Abstract:
An unmanned aerial vehicle/unmanned aircraft system including an airframe; a plurality of rotor assemblies respectively extending from a plurality of arms connected to said airframe, said rotor assemblies each having a rotor thereon with at least one rotor blade; a landing gear extending from said airframe; and a flight controller disposed on said airframe; wherein said flight controller receives instructions for unmanned aerial vehicle/unmanned aircraft system control.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     The present application is a Continuation Application of U.S. patent application Ser. No. 13/200,986, filed Oct. 6, 2011, which issued as U.S. Pat. No. 8,774,982, on Jul. 8, 2014, which claims priority from U.S. Patent Provisional Application No. 61/344,789, filed Oct. 6, 2010, and is a continuation-in-part (CIP) of U.S. patent application Ser. No. 12/805,971, filed Aug. 26, 2010, the contents of all of which are herein incorporated by reference in their entirety. 
    
    
     BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The present invention relates to a helicopter, in reduced scale form, for industrial use, that includes a modular structure, multiple rotors and wireless capability. The reduced scale modular airframe helicopter is remotely controlled, and provides a high performance platform for high or low altitude surveillance, with a payload such as camera systems for photographic missions. The reduced scale helicopter of the present invention may be used for industrial use, for example in surveillance operations, such as border control, crime prevention, military reconnaissance, disaster reconnaissance, etc., and is reliable to achieve a maximum flight time with a minimum of down time. The reduced scale helicopter of the present invention is a state of the art unmanned aerial vehicle/unmanned aircraft system (UAV)/(UAS) helicopter with a built-in autopilot and navigation system that allows for simple flight and usage by remote control, ground station control and non-remote control users. 
     2. Description of the Relevant Art 
     Although reduced scale helicopters are in existence, they suffer from reliability problems, navigation problems, and have long delays in launch time. Further, present day helicopters suffer from a lack of features that would be advantageous in industrial use (used mostly as toys), and are not modular and upgradeable. 
     Thus, a reduced scale helicopter that could be used industrially, which includes state-of-the-art technology with high reliability, modularity, and upgraded features, such as multi-rotors and wireless capability, is desired. 
     SUMMARY OF THE INVENTION 
     The present invention relates to a modular airframe, multi-rotor reduced scale helicopter with wireless capability, that has UAV/UAS and has a built-in autopilot and navigation system that allows for simple flight and usage by remote control, ground station control and non-remote control, users. The reduced scale helicopter with multi-rotor system of the present invention typically includes, in one embodiment, a modular center airframe or chassis, which consists of five (5) layered sections. 
     In a first embodiment, each layer of the airframe of the helicopter has a state-of-the-art “quick connection” (i.e., snap fit, pin connectors, etc.) that allows each of the layers to be easily removed, and another or similar layer to be inserted with the same connections. 
     In one embodiment, the top (first) layer of the airframe contains a global positioning satellite (GPS) receiver electrical device which is connected via an electrical connection, to the autopilot system in the second layer. The GPS receives satellite data, which data is sent in real-time to the autopilot, which uses it to identify the location of the helicopter in latitude, longitude, altitude, and velocity, and in real-time. 
     The second layer includes any state-of-the-art Commercial-off-the-Shelf (COTS) autopilot, which is connected to the electrical panel. The autopilot connects via the central “quick connect” system to separate speed controllers for the different motors of the helicopter in the fourth layer. Because the autopilot system is serial and modular, the autopilot can control from 4-8 speed controllers and motors in the fourth layer. These connections allow the autopilot to direct each of the different motors in order to maneuver the aircraft in any of X, Y or Z directions in the air. 
     The autopilot is connected to a wireless communication transmitter/receiver in the second layer, which transmits and receives wireless instructions from the ground station. The autopilot is also connected to a standard RC receiver, and has an electrical connector board that connects it to the autopilot. This separate connection allows the standard RC wireless transmitter/receiver to send separate instructions to the autopilot for vehicle control. 
     The autopilot is also connected to the electrical system in the second layer. The electrical power panel/conditioning system controls each rotor that is contained in the fourth layer. This electrical system allows the batteries in the third layer, not to be “overcharged” or to stop expending energy before the discharge completely. This electrical device conditions the power and acts as an adjustable speed regulator for the motors in the fourth layer. 
     A daylight-readable 2″-4″ LCD screen in the second layer, is connected via electrical wiring to the electrical panel and to the autopilot and other systems. Also mounted in the second layer is an optional data card which is used to save autopilot data collected from up to approximately 100 flights. 
     The helicopter has four, six, or eight rotors which are each connected via a shaft/wing to a separate speed controller. Each of the rotors is mounted horizontally on the end of shaft/wing, and at the top of the rotor is the rotor head assembly that has 2-6 rotor blades connected to it. 
     Each of the rotors&#39; shaft/wing is connected in a “spoke” back to the main chassis in the fourth layer which allows for the shaft/wing to be connected and disconnected using a state-of-the art connector system. The chassis contains openings or slots for four (4), six (6), or eight (8) arms with associated motor speed controllers. Thus, the appropriate layer with the appropriate number of shaft/wings or arms and rotors can be chosen by the user in assembling the aircraft. 
     In one exemplary embodiment, each arm/wing is connected via a hinged “connect/disconnect” mechanism that allows the entire wing/arm with attached motor mount and motor to be folded in parallel with each other (i.e., vertically). The arms/wings can be opened via a spring or piston per arm/wing, that would allow either a user actuated “release” or an automated “release” for launch, for example, and the arms/wings would open up into a flight position after launch. 
     In one embodiment, a rotor guard connects to the arms/wings and extends ⅕″ beyond the reach of the 4/6/8 blades, to allow the vehicle to come in contact with a vertical surface and the blades attached to the motors will not strike the vertical surface. 
     In one embodiment, the landing gear includes four (4) lightweight durable material, tubes that also slide into the fourth layer at a 45 degree angle with small rubber “feet” attached to the end, with the other end being attached inside the fourth layer via the “quick connect” system. In one embodiment, the landing gear can be folded parallel to one another for launch, and with a user-actuated or automated release, would spring back into landing position after launch. 
     In one embodiment, the helicopter carries a payload (i.e., camera) of several ounces to several pounds. In one embodiment, the camera system has the ability to allow for a remote wireless 2.4 Ghz RC transmitter and receiver system, for example, of a hand-held video and remote system, to remotely control a 360 degree left- and right-turning movement, with a 0-90 degree pan and tilt mechanism. This allows a user to move the camera while the helicopter is in operation at, for example, an altitude up to 12,000 ft, and a distance of up to 5 miles from the hand-held video and remote unit. 
     In a second embodiment, the helicopter layers are assembled together in a vertical, circular stacked arrangement, and are covered by a dome-shaped cover that secures to layer by suitable fasteners. In this second embodiment, there is a central core stacked shelf system, with the electronics disposed in an outer ring configuration around the fan of an air cooling system. In this configuration, the layers are implemented together, with the GPS disposed above the autopilot etc., and with the elements of the various layers being disposed in a ring-like configuration around the fan of the air cooling system. 
     In this second embodiment, a combination landing gear and camera mount is used. However, the combination landing gear/camera mount system can also be used with the first embodiment, with the landing gear legs of the first embodiment removed. 
     The helicopter has full autopilot operation via two separate modes—a hand-held remote control mode, and a ground station mode. 
     There has thus been outlined, some features that are consistent with the present invention in order that the detailed description thereof that follows may be better understood, and in order that the present contribution to the art may be better appreciated. There are, of course, additional features consistent with the present invention that will be described below and which will form the subject matter of the claims appended hereto. 
     In this respect, before explaining at least one embodiment consistent with the present invention in detail, it is to be understood that the invention is not limited in its application to the details of construction and to the arrangements of the components set forth in the following description or illustrated in the drawings. Methods and apparatuses consistent with the present invention are capable of other embodiments and of being practiced and carried out in various ways. Also, it is to be understood that the phraseology and terminology employed herein, as well as the abstract included below, are for the purpose of description and should not be regarded as limiting. 
     As such, those skilled in the art will appreciate that the conception upon which this disclosure is based may readily be utilized as a basis for the designing of other structures, methods and systems for carrying out the several purposes of the present invention. It is important, therefore, that the claims be regarded as including such equivalent constructions insofar as they do not depart from the spirit and scope of the methods and apparatuses consistent with the present invention. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a perspective view of a schematic drawing of a first embodiment of the helicopter of the present invention. 
         FIG. 2  is a top view of  FIG. 1   
         FIG. 3  is. an exploded view of  FIG. 1 . 
         FIG. 4  is a schematic showing the elements of the layers of the helicopter according to the first embodiment of the present invention. 
         FIG. 5  is a perspective view of a partially assembled second embodiment of the helicopter of the present invention. 
         FIG. 6  is a cross-sectional view of the internal features of the airframe of  FIG. 5 . 
         FIG. 7  is a perspective view of the combination landing gear and camera mount of the helicopter according to the second embodiment of the present invention. 
     
    
    
     DESCRIPTION OF THE INVENTION 
     The present invention relates to a modular airframe, multi-rotor reduced scale helicopter  10  with wireless capability, that has UAV/UAS and has a built-in autopilot and navigation system that allows for simple flight and usage by remote control, and non-remote control, users. The present invention includes similar elements and features to the reduced scale helicopter disclosed in U.S. patent application Ser. No. 12/805,971 (and incorporated by reference), from which this application is a continuation-in-part (CIP). 
     The reduced scale helicopter  10  with multi-rotor system of the present invention typically includes, in one embodiment, a modular center airframe or chassis  100 , which consists of five (5) layered sections ( 101 - 105 ) (see  FIGS. 1 and 3 ). However, one of ordinary skill in the art would know that more or less layers would be feasible, as long as the helicopter  10  has the disclosed operable features. 
     In a first embodiment, each layer  101 - 105  of the airframe  100  of the helicopter  10  has a state-of-the-art “quick connection” (i.e., snap fit, pin connectors, etc.) that allows each of the layers  101 - 105  to be easily removed, and another or similar layer to be inserted with the same connections. 
     The airframe or chassis  100  of the multi-rotor helicopter  10  of the present invention is comprised of a strong, durable material that is lightweight in order to reduce weight requirements for lift. In exemplary embodiments, the airframe  100  may be made of PVC plastic, carbon fiber, or injection-molded plastic and resin. 
     The reduced scale helicopter  10  of the present invention has standard dimensions, in an exemplary embodiment, of approximately 6-12 inches in height, 6-12 inches in length, a rotor diameter of approximately 6-12 inches (for each rotor), a weight of approximately 2-5 pounds, and engine power of approximately 0.25 Hp-1 Hp/motor (for each motor). However, one of ordinary skill in the art would know that the size and weight for lift of the reduced helicopter  10  depends on the scale desired, as long as the helicopter  10  meets the operable features described herein. 
     The layers  101 - 105  of the airframe  100  of the helicopter  10  are described as follows, but one of ordinary skill in the art would know that the elements described in each layer could be rearranged or provided in different layers as long as functionality is not affected. All elements in the layers  101 - 105  are grounded and attached to the body frame  100 . 
     In one embodiment, layer  101  of the airframe  100  contains a global positioning satellite (GPS) receiver electrical device  106  (see  FIG. 4 ), which is connected via an electrical connection, to the autopilot system  107  in layer  102 . The GPS electrical device  106  is connected to GPS antennae  108  that receive satellite data, which data is sent in real-time to the autopilot  107 , and which the autopilot  107  uses to identify the location of the helicopter  10  in latitude, longitude, altitude, and velocity, and in real-time. The GPS device  106  has a “quick connection” (as described above and throughout the present application) to the layer below (i.e., layer  102 ) for power, and data communications. The GPS module  106  can be a standard GPS card with antennae  108 , and which works with all the major navigational systems in use to receive, for example, LP1, LP2, Omnistar™, or Glosnas™ systems. 
     The airframe  100  houses any state-of-the-art Commercial-off-the-Shelf (COTS) autopilot  107  in layer  102 . The autopilot  107  is encased in a magnetic flux-resistant aluminum box lined with electromagnetic tape for electromagnetic interference (EMI) shielding. The autopilot system  107  is connected to the electrical panel  109 , also in layer  102 . The autopilot  107  then connects via the central “quick connect” system to separate speed controllers  110  for the different motors  111  of the helicopter  10 , in layer  104 . Because the autopilot system  107  is modular, the autopilot  107  can control from 4-8 speed controllers  110  and motors  111  in layer  104 . These connections allow the autopilot  107  to direct each of the different motors  111  in order to maneuver the aircraft  10  in any of X, Y or Z directions in the air. 
     The autopilot  107  provides power and is connected to a wireless communication transmitter/receiver  112  in layer  102 , which transmits and receives wireless instructions from the ground station (not shown, but described in U.S. patent application Ser. No. 12/805,971). The autopilot  107  is also connected to a standard RC receiver  113 , and has an electrical connector board  114  that connects it to the autopilot  107 . This separate connection allows the standard RC wireless transmitter/receiver  113  in layer  102  to send separate instructions to the autopilot  106  for vehicle control. The wireless receiver  112  has two (2) separate wireless antennae that are connected to, and receive power from the electrical connector board  114  of the helicopter  10 . 
     The autopilot  107  may include standard processing and memory capability, including a central processing unit (CPU), RAM, wireless communication interfaces, and/or other components. The autopilot  107  may include, or be modified to include, software that may operate to provide various functionality, such as data gathering. The autopilot  107  may be implemented as an application run on existing computer operating systems. The autopilot  107  application may be ported to other personal computer (PC) software, and/or any other digital device with appropriate storage capability. 
     The processor of the autopilot  107  may access a memory in which may be stored at least one sequence of code instructions that may include the software program for performing predetermined operations. While the system of the present invention may be described as performing certain functions, one of ordinary skill in the art will readily understand that the software program may perform the function rather than the entity of the system itself. The memory may be a storage device that stores at least one data file, such as image files, text files, data files, audio files, video files, among other file types. 
     Further, although the above-described features and processing operations may be realized by dedicated hardware, or may be realized as programs having code instructions that are executed on data processing units, it is further possible that parts of the above sequence of operations may be carried out in hardware, whereas other of the above processing operations may be carried out using a software program. Further, although specific components of the system have been described, one skilled in the art will appreciate that the system suitable for use with the methods and systems of the present invention may contain additional or different components. 
     The autopilot  107  is connected horizontally to a damped panel  116  in layer  102 . This damped panel  116  is then mounted via vibration mounts  117  in layer  102  (shown also in  FIG. 6 , for example). Thus, the autopilot  107  is contained inside of the airframe  100  with a dual vibration mount  117  from the X, Y and Z axes. There is a primary autopilot shelf  119  that is vibration isolated in the X and Y axes (see also  FIG. 6 , for example). All elements  107 ,  116 ,  117 ,  119  are set and mounted for shock and vibration via silicone bushings  118  in layer  102  (see also  FIG. 6 ). 
     The autopilot  107  is also connected to the electrical system  109  in layer  102 . The electrical power panel/conditioning system  109  controls each rotor  122  that is contained in layer  104 . This electrical system  109  allows the batteries  123  (see layer  103 ) not to be “overcharged” or to stop expending energy before the batteries  123  in layer  103  discharge completely. This electrical device  109  conditions the power and acts as an adjustable speed regulator for the motors  111  in layer  104 . 
     Also mounted inside the airframe  100  is a daylight-readable 2″-4″ LCD  124  screen that is connected via electrical wiring to the electrical panel  109  and to the autopilot  107  and other systems in layer  102 . This LCD  124  displays the status of the helicopter  10  and presents several different error codes in user-based languages (note: the helicopter  10  is set up with English as the primary language). The status and error codes which are programmed into the helicopter  10  software include: a) Status of the Autopilot; b) Satellite reception and grade of satellite reception; c) Power indication of % power used and % power available for both the main and autopilot sources; d) Helicopter  10  overall system health and ability to fly; e) Vehicle rotor RPM; and f) Stability mode of the helicopter  10 —i.e., Fully Stabilized, Partially Stabilized, or Remote Control (RC) Mode. 
     Also mounted in layer  102  module is an optional data card  125 . The data card  125  works in conjunction with the onboard electrical system  109 ,  114 , LCD panel  124 , and autopilot  107 . This data card  125  is commonly known as a black box recorder, and is used to save autopilot  107  data collected from up to approximately 100 flights (amount predetermined and programmed). The autopilot system  107  posts full data from all in-flight sensors and data channels to the data recorder/memory. These data channels include all avionics (i.e., X, Y, Z motion, command inputs, GPS  106  data, ground station unit input, etc.), and custom sensors mounted on the mini-helicopter platform  10 . The data card  125  is removable and allows for read-and-write capability. 
     In one embodiment, there are five (5) primary sensors, including a magnetometer  126  for compass headings, three (3) inertial measurement units (IMUs)  127  for X, Y and Z axis movements, and the GPS  106  for latitude, longitude and altitude), that indicate position and attitude of the helicopter  10  and feed into the primary power panel  109 . In an exemplary embodiment, the magnetometer  126  is connected to the onboard GPS receiver  106 , for example, and allows for the input of directional information to the autopilot  107  based upon magnetic compass readings. 
     The power of the mini-helicopter system  10  is powered with batteries  123  that are located in the battery compartment or layer  103  of the airframe  100 . Each battery  123  has a +/− connection lead that plugs into the airframe  100  via a “quick release” connector. There are two (2) main 12 Volt-4,000-6,000 LiPo batteries that have “quick release” connectors that can “slide into” and lock, and “slide out” for replacement, and connect into the electrical panel  109  for use by the 4/6/8 rotors  130  in layer  104 . There are battery terminals and transformers for the 12 volt systems. 
     In an alternative embodiment, layer  103  also includes the ability for a single “slide lock” battery unit  123 , as disclosed in U.S. patent application Ser. No. 12/805,971. In an exemplary embodiment, this battery unit  123  has 2 LiPo batteries on the inside with a single housing and an integrated handle. This battery unit  123  is supported by a “rail” system on the bottom of layer  103  and a matching rail system on the top of the battery unit  123 . This allows a user to pull a lever and “lock” or “release” the battery unit  123 . Once the lever is set to lock, the battery  123  has a locking mechanism that will keep the battery unit locked to the primary chassis  100 . Once the lever to release the battery unit  123  has been implemented, the battery unit  123  can be slid out from the primary chassis  100  and replaced with another unit. This allows the battery unit  123  to be recharged, and helicopter  10  to keep a full charge. 
     In one embodiment, the batteries  123  may be used in harsh weather, such as under temperatures from −20 to 120 Fahrenheit, and at high altitude situations above 10,000 feet, without loss of thrust and freezing or overheating. 
     The battery/power module  123  in layer  103  has a “quick connection” for the layer above (i.e., layer  102 ) and below (i.e., layer  105  and camera  128 ) for power, video, camera command channels (Pan/Tilt/Zoom) and data communications. 
     The power for the helicopter&#39;s  10  systems and propulsion are electric, and powered from battery layer  103 . The on-board battery  123  supplies all power to the helicopter  10  for a flight time from 20 minutes to one (1) hour. However, one of ordinary skill in the art would know that the amount of battery life will affect flight time. 
     The 4/6/8 rotors  130  are each connected via a shaft/wing  129  to a separate speed controller  110  (see  FIGS. 1-3 and 5 ). The shaft/wing  129  is connected to the main body  100  and each shaft/wing or arm  129  is connected to the respective speed controller  110  located inside of layer  104 . Each of the rotors  130  is mounted horizontally on the end of shaft/wing  129 , and at the top of the rotor  130  is the rotor head assembly  122  that has 2-6 rotor blades  131  connected to it. The rotor blades  131  may number 2-5 blades, and are made of an appropriate durable material such as carbon fiber, which allows for easy lift of the helicopter  10 . The rotor head assembly  122  is secured to the rotor shaft by appropriate attachment mechanisms such as linkages. 
     Each of the rotors&#39; shaft/wing  129  is connected in a “spoke” back to the main chassis  100  in layer  104  which allows for the shaft/wing  129  to be connected and disconnected using a state-of-the art connector system. At the end of the shaft/wing  129  there is an electrical quick connect element (not shown). When the shaft/wing  129  is slid into the hole  132  in layer  104 , it will “click” into place using a “quick connect” mechanism, well known in the art (as described above). Once the shaft/wing  129  is connected, it has a mounting point inside (not shown), and electrical connections are made with the full electrical system  109  to provide power to the motor  111 . The rotors  130  create both a lifting force, and a clockwise rotation of the helicopter chassis  100 . As the rotors  130  turn and achieve the velocity needed for the aircraft  10  to lift from the ground, it generates a downward force. Also, layer  104 , with 4/6/8 rotors  130  can be interchanged (increased from 4 to 6 or 8) to allow for larger payloads and greater lift. 
     The multi-rotor system of the present invention is designed to allow for 4/6/8 shafts/wings or arms  129  and rotors  130  to be connected by interchanging layer  104 . The chassis  100  contains openings or slots  132  for four (4), six (6), or eight (8) arms  129  with associated motor speed controllers  110 . Thus, the appropriate layer  104  with the appropriate number of shaft/wings or arms  129  and rotors  130  can be chosen by the user in assembling the aircraft  10 . Layer  104  has a “quick connect” (i.e., pin connections, for example) with the layer above (i.e., layer  103 ) and below (i.e., layer  105 ) for power, data, and communications channels. Thus, layer  104  can be disconnected via a “quick release” mechanism, and changed from between the 4/6/8 arms  129 . 
     The shaft/wings or arms  129  are designed as hollow airfoil shapes that allow the downward thrust from the rotors  130  to cleanly flow over them. One end of the arm/wing  129  has a motor mount  133  attached to it for rotor  130 , which allows the motor  111  to be bolted or fixed to it. The other end of the motor mount  133  attaches to the arm/wing  129  and allows the electrical cables to be shielded inside the motor mount  133  and to be protected inside the hollow arm/wing  129  which runs into the center of layer  104 . The 4/6/8 arms/wings  129  connect to the power/battery  123  in layer  103 . 
     As stated above, each arm/wing  129  is connected via a “quick connect/disconnect mechanism”, suitable in the state of the art, that allows the entire arm/wing  129  with attached motor mount  133  and motor  111  to be completely disconnected. At the end of the arm/wing  129  there is an electrical connection that when the arm/wing  129  is slid into layer  104 , it will then “click” and power is now connected to the motor  111  at the end of the arm/wing  129 . Should a motor  111  or arm/wing  129  no longer work, the arm/wing  129  can be removed and a new arm/wing  129  with attached motor  111  slid into place. 
     In one exemplary embodiment, each arm/wing  129  is connected via a hinged “connect/disconnect” mechanism that allows the entire wing/arm  129  with attached motor mount  133  and motor  111  to be folded in parallel with each other (i.e., vertically). The arms/wings  129  can be opened via a spring or piston per arm/wing  129 , that would allow either a user actuated “release” or an automated “release” for launch, for example, and the arms/wings  129  would open up into a flight position after launch. 
     In one embodiment, a rotor guard  134  is a ring that connects to the arms/wings  129 . This ring extends ⅕″ beyond the reach of the 4/6/8 blades  131 . This allows the vehicle  10  to come in contact with a vertical surface and the blades  131  attached to the motors  11  will not strike the vertical surface. The rotor guard  134  is a single circular piece of plastic or carbon fiber. 
     In one embodiment, the landing gear includes four (4) lightweight durable material, tubes  135 , such as carbon fiber tubes  135 , that also slide into layer  104  at a 45 degree angle with small rubber “feet”  136  attached to the end, with the other end being attached inside layer  104  via the “quick connect” system. In one embodiment, the landing gear  135  can be folded parallel to one another for launch, and with a user-actuated or automated release, would spring back into landing position after launch. 
     In one embodiment, the helicopter  10  carries a payload (i.e., camera  128 ) of several ounces to several pounds. The camera mount is disposed in layer  105  and includes a single plate that is modular and has a “quick release” mechanism from layer  104 . The camera mount contains power, video, camera command channels (Pan/Tilt/Zoom) and data communications, and is described in U.S. patent application Ser. No. 12/805,971. This single plate creates a shelf for any type of camera system  128 . The single plate is connected to two (2) side plates with a gear system that is connected to a servo (see U.S. patent application Ser. No. 12/805,971) that allows for 0-180 degree tilting. Further, layer  105  can be easily disconnected and connected from layer  104  to insert another camera  128  system and mount, with the appropriate “quick release” pin connectors. 
     In one embodiment, the camera system  128  has the ability to allow for a remote wireless 2.4 Ghz RC transmitter and receiver system, for example, of a hand-held video and remote system, to remotely control a 360 degree left- and right-turning movement, with a 0-90 degree pan and tilt mechanism. This allows a user to move the camera  128  while the helicopter  10  is in operation at, for example, an altitude up to 12,000 ft, and a distance of up to 5 miles from the hand-held video and remote unit. 
     This single plate creates a shelf for any type of camera system  128 , such a high-definition (HD) camera, single lens reflex (SLR) camera, HD video, thermal imaging, night vision and infrared camera, or color block camera (e.g., FLIR Infrared Camera/Model Photon  320 , or Sony FCB-EX/Color Block Camera). In one embodiment, the camera  128  used may be military-qualified with thermal imaging, usable in a wide range of temperatures, with 8- or 14-bit digital video formats, digital zoom, image polarity, image colorization, video motion detection, picture freeze, etc. An additional battery may be used to power the camera system  128 . 
     In additional embodiments, there may be alternative payload arrangements used with the helicopter  10  of the present invention. In another alternative embodiment, the payload or camera system  128  is a hanging payload, and mounted hanging below the helicopter  10  by a cable (see U.S. patent application Ser. No. 12/805,971). 
     In one embodiment, an automated recharge mechanism  137  is supported in a full connection unit on the bottom of layer  105 . This recharge mechanism  137  allows for a positive and negative receiving unit, such that an external connection device can be connected for automated charging (see U.S. patent application Ser. No. 12/805,971). This allows for the entire battery system to be charged without removing the batteries  123 . 
     In a second embodiment, the helicopter  10  layers  101 - 104  are assembled together in a vertical, circular stacked arrangement, and are covered by a dome-shaped cover  138  that secures to layer  104  (see  FIGS. 5-7 ) by suitable fasteners. The elements described in this embodiment, are similar to the first embodiment described above, and uses similar reference numerals. 
     In this second embodiment, there is a central core stacked shelf system, with the electronics disposed in an outer ring configuration around the fan of an air cooling system  139 . In this configuration, layers  101 - 104  are implemented together, with the GPS  106  disposed above the autopilot  107  etc., and with the elements of layers  102  and  104  disposed in a ring-like configuration around the fan of the air cooling system  139  (see  FIG. 6 ). 
     In the air cooling system  139  of the helicopter  10 , a temperature sensor will turn on a fan  140  which will pull in cool air from the outside of the helicopter  10  and push that air through the air cooling ducts (4/6/8)  141 —one each for each of the motors  111 /speed controllers  110 —and over the electronics (i.e.,  107 ,  109 ,  110 ,  112 , etc.), etc., to create a lower internal temperature. The temperature gauges can be set by the user, and the air temperature will be monitored by the autopilot  107 . 
     Not shown in  FIG. 6 , is layer  105 , which is described as above, and which includes the camera  128  system. 
     In this second embodiment, a combination  144  landing gear  142  and camera mount  143 , is used (see  FIG. 7 ). The camera  128  (not shown in  FIG. 7 ) is mounted to shelf plate  145 , and the camera mount  143  includes a semicircular camera mounting frame  151  which is connected to two (2) semicircular framing elements  146 , that connect, to each other and to the landing gear legs  147 . The mounting frame  151  and framing elements  146  may be made of a lightweight durable material such as carbon fiber or PVC plastic. The framing elements  146  are connected at the top to four (4) “quick connect” pins which connect to layer  105  via bolts  149 . Mounted to the top of the arch of the framing elements  146  is a servomechanism  152  that allows the camera  128  to pan, and a servo/gear system  153  which allows 0-90 degree tilting of the shelf  145 . 
     The landing gear  142  of  FIG. 7 , includes two (2) parallel tubes  147  that are connected to the framing elements  146 , and are made of a lightweight durable material such as carbon fiber or PVC plastic. The landing gear legs  147  include protective rings  150  made of a similar material. The landing gear legs  147  may be hollow tubes for weight requirements, for example, and may also be made longer or shorter to create more space from the ground to the main chassis  100  when the helicopter  10  is sitting on any surface. 
     The combination landing gear/camera mount system  144  can also be used with the embodiment of  FIG. 1 , and attached to layer  105 , with the landing gear legs  135  of  FIG. 1  removed. 
     The helicopter  10  has full autopilot operation via two separate modes. 
     In one embodiment, wireless video receiving and viewing allows for an operator on the ground to view and operate the remote camera system  128  located on the helicopter  10 . In an exemplary embodiment, the first part of the system includes at least one camera  128  mounted on the helicopter  10 , connected to a video transmitter, which may be a wireless video link such as an analog, digital or WiFi video transmission/receiver (for example, a 900-5 GHz transmission analog, or Digital or WiFi device), that sends video and still photo signals wirelessly to the video and remote gimbal operation unit—whether hand-held, or at a ground station (see U.S. patent application Ser. No. 12/805,971). 
     Hand-Held Remote Control Unit 
     In an exemplary embodiment, the hand-held remote control unit includes, for example, a video receiver/transmitter (for example, a 900-5 GHz transmission in analog, digital, or WiFi), disposed in a primary assembly or housing, such as a metal (i.e., aluminum powder-coated) frame (see U.S. patent application Ser. No. 12/805,971 for description). The hand-held remote control unit includes antennae for receipt of the video transmission broadcast by the helicopter  10 , and an associated plug which connects to the LCD screen on the front side of the hand-held remote control unit. In one embodiment, the LCD screen is a flat panel LCD, such as a daylight “High Bright” with sizes from 32 inches to 4 inch screen, for example, that offers the ability to range in brightness from approximately 1,000 NIT&#39;s of brightness to ½ NIT. In one embodiment, the unit may also include dual RCA inputs and picture-in-picture video for screen systems. 
     In an exemplary embodiment, there is a standard operation remote control assembly with circuits and boards on the back side of the hand-held remote control unit, which would be familiar to one of ordinary skill in the art. The remote control assembly includes joy sticks (for example, 2.4 GHz R/C control sticks with programmable settings and sensitivities) disposed on the front side of the hand-held remote control unit, on either side of the LCD screen, for operation of the helicopter  10  and the payload, such as a camera  128 . The R/C mode allows the user to utilize the wireless R/C controls to wirelessly rotate the camera 360 degrees and pan and tile 0-90 degrees via the 2.4 GHz method. This also allows via a wireless 900-5 GHz transmitter on the helicopter to transmit to the active station video. 
     In one embodiment, the operation of the camera  128  includes three (3) degrees of motion for the camera  128 , including pan and tilt, up and down, and spinning 360 degrees in a circle. In one embodiment, there is a second data channel for the operation of the camera  128  including zoom, shutter, focus and other applicable camera functions, or for other payload functions. 
     In one embodiment; a portable 12 volt battery pack and integrated wiring is included in the housing (see the back side of the hand-held remote unit, as shown and described in U.S. patent application Ser. No. 12/805,971). In one embodiment, the complete frame and equipment of the hand-held remote control unit weighs approximately 5 lbs or less. In one embodiment, there is also an associated optional shoulder strap and harness to fit around the user&#39;s neck for ease in holding the hand-held remote control unit. 
     In one embodiment, the hand-held remote control unit described above, allows the user to utilize the joysticks to send wireless signals to a matching R/C receiver  113  as input to the helicopter  10  and onboard autopilot  107 . This 2.4 GHz Remote Control (R/C) receiving unit  113  connects to the power panel  108  that relays the commands from the ground R/C unit for the tilting and maneuvering of the rotors  122 . This input is also plugged into the primary electrical panel  108  and is used by the autopilot  107 . The electrical panel  108  may also include an LED for Autopilot engagement, LED for GPS tracking ‘On/Off’, LED for Battery strength with indicator shows as RED via the LED to visualize when the overall system battery strength has reached ¼ strength. 
     Ground Station Unit 
     The ground station unit is similar to the hand-held remote control unit, and includes the elements described above with the exception of the remote control assembly with joy sticks, and the harness (see U.S. patent application Ser. No. 12/805,971 for description). The ground station unit includes a rechargeable battery. In one embodiment, the LCD screen may be larger, such as a 15″ 1,000 NIT daylight viewable screen, connected to an active video, for example. As with the hand-held remote control unit, the LCD screen offers a picture-in-picture for two (2) simultaneous video feeds from the transmitter on the helicopter  10 . This mode allows the user to view via a wireless 900-5 GHz transmitter on the helicopter  10  to transmit to the active station video and a matching wireless video receiver shows the transmission on the station. The ground station has an active video stabilization unit, and a durable frame (i.e., aluminum) that contains the battery, dual video receivers and connections for the input to the video screen. 
     In one embodiment, the ground station unit includes a portable DVR, one for each RCA channel (i.e., two DVRs), and an additional high gain antenna/patch panel for additional gain. 
     In one embodiment, the ground station unit is supported by a stand, such as an aluminum tripod with extendable legs, mounted on the back side of the ground station unit at a bracket. 
     In an exemplary embodiment, the ground station unit utilizes both a remote control (R/C) and/or wireless-connected computer (such as a computer laptop (not shown)) configured with a wireless RS232 port, for example, which operates a software program specific to the present invention. This mode allows both controllers to be sending information to the helicopter  10  for controls and input via GPS position information. 
     As stated above, the helicopter  10  of the present invention has a wireless communication data link (for example, 900 MGHz-2.4 GHz) with the ability to transmit and receive flight instructions to and from the helicopter  10  and the ground station. The ground station has the ability to send input commands to the helicopter  10  via, for example: a) the remote control wireless controller, or b) a computer (not shown) configured with flight software connected to the wireless data link. Thus, the ground station allows the helicopter  10  to be managed fully from the ground station software program via a wireless modem transmission/receiving signal. 
     Also, the software allows for the ability to trigger camera and remote video via payloads at specific points. The software also shows ‘real time’ elements of the Helicopter health including battery, telemetry connectivity and other key attributes. The user always has the flexibility to switch during a mission into Assisted Mode (use of the R/C Controller without input from the laptop), RC Mode (with no autopilot at all), or Home Mode (allows the helicopter to return to a pre-determined GPS point and either hover, or land and turn off all rotors/motors). 
     With respect to the computer and software program, one of ordinary skill in the art would know that any state-of-the-art computer, particularly a laptop, may be used with the present invention. The present invention has the ability to specify via any computer code (i.e., XML, user interface, data files, Microsoft Windows® user interface or other computer elements), commands to control the helicopter  10 . The computer may include standard processing and memory capability, including any of a central processing unit (CPU), parallel processor, RAM/ROM with a program, USB interface, telephone interface, microphones, speakers, a computer mouse, a wide area network interface, image display device, local area network interfaces, hard disk drives, DVD/CD readers/burners, a keyboard, wireless communication interfaces, and/or other components. The computer used with the present invention may include, or be modified to include, software that may operate to provide data gathering and data exchange functionality. The invention may be implemented by an application that resides on the computer, wherein the application may be written to run on existing computer operating systems. Users may interact with the application through a graphical user interface. The application may be ported to other personal computer (PC) software, personal digital assistants (PDAs), cell phones, and/or any other digital device that includes a graphical user interface and appropriate storage capability. 
     While the system of the present invention may be described as performing certain functions, one of ordinary skill in the art will readily understand that the program may perform the function rather than the entity of the system itself. The program that runs the application may include separate programs having code that performs desired operations. Thus, the program may include a plurality of modules that perform sub-operations of an operation, or may be part of a single module of a larger program that provides the operation. 
     The memory or storage device may store at least one data file, such as image files, text files, data files, audio files, video files, among other file types. The data storage device may include a database, such as a centralized database and/or a distributed database that are connected via a network. 
     According to one embodiment, the present invention may be implemented using software applications that reside in a client and/or server environment. According to another embodiment, the present invention may be implemented using software applications that reside in a distributed system over a computerized network and across a number of client computer systems. Thus, in the present invention, a particular operation may be performed either at the computer, a server, or both. 
     Further, although the above-described features and processing operations may be realized by dedicated hardware, or may be realized as programs having code instructions that are executed on data processing units, it is further possible that parts of the above sequence of operations may be carried out in hardware, whereas other of the above processing operations may be carried out using software. 
     The underlying technology allows for replication to various other sites. Each new site may maintain communication with its neighbors so that in the event of a catastrophic failure, one or more servers may continue to keep the applications running, and allow the system to load-balance the application geographically as required. 
     Further, although aspects of one implementation of the invention are described as being stored in memory, one of ordinary skill in the art will appreciate that all or part of the invention may be stored on or read from other computer-readable media, such as secondary storage devices, like hard disks, floppy disks, CD-ROM, a carrier wave received from a network such as the Internet, or other forms of ROM or RAM either currently known or later developed. Further, although specific components of the system have been described, one skilled in the art will appreciate that the system suitable for use with the methods and systems of the present invention may contain additional or different components. 
     Method of Operation 
     In an exemplary embodiment, the autopilot  107  of the helicopter  10  of the present invention is operated in two separate modes: 1) via a wireless hand-held remote control unit (without computer programming/software), and 2) via a ground station unit (with computer programming/software) (see U.S. patent application Ser. No. 12/805,971 for description). The primary pilot handles the ground station mode, with the safety pilot handling the hand held remote control mode; and in some cases, the primary and safety pilot are one and the same when only a hand-held remote control unit is used. With either mode, the helicopter  10  can be placed into flight in a matter of minutes, providing flexibility and advantages of rapid deployment to the user. 
     a) Pre-Flight Checklist 
     In both modes of operation, the user follows a pre-flight checklist, with a specific pre-flight checklist for each mode of operation (i.e., hand-held or ground station). 
     Generally, in one embodiment of the overall pre-flight checklist, the user then turns on the helicopter  10 , at an on/off switch, and ensures the autopilot  107  is “ON” (LED is lighted), and then performs a gimbal and video check. This gimbal and video check is performed by ensuring power is being provided to the video transmitter, the payload (for example, camera  128 ), the computer modem (if applicable), the camera  128  transmitter (if applicable), the gimbal/gear system of the camera mount, the LCD panel on the hand-held remote or ground station, and the LCD transmitter. The user then checks the signal strength of the live video. 
     At this time, the user may check the main power flight batteries  123  on layer  3 , and then check that all is clear on the flight line (i.e., powering “ON” of rotors  130 ). 
     In one embodiment of the hand-held remote control unit operation, the user checks the battery  123  voltage to ensure that the target minimum for flight is available. The user would also check all the mechanical connections, including the rotors  130 , the layer connects  101 - 105 , and the landing gear. The video transmitter would be checked to ensure remote control is selected, and all LEDs should be “ON”, and the throttle trim setting should be checked. The GPS  106  should be “ON” and the status on the LCD  124  should be “OK” for all systems. The user can then check the joy stick operation on the hand-held remote control unit, with, for example, the throttle/rudder being operated by the left joy stick, with throttle being forward/backward, a counterclockwise direction on the throttle being the rudder and left/right, and the right joy stick used for elevator/aileron. 
     In another embodiment for the ground station checklist, the user must run through checks on the computer in addition to the above pre-flight checklist of the helicopter  10  itself. In this case, the user would turn on the computer at the ground station, and bring up the software program that handles the helicopter  10  flight. The ground station should be on A/C power (for example, more than 14 volts), or the user should ensure that the batteries on the helicopter  10  are sufficient for flight. 
     Specifically, in one embodiment, the user should verify that the icons which denote the helicopter  10  and ground station on the computer screen, are in the expected map area (i.e., that the GPS  106  telemetry is working properly). The GPS  106  count, the number of satellites, and the position dilution of position (PDOP) of the GPS  106  should be checked and verified, and radio settings requested. If waypoints are to be scheduled (discussed further below), the user should validate the sequence and the order of same. The user should check the mission limits, such as height maximum/minimum, flight battery time, flight termination conditions, and communications timeout (where lack of communications triggers a safety return (described later)), as well as the command settings (i.e., vehicle velocity, altitude, etc.—usually automatic). The helicopter  10  controls should be checked for pitch, rolling, collective, and yawing, as well as tilt forward, backward, lift up for artificial horizon, and for operation of the inertial measurement units (IMUs) in the autopilot  107  (used by the safety pilot). 
     Once all the safety and flight operation testing and checklist are performed by the user, if all systems are ready and the helicopter  10  can be flown, the user may begin flight operations using either the hand-held remote control unit or the ground station unit. Aircraft traffic should be checked and any radio calls mandated by air traffic control should be made. The operation of the flight mission can be timed by the user or the computer. 
     b) Hand Held Video Operation 
     In this exemplary mode, the wireless remote control unit sends wireless signals to the matching RC receiver  164  as input to the helicopter  100  and autopilot  157 . The user utilizes the two joy sticks on the wireless remote control  1  as input to the onboard helicopter autopilot  107 , and the autopilot  107  then interprets the input commands from the joy sticks to create outputs from the autopilot  107  to the helicopter  10  for flight: up, down, tail left, tail right, forward, backward, left sideways, right sideways. The autopilot  107  issues the appropriate commands via an electrical output to the onboard helicopter control mechanisms (i.e., rotors  130 , motors  111 , and servomechanism, etc.), that control the helicopter  10 . 
     In one embodiment, in the hand-held remote control mode, the user may utilize the wireless control system to send and receive camera  128  and gimbal functions, including, for example: i) three (3) degrees of motion for the camera  128 , including pan and tilt, up and down, and spinning 360 degrees in a circle. As stated above, a second data channel may be used for the operation of the camera  128  including zoom, shutter, focus and other applicable camera  128  functions. 
     c) Ground Station Video Operation 
     In this exemplary mode, both a ground station unit, with a wireless connected computer running helicopter operational software, are used. The ground station unit includes a second wireless communication data link with the ability to transmit and receive flight instructions to and from the helicopter  10  to the ground station. The ground station unit has the ability to send input commands to the helicopter  10  by: a) the remote control wireless controller, or b) a computer configured with flight software connected to the wireless data link. The ground station mode allows the helicopter  10  to be managed fully from the software program run from the computer via a wireless modem transmission/receiving signal. 
     In this exemplary embodiment, and similarly to the hand-held remote control unit, the helicopter  10  is controlled, via the autopilot  107 , but from the ground station unit, for flight, including: up, down, tail left, tail right, forward, backward, left sideways, right sideways. The ground station unit, thus, issues the appropriate commands via the wireless modem transmission/receiving signal, to the onboard helicopter control mechanisms (i.e., rotors  130 , motors  111 , and servomechanism, etc., that control the helicopter  10 . 
     Thus, as stated above, the user may utilize the ground station unit to command the autopilot  107  to control payload functions, such as camera  128  functions. In one embodiment, the camera  128  and gimbal functions, including: i) three (3) degrees of motion for the camera  128 , including pan and tilt, up and down, and spinning 360 degrees in a circle. As stated above, a second data channel may be used for the operation of the camera  128  including zoom, shutter, focus and other applicable camera  128  functions. 
     d) Features of Camera Payload 
     In one embodiment, whether using the hand-held remote control unit or ground station unit, the present invention includes a feature for an automated command to be sent from the autopilot  107  to the payload, i.e., the remote control camera  128 . The command would be an electronic trigger for the camera  128  to automatically take photographs in any direction. The user may command this automatic feature detailing when (time), where (GPS, altitude), and how (helicopter  10  vehicle attitudes), the photographs would be automatically taken by the camera  128 . The user may use the data and the photographs captured, to create a mosaic, for example. The helicopter will travel in a search and rescue pattern to capture an entire area with photos. End user requires a list detailing when (time), where (GPS, altitude), and how (vehicle attitudes) a photograph was automatically taken. 
     In an exemplary embodiment, the autopilot  107  of the present invention can also trigger automatic photographs to be taken in accordance with the following functions, for example: the number of waypoints or GPS specified points; the altitude of these waypoints; the specific latitude and longitude of the waypoints or GPS specified points; the forward velocity of the helicopter  10  between any of these points; and the percentage overlap of the photos to be taken. The total combination creates the ability to pick “n”-number of points for the autopilot  107  to follow. 
     In an exemplary embodiment, the autopilot  107  of the present invention has the ability to send an electronic command to the camera  128 , and simultaneously to data log the commands of the latitude, longitude, altitude and exact X, Y and Z velocities. These elements will be entered into a data file from the real time data coming from the autopilot  107  and readable by any type of common computer software program (i.e., XML, and Comma Delimited file). 
     e) Onboard Helicopter Autopilot Features 
     In other embodiments, there are several features which the onboard helicopter autopilot  107  can operate with input from the ground via the two previously mentioned modes (i.e., hand-held and ground station), and they include: 
     i) Automatic Takeoff 
     In one embodiment, the helicopter  10  of the present invention has the ability to “Auto takeoff” via the hand-held remote control unit mode, or the wireless ground station unit with computer mode. The computer software program includes a set of commands that instruct the helicopter  10  to lift from the ground into a stationary hovering position at a preset altitude (for example, typically set at 10 meters above the mean sea level of where the helicopter  10  started). 
     ii) Automatic Landing 
     In one embodiment, the helicopter  10  of the present invention has the ability to “Auto land” via the hand-held remote control unit mode, or the wireless ground station unit with computer mode. The computer software program includes a set of commands that will instruct the helicopter  10  to maintain a specified GPS  106  position, to descend at a predetermined velocity, and to land on the ground and turn off all rotors  130  and motors  111 . 
     iii) Autonomous Flight Between Waypoints 
     As discussed above, in one embodiment, the helicopter  10  of the present invention has the ability to fly automatically without human input from predetermined or predefined GPS  106  waypoints, at a specified altitude, specified velocity, and specified GPS latitude and longitude. This instruction will make the helicopter  10  move from a hover position at one GPS position, including a specified altitude, and forward velocity to another GPS waypoint. Then once at the new GPS position, the instructions will include further required helicopter  10  behavior (i.e., hover, or continue to yet another GPS waypoint). 
     iv) Safety Return 
     In one embodiment, the helicopter  10  of the present invention has the ability to perform an automated return to “home” flight function that allows for the helicopter  10  to fly back to a “home” pre-determined GPS latitude and longitude via a pre-determined flight course, at a specified altitude, specified velocity and specified heading. Once this function is triggered by the user, or by a predefined set of conditions, the helicopter  10  will descend at a pre-determined velocity and once on the ground, turn off all rotors  130  and motors  111 . The following conditions may create a “home” flight function, or safety return: 
     a) a pre-defined time frame of a lack of communication time between the helicopter  10  and the user at the hand-held remote control unit or ground station unit, requiring a return to a predetermined “home” GPS latitude and longitude. 
     b) achieving a pre-determined remaining percentage of total power, which triggers a return to a predetermined “home” GPS latitude and longitude. 
     c) achieving a specified helicopter  10  health condition (programmed into the software using custom functions), the health conditions including, but not limited to, “real-time” elements, such as battery power, telemetry connectivity, and other key attributes, along with motor temperature, humidity, wind and other conditions. 
     f) Predetermined Missions Software Program 
     In an exemplary embodiment, the ground station unit computer software program allows for the creation of pre-determined missions including the capability to download satellite images of terrain with geo-referenced data and develop complete flight plans that include detailed GPS coordinates/way points (i.e., longitude, latitude, velocity, and payload commands) management, and the ability to create height, attitude and helicopter  10  direction, and speed of movement, between all way points. The user can utilize the software program and an input device (i.e., mouse) to the computer, to point and “click”, for example, on the geo-referenced map to create, for example, waypoint programming, real time in-flight mission loading or mission changes, mission interrupt, “continue” command at waypoint X, automatic takeoff, and automatic landing. 
     In one embodiment, the user has the flexibility to switch between the hand-held remote control unit (with or without autopilot  107 ) and ground station unit during a mission (using a “toggle” switch), or “home” mode (which allows the helicopter  10  to return to a predetermined GPS point and either hover, or land and turn off all rotors/motors). The ability to seamlessly switch into and back from the mission mode completes the ability of the helicopter  10  to have autonomous flight. 
     It should be emphasized that the above-described embodiments of the invention are merely possible examples of implementations set forth for a clear understanding of the principles of the invention. Variations and modifications may be made to the above-described embodiments of the invention without departing from the spirit and principles of the invention. All such modifications and variations are intended to be included herein within the scope of the invention and protected by the following claims.