CN218317340U

CN218317340U - Aircraft engine mounting device and aircraft engine subassembly

Info

Publication number: CN218317340U
Application number: CN202222600232.3U
Authority: CN
Inventors: 刘康; 刘百奇; 刘建设
Original assignee: Beijing Xinghe Power Equipment Technology Co Ltd; Galactic Energy Beijing Space Technology Co Ltd; Anhui Galaxy Power Equipment Technology Co Ltd; Galactic Energy Shandong Aerospace Technology Co Ltd; Jiangsu Galatic Aerospace Technology Co Ltd
Current assignee: Beijing Xinghe Power Equipment Technology Co Ltd; Galactic Energy Beijing Space Technology Co Ltd; Anhui Galaxy Power Equipment Technology Co Ltd; Galactic Energy Shandong Aerospace Technology Co Ltd; Jiangsu Galatic Aerospace Technology Co Ltd
Priority date: 2022-09-29
Filing date: 2022-09-29
Publication date: 2023-01-17
Anticipated expiration: 2032-09-29

Abstract

The utility model relates to an aircraft engine installation technical field provides an aircraft engine installation device and aircraft engine subassembly, and this aircraft engine installation device includes: the positioning unit is detachably connected to a first mounting frame of the airplane and is used for radially positioning the engine; a plurality of fixed units, a plurality of fixed unit detachable connect on the inner wall of first installing frame, every fixed unit offsets with the outer wall of engine to fix the engine. During installation, the positioning unit can be installed on the first installation frame serving as an accurate installation reference, and then the engine is inserted into the positioning unit, so that the engine can be radially positioned through the inner wall of the positioning unit, and the use cost is reduced. After the radial positioning of the engine is completed, the engine is fixed by adjusting the fixing units one by one, so that a complicated adjusting process is avoided.

Description

Aircraft engine mounting device and aircraft engine subassembly

Technical Field

The utility model relates to an aircraft engine installs technical field, especially relates to an aircraft engine installation device and aircraft engine subassembly.

Background

The form of airplane power source is various, and one of them is to use solid rocket as engine to provide power. The mounting accuracy of the solid rocket relative to a full-aircraft datum is very important.

At present the solid rocket mainly adopts the installation device of solid back in front on unmanned aerial vehicle, and the terminal surface adopts screw and locating pin structure and fuselage connection before the engine promptly, and the engine rear portion adopts embracing ring and fuselage fixed connection to need the cooperation of cooperation laser tracker to adjust the armful position. However, the laser tracker has high use cost and a cumbersome hoop adjusting process.

SUMMERY OF THE UTILITY MODEL

The utility model provides an aircraft engine installation device and aircraft engine subassembly for use cost is higher among the solution prior art, and accommodation process is comparatively loaded down with trivial details defect also, has reduced use cost, avoids loaded down with trivial details adjustment process moreover.

The utility model provides an aircraft engine installation device, include:

the positioning unit is detachably connected to a first mounting frame of the airplane and is used for radially positioning the engine;

the fixing units are detachably connected to the inner wall of the first mounting frame, and each fixing unit abuts against the outer wall of the engine, so that the engine is fixed.

According to the utility model provides a pair of aircraft engine installation device, the positioning unit includes:

the positioning ring is detachably connected to the first mounting frame, and a plurality of pin holes are formed in the positioning ring along the circumferential direction;

and each pin is inserted into one pin hole.

According to the installation device of the aircraft engine provided by the utility model, a plurality of ear plates are arranged on the outer wall of the positioning ring, each ear plate is provided with a connecting hole,

the connecting holes correspond to the assembling holes in the first mounting frame, and the connecting holes and the corresponding assembling holes are detachably connected through connecting pieces.

According to the utility model provides a pair of aircraft engine installation device, fixed unit includes:

a pressure block having opposing inner and outer walls, the inner wall abutting the outer wall of the engine;

the mounting, the mounting with the rotatable connection of outer wall of briquetting, just the mounting is used for wearing to locate first installing frame.

According to the utility model provides an aircraft engine installation device, a ball socket is arranged on the outer wall;

the fixing piece comprises a spherical head and a screw rod, and the spherical head is rotatably connected to the ball socket.

According to the utility model provides a pair of aircraft engine installation device, fixed unit still includes: and the screw rod penetrates through the fixing plate, and the fixing plate is fixed on the outer wall.

According to the utility model provides an aircraft engine installation device, a plurality of guiding holes are formed between the inner wall and the outer wall;

the fixing unit further includes: and each guide pin is inserted between one guide hole and the first mounting frame.

According to the utility model provides a pair of aircraft engine installation device, the cover is equipped with spacing dish on the outer wall of uide pin, spacing dish be used for with the outer wall offsets.

According to the utility model provides a pair of aircraft engine installation device, the inner wall is the curved surface shape, the radian of inner wall with the radian of the outer wall of engine is the same.

The utility model also provides an aircraft engine component, which comprises a first mounting frame, an engine and any one of the aircraft engine mounting devices,

the positioning unit is detachably connected to the first mounting frame, the engine penetrates through the positioning unit and the first mounting frame, and each fixing unit is arranged between the first mounting frame and the engine.

The utility model provides an aircraft engine installation device, including positioning unit and a plurality of fixed unit. During installation, the positioning unit can be firstly installed on the first installation frame serving as an accurate installation reference, and then the engine is inserted into the positioning unit so as to be radially positioned through the inner wall of the positioning unit. Therefore, the engine can be accurately positioned without depending on a laser tracker, so that the device has lower use cost. After the radial positioning of the engine is completed, the engine is fixed by adjusting the fixing units one by one. The mounting process of the engine is divided into two steps of positioning and fixing, so that a complex adjusting process is avoided. Moreover, the positioning unit can be repeatedly used, and the use cost is further reduced.

The embodiment of the utility model provides an among the aircraft engine subassembly, owing to applied as above aircraft engine installation device, consequently possess like above each item advantage, no longer describe herein.

Additional aspects and advantages of embodiments of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of embodiments of the invention.

Drawings

In order to more clearly illustrate the technical solutions of the present invention or the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic structural diagram of an aircraft engine mounting device provided by the present invention;

fig. 2 is a schematic structural diagram of a positioning unit provided by the present invention;

fig. 3 is a schematic structural diagram of a fixing unit provided by the present invention;

FIG. 4 is a schematic illustration of an aircraft engine assembly according to the present disclosure;

FIG. 5 is a schematic illustration of a partial structure of an aircraft engine assembly according to the present disclosure;

reference numerals:

100: an aircraft engine mounting device;

110: a positioning unit; 111: positioning the circular ring; 112: a pin; 113: an ear plate;

120: a fixing unit; 121: briquetting; 122: an inner wall; 123: an outer wall; 124: a fixing member; 125: a fixing plate; 126: a guide pin; 127: a limiting disc;

200: a first mounting frame;

300: an engine;

1000: an aircraft engine assembly.

Detailed Description

To make the objects, technical solutions and advantages of the present invention clearer, the drawings of the present invention are combined to clearly and completely describe the technical solutions of the present invention, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on orientations or positional relationships shown in the drawings, and are only for convenience of description of the embodiments and for simplicity of description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the embodiments of the present invention. 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.

In the description of the embodiments of the present invention, it should be noted that, unless explicitly stated or limited otherwise, the terms "connected" and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the embodiments of the present invention can be understood in specific cases by those skilled in the art.

In embodiments of the invention, unless expressly stated or limited otherwise, the first feature may be directly on or directly under the second feature or indirectly via intermediate members. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature "under," "beneath," and "under" a second feature may be directly under or obliquely under the second feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

In the description of the present specification, references to the description of "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the embodiments of the present invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.

While the embodiments of the present invention will be described with reference to fig. 1 to 5, it should be understood that the following is only an exemplary embodiment of the present invention and does not limit the present invention in any way.

Fig. 1 is a schematic structural diagram of an aircraft engine mounting device provided in the present invention, please refer to fig. 1. With this aircraft engine mounting device 100, engine 300 can be mounted on first mounting frame 200 in the aircraft. Specifically, the first mounting frame 200 may be a rear frame, and a second mounting frame, i.e., a front frame, is also typically provided in the aircraft.

Engine 300 front end can be connected on this second installing frame through screw and locating pin, and engine 300 rear end can pass through the embodiment of the utility model provides an engine 300 installation device connects on this second installing frame. The first mounting frame 200 and the second mounting frame may also be used as precise references for mounting the engine 300.

The embodiment of the utility model provides an aircraft engine installation device 100 includes: a positioning unit 110 and a plurality of fixing units 120, wherein the positioning unit 110 is detachably connected to the first mounting frame 200. The plurality of fixing units 120 are detachably attached to the inner wall of the first mounting frame 200, and each fixing unit 120 is adapted to abut against the outer wall of the engine 300. That is, each of the fixing units 120 may be disposed between the first mounting frame 200 and the engine 300. When mounting, the positioning unit 110 may be mounted on the first mounting frame 200 as a precise reference for mounting, and the engine 300 may be inserted into the positioning unit 110 to radially position the engine 300 through the inner wall of the positioning unit 110. Therefore, the engine 300 can be accurately positioned without depending on a laser tracker, so that the device has lower use cost. After the radial positioning of engine 300 is completed, engine 300 is fixed by adjusting each fixing unit 120 one by one. By splitting the installation process of engine 300 into two steps, positioning and fixing, a cumbersome adjustment process is avoided.

It should be noted that the roundness of the surface of some engines 300 may be poor, and therefore, by providing the fixing units 120 at different positions, the positions of the fixing units 120 may be adjusted based on different positions, so that the fixing units 120 and the local surface of the engine 300 are better attached, and the engine 300 is stably fixed. Moreover, after the installation is completed, the positioning unit 110 can be disassembled so as to recycle the positioning unit 110, thereby reducing the use cost.

The utility model provides an aircraft engine installation device 100, including positioning unit 110 and a plurality of fixed unit 120. When mounting, the positioning unit 110 may be mounted on the first mounting frame 200 as a precise reference for mounting, and the engine 300 may be inserted into the positioning unit 110 to radially position the engine 300 through the inner wall of the positioning unit 110. Therefore, the engine 300 can be accurately positioned without depending on a laser tracker, so that the device has low use cost. After the radial positioning of the engine 300 is completed, the engine 300 is fixed by adjusting each of the fixing units 120 one by one. By splitting the installation process of engine 300 into two steps, positioning and fixing, a cumbersome adjustment process is avoided. Moreover, the positioning unit 110 can be reused, thereby further reducing the use cost.

Fig. 2 is a schematic structural diagram of a positioning unit according to the present invention, please refer to fig. 2. In an embodiment of the present invention, the positioning unit 110 includes: a positioning ring 111 and a plurality of pins 112. The positioning ring 111 is detachably connected to the first mounting frame 200, a plurality of pin holes are circumferentially formed in the positioning ring 111, and a pin 112 is inserted into each pin hole. The mounting positions of these pins 112 in the pin holes are preset, the inner end of each pin 112 is a theoretical mounting position of the outer edge of the engine 300, and the inner end of the pin 112 is used for contacting with the engine 300 so as to radially position the engine 300.

On an airplane, the installation accuracy of the first installation frame 200 and the second installation frame is ensured through the assembly fixture, that is, the positions of the first installation frame 200 and the second installation frame are determined through the connection with the assembly fixture, and after the installation is completed, the assembly fixture is separated from the first installation frame 200 and the second installation frame. According to the above process, the first mounting frame 200 is provided with the mounting holes for connecting the mounting fixture, and the mounting holes have high positional accuracy.

In an embodiment of the present invention, a plurality of ear plates 113 are disposed on the outer wall of the positioning ring 111, and each ear plate 113 has a connecting hole. Wherein, a plurality of connecting holes correspond to a plurality of pilot holes on the first installation frame 200, and the connecting holes and the corresponding pilot holes are detachably connected through a connecting member. Since the fitting hole is an inherent structure on the first mounting frame 200, the fixing of the positioning ring 111 is facilitated. The fitting hole has high positional accuracy, and therefore, the positioning ring 111 also has high positional accuracy.

When the engine 300 is mounted, after the front end surface of the engine 300 and the second mounting frame are fixed by the screws and the positioning pins, the positioning unit 110 and the fixing unit 120 are mounted on the first mounting frame 200, so that the positioning unit 110 has high position accuracy. Then, each pin 112 is inserted into a corresponding pin hole on the positioning ring 111, and the position of each fixing unit 120 is adjusted until no gap exists between the outer circle of the engine 300 and the inner end of the pin 112, which indicates that the engine 300 is positioned in place. Fixing unit 120 is then fixed to engine 300, and engine 300 is mounted.

Fig. 3 is a schematic structural diagram of a fixing unit according to the present invention, please refer to fig. 3. In an embodiment of the present invention, the fixing unit 120 includes: a pressing block 121 and a fixing member 124. The pressing block 121 is used for abutting against the outer wall of the engine 300, and the fixing member 124 is used for pushing the pressing block 121. Specifically, the pressure block 121 has an inner wall 122 and an outer wall 123 opposite to each other, the inner wall 122 being adapted to abut against the outer wall of the engine 300. One end of the fixing member 124 is rotatably connected to the outer wall 123 of the pressing block 121, and the other end of the fixing member can pass through the first mounting frame 200, so that the fixing member 124 can be pushed outside the first mounting frame 200. Therefore, by moving the fixing member 124 relative to the first mounting frame 200, the pressing member 121 can be pushed to move in the direction of the engine 300, and the engine 300 can be fixed.

Further, the fixing member 124 may be a common stud or a ball stud, which is not limited in this embodiment, and the fixing member 124 may be rotated outside the first mounting frame 200. Therefore, by moving the fixing member 124 relative to the first mounting frame 200, the pressing member 121 can be pushed to move in the direction of the engine 300, and the engine 300 can be fixed. The fixing member 124 not only can serve to connect and fasten the engine 300, but also can change the installation position of the tail of the engine 300 by screwing the fixing member 124 after the engine 300 is installed.

In a further embodiment provided by the present invention, a ball socket is provided on the outer wall 123 of the pressing block 121; the fixing member 124 is a ball stud, that is, the fixing member 124 includes a ball head rotatably connected to the ball socket and a screw rod extending outward and used for connecting with the first mounting frame 200. The ball stud can automatically adapt to the angle when being screwed down, and ensures that the pressing block 121 is attached to the tail of the engine 300 to the maximum extent.

In a further embodiment of the present invention, the fixing unit 120 further includes: a fixing plate 125 for fixing the fixing member 124, wherein the fixing plate 125 is fixed on the outer wall 123 to limit the ball head, and the screw of the fixing member 124 passes through the fixing plate 125, and the screw can rotate within a certain range of the fixing plate 125 based on the ball head.

In the conventional hoop connection structure, the hoop is in contact with the engine 300 through a line contact or a point contact. The utility model provides an in the above-mentioned embodiment, realize the laminating through the contact between face and the face between the outer wall 123 of bulb stud and briquetting 121, the self-adaptability is better. Compared with a hoop connecting structure or a common stud, the ball stud is used, so that the connecting rigidity is improved.

Moreover, an included angle between the ball stud and the outer wall 123 of the pressing block 121 is adjustable, and a relative angle between the pressing block 121 and the first mounting frame 200 can be adjusted through relative rotation between the ball stud and the outer wall 123 of the pressing block 121, so that the fitting degree of the pressing block 121 and the engine 300 is guaranteed.

In one embodiment of the present invention, a plurality of guiding holes are formed between the inner wall 122 and the outer wall 123; the fixing unit 120 further includes: and a plurality of guide pins 126, each guide pin 126 being inserted between one guide hole and the first mounting frame 200, thereby fixing the pressing piece 121 to the first mounting frame 200. Wherein the guide pin 126 functions to: the pressing block 121 is ensured to move along the axial direction of the guide pin 126 all the time so as to ensure the fit between the pressing block 121 and the engine 300.

In an embodiment of the present invention, the outer wall of the guiding pin 126 is sleeved with a limiting disc 127, the limiting disc 127 is used for abutting against the outer wall 123, and the guiding pin 126 is prevented from falling off due to passing through the pressing block 121 based on the limiting disc 127.

In one embodiment of the present invention, the inner wall 122 is curved, and the radian of the inner wall 122 is the same as the radian of the outer wall of the engine 300, so as to better fit the engine 300.

In addition, because the curved surface area of the pressing block 121 is smaller than that of the embracing ring, each pressing block 121 can be attached to a local surface of the engine 300, and the attachment degree is better.

In an embodiment of the present invention, the positioning unit 110 and the fixing unit 120 are respectively disposed at two opposite sides of the first mounting frame 200 along the axial direction, so as to better utilize the space at two sides of the first mounting frame 200. Further, the assembling holes on the first mounting frame 200 can be utilized better.

The method for mounting the aircraft engine 300 based on the device for mounting the aircraft engine 300 comprises the following steps: attaching the positioning unit 110 to a first mounting frame 200 of the aircraft; mounting a plurality of fixing units 120 on an inner wall of the first mounting frame 200; inserting engine 300 into fixing units 120, first mounting frame 200, and positioning unit 110; positioning engine 300 by adjusting the outer edge of engine 300 against the inner end of each pin 112; by adjusting the position of each fixing unit 120, the engine 300 is fixed; finally, the positioning unit 110 is disassembled to realize recycling.

Further, the fixing unit 120 includes a pressing block 121 and a fixing member 124, and a ball socket is disposed on an outer wall 123 of the pressing block 121; the fixing member 124 is a ball stud, that is, the fixing member 124 includes a spherical head rotatably connected to the ball socket and a screw rod extending outward and used for connecting with the first mounting frame 200. The ball stud can automatically adapt to the angle when being screwed down, and the pressing block 121 is guaranteed to be attached to the tail of the engine 300 to the maximum extent.

FIG. 4 is a schematic illustration of an aircraft engine assembly provided by the present disclosure; fig. 5 is a schematic view of a partial structure of an aircraft engine assembly according to the present invention, please refer to fig. 4 to 5. The utility model also provides an aircraft engine subassembly 1000, including first installing frame 200, engine 300 and any kind of aircraft engine installation device 100 of the aforesaid. The positioning unit 110 is detachably connected to the first mounting frame 200, the engine 300 passes through the positioning unit 110 and the first mounting frame 200, and each fixing unit 120 is disposed between the first mounting frame 200 and the engine 300.

The utility model provides an aircraft engine subassembly 1000 is through installing positioning unit 110 on the first installing frame 200 as the accurate benchmark of installation, inserts engine 300 again in this positioning unit 110 to through positioning unit 110's inner wall, carry out radial positioning to engine 300. Therefore, the engine 300 can be accurately positioned without depending on a laser tracker, so that the device has low use cost. After the radial positioning of the engine 300 is completed, the engine 300 is fixed by adjusting each of the fixing units 120 one by one. By splitting the installation process of engine 300 into two steps, positioning and fixing, a cumbersome adjustment process is avoided. Moreover, the positioning unit 110 can be reused, thereby further reducing the use cost.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.

Claims

1. An aircraft engine mounting arrangement, comprising:

2. An aircraft engine mounting arrangement according to claim 1, wherein the locating unit comprises:

and each pin is inserted into one pin hole.

3. An aircraft engine mounting arrangement as claimed in claim 2, wherein the outer wall of the locating ring is provided with a plurality of lugs, each lug being provided with a connecting aperture,

4. An aircraft engine mounting arrangement according to claim 1, wherein the securing unit comprises:

the pressure block is provided with an inner wall and an outer wall which are opposite, and the inner wall is abutted against the outer wall of the engine;

the fixing piece, the fixing piece with the rotatable connection of outer wall of briquetting, just the fixing piece is used for wearing to locate first installing frame.

5. An aircraft engine mounting arrangement according to claim 4, wherein the outer wall is provided with a ball socket;

6. An aircraft engine mounting arrangement according to claim 5, wherein the securing unit further comprises: and the screw rod penetrates through the fixing plate, and the fixing plate is fixed on the outer wall.

7. An aircraft engine mounting arrangement according to claim 1, wherein a plurality of pilot holes are formed between the inner wall and the outer wall;

8. An aircraft engine mounting arrangement as claimed in claim 7, wherein the guide pin is provided with a limiting disc on an outer wall thereof, the limiting disc being adapted to abut against the outer wall.

9. An aircraft engine mounting arrangement according to any one of claims 4 to 7 wherein the inner wall is curved, the arc of the inner wall being the same as the arc of the outer wall of the engine.

10. An aircraft engine assembly comprising a first mounting frame, an engine and an aircraft engine mounting device as claimed in any one of claims 1 to 9,

the positioning unit is detachably connected to the first mounting frame, the engine penetrates through the positioning unit and the first mounting frame, and the fixing units are arranged between the first mounting frame and the engine.