WO2013123944A1

WO2013123944A1 - Unmanned aerial device and system thereof

Info

Publication number: WO2013123944A1
Application number: PCT/DK2013/050042
Authority: WO
Inventors: Carsten Elkjær
Original assignee: Lifedrone Aps
Priority date: 2012-02-20
Filing date: 2013-02-18
Publication date: 2013-08-29

Abstract

The present invention relates to an unmanned aerial device (1) comprising two or more rotors arranged in an aerodynamic body (2) where first and second flight control units (28, 29) are configured to control the flight mode of the UAV. The UAV comprises a module (12, 16) arranged between the rotors for transporting various equipments. The module comprises a chamber (13, 17) for receiving the equipment and a release mechanism (22, 23) for holding the equipment in place until activating. The module may be configured as an interchangeable module which can be exchanged with another module quickly and easily. One or more life saving devices (41) in a compact state may be arranged in the chamber so that the UAV is able to perform an autonomous rescuing operation. This allows the UAV to continue to fly even if it is flipped over and allows it to fly in mean wind speeds up to 20^m/s. The body forms a compact and robust body that is less sensitive to external impacts and may even be used as a rescue unit if needed.

Description

Unmanned aerial device and system thereof

Field of the Invention

The present invention relates to an unmanned aerial device comprising

- a body having an aerodynamic shape, wherein the body comprises an upper side and a lower side;

- two or more rotors coupled to the body, wherein each rotor comprises two or more rotatable rotor blades which is coupled to at least one drive unit by at least one drive shaft; and

- at least one control system electrically coupled to the drive unit and at least sensor unit, wherein the control system is configured to control the flight of the device.

Background of the Invention

Every year a large number of people find themselves in an emergency situation where they are in need of being rescued quickly. Such situations often occur at sea in bad weather or as a result of an accident or collision. Such situations may also occur at land in or after extreme weather situations, e.g. floods, typhoons or hurricanes, or even in the mountains. In order to reduce these people, the rescue services have to respond quickly and effectively in order to locate and rescue these people. However, locating these people - particularly at sea or in remote locations - often requires the use of heli- copters, airplanes or boats. This is often a complex and costly process which involves a large number of rescuing units or other units. Once the person in distress has been located, the rescue service can be guided to the location. However, it may take time for the vessels or vehicles of the rescue service to reach the location. The person in distress may therefore die due to drowning or cooling before the rescue service arrives.

During the recent years, the use of unmanned aerial systems or drones, UAS or UAV, for non-military proposes has increased. Today the police and coast guard use such UAV for monitoring and mapping sites in emergency situations, e.g. floods, or searching for people at sea. Other industrial companies use such UAVs for inspection pur- poses, e.g. of wind turbines, power lines or oil/gas lines. An example of such an UAV is the MD4 model from Microdrone or Aeryon Scout model from Aeryon Labs. These drones have a camera attached to the bottom for supplying images or live images to a display located at the human operator. In order to operate and control the drones, the operator has to see the drones or use the images supplied from the drones. These drones are only able to locate a person in distress they cannot transport any rescue equipment to that person. Furthermore, these drones require the human operator to interact with the drone in order to control the flight of the drone and/or to decide on the appropriate action to be taken based on the images.

It is known to drop rescue equipment to a person in distress by airplanes or helicopters in order to help the person until the rescue service arrives. However, this rescue equipment is often dropped at a distance from the person which requires the person to move to the drop site. The dropped equipment may drift away from a person at sea, particularly if there are high waves or a strong current, or it might be difficult for the person to reach this drop site. Today radio controlled helicopters with a single rotor or fixed- wing aircrafts may be used to transport goods, however the goods are often stored in a cargo room inside the device thus making them large, heavy and expensive. The goods may be suspended from the bottom of the device; however this seriously affects the aerodynamic performance of the device which means that they are not able to operate in strong winds. This also restricts the manoeuvrability of the device during flight operations.

It is known to store life vests or life buoys on board marine vessels in the event of an emergency situation. Such live saving devices may also be located at offshore structures. These devices have a size that makes them difficult to store and often have a weight of about 2.5kg. This means that they typically are not able to be thrown by no more than 5m which means that the person throwing it has to be placed close to the person in distress. However, such life vests are designed to be put on and secured to the person before getting into the water, thus making them difficult to put on when lying in the water.

Other more compact devices, such as inflatable live vests, may be used instead. Such inflatable devices typically use a small container with compressed gas (carbon dioxide) to inflate the device. This canister is often attached to a valve on the outside of the lift vest and may be activated when it comes into contact with the water. The canister and inflating mechanism often irritates and annoys the person wearing the life vest due to its large size and weight. Such life vests are also designed to be put on and secured to the person before getting into the water, thus making them difficult to put on when lying in the water.

Neither of the live saving devices is able to supplying heat to a person in distress which is a critical issue when being in an emergency situation at sea. People in distress at sea are more likely to die from cooling than drowning, particularly in cold waters and dur- ing the winter.

Object of the Invention

An object of this invention is to provide an unmanned aerial vehicle capable of transport rescue equipment to a person in distress. An object of this invention is to provide unmanned aerial vehicle which can perform an autonomous rescuing operation.

An object of this invention is to provide a compact live saving device which can be thrown from a greater distance.

An object of this invention is to provide a live saving device which can supply heat to the person wearing the live saving device.

An object of this invention is to provide a compact inflating mechanism which can be integrated into a live saving device.

Description of the Invention

An object of the invention is achieved by providing an unmanned aerial device characterised in that

- the device comprises at least one module coupled to at least one of the sides of the body and is configured to receive and hold one or more equipments, wherein the module is electrically coupled to the control system and further configured to release at least one of the equipments upon receiving a control signal from the control system. This allows the unmanned aerial device, UAV, to transport and drop equipment for various applications from one location to another location. The UAV is particularly suited to transport and drop minor packages of equipments, such as rescue equipments, to people located in remote location, e.g. in an emergency situation. The use of an UAV allows it to be launched quickly and may perform one or more autonomous operations without any interaction with a human operator. This allows the UAV to transport equipments to remote locations that are difficult or dangerous to reach by conventional vessels or vehicles. According to one embodiment, the module is configured as an interchangeable module capable of being replaced with another module, wherein the module interchangeable module comprises a first coupling element configured to be coupled to a second coupling element on the body.

This allows the module to be easily and quickly replaced with another module configured to perform the same or another operation. The module may be configured as a rescue module, a camera module, a test sampling module, a monitoring module, a recognisance or inspection module, or another module configured to carry out a desired operation. The UAV may comprise two or more modules configured to perform the same or different operations. The test sampling module may comprise one or more units configured to acquire and store one or more test samples in a gaseous, solid or liquid stage. In a simple embodiment, it may instead comprise a sensor unit with at least one sensor configured to respond to an extern signal or stimulus. This allows the UAV to be very versatile since it may be outfitted with modules for various applications, such land or sea inspections, environmental studies, search or monitoring tasks, inspection of supply lines or plants. The interchangeable module may be attached or detached to the body by use of fastening means, such as screws, bolts or the like, or male and female coupling means, such as threads, a quick-release coupling or the like. According to one embodiment, the module comprises one or more chambers configured to at least partly receive and hold the equipment, wherein a release mechanism is coupled to the chamber for holding the equipment in place until the release mechanism is activated by the control system. The chamber may extend into the module so that the opening of the chamber is substantially flushed with the outer surface of the body. This allows the equipment to be partly or completely concealed inside the chamber during the flight. The chamber may be configured to receive the equipment in a compact configuration so that it takes less space. Alternatively the equipment may be placed, e.g. in a recess, on the upper or lower side of body. This allows the equipment to be arranged so that it has a minimal effect on the aerodynamic performance of the UAV. This also protects the equipment from any external impacts and minimizes the risk of the equipment accidentally gets into the airflow around the rotors and causing a failure. The release mechanism is con- figured to hold the equipment in place during the flight and allows the equipment to be delivered without having to land. The size and shape of the chamber may be adapted to the size and shape of the type of equipment intended to be transported. The configuration and position of the release mechanism relative to the chamber may be adapted to the type of equipment intended to be transported. The size and shape of the chamber may be adapted to the type of equipment intended to be transported.

The UAV may comprise two, three or more chambers arranged on the respective side of the body. Each chamber is coupled to a release mechanism which in turn is electrically coupled to the control system. The release mechanisms may be controlled indi- vidually or in groups thus allows the equipments to be leased or dropped selectively. The same type or different types of equipment may be positioned inside the chambers thus allowing the UAV to carry various equipments for various purposes.

The module may be configured to be coupled to one of the sides of the body and com- prise an aerodynamically shaped housing. The housing may be formed by at one or two shell parts which are shaped to form an open chamber in which the equipment is positioned. The chamber may be closed off by the outer surface of the UAV when the two pieces is coupled together, or by an innermost shell part arranged between the outer surface of the UAV and the outermost shell parts. The module or at least one of the shell parts may be attached to the body using any fastenings, such as screws or bolts, or female and male coupling means for a quick release, such treads, coupling elements or the like. The coupling means may function as the release mechanism which may be activated either manually by a person or automatically by control system. The outermost shell part or parts may be connected to a hinge mechanism configured to rotate the shell part relative to the outer surface of the UAV and optionally also to rotate the shell part back to its initial position. The contact surfaces between the module and the body may be sealed using sealing means, such as a deformable element in the form of an O- ring or another suitable seal. This allows the equipment to be transported on the outside of the body and encapsulated in an aerodynamic housing which has a limited effect on the aerodynamic performance of the UAV. The coupling means allows the entire module to be released or release the equipment by rotating the outermost shell part or parts.

According to one embodiment, the module extends through the body and the chamber is connected to an opening on the upper and lower sides respectively.

The length of the chamber may allow two or more separate pieces of equipments to be arranged inside the same chamber thus allowing the UAV to carry a greater number of equipments. The release mechanism may be arranged near one or both openings or in the middle of the chamber. This allows the equipment to be released or dropped from either side of the body when the UAV is facing the right side up or upside down. This allows the UAV to release the equipment even when it is turned over during flight due to high wind speeds or gusts.

Alternatively, a first module may be coupled to the upper side and a second module may be coupled to the lower side. The two modules may be relative to each other, e.g. over each other, and may be controlled independently or simultaneously via the control system. This allows the control system to selectively active the release mechanism coupled to each of the chambers in the modules.

According to one embodiment, the release mechanism comprises at least one moveable element acting on the rescue equipment, wherein the release mechanism is configured so that the rescue equipment is released from the chamber at a predetermined exit velocity. The release mechanism may comprise at least one moveable mechanical element configured to be brought into direct contact with the outer surface of the equipment. The mechanical element may be configured as a tap or rod having a free end which is moved in and out of the chamber through a small opening in the chamber. An activat- ing element, e.g. a spring, is coupled to the moveable element and is compressed or decompressed upon activation. Two, three or more elements may be used to hold the equipment in place. The release mechanism may be a gripping or suction unit configured to apply a gripping or suction force to the equipment. The equipment may be released when suction is stopped or the gripping means are moved away from the equip- ment. Alternatively, a lid or cover arranged at one of the openings may be used instead. The equipment may be released by moving the lid or cover relative to the opening, e.g. by rotating it around a hinge or retracting it into a recess located in the chamber. This allows the equipment to be released from the chamber in the UAV using gravity. The release mechanism may comprise at least one rotatable wheel or disk connected to an activation unit. The wheel or disk is configured to contact the outer surface of the equipment and to accelerate the equipment from a first velocity to a second velocity. The outer surface of the wheel or disk may be lined or coated with a material for added grip or friction. The wheel or disk may be activated before the equipment inside the chamber comes into contact which will increase the exit velocity of the equipment. Two, three or more wheels or disks may be used to accelerate the equipment. This allows the UAV to release the equipment from the chamber at a desired exit velocity by applying a force to it. This allows the equipment to be released at a greater distance or height and makes it less susceptible to the wind.

According to one embodiment, the release mechanism comprises at least one magnetic element interacting with at least one magnetic element in the equipment.

The release mechanism may comprise at least one magnetic element in the form of a permanent magnet or an electromagnet configured to generate an electromagnetic field. The equipment may comprise at least one other permanent magnet or magnetic element configured to interact with the magnetic field. Two, three or more magnetic couplings may be used to hold the equipment in place. This allows the release mechanism to hold the equipment in place and release it without any direct contact. The magnetic couplings may be arranged along the length of the chamber and configured to accelerate the equipment before it exits the chamber. According to one embodiment, the control system comprises a first flight control unit and a second flight control unit electrically coupled to the rotors, both of which are electrically coupled to an orientation detection unit, wherein the first flight control unit is configured to control the flight in a first state and the second flight control unit is configured to control the flight in a second state.

Each of the rotors may be electrically coupled to two redundant control units which are configured to control the flight in different states. A gyroscope having multiple, e.g. five, measuring axes, an accelerometer or another orientation unit may be used to determine the orientation of the UAV. The first flight control unit may be configured to control the flight when the UAV is facing right side up. The second flight control unit may be configured to control the flight when the UAV is facing upside down (turned over). The switching between the two flight control units may be performed automatically. Alternatively a single flight control unit may be used which is configured to operate in other different modes depending on the orientation of the UAV. This allows the UAV to continue flying when if the UAV is turned over thus making it less sensitive to wind gusts and allows it to be operated in high wind speeds, e.g. up to 18^m/_s or 20^m/_s. The two control units may also be configured to monitor each other so that one is able to take over if the other fails. This increases the safety of the system and allows the power consumption to be reduced if the data communication between the two units is reduced.

According to one embodiment, the body has a disc shaped configuration in which the rotors are arranged near the periphery of the disc and the module is arranged relative to the centre of the disc.

The use of a disc shaped configuration allows the upper and lower sides of the body to have the same shape and/or configuration. This aerodynamically shaped body allows incoming air to have a more optimal flow over the upper and lower sides thus reducing the drag and increasing the lift. The rotors may be arranged along the periphery of the disc shaped body in a predetermined pattern. This also allows the UAV to continue flying when it is turned over (facing upside down) due to high wind speeds or wind gusts. The aerodynamic shape allows the UAV to take up if it is positioned on a flat planar surface or even on the water surface. The disc shaped body allows the UAV to pivot relative to the water surface thus avoiding a vacuum to be formed between the UAV and the water surface during take off. The body may have a maximum outer height or thickness of 10-20cm, preferably 12-16cm and/or an outer diameter of 70- 130cm.

The UAV may comprise between two and twelve rotors arranged in two or more sets, e.g. three, four or five or six sets. Each set may comprise a first rotor facing towards the upper side and a second rotor facing towards the lower side along the same axis. Each rotor may be coupled to its own motor which is electrically coupled to the con- trol system. The rotor blades may be angled relative to the rotation plane for improved lift. A protective grid may be positioned around or in front of each rotor. This allows the rotors to be positioned within the circumference of the body so they are less sensitive to external impacts and may be operated similar to that of a multicopter. This allows the UAV to be configured as a compact unit which increased structural strength. The compact shape allows the UAV to be manoeuvrable in bad weather and in mean wind speeds up to 18^m/_s or 20 ^m/_s. The use of multiple rotors allows the UAV to continue to fly even if one or more rotors should fail.

The flight control units may be configured to operate in an autonomous mode which the UAV is able to execute one or more predetermined flight programs or flight patterns loaded into the control system. The flight programs or patterns may be loaded into the UAV at installation or uploaded to the UAV upon initialisation via a remote unit or central station. The remote unit or central station may comprise a display and/or a user interface for planning and setting up the parameters (e.g. waypoints) defining the flight program or pattern. The control units may be coupled to one or more sensor units configured to sense one or more flight related parameters, such as airflow, per- formable of each motor, wind speed or direction, or other relevant parameters. According to one embodiment, the device comprises a second chamber in which a parachute is located, and wherein the parachute may be deployed upon detecting a failure by the control system. This allows the UAV to land safely on the ground or at the sea so that it may be retrieved later. The body may be sealed to prevent water or moisture from entering the body, even if it lands on water, thus allowing it to float. This allows the UAV it self to be used as a life saving device for a person in distress at sea. The body may be made of plastic, a composite material, e.g. carbon, or another shock or impact resistant mate- rial.

According to one embodiment, the control system comprises a data control unit electrically coupled to a wireless communications unit configured to communicate with a remote unit, a central station and/or a second unmanned aerial device via a wireless communication link.

The UAV may comprise a wireless communications unit for communicating with various remote devices using RF signals, IR signals, hypersonic signals, GSM signals, optical signals or another communication standard. The data control unit may be electri- cally coupled to a GIS system or location unit in the form of a GPS receiver or another positioning receiver. The data control unit may determine the orientation of the UAV based on the data from the GPS receiver, the gyroscope or an inertial navigation unit in the form of a gyrocompass or a laser range finder. This allows the UAV to determine its position and adjust the flight according to the flight program or plan. The communi- cations unit may communicate with a corresponding communications unit at a central station, e.g. a rescue service or control centre. The data control unit may be electrically coupled to one or more sensor units configured to sense various status information of the UAV, such as battery level, speed, or other relevant status information. The data control unit may transmit various data to the central station thus allowing the station to monitor the status, current settings and location of each UAV. These data may be logged in the central station and/or stored in the UAV before being transmitted to the central station. These data may be stored in a flight data recorder electrically coupled to the control system for analysis in the event of a failure or accident. The communica- tions unit may communicate, one-way or two-way, with a microprocessor unit coupled to various rescue equipments, such as a life saving device.

The operation, e.g. the flight and/or the release, of the UAV may be controlled from the central station by transmitting various control signals to the UAV. The UAV then perform the desired tasks based on the received control signal. A remote unit in the form of a remote control comprising a wireless communications unit may be used to control the operation of the UAV. The remote control may comprise a gyroscope used to generate various control signals for controlling the UAV. The control signals are then transmitted to the UAV which perform the desired task accordingly. A laser pointer in the remote control may be used to measure the distance to the target and to guide the UAV to the desired target. This allows the UAV to be controlled in a simple and easy way even for an inexperienced user. The UAV may then automatically return to its starting position.

The UAV may have a unique identification number which may be used when communicating with another device, e.g. another UAV. This allows more than one UAV to interact with each other in order to carry out the same operation. The UAV may transmit its location to another UAV so that they avoid hitting each other or is able to continue where the other UAV stopped.

According to one embodiment, the data control unit is electrically coupled to an image capturing unit, and wherein the data control unit is configured to analyse the image data from the image capturing unit for recognizing one or more patterns or move- ments.

The data control unit may be electrically coupled to a thermal camera, an infrared camera or a photographic camera configured to capture still images or live images. The image data is then transmitted to the data control unit which is configured to analyse the data, extract different features and evaluate the extracted features by comparing them to one or predetermined parameters. This allows the UAV to recognize various patterns or movements, such as people or parts thereof, hand or body gestures. The recognized patterns or movements may be used to transmit commands or control sig- nals to the UAV which may be then transmitted to the flight control unit or the central station. This allows the UAV to be guided into an optimum position relative to the person before leasing or dropping the equipment or to perform the desired operation. The extracted data may also be used by the data control unit to carrying various operations according to a prioritised list or arranging the data in a prioritised order. Data received from a microprocessor unit in one or more rescue equipments, such as life saving devices, may be arranged in a prioritised order according to one or more parameters. This allows the UAV to determine where to release or drop the equipment, e.g. identifying the person in must distress and dropping the rescue equipment next to that person. The priority of extracted data may also be used to determine which flight operation should be carried out, such as position to hover or circulate, next waypoint or other relevant operations. The UAV may comprise means for audio and/or visual communication with a person at the location. The UAV may play and/or display various recorded messages to that person. A microphone may be coupled to the control system for picking audio messages from the person or the person may be introduced to perform a desired movement or gesture which may be recognised via the camera. The gesture or movement is then recognized by the data control unit which then executes the corresponding command.

According to one embodiment, the device comprises an energy source electrically coupled to a charging unit which configured to interact with another power energy source. This allows the batteries or battery pack used to power the UAV to be recharged through a charging unit which comprises one or more solar cells. The charging unit may be configured as an inductive charging element configured to interact with a corresponding inductive charging element located in a charging station. The charging station may form part of a base station for receiving and holding the UAV when it is in use. The energy source may be configured to have a battery capacity of at least 40 minutes. The control system may comprise an activation unit configured to initiate and activate the UAV. When the UAV is not use, only the activation unit is active while the other units are shut down thus saving power. The activation unit may receive an activation signal from the central station and/or the remote unit, after which the activation unit wakes up the rest of the control system which then initials the flight mode. The activation unit may be electrically coupled to an accelerometer or airflow sensor which is used to activate the UAV. The UAV may be activated when a predetermined activation level is exceeded, e.g. an acceleration of more than 2m/s². According to one embodiment, the equipment is rescue equipment packed in a compact state, wherein the rescue equipment is selected from the group of life saving device, personal floating device or an emergency kit.

The module may be configured as a rescue module in which various rescue equipment may be stored in the chamber. The rescue equipment may be a life saving device in the form of a vest or buoy or an emergency kit with various items packaged in a compact state. The life vest or buoy may comprise an inflating mechanism coupled to at least one inflatable chamber configured to inflate the device upon activation. The equipment is packages so that it has an aerodynamic shape, e.g. a round or oval ball or cylinder, allowing it to be stored and dropped from the chamber.

The rescue module may alternatively be configured to tow or transport a guide wire out to the person. The guide wire may be attached to guide a stronger and bigger wire or rope which is then guided out to the person. One end of the guide wire may be cou- pled to the release mechanism of the UAV while the other end may be attached to the UAV, a vessel or a point on land. The guide wire may be omitted and the larger rope or wire may be coupled directly to the release mechanism of the UAV. The UAV may in this mode fly over the person and then drop the wire so that the person is able to grip firmly around the wire. This allows the person to pull him self to safety or to be pulled by the UAV.

This allows the UAV to function as a rescue unit capable of rescuing a person in distress or assisting in a rescue operation. The module allows the UAV to transport and drop various rescue equipment to the person in distress. Two or more compact packages of rescue equipments may be stored in the UAV. This allows the person to be rescued quickly which increases the survival probability for the person in distress. According to one embodiment, the rescue equipment comprises an inflating mechanism which is coupled to at least one inflatable chamber arranged in the rescue equipment and is configured to inflate that chamber when activated.

The inflating mechanism may be configured to automatically inflate the chamber when the person enters the water. The inflating mechanism may be configured as a compact unit which may be integrated and thus concealed inside the life saving device. This allows the inflating mechanism to be better protected as it is integrated into the life saving device. The life saving device may comprise a ring or horseshoe shaped inflatable chamber. The chamber may be formed by a single piece of flexible material such as plastic or pieces welded or glued together. A protective layer of plastic or a coating may be arranged on the outer surface of the pieces forming the chamber. An arrangement of tightening means in the form of straps may be coupled to the inflatable chamber for securing the life saving device to the user. The chamber may be configured to form a large surface area around the body of the user. The surface of the life saving device may be treated or coated with a colour or reflective material which is easy to detect visually in the dark or in bad weathers or allows for a better detection/recognition through a camera. This allows for an easier detection of a person in distress from an approaching vessel, a helicopter, an airplane or via the UAV.

A manual inflating element in the form of a mouth piece may be coupled to the chamber by a valve. The valve may be configured to automatic close when air or another gas is no longer lead into the chamber. This prevents the gas inside the chamber from es- caping. Alternatively a second valve may be coupled to the chamber for regulating the pressure inside the chamber.

Other means for locating the person in distress may be coupled to the life saving device. The means may be a visual light diode and/or an IR diode electrically coupled to a battery, a whistle, a pulse meter or another suitable element. A microprocessor unit having a transceiver, a location detection unit in the form of a GPS tracking unit, may even be coupled to the life saving device for transmitted at least the location data to a remote located receiver, e g. located with a predetermined distance from the person. The data may be transmitted to a GIS system or communications unit in a UAV. A floating anchor in the form of an element having a predetermined weight may be coupled to the life saving device so that it always corrects it self when dropped into the water. The life saving device may be packaged into a compact state which takes up less space. The device may be packaged so that it has an aerodynamic shape which is less sensitive to the wind acting on the package. The life saving device may be configured so that it fits inside the chamber of the UAV or a container located on a vessel or an offshore structure. The aerodynamic profile of the device may be optimised so that it is less sen- sitive to the wind when dropped or leased from the UAV. The aerodynamic profile of the device may instead be optimised so that it is less sensitive to the wind when thrown from a vessel or a structure and has optimal flight characteristics. The surface of the compact package may comprise multiple recesses/dimples or tracks configured to reduce drag and/or improve the laminar airflow over the surface during flight. If the de- vice is to be stored in a container, it may be packaged in a perforated film or foil for protecting the life saving device. The life saving device may in the compact state be shaped as a circular or oval ball. One or more fins, e.g. flexible fins, may be arranged on the device for spinning or stabilising the device during the flight. The optimised aerodynamic profile allows a person to thrown the compact device at a distance of more than 10m, preferably more than 15m. The maximum outer diameter or height/width of the life saving device in the compact state may be between 10-30cm, preferably between 10-20cm or 20-30cm. The maximum weight of the life saving device may be no more than l .OOOg, preferably between 400-800g. The inflating mechanism may comprise a container in which a fluid under pressure may be stored. The container may have an elongated or ball shaped form for allows the device to be packaged into a compact form. The container may be made of metal, plastic or a composite material. The fluid may be a gas or liquid capable of transforming into its gaseous phase upon activating. Alternatively the container may comprise two different fluids which are stored separately and generate a gas when mixed. The fluids used to inflate the chamber may be selected so that they generate a chemical reaction that heats up the gas, e.g. up to 60-70°C, which is used to inflate the chamber. This allows the inflating mechanism to function as a heat source upon activation. Alternatively one or more heating sources may be arrange inside the chamber and activated wither manually or upon inflation. The heat may be transferred to the body of the user, e.g. a person floating in cold waters, thus heating up the user so that the effect of the cooling is reduced. This provides a greater thermal profile due to the size of the chamber. This allows for a better detection/recognition of the life saving device through a thermal camera or another heat-seeking device.

An activation unit made be coupled to the container or arranged inside a recess in the container. The activation unit is configured to perforate the wall of the container or cause the two fluids to mix. This allows the gas to flow from the container and into the chamber in the device. A perforating element in the form of a needle may be arranged inside a tube located in the recess. The needle may be coupled to a moveable element in the form of a firing pin arranged inside the tube. The firing pin may be configured as a plate or inner tube to which the perforating element is attached. The firing may be acti- vated by applying a force so that is moves from a first position to a second position. The firing pin may be activated by a spring, e.g. a compression or extension spring, arranged in the tube. The tube may at one end be closed off by a cover or lid where the spring rest against the inner surface of the cover or lid. The other end of the tube is positioned at the wall of the container so that the perforating element is pushed or pulled through the wall when activated.

A locking unit may be coupled to the activation unit and may be configured to hold the activation unit in place when not activated. When the locking unit is unlocked, the activation unit is activated and the perforating element is pushed or pulled through the wall. The locking unit may comprise a tube arranged relative, e.g. parallel or perpendicularly, to the tube of the activation unit. A first moveable element in the form of a rod may be positioned inside the tube and extend through the cover or lid. The first element may at one end comprise a recess configured to at least partly receive a second moveable element which is configured to engage the firing pin and the first element. The second element in the form of at least a ball or a rod may be arranged in a third tube which connects the tube of activation unit with the tube of the locking unit. The second element is configured to hold the firing pin in the first position when not acti- vated. Means for moving the first element in the form of a spring, e.g. a compression or extension spring, may be arranged between the cover or lid and the recess, or vice versa. The spring is configured to move the first element from a first position to a second position. Once unlocked the spring pushes or pulls the first element so that the recess is aligned with the second element. This allows the second element to be moved into the recess which in turn activates the firing pin.

The first element is held in the first position by a release mechanism in the form of an arm. The arm may be coupled to the cover or lid so that it is able to be moved relative the first element. The arm may at one end comprise means for holding the first element in the first position, as fingers or a rod. A dissolvable element in the form of a bobbin may be arranged between the fingers and the first element. The dissolvable element may be made of a substance, such as salt, which dissolves when it comes into contact with a liquid, such as water. The arm may at the other end be coupled to a string or wire which at the free end may comprise means in the form of a ring or ball for grip- ping the string or wire. When the string or wire is pulled, the arm is moved relative to the first element and the dissolvable element is moved out of contact with the first element. This allows the first element to be moved into the second position.

The locking unit may be omitted so the release mechanism is coupled directly to the activation unit. The dissolvable element may be arranged between the firing pin and the release mechanism or inside the release mechanism. The activating unit and the release mechanism may be arranged on the outside of the container instead of in a recess in the container. This allows the size of the inflating mechanism to be reduced and it comprises fewer parts thus reducing the risk of one of the parts failing. Description of the Drawing

The invention is described by example only and with reference to the drawings, wherein: Fig. 1 shows an exemplary embodiment of an unmanned aerial device according to the invention seen from the top;

Fig. 2 shows a first cross section of an unmanned aerial device;

Fig. 3 shows a second cross section of an unmanned aerial device;

Fig. 4 shows a flow chart of the function of the unmanned aerial device;

Fig. 5 shows an exemplary embodiment of an unmanned aerial device configured for performing a rescue operation;

Fig. 6 shows an exemplary embodiment of a life saving device seen from the front; Fig. 7 shows the life saving device of Fig. 6 seen from the side;

Fig. 8 shows a cross section of the life saving device of Fig. 6 with an inflating mechanism;

Fig. 9 shows an exemplary embodiment of the inflating mechanism of Fig. 8; and Fig. 10 shows the inflating mechanism of Fig. 9 seen from the top.

In the following text, the figures will be described one by one and the different parts and positions seen in the figures will be numbered with the same numbers in the different figures. Not all parts and positions indicated in a specific figure will necessarily be discussed together with that figure.

Detailed Description of the Invention

Fig. 1 shows an exemplary embodiment of an unmanned aerial device 1 (also called an UAV) seen from the top. The device 1 may comprise a body 2 having an aerodynamic shape. The body 2 may comprise an upper side 4 connected to a lower side 3 by a peripheral edge 5. The body 2 may comprise one or more cut-outs 2a arranged near the peripheral edge 5 for saving materials and reducing the weight.

The device 1 may comprise multiple rotors 6, 7, 8, 9 with two or more rotatable rotor blades of a composite or metallic material arranged within the circumference of the body 2. The rotors 6, 7, 8, 9 may be arranged along the peripheral edge 5 in a prede- termined pattern. The rotors 6, 7, 8, 9 may be arranged in four sets, as shown in fig. 1. Each set may comprise a first rotor 6a, 7a, 8a, 9a facing the upper side 3 and a second rotor (not shown) facing the lower side 4 where the first and second rotors are aligned along the same axis 10. Each of the rotors 6, 7, 8, 9 may be coupled to its own drive unit (not shown) located inside the body 2 by a drive shaft (not shown). The drive units in the form of motors, e.g. brushless motors, are electrically coupled to a control system 11. A protective grid (not shown) may be positioned in front of each rotor 6, 7, 8, 9 on both sides 3, 4.

An interchangeable module 12 may be arranged in the centre of the body 2. The module 12 may be coupled to the body 2 by at least one male and female coupling means (not shown), such as threads, a quick-release coupling or the like. The module 11 may be configured as a rescue module comprising three chambers 13a, 13b, 13c each of which is configured to receive at least one piece of rescue equipment 14 in a compact state. At least one release mechanism 15a, 15b, 15c may be arranged relative to the chamber 13a, 13b, 13c and may be configured to directly or indirectly interact with the rescue equipment 14. The release mechanism 15 may be electrically coupled to the control system 11 and configured to release at least one of the rescue equipments 14 upon receiving a control signal from the control system 11.

The size and shape of the chamber 13 may be adapted to the size and shape of the type of rescue equipment 14 intended to be transported. The position of the release mecha- nism 15 relative to the chamber 13 and/or the rescue equipment 14 may be adapted to the type of rescue equipment 14 intended to be transported.

Fig. 2 shows a first cross section of the device 1 with a rescue module 16 having one chamber 17 for receiving the rescue equipment 14. The body 2 may have a disc shaped configuration, as shown, in which the rotors 6, 7, 8, 9 may be arranged near the peripheral edge 5 of the disc and the module 16 may be arranged in the centre of the disc.

The module 16 may extend through the body 2 and the chamber 17 may be connected to an opening 18, 19 on the upper and lower sides 3, 4 respectively. The module 16 may have a height which is substantially equal to the height of the body 2 so that the upper and lower sides 20, 21 of the module 16 are substantially flushed with the upper and lower sides 3, 4 of the body 2 respectively. The length of the chamber 17 may allow two or more separate pieces of rescue equipments 14 to be arranged inside the chamber 17. The release mechanism 22 may be arranged in the middle of the chamber 17 which enables the equipment 14 to exit the chamber 17 through either one of the openings 18, 19. The release mechanism 22 may comprise at least one magnetic element 22a in the form of an electromagnet arranged close to the inner surface of the chamber 17. The magnetic element 22a may be configured to generate an electromagnetic field which extends into the chamber 17. The rescue equipment 14 may comprise at least one magnetic element 22b made of a magnetic permeable material arranged near the outer sur- face of the rescue equipment 14. The magnetic element 22b may be configured to interact with the magnetic field so that the rescue equipment 14 may held in place without any direct contact. The release mechanism 22 may be configured so that the rescue equipment 14 is released by using the gravity. Fig. 3 shows a first cross section of the device 1 with the rescue module 16 having one chamber 17 for receiving the rescue equipment 14. This embodiment differs from the embodiment shown in fig. 2 by using a different release mechanism.

The release mechanism 23 may comprise at least one moveable element 24 in the form of a rotatable wheel or disc acting on the rescue equipment 14. The release mechanism 23 may be configured to accelerate the rescue equipment 14 so that it is released from the chamber 17 at a predetermined exit velocity. The moveable element 24 may be configured to be brought into direct contact with the outer surface of the rescue equipment 14. The element 24 may be configured to be moved in and out of a small opening in the chamber 17. The element 24 may be electrically coupled to an activation unit (not shown) configured to rotate the wheel or disc at a predetermined rotation speed. The element 24 may be activated before the rescue equipment 14 located inside the chamber 17 comes into contact. Two wheels or discs 24a, 24b may be arranged on oppo- sites of the rescue equipment 14.

Fig. 4 shows a flow chart of the function of the control system 11 of the device 1. The control system 11 may comprise an activation unit 25 configured to activate the control system 11. When the device 1 is not in use, only the activation unit 25 is active while the other units are powered down, thereby saving power. The activation unit 25 may be electrically coupled to a data control unit 26 which in turn is electrically coupled to a wireless communications unit 27. The activation unit 25 may be electrically coupled to an accelerometer (not shown) which is used to activate the device 1. The device 1 may be activated when the detected acceleration level exceeds a predetermined activation threshold, e.g. 2m/s². When the activation threshold is exceeded, the activation unit 25 transmits an action signal to the data control unit 26, which then initiates and starts 25a the device 1. The activation unit may alternatively receive an activation signal from a central station and/or a remote unit via the wireless communications unit 27.

The wireless communications unit 27 may be configured to communicate with a remote unit, a central station and/or a second unmanned aerial device via a wireless communi- cation link. The communications unit 27 may be configured to communicate another device using GSM signals, such as SMS and/or MMS.

After being activated, the data control unit 26 determines if any control signals have been received via the communications unit 27. If the one or more control signals have been received, then the data control unit 26 performs one or more predetermined task according to the control signals.

The data control unit 26 may be electrically coupled to one or more sensor units (not shown) configured to sense various status information of the device 1, such as battery level, speed, or other relevant status information. The data control unit 26 may transmit various data to the central station which allows the station to monitor the status, current settings and location of each device 1. These data may be logged in the central station. A flight data recorder (not shown) electrically coupled to the data control unit 26 may store various status information and settings of the control system.

The data control unit 26 may communicate with one or more flight control units 28, 29 configured to control the flight mode of the device 1. A first flight control unit 28 and a second flight control unit 29 may be electrically coupled to the rotors 6, 7, 8, 9. The first flight control unit 28 may be configured to control the flight in a first state and the second flight control unit 29 may be configured to control the flight in a second state.

A GIS system 30 may comprise a location unit in the form of a GPS receiver electri- cally coupled to the flight control unit 28 for determining the position of the device 1. The GIS system 30 may comprise a gyroscope having five measuring axes for determining the orientation of the UAV. The GIS system 30 may comprise a compass unit configured to determine the geographic orientation of the device 1. The flight control unit 28 may determine the orientation and bearing of the device 1 based on the data from the GIS system 30. The flight control unit 28 uses the GIS system 30 to navigate in the flight mode.

One or more sensor units 31, e.g. an optical or mechanical airflow sensor, may be electrically coupled to the flight control unit 28. Other suitable sensors, e.g. a speed sensor, for controlling the flight mode may further be coupled to the flight control unit 28. The flight control unit 28 may control the flight mode based on the data from the sensor units 31 and/or the data from the GIS system 30. A predetermined flight program or plan may be stored in the control system 11 which the flight control unit 28, 29 uses to carry out the flight mode. The control system 11 may be configured to carry out one or more autonomous flight operations.

An image capturing device 32 in the form of a camera may be electrically coupled to the data control unit 26 or alternatively the flight control unit 28, 29. The control unit 26, 28, 29 may be configured to analyse the image data from the image capturing unit 32 for recognizing one or more patterns or movements. The data control unit 26 may be configured to analyse the image data and extract one or more features from the image. The data control unit 26 may be configured to evaluate the extracted features and detect or recognise predetermined patterns or movements by comparing the features to one or more predetermined parameters or patterns.

The flight control units 28, 29 may both be coupled to the GIS system 30 which may be used to determine the orientation of the device 1. The data from the GIS system 30 may be used to determine which of the two flight control units 28, 29 should control the flight mode. If the first flight control unit 28 determines that the device 1 is turned over, then the control of the flight mode may automatically be switched 33 over to the second flight control unit 29, and vice versa. Once the proper flight control unit 28, 29 have performed its initialisation, the control system 11 ready to carry out the desired task 34 determined by the control signals received via the communications unit 27. The control system 11 may be configured to carry out one or more predetermined tasks which may be stored in the control system 11.

Fig. 5 shows an exemplary embodiment of the device 1 configured for performing a rescue operation. The device 1 may be configured to operate in one or more autonomous modes, e.g. a flight mode and/or a rescue mode.

The device 1 may be configured to be stored on a base station 35 configured to receive and hold the device 1 when not used. The base station 35 may comprise a charging unit (not shown) configured to charge the energy source, e.g. batteries, in the device 1. The charging unit may be configured to charge the energy source in the device 1 from an external power source by an inductive coupling. The base station 35 may be located in structures, such as wind turbines, life guard towers, and/or in vessels, such boats.

The device 1 may be activated by shaking or throwing 36a the device 1 so that the activation unit 25 is activated and starts up the device 1. The device 1 may be activated by moving the device 1 quickly up and down one or more times thus triggering the activation unit 25. The device 1 may instead be activated by placing it on the ground 36b and using a remote unit (not shown) to activate the device 1. Alternatively, it may be activated remotely from a central station.

Once activated, the device 1 may execute an autonomous flight mode 37 which may be pre-programmed or uploaded into the device 1. The flight program or plan may be up- loaded to the device 1 via the central station (not shown). The control system 11 uses the data from the units 26, 28, 29 to continuously control and adjust the flight. A remote unit (not shown) in the form of a remote control may be configured to control the operation of the device 1. The remote unit may comprise a wireless communications unit configured to communicate with the device 1 via a wireless communications link. The remote unit may be configured to guide the device 1 to a person in dis- tress 38 using a laser pointer. A gyroscope arranged in the remote unit may be used to control the flight mode of the device 1.

When the device 1 has detected or have been guided to one or more persons in distress, it may release one of the rescue equipments 14 located in the chambers 13, 17 using the release mechanism 15, 22, 23. The device 1 may be configured to detect the person in distress 38 by recognising predetermined patterns or movements derived from the image data acquired by the image capturing unit 32, e.g. the person or parts thereof. The device 1 may be configured to execute an autonomous rescue mode 39 in which the rescue equipment 14 located in the rescue module 16 is released or dropped close to the person in distress 38. The GIS system 30 may be used by the flight control unit 28, 29 to position the device 1 at a predetermined height and distance relative to the person in distress 38. The device 1 may then dropped, e.g. automatically, one of the rescue equipments 14 by activating the respective release mechanism 15, 22, 23. This allows the rescue equipment 14 to be dropped much more precise and closer to the person in distress 38.

If the device 1 has detected more than one person in distress 38, the data control unit 26 may carry one or more intelligent data decisions. The data control unit 26 may be configured to analyse the extracted data from the unit 32 relating to each of the persons in distress 38 in order to determine which of the people is in a must critical state. The extracted data or parameters may be categorised according to a prioritised list, e.g. movement, body temperature, audio/visual response to stimulus or instructions. Once the data control unit 26 has determined which person is in the most critical state, the data control unit 26 may send control signals to the flight control unit 28, 29 when then positions the device relative to that person 38. After dropping a rescue equipment 14 to the person 38, the device 1 may then be positioned over the second must critical person. After which the device 1 drops another rescue equipment 14 to that person 38. The device 1 may be configured to autonomously hover over the person or person in distress 38 and continuously transmit data back to the central station and/or remote unit. This allows the rescue service to follow the progress and/or communicating with the person in distress 38 through audio and/or visual communication means. The person in distress 38 may communicate with the device 1 to guide it into position before dropping the equipment 14 and/or the central station by predetermined gestures which recognised by the data control unit 26.

The device 1 may be configured to automatically return 40 to its starting position when the flight mode and/or the rescue mode or tasks have been completed. The data control unit 26 may be configured to continuously monitor various status information detected or sensed by the sensors 31 located on the device 1. If the data control unit 26 detects a critical status information, e.g. low battery level, failure in a critical number of the rotors 6, 7, 8, 9, too high mean wind speed or another relevant information, the data control unit 26 may transmit a control signal to the flight control unit 28, 29 instructing it to fly back to the starting position. Fig. 6 shows an exemplary embodiment of the rescue equipment 14 in the form of a life saving device 41 seen from the front. The life saving device 41 may be packaged in a compact state having a shape that differs from its shape in its normal state. The life saving device 41 may configured as a life vest or buoy. The life saving device 41 may comprise at least one inflatable chamber (not shown), e.g. a ring or horseshoe shaped chamber, coupled to at least one inflating mechanism 42. The chamber may be formed by a single piece or two pieces of flexible material, e.g. plastic, which is welded together along the edges.

The life saving device 41 may have an aerodynamic shape in the compact state where the shape may optimised so that it is less sensitive to the wind when passing through the air. The life saving device 41 may be packaged to form a ball shaped configuration, as shown in fig. 6. The dimensions of the ball may be selected so that it may be positioned inside the chamber 13, 17 of the device 1 and/or inside a container or holder located on a structure or vessel. The aerodynamic shape of the life saving device 41 in its compact state may be optimised so that the air flows in a more optimal path over the outer surface of the life saving device 1 when it is dropped from the device 1 or being thrown through the air. A protective layer, e.g. a perforated film or foil, may be wrapped around at least a portion of its outer surface in order to protect the life saving device 41 from any external impacts. The maximum outer diameter of the life saving device 41 in the compact state may be between 10-30cm, preferably between 10-20cm or 20-30cm. The maximum weight of the life saving device 41 may be no more than lOOOg, preferably between 400-800g.

A floating anchor 43 may be coupled to the bottom of the life saving device 41. The floating anchor 43 may be configured as an element having a predetermined weight that the lift saving device always corrects it self when dropped into the water. The anchor 43 may be positioned over the inflating mechanism 42 for protecting the components of the mechanism 42. The anchor 43 may comprise at least one or more holes 44 so that the water may pass through these holes and into contact with the inflating mechanism 42 which located inside the anchor 43.

Fig. 7 shows the life saving device 41 seen from the side. The inflating mechanism 42 may comprise manual activation means in the form of a ring 45 connected to a wire 46 which connected the ring 45 with a release mechanism located in an activation unit 47. A protective cover or layer 48 may be positioned around the anchor and the wire 46. The wire 46 may be placed in a track 49 which may comprise a tear line 50 located in a layer 51 closing off the track 49.

Fig. 8 shows a cross section of the life saving device 41 with the inflating mechanism 42 arranged inside the ball shaped life saving device 41. The inflating mechanism 42 may be encapsulated by the other components of the life saving device 41 so the mechanism is protected against external impacts. The inflating mechanism 42 may be configured to either manually active the inflation process or automatically active the inflation process when it comes into contact with the water.

The inflating mechanism 42 may comprise a container 52 in which one or more fluids is stored, e.g. under pressure. The fluids may be selected so that they generate a chemical reaction that produces gas which is lead into and inflates the chamber. The container 52 may comprise a gas, e.g. C0₂, stored under pressure. The gas is lead into the chamber when the inflating mechanism 42 is activated. Fig. 9 shows an exemplary embodiment of the inflating mechanism 42 which may be configured to be used to inflate a life saving device 41, as shown in fig. 8. The container 52 may have a ball shaped form which comprises a recess 53 extending towards the centre of the ball. The recess 53 may comprise a bottom connected to at least side which in the other end may be connected to the peripheral edge of the container 52. This allows the inflating mechanism 42 to be positioned in the recess 53 so that at least a part of the inflating mechanism is located inside the recess 53. The container 52 may be made of a composite material. The gas used to inflate the chamber may be selected so that it when released into the chamber generates a chemical reaction that produces heat, e.g. up to 60-70°C. This allows the gas to also function as a heat source for the person wearing the life saving device 41.

The activation unit 47 made be arranged inside the recess 53 of the container 52. The activation unit 47 may be configured to perforate the inner wall of the container 52, e.g. the bottom or side of the recess 53. A perforating element 54 in the form of a nee- die may be arranged inside a tube 55 located in the recess 53. The performing element 54 may be configured to perforate the wall so that the gas inside the container 52 may be lead into the chamber. The perforating element 54 may be coupled to a moveable element 56 in the form of a firing pin arranged inside the tube 55. The element 56 may be configured to move the perforating element 54 from a first position to a second po- sition. A spring 57 in the form of an extension spring may be used to move the element 54 so that it perforates the wall of the container 52. One end of the tube 55 may lie against the bottom of the recess 53 and the other end may be closed off by a cover 58. The spring 57 may be arranged between the cover 58 and the moveable element 56. A locking unit 59 may be coupled to the activation unit 47 and may be configured to hold the activation unit 47 in place when not activated. The locking unit 59 may be configured to be unlocked, which actives the activation unit 47 and the perforating element 54 is pushed through the wall of the container 52. The locking unit 59 may comprise a tube 60 arranged parallel to the tube 55 of the activation unit 47. A first moveable element 61 in the form of a rod may be positioned inside the tube and may extend through the cover 58. A recess 62 configured to at least partly receive a second moveable element 63 may be arranged near one end of the element 61. The second element 63 in the form of two balls may be positioned in a tube 64 that connects the tube 55 with the tube 60. The second element 63 may be formed as two balls where one ball engages the element 56 and the other ball engages the first element 61. A spring 65 may be arranged between the cover 58 and the recess 62 so it moves the recess 62 into alignment with the tube 64. When not activated, the recess 62 may be off- set relative to the tube 64 so that one of the balls engages and holds the element 56

Fig. 10 shows the inflating mechanism 42 seen from the top. The first element 61 may be held in a first position by a release mechanism 66 in the form of an arm. The release mechanism 66 may be coupled to the cover 58 in a rotation point 67. The release mechanism 66 may at one end comprise holding means in the form of fingers 68 for holding the first element 61 in the first position. A dissolvable element 69 in the form of a bobbin may be arranged between the fingers 68 and the first element 61. The dissolvable element 69 may be made of salt which dissolves when it comes into contact with the water. The release mechanism 66 may at the other end be coupled to the wire 46 which at the other end is connected to the ring 45. When the wire 46 is pulled, the release mechanism 66 rotates relative to the rotation point 67 and the dissolvable element 69 is moved out of contact with the first element 61. This activates inflating mechanism 42.

Claims

1. An unmanned aerial device (1) comprising

- a body (2) having an aerodynamic shape, wherein the body (2) comprises an upper side (3) and a lower side (4);

- two or more rotors (6, 7, 8, 9) coupled to the body (2), wherein each rotor comprises two or more rotatable rotor blades which is coupled to at least one drive unit by at least one drive shaft;

- at least one control system (11) electrically coupled to the drive unit and at least sen- sor unit (31), wherein the control system (11) is configured to control the flight of the device (1) characterized in that

- the device (1) comprises at least one module (12, 16) coupled to at least one of the sides (3, 4) of the body (2) and is configured to receive and hold one or more equipments (14), wherein the module (12, 16) is electrically coupled to the control system (11) and further configured to release at least one of the equipments (14) upon receiving a control signal from the control system (11).

2. An unmanned aerial device according to claim 1, wherein the module is configured as an interchangeable module (12) capable of being replaced with another module, wherein the interchangeable module (12) comprises a first coupling element configured to be coupled to a second coupling element on the body (2).

3. An unmanned aerial device according to claim 1 or 2, wherein the module (12, 16) comprises one or more chambers (13, 17) configured to at least partly receive the equipment (14), wherein a release mechanism (15, 22, 23) is coupled to the chamber (13, 17) for holding the equipment (14) in place until the release mechanism (15, 22, 23) is activated by the control system (11).

4. An unmanned aerial device according to claim 3, wherein the module (16) extends through the body (2) and the chamber (17) is connected to an opening (18, 19) on the upper and lower sides (20, 21) respectively.

5. An unmanned aerial device according to claim 3 or 4, wherein the release mechanism (23) comprises at least one moveable element (24) acting on the rescue equipment (14), wherein the release mechanism (23) is configured so that the rescue equipment (14) is released from the chamber (17) at a predetermined exit velocity.

6. An unmanned aerial device according to any one of claims 3 or 5, wherein the release mechanism (22) comprises at least one magnetic element (22a) interacting with at least one magnetic element (22b) in the equipment (14). 7. An unmanned aerial device according to any one of claims 1 to 6, wherein the control system (11) comprises a first flight control unit (28) and a second flight control unit (29) electrically coupled to the rotors (6,

7, 8, 9), both of which are electrically coupled to an orientation detection unit (30), wherein the first flight control unit (28) is configured to control the flight in a first state and the second flight control unit (29) is configured to control the flight in a second state.

8. An unmanned aerial device according to any one of claims 1 to 7, wherein the body (2) has a disc shaped configuration in which the rotors (6, 7, 8, 9) are arranged near the periphery (5) of the disc and the module (12, 16) is arranged relative to the centre of the disc.

9. An unmanned aerial device according to any one of claims 1 to 8, wherein the device (1) comprises a second chamber in which a parachute is located, and wherein the parachute may be deployed upon detecting of a failure by the control system (11).

10. An unmanned aerial device according to any one of claims 1 to 9, wherein the control system comprises a data control unit (26) electrically coupled to a wireless communications unit (27) configured to communicate with a remote unit, a central station and/or a second unmanned aerial device via a wireless communication link.

11. An unmanned aerial device according claim 10, wherein the data control unit (26) is electrically coupled to an image capturing unit (32), and wherein the data control unit (26) is configured to analyse the image data from the image capturing unit (32) for recognizing one or more patterns or movements.

12. An unmanned aerial device according to any one of claims 1 to 11, wherein the device (1) comprises an energy source electrically coupled to a charging unit which configured to interact with another power energy source.

13. An unmanned aerial device according to any one of claims 1 to 12, wherein the equipment is rescue equipment (41) packed in a compact state, wherein the rescue equipment is selected from the group of life saving device, personal floating device or a emergency kit.

14. An unmanned aerial device according to claim 13, wherein the rescue equipment (41) comprises an inflating mechanism (42) which is coupled to at least inflatable chamber in the rescue equipment (41) and is configured to inflate that chamber when activated.