CN105217046B - Exhaust passage with flexible venting tube - Google Patents

Abstract

The invention discloses a kind of exhaust passage with flexible venting tube, belong to unmanned air vehicle technique field, the exhaust passage with flexible venting tube includes：Blast pipe, the blast pipe is arranged on the fuselage, and is connected with the engine flexible in fuselage；Exhaust end, the exhaust end is arranged on the end of blast pipe, and the exhaust end includes：Tapered barrel, the tapered barrel includes offering several communication ports on tapered wide opening and tapered slot, and the side wall of the tapered barrel；Anechoic room, the anechoic room is set in the peripheral position of the tapered barrel, and the anechoic room is internally provided with an exhaust outlet.The present invention is solved in the prior art due to not having single silencing apparatus or noise elimination structure so that be there is larger noise during blast pipe discharge tail gas, is in turn resulted in the technological deficiency of noise pollution.

Description

Exhaust passage with flexible venting tube

Technical field

The invention belongs to unmanned air vehicle technique field, more particularly to a kind of exhaust passage with flexible venting tube.

Background technology

UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself Not manned aircraft.Without driving cabin on machine, but the equipment such as automatic pilot, presetting apparatus, information collecting device are installed. On ground, naval vessels or machine tool remote control station personnel are by equipment such as radars, it is tracked, positioned, remote control, remote measurement and numeral are passed It is defeated.It can take off or be launched with booster rocket as conventional airplane under wireless remotecontrol, can also be taken in the air by machine tool Deliver flight.

In the prior art, in the sidepiece of depopulated helicopter fuselage, a blast pipe for being used to discharge tail gas is provided with, is used for Discharge the tail gas of burning in fuselage.

However, when the tail gas in fuselage is discharged by blast pipe, due to not having single silencing apparatus or disappearing Acoustic form so that there is larger noise during blast pipe discharge tail gas, in turn result in noise pollution.

The content of the invention

The present invention provides a kind of exhaust passage with flexible venting tube, by setting exhaust end in the end of blast pipe, And the exhaust end is eliminated the noise by tapered barrel and anechoic room to the tail gas for entering exhaust end, solve or part is solved now Have in technology due to not having single silencing apparatus or noise elimination structure so that there is larger make an uproar during blast pipe discharge tail gas Sound, in turn results in the technological deficiency of noise pollution.

The invention provides a kind of exhaust passage with flexible venting tube, applied to depopulated helicopter, described nobody is straight The machine of liter includes being provided with engine in fuselage, and the fuselage, and the exhaust passage with flexible venting tube includes：Exhaust Pipe, the blast pipe is arranged on the fuselage, and is connected with the engine flexible so that the blast pipe starts with described Machine can be relatively moved；Exhaust end, the exhaust end is arranged on the end of blast pipe, and the exhaust end includes：Cone Type tube, the tapered barrel includes offering several communication ports on tapered wide opening and tapered slot, and the side wall of the tapered barrel； Anechoic room, the anechoic room is set in the peripheral position of the tapered barrel, and the anechoic room is internally provided with an exhaust outlet； Wherein, the tail gas in the blast pipe flows into the inner space of the tapered barrel by the tapered wide opening, and from described tapered The inner space of cylinder is entered in the anechoic room by the communication port and/or the tapered slot, and the tail gas is by the row Gas port is discharged.

Optionally, the blast pipe include first pipe, it is described first pipe be arranged on the fuselage on, and with the engine Flexible connection so that first pipe can be relatively moved with the engine；Second pipe, second pipe and described the One pipe is flexibly connected so that first pipe can be relatively moved relative to second pipe, and the exhaust end is set At the end portion of second pipe；Wherein, first pipe and the engine are communicated, first pipe and described second Pipe is communicated so that the tail gas after being burnt in the engine passes sequentially through first pipe and second pipe flows into the exhaust End.

Optionally：The U-shaped shape of first pipe, and first pipe includes the first flexible ends and the second flexible ends；It is described Second pipe is in straight-tube shape, and second pipe includes the 3rd flexible ends, the exhaust end and setting that the 3rd flexible ends oppose Put at the two ends of second pipe；And, the exhaust passage with flexible venting tube also includes：First flexible connecting member, institute State the first flexible ends to be connected with the engine flexible by first flexible connecting member so that first pipe is relative to institute Stating engine can relatively move；Second flexible connecting member, second flexible ends pass through second flexible connecting member It is flexibly connected with the 3rd flexible ends so that second pipe can be relatively moved relative to first pipe；Wherein, Tail gas after being burnt in the engine is flowed into be buffered in first pipe, and the tail gas after buffering is passed sequentially through again Second flexible ends and the 3rd flexible ends enter the described second pipe, and are discharged from the exhaust end.

Optionally, first flexible connecting member includes：First groups of springs and the first plate group；Wherein, first spring Group includes at least three first springs；The first plate group includes the first fixed plate and the second fixed plate；First fixed plate At the gas outlet for being fixed on the engine, second fixed plate is fixed in first flexible ends, and described at least three In individual first spring, one end of each the first spring is connected with first fixed plate, the other end and second fixed plate Connection；The gas outlet of the engine is set in first flexible ends, and passes through at least three first spring so that First flexible ends can be relatively moved relative to the engine；And/or, second flexible connecting member includes： Second spring group and the second plate group；Wherein, the second spring group includes at least three second springs；The second plate group includes 3rd fixed plate and the 4th fixed plate；3rd fixed plate is fixed in second flexible ends, and the 4th fixed plate is consolidated Due in the 3rd flexible ends, and at least three second spring, one end of each second spring and the described 3rd Fixed plate is connected, and the other end is connected with the 4th fixed plate；3rd flexible ends are set in second flexible ends, and Pass through at least three second spring so that relative to second flexible ends relative shifting can occur for the 3rd flexible ends It is dynamic.

A kind of exhaust passage with flexible venting tube that the present invention is provided, is vented by being set in the end of blast pipe End so that the tail gas in blast pipe flows into the inner space of tapered barrel by tapered wide opening, and leads to from the inner space of tapered barrel Cross the communication port and/or tapered slot enters in the anechoic room, eventually through tapered barrel and anechoic room to entering exhaust end Tail gas eliminated the noise, solve in the prior art due to not having single silencing apparatus or noise elimination structure so that exhaust There is larger noise in pipe, in turn result in the technological deficiency of noise pollution when discharging tail gas.

Brief description of the drawings

In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment The accompanying drawing needed to use is briefly described, it should be apparent that, drawings in the following description are only some implementations of the present invention Example, for those of ordinary skill in the art, on the premise of not paying creative work, can also be obtained according to these accompanying drawings Obtain other accompanying drawings.

Fig. 1 be the exhaust passage provided in an embodiment of the present invention with flexible venting tube applied to depopulated helicopter when it is whole Body structural front view；

Fig. 2 is Fig. 1 side view；

Fig. 3 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, depopulated helicopter The second side partial sectional view；

Fig. 4 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, depopulated helicopter The 3rd side partial sectional view；

Fig. 5 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, depopulated helicopter Air inlet system front view；

Fig. 6 for Fig. 5 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, air inlet system Overall structure diagram；

Fig. 7 for the airscoop shroud of Fig. 5 air inlet systems provided top view；

The side view one of airscoop shroud in the air inlet system that Fig. 8 provides for Fig. 7；

The side view two of airscoop shroud in the air inlet system that Fig. 9 provides for Fig. 7；

Figure 10 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, nobody goes straight up to The front view of the gas extraction system of machine；

Figure 11 for Figure 10 gas extraction system provided side view；

The structural representation of the second flexible connecting member in the gas extraction system that Figure 12 provides for Figure 10；

Figure 13 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, air inlet system Annexation schematic diagram during heat shield is not included with gas extraction system；

Figure 14 does not include annexation front view during heat shield for Figure 13 air inlet systems provided and gas extraction system；

Figure 15 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, air inlet system Annexation schematic diagram during heat shield is included with gas extraction system；

Figure 16 includes annexation front view during heat shield for Figure 15 air inlet systems provided and gas extraction system；

Figure 17 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, cooling system, The annexation front view of engine and the first cover body；

The annexation schematic diagram of cooling system, engine and the first cover body that Figure 18 provides for Figure 17；

Figure 19 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, air inlet system, The annexation schematic diagram of cooling system, gas extraction system；

Air inlet system that Figure 20 provides for Figure 19, cooling system, the annexation front view of gas extraction system；

Figure 21 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, cooling system Structural representation；

Figure 22 is Figure 21 cooling systems provided and the annexation schematic diagram of the first cover body；

The overall structure diagram of centrifugal fan in the cooling system that Figure 23 provides for Figure 21；

The front view of centrifugal fan in the cooling system that Figure 24 provides for Figure 21；

Figure 25 for Fig. 1 provide by the exhaust passage with flexible venting tube be applied to depopulated helicopter when, dynamic balancing system The structural representation of system；

The sectional view of dynamic balancing component in the dynamic balance system that Figure 26 provides for Figure 25.

Embodiment

Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on Embodiment in the present invention, the every other embodiment that those of ordinary skill in the art are obtained belongs to what the present invention was protected Scope；Involved "and/or" keyword wherein in this implementation, represent and or two kinds of situations, in other words, the present invention implement A and/or B mentioned by example, illustrate A and B, two kinds of situations of A or B, describe three kinds of states present in A and B, such as A and/or B, is represented：Only including A does not include B；Only including B does not include A；Including A and B.

Meanwhile, in the embodiment of the present invention, when component is referred to as " being fixed on " another component, it can be directly at another On component or there can also be a component placed in the middle.When a component is considered as " connection " another component, it can be direct It is connected to another component or may be simultaneously present component placed in the middle.When a component is considered as " being arranged at " another group Part, it can be set directly on another component or may be simultaneously present component placed in the middle.Made in the embodiment of the present invention Term " vertically ", " level ", "left", "right" and similar statement are merely for purposes of illustration, and are not intended to The limitation present invention.

A kind of exhaust passage provided in an embodiment of the present invention, applied to depopulated helicopter, is set by the end in blast pipe Put exhaust end so that tail gas in blast pipe flows into the inner space of tapered barrel by tapered wide opening, and from the inside of tapered barrel Space is entered in the anechoic room by the communication port and/or tapered slot, eventually through tapered barrel and anechoic room to entering The tail gas of exhaust end is eliminated the noise, and is solved in the prior art due to not having single silencing apparatus or noise elimination structure, is made There is larger noise when obtaining blast pipe discharge tail gas, in turn result in the technological deficiency of noise pollution.

Below, in order to be elaborated to the exhaust passage with flexible venting tube that the present invention is provided, to support this to send out Bright technical problem to be solved, first, the embodiment of the present invention is first provided in an embodiment of the present invention to application to have flexible exhaust The depopulated helicopter of the exhaust passage of pipe elaborates, with the structure to exhaust passage, using aiding in illustrating.

Specifically, Fig. 1-2 is referred to, it is provided in an embodiment of the present invention to be provided with the exhaust passage with flexible venting tube Depopulated helicopter include head 1, fuselage 2 and afterbody 3.Wherein, the fuselage 2 includes the first side 21, the second side 22, the 3rd side 23 and the 4th side 24.And the paddle 4 for the unmanned helicopter flight, the 4th side 24 are provided with first side 21 On be provided with for the depopulated helicopter land undercarriage 5, second side 22 and the 3rd side 23 are symmetrically distributed In first side 21 and/or the both sides of the 4th side 24 so that by first side 21, second side 22, described Three sides 23 and the 4th side 24 are surrounded to form the fuselage 2.

Wherein, because unmanned helicopter-mounted equipment requirement is high, this causes the first side of middle fuselage of the embodiment of the present invention 2 21st, the second side 22, the 3rd side 23 and the 4th side 24 are multiple from high-performance composite materials such as carbon fibre composite, glass fibre Condensation material, honeycomb sandwich composite etc. are made.Compared with traditional depopulated helicopter fuselage designing material, the present invention is real Applying carbon fibre composite, glass fiber compound material, honeycomb sandwich composite selected by example etc. at least has following spy Point：Specific strength and specific stiffness height, small thermal coefficient of expansion, anti-fatigue ability and vibration resistance are strong.

In addition, the embodiment of the present invention is by making fuselage 2 of the invention from above-mentioned composite, due to composite sheet Body has designability, so in the case where not changing construction weight, can require that progress is excellent according to the strong and unyielding degree of intensity of aircraft Change design, meet depopulated helicopter in large area global formation this requirement needed for height blended wing-body structure.And it is compound Material has extremely strong decay resistance, can meet the particular/special requirement of long storage life under depopulated helicopter adverse circumstances, reduction The life cycle cost of working service.

Furthermore, composite is applied to provided in an embodiment of the present invention be provided with exhaust passage with flexible venting tube Depopulated helicopter, because composite has special electromagnetic performance, can meet it is provided in an embodiment of the present invention nobody go straight up to The high stealth technology requirement of machine structure/functions.And by from carbon fibre composite, glass fiber compound material, honeybee Nest interlayer composite material etc., also causes the embodiment of the present invention to have easily implantation chip or alloy conductor formation intellectual material, structure The characteristics of.

Further, Fig. 3-4 are referred in the lump incorporated by reference to Fig. 1-2, it is provided in an embodiment of the present invention to be provided with flexible row The depopulated helicopter of the exhaust passage of tracheae also includes：Cooling system 8, dynamic balance system 9, air inlet system 6 and gas extraction system 7. Wherein, exhaust passage provided in an embodiment of the present invention can be understood as being included in gas extraction system 7.That is, gas extraction system 7 includes Exhaust passage provided in an embodiment of the present invention with flexible venting tube.

In embodiments of the present invention, air inlet system 6 is fixed on second side 22, and the air intake of the air inlet system 6 Direction of the direction towards the head.Gas extraction system 7 is fixed on the 3rd side 23, and the exhaust side of the gas extraction system 7 To the direction towards the afterbody 3, the tail gas for generation of being burnt in the depopulated helicopter is passed through into the row of gas extraction system 7 Go out.Cooling system 8 is fixed on first side 21 so that extraneous cold air is inhaled into described by the cooling system 8 The inside of fuselage 2, is cooled down to the fuselage 2.Dynamic balance system 9 is rotationally fixed to the afterbody 3, and the dynamic balancing The rotational plane of the rotational plane of system 9 and the paddle 4 is perpendicular, to control institute by the rotation of the dynamic balance system 9 State the dynamic balancing degree during unmanned helicopter flight.

In order to be done to the depopulated helicopter provided in an embodiment of the present invention for being provided with the exhaust passage with flexible venting tube Describe in detail；Below, by detailed one by one to air inlet system 6, gas extraction system 7, cooling system 8 and dynamic balance system 9 with reference to accompanying drawing State：

For the part of air inlet system 6,

Fig. 5-6 are referred to, the air inlet system 6 at least includes：Airscoop shroud 61 and engine provided in an embodiment of the present invention 62.Wherein, airscoop shroud 61 is fixed on second side 22, and the airscoop shroud 61 air intake direction towards the head 1 Direction.That is, relative to depopulated helicopter reverse flow air-flow flow direction the fuselage relative to unmanned plane backward when (can With reference to shown in Fig. 1,3), the air intake direction of the air-flow set by airscoop shroud 61, also relative to unmanned plane fuselage backward, so may be used It is smooth, quick, high to cause the air-flow outside depopulated helicopter under itself flow velocity effect relative to the depopulated helicopter In the inflow airscoop shroud 61 of effect.Meanwhile, engine 62 is fixed on the inside of the fuselage 2, and positioned at second side 22 and institute State between the 3rd side 23, and the engine 62 is connected with the airscoop shroud 61 so that the air-flow passes through the airscoop shroud 61 Flow into the engine 62 and burn.

Continuing with referring to Fig. 7-9, airscoop shroud 61 can at least include in above-mentioned air inlet system 6：Air inlet 611, filter screen 612 With surge chamber 613.Wherein, air inlet 611 is used to flow into relative to the air-flow of the depopulated helicopter reverse flow.And filter screen 612 are fixed at the air inlet 611, for filling out the whole air inlet 611 of envelope, have reached and have removed the members such as S, N for containing in air The air plankton of element, is entered in engine 62 by airscoop shroud 61 beneficial to the air after purification and burnt, further improve the pure of tail gas The purpose of cleanliness.Meanwhile, a dividing plate 6131 is provided with surge chamber 613.And by the dividing plate 6131 by the surge chamber 613 It is divided into first area 6132 and second area 6133 so that be introduced into firstth area by the air-flow of the filter screen 612 Buffered in domain 6132, and the air-flow after buffering flows into the second area 6133 from the first area 6132 again, And flowed into by second area 6133 in the engine 62.

It is noted that surge chamber 613 in set dividing plate 6131 be a semiclapboard, it can be understood as by this every Surge chamber 613 divide into three parts by plate 6131, referring to Fig. 7, first part is the surge chamber 613 shown in Fig. 7 Right episphere, i.e. first area 6132；The second part is the left episphere of the surge chamber 613 shown in Fig. 7, i.e., second Region 6133；3rd part is the lower semisphere of the surge chamber 613 shown in 7, and the lower semisphere can be understood as by the filter The air-flow of net 612 is introduced into the first area 6132 and buffered, and the air-flow after buffering is again from described the The circulation passage that one region 6132 is flowed into required for the second area 6133.And dividing plate 6131 is arranged on first area 6132 Between second area 6133.The purpose for entering row buffering to the air-flow for flowing into surge chamber 613 is reached, is overcome due to air inlet 611 air-flows flowed into are too fast because of the flow velocity of itself, and cause the air-flow under flow at high speed directly by engine 62 and by being vented It when system 7 is discharged, can not fully be burnt within the engine because of excessive velocities, then influence the power supply of depopulated helicopter Technological deficiency.

Certainly, it will be understood by those skilled in the art that being divided into first area by setting dividing plate 6131 by surge chamber 613 6132 and second area 6133, wait until to buffer in order to flowing into the air-flow of surge chamber 613 be only the embodiment of the present invention one kind it is real Mode is applied, is not limited to.Internal structure that can also be in other way to surge chamber 613 is designed, e.g., in surge chamber Gas channel (autodrome for being similar to ring-type) annular in shape is set in 613 inner space so that enter surge chamber 613 Circulate and flow into the presence of annular flow passage, the flow velocity of air-flow is gradually reduced with this, or, in surge chamber 613 Several blinkers (flabellum for being similar to electric fan) are set in portion space so that enter being kept out the wind at several for surge chamber 613 Speed is decayed in the presence of piece, and then flows into burning in engine through blinker.In other words, if can realize by The air-flow that air inlet 611 is flowed into, enters the surge chamber 613 of row buffering, in the present invention before engine 62 is entered to its flow velocity Within the protection domain of embodiment.

For the part of gas extraction system 7,

Figure 10-16 are referred to, the gas extraction system 7 at least includes：Blast pipe 71 and heat shield 72.Wherein, blast pipe 71 It is arranged on the 3rd side 23, and the discharge directions of the blast pipe 71 (can combine Fig. 2 institutes towards the direction of the afterbody 3 Show), the tail gas for generation of being burnt in the engine 62 is discharged by the blast pipe.Explanation is needed exist for, due to The discharge directions of blast pipe 71 are towards the direction of the afterbody 3, i.e. afterbody 3 is at the rear of depopulated helicopter, then blast pipe 71 Discharge directions towards the rear of depopulated helicopter.Because depopulated helicopter is during flight, fuselage 2 is straight relative to nobody Rise machine outside air-flow there is certain relative velocity, when blast pipe 71 discharge directions towards depopulated helicopter rear when, Tail gas in blast pipe 71 can quickly be discharged in blast pipe 71, improved in fuselage 2 in the presence of above-mentioned relative velocity The air-flow conduction property in portion.

Simultaneously as engine 62 is during burning, and blast pipe 71 is either sent out during last person's gas Motivation 62 or blast pipe 71, in the presence of higher temperature.Other inside fuselage 2 are had influence in order to avoid the higher temperature Part, causes miscellaneous part to occur damaging or burn because temperature is too high.The embodiment of the present invention is in the engine 62 and institute State between blast pipe 71, be additionally provided with heat shield 72.So that the inside of the blast pipe 72 and engine 62 and the fuselage 2 is empty Between be isolated.Prevent engine 62 and the high temperature of itself of blast pipe 71 from having influence on the normal fortune of depopulated helicopter to external diffusion OK.Preferably, please continue to refer to Figure 15-16, heat shield 72 includes the first cover body 721 and the second cover body 722.Wherein, first Cover body 721 is adapted with the shape of engine 62, is set in the outside of engine 62, the shape of the second cover body 722 and blast pipe 71 Shape is adapted, and is set in the outside of blast pipe 71.And first can be between cover body 721 and the second cover body 722 be fixedly connected as Weld or be integrally formed and be made.And, the top of the first cover body 721 is open type, is easy to the cold of cooling system 8 Air outlet slit is mutually connected with the top of the first cover body 721 so that the cold air in cooling system 8 is by the top of the first cover body 721 The first cover body of entrance 721 in engine 62 is cooled down.The internal structure of cooling system 8 can be described in further detail below, First gas extraction system 7 is illustrated herein.

Further, incorporated by reference to shown in Figure 10, the blast pipe 71 in gas extraction system 7 can include：First pipe 711, Second pipe 712, the first flexible connecting member 713 and the second flexible connecting member 714.

Wherein, the U-shaped shape of first pipe 711.And first pipe 711 includes first for being connected with engine 62 Flexible ends 7111 and the second flexible ends 7112 for being connected with the second pipe 722.Second pipe 712 is in straight-tube shape, and described Second pipe 712 includes the 3rd flexible ends 7121 for being connected with the first pipe 711 and the exhaust end 7122 for emission.Institute State the first flexible ends 7111 to be flexibly connected with the engine 62 by first flexible connecting member 713 so that described first Pipe 711 can be relatively moved relative to the engine 62.Second flexible ends 7112 are connected by the described second flexibility Fitting 714 is flexibly connected with the 3rd flexible ends 7121 so that second pipe 712 can be with relative to first pipe 711 Relatively move.

Specifically, by the way that the first pipe 711 is designed into U-shaped shape, the first pipe 711 is on the one hand saved in the inside of fuselage 2 Occupied space, is on the other hand once buffered to the tail gas discharged by engine 62 so that described after once buffering Tail gas obtains first bounce.Because in the tail gas discharged by engine 62, more or less presence part and non-fully The gas of burning, the gas burnt so and non-fully with tail gas from engine 62 discharge when, the first pipe of tail gas and U-shaped shape 711 tube wall collides, and is once buffered, and the tail gas after once buffering obtains the in the presence of the tube wall of the first pipe 711 Once rebound, now partial tail gas can continue to be back in engine 62 to be fired in the presence of first bounce active force Burn.Improve the operating efficiency of engine 62.

Please continue to refer to Figure 11-12, preferably, the first flexible connecting member 713 includes described in the embodiment of the present invention：The One groups of springs and the first plate group.Second flexible connecting member 714 includes：Second spring group and the second plate group.

Wherein, first groups of springs includes at least three first springs 7131.The first plate group includes first and fixed The fixed plate 7133 of plate 7132 and second.First fixed plate 7132 is fixed at the gas outlet of the engine 62, and described Two fixed plates 7133 are fixed in first flexible ends 7111.And at least three first spring 7131, each One end of one spring 7131 is connected with first fixed plate 7132, and the other end is connected with second fixed plate 7133.It is identical , the second spring group includes at least three second springs 7141.The second plate group includes the 3rd fixed plate 7142 and the Four fixed plates 7143.3rd fixed plate 7142 is fixed in second flexible ends 7112, the 4th fixed plate 7143 It is fixed in the 3rd flexible ends 7121, and at least three second spring 7141, each second spring 7141 One end is connected with the 3rd fixed plate 7142, and the other end is connected with the 4th fixed plate 7143.

Specifically, the gas outlet of engine 62 is set in first flexible ends 7111 in the embodiment of the present invention, and By at least three first spring 7131, the first fixed plate 7132 and the second fixed plate 7133 are flexibly connected, so made Obtain the first fixed plate 7132 and the second fixed plate 7133 is leaned in the presence of the elastic pulling force of the first spring 7131 or elasticity tension It is near or remote.The first pipe 711 is realized eventually through the first fixed plate 7132 and the close or remote of the second fixed plate 7133 It can be relatively moved relative to engine 62.The 3rd flexible ends 7121 are set in identical principle, the embodiment of the present invention In second flexible ends 7112, and by least three second spring 7141, the 3rd fixed plate 7142 and the 4th is consolidated Fixed board 7143 is flexibly connected, so that the 3rd fixed plate 7142 and the 4th fixed plate 7143 are in the elastic pulling force of second spring 7141 Or the effect of elasticity tension is close or remote.Eventually through the 3rd fixed plate 7142 and the 4th fixed plate 7143 close to or Person is remote to realize that the second pipe 712 can be relatively moved relative to the first pipe 711.

Certainly, in embodiments of the present invention or first flexible ends 7111 are set in the outlet of engine 62 On mouth, second flexible ends 7112 are set in the 3rd flexible ends 7121；Either, 7111 sets of first flexible ends On the gas outlet for being located at engine 62, the 3rd flexible ends 7121 are set in second flexible ends 7112；Either, send out The gas outlet of motivation 62 is set in first flexible ends 7111, and it is flexible that second flexible ends 7112 are set in the described 3rd Other combinations are waited on end 7121, the present invention does not limit to.In other words, as long as can realize that the first flexible ends 7111 are relative In the engine, the second flexible ends 7112 are relative to the side of being arranged that the 3rd flexible ends 7121 can be relatively moved Formula, within protection scope of the present invention.

It should be strongly noted that why needing to realize the first flexible ends 7111 relative to institute in embodiments of the present invention Engine is stated, the second flexible ends 7112 can be relatively moved relative to the 3rd flexible ends 7121, be because nobody is straight The machine of liter is in flight operation process, either due to fuselage interior component normal work, is also due to external air flow to fuselage Impact, or other extraneous factors, can all cause the fuselage 2 of depopulated helicopter to shake, especially for gas extraction system 7 For engine 62, only one of which tie point therebetween, namely the pipe 711 of engine 62 and first the first flexible ends 7111 Connected point.So because only existing an impetus, when shaking, the pipe 711 of engine 62 and first is easily caused There is connection and damage even fracture, have a strong impact on the normal flight of depopulated helicopter.Therefore, the embodiment of the present invention is soft by first Property connector 713 engine and blast pipe 71 are flexibly connected so that therebetween when frequent vibrations occur for whole fuselage 2, Can be relatively moved with the vibrations of fuselage 2, so it is effective avoid because of the frequent vibrations of fuselage 2 to engine 62 with The connection of first pipe 711 causes the technological deficiency damaged or even be broken.

Further, because the entire length of blast pipe 71 is longer, when blast pipe 71 is puted forth effort with engine in the presence of one During point, due to the vibrations of fuselage 2, the whole pipe shaft of blast pipe 71 is also easily caused to be broken.Therefore, the embodiment of the present invention is led to The first pipe 711 that the second flexible connecting member 714 will constitute blast pipe 71 is crossed, and the second pipe 712 is flexibly connected so that therebetween When frequent vibrations occur for whole fuselage 2, it can be relatively moved with the vibrations of fuselage 2, and then effectively avoid because of machine The frequent vibrations of body 2 and the technological deficiency that fracture is caused to the whole pipe shaft of blast pipe 71.

Continuing with referring to Figure 10, for the exhaust end 7122 of the second pipe 712, at least include：Tapered barrel 7123, noise elimination Room 7127.Wherein, the tapered barrel 7123 includes tapered wide opening 7124 and tapered slot 7125, and the side of the tapered barrel 7123 Several communication ports 7126 are offered on wall.The anechoic room 7127 is in hollow cylindrical, is set in the tapered barrel 7123 Peripheral position, and one end of the anechoic room 7127 aligns with tapered wide opening 7124 matching, the whole cone of other end parcel Type slot 7125.And one end that the anechoic room 7127 wraps up whole tapered slot 7125 is provided with least one exhaust outlet 7128.The central axis of the central axis and tapered slot 7125 of exhaust outlet 7128 mutually staggers simultaneously, i.e. the central shaft of the two Line is not on the same line.

Specifically, it is above-mentioned to elaborate by the way that the first pipe 711 is designed into U-shaped shape so as to what is discharged by engine 62 Tail gas is once buffered, and the tail gas after once buffering obtains first bounce in the presence of the tube wall of the first pipe 711, now portion Tail gas is divided to continue to be back in engine 62 in the presence of first bounce active force to be burnt.But, in the present invention In order to further improve the efficiency of combustion of engine 62 in embodiment, the mesh that the air in engine 62 burns completely is reached 's.The embodiment of the present invention is designed also in exhaust end 7122 includes the tapered barrel 7123 of tapered wide opening 7124 and tapered slot 7125 Structure, because the bore of tapered wide opening 7124 is more than the bore of tapered slot 7125 so that the barrel dliameter of tapered barrel 7123 is by tapered Wide opening 7124 to tapered slot 7125 is gradually decreased, and then forms tapered structure.Enter the tail of the second pipe 712 from the first pipe 711 Gas, carries out secondary bounce-back, and then realize the secondary buffer of tail gas in the presence of the tapered wall of tapered barrel 7123.After secondary buffer Gas backstreaming burnt away into engine 62, reached the purpose for making the gas in engine 62 cmpletely burn, lead to Once buffering and the secondary buffer for crossing tail gas are combined the efficiency of combustion for greatly improving engine 62.

Simultaneously as the secondary buffer structure in order to form tail gas, thus be accordingly used in what tail gas flowed out from tapered barrel 7123 The bore of tapered slot 7125 is smaller, so tail gas list from tapered slot 7125 flow out when outlet efficiency it is too low.Therefore, it is of the invention Embodiment offers several communication ports 7126 on the barrel of tapered barrel 7123, is easy to tail gas on the one hand by tapered slot 7125 flow into anechoic rooms 7127, on the other hand by the tapered anechoic room 7127 of slot 7125, and then are ensureing that tail gas is secondary While buffering, the purpose of the outlet efficiency of further raising tail gas has also been reached.

Furthermore, the central axis of the central axis of exhaust outlet 7128 and tapered slot 7125 is mutually staggered, i.e. the two Central axis is not on the same line.So because of when tail gas is directly discharged from tapered barrel 7123, in the effect of air-flow Noise is larger.And the embodiment of the present invention is arranged a noise elimination in hollow cylindrical at the tapered slot 7125 of tapered barrel 7123 Room 7127, and anechoic room 7127 is provided with one end of exhaust outlet 7128 and is provided with a flow-stopping plate, the plate face and cone of the flow-stopping plate The outgassing direction of type slot 7125 is perpendicular.When tail gas is discharged by tapered slot 7125, the air-flow of discharge is in anechoic room 7127 It is middle to collide the plate face of flow-stopping plate, then rebound.It is well known that in anechoic room 7127, when the air-flow of bounce-back hits with being about to When the air-flow of flow-stopping plate meets, pass through the principle of stacking of sound wave (crest is superimposed with trough) so that the air-flow after superposition reaches The purpose of noise elimination.Finally, the air-flow after noise elimination is discharged from exhaust outlet 7128.Serve reduces nobody and goes straight up to greatest extent The effect of tail gas noise.

For the part of cooling system 8,

Figure 17-24 are referred to, the cooling system part at least includes：Radome fairing 81 and centrifugal fan 82.The rectification Cover 81 is fixed on the first side 22 of the depopulated helicopter, is flowed into for extraneous cold air.Centrifugal fan 82 is fixed on institute The inside of radome fairing 81 is stated, and the centrifugal fan 82 is connected with the engine 62, and institute is driven by the engine 62 State centrifugal fan 82 to be rotated so that the centrifugal fan 82 after rotation drives the cold air in the radome fairing 81 Flowed.

Wherein, because engine 62 is during burning, and blast pipe 71 is either sent out during last person's gas Motivation 62 or blast pipe 71, cause the two to there is higher temperature because internal gas temperature is very high.In order to avoid this The miscellaneous part that higher temperature is had influence on inside fuselage 2, causes miscellaneous part to occur damaging or burn because temperature is too high. Figure 17,18,19 and Figure 21,22 are referred to, by fixing a radome fairing 81, the rectification on the first side 22 of depopulated helicopter The top of cover 81 is provided with a horn mouth, the inflow for external air flow.The of the bottom of the radome fairing 81 and heat shield 72 One cover body 721 is mutually connected so that the air-flow flowed into by the horn mouth of radome fairing 81 enters the first cover by the bottom of radome fairing 81 In body 721, and then air-flow is distributed to by different parts inside depopulated helicopter fuselage 2 by the first cover body 721, reached to nothing The purpose that the inner space of man-machine fuselage is cooled down, effectively avoids higher temperature and has influence on other inside fuselage 2 Part, the technological deficiency for causing miscellaneous part to occur damaging or burn because temperature is too high.

Meanwhile, in order to which the air for being more beneficial for the external world fast and efficiently flows into radome fairing 81 by the horn mouth of radome fairing 81 In.Preferably, the embodiment of the present invention is also internally provided with centrifugal fan 82 in radome fairing 81.Can as shown in figs. 23-24, should Centrifugal fan 82 is connected by clutch 83 with engine 62 so that drive centrifugal fan 82 to be rotated by engine 62. Centrifugal fan 82 in rotation forms turbine whirlpool in the inner space of radome fairing 81, and then by the horn mouth in radome fairing 81 In outer cold air suction radome fairing 81, and then the inner space of fuselage 2 is cooled down.Certainly, those skilled in the art can ,, can also be using other with drive in addition to being driven by engine 62 in order to realize the rotation of centrifugal fan 82 to understand The drive device of dynamic function is driven.For example, by installing driving battery in the inside of centrifugal fan 82, or wind will be centrifuged 82 external driving power supplies etc. are fanned, suitable for the present invention.

For the part of dynamic balance system 9,

Figure 25-26 are referred to, the dynamic balance system 9 at least includes：Tail rotor 91, rotor shaft 92 and dynamic balancing component 93.Wherein, the rotor shaft 91 is rotated with the tail rotor 91 by the dynamic balancing component 93 and is connected, and the tail rotor 91 Rotational plane and the paddle 4 rotational plane it is perpendicular.

Specifically, because two tail rotors 91 of depopulated helicopter need doing dynamic balancing tune along along the direction of rotor shaft 92 Section so that tail rotor 91, rotor shaft 92 center of gravity at the connecting portion of two tail rotors 91 so that complete machine is steady.But such as When fruit blindly increases the local weight of the rotor shaft 92 of tail rotor 91/ and reaches above-mentioned purpose, the rotating speed of tail rotor 91 can be also influenceed, And then influence the flight operation of depopulated helicopter.

However, dynamic balance system 9 provided in an embodiment of the present invention, by other portions of the non-rotor shaft 92 of tail rotor 91/ Position, sets up dynamic balancing component 93, in the case where not influenceing the speed conditions of tail rotor 91, adjusts the dynamic balancing degree of complete machine, reduces nobody The level of vibration of afterbody 3 of helicopter, overcomes because blindness increases the local weight of the rotor shaft 92 of tail rotor 91/, and to tail rotor The technological deficiency that 91 rotating speeds are impacted.

Wherein, dynamic balancing component 93 includes：At least one pad 931, dynamic balancing bar 932, the first bolt 9324 and second Bolt 9325.It is described dynamic flat and the end of the dynamic balancing bar 932 offers the first screwed hole 9321 and the second screwed hole 9322 The middle part of weighing apparatus bar 932 offers rotating hole 9323, and the rotor shaft 92 passes through the rotating hole 9323 and the tail rotor 91 rotate connection.First bolt 9324 is corresponding to be threadedly coupled with first screwed hole 9321, second bolt 9325 it is corresponding be threadedly coupled with second screwed hole 9322, and the pad 931 is placed in first bolt 9324 and institute State between the first screwed hole 9321, and/or, the pad 931 be placed in second bolt 9325 and second screwed hole Between 9322.

As stated above, in order to avoid directly increasing weight in the local of the rotor shaft 92 of tail rotor 91/, and to tail rotor 91 rotating speeds are impacted, and the embodiment of the present invention is by using opening up the first screwed hole 9321 and at the two ends of dynamic balancing bar 932 Two screwed holes 9322, and by between the first bolt 9324 and first screwed hole 9321, or the second bolt 9325 with Pad 931 is placed between second screwed hole 9322, with this by controlling the quantity of pad 931, and then accurate adjustment is reached The purpose of depopulated helicopter afterbody dynamic balancing degree, with security performance it is high the characteristics of.

, but those skilled in the art once know basic creation although preferred embodiments of the present invention have been described Property concept, then can make other change and modification to these embodiments.So, appended claims are intended to be construed to include excellent Select embodiment and fall into having altered and changing for the scope of the invention.

Obviously, those skilled in the art can carry out the essence of various changes and modification without departing from the present invention to the present invention God and scope.So, if these modifications and variations of the present invention belong to the scope of the claims in the present invention and its equivalent technologies Within, then the present invention is also intended to comprising including these changes and modification.

Claims (2)

1. a kind of exhaust passage with flexible venting tube, applied to depopulated helicopter, the depopulated helicopter includes fuselage, and Engine is provided with the fuselage, it is characterised in that the exhaust passage with flexible venting tube includes：

Blast pipe, the blast pipe is arranged on the fuselage, and be connected with the engine flexible so that the blast pipe and The engine can be relatively moved；

Exhaust end, the exhaust end is arranged on the end of blast pipe, and the exhaust end includes：

Tapered barrel, the tapered barrel includes offering several on tapered wide opening and tapered slot, and the side wall of the tapered barrel Communication port；

Anechoic room, the anechoic room is in hollow cylindrical, and the anechoic room is set in the peripheral position of the tapered barrel, and described One end of anechoic room is alignd with the tapered wide opening matching, the whole tapered slot of other end parcel, and the anechoic room It is internally provided with an exhaust outlet；

Wherein, the tail gas in the blast pipe flows into the inner space of the tapered barrel by the tapered wide opening, and from described The inner space of tapered barrel is entered in the anechoic room by the communication port and/or the tapered slot, and the tail gas is by institute State exhaust outlet discharge；

The blast pipe includes：

First pipe, first pipe is arranged on the fuselage, and be connected with the engine flexible so that first pipe and The engine can be relatively moved；

Second pipe, second pipe is flexibly connected with first pipe so that first pipe can be with relative to second pipe Relatively move, and the exhaust end is arranged at the end portion of second pipe；

Wherein, first pipe and the engine are communicated, and first pipe and second pipe are communicated so that the engine Tail gas after interior burning passes sequentially through first pipe and second pipe flows into the exhaust end；

The U-shaped shape of first pipe, and first pipe includes the first flexible ends and the second flexible ends；

Second pipe is in straight-tube shape, and second pipe includes the 3rd flexible ends, the exhaust end and the 3rd flexible ends The two ends for being arranged on second pipe of opposition；

And, the exhaust passage with flexible venting tube also includes：

First flexible connecting member, first flexible ends are connected by first flexible connecting member with the engine flexible, First pipe is relatively moved relative to the engine；

Second flexible connecting member, second flexible ends are connected by second flexible connecting member and the 3rd flexible ends flexibility Connect so that second pipe can be relatively moved relative to first pipe；

Wherein, the tail gas after being burnt in the engine is flowed into be buffered in first pipe, the tail gas after buffering Second flexible ends are passed sequentially through again and the 3rd flexible ends enter the described second pipe, and are discharged from the exhaust end.

2. there is the exhaust passage of flexible venting tube as claimed in claim 1, it is characterised in that

First flexible connecting member includes：First groups of springs and the first plate group；Wherein, first groups of springs includes at least three Individual first spring；The first plate group includes the first fixed plate and the second fixed plate；First fixed plate is fixed on the hair At the gas outlet of motivation, second fixed plate is fixed in first flexible ends, and at least three first spring, One end of each the first spring is connected with first fixed plate, and the other end is connected with second fixed plate；It is described to start The gas outlet of machine is set in first flexible ends, and passes through at least three first spring so that described first is flexible End can be relatively moved relative to the engine；

And/or,

Second flexible connecting member includes：Second spring group and the second plate group；Wherein, the second spring group includes at least three Individual second spring；The second plate group includes the 3rd fixed plate and the 4th fixed plate；3rd fixed plate is fixed on described In two flexible ends, the 4th fixed plate is fixed in the 3rd flexible ends, and at least three second spring, it is each One end of individual second spring is connected with the 3rd fixed plate, and the other end is connected with the 4th fixed plate；Described 3rd is flexible End is set in second flexible ends, and passes through at least three second spring so that the 3rd flexible ends relative to Second flexible ends can be relatively moved.