Description:FIELD OF INVENTION
[001] The present invention relates to smart intelligent operations of the emergency services that have to carry out during a specific mission to transport trained personnel to remote places where there is disturbance due to natural calamities, to enter in forest/ difficult location to caught the criminals, to do rescue operations, to counter the illegal and anti-national, anti-social activity and where there is no access by road in the quickest possible time. More particularly, the invention for designing of typical slithering platform for Aircraft using composite materials. The aim of the project is to design a platform using composite materials approximating it on a simply supported beam to carry a load of 300 Kg.

BACKGROUND OF INVENTION
[002] Background description includes information that may be useful in understanding the present invention. It is not an admission that any of the information provided herein is prior art or relevant to the presently claimed invention, or that any publication specifically or implicitly referenced is prior art.

[003] Whenever it is not possible to reach certain areas by motorable road by the emergency service people, particularly for the emergency service agency, it is a general practice to take the trained personnel in an Aircraft in a hovering condition, the trained personnel will be asked to slide down at the desired destination. This operation is called the slithering operation. A slithering operation can be carried out both on skid and wheel landing gear of Aircraft versions.
[004] Extended platform used for trained personnel to stand before sliding and to avoid injury due to hitting of skids when sliding down. A boom to hang the rope on which trained personnel can slither down. A suitable rope capable of withstanding the load of two trained personnel s at a time.

[005] Anchoring point as a safety measure. In the present project, attempts have been made to design and developed an extended platform using composite materials and compare the advantages over metallic (conventional material) platforms consisting of sheet stringers in the axial and transverse direction in semi-monocoque constructions. The sandwich composite constructions design not only reduces the weight but also minimizes the number of components hence enhancing safety. Use of advanced composite materials like carbon and honeycomb core provides the required strength, stiffness and dynamic properties at a minimum weight penalty.

[006] Advanced Composite Main Rotor Flex Beam: The flex beam connects the main rotor to the main rotor blade. The composite flex beam is used in the bearing fewer rotor hubs in the main rotor system of the Aircraft with the evolution of advanced composites, the flexibility of designing bearing less or hinge fewer rotor systems become a reality

[007] Design Details: During the design of the flex beam the following consideration is needed, Flap-lag-torsion deformation must be accommodated through the flex beam. There should be a balance between maneuverability and dynamic vibrations. Hub size must be kept at a minimum to reduce the weight and hub drag. To maximize in-plane damping, the optimum tailoring at the damper and in-plane flex beam deformation must be obtained. Flex beam design criterion includes rotor shaft/mast/hub impendence characteristics. Cross-section of flex beam. Composite material type and configuration. Hub and blade attachments and configurations. The material used: S2-fibreglass impregnated with a 350F curing(toughened epoxy resin system)

[008] Composite Fuselage: An innovative composite fuselage design concept was developed, which will meet the structural and flight loads requirement and satisfy the design goals for less weight and crashworthiness. The fuselage is fabricated using a composite sandwich construction and consist of a relatively rigid upper section or passenger's cabin, including a stiff structural floor and a frangible lower section that encloses the crash energy system. Due to the very high stiffness and strength of the fuselage, there is very little chance of structural collapse.

[009] However, these techniques bring about user inconvenience in that the invention for designing of typical slithering platform for Aircraft using composite materials which aim of the project is to design a platform using composite materials approximating it on a simply supported beam to carry a load of 300 Kg.

[0010] The patent application number US6497553B2 discloses Vortex attractor which is described as A vortex generating apparatus that has the capability of attracting and removably adhering to one or more solid objects. The apparatus comprises an impeller housed within a shell. The vortex attractor generates a vortical fluid flow generally in the form of a helical or spiral-shaped flow. The fluid flow creates a low-pressure region extending from the impeller end of the device. This low-pressure region is contained by the walls of the fluid flow, thus directing the attractive forces toward a surface and minimizing the effects of ambient fluid on the system. When the surface is part of a stationary object, wall, floor or ceiling, the vortex attractor may move toward and adhere to the surface. When the surface is part of a movable object, the vortex attractor may attract the object and maintain the attracted position.

[0011] Yet another disclosure, the patent application number US20080087762A1 discloses as System, method, and apparatus for hybrid dynamic shape buoyant, dynamic lift-assisted air vehicle, employing aquatic-like propulsion which is Disclosed A method and system for air flight is shown. The blended lifting body system includes a lift module, a propulsion module, a payload module and a control system. A conventional control system morphs the other modules through the variable buoyant lift, internal structures and a flexible exterior, and varies bio-inspired oscillation in the propulsion module to facilitate takeoff, flight and landing. The hybrid dynamic/morphing shape buoyant, dynamic lift-assisted (hybrid) air vehicle, employing aquatic-like (e.g. fin) propulsion was discussed, with many variations and examples.

[0012] Yet another disclosure, The patent application number US20020182077A1 discloses Vortex attractors with propellers which are described as A vortex generating apparatus that has the capability of attracting and removably adhering to one or more solid objects. The apparatus comprises an impeller housed within a shell. The vortex attractor generates a vortical fluid flow generally in the form of a helical or spiral-shaped flow. The fluid flow creates a low-pressure region extending from the impeller end of the device. This low-pressure region is contained by the walls of the fluid flow, thus directing the attractive forces toward a surface and minimizing the effects of ambient fluid on the system. When the surface is part of a stationary object, wall, floor or ceiling, the vortex attractor may move toward and adhere to the surface. When the surface is part of a movable object, the vortex attractor may attract the object and maintain the attracted position.

[0013] Further limitations and disadvantages of conventional approaches will become apparent to one of skill in the art through comparison of described systems with some aspects of the present disclosure, as outlined in the remainder of the present application and concerning the drawings.

[0014] In some embodiments, the numbers expressing quantities or dimensions of items, and so forth, used to describe and claim certain embodiments of the invention are to be understood as being modified in some instances by the term “about.” Accordingly, in some embodiments, the numerical parameters outlined in the written description and attached claims are approximations that can vary depending upon the desired properties sought to be obtained by a particular embodiment. In some embodiments, the numerical parameters should be construed in light of the number of reported significant digits and by applying ordinary rounding techniques. Notwithstanding that the numerical ranges and parameters setting forth the broad scope of some embodiments of the invention are approximations, the numerical values outlined in the specific examples are reported as precisely as practicable. The numerical values presented in some embodiments of the invention may contain certain errors necessarily resulting from the standard deviation found in their respective testing measurements.

[0015] As used in the description herein and throughout the claims that follow, the meaning of “a,” “an,” and “the” includes plural reference unless the context dictates otherwise. Also, as used in the description herein, the meaning of “in” includes “in” and “on” unless the context dictates otherwise.

[0016] Groupings of alternative elements or embodiments of the invention disclosed herein are not to be construed as limitations. Each group member can be referred to and claimed individually or in any or a combination with other members of the group or other elements found herein. One or more members of a group can be included in, or deleted from, a group for reasons of convenience and/or patentability. When any such inclusion or deletion occurs, the specification is herein deemed to contain the group as modified thus fulfilling the written description of all groups used in the appended claims.

SUMMARY OF INVENTION
[0017] The present invention relates to smart intelligent operations the emergency services agencies have to carry out during a specific mission is to transport trained personnel to remote places where there is no access by road in the quickest possible time. More particularly, the invention for designing of typical slithering platform for Aircraft using composite materials which aim of the project is to design a platform using composite materials approximating it on a simply supported beam to carry a load of 300 Kg.

[0018] Whenever it is not possible to reach certain areas by motorable road by the emergency service people, particularly for the emergency service agencies, it is a general practice to take the trained personnel in an Aircraft in a hovering condition, the trained personnel will be asked to slide down at the desired destination. This operation is called the slithering operation. The slithering operation can be carried out both on skid and wheel landing gear of Aircraft versions.

[0019] Extended platform used for trained personnel to stand before sliding and to avoid injury due to hitting of skids when sliding down. A boom to hang the rope on which trained personnel can slither down. A suitable rope capable of withstanding the load of two trained personnel at a time.

[0020] Anchoring point as a safety measure. In the present project, attempts have been made to design and developed an extended platform using composite materials and compare the advantages over metallic (conventional material) platforms consisting of sheet stringers in the axial and transverse direction in semi-monocoque constructions. The sandwich composite constructions design not only reduces the weight but also minimizes the number of components hence enhancing safety. Use of advanced composite materials like carbon and honeycomb core provides the required strength, stiffness and dynamic properties at a minimum weight penalty.

[0021] Advanced Composite Main Rotor Flex Beam: The flex beam connects the main rotor to the main rotor blade. The composite flex beam is used in the bearing fewer rotor hubs in the main rotor system of the Aircraft with the evolution of advanced composites, the flexibility of designing bearing less or hinge fewer rotor systems become a reality

[0022] Design Details: During the design of the flex beam the following consideration is needed, Flap-lag-torsion deformation must be accommodated through the flex beam. There should be a balance between maneuverability and dynamic vibrations. Hub size must be kept at a minimum to reduce the weight and hub drag. To maximize in-plane damping, the optimum tailoring at the damper and in-plane flex beam deformation must be obtained. Flex beam design criterion includes rotor shaft/mast/hub impendence characteristics. Cross-section of flex beam. Composite material type and configuration. Hub and blade attachments and configurations. The material used: S2-fibreglass impregnated with a 350F curing (toughened epoxy resin system)
[0023] Composite Fuselage: An innovative composite fuselage design concept was developed, which will meet the structural and flight loads requirement and satisfy the design goals for less weight and crashworthiness. The fuselage is fabricated using a composite sandwich construction and consist of a relatively rigid upper section or passenger's cabin, including a stiff structural floor and a frangible lower section that encloses the crash energy system. Due to the very high stiffness and strength of the fuselage, there is very little chance of structural collapse.

[0024] In this work using composite material reduction in weight is possible by cutting down some of the layers at the desired lengths following constraints like symmetry and ply orientation. The reverse factor which is obtained for fibre and matrix in the analysis is more than sufficient to take large loads in any extreme case. Weight reduction is about 60% when compared with steel and 30% when compared with aluminium alloy.

[0025] The designed platform has higher strength than the recommended strength as per design standards. The cost of producing the composite platform may be higher but prove to be useful on the following considerations. Design safety. Weight reduction. More effective structure. Higher levels of functionality.

[0026] In some space applications, the honeycomb cell must be vented to allow the entrapped air to escape. There are several methods used to vent the honeycomb cores. An aluminium honeycomb can have the foil perforated. Here needles on a cylinder, which rolls over the flat foil, puncture the foil. This operation is done after the node glue lines have been printed onto the foil after perforation hard rubber rollers flatten oat the metal that was upset during perforation this results in the holes in the aluminium foils the holes in the nodes tend to be blocked by node adhesive when the block is pressed and cured the needles are in diagonal rows around the rolls.

[0027] Further limitations and disadvantages of conventional approaches will become apparent to one of skill in the art through comparison of described systems with some aspects of the present disclosure, as outlined in the remainder of the present application and concerning the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS
[0028] The accompanying drawings are included to provide a further understanding of the present disclosure and are incorporated in and constitute a part of this specification. The drawings illustrate exemplary embodiments of the present disclosure and, together with the description, serve to explain the principles of the present disclosure.

[0029] FIG. 1 illustrates an exemplary representation of a detailed view of the Invention.
DETAILED DESCRIPTION
[0030] The following is a detailed description of embodiments of the disclosure depicted in the accompanying drawings. The embodiments are in such detail as to communicate the disclosure. However, the amount of detail offered is not intended to limit the anticipated variations of embodiments; on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the present disclosure as defined by the appended claims.

[0031] Embodiments of the present invention include various steps, which will be described below. The steps may be performed by hardware components or may be embodied in machine-executable instructions, which may be used to cause a general-purpose or special-purpose processor programmed with the instructions to perform the steps. Alternatively, steps may be performed by a combination of hardware, software, and firmware and/or by human operators.

[0032] Furthermore, embodiments may be implemented by hardware, software, firmware, middleware, microcode, hardware description languages, or any combination thereof. When implemented in software, firmware, middleware, or microcode, the program code or code segments to perform the necessary tasks (e.g., a computer program product) may be stored in a machine-readable medium.

[0033] Various terms as used herein are shown below. To the extent a term used in a claim is not defined below, it should be given the broadest definition persons in the pertinent art have given that term as reflected in printed publications and issued patents at the time of filing.

[0034] In general, the parameters governing the choice of a particular type of composite material for aircraft application can be grouped under the technical requirements and competitive unit cost. The type of fibre is mainly determined by the component structural classification and on basic fibre material cost, while resin choice is heavily dominated by the environmental condition for which the component is subjected. The high impact resistance and durability required for components in airframe areas will influence both resin and fibre. Thus, any structure components made of composite fibre are oriented in such a way as to sustain the applied load. The stress-strain diagram of composite material shows that the material is elastic up to sudden failure whereas conventional metal exhibits the phenomena of plastic flow which allows it to yield before failure. Thus, composites exhibit brittle material characteristics as shown in fig.1

[0035] The invention is not restricted to the details of the foregoing embodiment(s). The invention extends to any novel one, or any novel combination, of the features, disclosed in this specification (including any accompanying claims, abstract and drawings), or to any novel one, or any novel combination, of the steps of any method or process so disclosed.

[0036] While the foregoing describes various embodiments of the invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof. The scope of the invention is determined by the claims that follow. The invention is not limited to the described embodiments, versions, or examples, which are included to enable a person having ordinary skill in the art to make and use the invention when combined with information and knowledge available to the person.
 
, Claims:We claim
1. A System of slithering platform for Aircraft using composite materials comprising:
Advanced Composite Main Rotor Flex Beam;
the honeycomb cell;
an extended platform using composite materials and compare the advantages over metallic (conventional material) platforms consisting of sheet stringers in the axial and transverse direction in semi-monocoque constructions wherein The sandwich composite constructions design not only reduces the weight but also minimizes the number of components hence enhancing safety wherein Use of advanced composite materials like carbon and honeycomb core provides the required strength, stiffness and dynamic properties at a minimum weight penalty;
an operations wherein the emergency services have to carry out during a specific mission is to transport personnel to remote places where there is no access by road in the quickest possible time wherein Aviation Department uses the Aircrafts for the said mission wherein the personnel are carried in the Aircraft to a predetermined destination and are made to slide down the Aircraft with the Aircraft in hovering condition at about 200 feet to 300 feet above the ground.
2. The system as claimed in claim 1, wherein the system has weight reduction is about 60% when compared with steel and 30% when compared with aluminium alloy.
3. The system as claimed in claim 1, wherein the system has a designed Constant refrigeration of resins before use-in order to minimize polymerization as the resins have limited shelf life.
4. The system as claimed in claim 1, wherein the system has Monitoring of material life cycle- as the properties change even if the material is stored properly.
5. The system as claimed in claim 1, wherein the system has availability of the specific manufacturing equipment for handling and curing of composites before selection of the material.

6. The system as claimed in claim 1, wherein Advanced Composite Main Rotor Flex Beam connects the main rotor to the main rotor blade wherein the composite flex beam is used in the bearing fewer rotor hubs in the main rotor system of the Aircraft with the evolution of advanced composites, the flexibility of designing bearing less or hinge fewer rotor systems become a reality; wherein during the design of the flex beam the following consideration is needed, Flap-lag-torsion deformation must be accommodated through the flex beam;

Establishing a balance between maneuverability and dynamic vibrations. Hub size must be kept at a minimum to reduce the weight and hub drag;
to maximize in-plane damping, the optimum tailoring at the damper and in-plane flex beam deformation must be obtained;
Flex beam design criterion includes rotor shaft/mast/hub impendence characteristics;
Composite material type and configuration. Hub and blade attachments and configurations. The material used: S2-fibreglass impregnated with a 350F curing (toughened epoxy resin system)
using an innovative composite fuselage design concept was developed, which will meet the structural and flight loads requirement and satisfy the design goals for less weight and crashworthiness, wherein the fuselage is fabricated using a composite sandwich construction and consist of a relatively rigid upper section or passenger's cabin, including a stiff structural floor and a frangible lower section that encloses the crash energy system, and wherein due to the very high stiffness and strength of the fuselage, there is very little chance of structural collapse.

7. The system as claimed in claim 1, wherein composite material reduction in weight is possible by cutting down some of the layers at the desired lengths following constraints like symmetry and ply orientation, the reverse factor which is obtained for fibre and matrix in the analysis is more than sufficient to take large loads in any extreme case, weight reduction is about 60% when compared with steel and 30% when compared with aluminium alloy.

8. The system as claimed in claim 1, wherein the honeycomb cell are vented to allow the entrapped air to escape.

9. The system as claimed in claim 1, wherein to vent the honeycomb cores can be done by multiple methods, here needles on a cylinder, which rolls over the flat foil, puncture the foil, the said operation operation is done after the node glue lines have been printed onto the foil after perforation hard rubber rollers flatten oat the metal that was upset during perforation this results in the holes in the aluminium foils the holes in the nodes tend to be blocked by node adhesive when the block is pressed and cured the needles are in diagonal rows around the rolls.