CN213354817U - Inflatable suspension adjustable propeller azimuth aircraft - Google Patents

Abstract

The utility model provides an aerify adjustable propeller position aircraft of suspension, including organism, fixed mounting at the plenum box at organism top, fixed mounting be used for supplementary lift assembly of going up and down at the organism middle part at the wing subassembly that organism middle part power take off direction adjustable, fixed mounting can open and shut at the organism rear portion and fixed mounting, it has inert gas to fill in the plenum box. The utility model provides a helicopter energy resource consumption's big technical problem, produced the technological effect of practicing thrift the aircraft flight consumed the energy.

Description

Inflatable suspension adjustable propeller azimuth aircraft

Technical Field

The utility model relates to a flight vehicle technical field especially relates to an aerify adjustable propeller position aircraft of suspension.

Background

With the development of productivity and road traffic, more and more people buy automobiles for going out, and the early peak and the late peak often appear on the streets of a large city, so that the commuting time of going to work is increased, and the difficulty of road maintenance is increased; and the air is gone out and will be able to liberate road traffic, but current fixed wing aircraft can't realize the vertically and lift off and land, and the helicopter uses the screw as the power supply and goes up and down, all has the huge problem of energy consumption.

SUMMERY OF THE UTILITY MODEL

Not enough to exist among the prior art, the utility model provides an aerify adjustable propeller position aircraft of suspension, it has solved the big problem of helicopter energy resource consumption who exists among the prior art.

According to the utility model discloses an embodiment, an aerify adjustable propeller position aircraft of suspension, including organism, fixed mounting at the plenum box at organism top, fixed mounting at organism middle part power take off direction adjustable power component, the wing subassembly that fixed mounting can open and shut at the organism rear portion and the lifting unit that fixed mounting is used for supplementary lift at the organism middle part, it has inert gas to fill in the plenum box.

The technical principle of the utility model is that: the buoyancy of the aircraft is increased by filling inert gas in the inflation box, the power assembly capable of adjusting the power output direction realizes the multidirectional flight of the aircraft, the wings capable of being opened and closed reduce air resistance when the aircraft runs, and the lifting assembly and the power assemblies on two sides of the aircraft body form a triangular shape, so that the stable lifting of the aircraft body is realized.

Compared with the prior art, the utility model discloses following beneficial effect has: the technical problem of high energy consumption of the helicopter is solved by adopting the inflation boxes filled with inert gas, the power components with adjustable power output directions and the openable wings, and the technical effect of saving energy consumed by the flight of the helicopter is achieved.

Drawings

Fig. 1 is a front view of an embodiment of the present invention.

Fig. 2 is a schematic structural diagram of a retracted state of the wing assembly according to an embodiment of the present invention.

Fig. 3 is a schematic structural diagram of an opened state of a wing assembly according to an embodiment of the present invention.

Fig. 4 is a schematic diagram of a moving block structure in the embodiment of the present invention.

Fig. 5 is a schematic structural diagram of a power assembly according to an embodiment of the present invention.

Fig. 6 is a schematic structural view of the lifting assembly in the embodiment of the present invention.

In the above drawings: 10. a body; 20. a wing assembly; 21. a wing accommodating groove; 22. an airfoil; 23. a hinged end; 24. a rotating shaft; 25. a travel bar; 26. a drive member; 27. a telescopic rod; 28. a moving block; 29. a roller; 30. an air-filled tank; 40. a power assembly; 41. a turbo fan; 42. a commutation motor; 43. a reduction gearbox; 44. a drive shaft; 45. a first helical gear; 46. a second helical gear; 47. installing a box; 48. adjusting a direction shaft; 50. a tail assembly; 51. a main tail; 52. an auxiliary tail wing; 60. a bottom wheel; 70. a lifting assembly; 71. a lifting channel; 72. a lifting fan; 73. an electric telescopic rod; 74. a wind deflector; 75. aerofoil slide.

Detailed Description

The technical solution of the present invention will be further explained with reference to the accompanying drawings and embodiments.

As shown in fig. 1, fig. 2, fig. 3 and fig. 5, an embodiment of the present invention provides an inflatable suspension adjustable propeller azimuth aircraft, which includes a machine body 10, an inflation tank 30 fixedly installed at the top of the machine body 10, a power assembly 40 fixedly installed in the middle of the machine body 10 and adjustable in power output direction, a wing assembly 20 fixedly installed at the rear of the machine body 10 and capable of being opened and closed, and a lifting assembly 70 fixedly installed in the middle of the machine body 10 and used for assisting lifting, wherein the inflation tank 30 is filled with inert gas; the gas-filled tank 30 is filled with helium to increase buoyancy of the aircraft, and the power assembly 40 is arranged in the middle of the aircraft body 10 for balancing weight and adjusting the center of gravity of the aircraft body 10.

As shown in fig. 1 and 5, the power assembly 40 includes a reversing motor 42 fixedly installed in the machine body 10, an output shaft of the reversing motor 42 is connected with a reduction gearbox 43 and is in transmission connection with a driving shaft 44 through the reduction gearbox 43, the driving shaft 44 is connected with a first bevel gear 45, the power assembly 40 further includes a mounting box 47 symmetrically and fixedly installed in the machine body 10 along the driving shaft 44, a steering shaft 48 is rotatably installed on the mounting box 47, one end of the steering shaft 48 is connected with a second bevel gear 46, the first bevel gear 45 is in meshing transmission with the second bevel gear 46, and the other end of the steering shaft 48 is connected with a turbofan 41; the storage battery is arranged in the machine body 10, the turbo fan 41 and the reversing motor 42 are powered by the storage battery, the reversing motor 42 can randomly adjust the output angle of the turbo fan 41, and the energy utilization efficiency of the aircraft is improved.

As shown in fig. 1, 2, 3 and 4, the wing assembly 20 includes wings 22 symmetrically hinged to two sides of the machine body 10, one end of each wing 22 is provided with a hinged end 23, the middle part of each hinged end 23 is hinged in the machine body 10 through a rotating shaft 24, the end part of each hinged end 23 is connected with a moving rod 25, a roller 29 is rotatably mounted on each moving rod 25, the wing assembly 20 further includes a driving part 26 fixedly mounted in the machine body 10, the driving part 26 is connected with an expansion link 27 controlled by the driving part 26 to reciprocate and extend, one end of the expansion link 27 is connected with a moving block 28, the top of the moving block 28 is provided with a through hole, and the moving rod 25 is disposed; the driving piece 26 and the telescopic rod 27 are connected to form an electric push rod in the prior art, the electric push rod is an electric driving device which converts the rotary motion of a motor into the linear reciprocating motion of the push rod, the motor drives a pair of screw rod nuts after being decelerated by a gear or a worm gear, the rotary motion of the motor is converted into the linear motion, and the push rod action is completed by the positive and negative rotation of the motor; the storage battery supplies power to the motor in the driving part 26, the air resistance of the aircraft is adjusted by opening and closing the wing 22, the air resistance of the machine body 10 is reduced when the wing 22 is folded, the aircraft is accelerated, buoyancy is increased when the wing 22 is unfolded, the aircraft is lifted, and the energy utilization efficiency is improved, wherein the wing 22 is positioned between the turbofan 41 and the lifting assembly 70, and the wing 22 is positioned above the turbofan 41.

As shown in fig. 1, in order to reduce flight resistance in the flight process of an aircraft, a wing accommodating groove 21 for accommodating the wing 22 is formed in the side surface of the aircraft body 10; the wings 22 are retracted into the wing accommodating grooves 21, so that the wind area of the wings 22 is reduced, and the flying resistance of the aircraft is reduced.

As shown in fig. 1, in order to realize smooth flight and lifting of the aircraft, a tail assembly 50 is arranged at the tail of the aircraft body 10, and the tail assembly 50 comprises a main tail wing 51 vertically fixed at the tail of the aircraft body 10 and two auxiliary tail wings 52 horizontally symmetrically fixed at the tail of the aircraft body 10; the balance of the rear portion of the body 10 is adjusted by the main tail wing 51 and the ailerons 52.

As shown in fig. 1, a plurality of bottom wheels 60 are installed at the bottom of the machine body 10, and shock absorbers are installed on the installation rods of the bottom wheels 60; the landing of the aircraft is facilitated.

As shown in fig. 1, in order to make the machine body 10 lift more rapidly, the lifting assembly 70 includes a lifting channel 71, the lifting channel 71 is vertically arranged on the machine body 10 in a penetrating manner, a lifting fan 72 is horizontally and fixedly arranged on the inner wall of the lifting channel 71, and further includes two wind plate slideways 75 horizontally arranged in the machine body 10, the two wind plate slideways 75 are respectively communicated with two ends of the lifting channel 71, wind shields 74 for sealing the lifting channel 71 are slidably arranged in the wind plate slideways 75, an electric telescopic rod 73 is horizontally and fixedly arranged in the machine body 10, the electric telescopic rod 73 and the wind shields 74 are located on the same horizontal plane, and one end of the electric telescopic rod 73 is fixedly connected with the wind shields 74; the cross-sectional area of wind shield 74 is greater than the bore of lift passageway 71, when the aircraft goes up and down, electric telescopic handle 73 contracts, pulling wind shield 74 slides on wind shield slide 75, open lift passageway 71, start lift fan 72, increase the air runner, reduce the air resistance of organism 10 lift in-process, and lift passageway 71 arranges the middle part in organism 10, it is steady to go up and down, at aircraft flight in-process, electric telescopic handle 73 is in the state of stretching out, wind shield 74 blocks up lift passageway 71, keep the steady of aircraft flight.

The detailed working process of the embodiment is as follows: in the lifting process of the aircraft, the reversing motor 42 is started, the reversing motor 42 drives the driving shaft 44 to rotate through the reduction gearbox 43, the driving shaft 44 drives the first bevel gear 45 to rotate, and the first bevel gear 45 drives the two second bevel gears 46 to rotate, so that the steering shaft 48 rotates, when the power output direction of the turbo fan 41 is downward, the reverse motor 42 is turned off, the turbo fan 41 is turned on, the body 10 is raised, meanwhile, the electric telescopic rod 73 is controlled to contract, the electric telescopic rod 73 pulls the wind shield 74 to move, so that the wind guard 74 is removed from the lifting channel 71, the lifting fan 72 is started, the lifting fan 72 assists the turbo fan 41 in lifting the body 10, after the aircraft is lifted off, the reversing motor 42 is started, the direction of the turbofan 41 is adjusted to realize the movement of the aircraft body 10 in the horizontal direction, and the electric telescopic rod 73 is controlled to extend out, so that the lifting channel 71 is blocked by the wind shield 74; in the aircraft flight process, make telescopic link 27 shrink through control driving piece 26, telescopic link 27 drives movable block 28 and removes, and then drive movable rod 25 and rotate around rotation axis 24, make the wing rotate, finally make wing 22 rotate to holding in the wing groove 21, reduce the air resistance of organism 10, organism 10 buoyancy reduces after wing 22 packs up, organism 10 descends, when organism 10 descends, the telescopic link stretches out, make wing 22 open, and then increase organism 10 buoyancy, organism 10 rises, can realize the effect that the aircraft reduces the flight energy of consumption in service.

Finally, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the present invention can be modified or replaced by other means without departing from the spirit and scope of the present invention, which should be construed as limited only by the appended claims.

Claims (7)

1. The utility model provides an aerify adjustable propeller position aircraft of suspension which characterized in that: the aircraft comprises an engine body (10), an inflation box (30) fixedly installed at the top of the engine body (10), a power assembly (40) fixedly installed in the middle of the engine body (10) and adjustable in power output direction, a wing assembly (20) fixedly installed at the rear part of the engine body (10) and capable of being opened and closed, and a lifting assembly (70) fixedly installed in the middle of the engine body (10) and used for assisting lifting, wherein inert gas is filled in the inflation box (30).

2. The inflatable levitation adjustable thruster azimuth craft of claim 1, wherein: the power assembly (40) comprises a reversing motor (42) fixedly mounted in the machine body (10), an output shaft of the reversing motor (42) is connected with a reduction gearbox (43) and is in transmission connection with a driving shaft (44) through the reduction gearbox (43), the driving shaft (44) is connected with a first helical gear (45), the power assembly (40) further comprises a mounting box (47) symmetrically and fixedly mounted in the machine body (10) along the driving shaft (44), a steering shaft (48) is rotatably mounted on the mounting box (47), one end of the steering shaft (48) is connected with a second helical gear (46), the first helical gear (45) is in meshing transmission with the second helical gear (46), and the other end of the steering shaft (48) is connected with a turbofan (41).

3. The inflatable levitation adjustable thruster azimuth craft of claim 1, wherein: wing subassembly (20) articulate wing (22) in organism (10) both sides including the symmetry, and wing (22) one end sets up hinged end (23), and hinged end (23) middle part articulates in organism (10) through pivot (24), and hinged end (23) end connection carriage release lever (25), last rotation of carriage release lever (25) are installed gyro wheel (29), wing subassembly (20) still include driving piece (26) of fixed mounting in organism (10), connect on driving piece (26) telescopic link (27) of reciprocating telescopic motion under driving piece (26) control, and movable block (28) are connected to telescopic link (27) one end, and the through-hole is seted up at movable block (28) top, and the through-hole of movable block (28) is arranged in to carriage release lever (25).

4. An inflatable levitation adjustable thruster orientation aircraft as claimed in claim 3 wherein: and a wing accommodating groove (21) for accommodating the wing (22) is formed in the side surface of the machine body (10).

5. The inflatable levitation adjustable thruster azimuth craft of claim 1, wherein: the tail part of the machine body (10) is provided with a tail assembly (50), and the tail assembly (50) comprises a main tail (51) vertically fixed at the tail part of the machine body (10) and two auxiliary tail wings (52) horizontally and symmetrically fixed at the tail part of the machine body (10).

6. The inflatable levitation adjustable thruster azimuth craft of claim 1, wherein: a plurality of bottom wheels (60) are installed at the bottom of the machine body (10), and shock absorbers are installed on installation rods of the bottom wheels (60).

7. The inflatable levitation adjustable thruster azimuth craft of claim 1, wherein: lifting unit (70) are including lift passageway (71), and lift passageway (71) is vertical to run through the setting on organism (10), lift passageway (71) inner wall level fixed mounting lifting fan (72), still include the level setting and be in two aerofoil slide (75) in organism (10), two aerofoil slide (75) communicate with each other with lift passageway (71) both ends respectively, and slidable mounting is used for sealing deep bead (74) of lift passageway (71) in aerofoil slide (75), horizontal fixed mounting has electric telescopic handle (73) in organism (10), and electric telescopic handle (73) and deep bead (74) are in same horizontal plane, electric telescopic handle (73) one end and deep bead (74) fixed connection.

Images