Multifunctional cabin section structure with instrument installation and large cone angle transition functions

Abstract

The invention relates to a multifunctional cabin section structure integrating instrument installation and large cone angle transition, the functions of two cabin sections of a traditional rocket are achieved through one cabin section, the number of sections is reduced, the rocket body structure is more compact, the length of the whole rocket is shortened, and the weight of the final stage of the rocket is further reduced. Based on the outer surface of the conical skin, the inertial device mounting bracket with an integrated thin-wall triangular conical structure is designed, a cast magnesium alloy structure is adopted, and the requirements of high specific stiffness and high precision of a large-taper-angle inclined plane mounting inertial device are met. The modular general instrument support is designed on the outer surface of the skin, installation of dozens of devices is achieved through a certain number of modular supports, the design difficulty of a conical cabin section instrument support is effectively solved, and meanwhile the design and production efficiency is greatly improved through the modular instrument support.

Description

Technical Field

[0001] The invention belongs to the technical field of launch vehicle structure design, and relates to a multifunctional cabin structure with both instrument installation and large cone angle transition. Background Art

[0002] With the development of aerospace technology, the surge in the satellite launch market, the diversity of satellite sizes, and the normalization of the launch of multiple satellites with one rocket, there is an increasing demand for satellite brackets that can adapt to multiple interfaces on launch vehicles. The last stage of the rocket usually matches satellite brackets of different diameters through a transition bracket with a cone angle, and the transition with a large cone angle puts higher requirements on the stiffness and strength design of this compartment.

[0003] At present, the instrument layout of domestic and foreign launch vehicles is mostly realized by a single compartment. The instrument compartment of Ariane 5 is an outer cylindrical shell section, an inner truncated cone shell and a horizontal instrument installation plate. The Delta IV rocket does not have an independent instrument compartment. The control system instruments and equipment are suspended on the instrument installation platform extending from the bottom of the second-stage oxygen tank. The Falcon 9 rocket does not have a separate instrument compartment. Its instruments and equipment are installed on the second-stage tail section and the fairing transition bracket. The instrument compartment of the Angara series launch vehicles is set in the upper stage. The Proton M / Breeze M third stage has an independent instrument compartment. The core stage of the Atlas 5 rocket is composed of two universal modules, the universal core stage and the Centaur upper stage, each of which has an independent instrument compartment structure. Domestic launch vehicles all have independent instrument compartment sections to realize the installation layout of instruments.

[0004] In order to improve the carrying capacity of the rocket, the rocket's last stage needs to minimize the number of single-function compartments. The setting of independent instrument compartments increases the rocket's weight, body length and flight payload.

[0005] In addition, traditional rocket instrument cabins are used to integrate and install professional instruments and equipment, pipeline gas cylinders, and provide mounting brackets for dozens of types of equipment. Depending on the instrument pipeline installation interface and installation location, a separate mounting bracket is often provided for each device, which greatly increases the design and production costs. Summary of the invention

[0006] The technical problem solved by the present invention is to overcome the deficiencies of the prior art and propose a multifunctional cabin structure with both instrument installation and large cone angle transition.

[0007] The solution of the present invention is:

[0008] A multifunctional cabin section structure with both instrument installation and large cone angle transition, including an upper docking ring frame, a lower docking ring frame, a skin, a first intermediate ring frame, a second intermediate ring frame, a T-shaped stringer, an inertial device mounting bracket, and a modular instrument bracket;

[0009] The upper docking ring frame and the lower docking ring frame are both integrally forged from aluminum alloy. The upper docking ring frame is axially docked with the satellite bracket, and the lower docking ring frame is axially docked with the rocket's final stage. The skin is fixedly connected between the upper docking ring frame and the lower docking ring frame with a conical structure. The first intermediate ring frame and the second intermediate ring frame have the same structure, and are both spliced ​​by two Ω-shaped frames through connecting plates. The Ω-shaped frames are rolled and bent from hard aluminum alloy. The first intermediate ring frame and the second intermediate ring frame are fixed to the inner wall of the skin by rivets. A number of T-shaped trusses are evenly distributed on the inner wall of the skin. The T-shaped trusses are made of high-strength aluminum alloy profiles. The "one" part of the T-shaped truss structure is fixedly connected to the inner wall of the skin, and is respectively connected to the upper docking ring frame and the lower docking ring frame by bolts. The "|" part of the T-shaped structure points to the center of the cabin structure.

[0010] The inertial device mounting bracket is made of cast magnesium alloy material and is fixed on the outer wall of the skin. It is an integrated triangular pyramid structure. The four sides of the triangular pyramid structure are opposite to each other and are designed with weight reduction holes. The upper side is the inertial device mounting surface. Several bosses are machined and installed on the mounting surface to ensure the installation flatness. Two sets of pin structures are set on the inertial device mounting bracket to ensure the relative relationship between the instrument and the arrow body when installing;

[0011] The modular instrument bracket has an I-shaped cross-section and is arranged on the outer surface of the skin. The modular instrument bracket is connected to the T-shaped beam by rivets on all sides. The upper surface serves as the instrument mounting surface and provides mounting interfaces for various instruments and equipment. The middle part of the upper surface is fixedly connected to the T-shaped beam by a C-shaped beam.

[0012] Preferably, the T-shaped trusses are made of high-strength aluminum alloy profiles.

[0013] Preferably, both the upper docking ring frame and the lower docking ring frame are designed with outward-turned frames.

[0014] Preferably, on the inertial device mounting bracket, a thickened flange is provided around the larger weight-reducing hole.

[0015] Preferably, the inertial device mounting bracket is located at the lower part of the cabin section, with its upper end connected to the second intermediate ring frame and its lower end connected to the lower docking ring frame.

[0016] Preferably, the surface of the inertial device mounting bracket is treated by micro-arc oxidation.

[0017] Preferably, the modular instrument bracket is an aluminum alloy sheet metal bracket.

[0018] Preferably, mounting holes are prepared on the upper surface of the modular instrument bracket according to the equipment mounting interface, and the mounting holes are riveted with support plate nuts to provide a mounting interface for the instrument.

[0019] Preferably, modular instrument brackets are freely placed in the skin circumference, and the number is determined according to demand.

[0020] Preferably, three short flanges extend from the upper and lower parts of the mounting surface of the modular instrument bracket, and the two sides and the short flanges of the modular instrument bracket are connected to the T-shaped beams by rivets.

[0021] Based on the space and weight limitations of the rocket's final stage, the present invention provides a lightweight, high-load-bearing, multifunctional cabin structure that has both instrument installation and large-cone angle transition, which can simultaneously meet the transition function from the rocket's final stage to the satellite bracket and the instrument and equipment installation function. The specific innovations and beneficial effects are as follows:

[0022] The present invention has both instrument installation and large cone angle transition functions, and realizes the functions of two traditional rocket compartments through one compartment. The reduction of sections makes the rocket body structure more compact, shortens the length of the entire rocket, and further reduces the weight of the rocket's final stage. At the same time, the main structure layout scheme of strong trusses and strong frames is adopted to solve the problem of light weight and high load-bearing capacity of large cone angle structures, and realize the rigidity and strength index requirements of rockets.

[0023] Based on the outer surface of the conical skin, the present invention designs an inertial device mounting bracket with an integrated thin-walled triangular cone structure, which adopts a cast magnesium alloy structure and meets the high specific stiffness and high precision requirements for mounting inertial devices on large cone-angle inclined surfaces.

[0024] The present invention designs a modular universal instrument bracket on the outer surface of the skin. The size and number of the instrument bracket are no longer restricted by the instrument equipment itself. Instead, a certain number of modular brackets are used to install dozens of equipment, effectively solving the difficulty of designing instrument brackets for conical cabin sections. The embedded C-shaped truss connection further enhances the rigidity of the instrument bracket. At the same time, the modular instrument bracket greatly improves the design and production efficiency. In addition, the main structure of the cabin section adopts the structural form of the inner truss, which makes the layout of the instrument bracket on the outer surface of the bulkhead more flexible. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a multifunctional cabin structure with both instrument installation and large cone angle transition.

[0026] Figure 2 Schematic diagram of mounting bracket for inertial devices;

[0027] Figure 3 This is a schematic diagram of the inward thickening and flanging of the weight-reducing hole;

[0028] Figure 4 This is a schematic diagram of modular bracket installation;

[0029] Figure 5 Schematic diagram of C-shaped beam connection. DETAILED DESCRIPTION

[0030] The present invention will be further described below in conjunction with the accompanying drawings.

[0031] The present invention combines the two cabin sections of the instrument cabin and the transition bracket into one, and integrates the functions of the two into one cabin section, and proposes a multifunctional cabin section structure with both instrument installation and large cone angle transition, which not only meets the requirements of light structure, high load-bearing capacity, high rigidity, and instrument equipment installation, but also realizes the reliable connection between the rocket body and the satellite bracket through the large cone angle transition.

[0032] The present invention adopts the design concept of modular bracket structure, improves the manufacturing efficiency of the instrument bracket, and realizes the compact layout of the installation space of a large number of instrument brackets.

[0033] The technical solution of the present invention mainly includes three points: first, a high-load-bearing main structure with a large cone angle transition; second, a lightweight, high-rigidity, and high-precision inertial device mounting bracket; and third, a modular high-rigidity universal instrument bracket that provides mounting interfaces for dozens of instruments.

[0034] The main structure of the multifunctional cabin section of the present invention is shown in FIG. Figure 1 , which is composed of an upper docking ring frame 1, a lower docking ring frame 2, a skin 3, a T-shaped girder 4, a first intermediate ring frame 5, and a second intermediate ring frame 6. In order to solve the problem of low load-bearing efficiency caused by excessive structural cone angle, the upper docking ring frame 1 and the lower docking ring frame 2 both adopt an integral aluminum forging ring structure. In addition to realizing the docking function between sections, more importantly, the circumferential stiffness of the structure is increased. In order to facilitate the connection operation between sections, the upper and lower docking ring frames both adopt an outward-turned frame solution. The skin 3 is fixedly connected between the upper docking ring frame and the lower docking ring frame with a cone-shaped structure; the skin 3 mainly plays a shaping role, bears and provides a basis for equipment installation. In order to further enhance the stiffness of the large cone angle cabin section, the present invention sets two intermediate ring frames 5 and 6, both of which are spliced ​​by two Ω-shaped aluminum alloy half frames through a frame connecting plate. In addition, by installing a number of evenly distributed T-shaped girder 4, the high load-bearing requirements of the cabin section are met. In order to facilitate the installation of instruments on the outside of the skin, the girder adopts an internal girder solution. The upper and lower butt-jointed ring frames 1, 2, the skin 3, the T-shaped beam 4, and the two middle ring frames 5, 6 are connected by riveting or bolts to form an integral shell section.

[0035] The inertial devices of a rocket are different from other instruments and equipment, and higher requirements are placed on the rigidity of the bracket. However, the inertial devices are large in size and weight, and are installed on the outer surface of the conical cabin section, which greatly increases the difficulty of designing the installation bracket. Based on the demand for lightweight, the present invention selects cast magnesium alloy material, and adopts an integrated thin-walled (wall thickness 6-8mm) triangular cone structure fixed to the outer wall of the skin as the inertial device installation bracket 7. The inertial device installation bracket 7 has four side faces, and the four side faces are opposite to each other to form two groups of side faces, one group of side faces is a quasi-quadrilateral, and the other group of side faces is a quasi-triangle. The sides of the quasi-quadrilateral and the quasi-triangle in contact with the skin are curved sides. While designing weight-reducing holes on the four sides, the size of the weight-reducing holes on the quasi-quadrilateral is larger than the size of the weight-reducing holes on the quasi-triangle. For example Figure 3As shown, the flanges 11 and 12 are thickened in the circumferential direction of the quadrilateral side weight-reducing holes, and the flange size is 8 mm wide × 8 mm high to improve the circumferential stiffness. In order to improve the installation accuracy of the inertial device, a mounting boss 8 is separately set up on the upper side surface of the bracket, i.e., the mounting surface. In addition, in order to further improve the assembly stiffness of the bracket, the upper end of the bracket is connected to the middle frame of the cabin section, and the lower end is connected to the lower end frame of the cabin section. The bracket and the cabin section are connected by bolts, which can further improve the assembly accuracy of the bracket.

[0036] This compartment not only needs to realize the transition function between the last stage of the rocket and the satellite bracket, but also needs to meet the installation function of the instrument equipment. In order to reduce the design difficulty of the instrument bracket of the conical compartment, the present invention designs a modular modular instrument installation bracket 9, which adopts an aluminum alloy sheet metal bracket. The two sides of the bracket are connected to the T-shaped beam, and three short flanges are extended from the upper and lower parts to connect with the T-shaped beam. In order to further increase the rigidity of the bracket, the modular instrument installation bracket is a "J"-shaped structure, and the upper surface is the installation surface. The middle part of the installation surface is connected to the T-shaped beam 4 through a C-shaped beam 10, thereby realizing the lightweight and high rigidity design of the instrument bracket. The surface of the bracket provides installation interfaces for various instruments and equipment.

[0037] Example

[0038] The multifunctional cabin structure with both instrument installation and large cone angle transition designed by the present invention has been applied to a certain type of domestic launch vehicle, and its specific implementation method is as follows:

[0039] a Figure 1 As shown, the upper and lower docking ring frames 1 and 2 of the main load-bearing structure are integrally forged with aluminum alloy. The upper docking ring frame is axially docked with the satellite bracket by bolts, and the lower docking ring frame is axially docked with the rocket's last stage by bolts. The intermediate ring frames 5 and 6 are rolled and bent with hard aluminum alloy. The two half frames are connected by a frame connecting plate. The skin 3 is spliced ​​with 4 thick hard aluminum plates. The stringer 4 is selected from T-section high-strength aluminum alloy profiles (strength σb ≥ 550MPa). The "one" part of the T-shaped stringer structure is fixedly connected to the inner wall of the skin, and is bolted to the upper docking ring frame and the lower docking ring frame respectively, and self-locking nuts are used to prevent loosening. The "|" part of the T-shaped structure points to the center of the cabin structure. The skin 3 is connected to the intermediate ring frames 5 and 6 by rivets.

[0040] b Figure 2As shown, the inertial device mounting bracket 7 is cast with magnesium alloy, the flange is locally thickened, and the equipment mounting surface is finely processed to ensure the installation flatness. In order to improve the equipment installation accuracy, two sets of pin structures are provided on the bracket 7 to ensure the relative relationship between the instrument and the arrow body when the instrument is installed. The pin structure is specifically set as follows: two bosses 8 are selected, and two mounting holes are processed on each selected boss, one of which is provided with a pin, and the other mounting hole is used to install the inertial device, to ensure the relative relationship between the instrument and the arrow body when the instrument is installed. At the same time, in order to improve the environmental adaptability of the inertial device mounting bracket 7, the bracket surface is treated with micro-arc oxidation. The inertial device mounting bracket is connected to the cabin section by bolts, and is prevented from loosening by self-locking nuts.

[0041] c Figure 4 As shown, the modular instrument bracket is arranged on the surface of the shell segment skin. According to the layout and size of the instrument, the modular instrument bracket can be freely placed in the skin circumference, and the number is determined according to demand; the modular instrument bracket is connected to the truss by rivets around it. Figure 5 As shown, the middle of the upper surface of the modular instrument bracket is connected to the upper end of the C-shaped beam 10 by countersunk rivets, and the bottom of the C-shaped beam is connected to the T-shaped beam 4 by blind rivets. The modular instrument bracket is formed by high-strength aluminum alloy (σb≥415MPa) sheet metal. The upper surface of the modular instrument bracket is used to install equipment. The mounting holes are prepared according to the equipment installation interface, and the bracket nuts are riveted to provide the installation interface.

[0042] Under the limited space and weight of the rocket's final stage, the present invention proposes a main structure solution with strong trusses and strong frames that have both instrument installation and large cone angle transition functions, which solves the problem of light weight and high load-bearing capacity of large cone angle structures and meets the rocket's stiffness and strength index requirements; based on the outer surface of the conical skin, an integrated thin-walled triangular cone structure inertial device mounting bracket is designed, which adopts cast magnesium alloy material to meet the high specific stiffness and light weight requirements of large cone angle inclined surface installation inertial devices; the mounting surface is designed with mounting bosses to meet the high-precision installation requirements of inertial devices; modular universal instrument brackets are designed on the outer surface of the skin to achieve the installation of dozens of equipment, effectively solving the difficulties in the design of instrument brackets for conical cabin sections, and the embedded C-shaped truss connection further enhances the stiffness of the instrument bracket. At the same time, the modular instrument bracket greatly improves the design and production efficiency. In addition, the main structure of the cabin section adopts the structural form of internal trusses, which makes the layout of the instrument bracket on the outer surface of the cabin wall more flexible.

[0043] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. A multifunctional cabin structure with both instrument installation and large cone angle transition, characterized in that: It comprises an upper docking ring frame (1), a lower docking ring frame (2), a skin (3), a first intermediate ring frame (5), a second intermediate ring frame (6), a T-shaped stringer (4), an inertial device mounting bracket (7), and a modular instrument bracket (9); The upper docking ring frame (1) and the lower docking ring frame (2) are both integrally forged from aluminum alloy. The upper docking ring frame is axially docked with the satellite bracket, and the lower docking ring frame is axially docked with the rocket's final stage. The skin (3) is fixedly connected between the upper docking ring frame (1) and the lower docking ring frame (2) in a conical structure. The first intermediate ring frame (5) and the second intermediate ring frame (6) have the same structure and are both formed by splicing two Ω-shaped frames through a connecting plate. The Ω-shaped frames are formed by rolling and bending hard aluminum alloy. The first intermediate ring frame (5) and the second intermediate ring frame (6) are fixed to the inner wall of the skin by rivets. A plurality of T-shaped girders (4) are evenly distributed on the inner wall of the skin. The T-shaped girders (4) are made of high-strength aluminum alloy profiles. The "I" part of the T-shaped girders structure is fixedly connected to the inner wall of the skin and is respectively connected to the upper docking ring frame (1) and the lower docking ring frame (2) by bolts. The "|" part of the T-shaped structure points to the center of the cabin structure. The inertial device mounting bracket (7) is made of cast magnesium alloy material and is fixed on the outer wall of the skin. It is an integrated triangular pyramid structure. The four sides of the triangular pyramid structure are opposite to each other and are all designed with weight reduction holes. The side located at the top is the inertial device mounting surface. A plurality of bosses (8) are machined and installed on the mounting surface to ensure the installation flatness. Two sets of pin structures are arranged on the inertial device mounting bracket (7) to ensure the relative relationship between the instrument and the arrow body when the instrument is installed. The modular instrument bracket (9) has an "I"-shaped cross section and is arranged on the outer surface of the skin. The modular instrument bracket (9) is connected to the T-shaped beams by rivets on all sides, and the upper surface serves as an instrument installation surface, providing installation interfaces for various instruments and equipment; the middle part of the upper surface is fixedly connected to the T-shaped beams by C-shaped beams (10).

2. A multifunctional cabin structure with both instrument installation and large cone angle transition according to claim 1, characterized in that: The T-shaped beam (4) is made of high-strength aluminum alloy profile.

3. The multifunctional cabin structure with both instrument installation and large cone angle transition according to claim 1, characterized in that: The upper docking ring frame (1) and the lower docking ring frame (2) are both designed with outward turning frames.

4. The multifunctional cabin structure with both instrument installation and large cone angle transition according to claim 1, characterized in that: On the inertial device mounting bracket, thickened flanges are provided around the larger weight-reducing holes.

5. The multifunctional cabin structure with both instrument installation and large cone angle transition according to claim 1, characterized in that: The inertial device mounting bracket (7) is located at the lower part of the cabin section, with its upper end connected to the second intermediate ring frame (6) and its lower end connected to the lower docking ring frame (2).

6. The multifunctional cabin structure with both instrument installation and large taper angle transition according to claim 1, characterized in that: The surface of the inertial device mounting bracket (7) is treated by micro-arc oxidation.

7. The multifunctional cabin structure with both instrument installation and large cone angle transition according to claim 1, characterized in that: The modular instrument bracket (9) is an aluminum alloy sheet metal bracket.

8. The multifunctional cabin structure with both instrument installation and large cone angle transition according to claim 1, characterized in that: The upper surface of the modular instrument bracket (9) is provided with mounting holes according to the equipment mounting interface, and the mounting holes are riveted with support plate nuts to provide a mounting interface for the instrument.

9. The multifunctional cabin structure with both instrument installation and large cone angle transition according to claim 1, characterized in that: The modular instrument brackets (9) are freely placed in the skin circumference, and the number is determined according to demand.

10. The multifunctional cabin structure with both instrument installation and large taper angle transition according to claim 1, characterized in that: Three short flanges extend from the upper and lower parts of the mounting surface of the modular instrument bracket (9), and the two sides and the short flanges of the modular instrument bracket (9) are connected to the T-shaped beams through rivets.

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