TECHNICAL FIELD

[0001] The present disclosure relates to the field of stability systems in planes. More particularly, the present disclosure relates to an aeroplane multipurpose wing stability system.

BACKGROUND

[0002] Generally, the wing of a plane is used for lifting the plane and controlling its motion in air. The thrust is generated by the propellers or the jet engines speedup the plane and it creates the lifting power on the wings. The horizontal stabilizer which is located at back of the plane is used for plane stability purpose and lifting the plane at rear portion. These wing systems are fixed to the main body of the plane and these do not show any kind of flexible movements. The sub systems located on a wing, called as flaps and slats are used for lifting the plane, spoilers are used for landing by increasing the dragging of plane and the ailerons are used for rolling the plane. The elevators located on horizontal stabilizer are used to change the pitch of a flight up and down and the rudders located on the vertical stabilizer are used to change the yaw that is turn the plane right to left or vice versa. But in most of the cases the wings are not participated in controlling system of a plane in terms of rolling, pitch changing and turning the plane and these wings and the horizontal stabilizers are used only for the purpose of lifting the plane in air.

[0003] The existing subsystems of the wings possess flaps, elevators and etc. are smaller in size and they are not in a position to control the flight in critical situations like heavy rain season, high wind flow, weather issues and control lost due to huge weight and speed and landing, take off issues and the like. By the existing subsystems, rolling the aeroplane body with passengers and heavy cargo has some limits and cannot roll the plane body more than certain permissible limits whenever it is required. The plane body may not be possible to keep stable without rolling and allowing the wings only to roll on both the sides up to the required limits and changing the pitch of a plane by means of wings and may not possible to keep the plane body stable while changing the yaw of a plane and pitch by means of wings. Without the support of sub systems like the spoilers, elevators, flaps and etc. wings and the horizontal stabilizers cannot be used as a take -off supporting system, controlling system and landing break system.

[0004] Conventionally, in most of the planes the angle and space line between jet engines or the propellers that are fixed to the plane wings with respect to the plane body remains same in all the positions and its angle of thrust generated by the engine systems is always parallel to the body. By using the existing methods it is not possible to change the angle of thrust generated by jet engines fixed to the wings with respect to the plane body while changing its direction of yaw (by means of rudders located on the vertical stabilizers).

[0005] In the light of aforementioned discussion there exists a need an aeroplane multipurpose wing stability system.

BRIEF SUMMARY

[0006] The following presents a simplified summary of the disclosure in order to provide a basic understanding to the reader. This summary is not an extensive overview of the disclosure and it does not identify key/critical elements of the disclosure or delineate the scope of the disclosure. Its sole purpose is to present some concepts disclosed herein in a simplified form as a prelude to the more detailed description that is presented later.

[0007] A more complete appreciation of the present disclosure and the scope thereof can be obtained from the accompanying drawings which are briefly summarized below and the following detailed description of the presently preferred embodiments.

[0008] Exemplary embodiments of the present disclosure are directed towards an aeroplane multipurpose wing stability system. [0009] According to an exemplary aspect, the system includes a wing shell connected to a fuselage of the aeroplane configured with a wing socket for providing flexible movements to the wings of the aeroplane, whereby the wings coupled to the fuselage of the aeroplane depends on centre of gravity.

[0010] According to an exemplary aspect, the system includes a yaw line socket internally incorporated on top side and lower side of the wing shell with a yaw line axis configured to allow free rotation in both sides of the yaw line socket, the rotation of the yaw line socket supported by a plurality of bearings and an actuator connected at an inside of the yaw line socket.

[0011] According to an exemplary aspect, the system includes a saw wheel coupled to the actuator by a wheel connector configured to provide rotations to the aeroplane wings in required directions by keeping the fuselage of the aeroplane in stable.

[0012] According to an exemplary aspect, the system includes a wing roll wheel coupled to an elevated pitch axis line configured to maintain sustainable of heavy pressure and weight of the aeroplane wings, the wing roll wheel freely hanged in longitudinal direction in a provided space in the wing shell at certain height.

[0013] According to an exemplary aspect, the system includes the central yaw axis configured to allow the rotation to the aeroplane wings in a predetermined extent and up to predetermined degrees depending on side to side yaw changes by supporting of the actuator.

[0014] According to an exemplary aspect, the system includes a central elevated pitch axis oriented in longitudinal direction of the aeroplane fuselage configured to connect the wing roll wheel at a front end and a back end at the link in longitudinal direction.

[0015] According to an exemplary aspect, the system includes a wheel shaped shell configured to provide a required internal space by a plurality of elevator wheel sockets to arrange the wing roll wheel inside into it. [0016] According to an exemplary aspect, the system includes the elevator wheel sockets configured to provide required space for an elevation wheel to rotate in 360 degrees vertically in both the sides at one corner of the wing roll wheel. The elevation wheel coupled to the wing roll wheel at a lower surface configured to convert a source of energies into motion energy for rotating the elevation wheel in a required direction.

[0017] According to an exemplary aspect, the system includes a central wing frame coupled with a wing roll wheel by two side trunks prolonging transversely towards the wing shell side openings configured to form a complete wing frame of the aeroplane.

[0018] According to an exemplary aspect, the system includes two or more pitch elevator wheels coupled to the elevator wheel configured to provide pitch movements in up and down rotations of the aeroplane wing.

[0019] According to an exemplary aspect, the system includes roll elevator wheel coupled to the elevator wheel configured to provide rolling movements to the elevator wheel.

[0020] According to an exemplary aspect, the system includes a horizontal stabilizer configured to keep the aeroplane fuselage in stable position at the movements of the wings.

[0021] According to an exemplary aspect, the system includes the aeroplane wing rotations depend on the levels of the elevation of the elevator wheel.

BRIEF DESCRIPTION OF DRAWINGS

[0022] Other objects and advantages of the present disclosure will become apparent to those skilled in the art upon reading the following detailed description of the preferred embodiments, in conjunction with the accompanying drawings, wherein like reference numerals have been used to designate like elements, and wherein: [0023] FIG. 1 is a diagram of an aeroplane multipurpose wing stability system, according to an embodiment of the present disclosure.

[0024] FIG. 2 is a diagram of an arrangement of the wing roll wheel at the wings of the aeroplane, according to an embodiment of the present disclosure.

[0025] FIG. 3 is a diagram of an arrangement for coupling the wing roll wheel to the central wing frame of the aeroplane, according to an embodiment of the present disclosure.

[0026] FIG. 4A is a diagram of an arrangement of an elevator wheel coupled to the pitch elevator wheels, according to an embodiment of the present disclosure.

[0027] FIG. 4B and 4C depicts diagrams of the aeroplane wing rotations, according to an embodiment of the present disclosure.

[0028] FIG. 5A depicts a diagram of an arrangement of an elevator wheel coupled to the roll elevator wheels, according to an embodiment of the present disclosure.

[0029] FIG. 5B and 5C depicts diagrams of the roll movements in wings, according to an embodiment of the present disclosure.

[0030] FIG. 6 depicts a diagram of elevation levels of elevator wheel, according to an embodiment of the present disclosure.

DETAILED DESCRIPTION

[0031] It is to be understood that the present disclosure is not limited in its application to the details of construction and the arrangement of components set forth in the following description or illustrated in the drawings. The present disclosure is capable of other embodiments and of being practiced or of being carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.

[0032] The use of "including", "comprising" or "having" and variations thereof herein is meant to encompass the items listed thereafter and equivalents thereof as well as additional items. The terms "a" and "an" herein do not denote a limitation of quantity, but rather denote the presence of at least one of the referenced item. Further, the use of terms "first", "second", and "third", and the like, herein do not denote any order, quantity, or importance, but rather are used to distinguish one element from another.

[0033] FIG. 1 depicts a diagram 100 of an aeroplane multipurpose wing stability system, according to an embodiment of the present disclosure. The system 100 includes a vertical stabilizer 101 connected to a fuselage 106 of the aeroplane. The plane wings 102a and horizontal stabilizers 102b, which are configured with in the respective shells 104a and 104b. The wing shell 104a and the horizontal stabilizer shell 104b are connected to a fuselage 106 of the aeroplane. Here the fuselage 106 may be referred as a body of the aeroplane without limiting the scope of the disclosure. The wing shells 104a and 104b are connected to the fuselage of the aeroplane according to the type of the wing such as low wing, mid wing, high wing and the like without limiting the scope of the disclosure. This wing shell 104a system is in semi rectangular shell shaped without limiting the scope of the disclosure made up of light and thick metal normally used in planes body manufacturing and it is closed in all the directions except on two sides where the wings are connected. This wing shell 104a system is moulded and designed in such a way that this shell allows free space for the wings to show the flexible movements.

[0034] As shown in FIG.l, the trunks of the wings 102a and the horizontal stabilizer 102b possess wing sockets 108a and the horizontal stabilizer socketl08b. These two sockets 108a and 108b projected towards outside at the end of the wings 102a and 102b.

[0035] FIG. 2 depicts a diagram 200 of an arrangement of the wing roll wheel at the wings of the aeroplane, according to an embodiment of the present disclosure. The arrangement 200 includes a central yaw axis 202 depict vertically at center of a wing shell of the plane, there is a huge, strong and cylindrical yaw rod or line placed vertically. The central yaw axis 202 is strong with a base structure for forming a required wing central structure. The central yaw axis 202 is internally incorporated into a central yaw axis socket208 on top and lower side of a wing shell 204 of the aeroplane. A yaw line socket 208 arranged on top side and lower side of the wing shell 204 in which the central yaw axis 202 is incorporated and it is allowed to rotate freely in the both sides of the yaw line socket 208. The free rotation of the yaw line socket 208 is on both sides such as right side of the aeroplane, left side of the aeroplane, and the like, without limiting the scope of the disclosure and this rotation may be related to change in a yaw line of the aeroplane. Here the yaw line may be referred as side to side turning line of the aeroplane and the like, without limiting the scope of the disclosure. The yaw line socket 208 may be configured with internal bearings for supporting the free rotation. The process of rotation of the central yaw axis 202 is allowed to some extent only, up to few degrees required for side to side yaw changes by a support of an actuator 206 which is internally connected to the cockpit of the aeroplane plane to operate. There is an extension from the central vertical yaw axis 202 which possess a cut-saw steering 210. The cut-saw steering 210 is used to rotate the central yaw axis 202.

[0036] As shown in FIG.2, the actuator 206 is coupled to the central yaw axis 202 at cut-saw steering 210 by means of a saw wheel 212 gear-up. The saw wheel 212 supported by a wheel connector 214 of the actuator 206 for providing rotation to the wings by keeping the aeroplane body stable which helps in turning the aeroplane in required directions. The centers of the central yaw axis 202 possess a central elevated pitch axis 216 which is connected through a central axis line of the wing roll wheel. The central elevated pitch axis 216 is oriented in longitudinal direction of the aeroplane body and is connected to a wing-roll wheel 218 which is configured with a circular railing at down side of it. The wing-roll wheel 218 may be made up of sustainable metal and the like without limiting the scope of the disclosure and huge in size and sustainable of heavy pressure. The wing-roll wheel 218 is connected to central elevated pitch axis 216 at a front end and a back end at the link in a longitudinal direction; it freely hangs in to the space provided in the shell 204 at certain height having the elevated pitch axis 216 as base.

[0037] As shown in FIG. 2, there is a wheel shaped shell 220 which is fixed on to the wing shell exactly below the wing roll wheel 218 location and the wing shell configured with an required internal space in the form of elevator wheel sockets 222 covered by outer walls separated by the internal socket separating wall. The elevator wheel sockets 222 internally contain an elevation wheel 224. The elevation wheel 224 positioned at a space provided by the elevator wheel sockets 222 by an elevation wheel base axis 226. The elevation wheel 224 may be made up of sustainable metal, and the like, without limiting the scope of the disclosure and is connected to the elevation wheel base axis 226 at the corner to rotate the height of the elevation wheel 224 which is change up and down keeping the centre of elevator wheel base axis 226 at fixed position in the respective elevator wheel socket.

[0038] As shown in FIG. 2, the elevator wheel sockets 222 provide required space for the elevation wheel 224 to rotate in 360 degrees vertically in both the sides which is having the base axis at one corner of the wheel. The elevation wheel base axis 226 extends and passes out side towards the outer space of the elevated wheel sockets 222 through an elevator wheel base line passage 228 and it is connected to the individual and separate the actuator located near to the each elevator wheel sockets like each elevator wheel is having its own and separate actuators near to the sockets which brings the rotations in wheel base axis 226 and then into the elevation wheel 224. The rotations in the elevation wheel 224 may be carried out by means of the separate and individual actuator connected to the elevation wheel base axis 226 which is operated by a source of energy, typically electric current, hydraulic fluid pressure, pneumatic pressure, and the like, without limiting the scope of the disclosure, and these energies may convert into motion that brings rotations in the elevation wheel 224 which is linked to elevation wheel base axis 226. The elevation wheel 224 configured with smooth friction less vertical surface to rotate smoothly on the lower surface of the wing roll wheel 218. The wing roll wheel 218 at its down line has some empty sockets 230 which contain cylindrical separate bearings 232. The bearings 232 are used for friction reduce and exposed out at down side and located inside the empty sockets 230.

[0039] FIG. 3 depicts a diagram 300 of an arrangement for coupling the wing roll wheel to the central wing frame of the aeroplane, according to an embodiment of the present disclosure. The diagram 300 includes a central axis line 302 configured to connect at a central elevated pitch axis. The central axis line 302 is connected and located in the central yaw axis which is projected towards outside in transverse direction of the aeroplane. The central elevated pitch line is connected to the central axis line 302 at end points of the central axis line, may be referred as central pitch axis line connection point 302a in the longitudinal direction and it provides the free up and down rotations on the central axis line 302. There are two side by side pitch lines that project from both the sides of the central axis line 302 and it prolongs longitudinally on both front and back directions and together forms in to a central elevated pitch axis line 304 with two ends one front end and the other to rear end. These movements such as up and down in pitch axis cause the wing to move up and down like an elevator and these movements help in changing the pitch of the aeroplane in up and down motions. This type of movements helps in take-off movement as the wings elevates in upper direction creating the more pressure line below the wings space as the speed increases and the angle of thrust direction also changes to down side at the back of the wings and the reverse force will push the wings and the plane in upper direction so that the plane can take-off even at slow motion. The movements are in landing situations as the wings elevated to the down side it creates more space at the top side of the wing and provides more space to the wings, flaps and spoilers which increases more dragging pressure on to the plane and landing can be made so easy. Whenever the wings bends down at front side, the angle of thrust with respect to the plane body will change up side at the back and the reverse of thrust pressure may work on to ground at front side of the wings, which increase the dragging pressure on plane body which helps in easy landing process.

[0040] As shown in FIG.3, a wing roll wheel 306 is connected to a central wing frame 308 which has two side trunks 308a prolonging transversely towards the shell side openings. The wing roll wheel 306 and central wing frames together forms a structural frame having with wing roll wheel railings at down side and the wing frame having the skeletal frames and beams inside it and also connected to the wing roll wheel 306 to form a strong and complete wing frame of the aeroplane. These two side trunks 308a possess two wing sockets 310 projected towards outside in transverse direction at the end points of the wing frame trunks. This wing-frame connecting socket is used for connecting the outside wings to the central wing frame system at the side openings of the shell. The central wing frame system shows different movements as per rotation of the central yaw axis, the central pitch axis and the wing roll wheel 306 and these rotations shows the movements in the trunks 308a of the wing frame and the wing sockets 310 and finally in to the wings. [0041] FIG. 4A depicts the diagram 400a of an arrangement of wing roll wheel 402 positioned in free space as pitch elevator axis as base and coupled with the two or more pitch elevator wheels 404a, 404b placed in longitudinal direction of the wheel socket. The two or more pitch elevator wheels are connected to the elevator wheel base axis 406 connected on one corner of the elevator wheel. This elevator wheel base axis is connected to an actuator that brings up and down rotations in elevator wheel that elevates or pushes or moves the wing roll wheel 402 up and down pitch movements that moves the wing frame up and down as shown in FIG 4B.

[0042] FIG. 4B depicts the diagram 400b of movements of wings 408 as per the up and down pitch movements of the wig roll wheel 402 supported by the pitch elevator wheels up and down rotations 404a,404b by keeping the plane body stable. The pitch rotations in wings 408 brings up and down movements along its (wings) transverse line by which the aeroplane pitch( altitude) can be changed at required positions and also the angle of thrust with respect to the fuselage (by keeping the plane body stable) can be changed which is used in landing and take-off situations. This type of movements helps in take-off movement as the wings elevates in upper direction creating the more pressure line below the wings space as the speed increases and the angle of thrust direction also changes to down side at the back of the wings and the reverse force will push the wings and the plane in upper direction so that the plane can take-off even at slow motion. The movements are in landing situations as the wings elevated to the down side it creates more space at the top side of the wing and provides more space to the wings, flaps and spoilers which increases more dragging pressure on to the plane and landing can be made so easy. Whenever the wings bends down at front side, the angle of thrust with respect to the plane body will change up side at the back and the reverse of thrust pressure may work on to ground at front side of the wings, which increase the dragging pressure on plane body which helps in easy landing process.

[0043] FIG. 4C depicts the diagram 400c of movements of the wings changing its yaw line by turning the wings front and back on both the sides of wings. The saw wheel 409 is connected to the central yaw axis line via saw wheel steering. This central yaw axis is connected to the wing roll wheel 402 via pitch elevation axis. The actuator that is connected to the saw wheel 409 rotates the central yaw line by side turnings which rotates the wing roll wheel 402 on both the sides up to some extent as per predetermined degrees. The rotating wing roll wheel brings the front and back turning movements in the wing frame and then in to the wings 410. These yaw turnings along with the change in angle of thrust with respect to plane body, helps the aeroplane to turn on both the sides keeping the plane body stable which is used in critical situations like cross winds, landing and take-off movements. This rotation brings the to and fro motion of the wings on both the sides by keeping the plane body stable which helps in turning the plane in required directions. This rotation changes the angle of thrust of the jet engines located on the plane wings with respect to the direction of plane body, towards opposite side of wings rotation which creates the reverse force on to the plane in opposite direction towards the rotation of wings as per law of forces. The yaw line can be used in critical situations like the angle of thrust can be changed with respect to the plane body according to the required direction by keeping the plane body at stable and the anti-thrust force can be used to overcome the critical situations like cross winds, monsoon issues and control lost in landing and take-off situations.

[0044] FIG 5A- 5B depicts diagrams 500a and 500b of movements of the wing rolls by keeping the fuselage stable by means of the roll elevator wheels positioned in transverse line of the wheel sockets. As per diagram 500a the wing roll wheel 502 is coupled with the two or more roll elevator wheels 504a, 504b that shows up and down movements by pushing the wing roll wheel 502 up and down that rolls the wing frame in the shell. In this situation the plane body can be kept stable and the wings 506a can be used for rolling up and down as shown in Fig 5B. The diagram 500b depicts the fuselage 508a is at stable position and the plane wings 506a are rolled on both the sides to overcome cross wind issues and also the plane body can be kept stable even at minor roll movements of the plane.

[0045] FIG. 5C is a diagram 500c depicting movements of the plane body or fuselage by keeping the wings at stable position. As per diagram 500a the wing roll wheel 502 is coupled with the two or more roll elevator wheels 504a, 504b can be used for rolling the plane body by the support of the horizontal and vertical stabilizers 508b by keeping the plane wings at stable 506b by the coordinated process between the wing roll wheels and the horizontal and vertical stabilizers. The process of fuselage rolling by keeping the plane wings at stable position helps in overcoming of critical situations like control lost and cross wind situations.

[0046] As the flexible wing system in aeroplane brings the multiple and flexible movements in terms of its yaw line turning movements, pitch up and down movements and wing rolling movements along with changing the angle of thrust with respect to the plane body and keeping the plane body at constant position, the horizontal stabilizer 102b also plays a major role in rotating the plane body and changing the plane pitch line by moving the horizontal stabilizer wings which contains the shell 104b, central vertical yaw axis, wing- roll wheel system, wing sockets 108b located at the end of wing trunks and the elevation wheels located in elevation wheel socket system. (The parts described in flexible wing system and the horizontal stabilizers are similar in its working process and technicalities and performance but they are different in their sizes which are smaller and little bit differs in usage).

[0047] As per new invention the horizontal stabilizers with the flexible stabilizer wings are used to give support at rear portion of the plane and whenever the plane body is to be rotated by keeping the plane wings at stable especially in crosswind situations a heavy wind flow and control loss while landing and take-off situations the wings can be kept stable towards the direction of wind force and the plane body can be rolled and controlled by means of the new horizontal stabilizers 506b and 508b as shown in Fig 5C. In order to roll the plane body by means of the horizontal stabilizers is supplemented by the new ailerons (for rolling the plane) at the end points of the both sides of stabilizer wings.

[0048] Now in the new system the horizontal stabilizers 102b are flexible which shows the different kinds of movements by rotating its central yaw axis and the wing roll wheel system by means of the elevation wheels located in the wheel socket as (components) like in the flexible wing system. These flexible horizontal stabilizers participates in plane body rolling, change in minor yaw lines and pitch lines especially designed to support the plane body in critical situations like cross winds, the uncontrolled situations like landing and take-off of a plane. [0049] FIG. 6 depicts a diagram 600 of elevation levels of elevator wheel, according to an embodiment of the present disclosure. The wing rotations are depending upon the level of elevation of the elevator wheel which is located in wheel socket. The maximum length between the elevator wheel base axis to the maximum vertical height of the elevator wheel is referred as elevation line 601a, 602a, 603a. The level of the elevation of the elevator well is known by the orientation of the elevation line in the wheel socket either it may be in vertically down position 603a and 604a, horizontally parallel to the wheel socket top line 602a, 604c and vertically up 601a, 604b.

[0050] As shown in FIG. 6, the elevation line 601a is vertically up and the elevation wheel is totally placed outside the socket 604b it is referred as high elevation or the maximum elevation line 601. At the maximum elevation stage, the elevation wheel pushes the wing rolling wheel to the maximum height which brings the maximum elevation in the wings in the direction of location of the elevation wheel. The method of rotations of the elevation wheels from the minimum elevation 603a to the maximum elevation 601a by pushing the wing-roll wheel from down to the maximum height is called as 'pushing rotations' of the elevation wheel.

[0051] As shown in FIG. 6, the elevation line 603a is vertically down and the elevation wheel is totally placed inside the socket as shown in FIG.6 and it is known as zero elevation or the minimum elevation line 603. At this minimum elevation stage the elevation wheel supports the wing roll wheel which is elevated down wards to the direction of the minimum elevation wheel. The method of rotations of the elevation wheel from the maximum elevation 601a to the minimum elevation 603a which supports the downward elevating wing roll wheel is referred as the supporting rotations. To complete one elevation/ movement of wings either in transverse direction for rolling the wings or in longitudinal direction for change in pitch of plane there should be minimum of two elevation wheels participating. One elevation wheel works as pushing wheel for increasing the elevation, the wing with certain speed and height up to maximum elevation and the other wheel works as supporting wheel which is positioned opposite to the direction of the force, acting for supporting the elevating wheel on other side with the same speed and downing the height to minimum elevation. [0052] As shown in FIG. 6, the elevation line is in horizontal direction 602a and the elevation wheel is half out and half inside of the socket 604c is referred as medium or the stable elevation. At this stage the elevation of a wing on both the sides transversely and longitudinally is at stable and parallel to the plane body without any movements. Both the pushing elevation wheels and supporting wheel are at same height and these wheels holds the wings at steady, horizontal position by keeping the plane at stable position and it shows its steady movements.

[0053] The mid flexible wings and the back horizontal stabilizers always works on coordinated system between them in terms of flexible movements while changing the yaw line, pitch line, rolling the plane and take-off as well as landing situations which is controlled by the pilots in the cockpit. The cockpit controls like airplane primary controls and the secondary controls are connected with the flexible wing system and the flexible horizontal stabilizers to their central yaw lines and to the elevator wheels located in the wheel sockets to operate the flight movements.

[0054] The wing and horizontal stabilizer shells 104a, 104b, where the internal wing frame and the elevation wheel located are open on both the sides. The wings are connected to the wing frame on both the sides to the sockets of the wing frame which is located at the opening of the shell. This shell opening has enough space for wing frame to show movements while operating the wings. In order to avoid inflow of air, water and other foreign particles in to the shell, the shell opening and the wings are covered and connected with flexible and multi-layer sliding metal sheets. This sliding metal layer is sustainable of outer pressure and designed according to the aero dynamics and internally connected to the wing shell on one side and on other side connected to the wings at the connecting part of the wings to the sockets of the wing frame. Since it has multiple sliding layers of metal sheets, these metals sheets slide and rolls inside of each and shows movements in all the directions according to the wing movements of the side wings and the horizontal stabilizers while changing the yaw, pitch and roll movements of the plane on both the sides.

[0055] The new flexible wing, horizontal stabilizer system can be applied with the conventional manual flight controls of an aircraft and also with an electronic interface. [0056] In this new system the power lines and flexible fuel pumping lines passes from the wing shell lower or upper side and connected to the wing frame at the middle portion by means of flexible power cables and fuel transmission pipe lines and it passes via trunk of wing frame and then to the sockets finally passes to the wings as well as to the required destination.

[0057] While specific embodiments of the disclosure have been shown and described in detail to illustrate the inventive principles, it will be understood that the invention may be embodied otherwise without departing from such principles.