BACKGROUND

Technical Field of Invention

[001] The embodiments herein generally relate to an emergency support system and particularly relates to an airborne rescue lift for airlifting victims in emergency situations. The embodiments herein more particularly relate to an airborne recue lift with collapsible cage structure with capability to airlift more than 6 peoples simultaneously.

Description of Related Art

[002] A helicopter rescue basket is a basket suspended below a helicopter in order to rescue people from a fire or other disaster site. There are two main types of helicopter baskets. The smaller, more common type is used by rescuers to lift a person up from ground or water into the helicopter. The second type has wider base and is able to fit five people or more. It allows a large group of people to be rescued from a fire or other emergency site, without needing to load them into the helicopter itself. It enables the helicopter to load a large group without landing. The helicopter hovers over the site and rests the basket on the ground or other surface.

[003] To make a swift rescue operation, the prior arts are being adapted to house more passengers. One of such prior arts discloses a compact rescue lift device adapted to be deployed from an elevated location, having a central spine with upper and lower portions, where the upper portion of the spine includes a means for coupling the device to a structure and the lower portion includes a plurality of seating surfaces which include both supporting and retaining portions, with the device also including a plurality of hand grips, where the device is adapted to carry multiple victims at a time. [004] Another prior art discloses a helicopter-carried rescue apparatus including a collapsible net assembly which is adapted to be carried in a fully collapsed condition when the helicopter equipped with the rescue apparatus is in cruise toward the scene of a disaster and which is fully expanded at the scene for being capable of picking up a number of endangered lives such as occupants of a building on fire, shipwreck survivors, survivors from ditched aircraft, flood victims, injured mountain climbers, lives in snow storms, etc. The net assembly can be automatically expanded and collapsed by remote control from the helicopter in flight or from any spot outside the helicopter and the net assembly and can further be moved between an upright position suitable for accommodating relieved survivors and a lying position suitable for being carried by the helicopter when the helicopter is rushing to a scene.

[005] However, the rescue lifts in the prior arts have limitation of carriage of victims to 4-5 at a time. Further, the helicopter or an aircraft has to move slowly during a return journey from a rescue operation to allow least swinging effect and safe carriage of rescued victims. But slow movement decreases an overall rescue operation and still leading to significant casualties.

[006] In the view of foregoing, there is a need for an airborne rescue system enabled with a portable and space optimized lift mechanism for carrying more than 6 victims simultaneously. Also, there is a need for an airborne system enabled with a lift mechanism retracted near aircraft body allowing fast transportation to increase an overall saviour rate by a single aircraft.

[007] The above-mentioned shortcomings, disadvantages and problems are addressed herein, as detailed below.

OBJECTS OF THE INVENTION

[008] The primary objective of the embodiments herein is to provide an airborne rescue system enabled with a portable and space optimized lift mechanism for carrying more than 6 victims simultaneously. [009] Another object of the embodiments herein is to provide an airborne system enabled with a lift mechanism retracted near aircraft body allowing fast transportation to increase an overall saviour rate by a single aircraft.

[0010] These and other objects and advantages of the embodiments herein will become readily apparent from the following detailed description taken in conjunction with the accompanying drawings.

SUMMARY OF THE INVENTION

[0011] The various embodiments herein provide an airborne rescue lift system comprising a rescue cage, a latching mechanism, a plurality of sensors, a central control unit (CCU), and a plurality of ladders. The rescue cage is held to the lower body surface of an aircraft through a pulley mechanism. The rescue cage comprises a roof, an intermediate support structure, a floor, and a wind screen. The roof is connected to the pulley mechanism and has a semi-drum structure. The intermediate support structure is connected to an outer rim of the roof. The intermediate support structure comprises a plurality of support elements. The intermediate support structure connects the roof and the floor. The wind screen is connected to the roof in between each support element. The latching mechanism holds the rescue cage to an aircraft's base in a loaded as well as a no-load condition. The plurality of sensors comprises a weight sensor, a proximity sensor and an infrared (IR) imaging sensor. The weight sensor and the IR imaging sensor are connected to the floor of the rescue cage. The proximity sensor is connected to the roof of the rescue cage. The CCU is provide in an aircraft cockpit and is connected with the intermediate support structure and the plurality of sensors. The plurality of ladders are connected to the roof and the floor. Each ladder fitted to the roof and the floor at a horizontal angular displacement of 90°. The CCU gathers routes a command of lowering the rescue cage to the pulley mechanism. The rescue cage expands after receiving the command in simultaneous function with lowering of the rescue cage. The plurality of sensors sends back a data of total weight of the loaded victims on the floor and presence of victims in water. The recue cage is pulled back as the plurality of sensors after a threshold weight is sensed on the floor. The latching mechanism automatically arrests the rescue cage after reaching of the rescue cage in proximity to the bottom surface of the aircraft as detected by the proximity sensor.

[0012] According to one embodiment herein, each support element comprises at- least two bars hinged with each other to form a X- shape and a pair of actuators. The pair of actuators are connected at a portion of the scissor structure housed in the roof. The connection of the actuators with the scissor structure is in a way allowing widening an angle between tips of the bars by moving away from each other and reducing an angle between the tips by moving towards each other. The widening of angle of the tips allows to collapse the floor inside the roof and the reducing of angle allows to expand the floor out of the roof to form a cage design.

[0013] According to one embodiment herein, each support element is made up of pneumatically expandable bars. An expansion of each bar allows to form a cage design.

[0014] According to one embodiment herein, each support element is equally displaced in an angular manner from the adjacent support element.

[0015] According to one embodiment herein, the latching mechanism comprises a rotor, a male magnetic catcher and a female magnetic catcher. The male magnetic catcher is attached to the roof of the rescue cage. The female magnetic catcher is connected to the bottom surface of the aircraft. The male and female magnetic catchers hold each other through a magnet force.

[0016] According to one embodiment herein, the rotor rotates the male magnetic catcher in a clockwise direction away from the female magnetic catcher to release the recue cage. The rotor rotates the male magnetic catcher in an anti-clockwise direction towards the female magnetic catcher to dock the recue cage with the aircraft. [0017] According to one embodiment herein, the latching mechanism comprises an airlock unit further comprising a male protrusion connected to the roof and a female airlock chamber connected to the bottom surface of the aircraft.

[0018] According to one embodiment herein, the male protrusion unit protrudes inside the female airlock chamber and rotates in a clockwise direction to lock with the aircraft after receiving a command from the CCU on the basis of signal provided by the proximity sensor. The male protrusion unit rotates in an anti-clockwise direction and retracts from the female airlock chamber to undock from the aircraft.

[0019] According to one embodiment herein, the threshold weight over the floor is 800kg.

[0020] According to one embodiment herein, the floor and the roof of the rescue cage comprise an illumination strip, a plurality of flash lights, and an audible alert unit.

[0021] These and other aspects of the embodiments herein will be better appreciated and understood when considered in conjunction with the following description and the accompanying drawings. It should be understood, however, that the following descriptions, while indicating preferred embodiments and numerous specific details thereof, are given by way of illustration and not of limitation. Many changes and modifications may be made within the scope of the embodiments herein without departing from the spirit thereof, and the embodiments herein include all such modifications.

BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The other objects, features and advantages will occur to those skilled in the art from the following description of the preferred embodiment and the accompanying drawings in which: [0023] FIG. la illustrates an airborne rescue lift system in a resting mode attached with the aircraft, according to one embodiment herein.

[0024] FIG. lb and lc illustrates an airborne rescue lift system in a rescue mode attached with an aircraft and without an aircraft respectively, according to one embodiment herein.

[0025] FIG. 2 illustrates a magnetic latching mechanism for holding the rescue lift system during an in-flight condition, according to one embodiment herein.

DETAILED DESCRIPTION OF THE DRAWINGS

[0026] In the following detailed description, a reference is made to the accompanying drawings that form a part hereof, and in which the specific embodiments that may be practiced is shown by way of illustration. The embodiments are described in sufficient detail to enable those skilled in the art to practice the embodiments and it is to be understood that the logical, mechanical and other changes may be made without departing from the scope of the embodiments. The following detailed description is therefore not to be taken in a limiting sense.

[0027] FIG. la illustrates an airborne rescue lift system in a resting mode attached with the aircraft, according to one embodiment herein. FIG. lb and lc illustrates an airborne rescue lift system 100 in a rescue mode attached with an aircraft and without an aircraft 101 respectively, according to one embodiment of the present invention. With respect to FIG. la-lc, the airborne rescue lift system 100 comprising a rescue cage 103, a latching mechanism, a plurality of sensors, a central control unit (CCU), and a plurality of ladders 107. The rescue cage is held to the lower body surface of an aircraft through a pulley mechanism 105. The rescue cage comprises a roof 104, an intermediate support structure 103, a floor 105, and a wind screen 106. The roof is connected to the pulley mechanism and has a semi-drum structure. The intermediate support structure is connected to an outer rim of the roof. The intermediate support structure comprises a plurality of support elements. The intermediate support structure connects the roof and the floor. The wind screen is connected to the roof in between each support element. The latching mechanism holds the rescue cage to an aircraft' s base in a loaded as well as a no-load condition. The plurality of sensors comprises a weight sensor, a proximity sensor and an infrared (IR) imaging sensor. The weight sensor and the IR imaging sensor are connected to the floor of the rescue cage. The proximity sensor is connected to the roof of the rescue cage. The CCU is provide in an aircraft cockpit and is connected with the intermediate support structure and the plurality of sensors. The plurality of ladders are connected to the roof and the floor. Each ladder fitted to the roof and the floor at a horizontal angular displacement of 90°. The CCU gathers routes a command of lowering the rescue cage to the pulley mechanism. The rescue cage expands after receiving the command in simultaneous function with lowering of the rescue cage. The plurality of sensors sends back a data of total weight of the loaded victims on the floor and presence of victims in water. The recue cage is pulled back as the plurality of sensors after a threshold weight is sensed on the floor. The latching mechanism automatically arrests the rescue cage after reaching of the rescue cage in proximity to the bottom surface of the aircraft as detected by the proximity sensor.

[0028] FIG. Id illustrates a magnetic latching mechanism for holding the rescue lift system during an in-flight condition, according to one embodiment herein. With respect to FIG. Id, the latching mechanism 108 comprises a rotor, a male magnetic catcher and a female magnetic catcher, wherein the male magnetic catcher is attached to the roof of the rescue cage. The female magnetic catcher is connected to the bottom surface of the aircraft. The male and female magnetic catchers hold each other through a magnet force.

[0029] According to one embodiment herein, the rotor rotates the male magnetic catcher in a clockwise direction away from the female magnetic catcher to release the recue cage. The rotor rotates the male magnetic catcher in an anti-clockwise direction towards the female magnetic catcher to dock the recue cage with the aircraft. [0030] According to one embodiment herein, each support element comprises at-least two bars hinged with each other to form a X- shape and a pair of actuators. The pair of actuators are connected at a portion of the scissor structure housed in the roof. The connection of the actuators with the scissor structure is in a way allowing widening an angle between tips of the bars by moving away from each other and reducing an angle between the tips by moving towards each other. The widening of angle of the tips allows to collapse the floor inside the roof and the reducing of angle allows to expand the floor out of the roof to form a cage design.

[0031] According to one embodiment herein, each support element is made up of pneumatically expandable bars. An expansion of each bar allows to form a cage design.

[0032] According to one embodiment herein, each support element is equally displaced in an angular manner from the adjacent support element.

[0033] According to one embodiment herein, the latching mechanism comprises an airlock unit further comprising a male protrusion connected to the roof and a female airlock chamber connected to the bottom surface of the aircraft.

[0034] According to one embodiment herein, the male protrusion unit protrudes inside the female airlock chamber and rotates in a clockwise direction to lock with the aircraft after receiving a command from the CCU on the basis of signal provided by the proximity sensor. The male protrusion unit rotates in an anti-clockwise direction and retracts from the female airlock chamber to undock from the aircraft.

[0035] According to one embodiment herein, the threshold weight over the floor is 800 Kg.

[0036] According to one embodiment herein, the floor and the roof of the rescue cage comprise an illumination strip, a plurality of flash lights, and an audible alert unit.

[0037] The rescue lift system is attached at a bottom of a helicopter refitted for rescue operation. A contracted rescue lift system is mounted on a platform of 6 feet height. The platform is pulled below bottom of helicopter when it is in landed position and raised near to the magnetic latching mechanism, by a screw jack of platform. An alignment of a centre of gravity of the rescue lift system is made of centre of gravity of the helicopter. After successful alignment, the magnetic latching mechanism is magnetized, which in turn attracts the top of rescue cage and hold it firmly.

[0038] To lower the rescue cage, the magnetic latching mechanism is demagnetized to set free the rescue cage. The lowering of the rescue cage is done by the pulley mechanism centrally attached to the rescue cage. In lowering condition, the rescue cage expands into full size through the intermediate support structure, the expanded rescue cage allows nearly 8 victims with or without assistance of a rescue crew. The rescue cage assesses optimal weight on the floor and then pull back towards the helicopter bottom. After reaching the helicopter bottom the magnetic latching is re-magnetized to hold the rescue cage firmly to the helicopter body.

[0039] The rescue lift system allows more no. of victims to be transported simultaneously. Also, the rescue cage is latched closer to the helicopter, hence it nullifies swinging effect allowing a faster travel speed, thus leading quick turn-around time for the helicopter leading to save more no. of victims through the same helicopter. Also, the rescue lift system contracts and hence do not create any hindrance to the helicopter fight in no-use condition. Further, due to the adjustable height nature of the rescue cage, the same system can be used in multiple emergency situations.

[0040] It is to be understood that the phraseology or terminology employed herein is for the purpose of description and not of limitation. Therefore, while the embodiments herein have been described in terms of preferred embodiments, those skilled in the art will recognize that the embodiments herein can be practiced with modification within the spirit and scope of the claims.