CN-121990211-A - High-altitude balloon carrying and releasing powered unmanned aerial vehicle

CN121990211ACN 121990211 ACN121990211 ACN 121990211ACN-121990211-A

Abstract

The invention relates to the technical field of aerospace, and particularly discloses a powered unmanned aerial vehicle for carrying and releasing high-altitude balloon, which comprises a sounding balloon throwing system and a powered unmanned aerial vehicle. The sounding balloon throwing system comprises an air bag, an air bag rope, a load cabin and a throwing system formed by a throwing frame, the rope and a control system, and is used for carrying and releasing the powered unmanned aerial vehicle to a preset height. The powered unmanned aerial vehicle adopts a middle single wing conventional pneumatic layout, and comprises a fuselage, wings, a horizontal tail wing and a vertical tail wing. The unmanned aerial vehicle with power is carried and lifted through the sounding balloon, and in an ultra-high altitude lean air environment, stable flight and data acquisition tasks can be realized by means of the wing design with large lift-drag ratio and large aspect ratio and the power device. The invention solves the problems of high cost and complex emission of the existing ultra-high-altitude unmanned aerial vehicle platform, and provides a high-altitude detection scheme with low cost, flexible deployment and stable flight.

Inventors

YANG JUNFENG
PEI CHANGGUI
WANG JIANMEI
YANG FENGYI
LIU DAN
ZHANG YIMING
YUAN ZEKUN
GUO ZHANGXIA

Assignees

中国科学院国家空间科学中心

Dates

Publication Date: 20260508
Application Date: 20260211

Claims (10)

1. The powered unmanned aerial vehicle with high-altitude balloon carrying and releasing functions is characterized by comprising a sounding balloon throwing system (1) and the powered unmanned aerial vehicle; The sounding balloon delivery system (1) is used for carrying and releasing the powered unmanned aerial vehicle; The powered unmanned aerial vehicle comprises a machine body (2), wherein wings (3), a horizontal tail wing (4) and a vertical tail wing (5) are arranged on the machine body (2), a power device and flight control equipment are arranged in the machine body (2), and the wings (3) are designed by adopting trapezoid wings and a large aspect ratio.
2. The powered unmanned aerial vehicle with high-altitude balloon carrying and releasing according to claim 1, wherein the sounding balloon releasing system (1) comprises an air bag (6), an air bag rope (7), a load cabin (8) and a releasing system, the air bag (6) is connected with the load cabin (8) through the air bag rope (7), and the releasing system is arranged below the load cabin (8) and is used for carrying and releasing the powered unmanned aerial vehicle.
3. The powered unmanned aerial vehicle with high-altitude balloon carrying release according to claim 2, wherein the releasing system comprises a releasing frame (9), a flexible rope (10) and a control system, the releasing frame (9) adopts a truss structure, the flexible rope (10) is connected below the releasing frame (9), the flexible rope (10) is connected with at least three hanging points on a fuselage (2) of the powered unmanned aerial vehicle, the hanging points are located at the center of mass of the fuselage (2) and at two ends of the wing (3), and the control system is used for controlling the release of the powered unmanned aerial vehicle at a preset height.
4. The powered unmanned aerial vehicle with the high-altitude balloon carrying release according to claim 1, wherein the fuselage (2) comprises a fuselage skin (11), an inner connecting piece (12), a reinforcing bulkhead (13), a common bulkhead (14) and a truss (15), the fuselage skin (11) is covered on the outer side of the fuselage (2), the fuselage skin (11) is made of a multi-layer carbon fiber material, the inner connecting piece (12) is arranged on the inner sides of the reinforcing bulkhead (13) and the common bulkhead (14) in a penetrating manner, the inner connecting piece (12) is made of a carbon fiber piece, the inner connecting piece (12) is used for connecting the wing (3), the horizontal tail wing (4) and the vertical tail wing (5), the reinforcing bulkhead (13) and the common bulkhead (14) are fixedly connected to the truss (15), and the reinforcing bulkhead (13), the common bulkhead (14) and the truss (15) are made of a balsa material.
5. The high-altitude balloon onboard released powered unmanned aerial vehicle according to claim 1, wherein a multi-beam layout is adopted inside the wing (3), the wing (3) comprises a wing spar (17), a wing reinforcing rib (18), a wing ordinary rib (19), a wing stringer (21) and a wing skin (22), the wing spar (17) penetrates through the wing reinforcing rib (18) and the wing ordinary rib (19) and is fixedly connected with the fuselage (2), weight reducing holes (20) are formed in the wing reinforcing rib (18) and the wing ordinary rib (19), the wing reinforcing rib (18) and the wing ordinary rib (19) are fixedly connected with the wing stringer (21), the wing reinforcing rib (18) is arranged at the root of the wing (3), the wing (3) is provided with an aileron (23) and a wing (24) at the rear edge, the wing spar (17), the wing rib (21) and the wing skin (19) are made of light-weight fiber materials, and the wing spar (19) are made of the wing materials.
6. The high-altitude balloon onboard release powered unmanned aerial vehicle according to claim 5, wherein the wing profile of the wing (3) is a concave-convex wing profile, and the root tip ratio of the wing (3) is 2.
7. The powered unmanned aerial vehicle with high altitude balloon mounting and release according to claim 1, wherein the horizontal tail wing (4) comprises a horizontal tail wing rib (25), a horizontal tail wing spar (26), a horizontal tail wing stringer (27), a horizontal tail wing skin (28) and a horizontal tail wing elevator surface (29), wherein the horizontal tail wing spar (26) penetrates through the horizontal tail wing rib (25) and the horizontal tail wing spar (26) is fixedly connected with the fuselage (2), and wherein the horizontal tail wing rib (25) is fixedly connected with the horizontal tail wing stringer (27); The vertical tail wing (5) comprises a vertical tail wing rib (30), a vertical tail wing spar (31), a vertical tail wing stringer (32), a vertical tail wing skin (33) and a vertical tail wing rudder surface (34), wherein the vertical tail wing spar (31) penetrates through the vertical tail wing rib (30) and is fixedly connected with the machine body (2), and the vertical tail wing spar (31) is fixedly connected with the vertical tail wing stringer (32); The horizontal tail wing ribs (25) and the vertical tail wing ribs (30) are made of balsawood materials, and the horizontal tail wing spar (26), the horizontal tail wing stringer (27), the horizontal tail wing skin (28), the vertical tail wing spar (31), the vertical tail wing stringer (32) and the vertical tail wing skin (33) are made of carbon fiber materials.
8. The powered unmanned aerial vehicle with high-altitude balloon carrying release according to claim 4, wherein the head of the fuselage (2) is provided with a counterweight load for adjusting the center of mass, and the bottom of the fuselage (2) is provided with a high-strength PVC foam buffer bag.
9. The high altitude balloon onboard release powered unmanned aerial vehicle of claim 4, wherein the power device comprises a motor, a propeller (16), a battery and an electronic governor, wherein the propeller (16) is mounted at the front end outside the fuselage (2), the motor is connected with the propeller (16) for driving the propeller (16) to rotate, and the flight control equipment comprises a sensor, an airspeed meter and a GPS.
10. The high-altitude balloon-mounted release powered unmanned aerial vehicle according to claim 2, wherein the balloon (6) is made of natural rubber latex material, and the interior of the balloon (6) is filled with helium.

Description

High-altitude balloon carrying and releasing powered unmanned aerial vehicle Technical Field The invention relates to the technical field of aerospace, in particular to a powered unmanned aerial vehicle with high-altitude balloon carrying and releasing functions. Background The ultra-high altitude environment generally refers to an airspace 15 km-30 km away from the ground, and has the characteristics of thin air, relatively stable air flow, rich solar energy and the like. The ultra-high-altitude unmanned aerial vehicle is an aircraft which can fully utilize the environmental characteristics and stably run in the airspace, and mainly can be divided into two types, namely a ① low-speed long-endurance unmanned aerial vehicle which utilizes buoyancy or a large airfoil to provide lift force, and a ② unmanned aerial vehicle which utilizes a special aerodynamic shape to fly at a high speed. The unmanned aerial vehicle has important application value in the fields of remote transportation, reconnaissance monitoring, communication relay and the like. The sounding balloon is used as an air-to-air throwing platform to deliver the unmanned aerial vehicle to the ultrahigh altitude, so that the unmanned aerial vehicle is a novel operation mode. The mode can reduce the energy consumption and the design difficulty of autonomous climbing of the unmanned aerial vehicle, and is particularly suitable for small unmanned aerial vehicles with light weight and compact structures. However, in the prior art, with respect to the specific system design of combining the sounding balloon with the powered unmanned aerial vehicle, particularly, the unmanned aerial vehicle detailed configuration which can adapt to the ultra-high altitude thin atmospheric environment and has stable flight and data acquisition capability is less in research report. The current detection of the area has the following pain points of weak ① continuous detection capability, powerless, drifting along with wind, incapability of residing in a target area, normal disposable use, discontinuous data, high ② cost, complex stratospheric airship (capable of residing for a long time), extremely high manufacturing and maintenance cost, poor ③ deployment flexibility, long satellite observation revisit period, possibly insufficient resolution and inflexible airship deployment. Therefore, how to design a ball-borne unmanned aerial vehicle system which has reasonable structure, controllable cost and reliable release and can fly at ultrahigh altitude and high efficiency is a technical problem to be solved in the field. Disclosure of Invention The invention aims to provide a powered unmanned aerial vehicle with high-altitude balloon carrying and releasing so as to solve the problems in the prior art. In order to achieve the aim, the invention provides a powered unmanned aerial vehicle for carrying and releasing high-altitude balloon, which comprises a sounding balloon throwing system and a powered unmanned aerial vehicle; the sounding balloon delivery system is used for carrying and releasing the powered unmanned aerial vehicle; The powered unmanned aerial vehicle comprises a machine body, wherein wings, a horizontal tail wing and a vertical tail wing are arranged on the machine body, a power device and flight control equipment are arranged in the machine body, and the wings are designed by adopting trapezoid wings and a large aspect ratio. Preferably, the sounding balloon throwing system comprises an air bag, an air bag rope, a load cabin and a throwing system, wherein the air bag is connected with the load cabin through the air bag rope, the throwing system is arranged below the load cabin, and the throwing system is used for mounting and releasing the powered unmanned aerial vehicle. The throwing system comprises a throwing frame, a flexible rope and a control system, wherein the throwing frame is of a truss structure, the flexible rope is connected below the throwing frame and is connected with at least three hanging points on a fuselage of the powered unmanned aerial vehicle, the hanging points are located at the mass center of the fuselage and at two ends of the wing, and the control system is used for controlling the powered unmanned aerial vehicle to be released at a preset height. The fuselage comprises a fuselage skin, an internal connecting piece, a reinforcing bulkhead, a common bulkhead and a truss, wherein the fuselage skin covers the outer side of the fuselage, the fuselage skin is made of multiple layers of carbon fiber materials, the internal connecting piece is arranged on the inner sides of the reinforcing bulkhead and the common bulkhead in a penetrating mode, the internal connecting piece is made of carbon fiber pieces and is used for connecting the wing, the horizontal tail wing and the vertical tail wing, the reinforcing bulkhead and the common bulkhead are fixedly connected to the truss, and the reinforcing bulkhead, the common bulkhead and the truss are