Abstract:
A dual power helicopter without a tail rotor is especially a kind of helicopter with an enhanced ascending and descending power through the dual power. The dual power helicopter of present invention primarily uses two power devices which can be rotated in opposite directions to control a flight of the helicopter. The two power devices are rotated in the opposite directions by steering gears from a same engine, such that the engine power can be completely transmitted to the two power device, enabling the engine power to be completely developed, thereby improving a performance of the helicopter.

Description:
BACKGROUND OF THE INVENTION 
       [0001]    (a) Field of the Invention 
         [0002]    The present invention relates to a dual power helicopter without a tail rotor, and more particularly to a helicopter, an ascending and descending power of which is increased through a dual power, and which is especially provided with high power and safety. 
         [0003]    (b) Description of the Prior Art 
         [0004]    A helicopter has long been a most convenient air traffic vehicle and one of important air forces. The helicopter is widely used in that it can take off and descend vertically without requiring a runway. 
         [0005]    However, there is a very serious limitation to the helicopter, resulting from a flight principle of the helicopter. 
         [0006]    Referring to  FIG. 1 , a conventional helicopter includes a cabin  10 , an upper end of which is provided with a main rotor  11 , and a tail end of which is provided with a tail rotor  12 . Axes of the main rotor  11  and the tail rotor  12  are interleaved by 90 degrees, and the two rotors are driven by a same engine power. The main rotor  11  is used to control an ascending and descending, and a traveling movement in front, rear, left, and right directions, of the helicopter; whereas, the tail rotor  12  is used to assist the helicopter to travel in the left and right directions. 
         [0007]    Referring to  FIG. 2-A , when the helicopter is to move forward, a pilot is the cabin  10  will push a control lever forward to tilt the main rotor  11  forward, such that the helicopter will move forward through wind power generated by the main rotor  11 . Referring to  FIG. 2-B , the pilot in the cabin  10  will pull the control lever backward to tilt the main rotor  11  backward, such that the helicopter can move backward. 
         [0008]    Referring to  FIG. 3-A  and  FIG. 3-B , when the helicopter is to move rightward, the main rotor  11  is primary tilted forward, and is also tilted rightward if it is viewed from a front side (as shown in  FIG. 3-B ). At this time, the tail rotor  12  provides a high thrust, which will further enable the helicopter to turn right, thereby achieving an effect of traveling toward the right direction. On the other hand, referring to  FIG. 3-A  and  FIG. 3-C , when the helicopter is to move left, the main rotor  11  is primarily tilted forward, and is also tilted leftward if it is viewed from a front side. At this time, the tail rotor  12  provided a lower thrust, thereby enabling the helicopter to move left. 
         [0009]    Although the helicopter is a kind of convenient air traffic vehicle, its main rotor  11  is rather complicated, in that in addition to providing the effects of tilting forward and backward, it also needs to provide the effects of tilting leftward and rightward, such that the helicopter can freely fly on a sky. Moreover, the tail rotor  12  needs to provide the high thrust, and at other times, it needs to provide the low thrust; therefore, the structure of tail rotor  12  is also rather complicated. 
         [0010]    Accordingly, due to the complicated structures of main rotor  11  and tail rotor of helicopter, it will be very difficult to drive the helicopter, and is easy to result in an unbalanced flight. In addition, speed of the helicopter is limited by the main rotor  11 . On the other hand, other than providing the main rotor  11  to operate, the engine also needs to transmit 20% of its power to the tail rotor  12  for keeping a balance of the helicopter; therefore, it will be unable to provide an ascending power. Moreover, as the conventional helicopter is affected by an installation of the main rotor, it cannot be loaded with an ejection seat or a parachute. Therefore, when the helicopter is having a mechanical malfunction, it can only be crashed, thereby causing a casualty to the pilot and passengers. 
         [0011]    Accordingly, how to provide a helicopter with high power and safety is an issue to be solved by the present invention. 
       SUMMARY OF THE INVENTION 
       [0012]    The primary object of present invention is to provide a dual power helicopter without a tail rotor, wherein a simple mechanical principle is used to improve the complicated structure of conventional main rotor, and the tail rotor with complicated structure is removed, such that the engine power can develop into a maximum function. In addition, a complete balance is achieved to the aerodynamic force, thereby being able to automatically stabilize the helicopter. 
         [0013]    Another object of the present invention is to provide a dual power helicopter without a tail rotor, wherein a parachute can be loaded, such that when the helicopter is losing power from a mechanical malfunction, it can slowly descend through the parachute, thereby achieving an effect of keeping people and the helicopter safe. 
         [0014]    Accordingly, a dual power helicopter without a tail rotor of the present invention includes a cabin, a power device, a gear box set, a coupling lever set, and two rotors. The power device is located in an interior of the cabin to provide the engine power. The gear box consists of a main gear box and two secondary gear boxes, wherein the main gear box is connected with the power device, the two secondary gear boxes are located at two sides of the main gear box respectively, are coaxial with the main gear box, and are connected with the two rotors, respectively. The two secondary gear boxes are casings which are installed externally and can be freely rotated, in order to control a swinging of the two rotors. On the other hand, the coupling lever set consists of a control lever installed in an interior of the cabin, which is connected to the outer casings of secondary gear boxes through the plurality of coupling levers, such that the pilot in the cabin can manipulate the control lever to drive the two secondary gear boxes through the plurality of coupling levers, thereby controlling the swinging of two rotors. 
         [0015]    However, the two rotors will have different spinning directions through a change of spinning direction resulting from the main gear box and secondary gear boxes, such that the balance of helicopter can be obtained through a left and right spinning of the two rotors, thereby enabling the helicopter to fly more stably. Moreover, through a driving of the coupling lever set, the two secondary gear boxes will have a reverse spinning, to drive the two rotors to be tilted forward and backward, thereby enabling the helicopter to move left or move right through the difference of forward and backward tilting of the two rotors. 
         [0016]    Besides, for the dual power helicopter without a tail rotor of present invention, the engine power created by the power device is completely transmitted to the two rotors through the plurality of gear boxes; therefore, this engine power can be completely provided to the two rotors, thereby largely increasing the power of helicopter. 
         [0017]    Furthermore, for the dual power helicopter without a tail rotor of present invention, a parachute can be further added on a top end of the cabin. The parachute is collected between the two rotors, and it can be ejected outward through air pressure in order to be prevented from being damaged by the two rotors, such that the helicopter can slowly descend through the parachute, thereby achieving an effect of keeping people and the helicopter safe. 
         [0018]    To enable a further understanding of the said objectives and the technological methods of the invention herein, the brief description of the drawings below is followed by the detailed description of the preferred embodiments. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0019]      FIG. 1  shows a schematic view of a conventional helicopter. 
           [0020]      FIG. 2-A  shows a schematic view of a conventional helicopter which is moving forward. 
           [0021]      FIG. 2-B  shows a schematic view of a conventional helicopter which is moving backward. 
           [0022]      FIG. 3-A  shows a front view of a conventional helicopter which moves right. 
           [0023]      FIG. 3-B  shows a side view of a conventional helicopter which moves right. 
           [0024]      FIG. 3-C  shows a side view of a conventional helicopter which moves left. 
           [0025]      FIG. 4  shows a front view of the present invention. 
           [0026]      FIG. 5  shows a schematic view of a motion of a power device and a plurality of gear boxes of the present invention. 
           [0027]      FIG. 6  shows a side view of the present invention which moves forward. 
           [0028]      FIG. 7  shows a side view of the present invention which moves backward. 
           [0029]      FIG. 8-A  shows a front view of the present invention which moves right. 
           [0030]      FIG. 8-B  shows a side view of the present invention which moves right. 
           [0031]      FIG. 9-A  shows a front view of the present invention which moves left. 
           [0032]      FIG. 9-B  shows a side view of the present invention which moves left. 
           [0033]      FIG. 10  shows a schematic view of the present invention which uses a parachute. 
       
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
       [0034]    Referring to  FIG. 4 , a dual power helicopter without a tail rotor comprises a cabin  10 , a power device  20  (as shown in  FIG. 5 ), a gear box set  30 , two rotors  40 , and a coupling lever set  50 . 
         [0035]    An interior of the cabin  10  is provided with at least one driving space, and a bottom of the cabin  10  is installed with tires  13 . 
         [0036]    Referring to  FIG. 5 , the power device  20 , which is installed in an interior of the cabin  10 , primarily provides an engine power, and an upper end of the power device  20  is connected with a clutch  21  which is located at an exterior of top end of the cabin  10 . 
         [0037]    Referring to  FIG. 5 , a main gear box  31  is installed at an upper end of the clutch  21 , and two secondary gear boxes, including a left secondary gear box  32  and a right secondary gear box  33 , are located at a left and right sides of the main gear box  31 , respectively. A same axis  34  is located between the main gear box  31  and the left, right secondary gear boxes  32 ,  33  to drive the internal gears, such that a reverse spinning will be formed to the left and right gear boxes  32 ,  33 . In addition, casings at exteriors of the left and right secondary gear boxes  32 ,  33  can be freely rotated at two sides of the main gear box  31 . 
         [0038]    The two rotors  40  are located at upper ends of the left and right secondary gear boxes  32 ,  33  respectively, and a reverse spinning is formed to the two rotors  40 , through a driving by the left and right secondary gear boxes  32 ,  33 . 
         [0039]    The coupling lever set  50  includes a control lever  51  and a plurality of coupling levers  52 . The control lever  51  is located in an interior of the cabin  10 , and is connected with the plurality of coupling levers  52  which are connected to the outer casings of left and right secondary gear boxes  32 ,  33 . 
         [0040]    Accordingly, referring to  FIG. 6 , when the dual power helicopter without a tail rotor of present invention is to move forward, a pilot in the cabin  10  only needs to push the control lever  51  in the cabin  10  forward, to drive the coupling lever  52 , thereby driving the left and right secondary gear boxes  32 ,  33  to be rotated backward a little through the coupling lever  52 , so as to tilt the two rotors  40  forward and to achieve an effect of moving forward. On the other hand, referring to  FIG. 7 , when the pilot in the cabin  10  pulls the control lever  51  backward to drive the coupling lever  52 , the left and right secondary gear boxes  32 ,  33  will be rotated forward a little, thereby driving the two rotors  40  to tilt backward, so as to achieve an effect of moving backward. 
         [0041]    Referring to  FIG. 8-A , when the pilot in the cabin  10  pushes the control lever  51  right, the control lever  51  will displace the coupling lever  52  toward a left, which will drive the left and right secondary gear boxes  32 ,  33  to be rotated in two opposite directions, thereby enabling the two rotors  40  to form a change of direction of tilting forward and backward. In this embodiment, when the control lever  51  is pushed right, the right secondary gear box  32  will be rotated backward through the driving of coupling lever  52 , thereby enabling the rotor  50  above the right secondary gear box  32  to tilt backward. Referring to  FIG. 8-B , the left secondary gear box  31  will be rotated forward, which enables the rotor  40  above the left secondary gear box  31  to tilt forward. Accordingly, the dual power helicopter without a tail rotor of present invention can turn right. 
         [0042]    Referring to  FIG. 9-A , when the control lever  51  is pushed left, it will drive the coupling lever  52  to be displaced rightward, thereby driving the left and right secondary gear boxes  32 ,  33  to be rotated reversely, through the coupling lever  52 . In this embodiment, when the control lever  51  is pushed left, the left secondary gear box  32  will be rotated backward through the driving of coupling lever  52 , thereby enabling the rotor  40  above the left secondary gear box  32  to tilt backward. On the other hand, referring to  FIG. 9-B , the right secondary gear box  33  will be rotated forward, enabling the rotor  40  above the right secondary gear box  33  to tilt forward. Accordingly, the dual power helicopter without a tail rotor of present invention can turn left. 
         [0043]    Accordingly, the engine power created by the power device  20  can be completely used to drive the two rotors  40  through a transmission of the main gear box  31 , the left secondary gear box  32 , and the right secondary gear box  33 , such that the engine power from the power device can develop into a maximum performance, thereby improving an entire performance of the helicopter. 
         [0044]    On the other hand, referring to  FIG. 10 , in order to enhance a flight safety for the dual power helicopter without a tail rotor of present invention, a top end of the main gear box  31  is further provided with a containing part  14 . Referring to  FIG. 4 , the containing part  14  can be used to collect a parachute  60 , such that when the two rotors  40  cannot operate due to that the dual power helicopter without a tail rotor of present invention loses its power, the parachute  60  in the containing part  14  can be ejected timely to suspend the helicopter, such that the dual power helicopter without a tail rotor can slowly descend through the parachute, thereby keeping people and the helicopter safe. 
         [0045]    In this embodiment, in order to successfully eject the parachute  60 , a top end of the containing part  14  is provided with a cap  15 . Before ejecting the parachute  60 , the cap  15  is just covered on the containing part  14 , but the parachute  60  can be successfully ejected out of the containing part  14  through air pressure, wherein a large quantity of air pressure is filled into the containing part  14 , enabling an inner pressure of the containing part  14  to be larger than an ambient atmospheric pressure, thereby pushing out the cap  15  and ejecting out the parachute  60 , such that the parachute  60  can be opened timely during an emergency condition to keep people and the helicopter safe. 
         [0046]    Besides, the parachute  60  is further provided with control strings  61  at its two sides, which are extended into the cabin  10  respectively, enabling the pilot in the cabin  10  to control a descending direction of the parachute  60  through the two control strings  61 , such that the people and helicopter can be landed at a safe place. 
         [0047]    It is of course to be understood that the embodiments described herein is merely illustrative of the principles of the invention and that a wide variety of modifications thereto may be effected by persons skilled in the art without departing from the spirit and scope of the invention as set forth in the following claims.