Flying wing type composite adapter for parallel double-star launching

Abstract

The invention discloses a flying wing type composite adapter for parallel double-star launching, the flying wing type composite adapter for parallel double-star launching adopts an integrated flying wing type flat configuration, and the flying wing type composite adapter for parallel double-star launching comprises a structural framework, an upper skin and a lower skin which are assembled to form the flying wing type composite adapter for parallel double-star launching; the structural framework of the flying wing type composite adapter for parallel double-star launching comprises a force bearing frame, connecting plates, longitudinal beams, cross beams and side plates. All the components are formed by integrally laying light fiber reinforced composite materials and independently curing and molding the light fiber reinforced composite materials. According to the flying wing type composite adapter for parallel double-star launching, the problems that a traditional multi-star parallel adapter is complex in structure, high in production difficulty, low in structural bearing efficiency and the like are solved, the flying wing type composite adapter has the advantages of being compact in structure, convenient to operate, light and the like, and the adaptability of the adapter to parallel double-star launching tasks is improved.

Description

Technical Field

[0001] The invention relates to an adapter suitable for connecting a carrier and a parallel double satellite in the field of aerospace, and in particular to a flying wing composite material adapter for launching a parallel double satellite. Background Art

[0002] With the substantial increase in the number of satellites being developed in the aerospace field, the demand for launch vehicles is increasing. In order to meet the needs of multi-satellite launch missions, especially the multi-satellite parallel launch of medium and large satellites, launch vehicles need to be equipped with multi-satellite parallel adapters with complex structures.

[0003] Multi-satellite parallel adapters usually adopt a load-bearing cone or plane frame supplemented by struts or brackets. This type of adapter often finds it difficult to take into account the configuration size, assembly convenience, and lightweight requirements at the same time. For example, in order to meet the envelope space and dynamic characteristics of some satellites, the adapter height needs to be compressed as much as possible, resulting in coupling between auxiliary structures such as adapter struts and brackets and the vehicle assembly below, and complicating the satellite-rocket interface and interface relationship; conversely, in order to improve the convenience of assembly, the height of the main structure of the adapter needs to be increased to meet the effective structural height requirements required for the adapter struts and brackets to bear the load. At the same time, the complex structural form of traditional multi-satellite parallel adapters also increases the difficulty of product design and production, resulting in low load-bearing efficiency of the adapter structure, affecting the launch capability of the carrier rocket. Summary of the invention

[0004] In order to solve the above problems, the present invention provides a flying wing type composite material adapter for parallel double-satellite launch to meet the optimization requirements of satellite layout, weight and mechanical properties of the adapter for parallel double-satellite launch mission.

[0005] The specific technical solutions of the present invention are as follows:

[0006] A flying wing-shaped composite material adapter for parallel double-satellite launch, the flying wing-shaped composite material adapter for parallel double-satellite launch adopts an integrated flying wing-shaped flat configuration, and includes a structural skeleton, an upper skin, and a lower skin assembled to form the adapter; the structural skeleton assembled to form the adapter includes a load-bearing frame, a connecting plate, a longitudinal beam, a cross beam, and a side panel.

[0007] The components are all laid out in one piece using lightweight fiber-reinforced composite materials and cured and formed separately; after being formed separately, they are assembled at room temperature in the form of a secondary rubber-screw mixture to form an integrated adapter with a compact configuration, convenient operation, and light weight.

[0008] The load-bearing frame includes double oblique cone surfaces and double longitudinal surfaces; the oblique cone surface structure bears the axial load from the satellite, and the longitudinal surface structure bears the lateral and bending moment loads from the satellite.

[0009] The upper and lower ends of the double-oblique cone surface are designed with flanges; the upper end flange is designed with a mechanical connection interface for mechanical connection between the adapter and the satellite belt separation mechanism; the lower end flange is designed with a mechanical connection interface for mechanical connection between the adapter and the carrier, and the carrier can be any one of a rocket terminal stage, an upper stage and a space propulsion module.

[0010] The upper and lower ends of the double longitudinal surfaces are both designed with flanges; the upper flange is designed to be glued to the upper skin; the lower flange is designed to be glued to the lower skin.

[0011] The longitudinal beam is an integrated structure to ensure the structural continuity in the main load-bearing direction; the longitudinal beam adopts an "I"-shaped cross-section.

[0012] The cross beam is designed as a multi-segment structure to avoid the load-bearing frame and the longitudinal beam; the cross beam adopts an "I"-shaped cross-section.

[0013] The connecting plate adopts a box-type structure and is designed with flanges on all sides; the upper flange is designed with a mechanical connection interface for connecting the satellite tape separation mechanism; the flanges on both sides are connected to the load-bearing frame and the crossbeam by a mixture of rubber and screws.

[0014] The side panels adopt a box-shaped structure with flanges on all sides; the flanges on the upper end of the side panels are used for gluing the upper skin, and the flanges on the lower end of the side panels are used for gluing the lower skin. The flanges on both sides of the side panels are connected to the load-bearing frame and the crossbeam by glue and screws.

[0015] The upper skin and the lower skin both adopt a planar structure.

[0016] The load-bearing frame, connecting plate, longitudinal beam, cross beam and side plate are connected by a combination of rubber and screw through mechanical joints to form the structural framework of the adapter;

[0017] The upper skin, the lower skin and the structural frame are assembled by gluing.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] The flying wing composite material adapter for parallel dual-satellite launch provided by the present invention is made of lightweight fiber-reinforced composite materials, which are laid in one piece and cured separately. The load-bearing frame adopts an integrated symmetrical structure of "double oblique cone surface + double longitudinal surface", which meets the requirements of assembly convenience and light weight. Specifically, the following three points:

[0020] (1) This configuration has the bearing capacity of axial, lateral and bending loads, which reduces the adapter height and increases the satellite layout space while ensuring the structural load-bearing efficiency;

[0021] (2) This configuration eliminates auxiliary structures such as traditional adapter struts and brackets, and achieves assembly decoupling between the adapter and the carrier in the form of an independent compartment, thereby improving the convenience of final assembly;

[0022] (3) This configuration reduces the structural complexity of the adapter, improves the application feasibility of high-performance, lightweight fiber-reinforced composite materials, and improves the lightweight benefits of the adapter structure. The configuration size and design parameters of the adapter can be adaptively designed according to the load-bearing and interface requirements of the specific launch mission, and the adapter has a high degree of designability. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0024] Figure 1 is a schematic diagram of an adapter for parallel dual-satellite transmission according to an embodiment of the present invention;

[0025] Figure 2 Schematic diagram of the configuration of a flying wing-shaped composite material adapter for parallel double-satellite launch according to an embodiment of the present invention;

[0026] Figure 3 It is a schematic diagram of the configuration of a flying wing-type composite material adapter for parallel double-satellite launch according to an embodiment of the present invention (the skin is not shown);

[0027] Figure 4 is a schematic diagram of the adapter configuration design parameters of an embodiment of the present invention;

[0028] Figure 5 It is a schematic diagram of a load-bearing frame according to an embodiment of the present invention.

[0029] In the figure, 1 is the load-bearing frame; 2 is the connecting plate; 3 is the longitudinal beam; 4 is the transverse beam; 5 is the side plate; 6 is the upper skin; 7 is the lower skin; 8 is the double oblique cone surface; 9 is the double longitudinal surface; 10 is the parallel double star; 11 is the parallel double star adapter; and 12 is the carrier. DETAILED DESCRIPTION

[0030] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0031] like Figure 3The flying wing-shaped composite material adapter for parallel double-satellite launch comprises a structural frame, an upper skin (6), and a lower skin (7) assembled to form the flying wing-shaped composite material adapter for parallel double-satellite launch; the structural frame assembled to form the adapter comprises a load-bearing frame (1), a connecting plate (2), a longitudinal beam (3), a transverse beam (4), and a side plate (5).

[0032] The components are all laid out in one piece using lightweight fiber-reinforced composite materials and cured and formed separately; after being formed separately, they are assembled at room temperature in the form of a secondary rubber-screw mixture to form an integrated adapter with a compact configuration, convenient operation, and light weight.

[0033] like Figure 5 As shown, the load-bearing frame (1) comprises a double oblique cone surface (8) and a double longitudinal surface (9); the oblique cone surface structure bears the axial load from the satellite, and the longitudinal surface structure bears the lateral and bending moment loads from the satellite.

[0034] The upper and lower ends of the double-oblique cone surface (8) are both designed with flanges; the upper flange is designed with a mechanical connection interface for mechanical connection between the adapter and the belt separation mechanism of the parallel double star (10); the lower flange is designed with a mechanical connection interface for mechanical connection between the adapter and the carrier (12), and the carrier (12) can be any one of a rocket terminal stage, an upper stage and a space propulsion cabin.

[0035] The upper and lower ends of the double longitudinal surfaces (9) are both designed with flanges; the upper flange is used for gluing the upper skin (6); and the lower flange is designed for gluing the lower skin (7).

[0036] like Figure 3 As shown, the longitudinal beam (3) is an integrated structure, adopts an "I"-shaped cross section, and is a continuous structure to ensure the structural continuity in the main load-bearing direction. The cross beams (4) are three in number, and are designed as a multi-segmented structure to avoid the load-bearing frame (1) and the longitudinal beam (3); the cross beam (4) adopts an "I"-shaped cross section. The number and layout of the longitudinal beams (3) and the cross beams (4) can be adjusted according to the specific task, in principle to meet the strength and stiffness index requirements of the flying wing-type composite material adapter for parallel dual-satellite launch.

[0037] like Figure 3 As shown, the connecting plate (2) adopts a box-shaped structure and is designed with flanges on all sides; the upper flange is designed with a mechanical connection interface for connecting the parallel double star (10) wrapping separation mechanism; the flanges on both sides are connected to the load-bearing frame (1) and the crossbeam (4) by a combination of rubber and screws.

[0038] like Figure 3As shown, the side panel (5) adopts a box-shaped structure, and is designed with flanges on all sides; the flanges at the upper end of the side panel (5) are used to glue the upper skin (6), and the flanges at the lower end of the side panel (5) are glued to the lower skin (7). The flanges on both sides of the side panel (5) are connected to the load-bearing frame (1) and the crossbeam (4) by a combination of glue and screws.

[0039] like Figure 2 As shown, the upper skin (6) and the lower skin (7) both adopt a planar structure.

[0040] The load-bearing frame (1), the connecting plate (2), the longitudinal beam (3), the cross beam (4), and the side plate (5) are connected by mechanical joints by glue and screws, and assembled to form a structural skeleton of a flying wing composite material adapter for parallel dual-satellite launch; the upper skin (6), the lower skin (7) and the structural skeleton are assembled by adhesive bonding. Among them, the load-bearing frame (1) and the longitudinal beam (3) and the cross beam (4), and the longitudinal beam (3) and the cross beam (4) are all connected by mechanical joints by glue and screws; the connecting plate (2), the side plate (5) and the load-bearing frame (1), the longitudinal beam (3), and the cross beam (4) are connected by glue and screws; the upper skin (6), the lower skin (7) and the structural skeleton are assembled by adhesive bonding.

[0041] like Figure 4 As shown, the configuration design parameters of the flying wing composite material adapter (11) for parallel dual satellite launch mainly include: total height H, rear end diameter Φ 1 、Diameter of the two satellite interfaces at the front end Φ 2 , the front double star interface distance D and other four items. Among them, the overall height H is designed to meet the maximum axial layout size requirements of the parallel double star (10); the rear end diameter Φ 1 The design is based on the principle of meeting the connection requirements between the adapter and the carrier (12); the diameter of the satellite interface at the front 2 is Φ 2 The design principle is to meet the interface size requirements of the satellite wrapping separation mechanism; the design principle of the front-end dual-satellite interface distance D is to meet the maximum circumferential layout size requirements of the dual satellites.

[0042] The layup of each component follows the principle of continuous laying, and its design parameters mainly include two items: the number of layups n and the layup sequence. After the configuration design parameters of the flying wing composite adapter for parallel dual satellite launch are determined, the determination of the above composite layup parameters should be based on the principle of meeting the strength and stiffness index requirements of the flying wing composite adapter for parallel dual satellite launch.

[0043] like Figure 1As shown, the flying wing-type composite material adapter (11) for parallel double-satellite launch described in the present invention has a front end for layout and installation of the parallel double-satellite (10), and a rear end for connection with the carrier (12). Due to the configuration characteristics, the height dimension of the structure is greatly compressed, which increases the satellite layout space; the flying wing-type composite material adapter (11) for parallel double-satellite launch is an independent section, which realizes the decoupling of assembly with the carrier (12), and significantly improves the convenience of assembly; the flying wing-type composite material adapter for parallel double-satellite launch has a reduced structural complexity, which promotes the application of high-performance, lightweight fiber-reinforced composite materials, and improves the lightweight benefits of launch missions. The flying wing-type composite material adapter for parallel double-satellite launch has the advantages of compact configuration, good assembly convenience, and light weight.

[0044] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A flying wing composite adapter for parallel dual-satellite launch, characterized in that: The flying wing-shaped composite material adapter for parallel double-satellite launch adopts an integrated flying wing-shaped flat configuration, including a structural frame, an upper skin (6), and a lower skin (7) assembled to form the flying wing-shaped composite material adapter for parallel double-satellite launch; The structural framework of the flying wing composite material adapter assembled to form a parallel dual-satellite launch comprises a load-bearing frame (1), a connecting plate (2), a longitudinal beam (3), a cross beam (4), and a side plate (5); The components are all laid out in one piece and cured and formed separately using lightweight fiber-reinforced composite materials.

2. The flying wing composite adapter for parallel dual-satellite launch according to claim 1, characterized in that: The load-bearing frame (1) comprises a double oblique conical surface (8) and a double longitudinal surface (9).

3. The flying wing composite adapter for parallel double satellite launch according to claim 2, characterized in that: The upper and lower ends of the double-oblique cone surface (8) are both designed with flanges; the upper flange is designed with a mechanical connection interface for mechanical connection between the adapter and the belt separation mechanism of the parallel double satellite (10); the lower flange is designed with a mechanical connection interface for mechanical connection between the flying wing-type composite material adapter for parallel double satellite launch and the carrier (12).

4. The flying wing composite adapter for parallel double satellite launch according to claim 2, characterized in that: The upper and lower ends of the double longitudinal surfaces (9) are both designed with flanges; the upper flange is designed to be glued to the upper skin (6); and the lower flange is designed to be glued to the lower skin (7).

5. The flying wing composite material adapter for parallel double satellite launch according to claim 1, characterized in that: The longitudinal beam (3) is an integral structure, and its cross section is an "I"-shaped cross section.

6. The flying wing composite adapter for parallel double satellite launch according to claim 1, characterized in that: The crossbeam (4) is a multi-segmented structure, and the cross-section is an "I"-shaped cross-section.

7. The flying wing composite adapter for parallel double satellite launch according to claim 1, characterized in that: The connecting plate (2) adopts a box-shaped structure and is provided with flanges on all sides; the upper flange is provided with a mechanical connection interface for connecting a parallel double-star belt separation mechanism; the flanges on the left and right sides are connected to the load-bearing frame (1) and the crossbeam (4) by means of a mixture of rubber and screws.

8. The flying wing composite adapter for parallel double satellite launch according to claim 1, characterized in that: The side panel (5) adopts a box-shaped structure and is provided with flanges on all sides; the flanges at the upper ends of the side panels (5) are used for gluing the upper skin (6), and the flanges at the lower ends of the side panels (5) are gluing the lower skin (7); the flanges on both sides of the side panels (5) are connected to the load-bearing frame (1) and the crossbeam (4) by a mixture of glue and screws.

9. The flying wing composite adapter for parallel double satellite launch according to claim 1, characterized in that: The upper skin (6) and the lower skin (7) both adopt a planar structure.

10. The flying wing composite material adapter for parallel double satellite launch according to claim 1, characterized in that: The number and layout of the longitudinal beams (3) and the transverse beams (4) are adjusted according to the strength and stiffness indicators of the flying wing-shaped composite material adapter for parallel dual-satellite launch.

Images