CN219056574U

CN219056574U - Helicopter exhaust system

Info

Publication number: CN219056574U
Application number: CN202223166493.5U
Authority: CN
Inventors: 刘昱含; 陈诗萌; 田巍; 高岚
Original assignee: Shenyang Yuncheng Navigation Technology Co ltd
Current assignee: Shenyang Kailong Jiuying Technology Co ltd
Priority date: 2022-11-28
Filing date: 2022-11-28
Publication date: 2023-05-23
Anticipated expiration: 2032-11-28

Abstract

The utility model discloses a helicopter exhaust system, which relates to the technical field of helicopter design and comprises a helicopter equipment cabin body, wherein a fixed block is arranged at the top of the helicopter equipment cabin body, a hydraulic cylinder is arranged at the bottom of the fixed block, and a U-shaped block is arranged at the bottom end of an output shaft of the hydraulic cylinder. When the double-shaft motor is used, the hydraulic cylinder works to drive the first connecting rod and the second connecting rod to drive the first sliding rod, the second sliding rod, the two connecting columns and the two bearings to move in the direction away from each other, the two bearings drive the U-shaped rod and the racks to move in the direction away from each other, the two racks are meshed with the two gears to drive the two bellows to rotate in the same direction, the double-shaft motor works, the output shaft of the double-shaft motor drives the two rotating shafts to rotate, the two bearings, the two U-shaped rods, the two racks and the two connecting shafts drive the two gears and the two bellows to rotate, and the two racks are always kept in a meshed state with the two gears.

Description

Helicopter exhaust system

Technical Field

The utility model relates to the technical field of helicopter design, in particular to a helicopter exhaust system.

Background

In unmanned aerial vehicle field, how not to increase too much load and influence the condition of aircraft performance for unmanned aerial vehicle, to dispel the heat to unmanned aerial vehicle's engine, it is always research trending to promote engine performance, it also becomes main research direction to utilize the forced air cooling to dispel the heat, publication number CN 109511245B among the prior art has disclosed a helicopter equipment cabin and advances exhaust heat radiation structure, it can dispel the heat to helicopter equipment cabin, but neglected the helicopter when flying, often need adjust different postures, because the air intake air exit fixed in position that its set up and unable regulation still guarantee effective quick air inlet after the aircraft adjusts the posture, to above-mentioned problem, so a helicopter exhaust system is proposed.

Disclosure of Invention

The present utility model is directed to a helicopter exhaust system to solve the above-mentioned problems.

In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides a helicopter exhaust system, includes the helicopter equipment cabin body, the fixed block is installed at the top of the helicopter equipment cabin body, the pneumatic cylinder is installed to the bottom of fixed block, the U-shaped piece is installed to the output shaft bottom of pneumatic cylinder, rotate on the U-shaped piece and install first connecting rod and second connecting rod, the other end of first connecting rod rotates and installs first slide bar, the other end of second connecting rod rotates and installs the second slide bar, first slide bar with the spliced pole is all installed to the bottom of second slide bar, two the bearing is installed to the bottom of spliced pole, the bi-axial motor is all connected with the pivot through the fixed column on the bottom side inner wall of the helicopter equipment cabin body, two the U-shaped hole has all been seted up in the pivot, two the U-shaped hole orientation is opposite, two equal slidable mounting has the U-shaped pole in the U-shaped hole, two the one end that the U-shaped pole is close to each other is installed respectively on the inner wall of two the bearing, two the U-shaped pole with the bottom all installs the spliced pole, two inner race, two the two inner race grooves are equipped with two in the two inner race grooves are equipped with in the two, two inner race grooves are connected with each other, two the two inner race grooves are kept away from each other, two inner race grooves are equipped with each other, two inner race and two the two inner shafts are connected with each other, and are equipped with the two through-shafts.

Preferably, the lateral parts of the two bellows are provided with air openings, the air openings are provided with filter assemblies, and the lateral parts of the two bellows, which are far away from the air openings, are communicated with the helicopter equipment cabin body through hoses.

Preferably, the filter assembly comprises a filter screen mounted at the mouth of both said bellows.

Preferably, two bellows are all installed crossover sub with the through-hole that helicopter equipment cabin body both sides portion was seted up on, the hose passes through crossover sub and realizes sealing connection.

Preferably, two sides of the bellows, which are close to each other, are provided with avoidance grooves, and two ends of the connecting shaft are fixedly arranged on inner walls at two sides of the avoidance grooves.

Preferably, the positions of the tuyeres of the two bellows are opposite.

Preferably, the hydraulic cylinder corresponds to the position of the biaxial motor.

When the dual-shaft type air conditioner is used, the hydraulic cylinder works, the output shaft of the hydraulic cylinder drives the U-shaped block, the first connecting rod and the second connecting rod to move downwards, the first connecting rod and the second connecting rod drive the first sliding rod, the second sliding rod, the two connecting columns and the two bearings to move away from each other, the two bearings drive the U-shaped rod and the racks to move away from each other, the two racks are meshed with the two gears to drive the two bellows to rotate in the same direction, so that the heat dissipation efficiency of an airplane can be guaranteed when the airplane flies leftwards and rightwards, the dual-shaft motor works, the output shaft of the dual-shaft motor drives the two rotating shafts, the two bearings, the two U-shaped rods, the two racks and the two connecting shafts to rotate, and the two connecting shafts drive the two gears and the two bellows to rotate, so that the two racks always keep meshed with the two gears, and the heat dissipation efficiency of the airplane can be guaranteed when the airplane flies forwards or backwards.

In the utility model, the positions of the wind openings of the two wind boxes are opposite, and the arrangement has the advantage that the air circulation flow characteristic can be utilized, so that wind can quickly circulate to dissipate heat.

Drawings

FIG. 1 is a schematic perspective view of the present utility model;

FIG. 2 is a schematic elevational view of the present utility model;

FIG. 3 is a schematic view of a portion of the structure of FIG. 1;

FIG. 4 is an enlarged schematic view of the structure of FIG. 3A;

FIG. 5 is a schematic cross-sectional view of the novel shaft;

fig. 6 is a schematic structural view of the connection of the connecting shaft, the gear and the rotating shaft according to the present utility model.

In the figure: 1. a helicopter equipment cabin; 2. a fixed block; 3. a hydraulic cylinder; 4. a first link; 5. a second link; 6. a first slide bar; 7. a second slide bar; 8. a connecting column; 9. a bearing; 10. a rotating shaft; 11. a rack; 12. a gear; 13. a wind box; 14. a filter screen; 15. a biaxial motor; 16. a hose; 17. a conversion joint; 18. a U-shaped rod; 19. and a connecting shaft.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

In the description of the present disclosure, it should be noted that the positional or positional relationship indicated by the terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", "top", "bottom", etc. are based on the positional or positional relationship shown in the drawings, are merely for convenience of describing the present disclosure and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present disclosure. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

It should be noted that standard parts used in the present application may be purchased from market, and may be customized according to the description of the specification and the drawings. Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this disclosure will be understood by those of ordinary skill in the art in the specific context, and without explicit limitation, machines, components, and equipment may take any form conventionally known in the art.

In this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of other like elements in a process, method, article or apparatus that comprises the element.

Examples: referring to a helicopter exhaust system shown in fig. 1-6, including the helicopter equipment cabin body 1, fixed block 2 is installed at the top of helicopter equipment cabin body 1, pneumatic cylinder 3 is installed to the bottom of fixed block 2, the U-shaped piece is installed to the output shaft bottom of pneumatic cylinder 3, install first connecting rod 4 and second connecting rod 5 on the U-shaped piece in the rotation, first slide bar 6 is installed in the other end rotation of first connecting rod 4, second slide bar 7 is installed in the other end rotation of second connecting rod 5, connecting column 8 is all installed to the bottom of first slide bar 6 and second slide bar 7, bearing 9 is installed to the bottom of two connecting columns 8, install biaxial motor 15 through the fixed column on the bottom side inner wall of helicopter equipment cabin body 1, two output of biaxial motor 15 all are connected with pivot 10, the U-shaped hole has all been seted up on two pivot 10, two U-shaped holes are opposite in the orientation, two U-shaped rod 18 are installed in the equal sliding movement, the one end that two U-shaped rods 18 are close to each other is installed respectively on the inner race inner wall of two bearings 9, two inner race 12 are equipped with the two end that keep away from each other in the two rack and pinion groove, two inner race 19 are located the two inner race 10, two inner race 12 are connected with the two inner race 12 are located the two end that keep away from each other, two inner race 10, two inner race 12 are connected with the two inner race 12 are located the two inner race, two end of the two inner race groove, two inner race 12 is far away from each other, two inner race 12 is equipped with the two end, and two inner race groove pieces are connected with each other, and two inner race groove, and two end piece is located the two inner race 12 is far away from each.

By the above structure: when the airplane cooling device is used, the hydraulic cylinder 3 works, the output shaft of the hydraulic cylinder 3 drives the U-shaped block, the first connecting rod 4 and the second connecting rod 5 to move downwards, the first connecting rod 4 and the second connecting rod 5 drive the first sliding rod 6, the second sliding rod, the two connecting columns 8 and the two bearings 9 to move away from each other, the two bearings 9 drive the U-shaped rod 18 and the racks 11 to move away from each other, the two racks 11 and the two gears are meshed to drive the two bellows 13 to rotate in the same direction, so that the cooling efficiency can be ensured when the airplane flies leftwards and rightwards, the double-shaft motor 15 works, the output shaft of the double-shaft motor drives the two rotating shafts 10, the two bearings 9, the two U-shaped rods 18, the two racks 11 and the two connecting shafts 19 to rotate, the two connecting shafts 19 drive the two gears 11 and the two bellows 13 to always keep the meshing state with the two gears 12, and the cooling efficiency can be ensured when the airplane flies forwards or backwards.

As shown in fig. 1, the sides of the two bellows 13 are provided with air openings, the air openings are provided with filter assemblies, the sides of the two bellows 13 far away from the air openings are communicated with the helicopter equipment cabin body 1 through hoses 16, and the arrangement has the advantage that the connection with the helicopter equipment cabin body is still ensured while the steering of the bellows 13 is regulated.

As shown in fig. 4, the filter assembly includes a filter screen 14 installed at the mouth of two bellows 13, which has the advantage of preventing foreign matters contained in the air from being sucked into the bellows 13.

As shown in fig. 1, two bellows 13 and through holes formed in two side portions of the helicopter equipment cabin body 1 are respectively provided with an adapter 17, and the hose 16 cannot be fixedly connected with the bellows 13 and the helicopter equipment cabin body 1, so that the adapter 17 is installed, and the hose 16 is in sealed connection through the adapter 17.

As shown in FIG. 4, the side of two bellows 13 that are close to each other has been seted up and has been dodged the groove, and the both ends fixed mounting of connecting axle 19 dodges on the both sides inner wall in groove, and the benefit of setting like this is that connecting axle 19 can drive bellows 13 upset simultaneously when overturning along with pivot 10.

As shown in fig. 3, the positions of the air openings of the two bellows 13 are opposite, which has the advantage of using the air circulation flow characteristic to enable the air to circulate rapidly for heat dissipation.

As shown in fig. 1, the hydraulic cylinder 3 corresponds to the position of the double-shaft motor 15, so that the hydraulic cylinder 3 can ensure that two sides are simultaneously controlled during operation, and the positions of components at two sides are corresponding.

Working principle: when the helicopter is used, firstly, when the helicopter receives an ascending and descending instruction, the hydraulic cylinder 3 is reset, the two bellows 13 are kept in a fixed state, one side of the hydraulic cylinder is induced to draft, the other side of the hydraulic cylinder is exhausted after circulation, when the aircraft receives an advancing or retreating instruction, the double-shaft motor 15 is started, two output shafts of the double-shaft motor 15 rotate to drive the two rotating shafts 10 to rotate, the two rotating shafts 10 rotate to drive the two U-shaped rods 18 and the two connecting shafts 19 to rotate, the two U-shaped rods 18 rotate to drive the two racks 11 to rotate, the two connecting shafts 19 drive the two gears 12 to rotate, the two racks 11 and the two gears 12 are kept in a meshed state at all times, the two connecting shafts 19 rotate to drive the two bellows 13 to overturn, so that air inlets on the two bellows 13 are respectively aligned horizontally at the front end and the rear end to ensure the air inlet and outlet efficiency, when the aircraft receives a leftward or rightward instruction, the hydraulic cylinder 3 is started, the output shafts of the hydraulic cylinder 3 move downwards, the U-shaped block is driven to move downwards, the first connecting rod 4 and the second connecting rod 5 are driven to move downwards, the first sliding rod 6 and the second sliding rod 7 are driven to move in the direction of mutual distancing, the two connecting columns 8 are driven to move in the direction of mutual distancing, the two bearings 9 are driven to move in the direction of mutual distancing, the two U-shaped rods 18 are driven to move in the direction of mutual distancing, the two racks 11 are respectively meshed with the two gears 12 to drive the two gears 12 to rotate in the same direction, the two connecting shafts 19 are driven to rotate in the same direction, the two connecting shafts 19 rotate in the same direction to drive the two bellows 13 to rotate in the same direction, so that air inlets on the two bellows 13 are respectively aligned horizontally to two sides, air inlet and air outlet efficiency is guaranteed, air enters from an air inlet of the bellows 13, air enters the helicopter equipment cabin body 1 through a hose 16, heat is circularly driven to enter the other bellows 13 from the hose 16 on the other side, and finally air is discharged from an air outlet, and cooling work is completed.

Finally, it should be noted that: the foregoing description of the preferred embodiments of the present utility model is not intended to be limiting, but rather, although the present utility model has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements or changes may be made without departing from the spirit and principles of the present utility model.

Claims

1. A helicopter exhaust system comprising a helicopter equipment nacelle (1), characterized in that: the utility model discloses a helicopter equipment cabin, including helicopter equipment cabin body, fixed block (2) are installed at the top of helicopter equipment cabin body (1), pneumatic cylinder (3) are installed to the bottom of fixed block (2), U-shaped piece is installed to the output shaft bottom of pneumatic cylinder (3), rotate on the U-shaped piece and install first connecting rod (4) and second connecting rod (5), first slide bar (6) are installed in the other end rotation of first connecting rod (4), second slide bar (7) are installed in the other end rotation of second connecting rod (5), connecting column (8) are all installed to the bottom of first slide bar (6) with connecting column (7), two connecting column (8) are installed in the bottom of bottom, through the fixed column on the bottom side inner wall of helicopter equipment cabin body (1), two output ends of biax motor (15) all are connected with pivot (10), two U-shaped hole have all been seted up on pivot (10), two U-shaped hole orientation are opposite, two U-shaped hole orientation is installed in the other end rotation of second slide bar (7), two U-shaped hole (18) are installed in the inner circle (18) respectively, two inner circle (18) are installed in the inner circle (18) respectively, one end is kept away from each other in the inner circle (18) respectively, holes are formed in two side portions of a helicopter equipment cabin body (1), two ends, away from each other, of the rotating shafts (10) penetrate through the two holes respectively, grooves are formed in the two ends, away from each other, of the rotating shafts (10), through holes are formed in the inner walls, away from each other, of the grooves, connecting shafts (19) are rotatably installed in the through holes, gears (12) located in the grooves are fixedly sleeved on the connecting shafts (19), the two gears (12) are meshed with two racks (11) respectively, and bellows (13) are installed at two ends of the connecting shafts (19).

2. A helicopter exhaust system as claimed in claim 1 wherein: the lateral parts of the two bellows (13) are provided with air openings, filter assemblies are arranged at the air openings, and the lateral parts of the two bellows (13) away from the air openings are communicated with the helicopter equipment cabin body (1) through hoses (16).

3. A helicopter exhaust system as claimed in claim 2 wherein: the filter assembly comprises a filter screen (14) arranged at the air inlet of the two bellows (13).

4. A helicopter exhaust system as claimed in claim 2 wherein: the two bellows (13) and through holes formed in two side parts of the helicopter equipment cabin body (1) are respectively provided with an adapter joint (17), and the hoses (16) are in sealing connection through the adapter joints (17).

5. A helicopter exhaust system as claimed in claim 1 wherein: the two bellows (13) are close to each other and are provided with avoidance grooves on one side, and two ends of the connecting shaft (19) are fixedly arranged on two side inner walls of the avoidance grooves.

6. A helicopter exhaust system as claimed in claim 1 wherein: the positions of the tuyeres of the two bellows (13) are opposite.

7. A helicopter exhaust system as claimed in claim 1 wherein: the hydraulic cylinder (3) corresponds to the position of the double-shaft motor (15).