to exemplify the use of the mechanism for reversibly folding and deploying panels in accordance with an embodiment of the present invention the folding and deployment of wings of projectiles and other flying devices are detailed hereinafter . it is an object of the present invention to provide a foldable and deployable panel that is capable of easy and swift deployment . another object of the present invention is to provide a foldable deployable panel , which can be folded neatly and stored in a confined space comparable in its size to the main body to which the panel is attached , thus reducing substantially storage footprint required for main - body having the wing attached . other objects and advantages of the present invention when used for the folding and deployment of panels in various usages will become apparent after reading the present specification and reviewing the accompanying figures . the present invention improves the efficiency of compaction and reduction of packaging volume required for reversibly foldable and deployable panels . the folding of the panel is done by two consecutive turns that bring the panel to a “ wrapping ” posture along side the object to which it is coupled , where the broad surface of the panel is substantially tangential to the external surface of the object body ( i . e ., a “ folded position ”). correspondingly , the deployment of the panel is done by implementing the above two consecutive turns in reverse , bringing the panel to a posture erect with respect to the object panel ( i . e ., a “ deployed position ”). an explanation of the deployment and folding of panels in accordance with the present invention follows : from a folded state an electronic command - signal , a pyrotechnical - mechanism or some other triggering mechanism commences the deployment of a panel device in accordance with the present invention . the triggering command releases a locking mechanism . from the folded position , the released panel undergoes a first turning about a first turning axis substantially parallel to the surface of the object body , so as to be positioned perpendicularly to the object body in a “ first erect posture ”. the panel is then displaced along the first turning axis to be positioned in a “ second erect posture ”. a first pivot constrains the motion of the panel to the first turning , except for when the panel is displaced into the second erect posture . next , by “ stored energy ” originating from either a spring , a hydraulic - piston or a pneumatic mechanism connected to a pressured gas source or a gas - generator , the panel undergoes a second turning about a second turning axis that is substantially 90 degrees in perpendicular to the first turning axis , and the panel is inserted into a stabilizing slot between two protective plates , where it is now in the deployed position . a second pivot constrains the motion of the panel to the second turning , except for when the panel is in the first erect posture . the panel can now be locked in place in either a permanent locking arrangement or a locking arrangement that permits the refolding of the panel . by way of example detailed elaboration of a embodiment of the present invention is given hereinafter , where the panels are wings of a projectile or other flying object . wings serve as aerodynamic surfaces providing lift to a flying object . to be effective wings typically span a substantial distance from the body of projectile thus bestowing a large footprint . the footprint dictates large packaging , storage and maintenance volumes . foldable wings were introduced , and can be seen , for example on aircraft parked on aircraft carrier decks . the need for parking room is met by reducing the wing span of parked aircraft on board aircraft carriers . but when a substantial portion of the wing folded to an up - right position , the space freed on the sides of the aircraft is replaced with occupied space over the aircraft , a space which on the upper deck of an aircraft carrier is abundant . if a winged object is to be stored in on a confined space the wing span may pose a true problem . as the length of a wing is usually greater than its width , folding it across results in either shortening the wing by as much as half ( in the case of about 180 degrees fold ), or having the wind protrude upwards ( in the case of about 90 degrees fold ). the present invention introduces a wing of a projectile which can be folded in a twin - action sequence . a first action brings the elongated aspect of the wing to a substantially parallel position along the adjacent body to which it is attached , to a side - by - side configuration with the body , and a second action in which the now side - by - side wing is turned about an axis parallel to the adjacent body , bringing the broad surface of the wing to a tangential stored position with respect to the body external surface . by doing so the footprint of the wing is greatly reduced , allowing for minimal space storage . when deploying the wing from the stored position the above sequence of actions is performed in reverse order , bringing the wing to the deployed position . according to an embodiment of the present invention , a wing is disclosed that can be easily and swiftly deployed from the folded state and remain fixed in the deployed position . by “ projectile ” is meant , for the purpose of the present invention and throughout this specification ( unless specifically stated otherwise ) any object that is ejected , thrown , tossed , propelled , shot , dropped , flown or otherwise dispatched to make its way in air , be it aerodynamically , free falling or any other way of travel in air . in some embodiments of the present invention the body with the folded wing is stored in a container which holds the folded wing to the body of the object . in some embodiments of the present invention the folded wing is fastened to the body of the object by a fastener and a controlled release mechanism removes the fastener to allow immediate deployment of the wing . fig1 is an illustration of a foldable deployable wing 12 in accordance an embodiment of the present invention with the wing locked in a deployed position by a flexible snap - lock mechanism 14 in a substantially vertical , perpendicular deployed position , relative to the outer surface of projectile 16 . fig1 should be viewed in conjunction with fig5 which illustrates a lateral cross - section illustration across the wing folding and deploying device in accordance an embodiment of the present invention with wing 12 in a deployed position . shown in fig1 is snap - lock 14 snapped into gap 18 in wing 12 in a region close to the surface of the projectile 16 , in a flight configuration . two parallel support plates , 20 and 22 ( only 20 is visible in fig1 , both shown in fig5 ) protrude from the surface of the projectile 16 and confine a proximal portion of the wing ( close to the projectile body ) between them . support plates 20 , 22 , serve as reinforcement members while snap - lock 14 and spring 28 , elastically hold the wing down . spring 28 rests on stand 26 which is a plate located in between support plates 20 and is secured at one end to pin 30 that runs substantially parallel to the plates , and at the other end to anchoring point 32 which is connected to wing 12 . a pin 29 is connected to the end of spring 28 , and is coupled to anchoring point 32 . pin 29 serves as a pivot when spring 28 is stretched and wing 12 is pulled from between support plates 20 and 22 ( shown in fig2 and explained hereinafter ). fig2 is an illustration of the foldable deployable wing shown in fig1 with the wing unlocked and turned so as to align with the adjacent body 16 . in the figure wing 12 is unlocked from the snap - lock 14 and rotated sideway in the direction - of - flight of the projectile utilizing peg 34 as a pivot , bringing it to a side - by - side alignment with the adjacent object 16 . the wing is pulled to bring its distal edge 38 towards auxiliary flap 36 so that docking pin 40 , extending from the auxiliary flap is inserted and fixed in corresponding bore 42 , defining a hinge . with the pulling of the wing spring 28 is stretched and pin 29 at the end of the spring serves as a pivot . with the wing pulled from between the support plates 20 and 22 the wing is free to turn side way on the defined hinge between docking pin 40 and pin 29 . fig3 is an illustration of wing 12 turned towards the body of projectile 16 on the hinge explained in fig2 . the inclined edge 21 of support plate 22 ( one of the two support plates ) has a protrusion 22 a , distanced from the body of the projectile . protrusion 22 a , illustrated in a lateral cross - section illustration in fig4 and fig5 , limits the angular movement of wing 12 to a single , predetermined , folding side towards the body of the projectile when removed from between support plates 20 and 22 and stops the wing from damaging the body of the projectile 16 when folded ( prevents “ over folding ”. fig4 is a lateral cross - section illustration of the foldable deployable wing 1 illustrated in fig3 . showing the wing in a folded state , stretched out of the support of support plates 20 and 22 . note that a portion of wing 12 adjacent the body 16 is thinner than the rest of the wing so as to fit that portion of the wing within the support plates 20 and 22 , while presenting a substantially aligned outer surface of the support plates and the rest of the wing . fig5 is a lateral cross - section illustration of the foldable deployable panel illustrated in fig1 showing the wing in a deployed ( erect ) state . fig6 is a cross - section illustration of a projectile 16 with four foldable deployable wings 12 in accordance with an embodiment of the present invention , in a storing position within a designated container 50 . the container is designed to hold the projectile with its folded wings neatly , keeping the wings in the folded position . the deployment of the wings is simple and swift . when the folded wings are not restrained they can be manually handled to return to the deployed state ( as shown in fig1 ). alternatively , the wings can assume the deployed position simply by removing the restraint that holds the wings in their folded position . the force of the spring 28 , and the inclined edges 21 ( see fig3 ) of support plates 20 and 22 , which by default favor sliding of the wings back into the confinement of support plates , act to together restore the wings deployed state . in order to have an illustration of the deployment the figures ought to be considered in reversed order ( fig3 , then fig2 and then fig1 ). in an embodiment of the present invention a springs mechanism 28 stores the energy needed ( until it hits its stopper , designated 22 a in fig1 and fig2 ) for the torque needed for convenient deployment of the wings . the first turn , which turns the wing along the projectile main body with respect to hinges , uses the spring as a torsion - spring device . the second turn , which turns the wing to extend from the projectile main body uses the same spring as a tension - spring , exerting torque on the wing with respect to hinge 34 . the displacement of the wing along the first turning axis from the first erect posture to the second erect posture uses the same spring as a tension spring . in an alternative embodiment of the present invention the projectile with the folded wings , according to an embodiment of the present invention is provided with a removable fastener , holding the wings in their folded state . when the fastener is removed or released the wings deploy . such a fastener may include a time dependent release mechanism or other automatic or remote - controlled release mechanism to ensure proper and timely deployment of the wings . in another embodiment of the present invention , panels of devices such as , but not limited to , sun - energy collectors and various broadcasting and reception antennas are folded and deployed in a manner that was previously described for wings of projectiles but instead of having a spring mechanism ( designated 28 in fig1 and fig2 ) that have a default state that favors sliding of a wing ( no . 12 in fig1 ) back into the confinement of support plates ( designated 20 and 22 in fig4 and fig5 ) another “ energy - storing ” element such as a hydraulic or pneumatic mechanism slides a panel back into the confinement of support plates . in another embodiment of the present invention , panels are folded and deployed in a manner that was previously described for wings of projectiles but instead of having an auxiliary flap ( numbered 36 in fig1 and fig2 ) a plate or bar has a pin ( designated 40 in the figures ) that inserts into a corresponding bore ( no . 42 in the figures ) in the deployed panel . in another embodiment of the present invention , a panel is coupled in a position substantially parallel along the adjacent body to which it is attached , to a side - by - side configuration with the body ( as illustrated in fig2 ). the folding and deployment of the panel is done by turning of the panel about an axis parallel to the adjacent body , bringing the broad surface of the panel to a tangential stored position with respect to the body external surface ( illustrated in fig3 ). it should be clear that the description of the embodiments and attached figures set forth in this specification serves only for a better understanding of the invention , without limiting its scope . it should also be clear that a person skilled in the art , after reading the present specification could make adjustments or amendments to the attached figures and above described embodiments that would still be covered by the present invention .