the present invention is embodied in a flying car / flying drone vehicle that operates in the manner of a vertical take - off and landing ( vtol ) or short take - off and landing ( stol ) or a helicopter type aircraft , but is sized and designed like a personal land vehicle . as shown in fig1 and 3 , the vehicle comprises a main body 10 is in the shape of an automobile or an amphibious vehicle and which has a front end 12 , a rear end 14 and side storage compartment cover doors 16 which close over storage compartments 18 formed in the sides of the vehicle . the compartments are sized to contain rotors / propellers 20 ( hereafter “ rotors ”, fig4 ), which can be folded into the compartments when not needed . the rotors can open and rotate independently . a pair of foldable , extensible wings 22 ( fig1 - 6 ), which are connected to the main body , also serve as covers for the storage compartments . folding and extensible wings are well known in the art and therefore their constructional details , which would be a matter of ordinary design skill , are not shown . in their collapsed vertical configuration ( fig1 ), the wings cover the rotors , and provide lift in their flight and cruise configuration ( fig3 ). the transformation of the vehicle between the land and air configuration can be rapidly done automatically , without operator assistance , as shown schematically in fig1 - 12 . the operator of the flying car / flying drone vehicle can enter the vehicle through a front door 9 ( fig1 ), or through a rear or side access door ( not shown ). during land operation , roadable land / amphibious mode , the rotors 20 are stored in the storage compartments 18 . during preparation for take off , in a transition mode , the wings 22 are raised , allowing the rotors 20 to be deployed , as shown in fig2 - 6 , in an initially close to vertical configuration , as when stored ( fig3 - 5 ). after rotors have exited the storage compartments , the side wings remain in their deployed vehicle flight configuration . the rotors are supported by hinged actuators 30 ( fig1 - 19 ), which move the stored rotors ( initially in a stowed position inside the compartments 18 ) to a deployed position outside the vehicle body ( fig5 ). the actuator comprises an electromechanism 32 , 35 which rotates the actuator &# 39 ; s arms 34 , 36 through 90 ° to move the rotors 20 from their initial open position to a flying position ( fig5 ). after the side storage compartment covers are closed completely , the rotors can move to a horizontal orientation ( fig6 ), which is the basic position for vertical take - off and landing ( vtol ). during flight , the rotors spin around their rotational axes ; the rotors may have blade pitch change capability . the side rotors can rotate around the rotors opening axes , in order to provide high maneuverability ( fig1 ). also , the rotors &# 39 ; speed and blade pitch can be adjusted based of the vehicle needs . after take - off , the rotors can be moved from horizontal to a vertical position (− 90 ° pitch ), in order to create the necessary thrust for the vehicle flight cruise configuration . the rotation of the rotors around the body hinge points , create the transition from the take - off to the cruise configuration . the flying vehicle &# 39 ; s computer microprocessor 40 ( fig1 ) receives signals from an altimeter 42 , motion detectors sensors 44 , a global positioning system ( gps ) 46 , and a gyroscoping type controller 48 , which processes the signals coming from gyroscopes 50 . the processor may use new or existing autonomous flying vehicle software ( afvs ) ( fig2 ) that will assure vehicle complete independent stabilization mode . the present invention obtains power needed to the move the vehicle on roadways or on water from a power unit , which may be : a ) an internal combustion , diesel or turbofan engine 52 which drive the vehicle &# 39 ; s wheels through shafts , pinions and gears , b ) an electric power supply , battery 54 or electric generator attached to a combustion , diesel , turboprop or turbofan engine , which provide the necessary electrical energy to drive the vehicle electric motors connected to vehicle wheels , or c ) an air power supply 56 , air from an air compressor attached to a combustion , diesel or turbofan engine , air from a turbofan engine or air from an air reservoir 58 , to create the necessary energy to drive the vehicle wheels through a central or independent air motor on each of the vehicle &# 39 ; s wheels . i ) an internal combustion , diesel or turbofan engine which drive the rotors through shafts , pinions and gears , ii ) an electric power supply , battery or electric generator attached to a combustion , diesel , turboprop or turbofan engine , which provide the necessary electrical energy to drive the rotors &# 39 ; electric motors , and / or iii ) an air power supply , air from an air compressor attached to a combustion , diesel or turbofan engine , air from a turbofan engine or air from an air reservoir , to create the necessary energy to drive each of the vehicle rotors through a central or through independent air driven motor for each of the vehicle rotor , or to drive each of the vehicle rotors through a central turbine or through independent turbine for each of the vehicle rotor . for emergency situations , the flying vehicle has benefit of the optional use of the manual or automatically deployed parachute 60 ( fig1 ) for land or water landing . the roadable land / amphibious configuration of the described flying vehicle is similar to an automobile in that it has multiple rotors packed in a very convenient and compact way . the general shape of the described present invention , during ground or water operations , having the rotors packed in a very convenient and compact way inside the flying car / flying drone vehicle body and covered by wings , is similar with a car vehicle configuration . for the flying configuration of the described present invention , the unfolded and rotated rotors allow the vehicle to fly in the similar manner of a vtol / stol helicopter or airplane . the flying configuration of the described flying car / flying drone vehicle has the rotors unfolded and rotated in a horizontal or up to vertical position relatively to ground that allow the vehicle to fly in the similar manner of a vtol / stol helicopter or airplane . for the roadable land / amphibious configuration , the vehicle has conventional pedals , controls and steering mechanism so it can be driven like a car . for flying configuration , the flying car / flying drone vehicle has a control stick ( not shown ) which is used in the flight mode . in order to transform to the flight configuration , the vehicle raises the side wings , thus uncovering the compact stored rotors , unfolds the rotors , rotates the rotors from their stored vertical position into a flying horizontal take off position , and starts spinning the rotors in order to create the necessary lift for the vehicle to take off , fly and land . during cruise configuration , the rotors may be pivoted to a vertical position , to create thrust for the vehicle in flight mode . the vehicle cabin , when closed , is hermetically sealed and can be pressurized . the foregoing description is of a presently preferred embodiment of the invention ; however , modifications of the vehicle will occur to those in the field of this invention . in particular , where single - propeller rotors are shown and described above , one might substitute multiple propellers . for example , a hexagonal array of seven coplanar smaller propellers , within the same diameter as the single propeller rotors described above , might prove to be as good as or better than a single propeller , in terms of weight , lift and efficiency . since the invention is subject to modifications and variations , it is intended that the foregoing description and the accompanying drawings shall be interpreted as only illustrative of the invention .