Helicopter lateral exhaust duct and auxiliary device

Abstract

The application discloses a kind of helicopter lateral exhaust pipe and auxiliary device, comprising: engine lateral exhaust pipe, horizontal limiting hole, slide bar, automatic opening and closing compensation exhaust pipe, helicopter exhaust pipe, power cabin skin, first hinge, second hinge and third hinge, wherein, the lower portion of the engine lateral exhaust pipe is equipped with the horizontal limiting hole;The first end of the slide bar is located in the horizontal limiting hole, and the second end of the slide bar is connected with the first end of the automatic opening and closing compensation exhaust pipe by the third hinge;The second end of the automatic opening and closing compensation exhaust pipe is connected with the helicopter exhaust pipe by the second hinge;The helicopter exhaust pipe is embedded in the power cabin skin;One end of the power cabin skin is connected with the helicopter by the first hinge.The helicopter lateral exhaust pipe and auxiliary device proposed in the application have simple and compact structure, and the skin opening and closing will not interfere with the exhaust pipe, which is beneficial to the routine maintenance of the helicopter.

Description

Technical Field

[0001] This invention relates to the field of aerospace vehicle technology, and in particular to a helicopter side exhaust pipe and auxiliary device. Background Technology

[0002] As one of the most distinctive creations of 20th-century aviation technology, the helicopter has greatly expanded the application range of aircraft. Compared to fixed-wing aircraft, the outstanding features of helicopters are their ability to perform low-altitude (a few meters above the ground), low-speed (starting from hovering), and constant-direction maneuvering, especially their ability to take off and land vertically in small areas. Due to these characteristics, helicopters have broad applications and development prospects, and have been widely used in many industries.

[0003] Routine maintenance and inspection of helicopters are essential for safe flight and a prerequisite for successfully completing various flight missions. Currently, some helicopter models have a three-section engine compartment skin. The skin before and after the exhaust pipe can be opened and closed freely, but the skin in the exhaust pipe area cannot be opened because there is a gap of more than 400mm between the skin before and after the exhaust pipe.

[0004] This three-section engine compartment skin structure presents significant challenges for routine maintenance. Furthermore, during helicopter maintenance, personnel are at high risk of burns from the intense heat fumes when crossing the engine exhaust nozzle. Therefore, a redesign of the helicopter exhaust pipe structure with added auxiliary devices is necessary. This would allow the skin before, after, and in the exhaust pipe area to form a unified whole that can open and close freely, improving the overall reliability of the exhaust pipe structure, reducing maintenance workload, and preventing burns from the high-temperature fumes in the engine exhaust nozzle. Summary of the Invention

[0005] The present invention aims to at least partially solve one of the technical problems in the aforementioned technologies. Therefore, the objective of the present invention is to provide a highly integrated and compact helicopter lateral exhaust pipe and auxiliary device, aiming to solve the problems of mutual interference and maintenance difficulties in the exhaust pipe components of certain helicopter models.

[0006] To achieve the above objectives, the present invention proposes a helicopter lateral exhaust pipe and auxiliary device, comprising: an engine lateral exhaust pipe, a horizontal limiting hole, a slide bar, an automatically opening and closing compensating exhaust pipe, a helicopter exhaust pipe, a power compartment skin, a first hinge, a second hinge, and a third hinge.

[0007] The horizontal limiting hole is provided below the engine side exhaust pipe;

[0008] The first end of the slide rod is located in the horizontal limiting hole, and the second end of the slide rod is connected to the first end of the automatic opening and closing compensation exhaust pipe through the third hinge;

[0009] The second end of the automatic opening and closing compensating exhaust pipe is connected to the helicopter exhaust pipe via the second hinge.

[0010] The helicopter exhaust pipe is embedded in the power compartment skin;

[0011] One end of the power compartment skin is connected to the helicopter via the first hinge.

[0012] Preferably, when the engine compartment skin is in the closed position, the engine side exhaust pipe is connected to the helicopter exhaust pipe.

[0013] Preferably, when the engine compartment skin is in the closed position, the automatic opening and closing compensating exhaust pipe is connected to the helicopter exhaust pipe to form a helicopter side exhaust pipe, and the helicopter side exhaust pipe is connected to the engine side exhaust pipe.

[0014] Preferably, the automatic opening and closing compensating exhaust pipe is connected to the helicopter exhaust pipe by an overlapping method.

[0015] Preferably, the automatic opening and closing compensation exhaust pipe is provided with an airflow guiding and protection structure for guiding the airflow away from the first hinge, the second hinge and the third hinge or pair; the airflow guiding and protection structure is also used to rectify the ejector airflow in the helicopter exhaust pipe.

[0016] Preferably, the projection of the junction between the automatic opening and closing compensating exhaust pipe and the helicopter exhaust pipe is one of a rectangle, a circle, and a rectangle with rounded edges.

[0017] Preferably, the slide bar and the horizontal limiting hole are used in a group, and several groups of horizontal limiting holes and slide bars are provided below the engine side exhaust pipe.

[0018] Preferably, the slide rod is slidably installed within the horizontal limiting hole.

[0019] Preferably, the slide bar body has a telescopic structure.

[0020] Preferably, one end of the power compartment skin is provided with a plurality of first hinges forming a first hinge group, and the connecting shaft of the plurality of first hinges is a spherical bearing.

[0021] Compared with the prior art, the beneficial effects of the present invention are:

[0022] 1. The helicopter side exhaust pipe and auxiliary device skin proposed in this invention have a high degree of integration, which is beneficial to the compact structure and weight reduction of the helicopter.

[0023] 2. In the helicopter lateral exhaust pipe and auxiliary device proposed in this invention, the skin opening and closing will not interfere with the engine exhaust pipe, which is beneficial to the daily maintenance of the helicopter, reduces the risk of burns to maintenance personnel during daily maintenance, and shortens the helicopter's return to sortie time.

[0024] 3. The helicopter side exhaust pipe and auxiliary device proposed in this invention have a simple structure. The helicopter using the helicopter side exhaust pipe and auxiliary device of this invention has fewer parts, higher reliability, and reduces the maintenance cost of the helicopter throughout its entire life cycle.

[0025] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures particularly pointed out in the written description and the accompanying drawings.

[0026] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0027] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0028] Figure 1 This is a schematic diagram of the structure of a helicopter side exhaust pipe and auxiliary device when the skin is in the maximum open position, according to an embodiment of the present invention.

[0029] Figure 2 This is a schematic diagram of the structure of a helicopter side exhaust pipe and auxiliary device when the skin is in the closed position, according to an embodiment of the present invention.

[0030] Figure 3 This is a schematic diagram of the structure of a helicopter side exhaust pipe and auxiliary device when the skin is in a partially open position, according to an embodiment of the present invention.

[0031] Reference numerals: 1. Engine side exhaust pipe, 2. Horizontal limiting hole, 3. Slide bar, 4. Automatic opening and closing compensating exhaust pipe, 5. Helicopter exhaust pipe, 6. Engine compartment skin, 7. First hinge, 8. Second hinge, 9. Third hinge. Detailed Implementation

[0032] The preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit the present invention.

[0033] like Figure 1As shown, the present invention provides a helicopter lateral exhaust pipe and auxiliary device, including: an engine lateral exhaust pipe 1, a horizontal limiting hole 2, a slide bar 3, an automatic opening and closing compensating exhaust pipe 4, a helicopter exhaust pipe 5, a power compartment skin 6, a first hinge 7, a second hinge 8, and a third hinge 9.

[0034] The horizontal limiting hole 2 is provided below the engine side exhaust pipe 1;

[0035] The first end of the slide rod 3 is located in the horizontal limiting hole 2, and the second end of the slide rod 3 is connected to the first end of the automatic opening and closing compensation exhaust pipe 4 through the third hinge 9;

[0036] The second end of the automatic opening and closing compensating exhaust pipe 4 is connected to the helicopter exhaust pipe 5 via the second hinge 8.

[0037] The helicopter exhaust pipe 5 is embedded in the power compartment skin 6;

[0038] One end of the power compartment skin 6 is connected to the helicopter via the first hinge 7.

[0039] In some embodiments of the present invention, the first hinge 7 is fixed to the helicopter, and the engine compartment skin 6 rotates about the first hinge 7 as a rotation axis, driving the helicopter exhaust pipe 5 embedded in the engine compartment skin 6 to move. When the helicopter exhaust pipe 5 moves, it drives the second hinge 8 and the automatic opening and closing compensation exhaust pipe 4 connected to the second hinge 8 to move. Since there is a second hinge 8 between the automatic opening and closing compensation exhaust pipe 4 and the helicopter exhaust pipe 5, the second end of the automatic opening and closing compensation exhaust pipe 4 rotates about the helicopter exhaust pipe 5 about the second hinge 8 as a rotation axis. The automatic opening and closing compensating exhaust pipe 4 is connected to the end of the slide rod 3 via a third hinge 9. The slide rod 3 moves horizontally within the horizontal limiting hole 2, allowing the third hinge 9 to move horizontally parallel to the horizontal limiting hole 2. (In some embodiments, the slide rod 3 is fixed in the horizontal limiting hole and does not slide, while the third hinge 9 is not fixed to the end of the slide rod 3 but can slide horizontally on the slide rod 3, allowing the third hinge 9 to move horizontally parallel to the horizontal limiting hole 2. In other embodiments, the third hinge 9 is always fixed to the end of the slide rod 3, and the slide rod 3 is always fixed in the horizontal limiting hole 2 and does not move horizontally, but the body of the slide rod 3 can freely extend and retract, allowing the third hinge 9 to move horizontally parallel to the horizontal limiting hole 2.) It should be noted that any technical solution using the above three embodiments or any combination of the above three embodiments should also be understood as being within the protection scope of this invention. Because the automatic opening and closing compensating exhaust pipe 4 is connected to the slide rod 3 through the third hinge 9, the automatic opening and closing compensating exhaust pipe 4 can also rotate around the third hinge 9 as the rotation axis. Since the automatic opening and closing compensating exhaust pipe 4 can rotate around both the third hinge 9 and the second hinge 8, when the power compartment skin 6 is opened, the automatic opening and closing compensating exhaust pipe 4 will slide parallel to the right and move under the cooperative action of the second hinge 8 and the third hinge 9. Figure 1 This is a schematic diagram of the helicopter's side exhaust pipes and auxiliary equipment when the engine compartment skin 6 is fully extended. Figure 3 This is a schematic diagram of the helicopter's side exhaust pipes and auxiliary equipment when the engine compartment skin is in its normal position. The above describes the structure. Figures 1 to 2 The process.

[0040] In some embodiments of the present invention, as the engine compartment skin 6 gradually opens, the automatic opening and closing compensation exhaust pipe 4 gradually separates from the helicopter exhaust pipe 5, at which time the angle of the skin opening gradually increases ( Figures 3 to 1 During the process, the automatic opening and closing compensation exhaust pipe 4 gradually moves away from the engine side exhaust pipe 1, while the automatic opening and closing compensation exhaust pipe 4 and the helicopter exhaust pipe 5 do not interfere with the engine side exhaust pipe 1. Under the action of the second hinge 8, the third hinge 9 and the first hinge 7, the slide bar 3 always remains in a horizontal state.

[0041] In some embodiments of the present invention, when the power compartment skin 6 is closed (e.g.) Figure 2As shown, the helicopter exhaust pipe 5 and the automatic opening and closing compensation exhaust pipe 4 are fitted together and overlap with the engine side exhaust pipe 1, so that the engine side exhaust pipe 1 can be inserted into the helicopter exhaust pipe 5.

[0042] In some embodiments of the present invention, when the engine compartment skin 6 is closed, the automatic opening and closing compensation exhaust pipe 4 and the helicopter exhaust pipe 5 together form the helicopter side exhaust pipe.

[0043] In some embodiments of the present invention, the opening and closing compensation exhaust pipe 4 and the helicopter exhaust pipe 5 are connected by an overlapping method to prevent gas leakage into the helicopter power compartment.

[0044] In some embodiments of the present invention, the projection of the junction of the automatic opening and closing compensating exhaust pipe 4 and the helicopter exhaust pipe 5 can be rectangular, rounded, or other irregularly shaped, and those skilled in the art can choose according to their needs.

[0045] In some embodiments of the present invention, the automatic opening and closing compensation exhaust pipe 4 may be provided with some airflow guiding and protection structures, which can prevent high-temperature hot air from affecting the second hinge 8 and the third hinge 9, and can also rectify the ejector airflow in the helicopter exhaust pipe 5.

[0046] In some embodiments of the present invention, the slide rods 3 are used in groups at the horizontal limiting holes 2, and one group, two groups or even more groups can be used.

[0047] In some embodiments of the present invention, the slide bar 3, the second hinge 8, the third hinge 9 and the first hinge 7 can be fitted with either cylindrical surfaces or with spherical bearings.

[0048] In some embodiments of the present invention, the first hinge 7 can be a hinge group composed of several hinges, the second hinge 8 can also be a hinge group composed of several hinges, and the third hinge 9 can also be a hinge group composed of several hinges. When a hinge group is used, a joint bearing is provided in the hinge.

[0049] According to the embodiment of the present invention, which has been simulated in three dimensions within the helicopter engine compartment, the helicopter lateral exhaust pipe and auxiliary device skin proposed in this invention have a high degree of integration, which is beneficial for the compact helicopter structure and weight reduction. Helicopters using the lateral exhaust pipe and auxiliary device of this invention have fewer parts, higher reliability, and reduced maintenance costs throughout the helicopter's life cycle. Simultaneously, the skin opening and closing will not interfere with the engine exhaust pipe, which is beneficial for routine helicopter maintenance, reduces the risk of burns to maintenance personnel during routine maintenance, and shortens the helicopter's return-to-flight time.

[0050] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A helicopter lateral exhaust pipe and auxiliary device, characterized in that, include: Engine side exhaust pipe, horizontal limiting hole, slide bar, automatic opening and closing compensating exhaust pipe, helicopter exhaust pipe, engine compartment skin, first hinge, second hinge and third hinge, The horizontal limiting hole is provided below the engine side exhaust pipe; The first end of the slide rod is located in the horizontal limiting hole, and the second end of the slide rod is connected to the first end of the automatic opening and closing compensation exhaust pipe through the third hinge; The second end of the automatic opening and closing compensating exhaust pipe is connected to the helicopter exhaust pipe via the second hinge. The helicopter exhaust pipe is embedded in the power compartment skin; One end of the power compartment skin is connected to the helicopter via the first hinge; When the engine compartment skin is in the closed position, the engine side exhaust pipe is connected to the helicopter exhaust pipe; When the engine compartment skin is in the closed position, the automatic opening and closing compensating exhaust pipe is connected to the helicopter exhaust pipe to form a helicopter side exhaust pipe, and the helicopter side exhaust pipe is connected to the engine side exhaust pipe.

2. The helicopter lateral exhaust pipe and auxiliary device as described in claim 1, characterized in that, The automatic opening and closing compensation exhaust pipe is connected to the helicopter exhaust pipe by an overlapping method.

3. The helicopter lateral exhaust pipe and auxiliary device as described in claim 1, characterized in that, The automatic opening and closing compensation exhaust pipe is provided with an airflow guiding and protection structure for guiding the airflow away from the first hinge, the second hinge and the third hinge or pair; the airflow guiding and protection structure is also used to rectify the ejector airflow in the helicopter exhaust pipe.

4. The helicopter lateral exhaust pipe and auxiliary device as described in any one of claims 1-3, characterized in that, The projection of the junction between the automatic opening and closing compensating exhaust pipe and the helicopter exhaust pipe is one of a rectangle, a circle, or a rectangle with rounded edges.

5. The helicopter lateral exhaust pipe and auxiliary device as described in claim 1, characterized in that, The slide bar and the horizontal limiting hole are used in a group, and several sets of horizontal limiting holes and slide bars are provided below the engine side exhaust pipe.

6. The helicopter lateral exhaust pipe and auxiliary device as described in claim 1, characterized in that, The slide bar is slidably installed in the horizontal limiting hole.

7. The helicopter lateral exhaust pipe and auxiliary device as described in claim 1, characterized in that, The slide bar body has a telescopic structure.

8. The helicopter lateral exhaust pipe and auxiliary device as described in claim 1, characterized in that, One end of the power compartment skin is provided with a number of first hinges forming a first hinge group, and the connecting shaft of the number of first hinges is a spherical bearing.

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