CN218329573U - A cold separation interstage structure of a launch vehicle - Google Patents

Abstract

The utility model belongs to the field of carrier rockets, in particular to a cold-separated interstage structure of a carrier rocket. After the existing stage discontinuity is manufactured and assembled, the discontinuity is an integral structure and cannot be changed; When making corresponding adjustments and modifications to the volume, we can only redesign and manufacture new interstage segments to meet the requirements of use, which is time-consuming and labor-intensive. The following scheme is now proposed, which includes the first-level discontinuity and the second-level discontinuity. The first The first-level discontinuity and the second-level discontinuity form a rocket cold separation stage discontinuity, and the first-level discontinuity is fixedly sleeved with a connecting ring; it includes an adjustment mechanism arranged on the second-level discontinuity for adjusting the length of the rocket cold-separation stage discontinuity The utility model has a reasonable structure, and the length of the discontinuity of the entire rocket cold separation stage can be adjusted through the adjusting mechanism, so that the discontinuity of the rocket cold separation stage can adapt to different requirements and is convenient to use.

Description

A cold separation interstage structure of a launch vehicle

technical field

The utility model relates to the technical field of launch vehicles, in particular to a cold separation interstage structure of a launch vehicle.

Background technique

In the existing multi-stage launch vehicle, the inter-stage section is the transition section connecting the upper and lower sub-stages of the multi-stage rocket, also known as the transition section, which is an indispensable and important structure on the launch vehicle, although the launch vehicle The series and model are generally fixed, but due to the change of the project mission, the length and volume of the storage tank of the internal structure of the rocket will change, which requires corresponding adjustment and modification of the interstage section of the rocket.

At present, there are the following problems in the use of stage breaks for cold separation of launch vehicles:

1. After the level discontinuity is manufactured and assembled, the level discontinuity is an integral structure and cannot be changed;

2. When it is necessary to make corresponding adjustments and modifications according to the length and volume of the rocket storage tank, it is time-consuming and labor-intensive to redesign and manufacture new interstage sections to meet the requirements of use.

Therefore, we propose a cold-separated interstage structure of a launch vehicle to solve the above-mentioned problems.

Utility model content

The purpose of this utility model is to solve the existing stage discontinuities in the prior art. After the manufacture and assembly are completed, the discontinuity is an integral structure and cannot be changed; , can only redesign and manufacture a new interstage section to meet the use requirements, time-consuming and labor-intensive shortcomings, and propose a launch vehicle cold separation interstage section structure.

In order to achieve the above object, the utility model adopts the following technical solutions:

A carrier rocket cold-separation interstage structure, comprising a first-stage discontinuity and a second-stage discontinuity, the first-stage discontinuity and the second-stage discontinuity form a rocket cold-separation stage discontinuity, and the upper fixing sleeve of the first-stage discontinuity provided with a connecting ring;

It includes an adjustment mechanism set on the second stage discontinuity for adjusting the discontinuity length of the rocket cold separation stage, and a fixed assembly for fixing the adjustment mechanism. The length of the entire rocket cold separation stage discontinuity can be adjusted through the adjustment mechanism, so that the rocket cold separation stage Intermittent can adapt to different needs and is convenient to use.

Preferably, the adjustment mechanism includes a plurality of reinforcing rib plates annularly fixedly connected to the second-level discontinuity and a plurality of rectangular holes annularly opened on the connecting ring, the reinforcing rib plates are slidably connected in the rectangular holes, the Both sides of the stiffener plate are fixedly connected with a connecting plate for fixing the stiffener plate, the bottom of the connecting plate is fixedly connected with the surface of the second-level discontinuity, and the second-level discontinuity is pulled outward, and the multiple stiffener plates are respectively placed on the Sliding in a plurality of rectangular holes, so that the cold separation stage of the rocket can be adapted to different requirements.

Preferably, the fixing assembly includes a plurality of second bolt holes opened on the stiffener plate and a through hole annularly opened on the connecting ring, and fastening bolts are threaded on the second bolt holes. , and turn the fastening bolt downwards so that the fastening bolt is connected with the corresponding second bolt hole, so that the reinforcement plate can be fixed.

Preferably, one end of the first-level discontinuity and the second-level discontinuity is fixedly connected with a first docking frame and a second docking frame for connecting the rocket, and the entire rocket can be connected through the first docking frame and the second docking frame. The cold separation stage can be connected to the rocket intermittently.

Preferably, one end of the first docking frame, the second docking frame, the first-level discontinuity and the second-level discontinuity away from each other are provided with a plurality of first bolt holes in a ring, and through the first bolt holes, it is convenient for the first docking frame to and the second docking frame are respectively axially docked with the rear end surface of the secondary engine and the front end surface of the primary engine.

Preferably, a slide rail is fixedly connected to the rectangular hole, and the stiffener plate is slidably connected to the slide rail, and the slide rail makes the movement of the stiffener plate more stable.

The beneficial effects of the utility model:

Due to the arrangement of the connecting ring, the rectangular hole and the stiffener plate, when it is necessary to adjust the length of the entire rocket cold separation stage discontinuity, the fastening bolt is first screwed upwards to disengage the fastening bolt from the corresponding second bolt hole, and then pulled outward The second stage is discontinuous, and a plurality of stiffener plates slide in a plurality of rectangular holes respectively. After adjustment, turn the fastening bolt downwards so that the fastening bolt is connected with the corresponding second bolt hole, and then the first stage The discontinuity and the second-level discontinuity are provided with skins, so that the rocket cold separation stage discontinuity can be adapted to different needs.

By setting the first docking frame and the second docking frame, and first bolt holes are provided on the first docking frame and the second docking frame, it is convenient for the first docking frame and the second docking frame to be connected with the rear end surface of the secondary engine and the first docking frame respectively. The front end face of the stage engine is axially butted.

The utility model has a reasonable structure, and the length of the discontinuity of the entire rocket cold separation stage can be adjusted through the adjusting mechanism, so that the discontinuity of the rocket cold separation stage can adapt to different requirements and is convenient to use.

Description of drawings

Fig. 1 is the front view structure schematic diagram of a kind of launch vehicle cold separation interstage structure that the utility model proposes;

Fig. 2 is the extended structural schematic diagram of a kind of launch vehicle cold separation interstage structure that the utility model proposes;

Fig. 3 is a structural schematic diagram of rib plates and slide rails of a cold-separated interstage structure of a launch vehicle proposed by the utility model.

In the figure: 1. First-level discontinuity; 2. Second-level discontinuity; 3. Connecting ring; 4. Rib plate; 5. Connecting plate; 6. Rectangular hole; 7. First docking frame; 8. Second docking Frame; 9, first bolt hole; 10, through hole; 11, second bolt hole; 12, slide rail; 13, fastening bolt.

detailed description

The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. example.

Embodiment one

Referring to Figures 1-3, a cold-separation interstage structure of a launch vehicle includes a first-stage discontinuity 1 and a second-stage discontinuity 2. The first-stage discontinuity 1 and the second-stage discontinuity 2 form a rocket cold-separation discontinuity. A connecting ring 3 is provided on the upper fixing sleeve of the first-level discontinuity 1;

It includes an adjustment mechanism set on the second stage discontinuity 2 for adjusting the discontinuity length of the rocket cold separation stage, and a fixed assembly for fixing the adjustment mechanism. The length of the entire rocket cold separation stage discontinuity can be adjusted through the adjustment mechanism, so that the rocket cold separation The level break can adapt to different needs and is convenient to use.

Embodiment two

Improvement on the basis of Embodiment 1: a cold separation stage structure of a launch vehicle, including a first stage discontinuity 1 and a second stage discontinuity 2, the first stage discontinuity 1 and the second stage discontinuity 2 form a rocket cold separation stage Discontinuity, the first stage of discontinuity 1 and the end of the second stage of discontinuity 2 are fixedly connected with the first docking frame 7 and the second docking frame 8 for connecting the rocket, through the first docking frame 7 and the second docking frame 8 can To enable the entire rocket cold separation stage discontinuity to be connected to the rocket, the ends of the first docking frame 7, the second docking frame 8, the first stage discontinuity 1 and the second stage discontinuity 2 that are far away from each other are provided with a plurality of first bolt holes in a ring 9. Through the first bolt hole 9, it is convenient for the first docking frame 7 and the second docking frame 8 to axially dock with the rear end face of the second-stage engine and the front end face of the first-stage engine respectively. with connecting ring 3;

It includes an adjustment mechanism set on the second-stage discontinuity 2 for adjusting the discontinuity length of the rocket’s cold separation stage, and a fixing assembly for fixing the adjustment mechanism. The adjustment mechanism includes a plurality of reinforcing ribs ring-shaped and fixedly connected to the second-stage discontinuity 2 The plate 4 and a plurality of rectangular holes 6 ring-shaped on the connecting ring 3, the rib plate 4 is slidably connected in the rectangular hole 6, and both sides of the rib plate 4 are fixedly connected with the connecting plate 5 for fixing the rib plate 4 , the bottom of the connecting plate 5 is fixedly connected to the surface of the second-stage discontinuity 2, and the second-stage discontinuity 2 is pulled outward, and a plurality of rib plates 4 slide in a plurality of rectangular holes 6 respectively, so that the cold separation stage of the rocket can be discontinuous Can adapt to different needs;

The fixing assembly includes a plurality of second bolt holes 11 provided on the stiffener plate 4 and a through hole 10 annularly provided on the connecting ring 3. The second bolt holes 11 are threaded with fastening bolts 13. After adjustment, Rotate the fastening bolt 13 downwards so that the fastening bolt 13 is connected with the corresponding second bolt hole 11, so that the stiffener plate 4 can be fixed;

A slide rail 12 is fixedly connected in the rectangular hole 6, and the stiffener plate 4 is slidably connected to the slide rail 12, and the slide rail 12 makes the movement of the stiffener plate 4 more stable.

The working principle of the present utility model: since the connecting ring 3, the rectangular hole 6 and the stiffener plate 4 are provided, when it is necessary to adjust the discontinuous length of the entire rocket cold separation stage, the fastening bolt 13 is first screwed upward to make the fastening bolt 13 Disengage from the corresponding second bolt hole 11, and then pull the second-level discontinuity 2 outward, and a plurality of reinforcing rib plates 4 slide in a plurality of rectangular holes 6 respectively. After adjustment, turn the fastening bolt 13 downward to make the fastening The fastening bolts 13 are connected with the corresponding second bolt holes 11, and then the skins are arranged on the first-level discontinuity 1 and the second-level discontinuity 2, so that the cold-separation stage discontinuity of the rocket can be adapted to different requirements. The docking frame 7 and the second docking frame 8, and the first docking frame 7 and the second docking frame 8 are all provided with first bolt holes 9, so that the first docking frame 7 and the second docking frame 8 are connected with the rear of the secondary engine respectively. The end face is axially butted with the front end face of the first-stage engine.

The above is only a preferred embodiment of the utility model, but the scope of protection of the utility model is not limited thereto. The equivalent replacement or change of the new technical solution and the concept of the utility model shall be covered by the protection scope of the utility model.

Claims (6)

1. A carrier rocket cold separation stage structure, comprising a first stage discontinuity (1) and a second stage discontinuity (2), and the first stage discontinuity (1) and the second stage discontinuity (2) form a rocket The cold separation stage discontinuity is characterized in that: the first stage discontinuity (1) is fixedly sleeved with a connecting ring (3); It includes an adjustment mechanism arranged on the second-stage discontinuity (2) for adjusting the discontinuity length of the cold separation stage of the rocket, and a fixing assembly for fixing the adjustment mechanism. 2. A kind of launch vehicle cold separation interstage structure according to claim 1, characterized in that: said adjustment mechanism comprises a plurality of ribs (4) annularly fixedly connected on the second stage discontinuity (2) And a plurality of rectangular holes (6) annularly opened on the connecting ring (3), the rib plate (4) is slidably connected in the rectangular hole (6), and both sides of the rib plate (4) are fixed A connecting plate (5) for fixing the rib plate (4) is connected, and the bottom of the connecting plate (5) is fixedly connected with the surface of the second-level discontinuity (2). 3. A kind of launch vehicle cold separation interstage structure according to claim 1, characterized in that: said fixing assembly includes a plurality of second bolt holes (11) and an annular A through hole (10) is opened on the connecting ring (3), and a fastening bolt (13) is threadedly connected to the second bolt hole (11). 4. A kind of launch vehicle cold separation interstage structure according to any one of claims 1-3, characterized in that: one end of the first stage discontinuity (1) and the second stage discontinuity (2) is far away from each other The upper part is fixedly connected with a first docking frame (7) and a second docking frame (8) for connecting the rocket. 5. a kind of launch vehicle cold separation interstage structure according to claim 4, is characterized in that: described first docking frame (7), second docking frame (8), first stage discontinuity (1) and A plurality of first bolt holes (9) are ring-shaped at one end of the second-stage discontinuity (2) away from each other. 6. A kind of launch vehicle cold separation interstage structure according to claim 2, characterized in that: said rectangular hole (6) is fixedly connected with a slide rail (12), and said stiffener plate (4) slides Connect on the slide rail (12).

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