CN113184187A

CN113184187A - Intelligent disaster relief aircraft

Info

Publication number: CN113184187A
Application number: CN202110656951.4A
Authority: CN
Inventors: 高梅
Original assignee: Xuzhou Zhipu Intelligent Equipment Co ltd
Current assignee: Xuzhou Yongsen Network Technology Co ltd
Priority date: 2021-06-11
Filing date: 2021-06-11
Publication date: 2021-07-30
Anticipated expiration: 2041-06-11
Also published as: CN113184187B

Abstract

The invention discloses an intelligent disaster relief aircraft which comprises an aircraft body, a fog dispersal module, a throwing module and an observation module, wherein the aircraft body comprises a fuselage, wings which surround the outer side of the fuselage and are fixedly connected with the fuselage, and a foot landing frame which is arranged at the bottom of the fuselage. According to the invention, the position of a victim is known through the camera, the rotation direction of the motor is controlled, when the supply is provided in an open place, the motor drives the right end of the rotating plate to tilt, then the supply box connected with the small parachute slides along the arc-shaped cavity and falls from the opening, when the obstacle is located, the left end of the rotating plate tilts, then the supply box connected with the rod body passes through the opening and falls downwards, the supply box is dragged by the rope body until the rope body extends to the maximum degree, the cutter cuts off the rope body, the supply is provided for the victim according to the actual situation, each supply can be confirmed to be delivered to the hand of the victim, and the life safety of the victim is improved.

Description

Intelligent disaster relief aircraft

Technical Field

The invention relates to the technical field of intelligent disaster relief, in particular to an intelligent disaster relief aircraft.

Background

An aircraft is an instrumental flying object made by humans, capable of flying off the ground, flying in space and controlled by humans, flying in the atmosphere or in the extraterrestrial space (space). The four-axis aircraft is one of miniature aircraft, also is an intelligent robot. Originally made by the aviation model enthusiast, many automated manufacturers later found it to be useful for a variety of purposes and actively worked on. The unmanned aerial vehicle has the advantages that four rotors are used as flight engines to carry out aerial flight, the unmanned aerial vehicle is small in size and light in weight, can carry certain task load like an unmanned aerial vehicle suitable for carrying and using, and has autonomous navigation flight capability. And the specific flight task is completed under the complex and dangerous environment.

In order to improve the life safety of people in disaster areas, the aircraft provides certain medical supply and food supply for the people in disaster areas, due to the complex situation of disaster areas, when dropped goods and materials fall, parachutes connected with the goods and materials are often hung in the air, so that the goods and materials cannot fall into the hands of the people in disaster areas, meanwhile, when fog occurs in the disaster areas, the visibility is reduced, the flight of the aircraft is blocked, the aircraft is easy to collide against solids such as buildings, and the damage of the aircraft causes the stagnation of disaster relief operation.

Disclosure of Invention

The present invention is directed to solving one of the technical problems of the prior art or the related art.

Therefore, the technical scheme adopted by the invention is as follows:

an intelligent disaster relief aircraft comprises an aircraft body, a fog dissipation module, a throwing module and an observation module, wherein the aircraft body comprises a fuselage, a wing assembly, a pressing plate, an electric push rod, a pipe body, a check valve and a spray head, the wing assembly is arranged on the outer side of the fuselage, the wing assembly is encircled on the outer side of the fuselage and fixedly connected with the fuselage, the wing assembly is arranged on the bottom of the fuselage, the wing assembly is connected with the aircraft body, the fog dissipation module comprises a shell, a partition plate, an air bag, a pressing plate, a check valve and a spray head, the partition plate is arranged on the top of the shell, the air bag is fixedly connected with the pressing plate, the electric push rod is arranged on the top of the pressing plate and extends to the top of the shell, the pipe body is fixedly connected with the air bag, the check valve is arranged on, With mounting panel sliding connection's the body of rod, install in place in inside small-size parachute of mounting panel place the supply tank of small-size parachute, with fuselage plug-in connection's baffle, install in two change the board between the baffle, with the motor of changeing the board rigid coupling, the opening has been seted up in the backup pad, the observation module including install in the carousel of fuselage bottom, with the camera of carousel rigid coupling and about the carousel symmetry and with the limiting plate of carousel rigid coupling.

Through adopting above-mentioned technical scheme, through fog dispersal modular structure design, fog around the dissipation aircraft improves visibility, makes aircraft main part flight safer, and the actual conditions and the personnel position of stranded in disaster area are known to the observation module, adopts the modular structure design of input after that, realizes providing the supply for the personnel of being difficult according to the actual conditions, guarantees that every supply can both be sent to the personnel of being difficult in hand, improves the life safety of the personnel of being difficult.

The present invention in a preferred example may be further configured to: the throwing module further comprises a cutter, the cutter is fixedly arranged in the opening, and the length of the cutter is consistent with that of the opening.

Through adopting above-mentioned technical scheme, the rope body between cutter will supply tank and the body of rod cuts off, ensures that the supply tank can fall to stranded personnel completely in hand.

The present invention in a preferred example may be further configured to: the wing assembly is composed of an arc-shaped plate and a plurality of connecting plates, the wing assembly is arranged on the outer side of the wing, and the connecting plates are connected between the arc-shaped plate and the wing.

By adopting the technical scheme, the wing assembly protects the wings and prolongs the service life of the main body of the aircraft.

The present invention in a preferred example may be further configured to: the novel aircraft is characterized in that a cavity is formed between the shell and the aircraft body, the cavity is divided into a first cavity and a second cavity by the partition plate, the first cavity is located at the bottom of the second cavity, the demisting agent is filled in the first cavity, the airbag is located in the second cavity, and the sprayer is communicated with the interior of the first cavity.

By adopting the technical scheme, the air bag is separated from the demisting agent by the partition board, and the demisting agent is prevented from generating adverse effects on the air bag.

The present invention in a preferred example may be further configured to: the body sets up to two, two the body respectively with gasbag rear side and gasbag bottom rigid coupling, is close to the body of gasbag rear side runs through a casing rear side lateral wall, keeps away from the body of gasbag rear side passes the baffle and extends to inside the first cavity, two the shower nozzle is located casing rear side and first cavity respectively.

Through adopting above-mentioned technical scheme, the body that is located the gasbag rear side is to the gasbag in air delivery, and the check valve on this body limits the air that the gasbag was spit and only can discharge into first cavity inside simultaneously, and the check valve that is located in first cavity is then in order to prevent that the defogging agent from getting into the gasbag.

The present invention in a preferred example may be further configured to: the opening is located between two mounting panels, the mounting panel is inside to be seted up to be suitable for the gliding arc chamber of supply tank, the arc slide has all been seted up to the inside both sides wall in arc chamber, the body of rod constitutes sliding connection relation with the arc slide.

Through adopting above-mentioned technical scheme, the arc slide leads the body of rod, makes the body of rod motion more smooth and easy.

The present invention in a preferred example may be further configured to: the body of rod is installed and is being close to inside the left arc chamber of fuselage, small-size parachute is installed and is kept away from inside the left arc chamber of fuselage, all be connected with the rope body between the body of rod and the supply case, between small-size parachute and the supply case, the helicla flute that is suitable for the installation of the rope body is seted up in the body of rod outside.

Through adopting above-mentioned technical scheme, set up the helicla flute and can arrange in order the rope body, make the rope body the condition of knoing can not appear.

The present invention in a preferred example may be further configured to: the baffle comprises a riser and a diaphragm, the riser is located between diaphragm and the mounting panel, it contacts with two diaphragm bottoms to change the board top, the motor is located changes the board rear side, be connected with the fagging between motor and the backup pad.

Through adopting above-mentioned technical scheme, adopt this structural design, ensure that the baffle can normally go up and down, and then realize the transport to the supply tank.

The present invention in a preferred example may be further configured to: the intelligent disaster relief aircraft further comprises a sealing plate, the sealing plate is mounted on the outer side of the mounting plate close to the left side of the aircraft body, the sealing plate is mounted between the aircraft body and the supporting plate, and a recovery cavity is formed between the sealing plate and the mounting plate.

Through adopting above-mentioned technical scheme, set up and retrieve the chamber and can prevent the space for the body of rod provides, improve resource utilization.

By adopting the technical scheme, the invention has the beneficial effects that:

1. according to the invention, the position of a victim is known through the camera, the rotation direction of the motor is controlled, when the supply is provided in an open place, the motor drives the right end of the rotating plate to tilt, then the supply box connected with the small parachute slides along the arc-shaped cavity and falls from the opening, when the obstacle is located, the left end of the rotating plate tilts, then the supply box connected with the rod body passes through the opening and falls downwards, the supply box is dragged by the rope body until the rope body extends to the maximum degree, the cutter cuts off the rope body, the supply is provided for the victim according to the actual situation, each supply can be confirmed to be delivered to the hand of the victim, and the life safety of the victim is improved.

2. According to the invention, the pressing plate repeatedly extrudes the air bag, then the pipe body positioned at the rear side of the air bag conveys air into the air bag, meanwhile, the check valve on the pipe body limits that the air spitted out by the air bag can only be discharged into the first cavity, and the check valve positioned in the first cavity is used for preventing the demisting agent from entering the air bag, so that the pressure in the first cavity is increased due to the air spitted out by the air bag, the further the demisting agent is sprayed out from the spray head, the demisting effect is improved, and the aircraft body can fly more safely.

3. In the invention, the top of the supporting plate is arranged to be an inclined surface, so that the length of the other rod body is greater than that of the opening, when the rod body falls onto the supporting plate, the rod body slides along the supporting plate, and after the rope body on the rod body is cut off by the cutter, the rod body smoothly rolls into the recycling cavity, thus improving the resource utilization rate and achieving the purpose of environmental protection

Drawings

FIG. 1 is a perspective view of the overall structure of the present invention;

FIG. 2 is a schematic cross-sectional view of the overall structure of the present invention;

FIG. 3 is a right sectional view of the overall structure of the present invention;

FIG. 4 is a front cross-sectional view of the overall structure of the present invention;

FIG. 5 is a right side view of FIG. 3 of the present invention;

FIG. 6 is a schematic view of the internal structure of the mounting plate of the present invention;

FIG. 7 is a perspective view of a baffle of the present invention;

FIG. 8 is an enlarged view of the portion A of FIG. 4 according to the present invention.

Reference numerals:

100. an aircraft body; 110. a body; 120. an airfoil; 130. a foot rest; 140. a wing assembly; 141. an arc-shaped plate; 142. connecting plates;

200. a fog dispersal module; 210. a housing; 220. a partition plate; 230. an air bag; 240. pressing a plate; 250. an electric push rod; 260. a pipe body; 270. a one-way valve; 280. a spray head;

300. a releasing module; 310. a support plate; 320. mounting a plate; 330. a rod body; 340. a small parachute; 350. a supply tank; 360. a baffle plate; 370. rotating the plate; 380. a motor;

400. an observation module; 410. a turntable; 420. a camera; 430. a limiting plate;

500. and (7) closing the plate.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be noted that the embodiments of the present invention and features of the embodiments may be combined with each other without conflict.

It is to be understood that this description is made only by way of example and not as a limitation on the scope of the invention.

The following describes an intelligent disaster relief aircraft provided by some embodiments of the invention with reference to the drawings.

The first embodiment is as follows:

referring to fig. 1 to 8, the intelligent disaster relief aircraft provided by the present invention includes an aircraft body 100, a fog dispersal module 200, a launch module 300 and an observation module 400, where the aircraft body 100 includes a fuselage 110, wings 120 surrounding the outside of the fuselage 110 and fixedly connected to the fuselage 110, a landing leg 130 installed at the bottom of the fuselage 110, and a wing assembly 140 connected to the aircraft body 100; in the using process, the aircraft body 100 drives the fog dispersal module 200 to disperse fog in the air, so that the visibility is improved, the probability of collision of the aircraft body in the air is reduced, and meanwhile, the observation module 400 is used for knowing a disaster and releasing rescue goods and materials according to the disaster;

the defogging module 200 comprises a shell 210 mounted on the top of the body 110, the shell 210 can protect the internal structure of the defogging module 200, a partition plate 220 mounted inside the shell 210, the partition plate 220 can separate the airbag 230 from the defogging agent to prevent the defogging agent from generating adverse effects on the airbag 230, the airbag 230 fixedly connected with the partition plate 220, a pressure plate 240 connected with the airbag 230, an electric push rod 250 mounted on the top of the pressure plate 240 and extending to the top of the shell 210, a tube 260 fixedly connected with the airbag 230, a one-way valve 270 mounted on the tube 260, and a spray head 280 fixedly connected with the shell 210; in the using process, the electric push rod 250 repeatedly extrudes the air bag 230 through the pressing plate 240, the air bag 230 spits air to enable the pressure in the first cavity to be larger and larger, so that the defogging agent sprayed out of the spray head 280 is farther and farther, and the defogging effect is improved;

the putting module 300 comprises a supporting plate 310 sleeved on the outer side of the foot stand 130, the supporting plate 310 provides support for the whole putting module 300, a mounting plate 320 which is fixedly connected with the supporting plate 310 and is symmetrical about the vertical central line of the supporting plate 310, the mounting plate 320 can provide placing space for a rod body 330, a supply tank 350 and a small parachute 340, the rod body 330 which is in sliding connection with the mounting plate 320, the small parachute 340 which is arranged in the mounting plate 320 and the supply tank 350 which is arranged in the small parachute 340, the supply tank 350 provides food and certain medical guarantee for the people in disaster areas, the safety rate of the people in disaster is greatly improved, the baffle plates 360 which are connected with the machine body 110 in an inserting mode, the rotating plate 370 which is arranged between the two baffle plates 360 and the motor 380 which is fixedly connected with the rotating plate 370 are arranged, and the supporting plate 310 is provided with an opening; according to the position of the disabled person, the motor 380 regularly drives the rotating plate 370 to rotate, then the rotating plate 370 drives the baffle 360 on one side to lift up each time of rotation, and then supplies to the disabled person;

the observation module 400 includes a turntable 410 mounted at the bottom of the body 110, a camera 420 fixedly connected to the turntable 410, and a limiting plate 430 symmetrical about the turntable 410 and fixedly connected to the turntable 410; in the using process, the operator of the aircraft body 100 can know the disaster situation through the observation module 400, and also know the position of the trapped person, so as to provide timely rescue and material supply for the trapped person.

Further, the releasing module 300 further comprises a cutter, the cutter is fixedly installed inside the opening, the length of the cutter is consistent with that of the opening, and after the supply tank 350 connected with the rod body 330 falls from the supporting plate 310, the cutter cuts off the rope body between the rod body 330 and the supply tank 350, so that the material rescue is completed, and meanwhile, the rod body 330 can be recycled.

Further, the wing assemblies 140 and the wings 120 are equal in number, the wing assemblies 140 are composed of an arc-shaped plate 141 and a plurality of connecting plates 142, the wing assemblies 140 are arranged on the outer sides of the wings 120, and the connecting plates 142 are connected between the arc-shaped plate 141 and the wings 120, so that the wing assemblies 140 can protect the wings 120, damage degree of the aircraft main body 100 during collision is reduced, and the service life of the aircraft main body 100 is prolonged.

Further, a cavity is formed between the housing 210 and the body 110, the partition plate 220 divides the cavity into a first cavity and a second cavity, the first cavity is located at the bottom of the second cavity, the first cavity is filled with the defogging agent, the airbag 230 is located in the second cavity, the spray head 280 is communicated with the interior of the first cavity, the partition plate 220 effectively separates the defogging agent from the airbag 230 to prevent the defogging agent from causing adverse effects on the airbag 230, two pipe bodies 260 are provided, the two pipe bodies 260 are respectively fixedly connected with the rear side of the airbag 230 and the bottom of the airbag 230, the pipe body 260 close to the rear side of the airbag 230 penetrates through a side wall of the rear side of the housing 210, the pipe body 260 far away from the rear side of the airbag 230 penetrates through the partition plate 220 and extends into the interior of the first cavity, the two spray heads 280 are respectively located at the rear side of the housing 210 and the interior of the first cavity, when the pressure plate 240 repeatedly extrudes the airbag 230, the tube 260 at the rear side of the air bag 230 supplies air into the air bag 230, and at the same time, the check valve 270 on the tube 260 limits the air spitted out by the air bag 230 to be discharged into the first cavity, and the check valve 270 in the first cavity is used for preventing the demisting agent from entering the air bag 230.

Further, baffle 360 comprises a riser and a diaphragm, the riser is located between diaphragm and the mounting panel 320, the commentaries on classics board 370 top contacts with two diaphragm bottoms, motor 380 is located commentaries on classics board 370 rear side, be connected with the fagging between motor 380 and the backup pad 310, adopt this structural design, change board 370 at every turn the swing and all can make an individual supply case 350 fall down, and the swing direction of changeing board 370 is established according to the topography of stranded personnel.

Example two:

combine fig. 2-6 to show, on the basis of embodiment one, the opening is located between two mounting panels 320, mounting panel 320 is inside to be seted up and is suitable for the gliding arc chamber of supply tank 350, the arc slide has all been seted up to the inside both sides wall in arc chamber, the body of rod 330 constitutes the sliding connection relation with the arc slide, and the arc slide can lead the body of rod 330, makes the body of rod 330 motion more smooth and easy, prevents that it from appearing the dead condition of card in the arc intracavity.

Specifically, body of rod 330 is installed in being close to inside the left arc intracavity of fuselage 110, small-size parachute 340 is installed and is kept away from inside the left arc intracavity of fuselage 110, between body of rod 330 and supply tank 350, all be connected with the rope body between small-size parachute 340 and the supply tank 350, the helicla flute that is suitable for the installation of the rope body is seted up in the body of rod 330 outside, sets up the helicla flute and can arrange the rope body in order, avoids the rope body phenomenon of knoing to appear, makes supply tank 350 can normally fall down.

Example three:

referring to fig. 2-5 and fig. 7, in the above embodiment, the intelligent disaster relief aircraft further includes a sealing plate 500, the sealing plate 500 is installed outside the mounting plate 320 near the left side of the fuselage 110, the sealing plate 500 is installed between the fuselage 110 and the support plate 310, a recovery cavity is formed between the sealing plate 500 and the mounting plate 320, and the rod body 330 can be recovered by the recovery cavity, so that the resource utilization rate is improved.

The working principle and the using process of the invention are as follows: when the invention is put into practical use, the electric push rod 250 repeatedly extrudes the air bag 230 through the press plate 240, then the tube 260 positioned at the rear side of the air bag 230 conveys air into the air bag 230, meanwhile, the one-way valve 270 on the tube 260 limits the air spitted by the air bag 230 to be only discharged into the first cavity, the one-way valve 270 positioned in the first cavity is used for preventing the demisting agent from entering the air bag 230, the air bag 230 spits the air to enable the pressure in the first cavity to be higher and higher, so the demisting agent sprayed out from the spray head 280 is farther, the demisting effect is improved, then an operator who controls the aircraft main body 100 to fly observes disaster situations and positions of trapped persons through the camera 420, when the supply is provided for the persons in distress on the open ground, the motor 380 causes the right end of the rotating plate 370 to tilt, the rotating plate 370 enables the baffle plate 360 at the right side of the rotating plate 370 to move upwards through acting force on the transverse plate, then supply tank 350 connected with small parachute 340 slides downwards along the arc-shaped cavity until supply tank 350 is completely separated from mounting plate 320, rotating plate 370 can restore to the initial position, when obstacles around trapped person are observed, motor 380 controls the left end of rotating plate 370 to tilt, under the same principle, supply tank 350 connected with rod 330 passes through the opening and falls downwards, in the period, the rope pulls supply tank 350 until the rope stretches to the maximum degree, the cutter cuts off the rope, then supply tank 350 is delivered to the hand of trapped person, and rod 330 is recovered by the recovery cavity, so that resource utilization rate is improved.

In the present invention, the term "plurality" means two or more unless explicitly defined otherwise. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items. The terms "mounted," "connected," "fixed," and the like are to be construed broadly, and for example, "connected" may be a fixed connection, a removable connection, or an integral connection; "coupled" may be direct or indirect through an intermediary. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

It will be understood that when an element is referred to as being "mounted to," "secured to" or "disposed on" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and the like as used herein are for illustrative purposes only and do not denote a unique embodiment.

In the description herein, the description of the terms "one embodiment," "some embodiments," "specific embodiments," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the claims and their equivalents.

Claims

1. Intelligent disaster relief aircraft, its characterized in that includes:

the aircraft main body (100) comprises a fuselage (110), wings (120) which surround the outer side of the fuselage (110) and are fixedly connected with the fuselage (110), a landing leg (130) arranged at the bottom of the fuselage (110) and wing assemblies (140) connected with the aircraft main body (100);

the fog dispersal module (200) comprises a shell (210) arranged at the top of the machine body (110), a partition plate (220) arranged inside the shell (210), an air bag (230) fixedly connected with the partition plate (220), a pressure plate (240) connected with the air bag (230), an electric push rod (250) arranged at the top of the pressure plate (240) and extending to the top of the shell (210), a pipe body (260) fixedly connected with the air bag (230), a one-way valve (270) arranged on the pipe body (260) and a spray head (280) fixedly connected with the shell (210);

the throwing module (300) comprises a supporting plate (310) sleeved on the outer side of the foot falling frame (130), a mounting plate (320) fixedly connected with the supporting plate (310) and symmetrical about a vertical central line of the supporting plate (310), a rod body (330) in sliding connection with the mounting plate (320), a small parachute (340) arranged inside the mounting plate (320), a supply box (350) arranged in the small parachute (340), baffles (360) connected with the machine body (110) in an inserting manner, a rotating plate (370) arranged between the two baffles (360) and a motor (380) fixedly connected with the rotating plate (370), wherein the supporting plate (310) is provided with an opening;

observe module (400), including install in carousel (410) of fuselage (110) bottom, with camera (420) of carousel (410) rigid coupling and about carousel (410) symmetry and with limiting plate (430) of carousel (410) rigid coupling.

2. The intelligent disaster relief aircraft as claimed in claim 1, wherein the launch module (300) further comprises a cutter, the cutter is fixedly mounted inside the opening, and the length of the cutter is consistent with the length of the opening.

3. The intelligent disaster relief aircraft as claimed in claim 1, wherein the wing assemblies (140) and the wings (120) are equal in number, the wing assemblies (140) are composed of an arc-shaped plate (141) and a plurality of connecting plates (142), the wing assemblies (140) are arranged outside the wings (120), and the connecting plates (142) are connected between the arc-shaped plate (141) and the wings (120).

4. The intelligent disaster relief aircraft as claimed in claim 1, wherein a cavity is formed between the housing (210) and the fuselage (110), the partition (220) divides the cavity into a first cavity and a second cavity, the first cavity is located at the bottom of the second cavity, the first cavity is filled with the defogging agent, the airbag (230) is located in the second cavity, and the nozzle (280) is communicated with the interior of the first cavity.

5. The intelligent disaster relief aircraft as claimed in claim 4, wherein the number of the tubes (260) is two, two tubes (260) are fixedly connected to the rear side of the airbag (230) and the bottom of the airbag (230), the tube (260) near the rear side of the airbag (230) penetrates through a side wall of the rear side of the housing (210), the tube (260) far away from the rear side of the airbag (230) penetrates through the partition (220) and extends into the first cavity, and two nozzles (280) are located at the rear side of the housing (210) and inside the first cavity.

6. The intelligent disaster relief aircraft as claimed in claim 1, wherein the opening is located between two mounting plates (320), an arc-shaped cavity is defined in the mounting plates (320) and is suitable for the supply tank (350) to slide, arc-shaped slideways are defined in two side walls of the arc-shaped cavity, and the rod body (330) and the arc-shaped slideways form a sliding connection relationship.

7. The intelligent disaster relief aircraft according to claim 6, wherein the rod body (330) is installed in an arc-shaped cavity close to the left side of the fuselage (110), the small parachute (340) is installed in an arc-shaped cavity far away from the left side of the fuselage (110), rope bodies are connected between the rod body (330) and the supply tank (350) and between the small parachute (340) and the supply tank (350), and spiral grooves suitable for the installation of the rope bodies are formed in the outer side of the rod body (330).

8. The intelligent disaster relief aircraft as claimed in claim 1, wherein the baffle (360) is composed of a vertical plate and a horizontal plate, the vertical plate is located between the horizontal plate and the mounting plate (320), the top of the rotating plate (370) is in contact with the bottom of the two horizontal plates, the motor (380) is located at the rear side of the rotating plate (370), and a supporting plate is connected between the motor (380) and the supporting plate (310).

9. The intelligent disaster relief aircraft as claimed in claims 1-8, further comprising a sealing plate (500), wherein the sealing plate (500) is mounted on the outer side of the mounting plate (320) near the left side of the fuselage (110), the sealing plate (500) is mounted between the fuselage (110) and the support plate (310), and a recovery cavity is formed between the sealing plate (500) and the mounting plate (320).