CN210942215U

CN210942215U - Civil light aircraft

Info

Publication number: CN210942215U
Application number: CN201921655513.0U
Authority: CN
Inventors: 纪东伟; 荆大庆
Original assignee: Zhuhai Technician College (zhuhai Senior Technical School)
Current assignee: Zhuhai Technician College (zhuhai Senior Technical School)
Priority date: 2019-09-30
Filing date: 2019-09-30
Publication date: 2020-07-07
Anticipated expiration: 2029-09-30

Abstract

The utility model relates to a civil lightweight aircraft, which comprises an aircraft main body and an aircraft power system, wherein the aircraft main body is in a bat shape and comprises a fuselage and wings; an annular through groove is formed in the middle of the machine body, a fixed seat is arranged in the through groove, and the fixed seat is connected with the machine body; the number of the wings is two, and the two wings are fixed to the end surfaces of the two sides of the fuselage; the power system comprises a driving unit and two groups of transmission units, the transmission units are arranged on two sides of the machine body respectively, the driving unit is arranged in the fixed seat, output shafts are arranged inside two sides of the machine body respectively, and the output shafts are used for connecting the transmission units and the driving unit. The utility model discloses an aircraft forces two screws to rotate along with the casing through the rotational speed of two motors in the adjustment aircraft fuselage, and steering angle is unrestricted, has increased the posture control means of aircraft, and to a great extent has improved the adaptability of aircraft to the environment.

Description

Civil light aircraft

Technical Field

The utility model relates to an aircraft technical field especially relates to a civilian lightweight aircraft.

Background

At present, the unmanned aerial vehicle is widely applied in the fields of aerial photography, agriculture, plant protection, self-shooting, express transportation, disaster rescue and the like, the use of the unmanned aerial vehicle is greatly improved, but the existing main rotor of the helicopter structurally can realize attitude control in a zero-speed state, but the range is lower, and the propeller fixed wing aircraft can be in the danger of stalling in a low-speed state. And even the output of the rotor system of the helicopter, which can change the volume in the sector area, can not ensure that the helicopter can take off and land on a slope with larger gradient in a harsh environment.

Disclosure of Invention

The utility model discloses a solve the problem that can not VTOL, environmental suitability is poor among the prior art, provide an unmanned aerial vehicle that makes things convenient for VTOL, environmental suitability is good.

In order to realize the purpose, the technical scheme of the utility model is that:

a civil lightweight aircraft comprises an aircraft main body and an aircraft power system, wherein the aircraft main body is of a batwing-shaped structure and comprises an airframe and wings, the front end and the rear end of the airframe are of V-shaped structures, the middle part of the airframe is a rectangular plate body, and the front end and the rear end of the airframe are in smooth transition to the middle part of the airframe; an annular through groove is formed in the middle of the machine body, a fixing seat which is hollow inside is arranged in the through groove, and the fixing seat is connected with the machine body; the number of the wings is two, and the two wings are fixed to the end surfaces of the two sides of the fuselage; the single wing comprises a plurality of fins, the single fin is in a spindle shape, and the plurality of fins are fixedly connected in sequence;

the power system comprises a driving unit and two groups of transmission units, the two groups of transmission units are respectively arranged on two sides of the fuselage, each transmission unit comprises a motor, two output shafts and two power output devices, the motors are fixed inside the joints of the wings and the fuselage, the power output devices are connected with the motors, one end of each output shaft is connected with the power output device, and the other end of each output shaft penetrates through a through groove of the fuselage and is arranged in the fixed seat; the drive unit includes power conversion device and rotor device, power conversion device sets up in the fixing base, power conversion device includes third bevel gear and fourth bevel gear, third bevel gear and fourth bevel gear are two, and third bevel gear and fourth bevel gear are the cross and lay, two the third bevel gear sets up relatively, the third bevel gear meshes rather than the fourth bevel gear of both sides, the third bevel gear is fixed in the output shaft tip, fourth bevel gear is connected with the transmission shaft, the transmission shaft is connected with the rotor device.

Furthermore, a connecting rod is obliquely arranged in the wing, a through hole is formed in each fin, and the connecting rod sequentially penetrates through the through holes in the fins to fixedly connect the fins.

Further, the area of one of the two adjacent fins is smaller than that of the other fin.

Further, the fixing base includes casing and sleeve pipe, casing and sleeve pipe are the cavity body, the sleeve pipe is two, singly sleeve pipe one end and casing intercommunication, the other end pass the fuselage and set up in motor one side, the output shaft sets up in the sleeve pipe.

Further, the power output device comprises a first bevel gear and a second bevel gear, the first bevel gear is fixedly connected with the motor, the second bevel gear is fixed at the end part of the output shaft, and the first bevel gear is meshed with the second bevel gear.

Furthermore, the power conversion device also comprises two bearings, wherein the single bearing is sleeved on the outer wall of the transmission shaft and is fixedly connected with the fixed seat.

Further, the rotor wing device comprises a rotor wing hinge and blades, the rotor wing hinge is fixedly connected with the transmission shaft, and the blades are connected to two ends of the rotor wing hinge.

Furthermore, the transmission shaft is connected with an inclined disc, and the inclined disc is respectively connected with the power conversion device and the rotor wing device.

Through the technical scheme, the beneficial effects of the utility model are that:

the utility model discloses driving system simple structure, compactness realize through the speed difference of the driving system's of two sets of drive unit and drive unit realization aircraft normal operating simultaneously through the motor of two sets of drive unit and realize that the rotor device rotates along with the fixing base, and steering angle is unrestricted, has increased the gesture adjustment means of aircraft, and to a great extent has improved the adaptability of aircraft to the environment.

The main body of the aircraft is bat-shaped, the front end and the rear end of the aircraft body are both V-shaped structures, and the front end and the rear end of the aircraft body are both smoothly transited to the middle part of the aircraft body; the wind resistance of the fuselage in the flight process is reduced, the wings are formed by a plurality of fusiform fins, and the fins are connected through connecting rods which are obliquely arranged, so that the strength and the stability of the wings are improved.

Drawings

Fig. 1 is a schematic structural diagram of the civil portable aircraft.

Fig. 2 is a schematic top view of the civil portable aircraft.

Fig. 3 is an exploded view of the civil portable aircraft of the present invention.

Fig. 4 is an enlarged structural view of the civil portable aircraft at a position in fig. 3.

Fig. 5 is an enlarged structural view of the civil portable aircraft at the position B in fig. 3.

Fig. 6 is a schematic structural diagram of a driving unit of the civil portable aircraft.

Figure 7 is the internal section view of the power fixing seat of the civil portable aircraft.

Fig. 8 is a power system schematic diagram of the civil portable aircraft.

Fig. 9 is a schematic structural diagram of a single fin of the civil lightweight aircraft.

The reference numbers in the drawings are as follows: the aircraft comprises a fuselage 1, wings 2, a handle 3, a sleeve 4, blades 5, a through groove 6, a rotor twist 7, a tilting disk 8, fins 9, a shell 10, a motor base 11, a motor 12, a second bevel gear 13, a first bevel gear 14, an output shaft 16, a third bevel gear 17, a fourth bevel gear 18, a transmission shaft 19, a through hole 20 and a bearing 21.

Detailed Description

The invention will be further described with reference to the accompanying drawings and specific embodiments:

as shown in fig. 1 to 9, a civil lightweight aircraft comprises an aircraft main body and an aircraft power system, wherein the aircraft main body is of a batwing-shaped structure, the aircraft main body comprises a fuselage 1 and wings 2, the front end and the rear end of the fuselage 1 are of a V-shaped structure, the wind resistance of the fuselage 1 in the flight process is reduced, the middle of the fuselage 1 is a rectangular plate body, and the front end and the rear end of the fuselage 1 are in smooth transition to the middle of the fuselage 1.

An annular through groove 6 is formed in the middle of the machine body 1, a fixing seat with a hollow interior is arranged in the through groove 6, and the fixing seat is connected with the machine body 1; specifically, the fixing base includes casing 10 and sleeve pipe 4, casing 10 is the cavity body with sleeve pipe 4, sleeve pipe 4 is two, singly 4 one end of sleeve pipe and 10 intercommunication, the other end pass fuselage 1 and set up in motor 12 one side,

casing

10 and 4 threaded connection of sleeve pipe.

The number of the wings 2 is two, and the two wings 2 are fixed to the end surfaces of the two sides of the fuselage 1; the single wing 2 comprises a plurality of fins 9, the single fin 9 is in a spindle shape, and the plurality of fins 9 are fixedly connected in sequence; one of the fins 9 of the adjacent two fins 9 has an area smaller than that of the other fin 9. Fusiform design makes fin 9 form streamlined structure after fixed connection in order, reduces the windage, improves unmanned aerial vehicle's portability. The connecting rods are obliquely arranged in the wings 2, the through holes 20 are formed in the single fins 9, the connecting rods sequentially penetrate through the through holes 20 in the multiple fins 9 to fixedly connect the multiple fins 9, and the stability of the wings 2 is improved.

The power system comprises a driving unit and two groups of transmission units. The two groups of transmission units are respectively arranged on two sides of the fuselage 1, each transmission unit comprises a motor 12, an output shaft 16 and a power output device, the motors 12 are fixed inside the joints of the wings 2 and the fuselage 1, the

motors

12 and 11 are arranged inside the joints of the wings 2 and the fuselage 1, and the motors 12 are fixed on the

motors

12 and 11; the power output device is connected with the motor 12, the number of the output shafts 16 is two, one end of each output shaft 16 is connected with the power output device, and the other end of each output shaft 16 penetrates through the through groove 6 of the machine body 1 and is arranged in the fixed seat; the output shaft 16 is disposed within the sleeve 4. The power output device comprises a first bevel gear 14 and a second bevel gear 13, the first bevel gear 14 is fixedly connected with the motor 12, the second bevel gear 13 is fixed at the end part of the output shaft 16, and the first bevel gear 14 is meshed with the second bevel gear 13.

The drive unit includes power conversion device and rotor device, power conversion device sets up in the fixing base, power conversion device includes third bevel gear 17, fourth bevel gear 18 and bearing 21, third bevel gear 17 is two with fourth bevel gear 18, and third bevel gear 17 is the cross with fourth bevel gear 18 and lays, two third bevel gear 17 sets up relatively, third bevel gear 17 meshes with the fourth bevel gear 18 of its both sides, third bevel gear 17 is fixed in the 16 tip of output shaft, fourth bevel gear 18 is connected with transmission shaft 19, transmission shaft 19 is connected with the rotor device. The power conversion device comprises a third bevel gear 17, a fourth bevel gear 18 and two bearings 21, wherein the single bearing 21 is sleeved on the outer wall of the transmission shaft 19, and the bearing 21 is fixedly connected with the fixed seat. The rotor wing device comprises a rotor wing hinge 7 and blades 5, the rotor wing hinge 7 is fixedly connected with the transmission shaft 19, and the blades 5 are connected to two ends of the rotor wing hinge 7.

In order to further optimize the product structure, be connected with swash plate 8 on the transmission shaft 19, swash plate 8 is connected with power conversion device and rotor device respectively, and the inclination of swash plate 8 control rotor, swash plate 8 provide a periodic displacement for driving system, work as the utility model discloses when changing to horizontal flight from VTOL, inside power conversion device converts driving system to flight state.

When the aircraft takes off and lands, two groups of rotor wing devices of the power system are parallel to each other and are started; the motors 12 of the two sets of transmission units are started to rotate the power output device, the power output device transmits power to the driving unit through the output shaft 16, and the driving unit moves to enable the rotor wing device to rotate for taking off and landing.

In actual flight of the aircraft, the rotating speeds of the two motors 12 of the power system of the aircraft are the same in magnitude but opposite in direction, the rotating speeds of the two third bevel gears 17 and the two fourth bevel gears 18 of the power conversion device in the driving unit are the same in magnitude, the rotating directions of the blades 5 in the two rotor wing devices are opposite in direction, and the blades and the fourth bevel gears and the third bevel gears and the fourth bevel gears cooperate to provide lift force for the aircraft.

When the aircraft is changed from horizontal lifting to vertical lifting, the rotating speeds of the two motors 12 are different, so that the rotating speeds of the two third bevel gears 17 are different, one first bevel gear 14 forces the corresponding transmission shaft 19 to generate acting force along the circumferential direction of the output shaft 16, the two acting forces are mutually overlapped to drive the fixed seat to rotate, and the two rotor wing devices rotate along with the fixed seat, so that the angle of the aircraft rotor wing devices is adjusted.

The above-mentioned embodiments are merely preferred embodiments of the present invention, and not intended to limit the scope of the present invention, so that equivalent changes or modifications made by the structure, features and principles of the present invention should be included in the claims of the present invention.

Claims

1. A civil lightweight aircraft comprises an aircraft main body and an aircraft power system, and is characterized in that the aircraft main body is of a batwing-shaped structure and comprises an aircraft body (1) and wings (2), the front end and the rear end of the aircraft body (1) are of V-shaped structures, the middle part of the aircraft body (1) is a rectangular plate body, and the front end and the rear end of the aircraft body (1) are in smooth transition to the middle part of the aircraft body (1); an annular through groove (6) is formed in the middle of the machine body (1), a fixing seat with a hollow interior is arranged in the through groove (6), and the fixing seat is connected with the machine body (1); the number of the wings (2) is two, and the two wings (2) are fixed to the end surfaces of the two sides of the fuselage (1); the single wing (2) comprises a plurality of fins (9), the single fin (9) is in a spindle shape, and the plurality of fins (9) are fixedly connected in sequence;

the power system comprises a driving unit and two groups of transmission units, wherein the two groups of transmission units are respectively arranged on two sides of the airframe (1), each transmission unit comprises a motor (12), an output shaft (16) and a power output device, the motors (12) are fixed inside the connection part of the wings (2) and the airframe (1), the power output devices are connected with the motors (12), the number of the output shafts (16) is two, one end of each output shaft (16) is connected with the power output device, and the other end of each output shaft penetrates through a through groove (6) of the airframe (1) and is arranged in a fixed seat; the drive unit comprises a power conversion device and a rotor wing device, the power conversion device is arranged in the fixed seat, the power conversion device comprises a third bevel gear (17) and a fourth bevel gear (18), the third bevel gear (17) and the fourth bevel gear (18) are two, the third bevel gear (17) and the fourth bevel gear (18) are arranged in a cross shape, the third bevel gear (17) is arranged oppositely, the third bevel gear (17) is meshed with the fourth bevel gears (18) on two sides of the third bevel gear (17), the third bevel gear (17) is fixed at the end part of the output shaft (16), the fourth bevel gear (18) is connected with a transmission shaft (19), and the transmission shaft (19) is connected with the rotor wing device.

2. The civil portable aircraft according to claim 1, characterized in that the wings (2) are provided with connecting rods in an inclined manner, through holes (20) are provided on the single fins (9), and the connecting rods sequentially penetrate through the through holes (20) on the plurality of fins (9) to fixedly connect the plurality of fins (9).

3. Civil light aircraft according to claim 1, characterized in that one (9) of the two adjacent fins (9) has a smaller area than the other fin (9).

4. The civil light aircraft as claimed in claim 1, wherein the fixing seat comprises a shell (10) and two sleeves (4), the shell (10) and the sleeves (4) are hollow tubes, one end of each single sleeve (4) is communicated with the shell (10), the other end of each single sleeve (4) penetrates through the aircraft body (1) and is arranged on one side of the motor (12), and the output shaft (16) is arranged in the sleeve (4).

5. The civil light aircraft as claimed in claim 1, wherein the power output device comprises a first bevel gear (14) and a second bevel gear (13), the first bevel gear (14) is fixedly connected with the motor (12), the second bevel gear (13) is fixed at the end of the output shaft (16), and the first bevel gear (14) is meshed with the second bevel gear (13).

6. The civil light aircraft as claimed in claim 1, wherein the power conversion device further comprises two bearings (21), a single bearing (21) is sleeved on the outer wall of the transmission shaft (19), and the bearing (21) is fixedly connected with the fixed seat.

7. The civil lightweight aircraft according to claim 1, characterized in that the rotor device comprises a rotor winch (7) and blades (5), the rotor winch (7) is fixedly connected with a transmission shaft (19), and the blades (5) are connected to both ends of the rotor winch (7).

8. Civil light aircraft according to claim 1, characterized in that a tilting disk (8) is connected to the transmission shaft (19), the tilting disk (8) being connected to the power conversion means and to the rotor means, respectively.