Patent Publication Number: US-2022212788-A1

Title: Solar unmanned aircraft

Description:
BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The present invention relates to a solar unmanned aircraft, and more particularly to a solar unmanned aircraft having vertical control wings. 
     2. Description of Related Art 
     A general aircraft has a main wing for providing buoyancy force and tail wing as a stabilizing wing for providing horizontal stabilization, and also has some control wings located above the main wing and the tail wing. When the control wings are utilized on a solar unmanned aircraft, the weight of the solar unmanned aircraft is increased. Besides, the control wings located above the main wing and the tail wing will also decrease an area for installing solar battery. In addition, a generally aircraft also has a landing gear for taking off and landing of the aircraft. The landing gear also increases the weight of the unmanned aircraft such that a sailing distance of the unmanned aircraft is greatly decreased. 
     Therefore, how to improve the current technology and decreasing the weight of the solar unmanned aircraft, and decreasing the control wings to provide more area for installing solar panel is a challenging research subject that needs to be improved urgently. 
     SUMMARY OF THE INVENTION 
     The purpose of the present invention is to provide a solar unmanned aircraft to decrease weight and control wings, and increase an installation area of the solar panels. 
     In order to solve the above-mentioned technical problem, a technical solution provided by the present invention is: a solar unmanned aircraft comprises a first body having a front end and a rear end; a second body having a front end and a rear end; a main wing having an upper surface and a lower surface, wherein the upper surface of the main wing is installed with solar panels, and the lower surface of the main wing is connected with the first body and the second body; a tail wing having an upper surface and a lower surface, wherein the upper surface of the tail wing is installed with solar panels, and the lower surface of the tail wing is connected with the first body and the second body; a first vertical control wing disposed below the main wing and having a first fixed wing and a first rudder; a second vertical control wing disposed below the main wing and having a second fixed wing and a second rudder; a third vertical control wing disposed below the tail wing and having a third fixed wing and a third rudder; a fourth vertical control wing disposed below the tail wing and having a fourth fixed wing and a fourth rudder; a first propeller fixed at the front end of the first body or the rear end of the first body; and a second propeller fixed at the front end of the second body or the rear end of the second body; wherein, the main wing is disposed between the front ends of the first body and the second body, and the tail wing is disposed between the rear ends of the first body and the second body, wherein, the first rudder, the second rudder, the third rudder and the fourth rudder are respectively capable of rotating with respect to the first fixed wing, the second fixed wing, the third fixed wing and the fourth fixed wing so as to control the solar unmanned aircraft to yaw, roll, reduce speed, pitch up or dive. 
     Wherein at least one of the first vertical control wing, the second vertical control wing, the third vertical control wing and the fourth vertical control wing is connected with the first body or the second body. 
     Wherein the first vertical control wing is connected with the first body and corresponding to a connection portion of the main wing and the first body, the second vertical control wing is connected with the second body and corresponding to a connection portion of the main wing and the second body, the third vertical control wing is connected with the first body and corresponding to a connection portion of the tail wing and the first body, and the fourth vertical control wing is connected with the second body and corresponding to a connection portion of the tail wing and the second body. 
     Wherein at least one of the first vertical control wing, the second vertical control wing, the third vertical control wing and the fourth vertical control wing is directly connected with the main wing or the tail wing. 
     Wherein an end terminal of at least one of the first vertical control wing, the second vertical control wing, the third vertical control wing and the fourth vertical control wing is installed with a sleeve. 
     Wherein when the solar unmanned aircraft is yawing, the first rudder is in parallel with the first body, the second rudder is in parallel with the second body, the third rudder and the fourth rudder are rotated together clockwise or counterclockwise with a same angle, and respectively form an included angle with the first body and the second body in order to generate a yaw moment. 
     Wherein when the aircraft is reducing the speed or reducing lift force, the first rudder is rotated counterclockwise and forms an included angle with the first body, the second rudder is rotated clockwise and forms an included angle with the second body, the third rudder is rotated clockwise and forms an included angle with the first body, and the fourth rudder is rotated counterclockwise and forms an included angle with the second body so that through the first rudder and the second rudder, a spoiling effect is generated, and through the third rudder and the fourth rudder, direction of the aircraft is controlled and pressing the head of the aircraft. 
     Wherein when the head of the aircraft is diving, the first rudder is in parallel with the first body, the second rudder is in parallel with the second body, the third rudder is rotated clockwise and forms an included angle with the first body, the fourth rudder is rotated counterclockwise and forms an included angle with the second body such that a dive moment is generated; when the head of the aircraft is pitching up, the third rudder and the fourth rudder are respectively in parallel with the first body and the second body, the first rudder and the second rudder are rotated with a same angle in opposite directions in order to respectively form an included angle with the first body and the second body, reducing airflow speed under the main wing, so as to generate an upward moment. 
     Wherein when t the unmanned aircraft performing an axially rolling, the first rudder is rotated counterclockwise or clockwise to form an included angle with the first body, the third rudder is rotated clockwise or counterclockwise in opposite to the first rudder of roughly the same angle, the second rudder is in parallel with the second body, the fourth rudder is in parallel with the second body, to generate a roll moment to life up the first body with respective to the second body. 
     Wherein the tail wing is capable of providing a horizontal stabilization and providing a lift force to sustain the motor and tail weight respect the gravity center of the aircraft, and using the lift force to generate a pitching control moment. 
     Wherein an internal space of the main wing and the tail wing is installed with a charge and discharge rechargeable battery as a power storage source of the aircraft. 
     Wherein the first vertical control wing, the second vertical control wing, the third vertical control wing and the fourth vertical control wing are used as a landing gear of the aircraft. 
     wherein the first propeller fixed at the rear end of the first body; and the second propeller fixed at the rear end of the second body, while lading the aircraft can have some speed and be captured by a prepared net, so as to avoid long runway and to be safe for the retry of landing. 
     Accordingly, through disposing the first vertical control wing, the second vertical control wing, the third vertical control wing and the fourth vertical control wing below the main wing and the tail wing, the upper surface of the main wing and the tail wing can be massively installed with solar panels in order to increase an area for installing the solar panels such that the solar unmanned aircraft can stay in the air for a longer time comparing to the conventional art. Besides, using the first rudder, the second rudder, the third rudder and the fourth rudder to respectively rotate with respect to the first fixed wing, the second fixed wing, the third fixed wing and the fourth fixed wing, the solar unmanned aircraft of the present invention can perform any kind of flight motion. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a schematic diagram of the solar unmanned aircraft having vertical control wings according to the present invention; 
         FIG. 2  is schematic diagram of the position of the control wings when yawing according to the present invention; 
         FIG. 3  is schematic diagram of the position of the control wings when landing according to the present invention; 
         FIG. 4  is schematic diagram of the position of the control wings when diving according to the present invention; 
         FIG. 5  is schematic diagram of the position of the control wings when pitching up according to the present invention; and 
         FIG. 6  is schematic diagram of the position of the control wings when rolling according to the present invention. 
     
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT 
     The following content combines the figures and the embodiments for detail description of the present invention. 
     With reference to  FIG. 1 ,  FIG. 1  is a solar unmanned aircraft according to the present invention. The solar unmanned aircraft  100  of the present invention includes a first body  11 , a second body  12 , a main wing  13 , a tail wing  14 , a first vertical control wing  15   a , a second vertical control wing  15   b , a third vertical control wing  15   c , a fourth vertical control wing  15   d , a first propeller  16  and a second propeller  17 . 
     The first body  11  and the second body  12  are parallel. The first propeller  16  is located at a rear end of the first body  11 , and the second propeller  17  is located at a rear end of the second body  12 . The main wing  13  is disposed between the front ends and rear ends of the first body  11  and the second body  12 . The tail wing is connected between the rear ends of the first body  11  and the second body  12 . Wherein, a width of the main wing  13  is wider than a width of the tail wing  14 . 
     An upper surface of the main wing  13  is installed with solar panels for providing the power when the solar unmanned aircraft flies. A lower surface of the main wing  13  is connected with the first body  11  and the second body  12 . The lower surface of the main wing  13  can also directly connect with the first vertical control wing  15   a  and/or the second vertical control wing  15   b.    
     An upper surface of the tail wing  14  is installed with solar panels for providing the power of the solar unmanned aircraft when flying. A lower surface of the tail wing can also directly connect with the third vertical control wing  15   c  and/or the fourth vertical control wing  15   d . The tail wing  14  can generate a lifting force as the main wing  13 , and using the lifting force to generate a pitch control moment with respect to the center of gravity of the aircraft. 
     The first vertical control wing  15   a  is disposed below the main wing  13  and the first body  11  so as to be adjacent to the lower surface of the main wing  13 . The first vertical control wing  15   a  is also corresponding to a connection portion of the main wing  13  and the first body  11 . The first vertical control wing  15   a  has a first fixed wing  151   a  and a first rudder  152   a . The first fixed wing  151   a  is fixed to the first body  11 . The first rudder  152   a  is fixed to the first fixed wing  151   a  and capable of rotating with respect to the first fixed wing  151   a . Wherein, the first vertical control wing  15   a  can also locate below the main wing  13  or the first body  11 , and the present invention is not limited. Besides, the first vertical control wing  15   a  has a top terminal and an end terminal. The top terminal is connected with the main wing  13  or the first body  11 , and the end terminal of the first vertical control wing  15   a  forms a free end. 
     The second vertical control wing  15   b  is disposed below the main wing  13  and the second body  12  so as to be adjacent to the lower surface of the main wing  13 . The second vertical control wing  15   b  is also corresponding to a connection portion of the main wing  13  and the second body  12 . In other words, the second vertical control wing  15   b  and the first vertical control wing  15   a  are located at a same side of the main wing  13 . The second vertical control wing  15   b  has a second fixed wing  151   b  and a second rudder  152   b . The second fixed wing  151   b  is fixed to the second body  12 . The second rudder  152   b  is fixed to the second fixed wing  151   b  and capable of rotating with respect to the second fixed wing  151   b . Wherein, the second vertical control wing  15   b  can also locate below the main wing  13  or the second body  12 , and the present invention is not limited. Besides, the second vertical control wing  15   b  has a top terminal and an end terminal. The top terminal is connected with the main wing  13  or the second body  12 , and the end terminal of the second vertical control wing  15   b  forms a free end. 
     The third vertical control wing  15   c  is disposed below the tail wing  14  and the first body  11  so as to be adjacent to the lower surface of the tail wing  13 . The third vertical control wing  15   c  is also corresponding to a connection portion of the tail wing  14  and the first body  11 . The third vertical control wing  15   c  has a third fixed wing  151   c  and a third rudder  152   c . The third fixed wing  151   c  is fixed to the first body  11 . The third rudder  152   c  is fixed to the third fixed wing  151   c  and capable of rotating with respect to the third fixed wing  151   c . Wherein, the third vertical control wing  15   c  can also locate below the tail wing  14  or the first body  11 , and the present invention is not limited. Besides, the third vertical control wing  15   c  has a top terminal and an end terminal. The top terminal is connected with the tail wing  14  or the first body  11 , and the end terminal of the third vertical control wing  15   c  forms a free end. 
     The fourth vertical control wing  15   d  is disposed below the tail wing  14  and the second body  12 . The fourth vertical control wing  15   d  is also corresponding to a connection portion of the tail wing  14  and the second body  12 . In other words, the fourth vertical control wing  15   d  and the third vertical control wing  15   c  are located at a same side of the tail wing  13 . The fourth vertical control wing  15   d  has a fourth fixed wing  151   d  and a fourth rudder  152   d . The fourth fixed wing  151   d  is fixed to the second body  12 . The fourth rudder  152   d  is fixed to the fourth fixed wing  151   d  and capable of rotating with respect to the fourth fixed wing  151   d . Wherein, the fourth vertical control wing  15   d  can also locate below the tail wing  14  or the second body  12 , and the present invention is not limited. Besides, the fourth vertical control wing  15   d  has a top terminal and an end terminal. The top terminal is connected with the tail wing  13  or the second body  12 , and the end terminal of the fourth vertical control wing  15   d  forms a free end. 
     Accordingly, through the first vertical control wing  15   a , the second vertical control wing  15 , the third vertical control wing  15   c  and the fourth vertical control wing  15   d , when the unmanned aircraft of the present invention is on the ground, the unmanned aircraft can be stably supported. Besides, when the unmanned aircraft is landing, the above four vertical control wings can be used as a landing gear such that an additional landing gear is not required. Specifically, end terminals of the first fixed wing  151   a , the second fixed wing  151   b , the third fixed wing  151   c  and the fourth fixed wing  151   d  can be installed with sleeves (not shown in the figures). The sleeves are made of rubber so that the friction when landing and sliding is reduced. 
     The first rudder  152   a , the second rudder  152   b , the third rudder and the fourth rudder  152   d  can rotate with respect to the first fixed wing  151   a , the second fixed wing  151   b , the third fixed wing  151   c  and the fourth fixed wing  151   d  in order to control the direction of the aircraft, specifically descripting as following paragraph. 
     With reference to  FIG. 2 , when the aircraft intends to rotate, that is also called yawing, the first rudder  152   a  is in parallel with the first body  11 , the second rudder  152   b  is in parallel with the second body  12 . The third ruder  152   c  is rotated clockwise or counterclockwise and forms an included angle with the first body  11 . The fourth rudder  152   d  is rotated clockwise or counterclockwise and forms an included angle with the first body  12 . Preferably, the third rudder  152   c  and the fourth rudder  152   d  are rotated together with a same angle, and respectively form an included angle with the first body  11  and the second body  12  in order to generate a yaw moment. 
     With reference to  FIG. 3 , when the aircraft  100  is landing, and reducing the speed through brake or reducing lift force is required, the first rudder  152   a  is rotated counterclockwise and forms an included angle with the first body  11 , the second rudder  152   b  is rotated clockwise and forms an included angle with the second body  12 , the third rudder  152   c  is rotated clockwise and forms an included angle with the first body  11 , and the fourth rudder  152   d  is rotated counterclockwise and forms an included angle with the second body  12 . Through the first rudder  152   a  and the second rudder  152   b , a spoiling effect is generated. Besides, through the third rudder  152   c  and the fourth rudder  152   d , direction of the aircraft is controlled and pressing the head of the aircraft. 
     With reference to  FIG. 4 , when the head of the aircraft  100  intends to pitch up or dive. Wherein, when the head of the aircraft intends to dive, the first rudder  152   a  is in parallel with the first body  11 , the second rudder  152   b  is in parallel with the second body  12 . The third rudder  152   c  is rotated clockwise and forms an included angle with the first body  11 , the fourth rudder  152   d  is rotated counterclockwise and forms an included angle with the second body  12  such that a dive moment is generated. The head of the aircraft dives by increasing the lift force of the tail wing through the third rudder  152   c  and the fourth rudder  152   d.    
     With reference to  FIG. 5 , when the head of the aircraft intends to pitch up, the third rudder  152   c  and the fourth rudder  152   d  are respectively in parallel with the first body  11  and the second body  12 . The first rudder  152   a  and the second rudder  152   b  are rotated with a same angle in opposite directions in order to respectively form an included angle with the first body  11  and the second body  12 , reducing airflow speed under the main wing, so as to generate an upward moment. 
     With reference to  FIG. 6 , when the unmanned aircraft intends to perform an axially rolling, the first rudder  152   a  is rotated counterclockwise or clockwise to form an included angle with the first body  11 , the third rudder  152   c  is rotated clockwise or counterclockwise in opposite to the first rudder  152   a  with roughly the same angle, the second rudder  152   b  is in parallel with the second body  12 , the fourth rudder  152   d  is in parallel with the second body  12 , to generate a roll moment to life up the first body  11  with respective to the second body  12  such that the solar unmanned aircraft  100  can perform an axially rolling. Accordingly, the lift force at one side of the aircraft is increased, and through the third rudder and the fourth rudder to generate a roll moment such that the solar unmanned aircraft  100  can perform an axially rolling. 
     Besides, an internal space of the main wing  13  and the tail wing  14  can be installed with a charge and discharge battery as a power source of the aircraft. 
     It should be noted that the first propeller  16  and the second propeller  17  are respectively installed at rear end of the first body  11  and the second body  12 . Accordingly, when the aircraft intends to pitch up or dive, the control ability of the rudders to the aircraft can be increased. Besides, when the aircraft is landing and sliding on the ground, the vertical control wing will be ripped off, and a net is required to catch the aircraft  100 . However, through the above design, the aircraft does not need to fully stop when landing so that the control process is simplified. 
     Accordingly, through disposing the first vertical control wing  15   a , the second vertical control wing  15   b , the third vertical control wing  15   c  and the fourth vertical control wing  15   d  below the main wing  13  and the tail wing  14 , the upper surface of the main wing  13  and the tail wing  14  can be massively installed with solar panels in order to increase an area for installing the solar panels such that the solar unmanned aircraft  100  can stay in the air for a longer time comparing to the conventional art. Besides, using the first rudder  152   a , the second rudder  152   b , the third rudder  152   c  and the fourth rudder  152   d  to respectively rotate with respect to the first fixed wing  151   a , the second fixed wing  151   b , the third fixed wing  151   c  and the fourth fixed wing  151   d , the solar unmanned aircraft of the present invention can perform any kind of flight motion. 
     The above embodiments of the present invention are not used to limit the claims of this invention. Any use of the content in the specification or in the drawings of the present invention which produces equivalent structures or equivalent processes, or directly or indirectly used in other related technical fields is still covered by the claims in the present invention.