclosure seeks to provide an unmanned aerial vehicle configured to protect a payload carried thereon.

The present disclosure also seeks to provide a method for protecting a payload carried on an unmanned aerial vehicle.

In one aspect, an embodiment of the present disclosure provides an unmanned aerial vehicle. The unmanned aerial vehicle comprises a payload arranged in a container, said container being equipped with a parachute, means for attaching the payload to the unmanned aerial vehicle and means for ejecting the payload from the unmanned aerial vehicle. The means for ejecting the payload from the unmanned aerial vehicle are communicatively coupled with the payload and configured to be actioned upon an emergency situation.

In another aspect, an embodiment of the present disclosure provides a method for protecting a payload carried on an unmanned aerial vehicle, which unmanned aerial vehicle comprises the payload arranged in a container, said container being equipped with a parachute, means for attaching the payload to the unmanned aerial vehicle, and means for ejecting the payload from the unmanned aerial vehicle, the means for ejecting the payload from the unmanned aerial vehicle being communicatively coupled with the payload. The method comprises detecting an emergency situation and actioning the means for ejecting the payload.

Embodiments of the present disclosure substantially eliminate or at least partially address the aforementioned problems in the prior art, and provide an unmanned aerial vehicle configured to protect a payload and a method for protecting a payload.

Additional aspects, advantages, features and objects of the present disclosure would be made apparent from the drawings and the detailed description of the illustrative embodiments construed in conjunction with the appended claims that follow.

It will be appreciated that features of the present disclosure are susceptible to being combined in various combinations without departing from the scope of the present disclosure as defined by the appended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

The summary above, as well as the following detailed description of illustrative embodiments, is better understood when read in conjunction with the appended drawings. For the purpose of illustrating the present disclosure, exemplary constructions of the disclosure are shown in the drawings. However, the present disclosure is not limited to specific methods and instrumentalities disclosed herein. Moreover, those in the art will understand that the drawings are not to scale. Wherever possible, like elements have been indicated by identical numbers.

Embodiments of the present disclosure will now be described, by way of example only, with reference to the following diagrams wherein:

FIG. 1 is a block diagram illustrating an unmanned aircraft system, in accordance with various embodiments of the present disclosure;

FIG. 2 is a block diagram illustrating an unmanned aerial vehicle, in accordance with various embodiments of the present disclosure;

FIG. 3 is a block diagram illustrating interaction between various components of the unmanned aerial vehicle and an operations base in the unmanned aircraft system, in accordance with various embodiments of the present disclosure;

FIG. 4 is a block diagram of a payload illustrating various components thereof, in accordance with an embodiment of the present disclosure;

FIG. 5 is a schematic illustration of the payload depicting various components thereof, in accordance with an embodiment of the present disclosure;

FIG. 6 is a block diagram of means for ejecting, the payload from the unmanned aerial vehicle, illustrating various components thereof, in accordance with an embodiment of the present disclosure;

FIG. 7 is a block diagram of a diagnostic module, of the unmanned aerial vehicle, illustrating various components thereof, in accordance with an embodiment of the present disclosure;

FIG. 8 is a block diagram illustrating interaction between various components of the unmanned aerial vehicle to attain various operation modes, in accordance with various embodiments of the present disclosure; and

FIG. 9 is an illustration of steps of a method for protecting a payload carried on an unmanned aerial vehicle, in accordance with an embodiment of the present disclosure.

In the accompanying drawings, an underlined number is employed to represent an item over which the underlined number is positioned or an item to which the underlined number is adjacent. A non-underlined number relates to an item identified by a line linking the non-underlined number to the item. When a number is non-underlined and accompanied by an associated arrow, the non-underlined number is used to identify a general item at which the arrow is pointing.

DETAILED DESCRIPTION OF EMBODIMENTS

The following detailed description illustrates embodiments of the present disclosure and ways in which they can be implemented. Although some modes of carrying out the present disclosure have been disclosed, those skilled in the art would recognize that other embodiments for carrying out or practicing the present disclosure are also possible.

In one aspect, an embodiment of the present disclosure provides an unmanned aerial vehicle. The unmanned aerial vehicle comprising a payload arranged in a container, said container being equipped with a parachute, means for attaching the payload to the unmanned aerial vehicle and means for ejecting the payload from the unmanned aerial vehicle. The means for ejecting the payload from the unmanned aerial vehicle are communicatively coupled with the payload and configured to be actioned upon an emergency situation.

In another aspect, an embodiment of the present disclosure provides a method for protecting a payload carried on an unmanned aerial vehicle, which unmanned aerial vehicle comprises the payload arranged in a container, said container being equipped with a parachute, means for attaching the payload to the unmanned aerial vehicle, and means for ejecting the payload from the unmanned aerial vehicle, the means for ejecting the payload from the unmanned aerial vehicle being communicatively coupled with the payload. The method comprises detecting an emergency situation and actioning the means for ejecting the payload.

In an embodiment, the present disclosure broadly relates to an Unmanned Aerial System (hereinafter UAS) having at least one UAV and an operations base. The UAS also includes components such as data links, displays, controls, remote human operators and the like. The UAV and the operations base may be communicably coupled to each other using the data link, which may include but are not limited to wireless links, satellite links, radio links and the like.

In an embodiment, the UAV is controlled autonomously based on pre-programmed route and/or mission data. For example, an on-board computing system having pre-programmed instructions (such as route information or other mission data) controls the UAV. Alternatively, the UAV may be controlled by a remote operator present on the operations base. For example, instructions related to the route and other parameters associated with the UAV are controlled by the remote operator present on the operations base.

In an embodiment, the UAV may include but is not be limited to drones, helicopters, airplanes, and balloons. The UAV flies over a geographical area and performs a specific mission such as collecting data related to the geographical area. For example, the UAV may be used for monitoring forestry/vegetation in the vicinity of power lines. Further, the UAV may include following flying parameters i.e. an altitude of 50-100 meters and a speed of 20-150 kilometre/hour.

The UAV of the present disclosure primarily includes the payload, means for attaching the payload to the UAV and means for ejecting the payload from the UAV.

According to an embodiment, the payload comprises at least one of one or more sensors, one or more cameras, a light detection and ranging device, a radar, a processor for recording and analyzing measured data, means for a wireless connection to an operations base, and a power source. The sensor can be for example temperature sensors, pressure sensors, inertial measurement unit (IMU) and the like. The processor can be for example a computing device.

According to another embodiment, the UAV can include other components such as a propulsion system, a flight control system, a navigation system, a sensor system, a communication system, a power system and an airframe, although one or more of these components may also be included in the payload, depending on the embodiment. The propulsion system includes an engine and a means to propel the engine to assist in acceleration of the UAV. The flight control system enables controlling operation modes of the UAV. The navigation system provides location data and controls the heading direction of the UAV. The sensor system collects various types of data including environmental conditions and the like. The communication system communicates with the UAV and the operations base. The power system supplies power to operate the various components of the UAV. The airframe refers to the physical structure including wings, actuators, body and the like.

In an embodiment, the payload provides various types of data to the UAV to decide the operation of the UAV. Specifically, the flight control system of the UAV may include a diagnostic module communicatively coupled with the payload. The diagnostic module is configured to initiate an operation mode of the unmanned aerial vehicle, which operation mode is selected from the group consisting of a first mode, wherein said first mode is a normal operation mode configured to be used when no errors are detected; a second mode, wherein said second mode is a safe landing mode configured to be initiated when one or more non-critical components of the unmanned aerial vehicle are in a non-responsive mode or not working according to pre-defined conditions; and a third mode, wherein said third mode is an emergency landing mode configured to be initiated when one or more critical components of the unmanned aerial vehicle are in non-responsive mode or not working according to pre-defined conditions. In this embodiment, the second mode is configured to override the first mode and the third mode is configured to override both the first mode and the second mode.

The diagnostic module, when present, is thus communicably coupled to the payload for receiving data associated with various components of the payload. Therefore, the diagnostic module is configured to decide an operation mode for the UAV based on the data provided by the payload.

In an embodiment, the diagnostic module collects the data from the communication system, the propulsion system and the power system (such as power failure signal/loss of power indication/low voltage indicator) of the UAV. For example, the communication system provides periodic signals to refresh time in the diagnostic module. Accordingly, the propulsion system provides the status of the engine and fuel (or battery or fuel cell in case of an electric UAV) in the propulsion system.

Further, the diagnostic module also collects data from the payload, particularly processed and analyzed data collected by the sensor system. For example, the sensor system provides operational status of devices including video camera, audio devices, sensors and the like.

In an embodiment, the diagnostic module is powered preferably through an independent power system. Specifically, power supplied to the diagnostics module through the independent power system is separated from the main power system of the UAV to ensure uninterrupted powering to the diagnostic module. Alternatively, the diagnostic module can be powered by the power system of the UAV.

The diagnostic module initiates actions corresponding to the different modes of operation of the UAV following the collection and analysis of data. The diagnostic module selects the corresponding mode of operation of the UAV on the basis of the data collected from the different components of the UAV and the payload.

In one embodiment, the operation mode is associated with operating the UAV in a first mode, i.e. a normal operations mode when no errors are detected. In the normal flying mode, the UAV flies in the air under normal control over the navigation to direct the UAV.

In another embodiment, the operation mode is associated with operating the UAV in a second mode, i.e. a safe landing mode when one or more non-critical components of the UAV are in a non-responsive mode or not working according to pre-defined conditions. The safe landing mode corresponds to some errors interrupting the normal operations of the UAV. Such errors do not prevent the UAV to stay in air but makes the operation unsafe. Examples of errors in non-critical components include but may not be limited to loss of video link or remote control links, or the presence of electronic counter-measures, or a failure of one instance of redundant components.

In one embodiment, the safe landing mode includes scanning an environment of the UAV with at least one sensor, ranking possible landing sites, selecting a landing site and landing. Further, the scanning an environment of the UAV further includes using information from at least one of a map and a memory. For example, in the safe landing mode, sensors such as LiDAR and the like are used to find a flat and open area nearby to land the UAV safely. Generally, the criterion for selecting an open area is to find an area with no moving objects to avoid persons, vehicles and the like. In addition, the diagnostic module can be configured to include a list of forbidden landing areas for landing the UAV.

In yet another embodiment, the operation mode is associated with operating the UAV in a third mode, i.e. an emergency landing mode when one or more critical components of the UAV are in non-responsive mode or not working according to pre-defined conditions. Further, the emergency landing mode includes but may not be limited to deploying of one of parachutes, airbags, shields (modifying the contraction of the UAV) and self-destruction (either breaking the UAV into small components or destroy the UAV).

According to an embodiment, the second mode is configured to override the first mode, and the third mode is configured to override both the first and second modes. Specifically, the second mode and the third mode are operable in erroneous situations. Therefore, the second mode overrides the first mode (i.e. the normal flying mode). However, the third mode being more critical compared to the second mode, overrides the first mode (i.e. the normal flying procedure) and the second mode (i.e. the safe landing mode) both.

In an embodiment, the diagnostic module comprises timers, watch dogs, generic inputs/outputs, a controller and a memory unit. The timers measure time between the communication events. The watch dogs analyze whether all the components of the diagnostic module provide signals in a pre-determined pattern. The generic inputs/outputs collect information including battery level of the diagnostic module and the power system. The controller programs rules for each type of input situation. Moreover, the controller programs response for every possible error scenario. Further, the controller forcefully switches the mode of operation of the UAV from the first mode to the second mode or the third mode on the basis of satisfying certain predefined conditions. The look-up table holds the programmed rules and the various inputs received from the other components of the diagnostic module.

The diagnostic module is communicatively coupled with the payload. Further, the means for ejecting the payload from the UAV is communicatively coupled with the payload and configured to be actioned upon an emergency situation. Therefore, in case of the emergency situation, particularly when the UAV is operated in the third mode (i.e. emergency landing mode as selected by the diagnostic module) the means for ejecting the payload comes into action.

In an embodiment, the means for ejecting the payload from the UAV comprises a processor, a power source and means for collecting and storing data. The processor is configured to monitor and analyze information received from the payload. Therefore, upon detection of the emergency situation the means for ejecting the payload comes into action.

In an embodiment, the emergency situation includes the UAV encountering any critical mechanical failure, electrical failure or both. Additionally, the emergency situation includes the UAV being subjected to strong unexpected wind making the UAV fall or lose its balance, the UAV flying towards an object, an external object coming towards UAV and the like. In such situations, the data associated with the communication system, the propulsion system, the power system and the sensor system becomes critical (i.e. beyond safe margins) causing the emergency situation. For example, the emergency situation is indicated by detection of at least one of an abnormal flying angle, a failure of automation, an acceleration beyond a threshold, a malfunction of a pilot system, an immediate crash and the like.

According to an embodiment, the emergency situation can be further categorised into following categories, i.e. a non-immediate but severe category, an immediate and severe category and a recoverable category. The non-immediate but severe category allows UAV to manoeuvre for a limited time before payload ejection. The immediate and severe category requires immediate payload ejection. The recoverable category allows UAV to manoeuvre and attempt safe landing without ejection of the payload. For example, there could be a situation where the UAV can still manage to land safely when operating in the third mode, i.e. emergency landing mode, in such situation the means for ejecting the payload may not be required to come into action for releasing the payload from the UAV as the entire UAV can land safely. It is to be understood that in such situation the flight parameters of the UAV or the sensor values do not excess critical limit.

In the present disclosure, the means for ejecting the payload comes into action for the ejection of the payload. Specifically, in the emergency situation the means for ejecting the payload releases the payload carried on the UAV such that the payload can land safely, i.e. to land in a known place without or least physical and functional damage.

The payload is arranged in a container. The container for the payload acts as a safety cover for protecting the payload from any physical and functional damage. For example, the container may be made of substantially hard and light material, such as hard plastic, hard rubber, light weight metals or any combination thereof, providing a required structural strength to the container. Further, in an embodiment, the container may be waterproof and optionally equipped with a floating device for protecting the payload from water.

Further, the payload is attached to the unmanned aerial vehicle by the means for attaching. Specifically, the payload is detachably coupled to the UAV using the means for attaching such that in case of emergency situation, the payload can be detached from the UAV. For example, the container for the payload may be detachably coupled to a body or airframe of the UAV. In an embodiment, the means for attaching the payload includes at least one of a cage and at least one rail. The cage may be arranged on the container for the payload and the rail may be arranged on the body or airframe of the UAV, or vice-versa.

As mentioned above, the means for ejecting the payload comes into action in the emergency situation. Specifically, in the emergency situation the means for ejecting comes into action for decoupling the means for attaching between the UAV and the payload or alternatively, the means for ejecting are strong enough to break the means for attaching, without a need to separately detaching the means. In an embodiment, the means for ejecting the payload from the UAV is arranged to be actioned by a mechanism selected from the group consisting of electrical current through servo detachment mechanism, pre-stressed spring, pressurized gas and combinations thereof. Specifically, the processor of the means for ejecting may instruct the mechanism to decouple the means for attaching (i.e. the rail and cage arrangement).

In one embodiment, the payload and the UAV may have a wired connection (for example for data exchange) in addition to the detachable coupling provided by the means for attaching. Therefore, in such situation, when the payload is ejected from the UAV a weight of the payload is sufficient to break such wired connection for completely releasing the payload from the UAV.

Once, the payload is ejected or released from the UAV, the parachute equipped in the container comes into action to attain a deployed position. The deployment of the parachute is controlled by the processor of the means for ejecting the payload.

In an embodiment, the parachute is arranged to be deployed after ejection with a delay of time ‘t’. The delay of time ‘t’ is provided for avoiding tangling of the deployed parachute with any part of the UAV, such as the wings or blades of the UAV. Further, the delay of time ‘t’ can be controlled by the processor of the means for ejecting the payload. For example, the time ‘t’ is set according to flight parameters at the time of ejection, i.e. the time ‘t’ may be associated for example with an altitude of the payload. In an example, when a safe altitude of about 40-50 meters is attained the parachute may be deployed. Otherwise, the time ‘t’ may be associated with a predetermined fixed time that is about, 0.5 to 2 seconds, after ejection of the payload from the UAV.

In one embodiment, the processor of the means for ejecting the payload from the UAV is arranged within the container of the payload. The means for collecting and storing data of the means for ejecting the payload accordingly collects data from the payload, and thereafter the processor of the means for ejecting the payload processes such data to instruct decoupling of the means for attaching the payload and the deployment of the parachute.

In an embodiment, the processor of the means for ejecting the payload from the UAV is configured to perform other functions apart from decoupling the means for attaching the payload and the deployment of the parachute after the ejection of the payload from the UAV. For example, the processor of the means for ejecting the payload from the UAV is configured to perform at least one of switch off one or more devices of the payload, download and save flight data into the payload, transmit location data into an operations base. Such functions help in protecting important data collected or stored in the payload and help in easily locating the ejected payload from the UAV.

In addition to above, the UAV of the present disclosure is also configured to protect itself after ejection of the payload. As mentioned above, the emergency landing mode includes deploying of one of parachutes, airbags or shields (associated with the UAV) for the protection thereof.

The present disclosure provides an unmanned aerial vehicle and a method for protecting a payload carried on the UAV. Specifically, when the UAV is subjected to an emergency situation, the payload is released from the UAV such that the payload can land safely, i.e. the payload can land in a known place without any or with minimal structural and functional damage. Further, the payload being the most important part of the UAV, the present disclosure provides improved structural, functional and monetary aspects to the UAV. For example, the present disclosure enables safe landing of the payload, i.e. by deploying the parachute, and thereby avoiding the damage which may be caused by uncontrolled landing and the considerable weight of the payload. Further, the payload can be conveniently retrieved from an emergency landing site, which avoids loss of payload and/or loss of important data collected or stored in the payload. Moreover, the present disclosure provides sufficient safety measure, such as rigid and waterproof container and floating device, for avoiding heavy financial loss which may be caused due to uncontrolled landing of the payload.

DETAILED DESCRIPTION OF THE DRAWINGS

Referring to FIG. 1, illustrated is a block diagram of an unmanned aerial system 100, in accordance with various embodiments of the present disclosure. The UAS 100 includes at least one unmanned aerial vehicle (UAV), such as an UAV 102 and an UAV 104, and an operations base 106. The operations base 106 is communicably coupled to the UAVs 102, 104. Further, the UAVs 102, 104 are also communicably coupled to each other.

Referring now to FIG. 2, illustrated is a block diagram of an unmanned aerial vehicle, such as the UAV 102, in accordance with various embodiments of the present disclosure. The UAV 102 includes a payload 200. The payload 200 is attached to the UAV 102 by a means for attaching 202. The UAV 102 also includes means for ejecting 204. The means for ejecting 204 is communicatively coupled with the payload 200 and configured to be actioned upon an emergency situation. Specifically, the means for ejecting 204 is operatively coupled to the means for attaching 202 and optionally configured to open (decouple) the means for attaching 202 for ejecting or releasing the payload 200 from the UAV 102 during the emergency situation.

Referring now to FIG. 3, it is a block illustrating interaction between various components of the UAV 102 and the operations base 106 in the unmanned aircraft system, in accordance with various embodiments of the present disclosure. As shown, a remote operator 300 is present at the operations base 106 for sending instructions to control the UAV 102. The UAV 102 further includes various components, such as, a propulsion system 302, a flight control system 304, a navigation system 306, a communication system 308, a power system 310 and an airframe 312. Moreover, the flight control system 304 of the UAV 102 includes a diagnostic module 314 to decide various operation modes to operate the UAV 102 in various situations. The diagnostic module 314 of the flight control system 304 is communicably coupled to the payload 200 for receiving data associated with various components of the payload 200. According to another embodiment, some of the above listed components are part of the payload.

Referring now to FIG. 4, illustrated is block diagram of the payload 200 showing various components thereof, in accordance with an embodiment of the present disclosure. The payload 200 includes a sensor system 402, a processor 404 for recording and analyzing measured data of the sensor system 402, means for a wireless connection 406 for the operations base 106 (shown in FIG. 3) and a power source 408 (which is a separate power source from the power system 310) for providing required electrical power to the sensor system 402, the processor 404 and means for the wireless connection 406. As shown, the sensor system 402 includes at least one or more sensors 412, one or more cameras 414, a light detection and ranging device 416 (LiDAR) and a radar 418.

Referring now to FIG. 5, illustrated is a schematic illustration of various components of the payload 200 carried on the UAV 102, in accordance with an embodiment of the present disclosure. As shown, the payload 200 is detachably coupled to the UAV 102 by the means for attaching 202. The payload 200 is arranged in a container 502 for surrounding various components of the payload 200. As shown, the container 502 surrounds the processor 404, one or more cameras such as a front camera 414a and a rear camera 414b, the LiDAR 416 and the radar 418. It is to be understood that, the container 502 also surrounds other components of the payload, such as one or more sensors 412, the means for a wireless connection 406 and the power source 408 (shown in the FIG. 4). The processor 404 is communicably coupled to front and rear cameras 414a, 414b, the LiDAR 416 and the radar 418. The processor 404 is communicably coupled to the UAV 102 by a wired connection 504.

The container 502 is also equipped with a parachute 506. The container 502 is further equipped with a parachute ejector 508 operatively coupled to the parachute 506 for allowing the parachute 506 to attain a deployed state. The parachute ejector 508 is further communicably coupled to the processor 404 of the payload 200 for receiving instruction for operating the parachute ejector 508. Specifically, the payload 200 is communicably coupled to the means for ejecting 204 (as shown in FIG. 3) to instruct the parachute ejector 508 to operate and allow the parachute 506 to attain the deployed state.

Referring now to FIG. 6, illustrated is block diagram of the means for ejecting 204 showing various components thereof, in accordance with an embodiment of the present disclosure. As shown, the means for ejecting 204 includes a processor 602, means for collecting and storing data 604 and a power source 606 (a separate power source). The processor 602 is configured to monitor and analyze information received from the payload 200 and configured to instruct a mechanism to action for opening or decoupling the means for attaching 200 and thereby ejecting or releasing the payload 200 from the UAV 102. Also, the processor 602 is configured to instruct the parachute ejector 508 (shown in FIG. 5) to operate and thereby allow the parachute 506 to attain the deployed state. In an example, the processor 602 of the means for ejecting 204 is arranged within the container 502 (shown in FIG. 5).

Referring now to FIG. 7, illustrated is a block diagram of the diagnostic module 314 showing various components thereof, in accordance with an embodiment of the present disclosure. As shown, the diagnostic module 314 includes timers 702, watch dogs 704, generic inputs/outputs 706, a controller 708 and a memory unit 710.

Referring now to FIG. 8, is a block diagram illustrating interaction between various components of the UAV (not shown) to attain various operation modes, in accordance with various embodiments of the present disclosure. As shown, the diagnostic module 314 in the flight control system 304 collects data from the propulsion system 302, the communication system 308 and the power system 310. The diagnostic module 314 also receives data from the payload 200. Specifically, the diagnostic module 314 is configured to receive processed and analyzed data from the processor 404 (shown in FIG. 4) collected by the sensor system 402. In an example, the diagnostic module 314 is powered through an independent power system 800.

The diagnostic module 314 analyzes the collected data, and initiates operation modes to operate the UAV. As shown, the UAV is configured to operate in three modes: a first mode i.e. a normal flying mode 802, a second mode i.e. a safe landing mode 804 and a third mode i.e. an emergency landing mode 806. Further, depending on the results of analysis of data, the diagnostic module 314 can initiate one of the modes including the normal flying mode 802, the safe landing mode 804 or the emergency landing mode 806.

Referring now to FIG. 9, illustrated are steps of a method 900 for protecting a payload carried on an unmanned aerial vehicle, in accordance with an embodiment of the present disclosure. Specifically, the method 900 illustrates the steps of protecting the payload carried on the UAV, explained in conjunction with the FIGS. 1-8.

At step 902, an emergency situation is detected.

At step 904, means for ejecting a payload is actioned. Specifically, in an emergency situation the payload carried on a UAV is released from the UAV and a parachute arranged inside the payload is deployed (immediately or after a time period, as explained above) for allowing the payload to land safely, i.e. to land in a known place without or least structural and functional damage.

The steps 902 to 904 are only illustrative and other alternatives can also be provided where one or more steps are added, one or more steps are removed, or one or more steps are provided in a different sequence without departing from the scope of the claims herein. For example, the method 900 further includes switching off one or more devices of the payload, downloading and saving flight data into the payload, and transmitting location data into an operations base.

The method 900 also includes operating the UAV in a first mode, i.e. a normal operations mode, when no errors are detected; operating the UAV in a second mode, i.e. a safe landing mode, when one or more non-critical components of the UAV are in a non-responsive mode or not working according to pre-defined conditions; and operating the UAV in a third mode, i.e. an emergency landing mode, when one or more critical components of the UAV are in non-responsive mode or not working according to pre-defined conditions. In which, the second mode overrides the first mode, and the third mode overrides both the first mode and the second mode. Further, the safe landing mode includes scanning an environment of the UAV with at least one sensor, ranking possible landing sites, selecting a landing site and landing. The scanning an environment of the UAV further includes using information from at least one of a map and a memory.

Modifications to embodiments of the present disclosure described in the foregoing are possible without departing from the scope of the present disclosure as defined by the accompanying claims. Expressions such as “including”, “comprising”, “incorporating”, “have”, “is” used to describe and claim the present disclosure are intended to be construed in a non-exclusive manner, namely allowing for items, components or elements not explicitly described also to be present. Reference to the singular is also to be construed to relate to the plural.

Claims

1. An unmanned aerial vehicle comprising:

a payload arranged in a container, said container being equipped with a parachute;

means for attaching the payload to the unmanned aerial vehicle; and

means for ejecting the payload from the unmanned aerial vehicle, the means for ejecting the payload from the unmanned aerial vehicle being communicatively coupled with the payload and configured to be actioned upon an emergency situation.

2. An unmanned aerial vehicle according to claim 1, wherein the means for ejecting the payload from the unmanned aerial vehicle comprises a processor, a power source and means for collecting and storing data, the processor being configured to monitor and analyze information received from the payload.

3. An unmanned aerial vehicle according to claim 2, wherein the processor of the means for ejecting the payload from the unmanned aerial vehicle is further configured to perform at least one of

switch off one or more devices of the payload,

download and save flight data into the payload, and

transmit location data into an operations base.

4. An unmanned aerial vehicle according to claim 2, wherein the processor of the means for ejecting the payload from the unmanned aerial vehicle is arranged within the container of the payload.

5. An unmanned aerial vehicle according to claim 1, wherein the emergency situation is indicated by detection of at least one of

an abnormal flying angle,

a failure of automation,

an acceleration beyond a threshold,

a malfunction of a pilot system, and

an immediate crash.

6. An unmanned aerial vehicle according to claim 1, wherein the payload comprises at least one of

one or more sensors,

one or more cameras,

a light detection and ranging device,

a radar,

a processor for recording and analyzing measured data,

means for a wireless connection to an operations base, and

a power source.

7. An unmanned aerial vehicle according to claim 1, wherein the container is waterproof and optionally equipped with a floating device.

8. An unmanned aerial vehicle according to claim 1, wherein the parachute is arranged to be deployed after ejection with a delay of time t.

9. An unmanned aerial vehicle according to claim 8, wherein the time t is set according to flight parameters at the time of ejection.

10. An unmanned aerial vehicle according to claim 8, wherein the time t is from 0.5 to 2 seconds.

11. An unmanned aerial vehicle according to claim 1, wherein the means for attaching the payload comprises at least one of a cage and at least one rail.

12. An unmanned aerial vehicle according to claim 1, wherein the means for ejecting the payload from the unmanned aerial vehicle are arranged to be actioned by a mechanism selected from the group consisting of electrical current through servo detachment mechanism, pre-stressed spring, pressurized gas and combinations thereof.

13. An unmanned aerial vehicle according to claim 1, further comprising a diagnostic module communicatively coupled with the payload, which diagnostic module is configured to initiate an operation mode of the unmanned aerial vehicle, which operation mode is selected from the group consisting of

a first mode, wherein said first mode is a normal operation mode configured to be used when no errors are detected,

a second mode, wherein said second mode is a safe landing mode configured to be initiated when one or more non-critical components of the unmanned aerial vehicle are in a non-responsive mode or not working according to pre-defined conditions, and

a third mode, wherein said third mode is an emergency landing mode configured to be initiated when one or more critical components of the unmanned aerial vehicle are in non-responsive mode or not working according to pre-defined conditions,

wherein said second mode is configured to override said first mode and said third mode is configured to override both said first mode and said second mode.

14. A method for protecting a payload carried on an unmanned aerial vehicle, which unmanned aerial vehicle comprises

the payload arranged in a container, said container being equipped with a parachute,

means for attaching the payload to the unmanned aerial vehicle, and

means for ejecting the payload from the unmanned aerial vehicle, the means for ejecting the payload from the unmanned aerial vehicle being communicatively coupled with the payload,

the method comprising detecting an emergency situation and actioning the means for ejecting the payload.

15. A method according to claim 14, further comprising at least one of

switching off one or more devices of the payload,

downloading and saving flight data into the payload, and

transmitting location data into an operations base.

16. A method according to claim 15, further comprising

operating said unmanned aerial vehicle in a first mode, wherein said first mode is a normal operations mode, when no errors are detected,

operating said unmanned aerial vehicle in a second mode, wherein said second mode is a safe landing mode, when one or more non-critical components of the unmanned aerial vehicle are in a non-responsive mode or not working according to pre-defined conditions, and

operating said unmanned aerial vehicle in a third mode, wherein said third mode is an emergency landing mode, when one or more critical components of the unmanned aerial vehicle are in non-responsive mode or not working according to pre-defined conditions,

wherein said second mode overrides said first mode and said third mode overrides both said first mode and said second mode.

17. The method according to claim 16, wherein said safe landing mode comprises

scanning an environment of the unmanned aerial vehicle with at least one sensor,

ranking possible landing sites,

selecting a landing site, and

landing.

18. The method according to claim 17, wherein said scanning the environment of the unmanned aerial vehicle further comprises using information from at least one of a map and a memory.