High-altitude balloon carrying and releasing powered unmanned aerial vehicle

Abstract

The invention relates to the technical field of spaceflight, and particularly discloses a high-altitude balloon carrying and releasing powered unmanned aerial vehicle which comprises a sounding balloon releasing system and a powered unmanned aerial vehicle body. The sounding balloon releasing system comprises an air bag, an air bag rope, a load cabin and a releasing system composed of a releasing frame, a rope and a control system, and is used for carrying the powered unmanned aerial vehicle to a preset height and releasing the unmanned aerial vehicle. The powered unmanned aerial vehicle adopts a conventional aerodynamic layout of a middle single wing and comprises a fuselage, wings, a horizontal tail and a vertical tail. The powered unmanned aerial vehicle is carried by the sounding balloon to lift off, and in the super-high-altitude rarefied air environment, stable flight and data acquisition tasks can be achieved by means of the design of the wings with the large lift-drag ratio and the large aspect ratio and a power device of the powered unmanned aerial vehicle. According to the invention, the problems of high cost and complicated launching of the existing superaltitude unmanned aerial vehicle platform are solved, and a high-altitude detection scheme with low cost, flexible deployment and stable flight is provided.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a powered unmanned aerial vehicle (UAV) launched from a high-altitude balloon. Background Technology

[0002] The ultra-high altitude environment generally refers to the airspace 15km to 30km above the ground, characterized by thin air, relatively stable airflow, and abundant solar energy. Ultra-high altitude unmanned aerial vehicles (UAVs) are aircraft that can fully utilize these environmental characteristics and operate stably in this airspace. They can be mainly divided into two categories: ① low-speed, long-endurance UAVs that utilize buoyancy or large wing surfaces to provide lift; ② UAVs that utilize special aerodynamic shapes for high-speed flight. These types of UAVs have significant application value in fields such as long-range transportation, reconnaissance and surveillance, and communication relay.

[0003] Using weather balloons as aerial delivery platforms to launch drones to ultra-high altitudes is a novel operational mode. This mode can reduce the energy consumption and design complexity of drones' autonomous climb, and is particularly suitable for lightweight, compact small drones. However, in existing technologies, there are few research reports on the specific system design of combining weather balloons with powered drones, especially detailed configurations of drones that can adapt to the thin atmosphere of ultra-high altitudes and have stable flight and data acquisition capabilities. Currently, detection in this region has the following pain points: ① Weak continuous detection capability: Traditional weather balloons are unpowered, drift with the wind, cannot stay in the target area, and are usually used only once, resulting in discontinuous data; ② High cost: Stratospheric airships (which can stay for a long time) are technically complex, with extremely high manufacturing and maintenance costs; ③ Poor deployment flexibility: Satellite observations have long revisit cycles and may have insufficient resolution; airship deployment is inflexible.

[0004] Therefore, how to design a ball-borne unmanned aerial vehicle system that is structurally sound, cost-effective, reliable in deployment, and capable of efficient flight at ultra-high altitudes is a technical problem that needs to be solved in this field. Summary of the Invention

[0005] The purpose of this invention is to provide a powered drone launched from a high-altitude balloon to solve the problems existing in the prior art.

[0006] To achieve the above objectives, the present invention provides a powered drone launched from a high-altitude balloon, comprising a weather balloon delivery system and a powered drone; The weather balloon delivery system is used to carry and release the powered drone; The powered unmanned aerial vehicle (UAV) includes a fuselage, on which wings, a horizontal tail, and a vertical tail are provided. The fuselage contains a power unit and flight control equipment. The wings are designed with a trapezoidal shape and a high aspect ratio.

[0007] Preferably, the weather balloon delivery system includes an airbag, an airbag rope, a payload compartment, and a delivery system; the airbag is connected to the payload compartment via the airbag rope; the delivery system is located below the payload compartment and is used to mount and release the powered UAV.

[0008] Preferably, the delivery system includes a delivery frame, a flexible rope, and a control system; the delivery frame adopts a truss structure, the flexible rope is connected below the delivery frame, and the flexible rope is connected to at least three attachment points on the fuselage of the powered UAV, the attachment points being located at the center of gravity of the fuselage and at both ends of the wings; the control system is used to control the release of the powered UAV at a predetermined altitude.

[0009] Preferably, the fuselage includes a fuselage skin, internal connectors, reinforcing frames, ordinary frames, and a stringer; the fuselage skin covers the outer side of the fuselage and is made of multi-layer carbon fiber material; the internal connectors pass through the inner sides of the reinforcing frames and the ordinary frames, and are made of carbon fiber, serving to connect the wings, the horizontal tail, and the vertical tail; the reinforcing frames and the ordinary frames are both fixedly connected to the stringer, and the reinforcing frames, the ordinary frames, and the stringer are all made of balsa wood.

[0010] The fuselage of a drone is its body, connecting the wings and tail. Its main function is to bear and transmit the loads from the various components.

[0011] The fuselage skin is a load-bearing component covering the fuselage structure. It maintains the aerodynamic shape and ensures sufficient strength, needing to withstand certain loads. The fuselage skin consists of five layers of carbon fiber material smoothly laid on the fuselage frame. Internal carbon fiber connectors connect the wings and tail, while also enhancing the strength of the internal fuselage structure. The bulkhead is a crucial load-bearing component of the UAV fuselage structure, bearing external loads perpendicular to the skin and maintaining the fuselage shape. Bulkheads are divided into reinforced bulkheads and ordinary bulkheads. The truss supports the skin, withstands the longitudinal forces generated by the longitudinal bending of the fuselage, and transfers the aerodynamic forces of the skin to the bulkhead.

[0012] Preferably, the wing adopts a multi-spar layout, and the wing includes wing spars, wing reinforcing ribs, wing standard ribs, wing stringers, and wing skin; the wing spars are arranged through the wing reinforcing ribs and the wing standard ribs, and are fixedly connected to the fuselage; both the wing reinforcing ribs and the wing standard ribs are provided with weight reduction holes; both the wing reinforcing ribs and the wing standard ribs are fixedly connected to the wing stringers, and the wing reinforcing ribs are located at the wing root; the trailing edge of the wing is provided with ailerons and wing flaps; the wing spars, the wing stringers, and the wing skin are all made of carbon fiber material; the wing reinforcing ribs and the wing standard ribs are all made of balsa wood material.

[0013] Preferably, the airfoil is a concave-convex airfoil, and the root-to-tip ratio of the airfoil is 2.

[0014] The wings of a drone are the primary component that generates lift. The formula for calculating the lift of a drone in level flight is: MERGEFORMAT (1) In the formula: For the lift generated when the drone is flying at extremely high altitudes, For drone gravity; This refers to the density of the atmosphere at extremely high altitudes. It is the sum of ultra-high altitude wind speed and cruising speed; This refers to the lift coefficient at extremely high altitudes. This represents the wing area of ​​the drone.

[0015] Drones cruise at very high altitudes at low speeds and for long periods. Choosing a concave-convex airfoil with low Reynolds number and high lift characteristics ensures that the drone has a high lift-to-drag ratio. Furthermore, selecting a trapezoidal wing shape ensures advantages such as high lift, low bending moment, and low induced drag.

[0016] The formula for the chord length of a drone is: MERGEFORMAT (2) In the formula: The mean chord length of the wing; For wingspan; For the aspect ratio.

[0017] Lianlide: MERGEFORMAT (3) Trapezoidal wings require consideration of the wing's root-to-tip ratio. Root tip ratio for: MERGEFORMAT (4) In the formula: This refers to the wing root chord length; The wingtip chord length; the root-to-tip ratio during this design process The value is 2.

[0018] Rise-to-drag ratio The calculation formula is: MERGEFORMAT (5) In the formula: For wing lift; For wing drag; The lift coefficient; This is the drag coefficient.

[0019] The wing spars run through the wing ribs and are fixedly connected to the fuselage at the wing root. Their function is to connect the wing ribs, ensuring the wing's shape and strength. The wing spars are purely load-bearing components, consisting of a web and flanges, with an I-shaped or channel-shaped cross-section.

[0020] Wing ribs are key internal components of the wing, forming its lateral load-bearing framework. They are divided into ordinary wing ribs and reinforcing wing ribs. Ordinary wing ribs connect to the wing stringers, spars, and skin, primarily maintaining the airfoil's cross-sectional shape and providing vertical support to the stringers and skin. Reinforcing wing ribs are located at the wing root, thickened from ordinary wing ribs, and serve as components connecting to the UAV fuselage, capable of withstanding significant loads. The wing ribs incorporate a weight-reducing perforation structure to ensure wing weight reduction while meeting strength requirements.

[0021] Wing stringers are slender, longitudinally arranged members in the wing surface structure. Together with wing ribs, wing stringers support the wing skin, improve its load-bearing capacity, and transfer aerodynamic forces from the wing skin to the wing ribs.

[0022] The carbon fiber wing skin fits smoothly onto the wing frame, maintaining the wing's aerodynamic shape and keeping the surface smooth, withstanding torque and ensuring sufficient strength. The ailerons are the primary control surfaces of a drone. By manipulating the differential deflection of the left and right ailerons to generate a rolling moment, the drone can perform horizontal roll. The ailerons are also composed of four parts: spars, ribs, stringers, and skin. The area of ​​the aileron relative to the wing is: MERGEFORMAT (6) In the formula For the aileron area, S represents the relative aileron area, and S represents the wing area.

[0023] Wing flaps are wing surfaces installed on the trailing edge of the wing near the fuselage. They can deflect downwards and rearwards around the axis. The wing flap structure increases lift by increasing the wing area.

[0024] Preferably, the horizontal tail includes a horizontal tail rib, a horizontal tail spars, a horizontal tail stringer, a horizontal tail skin, and a horizontal tail elevator surface; the horizontal tail spars are arranged through the horizontal tail ribs and are fixedly connected to the fuselage; the horizontal tail ribs are fixedly connected to the horizontal tail stringers. The vertical tail fin includes a vertical tail fin rib, a vertical tail fin sparsity, a vertical tail fin stringer, a vertical tail fin skin, and a vertical tail fin directional control surface; the vertical tail fin sparsity extends through the vertical tail fin rib and is fixedly connected to the fuselage; the vertical tail fin sparsity is fixedly connected to the vertical tail fin stringer. Both the horizontal and vertical tail wing ribs are made of balsa wood, while the horizontal tail wing spars, horizontal tail wing stringers, horizontal tail wing skin, vertical tail wing spars, vertical tail wing stringers, and vertical tail wing skin are all made of carbon fiber.

[0025] Calculate the lever arm of the horizontal stabilizer using the horizontal stabilizer capacity formula: MERGEFORMAT (7) In the formula: It is the tail capacity; It is the area of ​​the flat tail; It is the tail lever arm of the flat tail.

[0026] Calculate the lever arm of the vertical tail fin using the vertical tail fin capacity formula: MERGEFORMAT (8) In the formula: It is the tail capacity; It is the area of ​​the vertical tail; It is the tail lever arm of the vertical tail.

[0027] Preferably, the head of the machine body is provided with a counterweight load for adjusting the center of gravity, and the bottom of the machine body is provided with a high-strength PVC foam cushioning bag.

[0028] Preferably, the power unit includes an electric motor, a propeller, a battery, and an electronic speed controller; the propeller is mounted on the front end of the outer side of the fuselage, and the electric motor is connected to the propeller to drive the propeller to rotate; the flight control equipment includes sensors, an airspeed indicator, and GPS.

[0029] Preferably, the airbag is made of natural rubber latex material, and the interior of the airbag is filled with helium.

[0030] Compared with the prior art, the present invention has the following advantages and technical effects: This invention provides a powered unmanned aerial vehicle (UAV) launched from a high-altitude balloon. By using a low-cost, easily deployable weather balloon as the launch platform for the UAV, it significantly lowers the barrier to entry and cost for accessing ultra-high altitudes. The UAV employs a lightweight, high-strength carbon fiber and balsa wood composite structure, combined with a high aspect ratio and high lift-to-drag ratio aerodynamic design optimized for the low-density air at ultra-high altitudes, ensuring flight efficiency and stability in the thin atmosphere. The entire system boasts advantages such as low cost, short preparation time, high deployment accuracy, and strong environmental adaptability, providing an efficient and practical technical means for ultra-high-altitude scientific exploration and environmental monitoring missions. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0032] Figure 1 This is a schematic diagram of the overall structure of the powered unmanned aerial vehicle system launched from a high-altitude balloon according to the present invention.

[0033] Figure 2 This is a schematic diagram of the weather balloon delivery system of the present invention.

[0034] Figure 3 This is a schematic diagram of the fuselage structure of the powered unmanned aerial vehicle of the present invention.

[0035] Figure 4 This is a schematic diagram of the left wing structure of the powered unmanned aerial vehicle of the present invention.

[0036] Figure 5 This is a schematic diagram of the horizontal tail structure of the powered unmanned aerial vehicle of the present invention.

[0037] Figure 6 This is a schematic diagram of the vertical tail structure of the powered unmanned aerial vehicle of the present invention.

[0038] In the image: 1. Weather balloon delivery system; 2. Fuselage; 3. Wing; 4. Horizontal tail; 5. Vertical tail; 6. Airbag; 7. Airbag cable; 8. Payload compartment; 9. Delivery rack; 10. Flexible cable; 11. Fuselage skin; 12. Internal connectors; 13. Reinforced bulkhead; 14. Standard bulkhead; 15. Truss; 16. Propeller; 17. Wing spars; 18. Wing reinforcing ribs; 19. Standard wing ribs ; 20. Weight reduction hole; 21. Wing stringer; 22. Wing skin; 23. Wing aileron; 24. Wing flap; 25. Horizontal tail rib; 26. Horizontal tail spars; 27. Horizontal tail stringer; 28. Horizontal tail skin; 29. ​​Horizontal tail elevator; 30. Vertical tail rib; 31. Vertical tail spars; 32. Vertical tail stringer; 33. Vertical tail skin; 34. Vertical tail directional control surface. Detailed Implementation

[0039] It should be noted that, unless otherwise specified, the embodiments and features described in this invention can be combined with each other. The described embodiments are merely some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this invention. The invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0040] like Figures 1 to 6 As shown, the present invention provides a powered drone launched from a high-altitude balloon, including a weather balloon launch system 1 and a powered drone; The weather balloon delivery system 1 is used to carry and release powered drones; The powered drone includes a fuselage 2, on which wings 3, a horizontal tail 4, and a vertical tail 5 are mounted. The fuselage 2 contains a power unit and flight control equipment. The wings 3 are designed with a trapezoidal shape and a high aspect ratio.

[0041] This invention relates to a powered UAV designed with reference to fixed-wing UAVs, employing a mid-wing conventional aerodynamic layout. This layout leverages mature and stable aerodynamic theories to ensure basic flight stability and maneuverability of the UAV in complex ultra-high-altitude environments. The combination of the weather balloon delivery system 1 and the powered UAV allows for convenient transport of the UAV to ultra-high altitudes using a low-cost balloon platform, enabling stable release and autonomous flight, thus solving the problems of complex and expensive traditional ultra-high-altitude UAV launch platforms.

[0042] The design has been further optimized. The weather balloon delivery system 1 includes an airbag 6, an airbag rope 7, a payload compartment 8, and a delivery system. The airbag 6 is connected to the payload compartment 8 via the airbag rope 7. The delivery system is located below the payload compartment 8 and is used to mount and release powered drones.

[0043] The configuration of airbag 6, airbag ropes 7, and payload compartment 8 provides stable lift, secure connection, and supports the delivery system and drone. Airbag 6 is filled with helium, generating buoyancy to propel the entire system upwards. The symmetrically distributed airbag ropes 7 withstand tension and concentrate buoyancy to transfer to the payload compartment 8. The payload compartment 8 contains built-in control equipment to protect internal components from damage during the ascent.

[0044] The scheme is further optimized. The delivery system includes a delivery frame 9, a flexible rope 10, and a control system. The delivery frame 9 adopts a truss structure. The flexible rope 10 is connected to the bottom of the delivery frame 9 and is connected to at least three attachment points on the fuselage 2 of the powered UAV. The attachment points are located at the center of gravity of the fuselage 2 and at both ends of the wings 3. The control system is used to control the release of the powered UAV at a predetermined altitude.

[0045] The truss structure of the launch frame 9 serves as the primary load-bearing and force-transmitting component during the loading process, providing structural stability and effectively distributing and transferring the load. The flexible ropes 10, connected to multiple attachment points on the UAV (such as the center of gravity and wingtips), help restrain the UAV during balloon ascent, reducing its sway and maintaining a stable loading attitude. The control system precisely controls the release timing, ensuring the UAV successfully detaches at the target altitude or in the target airspace.

[0046] Further optimizing the design, the fuselage 2 serves as the body of the UAV, connecting various components and carrying internal equipment. The fuselage 2 includes a fuselage skin 11, internal connectors 12, reinforcing frames 13, ordinary frames 14, and a truss 15. The fuselage skin 11 covers the outside of the fuselage 2 and is made of multi-layered carbon fiber material. The internal connectors 12 pass through the inside of the reinforcing frames 13 and ordinary frames 14. The internal connectors 12 are made of carbon fiber and are used to connect the wings 3, the horizontal tail 4, and the vertical tail 5. The reinforcing frames 13 and ordinary frames 14 are both fixedly connected to the truss 15, and all three components—reinforcing frames 13, ordinary frames 14, and truss 15—are made of balsa wood.

[0047] By employing multi-layered carbon fiber materials for the fuselage skin 11, sufficient structural strength and rigidity are maintained while significantly reducing fuselage weight. The excellent specific strength and specific modulus of carbon fiber are ideally suited to the lightweight requirements of aviation. The internal carbon fiber connectors 12 reliably connect large components such as the wings and tail, enhancing the overall structural integrity of the fuselage. The use of balsa wood for the reinforced bulkhead 13, ordinary bulkhead 14, and stringers 15 further reduces structural weight while meeting load-bearing requirements. Furthermore, balsa wood is easy to process and shape, facilitating the construction of complex internal structures.

[0048] Further optimization of the design: the internal structure of wing 3 adopts a multi-spar layout. Wing 3 includes wing spars 17, wing reinforcing ribs 18, wing ordinary ribs 19, wing stringers 21, and wing skin 22. Wing spars 17 are set through wing reinforcing ribs 18 and wing ordinary ribs 19, and are fixedly connected to fuselage 2. Weight reduction holes 20 are provided on both wing reinforcing ribs 18 and wing ordinary ribs 19. Both wing reinforcing ribs 18 and wing ordinary ribs 19 are fixedly connected to wing stringers 21, and wing reinforcing ribs 18 are set at the wing root of wing 3. Ailerons 23 and wing flaps 24 are provided on the trailing edge of wing 3. Wing spars 17, wing stringers 21, and wing skin 22 are all made of carbon fiber material. Wing reinforcing ribs 18 and wing ordinary ribs 19 are both made of balsa wood material.

[0049] Further optimization of the design resulted in a concave-convex airfoil for wing 3, with a root-to-tip ratio of 2.

[0050] The trapezoidal wing and high aspect ratio design of wing 3 effectively reduce induced drag and improve lift-to-drag ratio in ultra-high altitude, low-density air, resulting in better cruise efficiency. The concave-convex airfoil design maintains a high lift coefficient at low Reynolds numbers (corresponding to high altitude, low speed), ensuring sufficient lift for the UAV in thin air. A root-to-tip ratio of 2 optimizes aerodynamic load distribution, balancing high lift with low bending moment. The multi-spar internal layout of wing 3 enhances its structural strength, stiffness, and torsional resistance. Weight-reduction holes 20 on the reinforcing wing ribs 18 and ordinary wing ribs 19 effectively reduce wing weight while maintaining rib structural functionality. The use of carbon fiber for the wing spars 17 and wing skin 22 ensures a high-strength, lightweight structure that can withstand major bending and torsional loads. The use of balsa wood in the wing reinforcement ribs 18 and ordinary wing ribs 19 helps maintain the wing's aerodynamic shape, support the skin and stringers, and reduce weight. The ailerons 23 allow for differential deflection control of the UAV's roll attitude. The wing flaps 24 deflect during takeoff, landing, or low-speed flight to increase wing camber and area, thereby enhancing lift.

[0051] The horizontal tail 4 is further optimized by including a horizontal tail rib 25, a horizontal tail sparsity 26, a horizontal tail stringer 27, a horizontal tail skin 28, and a horizontal tail elevator surface 29; the horizontal tail sparsity 26 is arranged through the horizontal tail rib 25 and is fixedly connected to the fuselage 2; the horizontal tail rib 25 is fixedly connected to the horizontal tail stringer 27. The vertical tail 5 includes a vertical tail rib 30, a vertical tail sparsity 31, a vertical tail stringer 32, a vertical tail skin 33, and a vertical tail directional control surface 34; the vertical tail sparsity 31 is disposed through the vertical tail rib 30 and is fixedly connected to the fuselage 2; the vertical tail sparsity 31 is fixedly connected to the vertical tail stringer 32. Both the horizontal tail rib 25 and the vertical tail rib 30 are made of balsa wood, while the horizontal tail spars 26, horizontal tail stringers 27, horizontal tail skin 28, vertical tail spars 31, vertical tail stringers 32 and vertical tail skin 33 are made of carbon fiber.

[0052] By employing a carbon fiber-balsa wood composite structure similar to that of wing 3 for the horizontal tail 4 and vertical tail 5, the tail structure can be made lightweight and high-strength, while providing stable pitch, yaw, and maneuverability. The horizontal tail elevator surface 29 is used to control the UAV's pitch attitude. The vertical tail directional control surface 34 is used to control the UAV's yaw attitude.

[0053] Further optimization of the design includes a counterweight load at the head of fuselage 2 for adjusting the center of gravity, and a high-strength PVC foam cushioning pack at the bottom of fuselage 2.

[0054] The counterweight configuration at the nose of fuselage 2 allows for flexible adjustment of the drone's center of gravity when carrying different mission equipment, ensuring stable flight attitude. The PVC foam cushioning at the bottom of fuselage 2 effectively absorbs impact energy during landing or emergency landing, protecting delicate internal equipment and facilitating drone recovery and reuse.

[0055] The further optimized scheme includes a power unit consisting of an electric motor, a propeller 16, a battery, and an electronic speed governor; the propeller 16 is mounted on the front of the outer side of the fuselage 2, and the electric motor is connected to the propeller 16 to drive the propeller 16 to rotate; the flight control equipment includes sensors, an airspeed indicator, and GPS.

[0056] By incorporating powered devices such as electric motors and propellers (16 units), the UAV can be propelled to fly autonomously at extremely high altitudes, enabling it to maneuver and extend its mission range, unlike unpowered gliding UAVs. The flight control equipment allows for real-time monitoring of the UAV's flight status and navigation information, and automatic or remote control of various control surfaces and the power system, ensuring stable flight and mission execution.

[0057] Further optimization of the design: Airbag 6 is made of natural rubber latex material, filled with helium, has a diameter of 2 meters, and weighs approximately 1.5 kilograms.

[0058] By using natural rubber latex material and filling it with helium, airbag 6 provides a safe and reliable buoyancy source. The rubber latex has good elasticity, allowing it to accommodate the airbag's volume expansion during ascent. By limiting the airbag size and mass within the specified range, a good balance is achieved between providing sufficient lift and maintaining the system's low cost and ease of operation.

[0059] The powered UAV launched from a high-altitude balloon provided by this invention is implemented as follows: First, the UAV is assembled on the ground and suspended below the launch frame 9 of the weather balloon launch system 1 via a flexible rope 10. The status of each connection point and equipment is checked. Then, a weather balloon filled with helium (airbag 6) is released, and the entire system ascends under the buoyancy of the balloon. During ascent, the control system inside the payload compartment 8 monitors the flight altitude based on GPS or altitude sensor information. When the system reaches the predetermined release altitude (e.g., the target detection airspace), the control system issues a command, and the release mechanism (e.g., a fusible rope, electromagnetic lock, etc.) actuates, causing the flexible rope 10 to detach from the UAV, and the UAV is successfully released. After release, the UAV's flight control system activates, the power unit operates, and the control surfaces are activated. The UAV enters autonomous flight mode and begins to perform preset reconnaissance, monitoring, or data transmission tasks. After the task is completed, the UAV can be remotely controlled or autonomously fly to the predetermined recovery area for landing. The cushioning pad on the bottom of the fuselage helps reduce landing impact.

[0060] This invention utilizes low-cost, readily available weather balloons as the primary lift-off power source, significantly reducing the deployment cost and complexity of ultra-high-altitude unmanned aerial vehicle (UAV) systems while improving their flexibility and ease of use. The UAV's aerodynamic layout and structural materials have been specifically optimized, featuring a high-aspect-ratio trapezoidal wing, a high-lift airfoil, and a carbon fiber-balsa wood composite structure, ensuring flight efficiency and structural reliability in ultra-high-altitude, low-density, low-Reynolds-number environments. The three-point sling and truss-type launch platform design guarantees attitude stability during the ascent phase, improving the release success rate. The system boasts high integration, forming a complete and feasible ultra-high-altitude operation solution from takeoff and precise release to autonomous flight, mission execution, and safe recovery, with broad application prospects in scientific exploration, meteorological observation, and communication relay.

[0061] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A powered unmanned aerial vehicle (UAV) launched from a high-altitude balloon, characterized in that, Including weather balloon delivery systems (1) and powered unmanned aerial vehicles; The weather balloon delivery system (1) is used to carry and release the powered drone; The powered UAV includes a fuselage (2), on which are mounted wings (3), a horizontal tail (4) and a vertical tail (5). The fuselage (2) contains a power unit and flight control equipment. The wings (3) are designed with a trapezoidal shape and a high aspect ratio.

2. The powered unmanned aerial vehicle launched from a high-altitude balloon according to claim 1, characterized in that, The weather balloon delivery system (1) includes an airbag (6), an airbag rope (7), a payload compartment (8), and a delivery system; the airbag (6) is connected to the payload compartment (8) via the airbag rope (7); the delivery system is located below the payload compartment (8) and is used to mount and release the powered UAV.

3. The powered unmanned aerial vehicle launched from a high-altitude balloon according to claim 2, characterized in that, The delivery system includes a delivery frame (9), a flexible rope (10), and a control system; the delivery frame (9) adopts a truss structure, the flexible rope (10) is connected below the delivery frame (9), and the flexible rope (10) is connected to at least three suspension points on the fuselage (2) of the powered UAV, the suspension points being located at the center of mass of the fuselage (2) and at both ends of the wings (3); the control system is used to control the release of the powered UAV at a predetermined altitude.

4. The powered unmanned aerial vehicle launched from a high-altitude balloon according to claim 1, characterized in that, The fuselage (2) includes a fuselage skin (11), internal connectors (12), a reinforcing frame (13), a regular frame (14), and a truss (15). The fuselage skin (11) covers the outside of the fuselage (2) and is made of multi-layer carbon fiber material. The internal connectors (12) are inserted inside the reinforcing frame (13) and the regular frame (14) and are made of carbon fiber. The internal connectors (12) are used to connect the wing (3), the horizontal tail (4), and the vertical tail (5). The reinforcing frame (13) and the regular frame (14) are both fixedly connected to the truss (15). The reinforcing frame (13), the regular frame (14), and the truss (15) are all made of balsa wood.

5. The powered unmanned aerial vehicle launched from a high-altitude balloon according to claim 1, characterized in that, The wing (3) adopts a multi-spar layout internally. The wing (3) includes a wing spars (17), wing reinforcing ribs (18), wing ordinary ribs (19), wing stringers (21), and wing skin (22). The wing spars (17) are arranged through the wing reinforcing ribs (18) and the wing ordinary ribs (19), and the wing spars (17) are fixedly connected to the fuselage (2). Weight reduction holes (20) are provided on both the wing reinforcing ribs (18) and the wing ordinary ribs (19). The wing reinforcing rib (18) and the wing ordinary rib (19) are both fixedly connected to the wing stringer (21), and the wing reinforcing rib (18) is located at the wing root of the wing (3); the trailing edge of the wing (3) is provided with ailerons (23) and wing flaps (24); the wing spars (17), the wing stringer (21) and the wing skin (22) are all made of carbon fiber material; the wing reinforcing rib (18) and the wing ordinary rib (19) are both made of balsa wood material.

6. The powered unmanned aerial vehicle launched from a high-altitude balloon according to claim 5, characterized in that, The airfoil of the wing (3) is a concave-convex airfoil, and the root-to-tip ratio of the wing (3) is 2.

7. The powered unmanned aerial vehicle launched from a high-altitude balloon according to claim 1, characterized in that, The horizontal tail (4) includes a horizontal tail rib (25), a horizontal tail sparsity (26), a horizontal tail stringer (27), a horizontal tail skin (28), and a horizontal tail elevator surface (29); the horizontal tail sparsity (26) is provided through the horizontal tail rib (25), and the horizontal tail sparsity (26) is fixedly connected to the fuselage (2); the horizontal tail rib (25) is fixedly connected to the horizontal tail stringer (27); The vertical tail fin (5) includes a vertical tail fin rib (30), a vertical tail fin sparsity (31), a vertical tail fin stringer (32), a vertical tail fin skin (33), and a vertical tail fin directional control surface (34); the vertical tail fin sparsity (31) is provided through the vertical tail fin rib (30), and the vertical tail fin sparsity (31) is fixedly connected to the fuselage (2); the vertical tail fin sparsity (31) is fixedly connected to the vertical tail fin stringer (32); The horizontal tail wing rib (25) and the vertical tail wing rib (30) are both made of balsa wood, and the horizontal tail wing spars (26), the horizontal tail wing stringers (27), the horizontal tail wing skin (28), the vertical tail wing spars (31), the vertical tail wing stringers (32), and the vertical tail wing skin (33) are all made of carbon fiber.

8. The powered unmanned aerial vehicle launched from a high-altitude balloon according to claim 4, characterized in that, The head of the body (2) is provided with a counterweight load for adjusting the center of gravity, and the bottom of the body (2) is provided with a high-strength PVC foam cushioning bag.

9. The powered unmanned aerial vehicle launched from a high-altitude balloon according to claim 4, characterized in that, The power unit includes an electric motor, a propeller (16), a battery, and an electronic speed controller; the propeller (16) is mounted on the front end of the outer side of the fuselage (2), and the electric motor is connected to the propeller (16) to drive the propeller (16) to rotate; the flight control equipment includes sensors, an airspeed meter, and GPS.

10. The powered unmanned aerial vehicle launched from a high-altitude balloon according to claim 2, characterized in that, The airbag (6) is made of natural rubber latex material and is filled with helium.

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