CN112611269A - Carrier rocket - Google Patents

Abstract

The invention provides a carrier rocket which is large in bearing capacity, light in weight, simple in structure, convenient to assemble and high in reliability. The carrier rocket comprises a fairing and a power system which are connected with each other, wherein the power system comprises a four-stage structure, a three-stage structure, a two-stage structure and a one-stage structure which are connected with each other, and the four-stage structure comprises a four-stage shell cover and a four-stage engine arranged in the four-stage shell cover.

Description

Carrier rocket

Technical Field

The invention relates to the technical field of aviation equipment, in particular to a carrier rocket.

Background

The effective loads such as various satellites and the like enter the space, and a carrier rocket is usually adopted as a transport tool. The structural system is used as a main subsystem of the carrier rocket, maintains the appearance of the rocket body, provides reliable installation for internal systems, bears loads in the processes of assembly, transportation, flight and the like, provides protection for each system, and keeps the integrity of the carrier rocket. Therefore, the design of the structural system is crucial, the structural weight is reduced, the carrying capacity is improved, the flight reliability of the carrier rocket is ensured, and the satellite is enabled to enter the orbit safely and with high precision.

In the prior art, the fourth stage of the four-stage carrier rocket generally directly uses the shell of a fourth-stage engine as the shell of the carrier rocket, and the fourth stage is designed into a conical structure. The design of the structural system enables the fourth-stage engine to be flat in appearance, limits the performance of the fourth-stage engine and simultaneously causes the overall weight of the carrier rocket to be larger.

Disclosure of Invention

Therefore, the carrier rocket is large in bearing capacity, light in weight, simple in structure, convenient to assemble and high in reliability.

The carrier rocket comprises a fairing and a power system which are connected with each other, wherein the power system comprises a four-stage structure, a three-stage structure, a two-stage structure and a one-stage structure which are connected with each other, wherein the four-stage structure comprises a four-stage housing and a four-stage engine arranged in the four-stage housing.

Optionally, the tertiary structure includes a tertiary engine and a first tertiary shroud and a second tertiary shroud connected at two ends of the tertiary engine, wherein two ends of the quaternary shroud are connected with the fairing and the first tertiary shroud respectively.

Optionally, the secondary structure comprises a secondary engine and a first secondary shroud and a second secondary shroud connected across the secondary engine, wherein the second tertiary shroud is connected to the first secondary shroud.

Optionally, the primary structure comprises a primary engine, and a first primary shroud and a second primary shroud connected at two ends of the primary engine, wherein the second primary shroud is connected with the first primary shroud.

Optionally, a rudder is arranged on the second primary housing cover.

Optionally, the rudder is multiple, and the multiple rudders are arranged at intervals along the axial direction of the second primary housing cover.

Optionally, the launch vehicle further comprises a cable cover attached to an exterior side of the primary, secondary, and tertiary structures.

Optionally, the fairing comprises a quadrant fairing and a quadrant fairing interconnected.

Optionally, a separation structure is provided between the fourth stage casing and the first third stage casing, between the second third stage casing and the first second stage casing, between the second stage casing and the first stage casing.

Optionally, the quaternary housing is of cylindrical configuration.

The technical scheme of the invention has the following advantages:

by utilizing the technical scheme of the invention, compared with the prior art, the four-stage shell cover is arranged outside the four-stage engine, so that the design performance of the four-stage engine is improved, and the structural system scheme of the carrier rocket is adopted, so that the carrier rocket is simple in design, safe and reliable, light in structural weight and high in bearing efficiency.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings 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 other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 shows a schematic structural view of a launch vehicle of the present invention;

FIG. 2 shows a schematic view of the fairing of the launch vehicle of FIG. 1;

FIG. 3 shows a schematic structural diagram of the quaternary structure of the launch vehicle of FIG. 1;

FIG. 4 shows a schematic structural view of the three-stage structure of the launch vehicle of FIG. 1;

FIG. 5 shows a schematic structural diagram of the secondary structure of the launch vehicle of FIG. 1;

FIG. 6 shows a schematic structural view of the primary structure of the launch vehicle of FIG. 1;

figure 7 shows a schematic structural view of the rudder of the launch vehicle of figure 1; and

figure 8 shows a schematic structural view of the cable cover of the launch vehicle of figure 1.

Description of reference numerals:

10. a primary structure; 11. a primary engine; 12. a first primary shroud; 13. a second primary housing; 20. a secondary structure; 21. a secondary engine; 22. a first secondary housing; 23. a second secondary housing; 30. a tertiary structure; 31. a tertiary engine; 32. a first tertiary shroud; 33. a second tertiary shell; 40. a quaternary structure; 41. a four-stage housing; 42. a four-stage engine; 50. a cowling; 51. a quadrant fairing; 52. a three-quadrant fairing; 60. a rudder; 70. a cable cover.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting 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 present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

As shown in fig. 1 to 6, the launch vehicle in this embodiment includes a fairing 50 and a power system connected to each other. The power system includes interconnected quaternary structures 40, tertiary structures 30, secondary structures 20, and primary structures 10. The four-stage structure 40 includes a four-stage casing 41 and a four-stage engine 42 disposed in the four-stage casing 41.

By using the technical scheme of the embodiment, compared with the prior art, the four-stage engine 42 is externally provided with the four-stage shell cover 41, so that the design performance of the four-stage engine 42 is improved, and the structural system scheme of the carrier rocket is adopted, so that the carrier rocket is simple in design, safe, reliable, light in structural weight and high in bearing efficiency.

As shown in fig. 4, in the technical solution of this embodiment, a four-stage housing 41 of a four-stage structure 40 is made of aluminum alloy by machining integrally, the inner surface is a grid reinforced structure, the inside of the four-stage engine 42 is fixed and installed by a tapered frame, an attitude and orbit control engine nozzle is installed on a bulkhead by a bracket, a satellite bracket installation interface is reserved at the upper end, and 3 maintenance covers are designed for internal equipment assembly and maintenance operation.

As shown in fig. 4, in the solution of the present embodiment, the three-stage structure 30 includes a three-stage engine 31, and a first three-stage casing 32 and a second three-stage casing 33 connected to two ends of the three-stage engine 31, wherein two ends of the four-stage casing 41 are respectively connected to the cowling 50 and the first three-stage casing 32. The tertiary structure 30 is divided into three stages of front and rear sections, namely a first tertiary shroud 32 and a second tertiary shroud 33. The first three-stage shell cover 32 and the second three-stage shell cover 33 are respectively positioned in the front and at the back of the three-stage engine 31, the two cabin sections are made of aluminum alloy through integral machining, the inner surfaces of the two cabin sections are of grid reinforced structures and are connected with the three-stage engine 31 through front and back end frames, and 4 groups of separating springs are designed on the first three-stage shell cover 32 and are used for separating the three-stage structure 30 from the four-stage structure 40.

As shown in fig. 5, in the solution of the present embodiment, the secondary structure 20 includes a secondary engine 21, and a first secondary housing 22 and a second secondary housing 23 connected to both ends of the secondary engine 21, wherein a second tertiary housing 33 is connected to the first secondary housing 22. The secondary structure 20 is divided into two parts, namely a secondary front section and a secondary rear section, namely a first secondary housing 22 and a second secondary housing 23. First second grade clamshell 22 and second grade clamshell 23 are located second grade engine 21 front and back respectively, and two cabin sections are the integrative machining of aluminum alloy and make, and the internal surface is the grid and adds the muscle structure, is connected with second grade engine 21 through front and back end frame, has designed 6 groups separation spring on first second grade clamshell 22 and has been used for the separation of secondary structure 20 and tertiary structure 30.

As shown in fig. 6, in the solution of the present embodiment, the primary structure 10 includes a primary engine 11, and a first primary shroud 12 and a second primary shroud 13 connected to both ends of the primary engine 11, wherein the second secondary shroud 23 is connected to the first primary shroud 12. The primary structure 10 is divided into a primary front section and a primary rear section, i.e., a first primary shroud 12 and a second primary shroud 13. First one-level clamshell 12 and second one-level clamshell 13 are located one-level engine 11 front and back respectively, and two cabin sections are the integrative machining of aluminum alloy and make, and the internal surface is the grid and adds the muscle structure, is connected with one-level engine 11 through end frame before and after, has designed 4 rudder axles on the second one-level clamshell 13 and is used for installing rudder 60.

As shown in fig. 7, in the solution of the present embodiment, a rudder 60 is provided on the second-stage casing 13. Specifically, the rudder is a grid rudder. The grid rudder has four control surfaces which are respectively positioned at the outer sides of four quadrants of the second primary housing cover 13, and the control surfaces are made of aluminum alloy through integral machining and are connected with a control shaft through a root flange plate.

As shown in fig. 1 and 8, in the solution of the present embodiment, the launch vehicle further comprises a cable cover 70, and the cable cover 70 is connected to the outside of the primary structure 10, the secondary structure 20, and the tertiary structure 30. The cable cover 70 is located outside the primary structure 10, the secondary structure 20, and the tertiary structure 30 for protecting the cables from aerodynamic heat damage. The cable cover 70 is made of stainless steel sheet metal.

As shown in fig. 2, in the present embodiment, the cowl 50 includes a quadrant fairing 51 and a quadrant fairing 52 that are connected to each other. The fairing 50 is attached at its lower end to the quaternary structure 40 of the launch vehicle and houses the payload, such as a satellite, therein to provide reliable environmental conditions for the same.

Preferably, a separation structure is provided between the fourth stage housing 41 and the first third stage housing 32, the second third stage housing 33 and the first second stage housing 22, the second stage housing 23 and the first primary stage housing 12. The separation structure is used for interstage separation between the primary structure 10, the secondary structure 20, and the tertiary structure 30.

In the present embodiment, as shown in fig. 3, the four-stage casing 41 has a cylindrical structure, and the four-stage engine 42 is housed in the cylindrical structure.

The process dimensions and the assembly of the structure of the components of the launch vehicle of this embodiment will be described below:

the first-quadrant fairing 51 and the third-quadrant fairing 52 adopt a honeycomb sandwich structure, the wall plates are resin-based carbon fiber laminated plates with the thickness of 0.8mm, the sandwich core adopts paper honeycomb and the height of 12mm, and the butt joint frame and the end frame are both made of integrated composite materials with the thickness of 10 mm. In order to meet the heat-proof requirement, the end cap is made of a 15mm glass fiber reinforced plastic laminated plate, and all the parts are connected through bolts.

The four-stage shell cover 41, the first three-stage shell cover 32, the second three-stage shell cover 33, the first two-stage shell cover 22, the second two-stage shell cover 23, the first primary shell cover 12 and the second primary shell cover 13 are all formed by machining 2A14 forged rings, and the cabin sections are in a grid reinforcement structure form. The wall thickness of the four-stage structure 40, the first three-stage housing 32 and the second three-stage housing 33 is 2mm, the thickness of the end frame is 8mm, and the height of the internal grid ribs is 12mm and the thickness is 2 mm. The wall thickness of the first secondary housing 22, the second secondary housing 23, the first primary housing 12 and the second primary housing 13 is 4mm, the thickness of the end frame is 12mm, and the height of the internal grid ribs is 15mm and the thickness is 3 mm.

The rudder 60 is made of an aluminum alloy 2A14 plate, the thickness of the rudder surface is 3mm, and the rudder is machined and formed.

The cable cover 70 is made of a 304 stainless steel plate, is formed by sheet metal, has the thickness of 1mm, and is externally sprayed with a heat-proof coating.

And (4) carrying out full arrow general assembly after each part is processed respectively.

Firstly, a first three-stage shell cover 32, a second three-stage shell cover 33, a first two-stage shell cover 22, a second two-stage shell cover 23, a first one-stage shell cover 12 and a second one-stage shell cover 13 are correspondingly arranged on a solid engine respectively, and the front skirt and the rear skirt are connected by adopting 20M 16 bolts.

The quaternary structure 40 is then mounted on the front end frame of the first tertiary can 32, using 8M 16 explosive bolts.

The one-quadrant fairing 51 and the three-quadrant fairing 52 are then mounted to the forward end bell of the quaternary structure 40 and attached using 8M 16 explosive bolts. The one-quadrant fairing 51 and the three-quadrant fairing 52 are also connected by 8M 16 explosive bolts.

The cable cover 70 is then installed over the primary structure 10, the secondary structure 20, and the tertiary structure 30.

Finally, the control surfaces of the 4 rudders 60 are mounted on the control shaft of the second primary housing 13 by 40 studs of M14.

Preferably, the number of each stage of separation springs can be 4 or 6, and other numbers can also be adopted.

The fairing 50 made of the composite material not only reduces the structural weight, but also reduces the aerodynamic resistance when the rocket is launched, and greatly improves the carrying efficiency of the rocket. The general design scheme of the structural system of the carrier rocket of the embodiment has the following typical characteristics: the bearing is large, the weight is light, the configuration is simple, the assembly is convenient, and the reliability is high.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.

Claims (10)

1. A launch vehicle comprising interconnected fairings (50) and a power system, said power system comprising interconnected quaternary structures (40), tertiary structures (30), secondary structures (20), and primary structures (10), wherein said quaternary structures (40) comprise a quaternary shroud (41) and a quaternary engine (42) disposed within said quaternary shroud (41).

2. A launch vehicle according to claim 1, characterised in that said tertiary structure (30) comprises a tertiary engine (31) and a first tertiary casing (32) and a second tertiary casing (33) connected at the ends of said tertiary engine (31), wherein the ends of said quaternary casing (41) are connected respectively to said fairing (50) and to said first tertiary casing (32).

3. A launch vehicle according to claim 2, characterised in that the secondary structure (20) comprises a secondary engine (21) and a first secondary shroud (22) and a second secondary shroud (23) connected at both ends of the secondary engine (21), wherein the second tertiary shroud (33) is connected with the first secondary shroud (22).

4. A launch vehicle according to claim 3, characterised in that the primary structure (10) comprises a primary engine (11) and a first primary shroud (12) and a second primary shroud (13) connected at both ends of the primary engine (11), wherein the second secondary shroud (23) is connected to the first primary shroud (12).

5. A launch vehicle according to claim 4, characterised in that the second primary casing (13) is provided with a rudder (60).

6. A launch vehicle according to claim 5, characterised in that said rudder (60) is plural, said rudders (60) being arranged at intervals in the axial direction of said second primary housing (13).

7. A launch vehicle according to claim 1, characterised in that it further comprises a cable cover (70), said cable cover (70) being attached outside said primary structure (10), said secondary structure (20) and said tertiary structure (30).

8. A launch vehicle according to claim 1, characterised in that said fairing (50) comprises a quadrant fairing (51) and a quadrant fairing (53) connected to each other.

9. A launch vehicle according to claim 4, characterised in that separation structures are provided between the four stage casing (41) and the first three stage casing (32), the second three stage casing (33) and the first two stage casing (22), the second two stage casing (23) and the first primary casing (12).

10. A launch vehicle according to claim 1, characterised in that said quaternary housing (41) is of cylindrical configuration.

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