CN210867421U

CN210867421U - Connecting device of aero-generator

Info

Publication number: CN210867421U
Application number: CN201921912930.9U
Authority: CN
Inventors: 程振华
Original assignee: Xi'an Lantianwei Aviation Technology Co ltd
Current assignee: Xi'an Lantianwei Aviation Technology Co ltd
Priority date: 2019-11-07
Filing date: 2019-11-07
Publication date: 2020-06-26
Anticipated expiration: 2029-11-07

Abstract

The utility model discloses an aerogenerator's connecting device, which comprises a housin, the internal connection of casing has the generator body, and the bottom fixedly connected with layer board of generator body, the mounting is installed respectively to the both sides of casing, and the one end of casing installs heat dissipation mechanism, heat dissipation mechanism's inside is including the air inlet chamber, and one side that the casing was kept away from in the air inlet chamber is fixed with the hose, the opposite side gomphosis of hose has the air intake. The utility model discloses in, under heat dissipation mechanism's effect, fix the air intake in the bottom of wing through fixed screw, make it when the aviation aircraft of going, the air intake is automatic to be entered into to the natural wind intracavity, and a plurality of through-hole of rethread carry out quick heat dissipation to the generator body, prevent to install the influence that receives high temperature in the wing at the other generator of wing, cause the damage of generator, improved the life of generator.

Description

Connecting device of aero-generator

Technical Field

The utility model relates to a generator technical field especially relates to an aeroengine's connecting device.

Background

The power generator is mechanical equipment for converting energy in other forms into electric energy, and the aviation power generator is a power generator used by a space plane and generally divided into two groups of power generators which are respectively arranged at the bottom ends of wings at two sides and provide necessary power for the whole plane.

When the connecting device of the existing aero-generator is used, the generator is influenced by higher temperature generated when the wings work, internal parts of the generator are easily damaged, and the wings can drive the generator to shake violently when taking off, so that the service life is shortened.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving some aerogenerator's connecting device, receiving the higher temperature influence that the wing during operation produced in its generator, cause the damage of generator internals, the shortcoming of life-span reduction easily, and the connecting device of an aerogenerator who provides.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the utility model provides an aerogenerator's connecting device, includes the casing, the internal connection of casing has the generator body, and the bottom fixedly connected with layer board of generator body, the mounting is installed respectively to the both sides of casing, and the one end of casing installs heat dissipation mechanism, the inside of heat dissipation mechanism is including the air inlet chamber, and one side that the casing was kept away from to the air inlet chamber is fixed with the hose, the opposite side gomphosis of hose has the air intake, and the top of air intake is connected with fixed thread, the through-hole has been seted up to one side equidistance of casing, and is connected between through-hole and the air inlet chamber, install protection mechanism between casing and the layer board, and the inner wall both sides of.

As a further description of the above technical solution:

the air inlet cavity is fixedly connected with one side of the shell, and the air inlet cavity is connected with the through hole in an embedded mode.

As a further description of the above technical solution:

protection machanism's inside is including flexible outer pole, and the bottom mounting of casing has a plurality of flexible outer poles, the inside of flexible outer pole is cup jointed and is connected with flexible interior pole, and is fixed connection between flexible interior pole and the layer board, the first reset spring of bottom fixedly connected with of layer board is fixed connection between its first reset spring's bottom and the casing, and is cup jointed and be connected between first reset spring and flexible outer pole, the flexible interior pole, the inside of flexible outer pole is cup jointed and is connected with the bottom plate, and the top fixedly connected with second reset spring of bottom plate, for cup jointing and being connected between second reset spring and the flexible outer pole, and be fixed connection between second reset spring and the flexible interior pole, the bottom threaded connection of casing has first hand to twist the bolt, and first hand twists the bolt and pass and be swing joint between flexible outer pole and the bottom plate.

As a further description of the above technical solution:

the central axes of the telescopic inner rod and the telescopic outer rod are parallel, and the telescopic inner rod and the telescopic outer rod form an elastic telescopic structure through a second reset spring.

As a further description of the above technical solution:

the inside of the noise reduction mechanism is cotton including the sound is inhaled to the peak type, and the cotton both sides of inhaling sound of peak type block respectively and be connected with the draw-in groove, the internal thread connection of draw-in groove has the second hand to twist the bolt, and the second hand is twisted the bolt and is close to the peak type and inhale one side fixedly connected with gasket of the cotton of sound.

As a further description of the above technical solution:

the gasket is swing joint with the peak type sound absorption cotton, and the peak type sound absorption cotton is connected with the shell in a fitting mode.

To sum up, owing to adopted above-mentioned technical scheme, the beneficial effects of the utility model are that:

1. the utility model discloses in, under heat dissipation mechanism's effect, fix the air intake in the bottom of wing through fixed screw, make it when the aviation aircraft of going, the air intake is automatic to be entered into to the natural wind intracavity, and a plurality of through-hole of rethread carry out quick heat dissipation to the generator body, prevent to install the influence that receives high temperature in the wing at the other generator of wing, cause the damage of generator, improved the life of generator.

2. The utility model discloses in, under protection machanism's effect, through the second reset spring in the flexible outer pole rather than outside first reset spring, can make aircraft when flying, prevent that the vibration that the fuselage produced from driving the violent rocking of generator body with the vibration of wing, the range of rocking of its motor has been alleviated, and twist the bolt through twisting first hand, can extrude the bottom plate removal in the flexible outer pole, nimble regulation second reset spring's elasticity of stretching, prevent to acutely rock and cause and take place not hard up between connecting piece and the generator body.

3. The utility model discloses in, under the effect of the mechanism of making an uproar that falls, inhale the sound cotton through the peak type of casing both sides, can make its generator body adsorb the noise that its produced at the during operation, reduce the noise that its generator body produced, and through twisting the second hand-operated bolt of twisting, can be quick inhale the sound cotton with the peak type and change and maintain.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic side view of the present invention;

fig. 3 is a schematic structural view of the protection mechanism of the present invention;

FIG. 4 is a schematic structural view of the interior of the protection mechanism of the present invention;

fig. 5 is a schematic structural view of the noise reduction mechanism of the present invention.

Illustration of the drawings:

1. a housing; 2. a generator body; 3. a support plate; 4. a fixing member; 5. a heat dissipation mechanism; 501. an air inlet cavity; 502. a hose; 503. an air inlet; 504. fixing threads; 505. a through hole; 6. a protection mechanism; 601. a telescopic outer rod; 602. a telescopic inner rod; 603. a first return spring; 604. a base plate; 605. a second return spring; 606. screwing the bolt by a first hand; 7. a noise reduction mechanism; 701. peak type sound absorbing cotton; 702. a card slot; 703. screwing a bolt by a second hand; 704. and (7) a gasket.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.

Referring to fig. 1-5, a connecting device of an aircraft generator comprises a housing 1, a generator body 2 is connected inside the housing 1, a supporting plate 3 is fixedly connected to the bottom end of the generator body 2, fixing members 4 are respectively installed on two sides of the housing 1, a heat dissipation mechanism 5 is installed at one end of the housing 1, an air inlet cavity 501 is included inside the heat dissipation mechanism 5, a hose 502 is fixed on one side of the air inlet cavity 501 away from the housing 1, an air inlet 503 is embedded on the other side of the hose 502, a fixing thread 504 is connected to the top end of the air inlet 503, through holes 505 are equidistantly formed in one side of the housing 1, the through holes 505 are connected with the air inlet cavity 501, a protection mechanism 6 is installed between the housing 1 and the supporting plate 3, noise reduction mechanisms 7 are installed on two sides of the inner wall of the housing 1, two fixing members 4 are directly welded with the housing, the input end of the air inlet 503 is the same as the air inlet end of the wing.

Further, the air inlet cavity 501 is fixedly connected with one side of the casing 1, and the air inlet cavity 501 is connected with the through hole 505 in a jogged manner, so that natural air can be fed into the casing 1.

Further, the inside of the protection mechanism 6 includes a telescopic outer rod 601, the bottom end of the housing 1 is fixed with a plurality of telescopic outer rods 601, the inside of the telescopic outer rod 601 is connected with a telescopic inner rod 602 in a sleeved manner, the telescopic inner rod 602 is fixedly connected with the supporting plate 3, the bottom end of the supporting plate 3 is fixedly connected with a first return spring 603, the bottom end of the first return spring 603 is fixedly connected with the housing 1, the first return spring 603 is connected with the telescopic outer rod 601 and the telescopic inner rod 602 in a sleeved manner, the inside of the telescopic outer rod 601 is connected with a bottom plate 604 in a sleeved manner, the top end of the bottom plate 604 is fixedly connected with a second return spring 605, the second return spring 605 is connected with the telescopic outer rod 601 in a sleeved manner, the second return spring 605 is fixedly connected with the telescopic inner rod 602 in a sleeved manner, the bottom end of the housing 1 is connected with a first hand-screwing bolt 606 in a threaded manner, and the first hand-screwing bolt 606 penetrates through the telescopic outer, the first hand bolt 606 can be pressed against the base plate 604 to move within the telescoping outer pole 601.

Further, the central axes of the inner telescopic rod 602 and the outer telescopic rod 601 are parallel, and the inner telescopic rod 602 forms an elastic telescopic structure with the outer telescopic rod 601 through the second return spring 605, so that the vibration of the supporting plate 3 can be relieved.

Further, the noise reduction mechanism 7 includes a peak-shaped sound absorption cotton 701 in the interior, and the both sides of the peak-shaped sound absorption cotton 701 are respectively connected with a clamping groove 702 in a clamping manner, the internal thread of the clamping groove 702 is connected with a second hand-screwed bolt 703, and one side of the second hand-screwed bolt 703 close to the peak-shaped sound absorption cotton 701 is fixedly connected with a gasket 704, and the peak-shaped sound absorption cotton 701 has a sound absorption effect.

Further, be swing joint between gasket 704 and the peak type sound absorption cotton 701, and be the laminating between peak type sound absorption cotton 701 and the casing 1 and be connected, be convenient for install and dismantle peak type sound absorption cotton 701.

The working principle is as follows: when the aircraft is used, firstly, the device is fixed with the inside of a wing of a space plane through the fixing pieces 4 on two sides of the shell 1, then the air inlet 503 is fixed with the bottom end of the wing through the fixing threads 504, when the aircraft is running, natural wind enters the air inlet cavity 501 from the air inlet 503 and the hose 502 and enters the shell 1 through the through holes 505 on one side of the air inlet cavity 501 to quickly dissipate heat of the generator body 2, the aircraft can generate larger vibration when running or taking off again, at the moment, the vibration of the supporting plate 3 is relieved through the second return spring 605 in the telescopic outer rod 601 and the first return spring 603 outside, the generator body 2 on the supporting plate 3 is prevented from shaking violently, the first hand-screwing bolt 606 can be screwed to extrude the bottom plate 604 in the telescopic outer rod 601 to move, the expansion elasticity of the second return spring 605 is adjusted, and the cushioning strength is adjusted, through manual twisting the second and twist bolt 703, inhale the cotton 701 card of sound with its peak profile and fix the cotton 701 of sound absorption with its peak profile, inhale the cotton 701 of sound through the peak profile of casing 1 inner wall both sides, adsorb the noise that its generator body 2 produced, reduce the noise that its generator body 2 produced.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a connecting device of an aircraft generator, includes casing (1), its characterized in that, the internal connection of casing (1) has generator body (2), and the bottom fixedly connected with layer board (3) of generator body (2), mounting (4) are installed respectively to the both sides of casing (1), and the one end of casing (1) installs heat dissipation mechanism (5), the inside of heat dissipation mechanism (5) is including air inlet chamber (501), and one side that casing (1) was kept away from in air inlet chamber (501) is fixed with hose (502), the opposite side gomphosis of hose (502) has air intake (503), and the top of air intake (503) is connected with fixed thread (504), through-hole (505) have been seted up to one side equidistance of casing (1), and be connected between through-hole (505) and air inlet chamber (501), install protection machanism (6) between casing (1) and layer board (3), and noise reduction mechanisms (7) are arranged on two sides of the inner wall of the shell (1).

2. The connection device of the aircraft generator as claimed in claim 1, wherein the air inlet cavity (501) is fixedly connected with one side of the housing (1), and the air inlet cavity (501) is connected with the through hole (505) in a fitting manner.

3. The connection device of the aircraft generator as claimed in claim 1, wherein the protection mechanism (6) comprises a telescopic outer rod (601) inside, the bottom end of the housing (1) is fixed with a plurality of telescopic outer rods (601), the telescopic outer rod (601) is connected with a telescopic inner rod (602) in a sleeved manner inside, the telescopic inner rod (602) is fixedly connected with the support plate (3), the bottom end of the support plate (3) is fixedly connected with a first return spring (603), the bottom end of the first return spring (603) is fixedly connected with the housing (1), the first return spring (603) is connected with the telescopic outer rod (601) and the telescopic inner rod (602) in a sleeved manner, the telescopic outer rod (601) is connected with a bottom plate (604) in a sleeved manner inside, the top end of the bottom plate (604) is fixedly connected with a second return spring (605), the second return spring (605) is connected with the telescopic outer rod (601) in a sleeved manner, and the second return spring (605) is fixedly connected with the telescopic inner rod (602), the bottom end of the shell (1) is in threaded connection with a first hand-screwed bolt (606), and the first hand-screwed bolt (606) penetrates through the telescopic outer rod (601) and is movably connected with the bottom plate (604).

4. The connection device of the aircraft generator as claimed in claim 3, wherein the central axes of the inner telescopic rod (602) and the outer telescopic rod (601) are parallel, and the inner telescopic rod (602) and the outer telescopic rod (601) form an elastic telescopic structure through the second return spring (605).

5. The connecting device of the aircraft generator as claimed in claim 1, wherein the noise reduction mechanism (7) comprises a peak-shaped sound absorption cotton (701), the two sides of the peak-shaped sound absorption cotton (701) are respectively connected with a clamping groove (702) in a clamping manner, the internal thread of the clamping groove (702) is connected with a second hand-screwed bolt (703), and one side of the second hand-screwed bolt (703) close to the peak-shaped sound absorption cotton (701) is fixedly connected with a gasket (704).

6. The aircraft generator connecting device as claimed in claim 5, wherein the spacer (704) is movably connected with the peak type sound absorption cotton (701), and the peak type sound absorption cotton (701) is connected with the shell (1) in a fitting manner.