阅读说明：本技术 一种太阳能与空气能复合飞行器 (Solar energy and air energy composite aircraft ) 是由 周启凤 于 2020-04-03 设计创作，主要内容包括：本发明公开了一种太阳能与空气能复合飞行器,当所述太阳能与空气能复合飞行器转弯减速时,由所述关节轴承带动作轴向圆周摆动,对所述第二活塞施加水平推力,驱使所述减震弹簧吸收所述第二活塞带来的压力,同时所述第二活塞对所述第一气缸传递压力,驱使所述第一气缸朝向所述第一活塞的方向挤压内部的气体对冲击进行减缓,位于所述机体相对一侧的所述第一气缸通过所述阻尼控制阀吸入气体,减缓所述第一气缸与所述第一活塞的分离速度,进而抑制所述减震弹簧吸收压力后反弹的振动,如此能在飞行器进行转向减速时,减小载重物的惯性对所述机体带来的冲击,进而使飞行器保持平稳飞行。(The invention discloses a solar energy and air energy composite aircraft, when the solar energy and air energy composite aircraft turns and decelerates, the solar energy and air energy composite aircraft is driven by a joint bearing to axially and circumferentially swing, exerting horizontal thrust on the second piston to drive the damping spring to absorb pressure brought by the second piston, meanwhile, the second piston transmits pressure to the first cylinder to drive the first cylinder to extrude the gas in the first cylinder towards the direction of the first piston to reduce impact, the first cylinder on the opposite side of the machine body sucks gas through the damping control valve to reduce the separation speed of the first cylinder and the first piston, and further the vibration rebounded after the damping spring absorbs the pressure is inhibited, so that when the aircraft is steered and decelerated, the impact of the inertia of the load on the aircraft body is reduced, and the aircraft can fly stably.)

1. A solar energy and air energy composite aircraft is characterized by comprising an aircraft body, a connecting arm, a carrying box, a connecting arm damping device and an aircraft body damping device;

the connecting arms are connected with the machine body in a sliding mode, the connecting arms are multiple in number and are respectively located on two sides of the machine body, the carrying boxes are matched with the connecting arms and are located at one ends, far away from the machine body, of the connecting arms, the connecting arm damping devices are connected with the machine body in a sliding mode, fixedly connected with the connecting arms and located between the machine body and the connecting arms, and the machine body damping devices are connected with the machine body in a sliding mode, fixedly connected with the connecting arm damping devices and located at one ends, far away from the connecting arms, of the machine body;

the connecting arm shock absorption device comprises a damper and a shock absorption spring, wherein the damper is connected with the machine body in a sliding mode and is positioned at one end, far away from the connecting arm, of the machine body; the damping spring is abutted against the damper, fixedly connected with the connecting arm and positioned between the damper and the connecting arm;

the damper comprises a first piston and a first cylinder, the first piston is fixedly connected with the machine body, is positioned on one side of the machine body close to the connecting arm, is far away from the connecting arm and faces the connecting arm; the first cylinder is connected with the machine body in a sliding mode, connected with the first piston in a sliding mode and abutted against the damping spring, and the first cylinder is located between the damping spring and the first piston.

2. The composite solar and air energy aircraft of claim 1,

the damper further comprises a damping control valve, wherein the damping control valve is fixedly connected with the first air cylinder, is positioned in the first air cylinder, is close to the first piston and faces the direction of the first piston.

3. The solar-air hybrid aircraft of claim 2,

the connecting arm damping device further comprises a second cylinder and a second piston, the second cylinder is connected with the first cylinder in a sliding mode, is abutted against the damping spring, and is arranged around the periphery of the first cylinder and faces the direction of the connecting arm; the second piston is connected with the second cylinder in a sliding mode, fixedly connected with the damping spring and fixedly connected with the connecting arm, and located between the damping spring and the connecting arm and between the first cylinder and the second cylinder.

4. The solar-air hybrid aircraft of claim 3,

the connecting arm damping device further comprises a joint bearing, the joint bearing is rotatably connected with the second piston, fixedly connected with the connecting arm and located on one side, far away from the machine body, of the second piston.

5. The composite solar and air energy aircraft of claim 4,

the machine body is provided with a sliding chute which is positioned inside the machine body; the machine body damping device comprises a sliding block and a damping component, the sliding block is connected with the machine body in a sliding mode, fixedly connected with the first piston and located in the sliding groove, and the damping component is connected with the machine body in a sliding mode, elastically connected with the sliding block and located between the sliding block and the machine body.

6. The composite solar and air energy aircraft of claim 5,

the damping assembly comprises an expansion spring and a third air cylinder, the expansion spring is abutted with the sliding block and the machine body and is positioned between the sliding block and the machine body; the third cylinder with the organism slides to with expanding spring butt, and be located the organism with between the expanding spring.

7. The composite solar and air energy aircraft of claim 6,

the machine body is also provided with a connecting groove, and the connecting groove is positioned on one side of the machine body close to the connecting arm, extends into the machine body and is communicated with the sliding groove; and the damping assembly further comprises a rotary bearing, the rotary bearing is fixedly connected with the second cylinder, is rotatably connected with the machine body and is positioned in the connecting groove.

8. The composite solar and air energy aircraft of claim 1,

the solar energy and air energy composite aircraft further comprises an air suction device and a recoil spray head, wherein the air suction device is fixedly connected with the carrying box and is positioned on one side of the carrying box, which is close to the connecting arm; the recoil sprayer is fixedly connected with the air suction device, is positioned on one side of the air suction device, which is far away from the carrying box, and faces the direction far away from the carrying box.

9. The composite solar and air energy aircraft of claim 8,

the air suction device comprises a compression air cylinder and an injection valve, the compression air cylinder is fixedly connected with the carrying box and fixedly connected with the recoil spray head, the compression air cylinder is positioned on one side of the carrying box close to the connecting arm, and the recoil spray head is communicated with the compression air cylinder; the injection valve is fixedly connected with the compression cylinder, is communicated with the compression cylinder, is positioned on the periphery of the compression cylinder and is far away from the carrying box.

10. The composite solar and air energy aircraft of claim 9,

solar energy and air can compound aircraft still include solar panel, solar panel with organism fixed connection, and with compression cylinder passes through the wire and connects, and is located the organism is kept away from carry one side of thing case.

Technical Field

The invention relates to the technical field of aircrafts, in particular to a solar energy and air energy composite aircraft.

Background

With the continuous development of science and technology, the aircraft technology is greatly improved in recent years, and a plurality of intelligent and multifunctional unmanned aircraft appear. In order to meet the requirements of information transmission, monitoring and the like in some small-range areas, the unmanned aerial vehicle is increasingly emphasized. The aircraft is a new concept aircraft in rapid development, and has the advantages of flexibility, quick response, unmanned flight and low operation requirement. The aircraft can realize the functions of real-time image transmission and high-risk area detection by carrying various sensors, and is a favorable supplement for satellite remote sensing and traditional aviation remote sensing. At present, the application range of unmanned aircrafts is widened to three fields of military affairs, scientific research and civil use, and the unmanned aircrafts are particularly widely applied to the fields of electric power, communication, weather, agriculture, ocean, exploration, photography, disaster prevention and reduction, crop yield estimation, drug control and smuggling, border patrol, public security and counter terrorism and the like.

With the rapid development of internet technology, online shopping becomes a choice of more and more people, and along with the rapid development of express delivery business. The discovery in the research of online shopping commodities shows that most parcels are light-weight small parcels, the small parcels are not heavy medium parcels, the heavy large-size parcels are few, how to quickly and safely send the medium and small parcels to customers, and the satisfaction of the vast customers is obtained.

After the express aircraft clamps the parcel load through the connecting arm, take off, turn, scram and other actions can all cause the inertial motion of parcel, and then produce certain reaction force to the express aircraft, make the flight of express aircraft unstable, lead to the express aircraft to collide with object on every side easily, cause the incident.

Disclosure of Invention

The invention aims to provide a solar energy and air energy composite aircraft, and aims to solve the technical problems that after a parcel load is clamped by a connecting arm, actions such as take-off, turning, sudden stop and the like of an express aircraft in the prior art can cause inertial motion of the parcel, the express aircraft flies unstably, and the express aircraft collides with surrounding objects easily to cause safety accidents.

In order to achieve the purpose, the solar energy and air energy composite aircraft comprises an aircraft body, a connecting arm, a carrying box, a connecting arm damping device and an aircraft body damping device, wherein the connecting arm is connected with the aircraft body; the connecting arms are connected with the machine body in a sliding mode, the connecting arms are multiple in number and are respectively located on two sides of the machine body, the carrying boxes are matched with the connecting arms and are located at one ends, far away from the machine body, of the connecting arms, the connecting arm damping devices are connected with the machine body in a sliding mode, fixedly connected with the connecting arms and located between the machine body and the connecting arms, and the machine body damping devices are connected with the machine body in a sliding mode, fixedly connected with the connecting arm damping devices and located at one ends, far away from the connecting arms, of the machine body; the connecting arm shock absorption device comprises a damper and a shock absorption spring, wherein the damper is connected with the machine body in a sliding mode and is positioned at one end, far away from the connecting arm, of the machine body; the damping spring is abutted against the damper, fixedly connected with the connecting arm and positioned between the damper and the connecting arm; the damper comprises a first piston and a first cylinder, the first piston is fixedly connected with the machine body, is positioned on one side of the machine body close to the connecting arm, is far away from the connecting arm and faces the connecting arm; the first cylinder is connected with the machine body in a sliding mode, connected with the first piston in a sliding mode and abutted against the damping spring, and the first cylinder is located between the damping spring and the first piston.

The damper further comprises a damping control valve, wherein the damping control valve is fixedly connected with the first air cylinder, is positioned in the first air cylinder, is close to the first piston and faces the direction of the first piston.

The connecting arm damping device further comprises a second cylinder and a second piston, wherein the second cylinder is connected with the first cylinder in a sliding mode, is abutted against the damping spring, is arranged around the periphery of the first cylinder and faces the direction of the connecting arm; the second piston is connected with the second cylinder in a sliding mode, fixedly connected with the damping spring and fixedly connected with the connecting arm, and located between the damping spring and the connecting arm and between the first cylinder and the second cylinder.

The connecting arm damping device further comprises a joint bearing, the joint bearing is rotatably connected with the second piston, fixedly connected with the connecting arm and located on one side, far away from the machine body, of the second piston.

The body is provided with a sliding chute which is positioned on the side surface of the body close to the connecting arm; the machine body damping device comprises a sliding block and a damping component, the sliding block is connected with the machine body in a sliding mode, fixedly connected with the first piston and located in the sliding groove, and the damping component is connected with the machine body in a sliding mode, elastically connected with the sliding block and located between the sliding block and the machine body.

The damping assembly comprises an expansion spring and a third air cylinder, the expansion spring is abutted with the sliding block and the machine body and is positioned between the sliding block and the machine body; the third cylinder with the organism slides to with expanding spring butt, and be located the organism with between the expanding spring.

The connecting mechanism comprises a connecting arm, a connecting groove and a connecting rod, wherein the connecting groove is arranged on one side of the machine body, which is close to the connecting arm, extends into the machine body and is communicated with the sliding groove; and the damping assembly further comprises a rotary bearing, the rotary bearing is fixedly connected with the second cylinder, is rotatably connected with the machine body and is positioned in the connecting groove.

The solar energy and air energy composite aircraft further comprises an air suction device and a recoil spray head, wherein the air suction device is fixedly connected with the carrying box and is positioned on one side of the carrying box, which is close to the connecting arm; the recoil sprayer is fixedly connected with the air suction device, is positioned on one side of the air suction device, which is far away from the carrying box, and faces the direction far away from the carrying box.

The air suction device comprises a compression air cylinder and an injection valve, the compression air cylinder is fixedly connected with the carrying box and fixedly connected with the recoil spray head, the compression air cylinder is positioned on one side of the carrying box close to the connecting arm, and the recoil spray head is communicated with the compression air cylinder; the injection valve is fixedly connected with the compression cylinder, is communicated with the compression cylinder, is positioned on the periphery of the compression cylinder and is far away from the carrying box.

The solar energy and air energy composite aircraft further comprises a solar panel, the solar panel is fixedly connected with the aircraft body, connected with the compression cylinder through a wire and located on one side of the aircraft carrier far away from the aircraft body.

According to the solar and air energy composite aircraft, when the solar and air energy composite aircraft turns and decelerates, the carrying box applies lateral pressure to the connecting arm to drive the connecting arm and the aircraft body to laterally displace, the joint bearing band acts to axially and circumferentially swing, horizontal thrust is applied to the second piston to drive the damping spring to absorb pressure brought by the second piston, meanwhile, the second piston transmits pressure to the first cylinder to drive the first cylinder to extrude gas inside towards the direction of the first piston to reduce impact, the first cylinder on the opposite side of the aircraft body sucks gas through the damping control valve to reduce the separation speed of the first cylinder and the first piston, and further the damping spring is inhibited from rebounding vibration after absorbing pressure, therefore, when the aircraft turns and decelerates, the impact of the inertia of the load on the aircraft body is reduced, and the aircraft can stably fly.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic representation of the flight of the cargo of the aircraft of the present invention.

Fig. 2 is a schematic structural view of the connecting arm damping device of the present invention.

Fig. 3 is a schematic structural view of the body damper of the present invention.

Fig. 4 is a schematic structural view of the rotary bearing of the present invention connecting the second cylinder and the housing.

Fig. 5 is a schematic structural view of an aircraft recoil unit of the present invention.

In the figure: 1-machine body, 2-connecting arm, 3-carrying box, 4-connecting arm damping device, 5-machine body damping device, 6-air suction device, 7-recoil sprayer, 8-solar panel, 11-chute, 12-connecting groove, 41-damper, 42-damping spring, 43-second cylinder, 44-second piston, 45-joint bearing, 51-slide block, 52-damping component, 61-compression cylinder, 62-injection valve, 100-solar energy and air energy composite aircraft, 411-first piston, 412-first cylinder, 413-damping control valve, 521-expansion spring, 522-third cylinder and 523-rotary bearing.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

In a first example of the present embodiment:

referring to fig. 1 and 2, the present invention provides a solar energy and air energy composite aircraft 100, which includes a body 1, a connecting arm 2, a carrying box 3, a connecting arm damping device 4 and a body damping device 5; the connecting arms 2 are connected with the machine body 1 in a sliding mode, the connecting arms are multiple in number and are respectively located on two sides of the machine body 1, the carrying boxes 3 are matched with the connecting arms 2 and located at one ends, far away from the machine body 1, of the connecting arms 2, the connecting arm shock absorption devices 4 are connected with the machine body 1 in a sliding mode, fixedly connected with the connecting arms 2 and located between the machine body 1 and the connecting arms 2, and the machine body shock absorption devices 5 are connected with the machine body 1 in a sliding mode, fixedly connected with the connecting arm shock absorption devices 4 and located at one ends, far away from the connecting arms 2, of the machine body 1; the connecting arm shock absorption device 4 comprises a damper 41 and a shock absorption spring 42, wherein the damper 41 is connected with the machine body 1 in a sliding manner and is positioned at one end of the machine body 1 away from the connecting arm 2; the damping spring 42 is abutted against the damper 41, fixedly connected with the connecting arm 2 and positioned between the damper 41 and the connecting arm 2; the damper 41 comprises a first piston 411 and a first cylinder 412, wherein the first piston 411 is fixedly connected with the machine body 1, is positioned on one side of the machine body 1 close to the connecting arm 2, and faces to the direction of the connecting arm 2; the first cylinder 412 is slidably connected to the machine body 1, slidably connected to the first piston 411, and abutted against the damping spring 42, and the first cylinder 412 is located between the damping spring 42 and the first piston 411.

Further, the damper 41 further includes a damping control valve 413, and the damping control valve 413 is fixedly connected to the first cylinder 412, located inside the first cylinder 412, close to the first piston 411, and facing the first piston 411.

Further, the connecting arm damping device 4 further includes a second cylinder 43 and a second piston 44, the second cylinder 43 is slidably connected to the first cylinder 412, abuts against the damping spring 42, and surrounds the outer periphery of the first cylinder 412 and faces the direction of the connecting arm 2; the second piston 44 is slidably connected to the second cylinder 43, fixedly connected to the damping spring 42, and fixedly connected to the connecting arm 2, and the second piston 44 is located between the damping spring 42 and the connecting arm 2, and between the first cylinder 412 and the second cylinder 43.

Further, the connecting arm damping device 4 further includes a joint bearing 45, and the joint bearing 45 is rotatably connected to the second piston 44, fixedly connected to the connecting arm 2, and located on a side of the second piston 44 away from the machine body 1.

In this embodiment, the internal of the machine body 1 is provided with a storage battery, the whole external structure is dragon-shaped, and has four rotor shafts distributed at four end portions of the machine body, the rotor at the end portion is driven to rotate by a motor on each rotor shaft, so as to generate thrust, the machine body 1 is internally provided with a plurality of components such as a signal receiver and a controller, so as to ensure the controllability and the anticollision of a flight path, the connecting arm 2 is an inverted L-shaped connecting arm 2, the horizontal section of the connecting arm 2 is fixed with the object carrying box 3 by threads and is fixed by a rotating bearing in the left-right sliding direction, the number of the connecting arms 2 is four, the left and the right are respectively provided with two connecting arms which are arranged oppositely, the vertical section of the connecting arm 2 is close to the machine body 1, the end portion of the connecting arm is connected with a buckle plate, and is detachably connected with the knuckle, the object box 3 is taken and placed by detaching the buckle plate of the connecting arm 2; the first piston 411 is fixed in a mounting groove inside the body 1. The first cylinder 412 is slidably connected with the first piston 411, the first piston 411 slides linearly in the first cylinder 412, a sealing gas is stored between the first piston 411 and the first cylinder 412 through the friction sliding of the rod head of the first piston 411 and the inner arm of the first cylinder 412, the second cylinder 43 is fixed with the mounting groove of the machine body 1, surrounds the outer surface of the first cylinder 412, is slidably connected with the first cylinder 412, the first cylinder 412 and the second cylinder 43 are communicated through the damping control valve 413, the first piston 411 presses the gas in the first cylinder 412 and enters the second cylinder 43 through the damping control valve 413, otherwise, the gas in the second cylinder 43 enters the first cylinder 412 through the damping control valve 413, the damping spring 42 is connected between the second cylinder 43 and the first cylinder 412, the damping spring 42 is connected with the bottom of the fixed second cylinder 43, the second piston 44 and the knuckle bearing 45 are connected between the damping spring 42 and the connecting arm 2, the second piston 44 is slidably connected with the inner wall of the second cylinder 43 and is entirely fixed on the spring surface of the damping spring 42, so that the force transmitted by the connecting arm 2 and the knuckle bearing 45 is uniformly distributed on the damping spring 42, the damping spring 42 is stressed more smoothly, the knuckle bearing 45 is rotatably connected with the second piston 44, the rotating direction is parallel to the side surface of the adjacent machine body 1, and the horizontal resistance of the machine body 1 and the second piston 44 to the connecting arm 2 is not applied when the carrier case 3 drives the connecting arm 2 to rotate, only rotates around the center line of the first cylinder 412, so that when the solar energy and air energy hybrid vehicle 100 turns and decelerates, the cargo box 3 applies lateral pressure to the connecting arm 2 to drive the connecting arm 2 and the body 1 to laterally displace, and is driven by the knuckle bearing 45 to swing, and applies horizontal thrust to the second piston 44 to drive the damping spring 42 to compress and absorb the pressure from the second piston 44, at the same time, the second piston 44 transmits pressure to the first cylinder 412 to drive the first cylinder 412 to press the gas inside towards the first piston 411, the impact is relieved by the process of pressing the gas, and the gas enters the second cylinder 43 through the damping control valve 413, and the first cylinder 412 on the opposite side of the body 1 sucks the gas through the damping control valve 413, the separation speed of the first cylinder 412 and the first piston 411 is slowed down, and then the vibration rebounded after the damping spring 42 absorbs the pressure is restrained, so that the impact of the inertia of a load on the machine body 1 can be reduced when the aircraft is steered and decelerated, and the aircraft can keep stable flight.

In a second example of the present embodiment:

referring to fig. 1 to 4, the present invention provides a solar energy and air energy composite aircraft 100, which includes a body 1, a connecting arm 2, a carrying box 3, a connecting arm damping device 4 and a body damping device 5; the connecting arms 2 are connected with the machine body 1 in a sliding mode, the connecting arms are multiple in number and are respectively located on two sides of the machine body 1, the carrying boxes 3 are matched with the connecting arms 2 and located at one ends, far away from the machine body 1, of the connecting arms 2, the connecting arm shock absorption devices 4 are connected with the machine body 1 in a sliding mode, fixedly connected with the connecting arms 2 and located between the machine body 1 and the connecting arms 2, and the machine body shock absorption devices 5 are connected with the machine body 1 in a sliding mode, fixedly connected with the connecting arm shock absorption devices 4 and located at one ends, far away from the connecting arms 2, of the machine body 1; the connecting arm shock absorption device 4 comprises a damper 41 and a shock absorption spring 42, wherein the damper 41 is connected with the machine body 1 in a sliding manner and is positioned at one end of the machine body 1 away from the connecting arm 2; the damping spring 42 is abutted against the damper 41, fixedly connected with the connecting arm 2 and positioned between the damper 41 and the connecting arm 2; the damper 41 comprises a first piston 411 and a first cylinder 412, wherein the first piston 411 is fixedly connected with the machine body 1, is positioned on one side of the machine body 1 close to the connecting arm 2, and faces to the direction of the connecting arm 2; the first cylinder 412 is slidably connected to the machine body 1, slidably connected to the first piston 411, and abutted against the damping spring 42, and the first cylinder 412 is located between the damping spring 42 and the first piston 411.

Further, the damper 41 further includes a damping control valve 413, and the damping control valve 413 is fixedly connected to the first cylinder 412, located inside the first cylinder 412, close to the first piston 411, and facing the first piston 411.

Further, the connecting arm damping device 4 further includes a second cylinder 43 and a second piston 44, the second cylinder 43 is slidably connected to the first cylinder 412, abuts against the damping spring 42, and surrounds the outer periphery of the first cylinder 412 and faces the direction of the connecting arm 2; the second piston 44 is slidably connected to the second cylinder 43, fixedly connected to the damping spring 42, and fixedly connected to the connecting arm 2, and the second piston 44 is located between the damping spring 42 and the connecting arm 2, and between the first cylinder 412 and the second cylinder 43.

Further, the connecting arm damping device 4 further includes a joint bearing 45, and the joint bearing 45 is rotatably connected to the second piston 44, fixedly connected to the connecting arm 2, and located on a side of the second piston 44 away from the machine body 1.

Further, the machine body 1 is provided with a sliding groove 11, and the sliding groove 11 is positioned on the side surface of the machine body 1 close to the connecting arm 2; the machine body damping device 5 comprises a sliding block 51 and a damping component 52, the sliding block 51 is connected with the machine body 1 in a sliding mode, fixedly connected with the first piston 411 and located inside the sliding groove 11, and the damping component 52 is connected with the machine body 1 in a sliding mode, elastically connected with the sliding block 51 and located between the sliding block 51 and the machine body 1.

Further, the damping assembly 52 includes a telescopic spring 521 and a third cylinder 522, the telescopic spring 521 abuts against the slider 51 and the machine body 1, and is located between the slider 51 and the machine body 1; the third cylinder 522 slides on the machine body 1, abuts against the extension spring 521, and is located between the machine body 1 and the extension spring 521.

Further, the machine body 1 further has a connecting groove 12, the connecting groove 12 is located on one side of the machine body 1 close to the connecting arm 2, extends into the machine body 1, and is communicated with the sliding groove 11; the damping component 52 further includes a rotary bearing 523, wherein the rotary bearing 523 is fixedly connected to the second cylinder 43, rotatably connected to the machine body 1, and located inside the connecting groove 12.

In this embodiment, the sliding chute 11 for the sliding block 51 to slide is arranged inside the machine body 1, the sliding block 51 is connected to the first piston 411 and the second cylinder 43 and drives the connecting arm 2 to horizontally slide, the third cylinders 522 are fixed to the front and rear sides of the sliding block 51, the sliding block 51 is connected to the third cylinders 522 in a sliding manner and can extend into the third cylinders 522, the expansion spring 521 is connected between the sliding block 51 and the third cylinders 522 and applies a resilience to the sliding block 51 and simultaneously extrudes the gas inside the third cylinders 522 to drive the third cylinders 522 to eject the gas from the side surface to decompress, so that when the solar energy and air energy hybrid aircraft 100 takes off and linearly decelerates, the cargo box 3 horizontally moves forward due to inertia, and further applies a forward thrust to the sliding block 51, the sliding block 51 is abutted against the telescopic spring 521, the sliding block 51 is decelerated and slides under the resilience force of the telescopic spring 521, and is connected with the third air cylinder 522 in a sliding manner, so that the gas in the third air cylinder 522 is extruded, the reaction force is applied to the sliding block 51, the sliding speed of the sliding block 51 is reduced, and the horizontal thrust force applied to the telescopic spring 521 is further reduced; the linking arm 2 passes through joint bearing 45 with the second cylinder 43 with the slider 51 is connected, and the second cylinder 43 runs through the spread groove 12, swivel bearing 523's inner shell with second cylinder 43 welded fastening, swivel bearing 523's shell with the lateral wall of spread groove 12 slides spacingly, swivel bearing 523 passes through ball connection inner shell and shell, and drives the second cylinder 43 with 2 rectilinear sliding of linking arm reduce the power of a plurality of directions is applyed to the aircraft to linking arm 2, and then makes the aircraft can fly steadily.

In a third example of the present embodiment:

referring to fig. 1, 2 and 5, the present invention provides a solar energy and air energy composite aircraft 100, which includes a body 1, a connecting arm 2, a carrying box 3, a connecting arm damping device 4 and a body damping device 5; the connecting arms 2 are connected with the machine body 1 in a sliding mode, the connecting arms are multiple in number and are respectively located on two sides of the machine body 1, the carrying boxes 3 are matched with the connecting arms 2 and located at one ends, far away from the machine body 1, of the connecting arms 2, the connecting arm shock absorption devices 4 are connected with the machine body 1 in a sliding mode, fixedly connected with the connecting arms 2 and located between the machine body 1 and the connecting arms 2, and the machine body shock absorption devices 5 are connected with the machine body 1 in a sliding mode, fixedly connected with the connecting arm shock absorption devices 4 and located at one ends, far away from the connecting arms 2, of the machine body 1; the connecting arm shock absorption device 4 comprises a damper 41 and a shock absorption spring 42, wherein the damper 41 is connected with the machine body 1 in a sliding manner and is positioned at one end of the machine body 1 away from the connecting arm 2; the damping spring 42 is abutted against the damper 41, fixedly connected with the connecting arm 2 and positioned between the damper 41 and the connecting arm 2; the damper 41 comprises a first piston 411 and a first cylinder 412, wherein the first piston 411 is fixedly connected with the machine body 1, is positioned on one side of the machine body 1 close to the connecting arm 2, and faces to the direction of the connecting arm 2; the first cylinder 412 is slidably connected to the machine body 1, slidably connected to the first piston 411, and abutted against the damping spring 42, and the first cylinder 412 is located between the damping spring 42 and the first piston 411.

Further, the solar energy and air energy composite aircraft 100 further comprises an air suction device 6 and a recoil spray head 7, wherein the air suction device 6 is fixedly connected with the carrying box 3 and is positioned on one side of the carrying box 3 close to the connecting arm 2; the recoil sprayer 7 is fixedly connected with the air suction device 6, is positioned on one side of the air suction device 6 far away from the carrying box 3 and faces the direction far away from the carrying box 3.

Further, the air suction device 6 comprises a compression cylinder 61 and an injection valve 62, the compression cylinder 61 is fixedly connected with the carrying box 3, is fixedly connected with the recoil sprayer 7, and is positioned on one side of the carrying box 3 close to the connecting arm 2, and the recoil sprayer 7 is communicated with the compression cylinder 61; the injection valve 62 is fixedly connected to the compression cylinder 61, penetrates the compression cylinder 61, is located on the outer periphery of the compression cylinder 61, and is far from the loading box 3.

Further, the solar energy and air energy composite aircraft 100 further comprises a solar panel 8, wherein the solar panel 8 is fixedly connected with the aircraft body 1, connected with the compression cylinder 61 through a wire and located on one side of the aircraft body 1 far away from the loading box 3.

In this embodiment, the solar panel 8 is screwed on the upper surface of the machine body 1 and located between four propellers, the solar panel 8 is a silicon crystal panel and converts solar energy into heat energy, and then converts the heat energy into electric energy by a solar cell and stores the electric energy in a storage battery, the compression cylinder 61 is screwed on four sides of the carrying box 3, the injection valve 62 is screwed on the outer side of the compression cylinder 61, the injection valve 62 is located on one side of the compression cylinder 61 close to the machine body 1 and faces the direction of the propellers of the machine body 1, so that more air enters the injection valve 62, the injection valve 62 is powered by the compression cylinder 61, the compression cylinder 61 is connected with the storage battery and powered on, so that the internal compressor works, so that air is sucked in a large amount by the injection valve 62 and is compressed and stored in the compression cylinder 61 rapidly, when the solar energy and air energy composite aircraft 100 receives a deceleration command through a radio, the recoil sprayer 7 with the same movement direction opens the valve to work, the compressed gas stored in the compressed air cylinder 61 is sprayed out through the recoil sprayer 7 and is sprayed out in the same direction of the movement direction, so that the carrying box 3 is subjected to a reaction force, and then a part of the inertia force of the carrying box 3 is offset, so that the carrying box 3 is stably decelerated, the influence on the aircraft is reduced, and the aircraft can stably fly.

While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.