Aerodynamic layout of a large solar-powered unmanned aerial vehicle

Abstract

This application belongs to the field of large solar-powered unmanned aerial vehicles (UAVs), and describes an aerodynamic layout for such a UAV, including a fuselage and deformable wings. The deformable wings include outer wings and inner wings. When all the pivots on the fuselage are deflected to their maximum angle, this is the ground taxiing state of the solar-powered UAV, which facilitates taxiing and other operations. When all the pivots on the fuselage are deflected to an appropriate angle, the wing dimension of the solar-powered UAV is adjustable, which can make full use of the runway, take into account lift characteristics, and improve take-off and landing performance. This state is called the take-off and landing taxiing state of the solar-powered UAV. When all the pivots on the fuselage are deflected to their minimum angle, the overall flight length of the aircraft is controlled to the maximum, which is the aerial flight state of the solar-powered UAV. When the solar-powered UAV is in different stages of flight, it can ensure the optimal state for the current stage of flight, thereby achieving efficient flight of the solar-powered UAV.

Description

Technical Field

[0001] This application belongs to the field of large solar-powered unmanned aerial vehicles (UAVs), and specifically relates to an aerodynamic layout for a large solar-powered UAV. Background Technology

[0002] Solar-powered drones are unmanned aerial vehicles (UAVs) whose surfaces are covered with solar power generation devices, using solar energy and onboard energy storage to propel the aircraft. Because the aircraft can utilize solar energy during flight, its maximum endurance is significantly increased, theoretically enabling it to operate indefinitely under fault-free conditions.

[0003] Based on the performance characteristics of solar-powered drones, these aircraft are suitable for tasks such as environmental monitoring and relay guidance, and are characterized by convenient application and high cost-effectiveness.

[0004] The main power source for the entire aircraft is solar power generation, therefore the design of solar-powered drones has the following characteristics:

[0005] 1. Low flight speed. The lower the flight speed, the lower the power output of air resistance, and the lower the requirement for propulsion energy;

[0006] 2. Large wing area. The larger the wing area, the more solar power generation devices can be installed.

[0007] 3. High aerodynamic efficiency. The higher the aerodynamic efficiency, the lower the drag for the same lift, and the lower the energy requirement for the aircraft.

[0008] 4. Lighter empty weight. The lighter the empty weight, the greater the effective payload for the same takeoff weight, and the stronger the aircraft's ability to complete its mission.

[0009] In summary, solar-powered drones are often designed with a high aspect ratio and large wing area. The spanwise dimension of a solar-powered drone is positively correlated with its mission capabilities, but existing solar-powered drones suffer from short range, poor lift performance, and low speed due to their own energy limitations.

[0010] Existing large solar-powered drones adopt layouts such as connected wings, flying wings, and multi-fuselage, and combine flexible wing and elastic wing technologies to gradually improve the product design of solar-powered drones.

[0011] The larger the size of a solar-powered drone, the greater its mission capabilities. However, the current size design of solar-powered drones is constrained by the conditions of the taxiway and runway surfaces for takeoff and landing. On the one hand, when taxiing on the ground, the drone's tires cannot extend beyond the taxiway area, and its wings cannot interfere with facilities alongside the taxiway. On the other hand, the main wheel track and runway width must meet design specifications when the drone is taxiing on the runway. In summary, the taxiway and runway widths of existing airports are key constraints on the size of solar-powered drones, and consequently, on their mission capabilities.

[0012] To improve the mission performance of large solar-powered drones, innovative wing designs are needed to enable them to meet the requirements of ground taxiing, take-off and landing, and aerial flight. Therefore, how to design innovative wings for solar-powered drones is a problem that needs to be solved. Summary of the Invention

[0013] The purpose of this application is to provide an aerodynamic layout for a large solar-powered unmanned aerial vehicle (UAV) to solve the problems of low flight speed and short range caused by airport runway limitations in the prior art.

[0014] The technical solution of this application is: an aerodynamic layout for a large solar-powered unmanned aerial vehicle (UAV), including a fuselage and deformable wings. The fuselage has at least three sets of fuselage sections arranged side by side. The deformable wings have multiple segments, with the number of segments being twice the number of fuselage sections. Each deformable wing includes outer wings and inner wings. The outer wings have two sets, symmetrically arranged and located on the two outermost fuselage sections. The inner wings have multiple sets, with each set located between two adjacent fuselage sections. The fuselage corresponds to either the inner or outer wing. A fuselage pivot is located at the position of the fuselage, which is connected to the inner or outer wing. Each inner wing consists of two sections, which are hinged together by a wing pivot. A power unit is installed inside the fuselage, and the output end of the power unit is connected to the fuselage pivot. The power unit can drive the fuselage pivot to rotate, and the fuselage pivot can drive the inner wing to deflect to different angles. When the inner wing deflects to its maximum angle, it forms a ground taxiing state; when the inner wing deflects to the middle angle, it forms a takeoff and landing runway state; and when the inner wing deflects to its minimum angle, it forms an airborne flight state.

[0015] Preferably, the outer wing includes a straight section and a sloping section connected to the straight section. The sloping section is located outside the straight section. The straight section is parallel to the spanwise direction of the aircraft. The straight section is fixedly connected to the fuselage. The sloping section is inclined to the spanwise direction of the aircraft and tilts towards the rear of the aircraft.

[0016] Preferably, the fuselage includes a propeller, a power compartment, an onboard equipment compartment, a pivot structure compartment, and a tail section compartment arranged sequentially from front to back. The propeller is connected to the power compartment, and the power compartment can drive the propeller to work. The power unit is located in the pivot structure compartment, and the tail is located at the end of the tail section compartment.

[0017] This application discloses an aerodynamic layout for a large solar-powered unmanned aerial vehicle (UAV), comprising a fuselage and deformable wings. The deformable wings include an outer wing and an inner wing. When all the pivots on the fuselage are deflected to their maximum angle, the inner wing is tightly retracted, minimizing the span of the entire aircraft. This is the ground taxiing state of the solar-powered UAV, facilitating taxiing and other operations. When all the pivots on the fuselage are deflected to an appropriate angle, the inner wing is appropriately retracted. At this time, the wing span of the solar-powered UAV is adjustable, allowing full utilization of the runway while considering lift characteristics, thus improving takeoff and landing performance. This state is called the takeoff and landing taxiing state of the solar-powered UAV. When all the pivots on the fuselage are deflected to their minimum angle, the span of the entire aircraft is maximized, which is the aerial flight state of the solar-powered UAV. The solar-powered UAV can maintain the optimal state for flight at different stages of flight, thereby achieving efficient flight. Attached Figure Description

[0018] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0019] Figure 1 This is an isometric drawing of the solar-powered UAV in its ground gliding state according to this application;

[0020] Figure 2 This is an isometric drawing of the solar-powered UAV in takeoff and landing taxiing mode for this application;

[0021] Figure 3 This is an isometric drawing of the solar-powered UAV in flight mode for this application.

[0022] Figure 4 This is a side view of the solar-powered drone of this application;

[0023] Figure 5 This is a front view of the solar-powered UAV in its ground gliding state according to this application;

[0024] Figure 6 This is a front view of the solar-powered UAV in its takeoff and landing taxiing state as described in this application;

[0025] Figure 7 This is the front view of the solar-powered drone in flight mode for this application.

[0026] 1. Fuselage; 2. Deformable wing; 3. Propeller; 4. Engine compartment; 5. Avionics compartment; 6. Rotary shaft compartment; 7. Tail section compartment; 8. Nose landing gear; 9. Rear landing gear; 10. Outer wing; 11. Inner wing; 12. Fuselage pivot; 13. Wing pivot. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0028] An aerodynamic layout for a large solar-powered unmanned aerial vehicle, such as Figure 1-4 As shown, it includes a fuselage 1 and a deformable wing 2. The fuselage 1 has at least three sets and multiple sets of fuselage 1 arranged side by side, specifically 3 sets, 5 sets, 7 sets or more. Each set of fuselage 1 is equipped with a front landing gear 8 and a rear landing gear 9. The following description takes three sets of fuselage 1 as an example.

[0029] The deformable wing 2 has multiple segments, and the number of segments of the deformable wing 2 is twice the number of fuselage 1. The deformable wing 2 includes an outer wing 10 and an inner wing 11. There are two sets of outer wings 10, and the two sets of outer wings 10 are symmetrically arranged and respectively located on the two outermost sets of fuselage 1. There are multiple sets of inner wings 11, and each set of inner wings 11 is located between two adjacent sets of fuselage 1. A fuselage pivot 12 is provided at the position of the inner wing 11 or the outer wing 10 on the fuselage 1. The fuselage pivot 12 is connected to the inner wing 11 or the outer wing 10. Each set of inner wings 11 has two segments, and a wing pivot 13 is hinged between the two segments of inner wings 11. A power unit is provided inside the fuselage 1, and the output end of the power unit is connected to the fuselage pivot 12.

[0030] The power unit can drive the fuselage shaft 12 to rotate, and the fuselage shaft 12 can drive the inner wing 11 to deflect to different angles. When the inner wing 11 deflects to the maximum angle, it forms a ground taxiing state; when the inner wing 11 deflects to the middle angle, it forms a take-off and landing runway state; when the inner wing 11 deflects to the minimum angle, it forms an air flight state.

[0031] Under takeoff and landing conditions, balancing the main wheel track parameters and low-speed lift characteristics is one of the key requirements; under in-flight conditions, increasing the aspect ratio and improving aerodynamic efficiency are one of the key requirements.

[0032] When all the pivots on fuselage 1 are deflected to their maximum angle, the inner wings 11 are tightly retracted, the overall span of the aircraft is minimized, and the main landing gear track is minimized. This is the ground taxiing state of the solar-powered UAV. Figure 1 and Figure 5 The ground taxiing configuration is compact, which is beneficial for the control span of the UAV and facilitates aircraft taxiing and other operations.

[0033] When all the pivots on fuselage 1 are deflected to an appropriate angle, between 30° and 60° (adjustable depending on the model), the inner wings 11 are appropriately retracted. The main landing gear distance and wingspan of the entire aircraft are controlled to the upper limit of the runway's allowable constraints. At this time, the wing dimensions of the solar-powered UAV are adjustable, allowing full utilization of the runway while considering lift characteristics, which is beneficial for improving takeoff and landing performance. The main landing gear distance parameters and low-speed lift characteristics are both guaranteed. This state is called the takeoff and landing taxiing state of the solar-powered UAV. See Figure 2 and Figure 6 .

[0034] When all the pivots on fuselage 1 are deflected to their minimum angle, the inner wings 11 unfold in a straight line, maximizing the overall length of the aircraft and achieving maximum wingspan in flight. This results in high aerodynamic efficiency and enhanced mission capabilities. This is the flight configuration of the solar-powered UAV. Figure 3 and Figure 7 .

[0035] Therefore, by changing the angle of the aircraft's wings, the aircraft can perform ground taxiing, take-off and landing, and aerial flight. When the solar-powered drone is in different stages of flight, it can ensure the optimal state for the current stage of flight, thereby achieving efficient flight of the solar-powered drone. In addition, the three modes can be switched freely, which is conducive to the solar-powered drone selecting the most suitable mode according to the flight state.

[0036] Preferably, the outer wing 10 includes a straight section and a sloping section connected to the straight section. The sloping section is located outside the straight section. The straight section is parallel to the spanwise direction of the aircraft. The straight section is fixedly connected to the fuselage 1. The sloping section is inclined to the spanwise direction of the aircraft and tilts towards the rear of the aircraft. This design can ensure that the aircraft has high aerodynamic performance.

[0037] Preferably, the fuselage 1 includes a propeller 3, a power compartment 4, an onboard equipment compartment 5, a pivot structure compartment 6, and a tail section compartment 7 arranged sequentially from front to back. The propeller 3 is connected to the power compartment 4, and the power compartment 4 can drive the propeller 3 to work. The front end of the power compartment 4 has a conical structure to reduce wind resistance. The power components are located in the pivot structure compartment 6, and the tail is located at the end of the tail section compartment 7. With this design, the various parts of the aircraft are compact and occupy little space, which meets the design requirements of solar-powered UAVs.

[0038] The above are merely specific embodiments of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aerodynamic layout for a large solar-powered unmanned aerial vehicle (UAV), characterized in that: The fuselage (1) includes a fuselage (1) and deformable wings (2). The fuselage (1) has at least three sets of fuselage (1) arranged side by side. The deformable wings (2) have multiple segments, and the number of segments of the deformable wings (2) is twice the number of fuselage (1). The deformable wings (2) include outer wings (10) and inner wings (11). The outer wings (10) have two sets, and the two sets of outer wings (10) are symmetrically arranged and respectively located on the two outermost sets of fuselage (1). The inner wings (11) have multiple sets of... Each set of inner wings (11) is located between two adjacent sets of fuselage (1). The fuselage (1) is provided with a fuselage pivot (12) at the position corresponding to the inner wing (11) or the outer wing (10). The fuselage pivot (12) is connected to the inner wing (11) or the outer wing (10). Each set of inner wings (11) has two sections. The two sections of inner wings (11) are hinged to a wing pivot (13). The fuselage (1) is provided with a power unit. The output end of the power unit is connected to the fuselage pivot (12). The power component can drive the fuselage shaft (12) to rotate, and the fuselage shaft (12) can drive the inner wing (11) to deflect to different angles. When the inner wing (11) deflects to the maximum angle, it forms a ground taxiing state; when the inner wing (11) deflects to the middle angle, it forms a take-off and landing taxiing state; when the inner wing (11) deflects to the minimum angle, it forms an air flight state.

2. The aerodynamic layout of the large solar-powered UAV as described in claim 1, characterized in that: The outer wing (10) includes a straight section and a sloping section connected to the straight section. The sloping section is located outside the straight section. The straight section is parallel to the spanwise direction of the aircraft. The straight section is fixedly connected to the fuselage (1). The sloping section is inclined to the spanwise direction of the aircraft and tilts towards the rear of the aircraft.

3. The aerodynamic layout of the large solar-powered UAV as described in claim 1, characterized in that: The fuselage (1) includes a propeller (3), a power compartment (4), an onboard equipment compartment (5), a pivot structure compartment (6), and a tail section compartment (7) arranged sequentially from front to back. The propeller (3) is connected to the power compartment (4), and the power compartment (4) can drive the propeller (3) to work. The power unit is located in the pivot structure compartment (6), and the tail is located at the end of the tail section compartment (7).

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