Rocket engine jet pipe storage and transfer frame

Abstract

The utility model discloses a rocket engine jet pipe storing and transferring frame which comprises a bottom frame, a plurality of supporting frames, a plurality of connecting rings and a plurality of binding bands, the supporting frames are vertically arranged and distributed at the upper end of the bottom frame at intervals in the front-back direction, and the supporting frames are used for jointly and horizontally supporting rocket engine jet pipes in the front-back direction. The connecting rings are equally divided into a plurality of connecting ring sets distributed above the bottom frame at intervals in the front-back direction, each connecting ring set is provided with two connecting rings, the two connecting rings in the same set are distributed at the upper end of the bottom frame at intervals in the left-right direction, and the bandages correspond to the connecting ring sets one to one. The middle of each binding belt passes through the upper end of the rocket engine jet pipe, the two ends of each binding belt are connected with the two corresponding connecting rings respectively, the multiple binding belts are used for hooping the rocket engine jet pipe to the multiple supporting frames together, and therefore the multiple supporting frames can horizontally support the rocket engine jet pipe in the front-back direction and limit the rocket engine jet pipe.

Description

Technical Field

[0001] The utility model belongs to the technical field of rocket engine nozzle storage and transportation equipment, and particularly relates to a rocket engine nozzle storage, transportation and transfer rack. Background Technique

[0002] The nozzle extension section of a small-thrust liquid rocket engine is relatively small as a whole. When the engine is assembled with the nozzle extension section, it is installed on the rocket body as a whole and transported horizontally to the launch site. If the nozzle extension section is relatively heavy or has a large area ratio (upper-stage engine), the nozzle extension section needs to be towed onto the rocket body to avoid damage to the large cantilever structure during transportation.

[0003] The nozzle extension section of a large-thrust liquid rocket engine is relatively large as a whole. Especially for the nozzle extension section of the upper-stage engine, the area ratio even reaches more than 100. Such a large and heavy nozzle extension section can only be transported separately from the engine body. After reaching the test stand or the rocket assembly plant respectively, first fix the engine body, and then assemble the nozzle extension section on the engine body. At this time, the engine is in a complete assembled state.

[0004] Due to the small overall stiffness, many cooling channels and precise docking dimensions of the nozzle extension section, the requirements for storage, transportation and assembly processes are high. Placing it vertically has a relatively high overall center, which is not conducive to transportation and fixation. It has to be flipped to the horizontal state before it can be docked and installed with the engine body. However, there is currently a lack of a storage rack that can horizontally support and place the rocket engine nozzle. Content of the Utility Model

[0005] In order to solve the above technical problems, the purpose of the utility model is to provide a rocket engine nozzle storage, transportation and transfer rack with a simple structure, which can horizontally support and place the rocket engine nozzle and prevent the rocket engine nozzle from shifting.

[0006] In order to achieve the above purpose, the technical solution of the utility model is as follows: A rocket engine nozzle storage, transportation and transfer rack includes a bottom frame, a plurality of support frames, a plurality of connecting rings and a plurality of straps. The bottom frame is horizontally arranged, and a plurality of the support frames are all vertically arranged at the upper end of the bottom frame and are spaced apart in the front-rear direction at the upper end of the bottom frame. The plurality of support frames are used to horizontally support the rocket engine nozzle in the front-rear direction together. The plurality of connecting rings are equally divided into a plurality of groups of connecting ring groups spaced apart in the front-rear direction above the bottom frame, and each group of the connecting ring groups has two connecting rings. The two connecting rings in the same group are spaced apart in the left-right direction at the upper end of the bottom frame. The plurality of straps correspond to the plurality of groups of connecting ring groups one by one. The middle of each strap passes through the upper end of the rocket engine nozzle, and its two ends are respectively connected to the corresponding two connecting rings. The plurality of straps are used to tightly fasten the rocket engine nozzle on the plurality of support frames together.

[0007] The beneficial effects of the above technical solution are as follows: In this way, the rocket engine nozzle can be horizontally supported in the front-back direction by multiple support frames, and at the same time, the rocket engine nozzle is tied by multiple straps to be limited on the multiple support frames, so as to prevent the rocket engine nozzle from falling off the multiple support frames.

[0008] In the above technical solution, a plurality of rotatable lifting rings that can swing up and down are arranged at intervals in the front-back direction on both sides of the chassis.

[0009] The beneficial effects of the above technical solution are as follows: In this way, when it is necessary to lift the rocket engine nozzle, the lifting rope of the lifting equipment can be directly connected to the multiple rotatable lifting rings. At this time, when the chassis is lifted horizontally, the rocket engine nozzle can be lifted horizontally synchronously.

[0010] In the above technical solution, the chassis includes a support plate and a plurality of bottom support members arranged at the lower end of the support plate.

[0011] The beneficial effects of the above technical solution are as follows: Its structure is simple, and the support plate is suspended, so that better protection can be provided for the rocket engine nozzle.

[0012] In the above technical solution, the support plate is an isosceles trapezoid, and its two trapezoid waists are distributed at intervals in the left-right direction.

[0013] The beneficial effects of the above technical solution are as follows: In this way, the structure of the entire chassis is more compact, and at the same time, it can cooperate with the horn-shaped structure of the rocket engine nozzle.

[0014] In the above technical solution, the bottom support member is an anchor bolt or a roller.

[0015] The beneficial effects of the above technical solution are as follows: Its structure is simple.

[0016] In the above technical solution, there are two support frames, and both ends of the rocket engine nozzle are respectively placed on the two support frames.

[0017] The beneficial effects of the above technical solution are as follows: In this way, when the rocket engine nozzle is horizontally supported by the two support frames, the force application points are located at both ends of it, so as to prevent the flow channels inside the side wall of the rocket engine nozzle from being squeezed and deformed.

[0018] In the above technical solution, the support frame includes two support bodies, and the two support bodies are distributed at intervals in the left-right direction at the corresponding ends of the chassis. The front and rear ends of the rocket engine nozzle are respectively located between the corresponding two support bodies, and are lifted to the horizontal by the multiple support bodies.

[0019] The beneficial effects of the above technical solution are as follows: In this way, the end of the rocket engine can sink between the corresponding two support bodies, so that the left and right limiting effects are good.

[0020] In the above technical solution, the support body includes a vertical column, a wheel seat and a grooved wheel. The vertical column is vertically arranged at the corresponding position on the upper end of the chassis, and the two vertical columns corresponding to the same support frame are spaced apart in the left-right direction. The wheel seat is arranged on the corresponding vertical column, and the two wheel seats corresponding to the same support frame are on the sides close to each other on the two vertical columns. The grooved wheel is rotatably installed on the corresponding wheel seat, and the rib rings at both ends of the rocket engine nozzle are supported on the corresponding two grooved wheels.

[0021] The beneficial effects of the above technical solution are as follows: In this way, the end of the rocket engine can sink between the corresponding two vertical columns, and the rib rings at its end can be supported on the corresponding two grooved wheels. In this way, the rocket engine nozzle can be limited both horizontally and axially, and the rocket engine nozzle has rolling friction with the grooved wheel when shaking, so that mechanical damage to the rocket engine nozzle will not be caused.

[0022] In the above technical solution, the distance between the two vertical columns at the rear is greater than the distance between the two vertical columns at the front; and the length of the two vertical columns at the front is greater than the length of the two vertical columns at the rear.

[0023] The beneficial effects of the above technical solution are as follows: In this way, the rocket engine nozzle has a better fit with the two support frames when horizontally supported.

[0024] In the above technical solution, the support body further includes a support seat, and the support seats are respectively installed at the upper ends of the corresponding vertical columns. The support seat has a first pin hole penetrating through the front and rear. Each rib ring has a plurality of connecting ears circumferentially spaced apart, and each connecting ear has a second pin hole penetrating through the front and rear. And each rib ring has two connecting ears corresponding to the positions of the corresponding two support seats, and the first pin hole and the second pin hole on the corresponding connecting ear and support seat are aligned and a pin connecting piece is inserted to connect them to each other.

[0025] The beneficial effects of the above technical solution are as follows: In this way, the corresponding end of the rocket engine can be detachably pin-connected by two connecting ears and two support seats on the corresponding support frame, so that the rocket engine nozzle can be further stably installed on the chassis. Description of the Drawings

[0026] Figure 1 It is a front view of the rocket engine nozzle;

[0027] Figure 2 It is Figure 1 The enlarged view of part A in

[0028] Figure 3 For Figure 1 An enlarged view of part B in

[0029] Figure 4 A front view of the rocket engine nozzle storage, transportation and transfer rack according to the embodiment of the present utility model;

[0030] Figure 5 A front view of the chassis according to the embodiment of the present utility model;

[0031] Figure 6 A schematic diagram showing the installation of the support frame on the chassis according to the embodiment of the present utility model;

[0032] Figure 7 A front view of the rocket engine nozzle placed on the rocket engine nozzle storage, transportation and transfer rack according to the embodiment of the present utility model;

[0033] Figure 8 For Figure 7 An enlarged view of part C in

[0034] Figure 9 For Figure 7 An enlarged view of part D in

[0035] In the figure: 100, rocket engine nozzle storage, transportation and transfer rack; 1, chassis; 11, pallet; 111, outer frame; 112, cross beam; 113, longitudinal beam; 12, bottom support member; 2, support frame; 21, support body; 211, column; 212, wheel seat; 213, grooved wheel; 214, support seat; 215, first pin hole; 3, connecting ring; 4, strap; 41, hook; 5, rotating lifting ring; 6, pin joint; 200, rocket engine nozzle; 210, rib ring; 220, connecting ear; 230, second pin hole. Detailed implementation manners

[0036] The principles and features of the present utility model will be described below with reference to the accompanying drawings. The examples given are only for explaining the present utility model and are not intended to limit the scope of the present utility model. In the following paragraphs, the present utility model will be described more specifically by way of example with reference to the accompanying drawings. The advantages and features of the present utility model will be clearer according to the following description and the claims. It should be noted that the accompanying drawings are all in a very simplified form and use non-precise scales, and are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present utility model.

[0037] As Figures 1 - 3As shown in the figure, in this embodiment, the rocket engine nozzle 200 is trumpet-shaped, with a large opening at one end and a small opening at the other end. Both ends thereof are provided with rib rings 210 that are coaxially distributed and protrude outward (the rib rings 210 are solid rings with relatively high structural strength). Moreover, a plurality of connecting lugs 220 that are circumferentially spaced apart are protruded on the periphery of the rib rings 210. The connecting lugs 220 are provided with second pin holes 230 that penetrate axially along the rocket engine nozzle 200. Preferably, each rib ring is provided with four connecting lugs 220 that are evenly circumferentially spaced apart. Among them, the plurality of connecting lugs at both ends correspond to and align with each other along the conical surface of the rocket engine nozzle respectively.

[0038] As Figure 4 and Figure 7 shown in the figure, this embodiment provides a storage, transfer and transportation rack 100 for a rocket engine nozzle that can horizontally support the rocket engine nozzle. Specifically, the storage, transfer and transportation rack 100 for the rocket engine nozzle includes a bottom frame 1, a plurality of support frames 2, a plurality of connecting rings 3 and a plurality of straps 4. The bottom frame 1 is horizontally arranged. A plurality of the support frames 2 are all vertically arranged at the upper end of the bottom frame 1 and are spaced apart in the front-rear direction at the upper end of the bottom frame 1. The plurality of support frames 2 are used to horizontally support the rocket engine nozzle 200 in the front-rear direction together. The plurality of connecting rings 3 are equally divided into multiple groups and are spaced apart in the front-rear direction to form connecting ring groups above the bottom frame 1. And each group of the connecting ring groups has two connecting rings 3. The two connecting rings 3 in the same group are spaced apart in the left-right direction at the upper end of the bottom frame 1. The plurality of straps 4 correspond to the multiple groups of connecting ring groups one by one. The middle of each strap 4 passes through the upper end of the rocket engine nozzle 200, and its two ends are respectively connected to the corresponding two connecting rings 3. The plurality of straps 4 are used to tightly bind the rocket engine nozzle 200 to the plurality of support frames 2 together. In this way, the rocket engine nozzle can be horizontally supported in the front-rear direction by the plurality of support frames, and at the same time, the rocket engine nozzle is bound by the plurality of straps to be limited on the plurality of support frames, so as to prevent the rocket engine nozzle from falling on the plurality of support frames. In this embodiment, the connecting rings can adopt eyebolt bolts (which are directly installed on the bottom frame). In this embodiment, four connecting rings can be provided, and the four connecting rings are also distributed at the four corners of an isosceles trapezoid (the distance between the two connecting rings in the front is less than the distance between the two connecting rings in the rear).

[0039] Specifically, in this embodiment, the strap 4 can adopt a tightening strap, and hooks 41 are respectively arranged at both ends thereof to be hooked to the corresponding two connecting rings.

[0040] In the above technical solution, a plurality of rotatable lifting rings 5 that can swing up and down are arranged at intervals along the front-rear direction on both sides of the chassis 1. In this way, when it is necessary to lift the rocket engine nozzle, the lifting rope of the lifting equipment can be directly connected to the plurality of rotatable lifting rings. At this time, the chassis can be lifted horizontally to synchronously lift the rocket engine nozzle horizontally. In this embodiment, a total of four rotatable lifting rings can also be provided, that is, two rotatable lifting rings are provided on each side of the chassis.

[0041] As Figure 5 shown, in the above technical solution, the chassis 1 includes a support plate 11 and a plurality of bottom support members 12 provided at the lower end of the support plate 11. Its structure is simple, and the support plate is suspended, so that better protection can be provided for the rocket engine nozzle; specifically, the support plate 11 is an isosceles trapezoid, and its two trapezoidal waists are distributed at intervals in the left-right direction, so that the structure of the entire chassis is more compact, and at the same time it can cooperate with the trumpet-shaped structure of the rocket engine nozzle. Specifically, the support plate is a hollow plate. Preferably, the support plate 11 includes an outer frame 111, cross beams 112 and longitudinal beams 113. The outer frame is an isosceles trapezoid, with its upper base facing forward and its lower base facing backward. A plurality of cross beams 112 are provided. The plurality of cross beams are arranged in the left-right direction and are spaced apart in the front-rear direction within the outer frame. The two ends of each cross beam are respectively connected to the two side waists of the outer frame. And a plurality of longitudinal beams arranged in the front-rear direction and spaced apart in the left-right direction are provided between any two adjacent cross beams (the two ends of the longitudinal beam are respectively connected to the corresponding two cross beams), and a plurality of longitudinal beams are also provided between the upper base and the lower base of the outer frame 111 respectively for connection between the adjacent cross beams (similar to the arrangement of the longitudinal beams between adjacent two cross beams, so it will not be elaborated here).

[0042] In the above technical solution, the bottom support member 12 is an anchor bolt or a roller. Its structure is simple. Preferably, four bottom support members can be provided. The four bottom support members are respectively provided at the lower ends of the four corners of the support plate. In addition, when the bottom support member in this embodiment is an anchor bolt, a shock-absorbing anchor bolt can be selected; and when the bottom support member in this embodiment adopts a roller, a universal wheel can be selected, and at least one of the rollers is a brakeable universal wheel.

[0043] As Figure 4 shown, in the above technical solution, two support frames 2 are provided, and the two ends of the rocket engine nozzle 200 are respectively placed on the two support frames 2. In this way, when the rocket engine nozzle is horizontally supported by the two support frames, the force points are located at its two ends, which can avoid squeezing and deforming the flow channels inside the side wall of the rocket engine nozzle.

[0044] As Figure 4As shown in the figure, in the above technical solution, the support frame 2 includes two support bodies 21, and the two support bodies 21 are spaced apart in the left - right direction at the corresponding ends of the chassis 1. The front and rear ends of the rocket engine nozzle 200 are respectively located between the corresponding two support bodies 21, and are lifted to the horizontal by the plurality of support bodies 21, so that the end of the rocket engine can sink between the corresponding two support bodies, thus achieving a good left - right limiting effect.

[0045] As Figure 6 shown in the figure, in the above technical solution, the support body 21 includes a column 211, a wheel seat 212 and a grooved wheel 213. The column 211 is vertically arranged at the corresponding position on the upper end of the chassis 1, and the two columns 211 corresponding to the same support frame 2 are spaced apart in the left - right direction. The wheel seat 212 is arranged on the corresponding column 211, and the two wheel seats 212 corresponding to the same support frame 2 are on the side close to each other on the two columns 211. The grooved wheel 213 is rotatably installed on the corresponding wheel seat 212. The rib rings 210 at both ends of the rocket engine nozzle 200 are respectively supported on the corresponding two grooved wheels 213, so that the end of the rocket engine can sink between the corresponding two columns, and the rib rings at its end can be placed on the corresponding two grooved wheels. In this way, the rocket engine nozzle can be limited both horizontally and axially, and the rocket engine nozzle has rolling friction with the grooved wheel when shaking, thus not causing mechanical damage to the rocket engine nozzle.

[0046] As Figure 4 shown in the figure, in the above technical solution, the distance between the two columns 211 at the rear is greater than the distance between the two columns 211 at the front; and the length of the two columns 211 at the front is greater than the length of the two columns 211 at the rear, so that the rocket engine nozzle has a better fit with the two support frames when horizontally supported.

[0047] As Figure 4 and Figure 6As shown, in the above technical solution, the support body 21 further includes a support base 214, and the support bases 214 are respectively installed at the upper ends of the corresponding columns 211. The support base 214 has a first pin hole 215 penetrating through the front and back. Each rib ring 210 has a plurality of connecting lugs 220 distributed at circumferential intervals, and each connecting lug 220 has a second pin hole 230 penetrating through the front and back. Each rib ring 210 has two connecting lugs 220 corresponding to the positions of the corresponding two support bases 214, and the first pin hole 215 and the second pin hole 230 on the corresponding connecting lug 220 and support base 214 are aligned and a pin connector 6 is inserted to connect them to each other. In this way, the corresponding end of the rocket engine can be detachably pin-connected by two connecting lugs and two support bases on the corresponding support frame, so that the rocket engine nozzle can be further stably installed on the chassis.

[0048] In this embodiment, the axle of the sprocket wheel is horizontally arranged in the front-back direction and connected to the corresponding wheel seat. One end of the wheel seat where the sprocket wheel is arranged is slightly tilted upward so that the sprocket wheel and the rib ring can have a better contact angle (while avoiding contact between the wheel seat and the rib ring).

[0049] Specifically, as Figures 7 - 9 shown, the connecting lugs at the smaller opening end of the rocket engine nozzle are all hinge plates, and the connecting lugs at the larger opening end of the rocket engine nozzle are all hinge supports. Correspondingly, in this embodiment, the two support bases at the front end are all hinge plates that cooperate with the corresponding two connecting lugs (at this time, the two support bases at the front end are respectively inserted into the corresponding two connecting lugs, and the first pin hole and the second pin hole are aligned to insert the pin connector), and the two support bases at the rear end are all hinge supports that cooperate with the corresponding two connecting lugs (at this time, the two connecting lugs at the rear end are respectively inserted into the corresponding two support bases, and the first pin hole and the second pin hole are aligned to insert the pin connector). In addition, in this embodiment, the upper ends of the two support bases corresponding to each support frame can be slightly bent to approach each other, so that it can have a better cooperation with the corresponding connecting lugs. Specifically, two adjacent connecting lugs on each rib ring are connected to the two support bases on the corresponding support frame. At this time, the rib ring can just be placed on the two sprocket wheels on the corresponding support frame. In the above technical solution, the pin connector 6 is a steel ball pin, and its disassembly and assembly are relatively convenient. Of course, the pin connector can also be a bolt and a nut. At this time, after the bolt passes through the corresponding first pin hole and second pin hole, the nut is tightened on the threaded end of the bolt.

[0050] The rocket engine nozzle storage, transportation and transfer rack 100 provided in this embodiment is overall symmetric about the left and right except for the strap 4. The installation positions and heights of the four grooved pulleys and the four support seats need to meet the requirement that the axis is in a horizontal state after the rocket engine nozzle 200 is installed in place.

[0051] The above are only the preferred embodiments of the present invention, and do not impose any form of limitation on the present invention. Any ordinary technician in the industry can smoothly implement the present invention according to the illustrations in the specification and the above description. However, any minor changes, modifications and evolutions made by those skilled in the art within the scope of the technical solution of the present invention by using the technical content disclosed above are equivalent embodiments of the present invention. At the same time, any equivalent changes, modifications and evolutions made to the above embodiments based on the essence of the present invention still fall within the protection scope of the technical solution of the present invention.

Claims

1. A storage, transportation and transfer rack for a rocket engine nozzle, characterized in that, It includes a chassis (1), a plurality of support frames (2), a plurality of connecting rings (3) and a plurality of straps (4). The chassis (1) is horizontally arranged. A plurality of the support frames (2) are all vertically arranged at the upper end of the chassis (1) and are spaced apart in the front-back direction at the upper end of the chassis (1). The plurality of support frames (2) are used to horizontally support the rocket engine nozzle (200) in the front-back direction together. The plurality of connecting rings (3) are equally divided into multiple groups and are spaced apart in the front-back direction in a group of connecting rings (3) above the chassis (1). And each group of the connecting rings (3) has two of the connecting rings (3). The two connecting rings (3) in the same group are spaced apart in the left-right direction at the upper end of the chassis (1). The plurality of straps (4) correspond to the multiple groups of the connecting rings (3) one by one. The middle of each strap (4) passes through the upper end of the rocket engine nozzle (200), and its two ends are respectively connected to the corresponding two connecting rings (3). The plurality of straps (4) are used to tightly hoop the rocket engine nozzle (200) on the plurality of support frames (2) together.

2. The rocket engine nozzle storage, transportation and transfer rack according to claim 1, wherein, A plurality of rotatable hanging rings (5) that can swing up and down are spaced apart in the front-back direction on both sides of the chassis (1).

3. The rocket engine nozzle storage, transportation and transfer rack according to claim 1, characterized in that, The chassis (1) includes a support plate (11) and a plurality of bottom support members (12) arranged at the lower end of the support plate (11).

4. The rocket engine nozzle storage, transportation and transfer rack according to claim 3, characterized in that, The support plate (11) is an isosceles trapezoid, and its two trapezoidal waists are spaced apart in the left-right direction.

5. The rocket engine nozzle storage, transportation and transfer rack according to claim 3, characterized in that, The bottom support member (12) is an anchor bolt or a roller.

6. The rocket engine nozzle storage, transportation and transfer rack according to claim 1, characterized in that, There are two of the support frames (2), and the two ends of the rocket engine nozzle (200) are respectively placed on the two support frames (2).

7. The rocket engine nozzle storage, transportation and transfer rack according to claim 6, wherein The support frame (2) includes two support bodies (21), and the two support bodies (21) are spaced apart in the left-right direction at the corresponding end of the chassis (1). The front and rear ends of the rocket engine nozzle (200) are respectively located between the corresponding two support bodies (21), and are supported to be horizontal by the plurality of support bodies (21).

8. The rocket engine nozzle storage, transportation and transfer rack according to claim 7, characterized in that, The support body (21) includes a column (211), a wheel seat (212) and a grooved wheel (213). The column (211) is vertically arranged at the corresponding position at the upper end of the chassis (1), and the two columns (211) corresponding to the same support frame (2) are spaced apart in the left-right direction. The wheel seat (212) is arranged on the corresponding column (211), and the two wheel seats (212) corresponding to the same support frame (2) are on the side close to each other on the two columns (211). The grooved wheel (213) is rotatably installed on the corresponding wheel seat (212). The rib rings (210) at both ends of the rocket engine nozzle (200) are both placed on the corresponding two grooved wheels (213).

9. The rocket engine nozzle storage, transportation and transfer rack according to claim 8, characterized in that, The distance between the two columns (211) at the rear is greater than the distance between the two columns (211) at the front; and the length of the two columns (211) at the front is greater than the length of the two columns (211) at the rear.

10. The rocket engine nozzle storage, transportation and transfer rack according to claim 8, characterized in that, The support body (21) further includes support seats (214), and the support seats (214) are respectively installed at the upper ends of the corresponding columns (211). The support seats (214) are provided with first pin holes (215) penetrating through in the front and rear directions. Each of the rib rings (210) is provided with a plurality of connecting lugs (220) distributed at circumferential intervals. Each of the connecting lugs (220) is provided with a second pin hole (230) penetrating through in the front and rear directions. Each of the rib rings (210) has two of the connecting lugs (220) corresponding to the positions of the corresponding two support seats (214). The first pin holes (215) and the second pin holes (230) on the corresponding connecting lugs (220) and support seats (214) are aligned and a pin connector (6) is inserted to connect them to each other.

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