Patent Publication Number: US-2022234732-A1

Title: Carrying apparatus

Description:
TECHNICAL FIELD 
     The present invention relates to a carrying apparatus which provides carrying passenger or load in drones and similar vehicles. 
     PRIOR ART 
     Drone is unmanned air vehicle which can be easily guided by means of remote control or software management. Drones or unmanned air vehicles are used in an active manner by various different sectors. Drones which gained popularity particularly in the recent years can realize various duties like communication, advertising, search and rescue works and cargo transportation. 
     Drones can carry loads with specific capacity according to their technical characteristics. Thus, it is possible to deliver a package, envelope or  coli  to an address by means of a drone. Today, pluralities of companies realize R&amp;D studies about order delivery by means of drones. By means of this, it is planned to deliver specific orders by means of drones. 
     In the literature, there is the utility model application with application number CN208585412U and with title “consumable material carrying hanger for unmanned airplane”. In said application, a kind of carrying hanger, particularly a carrying hanger which is suitable for carrying material for drones. In order to solve the technical problem, said invention comprises an assembly bracket, a first bracket, a second bracket, an assembly component, a discharge component, an electrical pushing rod, a carriage shelf which is suitable for the placement of a material. 
     As a result, because of all of the abovementioned problems, an improvement is required in the related technical field. 
     BRIEF DESCRIPTION OF THE INVENTION 
     The present invention relates to a carrying apparatus, for eliminating the above mentioned disadvantages and for bringing new advantages to the related technical field. 
     An object of the present invention is to provide a carrying apparatus for use in drones, which provides carrying of passenger or load in a manner moving with minimum friction and drifting to any direction in air, in aerodynamic lifting-off and landing. 
     Another object of the present invention is to provide a carrying apparatus which will be affected by air movements with minimum manner and which will use maximum volume for carrying extra load. 
     In order to realize the abovementioned objects and the objects which are to be deducted from the detailed description below, the present invention relates to a carrying apparatus which is associated with drones and similar vehicles and which provides carrying passenger or load. Accordingly, said carrying apparatus comprises a center part having a predefined geometrical shape, a first lateral wall which encircles a volume which begins in a manner encircling said center part and which decreases towards a first end provided at a first direction and a second lateral wall which begins in a manner encircling said center part and which decreases towards a second end provided at a second direction. Thus, a carrying apparatus is provided which provides carrying load in a manner moving with minimum friction and drifting to any direction in air, in aerodynamic lifting-off and landing. 
     In a possible embodiment of the present invention, said center part is in circular form. 
     In a possible embodiment of the present invention, said center part is in square form. 
     In a possible embodiment of the present invention, said center part is in equilateral triangle form. 
     In a possible embodiment of the present invention, the surface of said first lateral wall and the surface of said second lateral wall comprise more than one layer in cylindrical form positioned one above the other. Thus, minimum friction is provided during the movement of the carrying apparatus. 
     In a possible embodiment of the present invention, more than one depression is provided with respect to any one or ones of the polygonal, circular and ellipse forms provided on the first lateral wall and on the second lateral wall surfaces. Thus, the friction coefficient of the carrying apparatus is reduced. 
     In a possible embodiment of the present invention, at least one hook is provided on the first end for providing associating with the drone. 
    
    
     
       BRIEF DESCRIPTION OF THE FIGURES 
         FIG. 1  is a lateral view of the subject matter carrying apparatus. 
         FIG. 2  is a perspective view of the subject matter carrying apparatus. 
         FIG. 3  is a representative top view of the subject matter carrying apparatus. 
         FIG. 4  is the cross sectional view of the solution web of the subject matter carrying apparatus. 
         FIG. 5 a    is the speed distribution around the carrying apparatus with respect to the analysis in the orthogonal flight thereof. 
         FIG. 5 b    is the pressure distribution around the carrying apparatus with respect to the analysis in the orthogonal flight thereof. 
         FIGS. 5 c  and 5 d    are respectively the upper and lower views of the pressure distribution around the carrying apparatus with respect to the analysis in the orthogonal flight thereof. 
         FIG. 5 e    is the vector speed distribution around the carrying apparatus with respect to the analysis in the orthogonal flight thereof. 
         FIG. 6 a    is the speed distribution around the carrying apparatus with respect to the analysis in the horizontal flight thereof. 
         FIG. 6 b    is the pressure distribution around the carrying apparatus with respect to the analysis in the horizontal flight thereof. 
         FIGS. 6 c  and 6 d    are respectively the upper and lower views of the pressure distribution around the carrying apparatus with respect to the analysis in horizontal flight thereof. 
         FIG. 6 e    is the vector speed distribution around the carrying apparatus with respect to the analysis in horizontal flight thereof. 
         FIG. 7 a    is the speed distribution around the carrying apparatus with respect to the analysis in 45 degrees orthogonal flight thereof. 
         FIG. 7 b    is the pressure distribution around the carrying apparatus with respect to the analysis in 45 degrees orthogonal flight thereof. 
         FIGS. 7 c  and 7 d    are respectively the upper and lower views of the pressure distribution around the carrying apparatus with respect to the analysis in 45 degrees orthogonal flight thereof. 
         FIG. 7 e    is vector speed distribution around the carrying apparatus with respect to the analysis in 45 degrees orthogonal flight thereof. 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     In this detailed description, the subject matter carrying apparatus ( 1 ) is explained with references to examples without forming any restrictive effect only in order to make the subject more understandable. 
     In  FIG. 1 , a lateral view of the subject matter carrying apparatus ( 1 ) is given. The present invention relates to a carrying apparatus ( 1 ) for use in drones and similar vehicles and which provides carrying passenger or load in a manner moving with minimum friction in air, in aerodynamic lifting-off and landing. In said carrying apparatus ( 1 ), there is a center part ( 30 ) which has a pre-defined geometrical shape. There is a first lateral wall ( 10 ) which encircles a volume which begins in a manner encircling said center part ( 30 ) and which decreases towards a first end ( 11 ) provided at a first direction ( 31 ) and a second lateral wall ( 20 ) which begins in a manner encircling said center part ( 30 ) and which decreases towards a second end ( 21 ) provided at a second direction ( 32 ). At least one hook ( 40 ) is provided on said first end ( 11 ) for providing associating of the carrying apparatus ( 1 ) with the drone. 
     In  FIG. 2 , a representative perspective lateral view of the subject matter carrying apparatus ( 1 ) is given. The center part ( 30 ) can have a geometrical form like circle, square or equilateral triangle. In the preferred embodiment of the present invention, the center part ( 30 ) has a circular form. There is a chamber structure between the first lateral wall ( 10 ) which encircles a volume decreasing from the center part ( 30 ) towards the first end ( 11 ) provided at said first direction ( 31 ) and the second lateral wall ( 20 ) which encircles a volume decreasing from the center part ( 30 ) towards the second end ( 21 ) provided at said second direction ( 32 ). 
     Desired load can be placed into said chamber. In the preferred embodiment of the present invention, the first lateral wall ( 10 ) can be in conical shape which extends from the center part ( 30 ) towards the first end ( 11 ) and the second lateral wall ( 20 ) can be in inverse-conical shape which extends from the center part ( 30 ) towards the second end ( 21 ). 
     While realizing maneuver for changing direction, drones can move in any direction any time without realizing maneuver like rotocopter or multicopter in an opposite manner to airplanes. The carrying apparatus ( 1 ) associated with the drone has an equal surface structure in all orthogonal or horizontal movements. Since the chamber is narrowed at the bottom in the orthogonal plane, the load, carried in the chamber, stays at the bottom part of the chamber and the weight center of the carrying apparatus ( 1 ) is prevented from being deteriorating. 
     In the carrying apparatus ( 1 ), there may be more than one layer ( 50 ) in cylindrical form positioned one above the other on the first lateral wall ( 10 ) and on the second lateral wall ( 20 ) surfaces. Thanks to said cylindrical layer ( 50 ) structure provided on the first lateral wall ( 10 ) and on the second lateral wall ( 20 ) surface, minimum friction is provided in the carrying apparatus ( 1 ) during movement. Drones basically move orthogonally for lifting-off and they move horizontally during the trip. Thanks to the shape of surface of the carrying apparatus ( 1 ), the same form is protected independent from the movement direction thereof in air. 
     Moreover, in the carrying apparatus ( 1 ), more than one depression ( 60 ) is provided which can have polygonal, circular and ellipse forms provided on the first lateral wall ( 10 ) and on the second lateral wall ( 20 ) surfaces. Thanks to said depression ( 60 ) structure, a turbulent border layer is formed on the surface of the carrying apparatus ( 1 ) and thus, decrease in the drifting coefficient is provided. 
     Thus, a carrying apparatus ( 1 ) is provided for use in drones, which provides carrying of passenger or load in a manner moving with minimum friction and drifting to any direction in air, in aerodynamic lifting-off and landing. 
     ANALYSIS 
     In order to be able to obtain speed and pressure distributions around the carrying apparatus ( 1 ) as well as the pressure decreases and the reaction forces around the carrying apparatus ( 1 ), flow analyses are realized at 45 degrees and in horizontal and orthogonal flight. 
     The analysis in the orthogonal flight has been evaluated as the first state, the analysis in the horizontal flight has been evaluated as the second state and the 45 degrees orthogonal flight has been evaluated as the third state. For the first state, the speed value of the flight of the carrying apparatus ( 1 ) has been entered as 35 km/h. For the second state, the speed of the carrying apparatus ( 1 ) has been entered as 100 km/h. In the third state, the speed value of the flight of the carrying apparatus ( 1 ) has been entered as 50 km/h. For all states in the analyses, the temperature has been used as 20° C. The mechanical values of the air have been taken as the outer atmosphere value at 1 atm. The outer atmosphere pressure value has been taken as 1 atm. 
     The control volume in the analysis has been increased by ten times of the carrying apparatus ( 1 ) in every direction and all surfaces have been defined as the outer atmosphere. With reference to  FIG. 4 , totally approximately 1300000 solution webs have been used in the domain. The cells have been high in frequency around the carrying apparatus ( 1 ), and the cells have been low in frequency outwardly. 
     For the first state, in other words, in the orthogonal flight of the carrying apparatus ( 1 ), the analyses are as follows. The speed distribution around the carrying apparatus ( 1 ) has been given in  FIG. 5 a   . The pressure distribution around the carrying apparatus ( 1 ) has been given in  FIG. 5 b   . In  FIGS. 5 c  and 5 d   , the upper and lower views of the pressure distribution around the carrying apparatus ( 1 ) are respectively given. In  FIG. 5 e   , the vector speed distribution around the carrying apparatus ( 1 ) is given. The force, pressure and shear stress values of the carrying apparatus ( 1 ) for the first state are given in Table 1. As seen, for the carrying apparatus ( 1 ), ideal aerodynamic values have been reached in the orthogonal flight. 
     For the second state, in other words, in the horizontal flight of the carrying apparatus ( 1 ), the analyses are as follows. The speed distribution around the carrying apparatus ( 1 ) is given in  FIG. 6 a   . The pressure distribution around the carrying apparatus ( 1 ) is given in  FIG. 6 b   . In  FIGS. 6 c  and 6 d   , the upper and lower views of the pressure distribution around the carrying apparatus ( 1 ) are respectively given. In  FIG. 6 e   , the vector speed distribution around the carrying apparatus ( 1 ) is given. The force, pressure and shear stress values of the carrying apparatus ( 1 ) for the second state are given in Table 2. As seen, for the carrying apparatus ( 1 ), ideal aerodynamic values have been reached in the horizontal flight. 
     For the third state, in other words, in the 45 degrees orthogonal flight of the carrying apparatus ( 1 ), the analyses are as follows. The speed distribution around the carrying apparatus ( 1 ) is given in  FIG. 7 a   . The pressure distribution around the carrying apparatus ( 1 ) is given in  FIG. 7 b   . In  FIGS. 7 c  and 7 d   , the upper and lower views of the pressure distribution around the carrying apparatus ( 1 ) are respectively given. In  FIG. 7 e   , the vector speed distribution around the carrying apparatus ( 1 ) is given. The force, pressure and shear stress values of the carrying apparatus ( 1 ) for the third state are given in Table 3. As seen, for the carrying apparatus ( 1 ), ideal aerodynamic values have been reached in the 45 degrees orthogonal flight. 
     
       
         
           
               
             
               
                 TABLE 1 
               
             
            
               
                   
               
               
                 Force, pressure and shear stress values of the carrying  
               
               
                 apparatus (1) for the first state 
               
            
           
           
               
               
               
               
               
            
               
                   
                   
                 Unit 
                 Criterion 
                 First state 
               
               
                   
                   
               
            
           
           
               
               
               
               
               
            
               
                   
                 Average static pressure 
                 Pa 
                 1.50 
                 101319.35 
               
               
                   
                 Average total pressure 
                 Pa 
                 1.50 
                 101319.35 
               
               
                   
                 Force 
                 N 
                 0.913 
                 20.939 
               
               
                   
                 Force (X) 
                 N 
                 0.393 
                 0.012 
               
               
                   
                 Force (Y) 
                 N 
                 0.321 
                 −0.038 
               
               
                   
                 Force (Z) 
                 N 
                 0.883 
                 −20.939 
               
               
                   
                 Average shear stress 
                 Pa 
                 4.84e−03 
                 0.12 
               
               
                   
                 Average shear stress (X) 
                 Pa 
                 1.58e−03 
                 −3.66e−05 
               
               
                   
                 Average shear stress (Y) 
                 Pa 
                 1.27e−03 
                 −2.12e−04 
               
               
                   
                 Average shear stress (Z) 
                 Pa 
                 1.56e−03 
                 −0.04 
               
               
                   
                   
               
            
           
         
       
     
     
       
         
           
               
             
               
                 TABLE 2 
               
             
            
               
                   
               
               
                 Force, pressure and shear stress values of the 
               
               
                 carrying apparatus (1) for the second state 
               
            
           
           
               
               
               
               
               
            
               
                   
                   
                 Unit 
                 Criterion 
                 Second state 
               
               
                   
                   
               
            
           
           
               
               
               
               
               
            
               
                   
                 Average static pressure 
                 Pa 
                 1.18 
                 101306.81 
               
               
                   
                 Average total pressure 
                 Pa 
                 1.18 
                 101306.81 
               
               
                   
                 Force 
                 N 
                 0.191 
                 7.482 
               
               
                   
                 Force (X) 
                 N 
                 0.139 
                 −5.512 
               
               
                   
                 Force (Y) 
                 N 
                 0.037 
                 −0.093 
               
               
                   
                 Force (Z) 
                 N 
                 0.257 
                 −5.058 
               
               
                   
                 Average shear stress 
                 Pa 
                 5.60e−03 
                 0.19 
               
               
                   
                 Average shear stress (X) 
                 Pa 
                 3.91e−03 
                 −0.13 
               
               
                   
                 Average shear stress (Y) 
                 Pa 
                 1.38e−04 
                 −2.29e−05 
               
               
                   
                 Average shear stress (Z) 
                 Pa 
                 3.55e−04 
                 −5.83e−03 
               
               
                   
                   
               
            
           
         
       
     
     
       
         
           
               
             
               
                 TABLE 3 
               
             
            
               
                   
               
               
                 Force, pressure and shear stress values of the carrying 
               
               
                 apparatus (1) for the third state 
               
            
           
           
               
               
               
               
               
            
               
                   
                   
                 Unit 
                 Criterion 
                 Third state 
               
               
                   
                   
               
            
           
           
               
               
               
               
               
            
               
                   
                 Average static pressure 
                 Bar 
                 4.68e−05 
                 1.01 
               
               
                   
                 Average total pressure 
                 Bar 
                 4.68e−05 
                 1.01 
               
               
                   
                 Force 
                 N 
                 0.688 
                 23.196 
               
               
                   
                 Force (X) 
                 N 
                 0.468 
                 −8.038 
               
               
                   
                 Force (Y) 
                 N 
                 0.345 
                 −1.566 
               
               
                   
                 Force (Z) 
                 N 
                 0.713 
                 −21.702 
               
               
                   
                 Average shear stress 
                 Bar 
                 7.62e−08 
                   2.51e−06 
               
               
                   
                 Average shear stress (X) 
                 Bar 
                 3.33e−08 
                 −8.67e−07 
               
               
                   
                 Average shear stress (Y) 
                 Bar 
                 1.13e−08 
                 −6.15e−08 
               
               
                   
                 Average shear stress (Z) 
                 Bar 
                 1.86e−08 
                 −6.05e−07 
               
               
                   
                   
               
            
           
         
       
     
     When summarized, the reaction forces of the carrying apparatus ( 1 ) have been determined as 20.94 N, 7.48 N and 23.2 N respectively for the first state, the second state and the third state. For the shear stresses of the carrying apparatus ( 1 ), for the first state, the second state and the third state, the results of 0.12 Pa, 0.19 Pa and 0.251 Pa have been reached respectively. As seen, for the carrying apparatus ( 1 ), in all of the three states, ideal aerodynamic values have been reached. 
     The protection scope of the present invention is set forth in the annexed claims and cannot be restricted to the illustrative disclosures given above, under the detailed description. It is because a person skilled in the relevant art can obviously produce similar embodiments under the light of the foregoing disclosures, without departing from the main principles of the present invention. 
     REFERENCE NUMBERS 
     
         
           1  Carrying apparatus 
           10  First lateral wall 
           11  First end 
           20  Second lateral wall 
           21  Second end 
           30  Center part 
           31  First direction 
           32  Second direction 
           40  Hook 
           50  Layer 
           60  Depression