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THAILUOHLOINUS009776715B2 (12 ) United States Patent ( 10) Patent No. : US 9 ,776 ,715 B2 Zhou et al. (45 ) Date of Patent: * Oct. 3 , 2017 (54 ) AMPHIBIOUS VERTICAL TAKEOFF AND (58 ) Field of Classification Search en LANDING UNMANNED DEVICE CPC .. . B64C 29/ 0033 ; B64C 35/ 00 ; B64C 35/ 008 ; B64C 2201 /088 ; B60F 3 /0061 ; B60F 5 /02 (71 ) Applicants :Andrew H B Zhou , Tiburon , CA (US ); See application file for complete search history . Dylan T X Zhou , Belvedere Tiburon , CA (US ) ; Tiger T G Zhou , Tiburon , CA (US ) ( 56 ) References Cited (72 ) Inventors : Andrew H B Zhou , Tiburon , CA (US ); U . S . PATENT DOCUMENTS Dylan T X Zhou , Belvedere Tiburon , CA (US ) ; Tiger T G Zhou , Tiburon , 2 , 989 , 269 A * 6 / 1961 Le Bel ...... B64C 29/ 0033 114 /289 CA (US ) 3 ,029 , 042 A * 4 / 1962 Martin ...... B60F 3 / 00 ( * ) Notice : Subject to any disclaimer , the term of this 180 / 119 patent is extended or adjusted under 35 (Continued ) U . S .C . 154 (b ) by 0 days . This patent is subject to a terminal dis Primary Examiner — Joseph W Sanderson claimer . (74 ) Attorney, Agent, or Firm — Georgiy L . Khayet ( 21 ) Appl. No. : 15/ 350 ,458 (57 ) ABSTRACT ( 22 ) Filed : Nov. 14 , 2016 An amphibious vertical takeoff and landing (VTOL ) unmanned device is provided . The amphibious VTOL (65 ) Prior Publication Data unmanned device includes a modular and expandable water US 2017 /0072755 A1 Mar. 16 , 2017 proof body, an outer body shell , a gimbaled swivel propul sion system comprising a plurality of VTOL jet engines and Related U .S . Application Data VTOL ducted fans , a processor, electronic speed controllers , (63 ) Continuation - in -part of application No . 29/ 572 , 722 , a two -way telemetry device , a video transmitter, a radio control receiver, a power distribution board , an electrical filed on Jul . 29, 2016 , and a continuation - in -part of machine , an onboard electricity generator comprising a ( Continued ) plurality of solar cells , a light detection and ranging device , (51 ) Int. Cl. an ultrasonic radar sensor, a plurality of sensors , a tail B64C 35 /00 ( 2006 .01 ) configured to stabilize the amphibious VTOL unmanned B60F 5 / 02 device, a head VTOL ducted fan adapted for VTOL , a ( 2006 .01 ) plurality of wheels , a plurality of foldable wings configured (Continued ) to create a pressure difference and creating a lift, a plurality (52 ) U . S . CI. of parachutes configured to safely land the amphibious ??? ...... B64C 35 / 008 ( 2013. 01 ) ; B60F 5 / 02 (2013 . 01 ); B60K 16 /00 ( 2013 .01 ); B6OR 11/ 04 VTOL unmanned device in an emergency. ( 2013 .01 ) ; ( Continued ) 29 Claims, 50 Drawing Sheets 100 125

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Related U . S . Application Data ( 56 ) References Cited application No. 29 / 567, 712 , filed on Jun . 10 , 2016 , U .S . PATENT DOCUMENTS and a continuation - in - part of application No . 14 / 940 , 379 , filed on Nov . 13 , 2015 , now Pat. No . 9 , 493 , 235 , 4 ,579 , 297 A * 4 /1986 Ayoola ...... B60F 3 / 00 and a continuation - in -part of application No. 15 / 345 , 244 / 106 5 ,645 , 250 A * 7 /1997 Gevers .. . B64C 1 / 00 349 , filed on Nov. 7 , 2016 , which is a continuation 244 / 101 in - part of application No. 14 /957 , 644 , filed on Dec . 3 , 6 , 138 , 943 A * 10 / 2000 Huang .. . * ** . . .. . B60F 5 / 02 2015 , now Pat . No . 9 , 489 ,671 , which is a continua 244 / 17 . 25 tion - in -part of application No. 14 /815 , 988 , filed on 7 ,472 ,863 B2 * 1/ 2009 Pak ...... A63H 27 / 14 244 / 12 . 5 Aug. 1 , 2015 , now Pat. No . 9 , 342 , 829 , and a con 7 ,874 ,513 B1 * 1/ 2011 Smith ...... B64C 11 /001 tinuation - in -part of application No . 13 /760 ,214 , filed 244/ 12 . 4 on Feb . 6 , 2013 , now Pat. No . 9 , 016 , 565 , which is a 7, 959 , 104 B2 * 6 / 2011 Kuntz A63H 17 /00 continuation - in - part of application No . 10 /677 , 098 , 244 / 2 8 , 827, 200 B2 * 9/ 2014 Radu ...... B60F 5 / 02 filed on Sep . 30 , 2003 , now Pat . No . 7 , 702, 739 . 244 / 2 9 ,045 ,226 B2 * 6 / 2015 Piasecki GO5D 1 / 102 9 ,085 , 355 B2 * 7 / 2015 DeLorean ...... B64C 29 /0033 (60 ) Provisional application No. 60 /415 , 546 , filed on Oct. 9 ,493 , 235 B2 * 11/ 2016 Zhou ...... B60F 5 /02 1 , 2002 . 2002 /0125367 A1 * 9 /2002 Killingsworth ...... B60F 3 / 00 244 / 17 . 11 2002/ 0195518 A1* 12 /2002 Killingsworth B60F 3 / 00 244 / 7 A (51 ) Int . Ci. 2005 /0236520 Al * 10 /2005 Wukowitz ...... B64C 5 /02 B64C 29 /00 (2006 .01 ) 244 / 105 B64C 39 / 02 (2006 .01 ) 2006 / 0016930 A1 * 1 / 2006 Pak ...... A63H 27 / 14 244 / 12 . 4 G05D 1/ 04 ( 2006 . 01 ) 2008 /0048065 A1 * 2 /2008 Kuntz ...... A63H 17/ 00 B64C 37 /00 ( 2006 . 01 ) 244 / 17 .23 G05D 1 /08 2010/ 0181414 A1 * 7 /2010 Lopez , Jr...... B64C 29/ 0033 ( 2006 .01 ) 244 / 12 .4 G08G 5 / 04 ( 2006. 01 ) 2011 /0042507 A1* 2 / 2011 Seiford , Sr...... B60F 5 /02 B60R 11/ 04 ( 2006 .01 ) 244 / 2 2011/ 0315806 A1* 12/ 2011 Piasecki ...... GO5D 1/ 102 B60K 16 ,00 (2006 . 01) 244 / 2 (52 ) U .S . CI. 2013/ 0026303 A1* 1/ 2013 Wang ...... B64C 3/ 54 244 / 7 R ??? ...... B64C 29 /0033 (2013 .01 ) ; B64C 37700 2013/ 0026304 A1* 1/ 2013 Wang ...... B64C 29/ 0033 ( 2013 .01 ) ; B64C 39 /024 (2013 . 01 ) ; G05D 244 / 7 R 1 /0816 ( 2013 .01 ) ; G05D 1 /0858 ( 2013 .01 ) ; 2013 /0068876 Al* 3 /2013 Radu ...... B60F 5 /02 G08G 5 / 04 ( 2013 .01 ) ; B6OK 2016 /003 244 / 2 ( 2013 . 01 ) ; B64C 2201 /021 ( 2013 .01 ) ; B64C 2014 /0158816 A1 * 6 /2014 Delorean ...... B64C 29/ 0033 2201/ 102 ( 2013 .01 ); B64C 2201/ 141 244 / 12 . 4 ( 2013 .01 ) ; B64C 2201/ 162 ( 2013 .01 ) * cited by examiner U . S . Patent Oct. 3 , 2017 Sheet 1 of 50 US 9 ,776 ,715 B2 S 150 ww -160 100 wwwwwwwwwwwwww 120 rit . 125 p varit wimming -140

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primla un paintenantpointre US 9 ,776 ,715 B2 AMPHIBIOUS VERTICAL TAKEOFF AND converted into an automotive type vehicle capable of flying LANDING UNMANNED DEVICE on air , sometimes popularly referred to as a “ flying car " or “ flying jet vehicle ” . CROSS -REFERENCE TO RELATED APPLICATIONS 5 BACKGROUND This application is a continuation - in -part of U . S . patent Henry Ford once stated , “Mark my word : A combination airplane and motorcar is coming . You may smile . But it will application Ser. No . 29 / 572, 722 , entitled “ AMPHIBIOUS come” (Henry Ford , Chairman , Ford Motor Company VTOL , HOVER , BACKWARD , LEFTWARD , RIGHT 10 1940 ) . In fact, shortly after the Wright brothers ' first flight, WARD , TURBOJET, TURBOFAN , ROCKET ENGINE , people have been looking for ways to combine aircraft and RAMJET, PULSE JET, AFTERBURNER , AND SCRAM automobiles into one vehicle . In 1918 , Felix Longobardiwas JET SINGLE /DUAL ALL IN ONE JET ENGINE (FUEL / issued the first patent ( U . S . Pat. No . 1, 286 ,679 ) for a ELECTRICITY ) WITH ONBOARD SELF COMPUTER multi -use vehicle also known as a roadable aircraft . BASED AUTONOMOUS MODULE GIMBALED 15 Throughout the following 88 years , there have been numer SWIVEL PROPULSION (GSP ) SYSTEM DEVICE , ous patents issued for vehicle concepts that are capable of SAME AS DUCTED FAN ( FUEL / ELECTRICITY ) ” , filed both flying and driving . While there has been no shortage of on Jul. 29 , 2016 , U . S . patent application Ser. No. 29 /567 , inventions in this field , there have been no concepts , which 712 , entitled “ AMPHIBIOUS VTOL , HOVER , BACK have met with commercial success . And there is no flying WARD , LEFTWARD , RIGHTWARD , TURBOJET, TUR - 20 car used jet engines and putting two devices into one with BOFAN , ROCKET ENGINE , RAMJET, PULSE JET, both electricity and fuel . AFTERBURNER , AND SCRAMJET ALL IN ONE JET The reasons for the lack of commercial success for the ENGINE ( FUEL /ELECTRICITY ) WITH ONBOARD numerous previous roadable aircraft patents are as varied as SELF COMPUTER BASED AUTONOMOUS GIM the patents themselves . Some failed because the design was BALED SWIVEL PROPULSION SYSTEM DEVICE ” , 25 infeasible or unsafe . Others failed because the design was filed on Jun . 10 . 2016 . U . S . patent application Ser. No. too complicated or too expensive to manufacturer, while 14 /940 ,379 , entitled “ AMPHIBIOUS VERTICAL TAKE most did not satisfy the customer ' s need . Regardless of the OFF AND LANDING UNMANNED SYSTEM AND FLY specific reason , to this day no design appears to have been ING CAR WITH MULTIPLE AERIAL AND AQUATIC practical enough to become a commercial success . FLIGHT MODES FOR CAPTURING PANORAMIC VIR - 30 This is not too surprising when one considers the differ ence between an aircraft and automobile that must be TUAL REALITY VIEWS , INTERACTIVE VIDEO AND reconciled for such a combination vehicle to be practical. TRANSPORTATION WITH MOBILE AND WEARABLE One difference is the aircraft ' s wings . For flight, an aircraft APPLICATION ” , filed on Nov . 13 , 2015 , and U . S . patent requires long , high -aspect ratio wings. The high aspect ratio application Ser. No . 15 /345 ,349 , entitled “ SYSTEMS AND 35 allows for increased efficiency and performance . In order for METHODS FOR MESSAGING , CALLING , DIGITAL the vehicle to drive on the road , the wings must be dealt MULTIMEDIA CAPTURE AND PAYMENT TRANSAC with . Most roadable aircraft can be classified by how they TIONS ” , filed on Nov . 7 , 2016 , which is a continuation - in deal with the wings and tail of the vehicle when in driving part of U . S . patent application Ser. No . 14 / 957 ,644 , entitled mode . These classes are : VTOL ( vertical take -off and land “ SYSTEMS AND METHODS FOR MOBILE APPLICA - 40 ing ) , modular, and integrated . TION , WEARABLE APPLICATION , TRANSACTIONAL VTOL aircraft typically either have very short wings or no MESSAGING , CALLING , DIGITAL MULTIMEDIA CAP - wings at all . The idea is that if one is tired of being stuck in TURE AND PAYMENT TRANSACTIONS” , filed on Dec . traffic , one could push a button , take off straight up and fly 3 , 2015 , which is a continuation - in -part of U . S . patent over the traffic jam . However, VTOL aircraft are much more application Ser . No. 14 /815 , 988 , entitled “ SYSTEMS AND 45 akin to helicopters than the ‘ hovercraft ' envisioned as flying METHODS FOR MOBILE APPLICATION , WEARABLE cars . As with helicopters, VTOL vehicles generate lift by APPLICATION . TRANSACTIONAL MESSAGING , either helicopter - like blades or ducted fans, which force a CALLING . DIGITAL MULTIMEDIA CAPTURE AND large amount of air downwards. This downwash will gen PAYMENT TRANSACTIONS ” , filed on Aug . 1 , 2015 , erally kick up a lot of dirt and rocks . The debris would be which claims priority to U . S . patent application Ser. No. 50 thrown into the neighbouring cars and pedestrians thus 13 /760 ,214 , entitled “ WEARABLE PERSONAL DIGITAL making the idea of taking off in the middle of traffic DEVICE FOR FACILITATING MOBILE DEVICE PAY - infeasible . As a result , VTOL aircraft are generally restricted MENTS AND PERSONAL USE ” , filed on Feb . 6 , 2013 , to taking off from a helipad or remote area away from which is a continuation - in - part of U . S . patent application persons and property . Further, because of the complexity , Ser. No . 10 /677 ,098 , entitled “ EFFICIENT TRANSAC - 55 numbers of parts , and stability issues , VTOL aircrafts are TIONAL MESSAGING BETWEEN LOOSELY inherently complex and expensive to develop , build and COUPLED CLIENT AND SERVER OVER MULTIPLE maintain . INTERMITTENT NETWORKS WITH POLICY BASED Modular aircraft typically look like traditional aircraft ROUTING ” , filed on Sep . 30 , 2003 , which claims priority to when the vehicle is configured for flight. When configured Provisional Application No. 60 /415 ,546 , entitled “ DATA 60 for driving , the vehicle 's wings (and usually the tail section ) PROCESSING SYSTEM ” , filed on Oct. 1 , 2002 , which are are removed from the aircraft . This creates two problems. incorporated herein by reference in their entirety . First , the vehicle ' s operator must manually remove the wings for driving and reattach the wings for flight. Some FIELD vehicles allow for a single operator to perform the function , 65 while others require multiple persons . Regardless of the This application relates generally to the field of automo - design , many operators do not feel comfortable in their own biles, and more particularly to a type of device that can be skills to attach the wings safely to the aircraft. Also , when US 9 ,776 ,715 B2 the wings and tail are removed , the question becomes one of nical problems, such as a car will change shape, leading to what to do with them . If the wings are left at the airport , then the volume, the weight is increased , limiting the travel of the the operator must return to that same airport in order to fly . land vehicle drivability and flexibility . Thus, there is need This defeats the freedom of having a roadable aircraft. Some for a flying car with more flexibility and driveability , which modular aircraft solve this problem by allowing the wings to 5 overcomes the aforementioned complications . be towed behind the vehicle . The ’ 939 patent is an example of a modular aircraft where the wings and tail are towed SUMMARY behind the vehicle . Integrated aircraft keep the wings attached to the vehicle This summary is provided to introduce a selection of at all times. Typically , the wings are folded , either mechani- 10 concepts in a simplified form that are further described cally or manually , alongside or in the body of the vehicle . An below in the Detailed Description . This summary is not integrated vehicle with mechanically operated wings allows intended to identify key features or essential features of the for the operator of the vehicle to convert from aircraft mode claimed subject matter , nor is it intended to be used as an aid to automobile mode at the ' touch of a button ’. This may add in determining the scope of the claimed subject matter . a considerable amount of practicality to the vehicle . 15 An important object of the present invention is to provide Besides the wings, another aspect of an aircraft that is not a vehicle construction , which may be employed with equal directly compatible with an automobile is the propeller. The facility as a car or as an aircraft for travelling on the road as propeller is the most sensitive part of the aircraft to nicks and well as on air . dents . Because of this , pilots are trained to run their hand In another object, the invention contemplates a vehicle over the propeller before each flight to check for damage . 20 that is compact and capable of flying with great facility and When driving down the road , rocks and other debris are great speed and provided with great lifting power , in any often kicked up by traffic . In modular designs, the propeller medium , such as air , land and /or water, and readily , and is typically part of the structure that is removed in order to automatically convertible from one use to another, without convert the vehicle into an automobile . Therefore , modular loss of time or necessity of getting out of the vehicle . designs typically do not have to worry about the propeller 25 Yet another objective of the invention is to provide a when the vehicle is configured for driving . For integrated vehicle of this type with parachutes at the top center of the designs, the propeller is either removed , such as in U . S . Pat. body of the vehicle , wherein parachutes are adapted to be No . 2 ,430 , 869 , left attached to front of the vehicle ( such as ejected automatically , under all conditions or when the in the “ Fusion ” vehicle by Steve Nichols ), or left attached to engines have stopped operating during flight, permitting a the rear of the vehicle . Some vehicles, which leave the 30 safe landing . propeller attached to the rear of the fuselage, allow the Further objective of the invention is to facilitate the propeller to hang below the vehicle where it is still suscep - design as it was too complicated or too expensive to manu tible to road debris ( such as in U . S . Pat. No . 3 , 371 ,886 ) . In facturer, while most did not satisfy the customer ' s need . order to be practical , the propeller should be protected from These objectives are achieved by the system according to road debris at all times, without the need for the operator to 35 the invention , which is a flying car, having a body, adapted manually remove the propeller . for carrying the payload from once place to another , a tail An aspect of an automobile that is not directly compatible attached to body at rear end adapted for stabilizing the with an aircraft is the fact that the back of an automobile is vehicle , a head at body front end adapted for takeoff , typically a blunt surface . The reason for this includes the plurality of wheels at the bottom of car connected to a power need for a rear bumper , indicator lights (such as turn signals ) 40 transmission system , plurality of foldable wings on the sides and identification devices ( such as license plates ) . Aircraft , of body, adapted for creating the pressure difference and on the other hand , have sharp trailing edges to reduce the creating lift to the vehicle . Further , plurality of jet engines aerodynamic drag while in flight. Having a blunt surface , adapted for driving the jet flying car on surface as well as on such as that on the back of an automobile , would produce a air. A thrust vector control, to controls the direction of the substantial amount of drag on the vehicle when in the air . 45 thrust generated by the engines . And plurality of parachutes This extra drag is at least inefficient and may be unaccept - attached to the flying jet car to safe land the flying jet car able . Modular designs with removable tail structures can under emergency . hide the rear bumper and lights within the structure of the In further exemplary embodiments , modules, subsystems, tail . However , integrated designs must deal with this prob - or devices can be adapted to perform the recited steps . Other lem . The prior art vehicles do not appear to address this 50 features and exemplary embodiments are described below . issue . Either the vehicle has an automotive style aft end and takes the penalty in increased drag , or the vehicle has an BRIEF DESCRIPTION OF DRAWINGS aircraft aft end and does not address the need for bumpers or automotive lighting . Embodiments are illustrated by way of example and not Finally, automobiles are typically designed to be strong 55 limitation in the figures of the accompanying drawings , in and sturdy in order to survive the harsh environment of the which like references indicate similar elements and in road including potholes , bumps, curbs and other typical road which : hazards. This causes automobiles to be heavier than aircraft, FIG . 1 is a close up of the isometric view of the flying jet which only have to deal with runways that are usually well car, according to an embodiment of the present invention . paved . Fortunately , material technology is available now 60 FIG . 2 is a close up of the front view of the flying jet car, that allows for strong reliable structure at a fraction of the according to an embodiment of the present invention . weight of previous automotive structures . FIG . 3 is a close up of the rear view of the flying jet car, As such , while a number of flying car designs have been according to an embodiment of the present invention . contemplated or produced , these designs have in general FIG . 4 is a close up of the top view of the flying jet car, been impractical for use as general purpose driving and 65 according to an embodiment of the present invention . flying vehicles capable of meeting road and air vehicle FIG . 5 is a close up of the left view of the flying jet car, safety standards. Also existing flying car have many tech - according to an embodiment of the present invention . US 9 ,776 ,715 B2 FIG . 6 is a close up of the right view of the flying jet car, FIG . 30 is a close up of the rear view of the flying jet car according to an embodiment of the present invention . on road , according to an embodiment of the present inven FIG . 7 is a close up of the isometric view of flying jet car t ion . with tail wing in normal position , according to an embodi FIG . 31 is a close up of the top view of the flying jet car 5 on road , according to an embodiment of the present inven ment of the present invention . tion . FIG . 8 is a close up of the isometric view of flying jet car FIG . 32 is a close up of the left view of the flying jet car with tail wing in swivelled position , according to an embodi on road , according to an embodiment of the present inven ment of the present invention . tion . FIG . 9 is a close up of the isometric view of flying jet car FIG . 33 is a close up of the right view of the flying jet car with tail wing in upright position , according to an embodi- on road , according to an embodiment of the present inven ment of the present invention . tion . FIG . 10 is a close up of the top view of flying jet car with FIG . 34 is a close up of the isometric view of control of tail wing in upright position , according to an embodiment of lift of jet flying car , according to an embodiment of the present invention . the present invention . 15 FIG . 35 is a close up of the isometric view of control of FIG . 11 is a close up of the left view of flying jet car with take off of jet flying car, according to an embodiment of the tail wing in upright position , according to an embodiment of present invention . the present invention . FIG . 36 is a close up of the isometric view of thrust FIG .. 12 is a close up of thethe rightright view ofof flyingflying jet carcar withwith control of jet flying car, according to an embodiment of the tail wing in upright position , according to an embodiment of 20 present invention . the present invention . FIG . 37 is a close up of the isometric view of right FIG . 13 is a close up of the front view of flying jet car with movement control of jet flying car, according to an embodi tail wing in uprightat position position , accordingaccording to an embodiment of ment of the present invention . the present invention . FIG . 38 is a close up of the isometric view of left FIG . 14 is a close up of the rear view of flying iet car with 25 movement control of jet flying car , according to an embodi ment of the present invention . tail wing in uprightposition , according to an embodimentof FIG . 39 is a perspective view of self - jet and solar cells the present invention . powered all in one roadable aircraft with extended wings FIG . 15 is a close up of the isometric view of the flying and all over solar cells except windows and lights of the jet car with jet engine in normal position , according to an present invention embodiment of the present invention . FIG . 40 is a perspective view of self - jet and solar cells FIG . 16 is a close up of the left view of the flying jet car powered electrical hybrid car without wings of the present with jet engine in upright position , according to an embodi invention . ment of the present invention . FIG . 41 is left side view of self - jet and solar cells powered electrical hybrid car of the present invention . FIG . 17 is a close up of the left view of the flying jet car 35 FIG . 42 is right side view of self - jet and solar cells with jet engine in swivelled position , according to an powered electrical hybrid car of the present invention . embodiment of the present invention . FIG . 43 is front view of self - jet and solar cells powered FIG . 18 is a closelose up of the leftleft viewview of thethe flying jet car electrical hybrid car of the present invention . with jet engine in normal position , according to an embodi FIG . 44 is back view of self- jet and solar cells powered ment of the present invention . 40 electrical hybrid car with two jet engine nozzles of the FIG . 19 is a close up of the isometric view of the jet present invention . engine, according to an embodiment of the present inven - FIG . 45 is top view of self - jet and solar cells powered tion . electrical hybrid car of the present invention . FIG . 20 is a close up of the isometric view of the jet FIG . 46 is top back view of self - jet and solar cells engine , according to an embodiment of the present inven - 45 powered electrical hybrid car showing folded main big jet engine nozzle and two side three bearing duct nozzles of the tion . present invention . FIG . 21 is a close up of the left view of the jet engine , FIG . 47 is top back view of self - jet and solar cells according to an embodiment of the present invention . powered electrical hybrid car showing the main jet engine FIG . 22 is a close up of the right view of the jet engine , nozzle for forward jet powered super speed driving of the according to an embodiment of the present invention . 50 present invention . FIG . 23 is a close up of the top view of the jet engine , FIG . 48 is top back view of self - iet and solar cells according to an embodiment of the present invention . powered electrical hybrid car showing two jet engine FIG . 24 is a close up of the bottom view of the jet engine , nozzles and one main jet engine folded bent down inside the according to an embodiment of the present invention . trunk of the present invention . FIG . 25 is a close up of the front view of the jet engine , 55 FIG . 49 is top back view of self - jet and solar cells according to an embodiment of the present invention . powered electrical hybrid car showing the main jet engine FIG . 26 is a close up of the rear view of the jet engine , nozzle bent down with three bearing swivel of the present according to an embodiment of the present invention . invention . FIG . 27 is a close up of the isometric view of the flying FIG . 50 is top back view of self -jet and solar cells jet car with embedded parachute , according to an embodi- 60 powered electrical hybrid car showing dual jet engine ment of the present invention . nozzles of the present invention . FIG . 28 is a close up of the isometric view of the flying jet car on road , according to an embodiment of the present DETAILED DESCRIPTION invention . FIG . 29 is a close up of the front view of the flying jet car 65 All illustrations of the drawings are for the purpose of on road , according to an embodiment of the present inven - describing selected versions of the present invention and are tion . not intended to limit the scope of the present invention . US 9 ,776 ,715 B2 The following description with reference to the accom according to an embodiment of the present invention . The jet panying drawings is provided to assist in a comprehensive engines include a turbojet engine 190 . The turbojet engine understanding of exemplary embodiments of the invention 190 further comprises an afterburner, a rotating jet with as defined by the claims and their equivalents . It includes hydraulic actuator rotation communicating with the engine various specific details to assist in that understanding but 5 fuel system having a line management electrohydraulic these are to be regarded as merely exemplary . Accordingly, control converter mounted on the turbot engine 190 , wherein those of ordinary skill in the art will recognize that various the afterburners allow for powerful bursts of acceleration . changes and modifications of the embodiments described The turbojet engine 190 further consists of at least one herein can be made without departing from the scope and supercharger, the supercharger is adapted to increase the air spirit of the invention . In addition , descriptions of well - 10 density and the supercharger is adapted for charging batter known functions and constructions are omitted for clarity i es , the batteries are adapted to supply power to an auxiliary and conciseness . power unit , the jet powered hybrid automobile is adapted to The terms and words used in the following description generate power to a battery storage and producing thrust to and claims are not limited to the bibliographical meanings, increase torque. but are merely used by the inventor to enable a clear and 15 The jet engine of the amphibious VTOL unmanned device consistent understanding of the invention . Accordingly , it may be a turbojet , a turbofan , a turboprop , a turboshaft , a should be apparent to those skilled in the art that the ramjet , a scramjet. The jet engine 160 is adapted for short following description of exemplary embodiments of the take off and vertical landing ( STOVL ) , or the flying jet car present invention are provided for illustration purpose only 100 is adapted for vertical takeoff and landing (VTOL ), or and not for the purpose of limiting the invention as defined 20 the flying jet car 100 is adapted for conventional take -off and by the appended claims and their equivalents . landing (CTOL ) , or the flying jet car 100 is adapted for It is to be understood that the singular forms “ a ,” “ an, ” catapult assisted take -off but arrested recovery or catapult and “ the ” include plural referents unless the context clearly assisted take - off barrier arrested recovery (CATOBAR ) . dictates otherwise . In an embodiment the jet engine 160 is a tiltjet, the tiltjets FIG . 1 to FIG . 6 are the different views of an amphibious 25 employs the jet engines 160 , entire propulsion system being VTOL unmanned device shown as the flying jet car 100 , rotated from axial to dorsal to achieve a transition from according to an embodiment of the present invention .Refer - hover or vertical flight to horizontal. In another embodiment, ring to the figures, it can be understood that the present the jet engine 160 is a lift jet , the lift jet is a jet engine 160 invention is a car also called as flying jet car 100 that angled to provide the flying jet car 100 with aerostatic lift operates in the manner of an aircraft but is sized and 30 instead of thrust . designed to be a personal vehicle . Flying jet car 100 com - During the lift, with power being transferred from each of prises a modular and expandable waterproof body shown as the engines 160 to each of the lift fans of the lift fan drive a body 110 also called as fuselage in flight, adapted for systems through a single planetary gearbox , the plurality of carrying the payload from once place to another. An outer turbine engines 160 are also used to power the forward thrust body shell 112 may be associated with the modular and 35 fan drive system through a secondary gearbox . expandable waterproof body and may comprise one or more Furthermore , the flying jet car 100 is used as a thrust pieces . A tail 120 attached to body 110 at rear end adapted vector control to control the direction of the thrust generated for stabilizing the car and further comprises a tail 125 wing by the turbine engines 160. The thrust vector control is The tail wing 125 also called as spoilers is tiltable type controlled by a vectoring nozzle , the vectoring nozzle is which spoils unfavourable air movement across a body 110 40 controlled by the actuators . The thrust vector control is used of a car in motion , usually described as turbulence or drag . to control the direction of thrust of the flying jet car 100 , the The FIG . 7 to FIG . 14 shows the flying jet car 200 with a tail thrust vector control is controlled by a gimbaled thrust wing 225 in different positions , during various stages of the system , the gimbaled thrust system controls a exhaust nozzle flight according to an embodiment of the present invention of the jet car, the jet car is swivelled from side to side , the The flying jet car 100 may have a head 130 at body 110 front 45 nozzle is moved , the direction of the thrust is changed end adapted for takeoff , plurality of wheels 140 at the relative to the center of gravity of the jet car. bottom of car connected to a power transmission system (not The thrust vector control of the flying jet car 100 further shown ) , plurality of foldable wings 150 on the sides of body comprises plurality of bearing swivel module mechanism , 110 , adapted for creating the pressure difference and creating wherein the bearing swivel module controls the thrust direc lift to the vehicle . The flying jet car 100 also has plurality of 50 tion of the flying jet car 100 , the bearing swivel module doors, a windshield , and a dashboard in its construction . The controls are adapted to move the flying jet car 100 in all the major portion of the flying jet car 100 is made of aluminium direction by changing the front bearing swivel module alloy . controls and by changing the rear bearing swivel module Further, a plurality of as jet engines 160 and ducted fans controls . ( such as a ducted fan 390 shown on FIG . 39 ) are adapted for 55 Plurality of parachutes 170 are attached to the flying jet driving the flying jet car 100 on surface as well as on flight. car 100 to safe land the flying jet car 100 under emergency , The plurality of foldable jet engines 160 are attached to wherein a parachute 170 is fixed at the bottom of the flying either sides of the car , two jet engines 160 on front end of jet car 100, two parachutes 170 on front and back of the the flying jet car 100 and two jet engines 160 on rear end of flying jet car 100 . The parachute 170 is a drogue type the flying jet car 100 . The plurality of jet engines 160 can 60 parachute 170 , the drogue parachute 170 is adapted to also be swivelled in any desired direction to assist in lift, rapidly move an object in order to slow the object. FIG . 27 thrusting or during takeoff of the car. The corresponding is a close up of the isometric view of the flying jet car 100 FIGS . 15 to 18 show the different positions of jet engine 160 with embedded parachute 170 , according to an embodiment in a flying jet car 100 , according to an embodiment of the of the present invention . present invention . 65 Apart from the aforesaid features , the flying jet car 100 FIGS. 19 to 26 represents different views of an amphibi - also consists of a cockpit adapted for displaying the flight ous VTOL unmanned device 300 having the jet engines , conditions on the display , a cockpit speech recognition , a US 9 ,776 ,715 B2 10 seseat ejection system adapted for ejecting the seat during aid to help a pilot to avoid obstacles and select landing sites emergency , collision avoiding system etc . Further flying jet in unimproved areas during operating in low - light or low car 100 has a stability system having a plurality of inputs, visibility conditions ; detect and manoeuvre around a man lift including that of a pilot, and a plurality of actuating outputs , during flying ; detect high -tension wires over a desert terrain ; wherein one of the actuating outputs is to control the angular 5 and enable operation in a near earth obstacle rich environ pitch tiltjet, with the change in pitch of the tiltjet varies the ment; and a navigation sensor configured to : map an vertical thrust provided by each jet , wherein the stabilizer unknown area where obstructions limited landing sites ; arrangement includes canards . identify level landing sites with approach paths that are The additional features of the flying jet car 100 includes solar panels 405 , 406 , 407 , and 408 as shown on FIG . 39 to 10 accessible for evacuating a simulated casualty ; build three FIG . 50 , wherein the solar panels 405 , 406 , 407 , and 408 are dimensional maps of a ground and find obstacles in a path ; fixed on the top of the wings 150 , body 110 , the solar panels detect four- inch - high pallets , chain link fences, vegetation , 405 , 406 , 407 , and 408 are chrome plated , the solar panels people and objects that block a landing site ; enable continu 405 , 406 , 407 , and 408 give an electric charge to batteries, ously identifying potential landing sites and develop landing for power to generators, the solar panels 405 , 406 , 407 , and 15 approaches and abort paths; select a safe landing site being 408 supply energy to an auxiliary power unit (APU ) . closest to a given set of coordinates ; wherein the navigation The flying jet car 100 further consists of capturing of the sensor includes an inertial sensor and a laser scanner con flight and environmental conditions by plurality of cameras, figured to look forward and down , wherein the navigation the cameras are adapted for surveillance . And also flying jet sensor is paired with mapping and obstacle avoidance soft car 100 comprises of a slow landing system , to assist the 20 ware, the mapping and obstacle avoidance software being flying jet car 100 land slowly and steadily . operable to keep a running rank of the landing sites, Adding to all, the flying jet car 100 further consists of at approaches and abort paths to enable responding to unex least one two way telemetry device , a broad cast device , a pected circumstances, wherein the system includes an open collision avoidance system , a processor, a navigation device , source code and an open source software development kit , and plurality of sensors ( not shown ) . The flying jet car 100 25 wherein the one or more sensors are selected from a group further includes electronic speed controllers , a video trans comprising: individual sensors , stereo sensors, ultrasonic mitter, one or more antennas , a radio control receiver, and a sensors , infrared sensors , multispectral sensors , optical flow power distribution board . The processor may be configured sensors , and volatile organic compound sensors, wherein the to control at least vectoring of a gimbaled swivel propulsion one or more sensors are provided for intelligent positioning , (GSP ) thrust associated with a GSP system to control a 30 collision avoidance, media capturing, surveillance, and direction of a thrust generated by the plurality of VTOL jet monitoring engines . The electronic speed controllers are selected from FIGS. 28 to 33 and FIGS. 34 to 38 represents operation of a standalone electronic speed controller and an electronic the flying jet car 100 on road and on air respectively . In an speed controller integrated into the power distribution board . embodiment of the present invention the flying jet car 100 The flying jet car 100 further includes printed parts selected 35 can be operated on road as well as on air . On road the jet from 3 - dimensional (3D ) printed parts and 4 -dimensional engine 160 generates the power which propels the car to (4D ) printed parts . move , whereas during flight mode foldable wings 150 are The one way and two way telemetry device is configured open and various mechanisms are involved to fly the car , the to control an on screen display to inform a user of battery control mechanisms involved during transferring the pay voltage , current draw , signal strength , minutes flown , min - 40 load from once place to another are stabilizing the flying jet utes left on battery, joystick display , flight and dive mode car 100 obtained from a tail 120 , wherein the stabilizing of and profile, amperage draw per unit of time, GPS latitude flying jet car 100 is obtained by a wing tail and at least one and longitude coordinates , an operator position relative to a horizontal stabilizers , pitching of a tilt jet according to the position of the flying jet car 100 , number of GPS satellites, required lift. Tilting arrangement is adapted for titling the and artificial horizon displayed on a wearable device , the 45 tilting engines 340. The folding or unfolding is adapted for wearable device being selected from a tablet, a phone , and folding or unfolding of the wing of the flying jet car 100 the headset, wherein the one way and two way telemetry based on the flight requirement. Thrust vectoring is con device is configured to provide a follow -me mode when the trolled by a thrust control mechanism , wherein the thrust flying jet car 100 uses the wearable device as a virtual tether vectoring is controlled by a three bearing swivel module , to track the user via the camera when the user moves, 50 wherein the three bearing swivel module controls the thrust wherein the live broadcast device comprises an onboard direction of the flying jet car 100 , the bearing swivel module High Definition Multimedia Input port operable to transmit is adapted to move the flying jet car 100 in all directions by standard definition , high definition , virtual reality , and inter - changing the front bearing swivel module controls and by active video to one or more bystanders , wherein the inter - changing the rear bearing swivel module controls . active video is broadcasted on at least one of the following: 55 While certain features of the invention have been illus a screen , a projector, a split screen , a switch screen , and the trated and described herein , many modifications, substitu headset, wherein the live broadcast device further comprises tions, changes , and equivalents will now occur to those of an aerial, ground , and marine vehicle for filming the flying ordinary skill in the art. It is , therefore , to be understood that jet car 100 . the appended claims are intended to cover all such modifi The processor includes a flight controller , wherein the 60 cations and changes as fall within the true spirit of the flight controller is selected from an externalmicro controller invention . or an internal micro controller and a barometer , an acceler While various embodiments have been shown and ometer , a gyroscope a GPS and a magnetometer. described , it will be understood that there is no intent to limit The navigation device is configured to enable autonomous the invention by such disclosure , but rather, it is intended to flying at low altitude and avoiding obstacles ; evaluate and 65 cover all modifications and alternate constructions falling select landing sites in an unmapped terrain ; land safely using within the scope of the invention , as defined in the appended a computerized self -generated approach path ; enable a pilot claims . US 9 ,776 ,715 B2 11 12 What is claimed is : a plurality of parachutes attached to the amphibious 1 . An amphibious vertical takeoff and landing (VTOL ) VTOL unmanned device to safely land the amphibious unmanned device with an artificial intelligence ( AI) data VTOL unmanned device in an emergency, wherein at processing mobile and wearable apparatus , the amphibious least one parachute of the plurality of parachutes is VTOL unmanned device comprising : 5 fixed to each of: the bottom of the amphibious VTOL a modular and expandable waterproof body adapted for unmanned device , the front end of the amphibious carrying a payload ; VTOL unmanned device , and the rear end of the an outer body shell associated with the modular and amphibious VTOL unmanned device . expandable waterproof body and comprising one or 2 . The amphibious VTOL unmanned device of claim 1 , more pieces ; 10 further comprising a plurality of doors , a windshield , a a gimbaled swivel propulsion (GSP ) system , the GSP dashboard , and a tail wing . system comprising a plurality of VTOL jet engines and 3. The amphibious VTOL unmanned device of claim 2 , VTOL ducted fans associated with a plurality of wherein the stabilizing of the amphibious VTOL unmanned motors , wherein the plurality of VTOL jet engines are 16 device is obtained by the tail wing and at least one horizontal selected from turbojet engines , turbofan engines, and stabilizer. foldable variable pitch tilting engines , wherein the 4 . The amphibious VTOL unmanned device of claim 1 , VTOL ducted fans include at least a multi- blade ducted wherein the foldable variable pitch tilting engines of the fan , the plurality of VTOL jet engines being adapted for plurality of VTOL jet engines are attached to sides of the driving the amphibious VTOL unmanned device on a 20 modular and expandable waterproof body, and wherein two surface and in a flight, wherein the turbojet engines of the plurality of VTOL jet engines are attached to a front comprise afterburners configured to rotate a fuel jet end of the modular and expandable waterproof body, and with hydraulic actuator rotation and communicating wherein further two of the plurality of VTOL jet engines are with an engine fuel system of the amphibious VTOL attached to the rear end of the modular and expandable unmanned device , the engine fuel system having a line 25 waterproof body . management electro -hydraulic control converter 5 . The amphibious VTOL unmanned device of claim 1 , mounted on the turbojet engines, wherein the afterburn - further comprising batteries and at least one supercharger, ers allow for bursts of acceleration of the fuel jet; wherein the at least one supercharger is adapted to increase a processor, electronic speed controllers , a two -way air density, and wherein the at least one supercharger is telemetry device , a video transmitter , a radio control 30 adapted for charging the batteries , wherein the batteries are receiver, and a power distribution board , the processor adapted to supply power to an auxiliary power unit . being configured for controlling at least vectoring of a 6 . The amphibious VTOL unmanned device of claim 5 , GSP thrust associated with the GSP system to control wherein the batteries are partially or completely modular a direction of a thrust generated by the plurality of batteries, and wherein the electronic speed controllers are VTOL jet engines , wherein the electronic speed con - 35 configured to detach from an electronic speed controller trollers are selected from a standalone electronic speed stack , the video transmitter and the radio control receiver are controller and an electronic speed controller integrated removable for upgrading, the two -way telemetry device is into the power distribution board ; removable for upgrading , the plurality of motors are remov an electrical machine comprising a stator electrically able for upgrading , and the processor is configured to detach connected to an electrical power storage device , 40 from the power distribution board , wherein the batteries wherein the electricalmachine acts as an electric motor include a lithium ion polymer battery that conforms to an for driving rotation of the plurality of VTOL jet engines interior profile of the modular and expandable waterproof by using the electrical power storage device , and body and includes a built- in battery charge indicator. wherein the electrical machine with the plurality of 7 . The amphibious VTOL unmanned device of claim 5 , VTOL jet engines act as an electrical power generator 45 wherein the two -way telemetry device is configured to for re -charging the electrical power storage device; control an on screen display of the AI data processing mobile an onboard electricity generator comprising a plurality of and wearable apparatus to inform a user about a battery solar cells , wherein the onboard electricity generator voltage of the batteries , a current draw , a signal strength , includes carbon fiber hybrid solar cells ; minutes flown , minutes of operation left for the batteries , a printed parts selected from 3D printed parts and 4D 50 flight and dive mode and profile , an amperage draw per unit printed parts ; of time, GPS latitude and longitude coordinates , an operator a light detection and ranging (LIDAR ) device , an ultra - position relative to a position of the amphibious VTOL sonic radar sensor, and a plurality of sensors ; unmanned device , number of GPS satellites , and artificial a tail attached to the modular and expandable waterproof horizon displayed on the AI data processing mobile and body at a rear end and adapted for stabilizing the 55 wearable apparatus, the AI data processing mobile and amphibious VTOL unmanned device ; wearable apparatus being selected from a tablet , a phone , a head VTOL ducted fan attached to the modular and and a headset , wherein the two way telemetry device is expandable waterproof body at a front end and adapted configured to provide a follow -me mode when the amphibi for VTOL ; ous VTOL unmanned device uses the AI data processing a plurality of wheels at a bottom of the amphibious VTOL 60 mobile and wearable apparatus as a virtual tether to track the unmanned device connected to the power distribution user via one or more cameras when the user moves . board ; 8 . The amphibious VTOL unmanned device of claim 1 , a plurality of foldable wings on sides of the modular and further comprising one or more modules attached to the expandable waterproof body , the plurality of foldable modular and expandable waterproof body , the one or more wings being adapted for creating a pressure difference 65 modules are selected from a group comprising : a waterproof and creating a lift associated with the amphibious battery module , a camera stabilization device , a thermal VTOL unmanned device ; and inspection device , an environmental sample processor , a US 9 ,776 ,715 B2 13 14 seismometer, a spectrometer , an osmosampler , and a night one or more further sensors and one or more cameras vision device , and wherein the plurality of VTOL jet engines configured to control one or more of the following : include a turbine engine . obstacle avoidance , terrain and Geographical Informa 9 . The amphibious VTOL unmanned device of claim 8 , tion System mapping, close proximity flight including wherein the turbine engine is configured to transfer power to 5 terrain tracing , and crash resistant indoor navigation , an each of VTOL ducted fans of a lift fan drive system through autonomous takeoff , an auto - fly or dive to a destination a single planetary gearbox . with at least one manually or automatically generated 10 . The amphibious VTOL unmanned device of claim 1 , flight plan , an auto - fly or dive to the destination by wherein the modular and expandable waterproof body has a tracking monuments , a direction lock , a dual operator back portion and a front portion , wherein the back portion 10 control; and the front portion show colors , wherein the device is a transmitter and receiver control device comprising one configured to be launched from a body of a user , wherein the or more antennas , the one or more antennas including amphibious VTOL unmanned device is controlled by the high gain antennas ; user using the AI data processing mobile and wearable the transmitter and receiver control device further com apparatus via motion gestures , buttons, and a touch screen of 15 prising a lock mechanism operated by one or more of the AI data processing mobile and wearable apparatus, the following : numerical passwords , word passwords , wherein the amphibious VTOL unmanned device is operable fingerprint recognition , face recognition , eye recogni to perform an automatic landing and an automatic takeoff , tion , and a physical key . wherein the amphibious VTOL unmanned device is config 13 . The amphibious VTOL unmanned device of claim 12 , ured in a form of one of the following : a people - carrying 20 wherein the flight and dive control device is configured to : vehicle , a cargo -carrying vehicle , a radio controlled toy, an perform stable transitions between a hover mode, a full autonomous vehicle , a multi - blade ducted fan roadable forward flight mode, and an underwater mode; electric aircraft, an uncrewed vehicle , a driverless car, a enable or disable a GPS ; self- driving car , an unmanned aerial vehicle , a drone, a record flight parameters ; robotic car, a commercial goods and passenger carrying 25 allow inverted flight, aerial and aquatic rolls and flips ; vehicle , and a private self - drive vehicle ; stabilize proportional, integral, and derivative gains above wherein the autonomous vehicle is configured to sense water and below water ; environmental conditions, navigate without a human restrict the amphibious VTOL unmanned device to fly input, and perform auto -piloting , wherein the sensing is safe locations; performed via the plurality of sensors , the plurality of 30 receive and enact force shut -off commands associated sensors including , one or more of the following : a with a manufacturer ; radar, a Global Positioning System (GPS ) module , and receive software updates from the manufacturer ; a computer vision module ; wherein the processor is activate the amphibious VTOL unmanned device after a operable to interpret sensory information to identify user provides an input; navigation paths, obstacles and signage ; wherein the 35 provide thrust compensation for body inclination of the autonomous vehicle is configured to update maps based modular and expandable waterproof body by acting as on a sensory input to keep track of a position of the a body pitch suppressor of the modular and expandable amphibious VTOL unmanned device when conditions waterproof body to maintain an altitude in a forward change or when the amphibious VTOL unmanned flight; and device enters uncharted environments ; 40 compensate yaw and roll mixing when rotors of the wherein the multi -blade ducted fan roadable electric air amphibious VTOL unmanned device tilt . craft is propelled by one or more electric motors of the 14 . The amphibious VTOL unmanned device of claim 1 , plurality ofmotors using electrical energy stored in the further comprising : electrical power storage device ; and a navigation device configured to : wherein the AI data processing mobile and wearable 45 enable autonomous flying at low altitude and avoiding apparatus enables the user to submit a trip request, the obstacles ; trip request being routed to the amphibious VTOL evaluate and select landing sites in an unmapped ter unmanned device to initiate a peer - to -peer pick up rain ; service or a cargo transportation . land safely using a computerized self - generated 11 . The amphibious VTOL unmanned device of claim 1, 50 approach path ; wherein the GSP system is powered by : enable a pilot aid to help a pilot to avoid obstacles and a high pressure gas ; and wherein the VTOL ducted fans select landing sites in unimproved areas during oper are attached directly to a motor shaft associated with ating in low - light or low - visibility conditions; one or more of the plurality of motors or are mechani detect and maneuver around a man lift during flying ; cally linked to the one or more of the plurality of 55 detect high - tension wires over a desert terrain ; and motors through a series of pulley belts . enable operation in a near earth obstacle rich environ 12 . The amphibious VTOL unmanned device of claim 1, ment; and further comprising a collision avoidance , flight stabilization , wherein the plurality of sensors include a navigation and multi- rotor control system , the collision avoidance , sensor configured to : flight stabilization , and multi - rotor control system compris - 60 map an unknown area where obstructions limit landing ing: sites ; a flight and dive control device configured to perform one identify level landing sites with approach paths that are or more of the following : auto level control, altitude accessible for evacuating a simulated casualty ; hold , return to an operator automatically , return to the build three - dimensional maps of a ground and find operator by manual input, operating an auto - recogni - 65 obstacles in a path ; tion camera , monitoring a circular path around a pilot, detect four- inch - high pallets , chain link fences, vegeta and controlling autopilot; tion , people and objects that block a landing site ; US 9 ,776 ,715 B2 15 16 enable continuously identifying potential landing sites 26 . The amphibious VTOL unmanned device of claim 1, and develop landing approaches and abort paths; wherein the plurality of solar panels are fixed on a top of the select a safe landing site being closest to a given set of plurality of foldable wings and the modular and expandable coordinates ; waterproof body, the plurality of solar panels being chrome wherein the navigation sensor includes an inertial sen - 5 plated , the plurality of solar panels providing power to the sor and a laser scanner , onboard electricity generator. wherein the navigation sensor is paired with mapping 27 . A system of controlling an amphibious vertical takeoff and obstacle avoidance software, the mapping and and landing (VTOL ) unmanned device with an artificial obstacle avoidance software being operable to keep intelligence (AI ) data processing mobile and wearable the a running rank of the landing sites, the landing 10 system of controlling the amphibious VTOL unmanned approaches and the abort paths to enable responding device comprising : to unexpected circumstances . a processor configured to : 15 . The amphibious VTOL unmanned device of claim 14 , stabilize the amphibious VTOL unmanned device, wherein the mapping and obstacle avoidance software wherein the stabilizing of the amphibious VTOL includes an open source code and an open source software 15 unmanned device is performed by at least one wing tail development kit . stabilizer and at least one horizontal stabilizer of the 16 . The amphibious VTOL unmanned device of claim 1 , amphibious VTOL unmanned device by pitching at wherein the plurality of sensors are selected from a group least one tilting jet engine of a plurality of VTOL jet comprising : individual sensors, stereo sensors , ultrasonic engines of the amphibious VTOL unmanned device sensors , infrared sensors , multispectral sensors , optical flow 20 according to a required lift and using a plurality of lift sensors, and volatile organic compound sensors , wherein the fans of the amphibious VTOL unmanned device ; plurality of sensors are provided for intelligent positioning , perform a tilting arrangement of the amphibious VTOL collision avoidance , media capturing, surveillance , and unmanned device , the tilting arrangement is adapted for monitoringm . tilting the at least one tilting jet engine of the plurality 17 . The amphibious VTOL unmanned device of claim 1 , 25 of VTOL jet engines of the amphibious VTOL wherein the plurality of VTOL jet engines are adapted for unmanned device ; VTOL , short takeoff and vertical landing (STOVL ) , con fold and unfold a plurality of foldable wings of the ventional takeoff and landing ( CTOL ), and catapult assisted amphibious VTOL unmanned device; takeoff barrier arrested recovery (CATOBAR ) . vector a gimbaled swivel propulsion (GSP ) thrust, 18 . The amphibious VTOL unmanned device claim 1 , 30 wherein the vectoring is controlled by a thrust control wherein the plurality of VTOL jet engines include a tilt jet mechanism ; and a lift jet , the lift jet being a jet engine angled to provide wherein the vectoring of the GSP thrust is controlled by aerostatic lift. a plurality of bearing swivel modules , wherein the 19 . The amphibious VTOL unmanned device of claim 18 , plurality of beating swivel modules control a thrust further comprising a stability system being controlled by a 35 direction of the amphibious VTOL unmanned device, plurality of inputs including inputs of a pilot, and a plurality the plurality of bearing swivel modules are adapted to of actuating outputs , wherein one of the plurality of actuat move the amphibious VTOL unmanned device by ing outputs is to control an angular pitch of the tilt jet. controlling a front bearing swivel module of the plu 20 . The amphibious VTOL unmanned device of claim 1 , rality of bearing swivel modules and by controlling a wherein the GSP system is configured to perform GSP thrust 40 rear bearing swivel module of the plurality of bearing vector control by a vectoring nozzle . swivel modules ; 21 . The amphibious VTOL unmanned device of claim 20 , wherein the vectoring of the GSP thrust is further con wherein the GSP thrust vector control is used to control the trolled by a vectoring nozzle of the amphibious VTOL direction of a thrust of the amphibious VTOL unmanned unmanned device, the vectoring nozzle is controlled by device , the GSP system controls an exhaust nozzle of the 45 actuators associated with the amphibious VTOL amphibious VTOL unmanned device to change a direction unmanned device ; of the thrust relative to a center of gravity of the amphibious wherein the vectoring of the GSP thrust is further con VTOL unmanned device . trolled by a gimbaled thrust system of the amphibious 22 . The amphibious VTOL unmanned device of claim 21 , VTOL unmanned device , the gimbaled thrust system wherein the GSP thrust vector control further comprises a 50 controls the vectoring nozzle of the amphibious VTOL bearing swivel module including a front bearing swivel unmanned device, the direction of the GSP thrust is module and a rear bearing swivel module , wherein the changed relative to a center of gravity of the amphibi bearing swivel module controls the direction of the thrust , ous VTOL unmanned device ; the bearing swivel module being configured to move the charge batteries of the amphibious VTOL unmanned amphibious VTOL unmanned device by controlling the front 55 device via superchargers associated with the amphibi bearing swivel module and the rear bearing swivel module . ous VTOL unmanned device, the batteries are adapted 23 . The amphibious VTOL unmanned device of claim 22 , to supply power to an auxiliary power unit and a battery wherein the bearing swivel module of the GSP thrust vector storage associated with the amphibious VTOL control includes one or more multi - bearing swivels . unmanned device . 24 . The amphibious VTOL unmanned device of claim 1 , 60 28 . The system of claim 27, wherein the processor is wherein the plurality of parachutes include a drogue para configured to control: chute . displaying the flight conditions on a touch screen of the 25 . The amphibious VTOL unmanned device of claim 1 , amphibious VTOL unmanned device, recognizing a further comprising a cockpit configured to display flight speech in a cockpit of the amphibious VTOL unmanned conditions on a display , a seat ejection system adapted for 65 device , a seat ejecting system associated with the ejecting a seat of the amphibious VTOL unmanned device amphibious VTOL unmanned device and adapted for during emergency , and a collision avoiding system . ejecting a seat of the amphibious VTOL unmanned US 9 ,776 ,715 B2 17 device during emergency, and a collision avoiding system of the amphibious VTOL unmanned device ; capturing of flight conditions and environmental condi tions by a plurality of cameras of the amphibious VTOL unmanned device , the plurality of cameras being 5 adapted for surveillance ; opening of a parachute of the amphibious VTOL unmanned device for safe landing of the amphibious VTOL unmanned device during emergency landing and accidents . 29 . The system of claim 27 , wherein the amphibious VTOL unmanned device is made at least of aluminum and carbon fiber; wherein the amphibious VTOL unmanned device com prises the plurality of VTOL jet engines , at least one 15 two -way telemetry device , a broad cast device , a col lision avoidance system , a processor, a navigation device , and a plurality of sensors , the plurality of VTOL jet engines including at least the at least one tilting jet engine . 20 * * * *