A detachable solar-powered drone structure design

Abstract

This invention discloses a detachable solar-powered unmanned aerial vehicle (UAV) structural design, belonging to the fields of modular design and solar-powered aviation technology. It includes: a wing; a tail fin spaced a predetermined distance from the wing; and a mounting frame detachably connected between the wing and tail fin for attaching wings and tail fins of different lengths and for carrying various functional modules. The wing comprises a main wing midsection and an outer wing section spliced ​​together; the tail fin comprises a horizontal tail fin and a vertical tail fin spliced ​​together; solar panels are mounted on the surfaces of the wing, tail fin, and mounting frame. In this invention, the wing and tail fin are spliced ​​together with alternating concave and convex portions, allowing users to attach wings and tail fins of different lengths to the UAV according to actual mission requirements. This enables rapid adjustment and optimization of the wing structure, ensuring the UAV can adapt to various complex mission scenarios.

Description

Technical Field

[0001] This invention relates to the fields of modular design and solar-powered aviation technology, specifically to a detachable solar-powered unmanned aerial vehicle (UAV) structural design. Background Technology

[0002] With the rapid development of technology, solar photovoltaic and energy storage technologies have made significant progress. Their abundant and renewable nature makes their application prospects in the field of drones increasingly broad. The introduction of solar energy not only effectively extends the flight time of drones and reduces energy consumption, but also greatly expands the operating range and efficiency of drones.

[0003] Meanwhile, in responding to various emergencies (such as major natural disasters and public health crisis prevention and control), the rapid deployment of drones is subject to stringent requirements due to different geographical environments and diverse mission needs.

[0004] Therefore, it is necessary to provide a detachable solar-powered drone structure design. Summary of the Invention

[0005] The purpose of this invention is to provide a detachable solar-powered drone structure design, so that users can add wings and tail fins of different lengths to the drone according to actual mission requirements, ensuring that the drone can adapt to various complex mission scenarios.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A detachable solar-powered drone structural design includes:

[0008] Wings;

[0009] The tail fin is spaced at a predetermined distance from the wing;

[0010] A mounting bracket, detachably connected between the wing and the tail, is used to attach wings and tails of different lengths to the UAV and to carry various functional modules.

[0011] The wing includes: a main wing mid-section and an outer wing section that are spliced ​​together;

[0012] The tail fin includes: a horizontal tail fin and a vertical tail fin that are spliced ​​together;

[0013] Solar panels are mounted on the surfaces of the wings, the tail fin, and the mounting frame.

[0014] Furthermore, there are two outer wing sections, which are symmetrically spliced ​​at both ends of the middle section of the main wing.

[0015] Furthermore, there are two vertical tail fins, which are symmetrically spliced ​​at both ends of the horizontal tail fin.

[0016] Furthermore, the main wing has a mounting hole on its midsection that matches the mounting bracket. One end of the mounting bracket is spliced ​​to the end of the horizontal tail fin, and the other end of the mounting bracket extends through the mounting hole to a predetermined distance outside the midsection of the main wing. A splicing structure is provided between the mounting bracket and the mounting hole.

[0017] Furthermore, the splicing structure consists of a series of cooperating concave and convex portions.

[0018] Furthermore, there are two mounting holes, which are symmetrically located on the middle section of the main wing; there are two mounting brackets, which are symmetrically connected to both sides of the horizontal tail fin; and the two mounting holes and the two mounting brackets are arranged in a one-to-one correspondence.

[0019] Furthermore, the outer section of the wing is provided with a 10-degree dihedral angle to provide horizontal calm stability.

[0020] Furthermore, the main wing has a 1.5-degree installation angle at its midsection to provide greater lift.

[0021] The present invention has the following beneficial effects:

[0022] In this invention, the wings and tail are respectively spliced ​​together by the interlacing of concave and convex parts, which allows users to add wings and tails of different lengths to the drone according to actual mission requirements, realize the rapid adjustment and optimization of the wing structure, and ensure that the drone can adapt to various complex mission scenarios. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of the detachable solar-powered drone structure provided in this embodiment;

[0024] Figure 2 This is an enlarged structural diagram of the splicing structure in this embodiment. Figure 1 ;

[0025] Figure 3 This is an enlarged structural diagram of the splicing structure in this embodiment. Figure 2 ;

[0026] Figure 4 This is an enlarged structural diagram of the fixing frame in this embodiment;

[0027] Figure 5 This is a cross-sectional view of the MH114 airfoil in this embodiment;

[0028] Figure 6The curves showing the lift coefficient and drag coefficient of the MH114 airfoil in this embodiment are shown.

[0029] Figure 7 The polar line of the MH114 airfoil in this embodiment;

[0030] Figure 8 This is a cross-sectional view of the NACA6408 airfoil in this embodiment;

[0031] Figure 9 This is a diagram of the wingtip vortex traces behind the NACA0005 airfoil in this embodiment;

[0032] Figure 10 This is a cross-sectional view of the NACA0005 airfoil in this embodiment;

[0033] Figure 11 This is a basic layout diagram of the UAV in this embodiment;

[0034] Figure 12 This is the lift-to-drag ratio curve of the UAV in this embodiment;

[0035] Figure 13 The figures show the lift curve and pitch moment coefficient curve of the UAV near a 0-degree angle of attack in this embodiment.

[0036] Figure 14 This is a top-down view of the aerodynamic pressure (pressure difference between the upper and lower parts of the wing) distribution experienced by the UAV in this embodiment.

[0037] The components are: 1. Main wing midsection; 2. Mounting hole; 3. Outer wing section; 4. Horizontal tail; 5. Vertical tail; 6. Mounting frame. Detailed Implementation

[0038] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0039] Reference Figure 1-4 This embodiment provides a detachable solar-powered drone structure design to improve its flexibility, enabling faster deployment and use. It includes:

[0040] Wings; the tail is spaced at a predetermined distance from the wings.

[0041] The mounting bracket 6 is detachably connected between the wings and the tail, and is used to attach wings and tails of different lengths to the UAV and to carry various functional modules; solar panels are installed on the surfaces of the wings, tail and mounting bracket 6.

[0042] The wing comprises two interconnected main wing midsections 1 and outer wing sections 3. The main wing midsection 1 has a 1.5-degree angle of attack to provide greater lift. The outer wing section 3 has a 10-degree dihedral angle to provide horizontal stability. There are two outer wing sections 3, symmetrically joined at both ends of the main wing midsection 1.

[0043] The tail section includes two vertical tail fins 4 and 5, which are spliced ​​together. The two vertical tail fins 5 are symmetrically spliced ​​to the ends of the horizontal tail fin 4. The mid-section 1 of the main wing has mounting holes 2 that match the mounting bracket 6. One end of the mounting bracket 6 is spliced ​​to the end of the horizontal tail fin 4, and the other end of the mounting bracket 6 extends through the mounting hole 2 to a predetermined distance outside the mid-section 1 of the main wing. A splicing structure is provided between the mounting bracket 6 and the mounting hole 2. The splicing structure consists of multiple consecutive, mutually cooperating concave and convex portions.

[0044] In this embodiment, there are two mounting holes 2, which are symmetrically opened on the middle section 1 of the main wing; there are two fixing brackets 6, which are symmetrically connected to both sides of the first wing spars; the two mounting holes 2 and the two fixing brackets 6 are arranged in a one-to-one correspondence.

[0045] To achieve flexible deployment, this invention provides a detachable wing and tail design. This design mainly consists of two parts, each joined together by interlocking concave and convex sections. This allows users to add wings and tails of different lengths to the drone according to actual mission requirements, enabling rapid adjustment and optimization of the wing structure. This ensures the drone can adapt to various complex mission scenarios, while the surface is covered with flexible solar panels to continuously power the drone's flight.

[0046] This invention provides a detachable mounting bracket design to enable the installation of the longest possible wings on a drone. This design improves the stability of the wing between two reinforced designs spaced at a specific distance. It also serves as a fuselage design, responsible for carrying mission-related functional modules, and is covered with flexible solar panels to continuously power the drone's flight.

[0047] Reference Figure 5-10 This embodiment illustrates the application of this structure to a solar-powered drone that provides communication services while flying in the stratosphere.

[0048] 1. Basic parameters

[0049] Total weight estimated: 21kg

[0050] Estimated cruising speed: 20 m / s

[0051] Air density: 0.24 kg / m³ 3

[0052] Wingspan: 10m

[0053] Main chord length: 1m

[0054] Lifting area: 10m² 2

[0055] Overall lift coefficient estimation: C l =(210*2 / (20) 2 *10*0.24)) 0.5 =0.661

[0056] Reynolds number estimation: Re = 0.24 * 20 * 1 / 1.81 * 10 -5 =2.7*10 5

[0057] 2. Airfoil selection and basic aerodynamic layout

[0058] To provide sufficient lift and internal space to accommodate enough equipment, the main wing midsection 1 uses the MH114 airfoil with a large camber and thickness. At the same time, the main wing midsection 1 provides a 1.5-degree installation angle to provide greater lift.

[0059] Due to the excessive pressure difference between the upper and lower sections of the MH114 airfoil, in order to avoid excessive energy loss caused by excessive wingtip vortices and to reduce the weight of the main wing structure, the outer section 3 of the wing smoothly transitions to the NACA6408 airfoil, which has a relatively low camber and is thinner.

[0060] To achieve a lower weight while maintaining sufficient structural strength, the symmetrical thin airfoil NACA0005 was selected for the tail fin.

[0061] To minimize the weight of the fuselage structure, the lever arm of the tail fin was shortened, while the tail fin area was appropriately increased. This design ensures that the UAV still has good directional and pitch static stability even with a small tail fin lever arm. To avoid the UAV's insufficient horizontal static stability and excessive pitch and directional static stability, which would cause the UAV to exhibit a "Dutch roll" phenomenon when disturbed, a 10-degree dihedral angle was designed on the outer section of the main wing to provide horizontal static stability.

[0062] 3. Basic Aerodynamic Parameters and Stability of Unmanned Aerial Vehicles

[0063] like Figure 11 As shown, basic aerodynamic parameters of the UAV can be obtained through computer simulation software. This UAV configuration features a high lift-to-drag ratio and a high lift coefficient, meeting the requirements of high efficiency and low-speed, high-lift capabilities for solar-powered UAVs.

[0064] Reference Figure 12-14Analysis of the pitch moment curve shows that the UAV is balanced at a 0.5-degree pitch angle and has good pitch static stability. Due to manufacturing process and calculation errors, this 0.5 degrees can be approximated as the UAV being balanced at a 0-degree angle of attack.

[0065] The embodiments described above are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by persons skilled in the art should fall within the scope of protection defined by the claims of the present invention.

Claims

1. A detachable solar-powered unmanned aerial vehicle (UAV) structural design, characterized in that, include: Wings; The tail fin is spaced at a predetermined distance from the wing; A mounting bracket, detachably connected between the wing and the tail, is used to attach wings and tails of different lengths to the UAV and to carry various functional modules. The wing includes: a main wing mid-section and an outer wing section that are spliced ​​together; The tail fin includes: a horizontal tail fin and a vertical tail fin that are spliced ​​together; Solar panels are installed on the surfaces of the wings, the tail fin, and the mounting frame. The main wing has a mounting hole on its midsection that matches the mounting bracket. One end of the mounting bracket is spliced ​​to the end of the horizontal tail fin. The other end of the mounting bracket passes through the mounting hole and extends to a predetermined distance outside the midsection of the main wing. A splicing structure is provided between the mounting bracket and the mounting hole. The splicing structure consists of a series of cooperating concave and convex parts. The outer section of the wing is provided with a 10-degree dihedral angle to provide horizontal calm stability; The main wing has a 1.5-degree installation angle at its midsection to provide greater lift.

2. The detachable solar-powered UAV structural design according to claim 1, characterized in that, The number of wing outer sections is two, and the two wing outer sections are symmetrically spliced ​​at both ends of the main wing middle section.

3. The detachable solar-powered UAV structural design according to claim 1, characterized in that, The number of vertical tail fins is two, and the two vertical tail fins are symmetrically spliced ​​at both ends of the horizontal tail fin.

4. The detachable solar-powered UAV structural design according to claim 1, characterized in that, There are two mounting holes, which are symmetrically located on the middle section of the main wing; there are two mounting brackets, which are symmetrically connected to both sides of the horizontal tail fin; the two mounting holes and the two mounting brackets are arranged in a one-to-one correspondence.

Images