Detachable solar unmanned aerial vehicle structure design

Abstract

The invention discloses a detachable solar unmanned aerial vehicle structure design, and belongs to the technical field of modular design and solar aviation. The unmanned aerial vehicle comprises wings; the empennage and the wings are spaced by a preset distance; the fixing frame is detachably connected between the wings and the empennage and used for additionally installing the wings and the empennage of different lengths for the unmanned aerial vehicle and carrying all the function modules. Wherein the wing comprises a main wing middle section and a wing outer section which are spliced with each other; the empennage comprises a horizontal empennage and a vertical empennage which are spliced with each other; solar panels are installed on the surfaces of the wings, the empennage and the fixing frame. The wings and the empennage are spliced in a staggered mode through the concave parts and the convex parts, a user can be allowed to additionally install the wings and the empennage with different lengths for the unmanned aerial vehicle according to actual task requirements, rapid adjustment and optimal configuration of the wing structure are achieved, and it is ensured that the unmanned aerial vehicle can adapt to various complex task scenes.

Description

Technical Field

[0001] The invention relates to the field of modular design and solar energy aviation technology, and in particular to a detachable solar energy unmanned aerial vehicle structure design. Background Art

[0002] With the rapid development of science and technology, solar photovoltaic and energy storage technologies have made significant progress. The abundant and renewable characteristics of solar energy make its application prospects in the field of drones more and more 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] At the same time, when responding to various emergencies (such as major natural disasters, public health crisis prevention and control, etc.), due to different geographical environments and diverse mission requirements, strict requirements are placed on the rapid deployment of drones.

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

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

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A detachable solar-powered drone structure design, comprising:

[0008] Wings;

[0009] a tail wing spaced a predetermined distance from the wing;

[0010] A fixing frame, detachably connected between the wing and the tail, used to add wings and tails of different lengths to the UAV and to carry various functional modules;

[0011] Wherein, the wing comprises: a main wing middle section and a wing outer section spliced ​​to each other;

[0012] The tail wing comprises: a horizontal tail wing and a vertical tail wing spliced ​​to each other;

[0013] Solar panels are installed on the surfaces of the wing, the tail wing and the fixing frame.

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

[0015] Furthermore, the number of the vertical tail fins is two, and the two vertical tail fins are symmetrically spliced ​​at two ends of the horizontal tail fin.

[0016] Furthermore, a mounting hole matching the fixing frame is opened on the middle section of the main wing, one end of the fixing frame is spliced ​​with the end of the horizontal tail, and the other end of the fixing frame extends to a predetermined distance outside the middle section of the main wing after passing through the mounting hole, and a splicing structure is arranged between the fixing frame and the mounting hole.

[0017] Furthermore, the splicing structure is a plurality of continuous concave parts and convex parts that cooperate with each other.

[0018] Furthermore, the number of the mounting holes is two, and the two mounting holes are symmetrically opened on the middle section of the main wing; the number of the fixing frames is two, and the two fixing frames are symmetrically connected to both sides of the horizontal tail; the two mounting holes are arranged in a one-to-one correspondence with the two fixing frames.

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

[0020] Furthermore, a 1.5 degree installation angle is provided on the middle section of the main wing to provide greater lift.

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

[0022] In the present invention, the wings and tail are respectively spliced ​​by the interlaced concave parts and convex parts, which allows the user to add wings and tails of different lengths to the drone according to actual mission requirements, realize the rapid adjustment and optimal configuration of the wing structure, and ensure that the drone can adapt to various complex mission scenarios. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 The overall structural diagram of the detachable solar-powered drone structure design provided in this embodiment;

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

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

[0026] Figure 4 is an enlarged structural schematic 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 lift coefficient and drag coefficient curve of the MH114 airfoil in this embodiment;

[0029] Figure 7 It is 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] Fig. 9 The wing tip vortex trace diagram behind the NACA0005 airfoil in this embodiment;

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

[0033] Fig.11 This is the basic layout diagram of the drone in this embodiment;

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

[0035] Fig.13 : The lift curve and pitch moment coefficient curve of the drone near the 0 degree angle of attack in this embodiment;

[0036] Fig.14 This is a distribution diagram of the aerodynamic pressure (pressure difference between the upper and lower wings) on the UAV in this embodiment (top view).

[0037] Among them: 1. The middle section of the main wing; 2. Mounting holes; 3. The outer section of the wing; 4. The horizontal tail; 5. The vertical tail; 6. The fixing bracket. DETAILED DESCRIPTION

[0038] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with 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, the purpose of which is to improve its flexibility so that it can be deployed and used more quickly. It includes:

[0040] The wing; the tail is spaced a predetermined distance from the wing.

[0041] The fixing frame 6 is detachably connected between the wing and the tail, and is used to add wings and tails of different lengths to the UAV and to carry various functional modules; the surfaces of the wings, the tail and the fixing frame 6 are all installed with solar panels.

[0042] The wing includes: a main wing middle section 1 and a wing outer section 3 which are spliced ​​together; the main wing middle section 1 is provided with a 1.5 degree installation angle to provide greater lift. The wing outer section 3 is provided with a 10 degree dihedral angle to provide horizontal stability. There are two wing outer sections 3, which are symmetrically spliced ​​at both ends of the main wing middle section 1.

[0043] The tail wing includes: a horizontal tail wing 4 and a vertical tail wing 5 spliced ​​to each other; there are two vertical tail wing 5, and the two vertical tail wing 5 are symmetrically spliced ​​to the two ends of the horizontal tail wing 4. The main wing middle section 1 is provided with a mounting hole 2 matching with a fixing frame 6, one end of the fixing frame 6 is spliced ​​with the end of the horizontal tail wing 4, and the other end of the fixing frame 6 passes through the mounting hole 2 and extends to a predetermined distance outside the main wing middle section 1, and a splicing structure is provided between the fixing frame 6 and the mounting hole 2. The splicing structure is a continuous plurality of mutually matching concave and convex parts.

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

[0045] The present invention provides a detachable wing and tail design to achieve flexible deployment. This design mainly consists of two parts, each of which is staggered with a concave part and a convex part, allowing the user to add wings and tails of different lengths to the drone according to actual mission requirements, so as to achieve rapid adjustment and optimal configuration of the wing structure, ensuring that the drone can adapt to various complex mission scenarios. At the same time, the surface is covered with flexible solar panels to continuously provide energy for the drone flight.

[0046] The present invention provides a detachable fixing frame design to enable the drone to be equipped with as long a wing as possible. This part of the design improves the stability of the wing between two reinforcement designs separated by a specific distance. It also serves as a fuselage design, responsible for carrying mission-related functional modules, and is also covered with flexible solar panels to continuously provide energy for the drone flight.

[0047] Reference Figure 5-10 This embodiment shows the case where this structure is applied to a solar-powered UAV that provides communication services while flying in the stratosphere.

[0048] 1. Basic parameters

[0049] Total estimated weight: 21kg

[0050] Estimated cruising speed: 20m / s

[0051] Air density: 0.24kg / m 3

[0052] Wingspan: 10m

[0053] Main chord length: 1m

[0054] Lift area: 10m 2

[0055] Estimation of lift coefficient of the whole machine: 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] In order to provide sufficient lift and internal space to accommodate sufficient equipment, the middle section 1 of the main wing adopts the MH114 airfoil with large curvature and thickness. At the same time, the middle section 1 of the main wing provides a 1.5-degree installation angle to provide greater lift.

[0059] Due to the large pressure difference between the upper and lower parts 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 a relatively low-curvature and thinner NACA6408 airfoil.

[0060] In order to make the tail wing have a lower weight while having sufficient structural strength, the symmetrical thin airfoil NACA0005 is selected for the tail wing.

[0061] In order to minimize the weight of the fuselage structure, the length of the tail arm is shortened and the tail area is appropriately increased. This design ensures that the UAV still has good heading and pitch static stability when the tail arm is small. In order to avoid the UAV's insufficient horizontal static stability and excessive pitch and heading static stability, which may cause the UAV to "Dutch roll" when disturbed, a 10-degree upward angle is designed for the outer section of the main wing to provide horizontal static stability.

[0062] 3. Basic aerodynamic parameters and stability of drones

[0063] like Fig.11 As shown in the figure, the basic aerodynamic parameter data of the UAV can be obtained through computer simulation software. The UAV with this layout has the characteristics of large lift-to-drag ratio and large lift coefficient, which can meet the requirements of high efficiency and low-speed large lift of solar UAV.

[0064] Reference Figure 12-14,From the analysis of the pitch moment curve, it can be obtained that the UAV is balanced at an elevation angle of 0.5 degrees and has good pitch static stability. Due to problems such as manufacturing process and calculation deviation, this 0.5 degree can be approximately regarded as the UAV being balanced at an angle of attack of 0 degrees.

[0065] The embodiments described above are only descriptions of the preferred modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A detachable solar-powered drone structure design, characterized in that: include: Wings; a tail wing spaced a predetermined distance from the wing; A fixing frame, detachably connected between the wing and the tail, used to add wings and tails of different lengths to the UAV and to carry various functional modules; Wherein, the wing comprises: a main wing middle section and a wing outer section spliced ​​to each other; The tail wing comprises: a horizontal tail wing and a vertical tail wing spliced ​​to each other; Solar panels are installed on the surfaces of the wing, the tail wing and the fixing frame.

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

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

4. The detachable solar-powered drone structure design according to claim 1 is characterized in that: The middle section of the main wing is provided with a mounting hole matching the fixing frame, one end of the fixing frame is spliced ​​with the end of the horizontal tail, and the other end of the fixing frame passes through the mounting hole and extends to a predetermined distance outside the middle section of the main wing, and a splicing structure is provided between the fixing frame and the mounting hole.

5. The detachable solar-powered drone structure design according to claim 4 is characterized in that: The splicing structure is a plurality of continuous concave parts and convex parts that cooperate with each other.

6. The detachable solar-powered drone structure design according to claim 4 is characterized in that: The number of the mounting holes is two, and the two mounting holes are symmetrically opened on the middle section of the main wing; the number of the fixing frames is two, and the two fixing frames are symmetrically connected to the two sides of the horizontal tail; the two mounting holes are arranged in a one-to-one correspondence with the two fixing frames.

7. The detachable solar-powered drone structure design according to claim 1 is characterized in that: The outer section of the wing is provided with a 10-degree dihedral angle for providing horizontal stability.

8. The detachable solar-powered drone structure design according to claim 1 is characterized in that: A 1.5 degree installation angle is set on the middle section of the main wing to provide greater lift.

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