阅读说明：本技术 一种可伸缩式翼型太阳能变体浮空飞行器 (Retractable wing type solar variant floats empty aircraft ) 是由 宗剑 沈宝国 于 2020-04-28 设计创作，主要内容包括：本发明公开了一种可伸缩式翼型太阳能变体浮空飞行器,包括飞艇艇身、两个充吸气装置、载物平台、两个推进装置和起落装置,两个所述充吸气装置均对称安装于所述飞艇艇身的两侧,所述载物平台安装于所述飞艇艇身的下部,两个所述推进装置对称安装于所述飞艇艇身的侧部,所述起落装置安装于飞艇艇身的下部,所述飞艇艇身包括固定翼型艇体和两个伸缩翼型变体组件,所述载物平台包括两根连接杆和放置板,所述推进装置包括推进电机、驱动轴和叶片,所述起落装置包括两根第一支撑架、第二支撑架、两个第一滚轮和两个第二滚轮。本发明有效的延长航行时间、增大负载量以及延长高空驻留时间,增大其使用的范围。(The invention discloses a retractable wing type solar variant floating aircraft which comprises an airship hull, two air inflation and suction devices, a carrying platform, two propelling devices and a landing gear, wherein the two air inflation and suction devices are symmetrically arranged on two sides of the airship hull, the carrying platform is arranged on the lower part of the airship hull, the two propelling devices are symmetrically arranged on the lateral part of the airship hull, the landing gear is arranged on the lower part of the airship hull, the airship hull comprises a fixed wing type hull and two retractable wing type variant assemblies, the carrying platform comprises two connecting rods and a placing plate, the propelling devices comprise a propelling motor, a driving shaft and blades, and the landing gear comprises two first supporting frames, a second supporting frame, two first rollers and two second rollers. The invention effectively prolongs the navigation time, the load capacity and the high-altitude residence time, and enlarges the application range.)

1. A retractable wing type solar variant floating aircraft comprises an airship hull (100), two air inflation and suction devices (200), an object platform (300), two propelling devices (400) and a landing gear (500), and is characterized in that: the two air charging and sucking devices (200) are symmetrically arranged on two sides of the airship hull (100), the cargo platform (300) is arranged on the lower part of the airship hull (100), the two propelling devices (400) are symmetrically arranged on the side part of the airship hull (100), and the landing gear (500) is arranged on the lower part of the airship hull (100), wherein:

the airship hull (100) comprises a fixed airfoil hull (110) and two telescopic airfoil variant assemblies (120), wherein the two telescopic airfoil variant assemblies (120) are respectively arranged on two sides of the fixed airfoil hull (110);

the loading platform (300) comprises two connecting rods (310) and a placing plate (320), wherein the two connecting rods (310) are both installed at the lower part of the fixed wing-shaped hull (110), and the placing plate (320) is installed at the lower parts of the two connecting rods (310);

the propulsion device (400) comprises a propulsion motor (410), a driving shaft (420) and a blade (430), wherein the propulsion motor (410) is installed inside the fixed wing-shaped hull (110) through a propulsion motor base (440), the driving shaft (420) penetrates through the side wall of the fixed wing-shaped hull (110), the driving shaft (420) is in transmission connection with the output end of the propulsion motor (410), and the blade (430) is installed on the side part of the driving shaft (420);

the landing gear (500) comprises two first support frames (510), a second support frame (520), two first rollers (530) and two second rollers (540), wherein the two first support frames (510) are respectively installed at the lower parts of the two telescopic wing-shaped variant assemblies (120), the two first rollers (530) are respectively rotatably installed at the lower parts of the two first support frames (510), the second support frame (520) is installed at the lower part of the fixed wing-shaped hull (110), and the two second rollers (540) are respectively rotatably installed at the two sides of the lower part of the second support frame (520).

2. The retractable wing type solar variant floating aircraft according to claim 1, characterized in that: the fixed wing-shaped boat body (110) comprises a plurality of solar cell panels (111), a boat body air bag (112) and a boat body framework (113), the boat body air bag (112) is coated on the outer side of the boat body framework (113), the solar cell panels (111) are all installed on the upper portion of the boat body air bag (112), and each solar cell panel (111) is in clearance fit.

3. The retractable wing type solar variant floating aircraft according to claim 2, characterized in that: the boat body skeleton (113) comprises a fixed central wing rib (1131), a plurality of boat bag supporting rods (1132), a fixed side wing rib (1133), a fixed wing-shaped tail rod (1134) and a wing-shaped reinforcing plate shell (1135), the fixed side ribs (1133) are symmetrically arranged on two sides of the fixed central rib (1131), the fixed central rib (1131) and the fixed side ribs (1133) are connected through a plurality of boat bag supporting rods (1132), the fixed airfoil tail rod (1134) is installed at one side of the fixed central rib (1131), the side of the fixed airfoil tail rod (1134) is connected with one side of the fixed side wing rib (1133), the aerofoil stiffener plate shell (1135) is mounted to the other side of the fixed central rib (1131), the side of the wing section reinforcing plate shell (1135) is connected with the other side of the fixed side wing rib (1133), and the two connecting rods (310) are arranged at the lower part of the fixed central wing rib (1131).

4. The retractable wing type solar variant floating aircraft according to claim 3, characterized in that: a plurality of fixed central rib reinforcing rods (11311) are installed on the inner side of the fixed central rib (1131), a plurality of first mounting holes (11312) matched with the boat bag supporting rods (1132) are formed in the side portion of the fixed central rib (1131), second mounting holes (11313) matched with the airfoil reinforcing plate shell (1135) are formed in the side portion of the fixed central rib (1131), and first weight reduction holes (11314) are formed in the upper portion of the fixed central rib (1131), the lower portion of the fixed central rib (1131) and the tail portion of the fixed central rib (1131).

5. The retractable wing type solar variant floating aircraft according to claim 1, characterized in that: a plurality of fixed side rib reinforcing rods (11331) are installed inside the fixed side rib (1133), a plurality of third installation holes (11332) matched with the boat bag supporting rods (1132) are formed in the side portion of the fixed side rib (1133), a fourth installation hole (11333) matched with the airfoil reinforcing plate shell (1135) is formed in the side portion of the fixed side rib (1133), second weight reduction holes (11334) are formed in the upper portion of the fixed side rib (1133), the lower portion of the fixed side rib (1133) and the tail portion of the fixed side rib (1133), the propulsion motor base (440) is installed on the side portion of the fixed side rib (1133), the air charging and sucking device (200) is installed on the lower portion of the fixed side rib (1133), and the air charging and sucking hole (11335) matched with the air charging and sucking device (200) is formed in the side portion of the fixed side rib (1133).

6. The retractable wing type solar variant floating aircraft according to claim 1, characterized in that: the telescopic wing profile variant component (120) comprises a connecting wing rib component (121), a plurality of telescopic wing ribs (122) and a plurality of telescopic variant mechanisms (123), wherein the connecting wing rib component (121) is installed on the side part of the fixed side wing rib (1133), the telescopic wing ribs (122) are connected with the connecting wing rib component (121) through the telescopic variant mechanisms (123), and the telescopic wing ribs (122) are connected with one another through the telescopic variant mechanisms (123).

7. The retractable wing type solar variant floating aircraft according to claim 6, characterized in that: the connecting rib assembly (121) comprises a connecting rib (1211), a telescopic motor (1212), a driving screw rod (1213) and a telescopic guide rod (1214), a telescopic motor mounting seat (1215) is arranged inside the connecting wing rib (1211), a first slideway (1216) matched with the telescopic guide rod (1214) is arranged inside the connecting wing rib (1211), the telescopic motor (1212) is fixed inside the telescopic motor mounting seat (1215) through a telescopic motor mounting end cover (1217), the output end of the telescopic motor (1212) is connected with the driving screw rod (1213) through a coupling (1218), one end of the driving screw rod (1213) is connected with the telescopic wing rib (122) at the outermost side, the telescopic guide rod (1214) is sleeved in the first slideway (1216) in a sliding way, one end of the telescopic guide rod (1214) is connected with the telescopic wing rib (122) at the outermost side.

8. The retractable wing type solar variant floating aircraft according to claim 7, characterized in that: the fixed side wing rib (1133) is internally provided with a second slide way (11336) matched with the telescopic guide rod (1214), the fixed side wing rib (1133) is internally provided with a connecting block (11337) matched with the driving screw rod (1213), and the middle part of the connecting block (11337) is provided with a fifth mounting hole (11338) matched with the driving screw rod (1213).

9. The retractable wing type solar variant floating aircraft according to claim 6, characterized in that: the telescopic wing rib (122) is internally provided with a telescopic wing rib reinforcing rod (1221), the side part of the telescopic wing rib (122) is provided with a sixth mounting hole (1222) matched with the telescopic variant mechanism (123), the tail part of the telescopic wing rib (122) is provided with a third lightening hole (1223), and the telescopic wing rib (122), the connecting wing rib (1211), the fixed side wing rib (1133) and the fixed central wing rib (1131) are consistent in wing shape.

10. The retractable wing type solar variant floating aircraft according to claim 9, characterized in that: the telescopic variant mechanism (123) comprises two mounting heads (1231), a connecting rod (1232), two connecting rod rotating pins (1233), two rocker arms (1234) and two rocker arm rotating pins (1235), wherein the two mounting heads (1231) are hinged to one sides of the two rocker arms (1234) through the rocker arm rotating pins (1235), and the other sides of the two rocker arms (1234) are connected with the connecting rod (1232) through the connecting rod rotating pins (1233).

Technical Field

The invention relates to the technical field of aircrafts, in particular to a retractable wing type solar variant floating aircraft.

Background

Aircraft are instruments that fly in the atmosphere or in the outer space of the atmosphere, and can be classified into four types: the aircraft flying in the atmosphere is called as a balloon, an airship, an airplane and the like, the aircraft flies by the static buoyancy of the air or the aerodynamic force generated by the relative motion of the air, the aircraft flying in the space is called as a space vehicle, such as an artificial earth satellite, a manned spacecraft, a space detector, a space plane and the like, the aircraft, the spacecraft, the space vehicle and the space vehicle obtain the necessary speed to enter the space under the driving of the carrier rocket, and then the spacecraft and the space vehicle perform the orbital motion similar to the celestial body by means of inertia.

With the rapid development of aviation science and technology, aircrafts are developed at a higher speed, and can finish the tasks in the aspects of freight transportation, passenger transportation, agriculture, fishery, forestry, meteorology, prospecting, aerial measurement, aerial photography and the like in civil use.

However, these aircrafts have major disadvantages, such as limited endurance of rotor aircrafts and fixed-wing aircrafts, limited load capacity and poor wind resistance of the conventional airship, and cannot solve the problem of long-term air parking of the aircraft, and the use of further expanding stratosphere space is limited.

Disclosure of Invention

The invention aims to provide a retractable wing type solar variant floating aircraft, which prolongs the navigation time, increases the loading capacity and prolongs the high-altitude residence time so as to solve the problems in the background technology.

In order to achieve the purpose, the invention provides the following technical scheme: a retractable wing type solar variant floating aircraft comprises an airship hull, two air charging and sucking devices, a carrying platform, two propelling devices and a landing device, wherein the two air charging and sucking devices are symmetrically arranged on two sides of the airship hull, the carrying platform is arranged on the lower portion of the airship hull, the two propelling devices are symmetrically arranged on the lateral portion of the airship hull, and the landing device is arranged on the lower portion of the airship hull, wherein:

the airship hull comprises a fixed wing-shaped hull body and two telescopic wing-shaped variant assemblies, and the two telescopic wing-shaped variant assemblies are respectively arranged on two sides of the fixed wing-shaped hull body;

the loading platform comprises two connecting rods and a placing plate, the two connecting rods are both arranged at the lower part of the fixed wing-shaped hull, and the placing plate is arranged at the lower parts of the two connecting rods;

the propulsion device comprises a propulsion motor, a driving shaft and blades, the propulsion motor is mounted inside the fixed wing-shaped hull through a propulsion motor base, the driving shaft penetrates through the side wall of the fixed wing-shaped hull, the driving shaft is in transmission connection with the output end of the propulsion motor, and the blades are mounted on the side part of the driving shaft;

the landing gear comprises two first support frames, two second support frames, two first idler wheels and two second idler wheels, the two first support frames are respectively installed on the lower portions of the two telescopic wing-shaped variant assemblies, the two first idler wheels are respectively installed on the lower portions of the two first support frames in a rotating mode, the second support frames are installed on the lower portion of the fixed wing-shaped boat body, and the two second idler wheels are respectively installed on the two sides of the lower portion of the second support frame in a rotating mode.

Preferably, the fixed wing-shaped hull comprises a plurality of solar panels, a hull air bag and a hull framework, the hull air bag is coated on the outer side of the hull framework, the plurality of solar panels are installed on the upper portion of the hull air bag, and each solar panel is in clearance fit with the other solar panels.

Preferably, the hull framework comprises a fixed central wing rib, a plurality of hull support rods, fixed lateral wing ribs, a fixed wing-shaped tail rod and a wing-shaped reinforcing plate shell, the fixed lateral wing ribs are symmetrically arranged on two sides of the fixed central wing rib, the fixed central wing rib is connected with the fixed lateral wing ribs through the plurality of hull support rods, the fixed wing-shaped tail rod is arranged on one side of the fixed central wing rib, the lateral part of the fixed wing-shaped tail rod is connected with one side of the fixed lateral wing rib, the wing-shaped reinforcing plate shell is arranged on the other side of the fixed central wing rib, the lateral part of the wing-shaped reinforcing plate shell is connected with the other side of the fixed lateral wing rib, and the two connecting rods are arranged on the lower part of the fixed central wing rib.

Preferably, a plurality of fixed central rib reinforcing rods are installed on the inner sides of the fixed central ribs, a plurality of first mounting holes matched with the boat bag supporting rods are formed in the side portions of the fixed central ribs, second mounting holes matched with the wing-shaped reinforcing plate shells are formed in the side portions of the fixed central ribs, and first lightening holes are formed in the upper portions of the fixed central ribs, the lower portions of the fixed central ribs and the tail portions of the fixed central ribs.

Preferably, a plurality of fixed wing rib reinforcing rods are installed inside the fixed wing ribs, a plurality of third installation holes matched with the boat bag support rods are formed in the side portions of the fixed wing ribs, a fourth installation hole matched with the wing-shaped reinforcing plate shell is formed in the side portions of the fixed wing ribs, second lightening holes are formed in the upper portions of the fixed wing ribs, the lower portions of the fixed wing ribs and the tail portions of the fixed wing ribs, the propulsion motor base is installed on the side portions of the fixed wing ribs, the air charging and sucking device is installed on the lower portions of the fixed wing ribs, and air charging and sucking holes matched with the air charging and sucking device are formed in the side portions of the fixed wing ribs.

Preferably, the telescopic wing profile variant component comprises a connecting rib component, a plurality of telescopic ribs and a plurality of telescopic variant mechanisms, the connecting rib component is mounted on the side part of the fixed side rib, the telescopic ribs are connected with the connecting rib component through the telescopic variant mechanisms, and the plurality of telescopic ribs are connected through the telescopic variant mechanisms.

Preferably, the connection wing rib subassembly includes connection wing rib, flexible motor, drive lead screw and flexible guide arm, the internally mounted of connection wing rib have flexible motor mount pad the internally mounted of connection wing rib with flexible guide arm complex first slide, flexible motor is fixed in the inside of flexible motor mount pad through flexible motor installation end cover, the output of flexible motor pass through the shaft coupling with the drive lead screw links to each other, the one end of drive lead screw with be in the outside flexible wing rib links to each other, flexible guide arm sliding sleeve is located the inside of first slide, the one end of flexible guide arm with be in the outside flexible wing rib links to each other.

Preferably, the fixed lateral wing rib is internally provided with a second slide matched with the telescopic guide rod, the fixed lateral wing rib is internally provided with a connecting block matched with the driving screw rod, and the middle part of the connecting block is provided with a fifth mounting hole matched with the driving screw rod.

Preferably, a telescopic rib reinforcing rod is installed inside the telescopic rib, a sixth installation hole matched with the telescopic variant mechanism is installed on the lateral portion of the telescopic rib, a third lightening hole is formed in the tail portion of the telescopic rib, and the telescopic rib, the connecting rib, the fixed lateral rib and the fixed central rib are consistent in wing shape.

Preferably, the telescopic variant mechanism comprises two mounting heads, a connecting rod, two connecting rod rotating pins, two rocker arms and two rocker arm rotating pins, wherein the two mounting heads are respectively hinged with one sides of the two rocker arms through the rocker arm rotating pins, and the other sides of the two rocker arms are respectively connected with the connecting rod through the connecting rod rotating pins.

In summary, due to the adoption of the technology, the invention has the beneficial effects that:

according to the invention, the main body structure of the aircraft is formed by the fixed wing-shaped hull and the telescopic wing-shaped variant assembly, the telescopic wing-shaped variant assembly can be stretched according to actual requirements, so that corresponding working conditions can be adjusted according to actual conditions, and the lifting can be controlled without an auxiliary air bag, so that the overall navigation time, the loading capacity and the high-altitude residence time are increased, and the aircraft is more convenient to use.

According to the invention, the solar panels are arranged in a clearance fit manner, so that the hull airbag is prevented from being damaged due to the temperature rise of the solar panels, the solar panels are utilized to receive the sunlight to obtain electric power, the integral cruising ability is increased, and the integral energy-saving and environment-friendly effects are achieved.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is an axial view of a retractable wing type solar variant floating aircraft according to the present invention;

fig. 2 is a schematic view illustrating the expansion of a single-side telescopic rib of the retractable wing type solar variant floating aircraft according to the present invention;

FIG. 3 is a schematic view of the connection between the fixed central rib and the fixed lateral rib of the retractable wing type solar variant floating aircraft according to the present invention;

FIG. 4 is a schematic view of a fixed central rib structure of a retractable wing type solar variant floating aircraft according to the present invention;

FIG. 5 is a schematic view of a fixed side rib structure of a retractable wing type solar variant floating aircraft according to the present invention;

FIG. 6 is a schematic view of a connecting rib assembly of the retractable wing type solar variant floating aircraft according to the present invention;

FIG. 7 is a schematic side view of a retractable rib of a retractable wing type solar variant floating aircraft according to the present invention;

fig. 8 is a schematic structural diagram of a telescopic variant mechanism of the telescopic wing type solar variant floating aircraft.

In the figure: 100. an airship hull; 110. fixing the wing-shaped boat body; 111. a solar panel; 112. a hull airbag; 113. a hull skeleton; 1131. securing the center rib; 11311. a fixed central rib stiffener; 11312. a first mounting hole; 11313. a second mounting hole; 11314. a first lightening hole; 1132. a boat bag support bar; 1133. securing a lateral wing rib; 11331. a fixed lateral rib stiffener; 11332. a third mounting hole; 11333. a fourth mounting hole; 11334. a second lightening hole; 11335. a gas charging and sucking hole; 11336. a second slideway; 11337. connecting blocks; 11338. a fifth mounting hole; 1134. fixing the wing-shaped tail rod; 1135. an airfoil stiffener shell; 120. a telescoping aerofoil variant assembly; 121. connecting the rib assemblies; 1211. connecting ribs; 1212. a telescopic motor; 1213. driving the screw rod; 1214. a telescopic guide rod; 1215. a telescopic motor mounting seat; 1216. a first slideway; 1217. an end cover is installed on the telescopic motor; 1218. a coupling; 122. a telescoping rib; 1221. a telescopic rib stiffener; 1222. a sixth mounting hole; 1223. a third lightening hole; 123. a flexible variant mechanism; 1231. a mounting head; 1232. a connecting rod; 1233. a connecting rod rotation pin; 1234. a rocker arm; 1235. a rocker arm pivot pin; 200. an air charging and sucking device; 300. a carrier platform; 310. a connecting rod; 320. placing the plate; 400. a propulsion device; 410. a propulsion motor; 420. a drive shaft; 430. a blade; 440. a propulsion motor base; 500. a landing gear; 510. a first support frame; 520. a second support frame; 530. a first roller; 540. a second roller.

The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings of the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.

Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present invention, it is to be understood that the terms "longitudinal", "upper", "lower", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

The invention provides a retractable wing type solar variant floating aircraft as shown in fig. 1-8, which comprises an airship hull 100, two air-filling and air-sucking devices 200, a cargo platform 300, two propelling devices 400 and a landing gear 500, wherein the two air-filling and air-sucking devices 200 are symmetrically arranged on two sides of the airship hull 100, the cargo platform 300 is arranged on the lower part of the airship hull 100, the two propelling devices 400 are symmetrically arranged on the side part of the airship hull 100, and the landing gear 500 is arranged on the lower part of the airship hull 100, wherein:

the airship hull 100 comprises a fixed wing hull 110 and two telescopic wing variant assemblies 120, wherein the two telescopic wing variant assemblies 120 are respectively installed on two sides of the fixed wing hull 110;

the loading platform 300 comprises two connecting rods 310 and a placing plate 320, wherein the two connecting rods 310 are both installed at the lower part of the fixed wing-shaped hull 110, the placing plate 320 is installed at the lower part of the two connecting rods 310, and the placing plate 320 is arranged in a strip block shape and plays a role in bearing and placing articles;

the propulsion device 400 comprises a propulsion motor 410, a driving shaft 420 and a blade 430, wherein the propulsion motor 410 is mounted inside the fixed wing-shaped hull 110 through a propulsion motor base 440, the driving shaft 420 penetrates through the side wall of the fixed wing-shaped hull 110, the driving shaft 420 is in transmission connection with the output end of the propulsion motor 410, the blade 430 is mounted on the side part of the driving shaft 420, and the driving shaft 420 and the blade 430 are driven to rotate by the operation of the propulsion motor 410 to provide power, so that the position of the aircraft at high altitude is changed;

the landing gear 500 includes two first support frames 510, two second support frames 520, two first rollers 530 and two second rollers 540, the two first support frames 510 are respectively installed at the lower portions of the two telescopic wing profile variant assemblies 120, the two first rollers 530 are respectively rotatably installed at the lower portions of the two first support frames 510, the second support frame 520 is installed at the lower portion of the fixed wing profile hull 110, the two second rollers 540 are respectively rotatably installed at both sides of the lower portion of the second support frame 520, and the two first rollers 530 and the two second rollers 540 serve as good supports, so that the aircraft can be stably placed on the ground.

Specifically, fixed wing section hull 110 includes a plurality of solar cell panel 111, hull gasbag 112 and hull skeleton 113, the outside of hull gasbag 112 cladding and hull skeleton 113, a plurality of solar cell panel 111 are all installed in the upper portion of hull gasbag 112, be clearance fit between every solar cell panel 111, solar cell panel 111 is used for receiving illumination, provide the required electric power of whole operation, clearance fit's solar cell panel 111 can prevent to damage because hull gasbag 112 that solar cell panel 111 temperature risees and lead to.

Specifically, the hull framework 113 includes a fixed central rib 1131, a plurality of bladder support rods 1132, fixed side ribs 1133, a fixed wing-shaped tail rod 1134 and a wing-shaped stiffener shell 1135, the fixed side wing ribs 1133 are symmetrically disposed on two sides of the fixed central rib 1131, the fixed central rib 1131 is connected with the fixed side wing ribs 1133 through the plurality of bladder support rods 1132, the fixed wing-shaped tail rod 1134 is installed on one side of the fixed central rib 1131, the side portion of the fixed wing-shaped tail rod 1134 is connected with one side of the fixed side wing rib 1133, the wing-shaped stiffener shell 1135 is installed on the other side of the fixed central rib 1131, the side portion of the wing-shaped stiffener shell 1135 is connected with the other side of the fixed side wing rib 1133, and the two connecting rods 310 are installed on the lower portion of the fixed central rib 1131.

Specifically, a plurality of fixed central rib reinforcing rods 11311 are installed on the inner side of the fixed central rib 1131, a plurality of first installation holes 11312 matched with the boat bag support rods 1132 are formed in the side portion of the fixed central rib 1131, a second installation hole 11313 matched with the airfoil reinforcing plate shell 1135 is formed in the side portion of the fixed central rib 1131, first lightening holes 11314 are formed in the upper portion of the fixed central rib 1131, the lower portion of the fixed central rib 1131 and the tail portion of the fixed central rib 1131, the fixed central rib reinforcing rods 11311 can enhance the strength stability of the fixed central rib 1131, and the weight of the fixed central rib 1131 is reduced on the basis that the first lightening holes 11314 achieve sufficient strength.

Specifically, a plurality of fixed side rib stiffeners 11331 are installed inside the fixed side rib 1133, the fixed side rib stiffeners 11331 enhance the strength and stability of the fixed side rib 1133, a plurality of third mounting holes 11332 matched with the boat bag support rods 1132 are formed in the side portion of the fixed side rib 1133, a fourth mounting hole 11333 matched with the airfoil stiffener shell 1135 is formed in the side portion of the fixed side rib 1133, the upper portion of the fixed side rib 1133, the lower part of the fixed side wing rib 1133 and the tail part of the fixed side wing rib 1133 are both provided with a second lightening hole 11334, the second lightening hole 11334 reduces the weight of the fixed side wing rib 1133, the propulsion motor base 440 is mounted at the side part of the fixed side wing rib 1133, the air charging and sucking device 200 is mounted at the lower part of the fixed side wing rib 1133, the side part of the fixed side wing rib 1133 is provided with an air charging and sucking hole 11335 matched with the air charging and sucking device 200, and the air charging and sucking hole 11335 is used for being connected with the air charging and sucking device 200 to perform an air suction process.

Specifically, the telescopic wing profile variant assembly 120 includes a connecting rib assembly 121, a plurality of telescopic ribs 122 and a plurality of telescopic variant mechanisms 123, the connecting rib assembly 121 is installed at the side of the fixed side rib 1133, the telescopic ribs 122 are connected with the connecting rib assembly 121 through the telescopic variant mechanisms 123, and the plurality of telescopic ribs 122 are connected through the telescopic variant mechanisms 123.

Specifically, the connecting rib assembly 121 includes a connecting rib 1211, a telescopic motor 1212, a driving screw 1213 and a telescopic guide bar 1214, a telescopic motor mount 1215 is installed inside the connecting rib 1211, a first slideway 1216 matched with the telescopic guide bar 1214 is installed inside the connecting rib 1211, the telescopic motor 1212 is fixed inside the telescopic motor mount 1215 through a telescopic motor mount end cap 1217, an output end of the telescopic motor 1212 is connected with the driving screw 1213 through a coupler 1218, one end of the driving screw 1213 is connected with the telescopic rib 122 located on the outermost side, the telescopic guide bar 1214 is slidably sleeved inside the first slideway 1216, and one end of the telescopic guide bar 1214 is connected with the telescopic rib 122 located on the outermost side.

Specifically, a second slide channel 11336 matched with the telescopic guide bar 1214 is installed inside the fixed wing rib 1133, a connecting block 11337 matched with the driving screw 1213 is installed inside the fixed wing rib 1133, and a fifth mounting hole 11338 matched with the driving screw 1213 is formed in the middle of the connecting block 11337.

Specifically, a telescopic rib reinforcing rod 1221 is installed inside the telescopic rib 122, a sixth installation hole 1222 matched with the telescopic variant mechanism 123 is installed on the side of the telescopic rib 122, a third lightening hole 1223 is formed in the tail of the telescopic rib 122, and the telescopic rib 122, the connecting rib 1211, the fixed wing rib 1133 and the fixed central rib 1131 are in the same wing shape.

Specifically, the telescopic variant mechanism 123 includes two mounting heads 1231, a connecting rod 1232, two connecting rod rotating pins 1233, two rocker arms 1234 and two rocker arm rotating pins 1235, the two mounting heads 1231 are respectively hinged to one side of the two rocker arms 1234 through the rocker arm rotating pins 1235, and the other sides of the two rocker arms 1234 are respectively connected to the connecting rod 1232 through the connecting rod rotating pins 1233.

It should be noted that the specific models of the propulsion motor 410 and the telescoping motor 1212 are determined by calculating the size of the whole device and the size of the corresponding components; the air charging and sucking device 200 adopts a currently mature helium air charging and sucking device; the power supply principle of the solar panel 111 is the existing mature technology and will not be described in detail herein.

The working principle is as follows: when in use, the driving screw 1213 is driven to rotate by the operation of the telescopic motor 1212, so that the driving screw 1213 drives the plurality of telescopic ribs 122 to unfold, thereby adjusting the structure of the inner space of the aircraft, the telescopic wing-type variant component 120 can be telescopic according to the actual requirement, further can adjust corresponding working conditions according to actual conditions, can control the lifting without an auxiliary air bag, the whole navigation time, the load capacity and the high-altitude residence time are increased, the use is more convenient, the electric energy is provided by the solar cell panel 111, the aircraft is placed on a runway or a relatively flat ground, the propulsion motor 410 and the air charging and sucking device 200 are operated, the driving shaft 420 and the blades 430 are driven to rotate by the operation of the propulsion motor 410, the helium is charged into the airship hull 100 by the air charging and sucking device 200, and the aircraft takes off under the buoyancy provided by the helium and the power provided by the blades 430.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.