CN103587682A

CN103587682A - Air vehicle

Info

Publication number: CN103587682A
Application number: CN201310557048.8A
Authority: CN
Inventors: 张恒; 易翔; 王梅梅; 施龙; 赵林
Original assignee: China National South Aviation Industry Co Ltd
Current assignee: China National South Aviation Industry Co Ltd
Priority date: 2013-11-11
Filing date: 2013-11-11
Publication date: 2014-02-19

Abstract

The invention provides an air vehicle which comprises a main body (10) and also comprises two lifting devices (20) arranged on the main body (10), wherein the two lifting devices (20) are arranged at an interval in the forwarding direction of the main body (10). The air vehicle disclosed by the invention has a higher safety coefficient.

Description

Aircraft

Technical field

The present invention relates to airmanship field, in particular to a kind of aircraft.

Background technology

At present, in order to control moving forward and backward of aircraft, the way adopting is, the center-of-gravity position of change of flight device, for example, the counterweight arranging on mobile aircraft, when the gravity motion of aircraft is during to the front end of aircraft, the front end of aircraft moves down, and moves on the rear end of aircraft simultaneously, like this, aircraft moves forward; When the gravity motion of aircraft is during to the rear end of aircraft, the rear end of aircraft moves down, and moves on the front end of aircraft simultaneously, and like this, aircraft moves backward.But, the more difficult realization in operation of this way, and, the opposite direction of the application force bont of the direction of the application force of aircraft and aircraft self being provided due to counterweight, and do not overlap, easily cause the rolling of aircraft, reduced the safety factor of aircraft.

Summary of the invention

The present invention aims to provide the aircraft that a kind of safety factor is high.

To achieve these goals, the invention provides a kind of aircraft, comprise main body, aircraft also comprises: two bonts, be arranged in main body, and two bont intervals in the working direction of main body arrange.

Further, each bont comprises: rotating shaft, is arranged in main body rotationally; A plurality of rotating blades, a plurality of rotating blades are fixed on the outer peripheral face of rotating shaft at each interval.

Further, the quantity of a plurality of rotating blades is even number, and a plurality of rotating blades circumferentially evenly arrange along rotating shaft.

Further, each bont also comprises: Horizontal limiting portion, be set in rotating shaft, and Horizontal limiting portion is arranged in main body.

Further, each bont also comprises: bearing, is arranged between Horizontal limiting portion and rotating shaft.

Further, the hand of rotation of two of two bonts rotating shafts is contrary.

Further, each bont also comprises: ventilating duct, there are two relative open ends, and a plurality of rotating blades are arranged on the inside of ventilating duct.

Further, rotating blade is two, and two rotating blades extend in opposite direction, and two rotating blades are fixed on contiguous block, and contiguous block has the through hole of the rotating shaft of wearing, and contiguous block is fixed in rotating shaft.

Further, aircraft of the present invention also comprises: Double shaft-extension asynchronous motor, there is the first axle drive shaft and the second axle drive shaft, and two rotating shafts of two bonts and the first axle drive shaft and the second axle drive shaft one by one corresponding driving are connected.

Further, each bont is ducted fan.

Apply technical scheme of the present invention, owing to being provided with the bont at two intervals in main body, can the hoisting force of main body be reached advancing of aircraft or be retreated by controlling bont.Particularly, make the bont that is positioned at the place ahead be greater than and be positioned at the hoisting force of the bont at rear to main body the hoisting force of main body, raise the front portion of main body, now, two bonts to the direction of the hoisting force of main body backward lateral deviation move, like this, aircraft will move backward; Make the bont that is positioned at rear be greater than and be positioned at the hoisting force of the bont in the place ahead to main body the hoisting force of main body, raise at the rear portion of main body, now, two bonts to the direction of the hoisting force of main body forward lateral deviation move, like this, aircraft will move forward.Aircraft of the present invention replaces the counterweight of prior art realize advancing of aircraft or retreat with two bonts, simple to operate, because bont provides lift to main body, therefore, avoided the rollover phenomenon of main body, that is to say, aircraft of the present invention has higher safety factor.

Accompanying drawing explanation

The Figure of description that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:

Fig. 1 shows according to the structural representation of the embodiment of aircraft of the present invention.

Wherein, the Reference numeral in above-mentioned figure is as follows:

10, main body; 20, bont; 21, rotating shaft; 22, rotating blade; 23, Horizontal limiting portion; 24, ventilating duct; 25, contiguous block.

The specific embodiment

It should be noted that, in the situation that not conflicting, embodiment and the feature in embodiment in the application can combine mutually.Describe below with reference to the accompanying drawings and in conjunction with the embodiments the present invention in detail.

As shown in Figure 1, the aircraft of the present embodiment comprises that

main body

10 and 20, two bonts 20 of two bonts are arranged in main body 10, and two bont 20 intervals in the working direction of main body 10 arrange.

The aircraft of application the present embodiment, owing to being provided with the bont 20 at two intervals in main body 10, can reach advancing of aircraft or retreat by controlling the hoisting force of 20 pairs of main bodys 10 of bont.Particularly, the hoisting force that makes to be positioned at 20 pairs of main bodys 10 of bont in the place ahead is greater than the hoisting force of the 20 pairs of main bodys 10 of bont that are positioned at rear, raise the front portion of main body 10, now, the direction of the hoisting force of 20 pairs of main bodys 10 of two bonts backward lateral deviation is moved, like this, aircraft will move backward; The hoisting force that makes to be positioned at 20 pairs of main bodys 10 of bont at rear is greater than the hoisting force of the 20 pairs of main bodys 10 of bont that are positioned at the place ahead, raise at the rear portion of main body 10, and now, the direction of the hoisting force of 20 pairs of main bodys 10 of two bonts forward lateral deviation is moved, like this, aircraft will move forward.The aircraft of the present embodiment replaces the counterweight of prior art realize advancing of aircraft or retreat with two bonts 20, simple to operate, because 20 pairs of main bodys 10 of bont provide lift, therefore, avoided the rollover phenomenon of main body 10, that is to say, the aircraft of the present embodiment has higher safety factor.

As shown in Figure 1, in the present embodiment, each bont 20 comprises rotating shaft 21 and a plurality of rotating blade 22.Rotating shaft 21 is arranged in main body 10 rotationally, and rotating shaft 21 will that is to say for main body 10 provides tractive force simultaneously, and rotating shaft 21 can be not separated with main body 10.A plurality of rotating blades 22 are fixed on the outer peripheral face of rotating shaft 21 at each interval.Like this, under the drive that a plurality of rotating blades 22 rotate in rotating shaft 21, rotate, for main body 10 provides lift.Two bonts 20 can be the main powers that makes aircraft takeoff, that is to say, in main body 10, without being provided with the main power of extra jack up unit as aircraft takeoff, above-mentioned two bonts 20 mainly play the effect that aircraft is advanced or retreat.Certainly, above-mentioned two bonts 20 also can be only as the control apparatus that regulates aircraft advance or retreat.Certainly, bont 20 also can adopt jet-driven structure.Preferably, a plurality of rotating blades 22 are fixed on the same cross section of rotating shaft 21, like this, have improved the stability of aircraft when flight.

As shown in Figure 1, in the present embodiment, the quantity of a plurality of rotating blades 22 is even number, and a plurality of rotating blades 22 circumferentially evenly arrange along rotating shaft 21.That is to say, rotating blade 22 occurs in paired mode, each coincidence of extension line to rotating blade 22, and oppositely extend.In addition, a plurality of rotating blades 22 just define on the same cross section that a plurality of rotating blades 22 are located at rotating shaft 21 along the circumferential setting of rotating shaft 21.

As shown in Figure 1, each bont 20 also comprises Horizontal limiting portion 23, and Horizontal limiting portion 23 is set in rotating shaft 21, and Horizontal limiting portion 23 is arranged in main body 10.Horizontal limiting portion 23 can reduce rotating shaft 21 rocking of producing of when work, has improved the stability of aircraft when flight.Horizontal limiting portion 23 is preferably position-limiting tube, and position-limiting tube is set in rotating shaft 21.Certainly, as feasible embodiment, Horizontal limiting portion 23 can be also two discontiguous arc plates.

As shown in Figure 1, in the present embodiment, each bont 20 also comprises bearing (not shown), and bearing is arranged between Horizontal limiting portion 23 and rotating shaft 21.Bearing can avoid rotating shaft 21 and Horizontal limiting portion 23 to produce friction, reduced rotating shaft 21 suffered resistance when rotating, and like this, improved the life-span of rotating shaft 21.

As shown in Figure 1, in the present embodiment, the hand of rotation of two rotating shafts 21 of two bonts 20 is contrary.Like this, the opposite direction of the rotating torque that 20 pairs of main bodys of two bonts 10 produce, prevents that main body 10 from horizontally rotating, the safety factor of the aircraft having improved.

As shown in Figure 1, in the present embodiment, each bont 20 also comprises ventilating duct 24, and ventilating duct 24 has two relative open ends, and a plurality of rotating blades 22 are arranged on the inside of ventilating duct 24.Ventilating duct 24 plays the effect of assembling air-flow, and the hoisting force that the rotating blade 22 in ventilating duct 24 is produced is more concentrated, has improved the efficiency of bont 20.

As shown in Figure 1, in the present embodiment, rotating blade 22 is two, and two rotating blades 22 extend in opposite direction, and two rotating blades 22 are fixed on contiguous block 25 and are fixed at each interval on the outer peripheral face of rotating shaft 21 to realize a plurality of rotating blades 22.Contiguous block 25 has the through hole of rotating shaft of wearing 21, and contiguous block 25 is fixed in rotating shaft 21.Proof by experiment, rotating blade 22 is two, and two rotating blades 22 extend in opposite direction, more stable hoisting force can be provided, and be suitable as the main power of aircraft takeoff.In addition, contiguous block 25 has the through hole of rotating shaft of wearing 21, has improved the area of contact of contiguous block 25 with rotating shaft 21, and then has improved the stability of bont 20 when work.

The present embodiment aircraft also comprise Double shaft-extension asynchronous motor (not shown), Double shaft-extension asynchronous motor has the first axle drive shaft and the second axle drive shaft, the first axle drive shaft is identical with the hand of rotation of the second axle drive shaft, rotating speed can be different.Two rotating shafts 21 of two bonts 20 and the first axle drive shaft and the second axle drive shaft one by one corresponding driving are connected.Like this, can be by regulating the rotating speed of the first axle drive shaft and the second axle drive shaft to change the hoisting force of two bont 20 main bodys that offer 10, and then the advancing or retreat of change of flight device.

As shown in Figure 1, in the present embodiment, each bont 20 is ducted fan.Ducted fan Stability Analysis of Structures, proves, the lift that provides of aircraft is provided ducted fan by experiment.

The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.

Claims

1. an aircraft, comprises main body (10), it is characterized in that, described aircraft also comprises:

Two bonts (20), are arranged on described main body (10) upper, and described two bonts (20) interval in the working direction of described main body (10) arranges.

2. aircraft according to claim 1, is characterized in that, bont described in each (20) comprising:

Rotating shaft (21), is arranged in described main body (10) rotationally;

A plurality of rotating blades (22), described a plurality of rotating blades (22) are fixed on the outer peripheral face of described rotating shaft (21) at each interval.

3. aircraft according to claim 2, is characterized in that, the quantity of described a plurality of rotating blades (22) is even number, and described a plurality of rotating blades (22) circumferentially evenly arrange along described rotating shaft (21).

4. aircraft according to claim 2, is characterized in that, bont described in each (20) also comprises:

Horizontal limiting portion (23), is set in described rotating shaft (21) upper, and described Horizontal limiting portion (23) is arranged in described main body (10).

5. aircraft according to claim 4, is characterized in that, bont described in each (20) also comprises:

Bearing, is arranged between described Horizontal limiting portion (23) and described rotating shaft (21).

6. aircraft according to claim 2, is characterized in that, the hand of rotation of two rotating shafts (21) of described two bonts (20) is contrary.

7. aircraft according to claim 2, is characterized in that, bont described in each (20) also comprises:

Ventilating duct (24), has two relative open ends, and described a plurality of rotating blades (22) are arranged on the inside of described ventilating duct (24).

8. aircraft according to claim 2, it is characterized in that, described rotating blade (22) is two, described two rotating blades (22) extend in opposite direction, described two rotating blades (22) are fixed on contiguous block (25), described contiguous block (25) has the through hole that wears described rotating shaft (21), and described contiguous block (25) is fixed in described rotating shaft (21).

9. aircraft according to claim 2, is characterized in that, also comprises:

Double shaft-extension asynchronous motor, has the first axle drive shaft and the second axle drive shaft, and two rotating shafts (21) of described two bonts (20) and described the first axle drive shaft and described the second axle drive shaft one by one corresponding driving are connected.

10. aircraft according to claim 1, is characterized in that, bont described in each (20) is ducted fan.